Patent Application
20220055778
The invention relates to the area of space science and space transportation, in particular, to the area of commercial exploitation of outer space, and, namely—to the structure of multiple-mission geospatial transportation complex and method of operation thereof, based on the principle of non-rocket planet surface to the planned circular orbit payload insertion. Its intended purpose of use is to solve the set of geospatial problems in industrial-scale volumes, for instance, for the purpose of relocation of ecologically harmful portion of earth-based manufacturing into near space and non-rocket space industrialization, as well as—stabilization of global climate and carrying out of R&D, special-purpose, touristic and other types of works and services in outer space.
Russian scientist, the pioneer of cosmonautics, K. E. Tsiolkovsky, who was first to lay theoretical foundation for manned spaceflight, elaborated and justified rocket reaction principle. He highlighted the need to search for and create alternative methods and equipment to launch humans into space and set up extraterrestrial orbital space stations, as intermediate (support) bases in development of interplanetary communications and colonization in the form of human settlements in space. In his studies, K. E. Tsiolkovsky presents a profound assessment of the number of systems of possible transportation space structures developed by him, including Space Elevator, Equatorial Tower and Equatorial Circular Train.
The structure has been also known as proposed by Yu Artsutanov' cosmic (space) elevator as method for delivery of cargos to geostationary orbit. However, the design of cosmic elevator, with the overall viability of such approach to the issue of replacement of jet rocket thrust during payload insertion into circumplanetary orbit, has a sufficiently high unit cost of its delivery, with the required extremely high strength of materials of the self-bearing elevator cable, length around 40 thousand km, which are capable to withstand dead load and load due to massive counterweight.
The system of such space vehicle, named Space Fountain, is known: a structure for delivering cargos to orbit. Space Fountain is an alternative to space elevator, and as compared to the design thereof, Space Fountain is an extremely tall hollow tower with its cavity filled with special granular substance. This substance, after transferring kinetic energy to it, moves rapidly up from the base of the tower and transfers this energy to the top thereof, after which it falls back to the base of the tower under the influence of gravity. Cargos along the Space Fountain can be lifted in two ways: with the assistance of special systems like elevator in buildings, or with the stream of granules (pellets).
Unlike the traditional space elevator, Space Fountain can be built near the planet's surface. The tower will be capable of lifting all the payload needed for its own construction. Space Fountain can be built and will function successfully even on celestial bodies with very low gravity, such as the Moon, Mercury.
Drawback of this technical solution is that Space Fountain is active-use structure and therefore requires constant consumption of significant amount of energy to maintain its existence and can only lift cargo via assigned altitude rather than put payload into circular orbit at the first cosmic velocity.
The Slingatron of Tidman is known. Slingatron—space slingshot—features the same principle working as in a traditional slingshot. Slingatron is based on a large spiral tube, inside which acceleration of a small capsule with microsatellite happens. The spiral tube is fixed on system of rotating levers with counterweights that drive powerful electric motors.
Disadvantage of such technical solution is rather high specific cost of delivering payload to the orbit of a planet with a dense atmosphere and high overloads (accelerations) acting on the cargo put into space.
A space vehicle such as Space Gun is also known, a method of launching an object into outer space with a huge gun, of a shooting or electromagnetic type, is also known. It refers to rocket-free methods of placing objects into orbit.
Excessive launch overloads experienced by the “projectile” mean that the space gun will not be able to safely orbit humans or fragile objects, but will be limited to delivering increased strength cargo. The exception are such electromagnetic guns, as Gauss cannon and railgun, with which the acceleration time is theoretically unlimited and there is no barrel creating an extremely high force of air resistance on the nose of the “projectile”. The resistance of atmosphere creates additional difficulties in controlling the flight path of the object already released from the gun. At very large barrel lengths (about 2000 km), a human-acceptable overload can be obtained. In this case, it is better to position the barrel not vertically, but horizontally, until the half-barrel reaches the boundary of space (100 km altitude). If the space gun barrel reaches the upper stratosphere layers, where the air is less dense, these problems are partially solved. If acceptable solutions to these main problems are found, the space gun can allow cargo to enter outer space at an unprecedented low price (about $550 per kilogram).
There is a less well-known project to bring an object into outer space, which functions in the same way as space elevator, but does not need materials ahead of the modern state of the art. It's called Lofstrom loop. The construction of this loop is based on a conductive cord closed in a ring and drawn to a huge length inside a vacuum tube. To prevent contact of cord with tube walls, it is suspended therein by means of magnetic levitation.
With the help of a powerful linear electromagnetic motor located on the ground, the loop cord is accelerated to a velocity of 14-15 km/sec inside the tube. The moment of inertia of the rotating cord tends to give the structure a circular shape, however, this is hampered by the fasteners, which grip the part of the tube (in which the cord moves) located on Earth. But the other part—unrestrained, under the influence of the energy of the rotating cord, rises upwards. The huge energy accumulated in the cord rotating on the magnetic suspension, lifts the entire structure until a grand system appears—a loop, one portion of which lies on the ground, and another is raised to altitude of 80 kilometers and held on that level by rope fixtures. In order to launch the cargo into space, it is lifted to altitude of about 80 km and installed at one of ends of a multi-kilometer portion of the loop running parallel to Earth. Magnetic fields created by the acceleration unit interact with the magnetic field in the conductor and, due to the occurring eddy currents, accelerate the cargo until it has gained the required orbital velocity. After that, with the help of a small rocket engine, the cargo is separated from Lofstrom loop and enters the required orbit.
The disadvantage of such a design is the unpredictability of its electric discharge interaction with the ionosphere, as well as—in the process of electric closure of the ionosphere with the Earth's surface.
The Space Bridge (SB) is also known for its design of rocket-free space transportation systems. “SB” is the design of astroengineering installation for non-rocket method of inserting cargo into planetary orbit with the use of ring which becomes weightless by rotation around the planet's equator. “SB” represents a huge trestle (overpass) made in the form of an annular body with an endless flywheel belt placed therein with the feasibility of moving at space velocities, shrouding the Earth along the equator. Part of the trestle lies on the surface of the planet, and the other part extends into space. Along the trestle the cargo is taken into and back from space. The trestle is held suspended by centrifugal forces created therein by endless flywheel belt. Compared to the space elevator, “SB” has a significant advantage—stresses in its design are by an order less than those of the space elevator, and are quite bearable by existing structural materials.
The disadvantage of such a design is also the unpredictability of its electric discharge interaction with the ionosphere, as well as—in the process of electric closure of the ionosphere with the Earth's surface.
Earth-Moon Complex (EMC) is known, which comprises Earth-space lift and Earth-Moon module. Earth-space lift is made in form of retractable cylindrical sections having screws with hoops (collars) stabilizing vertical lift and mounted vertically in ground in reinforced concrete housing. The housing also has tanks filled with liquefied natural gas with high-pressure chambers supplying high pressure of gases and steam to the lower part of lifting cylinders. Earth-Moon module has cylindrical shape and is equipped with technical compartments, cargo elevator with lifting shock-absorbing pillar and movable supports.
The drawback of such design is the catastrophic consequences in case of earthquake, skew in one of the telescopic supports during cargo lifting, atmospheric effects on the space lift which features huge windage, and, in addition, the unpredictability of electric discharge interaction of “EMC” with the ionosphere, as well as—in the process of electric closure of the ionosphere with the Earth's surface. In addition, such a compression structure, with large altitude and relatively small transverse dimensions, will lose stability.
There is known magneto-plasma method of inserting payload in geostationary orbit, according to which a capsule with payload and passengers is isolated by magnetic field and ejected by plasma flow formed with the help of plasmatrons. Hereby, quenching effect on accelerating plasma from the side of Earth's atmosphere is eliminated by means of artificial vortex-whirl, which is created by gas-guiding elements of platform, using plasma, which flows from peripheral plasmatrons. Plasma flow ejecting capsule is directed inside and along axis of this vortex-whirl.
A disadvantage of such a method of putting payloads into Earth orbit is the unacceptable threat of destruction of the planet's protective ozone layer and the unpredictability of the results of the electric discharge interaction of the plasma whirl with the Earth's ionosphere.
A model of orbital station is known, comprising mockup of annular orbital station, which encircles the planet and is made in the form of an extensible toroid-shape shell, with which solenoids are fastened to, electrically connected to power source and interacting with a toroidal movable core of variable perimeter.
The disadvantage of such installation is the absence of cargo compartments and, as a result, the inability to perform a real task of delivering payload into space.
Accepted as a prototype, a general planetary vehicle by Yunitski is known, which represents a circular toroid-shape bearing structure, ringing around the planet and its center of mass, and comprising a vacuum sealed hollow body with axis symmetrically located inside thereof, at least two flywheels in the form of endless belts, and with electromagnetic suspension systems contactlessly mounted thereon on; equipped with electromagnetic drives connected through control system and a communication system of electric energy with power supply source; whereby the hollow body of flywheels is arranged inside the shell aligned therewith, also coaxially positioned within the female outer casing, the casing being assembled into a continuous chain of rigid units, performed with feasibility of mutual longitudinal movement, whereas space free of rigid units is used to form transportation compartments, whereby that said casing is furnished with locks to be secured-detached on launch overpass supports arranged along planet perimeter along the equator.
Disadvantages of the above planetary vehicle are as follows: uncertainty of specific characteristics and parameters of device elements implementation, their interaction and interconnection.
At the heart of the claimed invention lies the task of tackling the following technical tasks:
Technical goals according to the claimed invention are attained with use of general planetary geospatial transportation complex by Yunitski, which comprises general planetary vehicle encircling the planet along the line of the planet surface cross-section by the plane parallel to plane of the equator, fastened, according to the first variant (embodiment) of the claimed invention, on launch overpass of altitude h, m, defined by the ratio:
10−7≤h/R≤10−4, (1)
where R, m,—radius of planet in plane of arranging launch overpass,
and representing a linear bearing structure encircling the planet and having length L0, m, comprising pressure hull with at least two vacuum channels, ringing around the planet, in the first one of which the first endless planet-encircling linear flywheel is located, and in the second one—the second endless planet-encircling linear flywheel is located, whereas the first linear flywheel and the second linear flywheel are contactlessly positioned in relation to the walls of the corresponding vacuum channels and equipped with systems of magnetic and/or electromagnetic suspension and linear electromagnetic drives of the first flywheel and the second flywheel, respectively, configured to accelerate linear flywheels to velocity of V0, m/sec, defined by the ratio:
1.1≤V0/Veh≤5, (2)
where Veh, m/sec,—first cosmic velocity at altitude h, m,
linear bearing structure is equipped with transportation compartments and configured to be elongated without uniformity loss, defined by the ratio:
1.01≤LH/L0≤1.25, (3)
where LH, m,—length of linear bearing structure at circular orbit of altitude H, m, and linear flywheels having masses m1 and m2, kg, defined by the ratio:
0.1≤m1/m2≤10, (4)
whereas drives of linear flywheels are connected with power supply source via control and communication systems.
The specified result is achieved also thanks to the general planetary geospatial transportation complex by Yunitski, which includes general planetary vehicle encircling the planet along the line of the planet surface cross-section by the plane parallel to plane of the equator, fastened, according to the second variant (embodiment) of the claimed invention, in liquid ocean at launch depth hv, m, defined by the ratio:
10−7≤hv/Rv≤10−4, (5)
where Rv, m,—radius of planet in plane of arranging general planetary vehicle in liquid ocean, and representing a linear bearing structure encircling the planet and having length L0, m, comprising pressure hull with at least two vacuum channels, ringing around the planet, in the first one of which the first endless planet-encircling linear flywheel is located, and in the second one—the second endless planet-encircling linear flywheel is located, whereas the first linear flywheel and the second linear flywheel are contactlessly positioned in relation to the walls of the corresponding vacuum channels and equipped with systems of magnetic and/or electromagnetic suspension and linear electromagnetic drives of the first flywheel and the second flywheel, respectively, configured to accelerate linear flywheels to velocity of V0, m/sec, defined by the ratio:
1.1≤V0/Vvh≤5, (6)
where Vvh, m/sec,—first cosmic velocity at launch depth hv, m,
linear bearing structure is equipped with transportation compartments and configured to be elongated without uniformity loss, defined by the ratio (3):
1.01≤LH/L0≤1.25;
and linear flywheels have masses m1 and m2, kg, defined by the ratio (4):
0.1≤m1/m2≤10;
whereby general planetary vehicle is performed with launch density ρ1v, kg/m3, defined by the ratio:
0.5≤ρ2/ρ1v≤2, (7)
where ρ2, kg/m3,—density of liquid of planetary ocean at launch depth hv, m,
whereas drives of linear flywheels are connected with power supply source via control and communication systems.
Achieving the given technical result is secured also by general planetary geospatial transportation complex by Yunitski comprising general planetary vehicle encircling the planet along the line of the planet surface cross-section by the plane parallel to plane of the equator, fastened, according to the third variant (embodiment) of the claimed invention, in gaseous environment of planetary atmosphere at launch altitude hl, m, defined by the ratio:
10−7≤hl/Rl≤10−2, (8)
where Rl, m,—radius of planet in plane of arranging general planetary vehicle in gaseous environment of planetary atmosphere,
and representing a linear bearing structure encircling the planet and having length L0, m, comprising pressure hull with at least two vacuum channels, ringing around the planet, in the first one of which the first endless planet-encircling linear flywheel is located, and in the second one—the second endless planet-encircling linear flywheel is located, whereas the first linear flywheel and the second linear flywheel are contactlessly positioned in relation to the walls of the corresponding vacuum channels and equipped with systems of magnetic and/or electromagnetic suspension and linear electromagnetic drives of the first flywheel and the second flywheel, respectively, configured to accelerate linear flywheels to velocity of V0, m/sec, defined by the ratio:
1.1≤V0/Vlh≤5, (9)
where Vlh, m/sec,—first cosmic velocity at launch altitude hl, m,
linear bearing structure is equipped with transportation compartments and configured to be elongated without uniformity loss, defined by the ratio (3):
1.01≤LH/L0≤1.25;
and linear flywheels have masses m1 and m2, kg, defined by the ratio (4):
0.1≤m1/m2≤10;
whereby general planetary vehicle is performed with launch density ρ1l, kg/m3, defined by the ratio:
0.1≤ρ3/ρ1l≤2, (10)
where ρ3, kg/m3,—density of the liquid and/or gaseous environment of planetary atmosphere at launch altitude hl, m,
whereas drives of linear flywheels are connected with power supply source via control and communication systems.
Achieving the defined goals according to any of the three variants of the present invention is guaranteed also by the fact that transportation compartments may be embodied both inside the body of linear bearing structure, or fastened outside thereupon.
Achieving the defined goals according to any of the three variants of the present invention is guaranteed also by the fact that general planetary vehicle is equipped by linear ballast system, covering the planet and uniformly loaded along its entire length with liquid and/or gaseous ballast.
General planetary geospatial transportation complex by Yunitski, according to any of the three variants of the present invention, may be embodied in such way that linear bearing structure of general planetary vehicle is made from elastically deformable material with modulus of elasticity E, Pa, within the following range:
108≤E≤5×1011 (11).
General planetary geospatial transportation complex by Yunitski, according to any of the three variants of the present invention, may be embodied in such way that linear bearing structure is embodied as telescopically interconnected units.
General planetary geospatial transportation complex by Yunitski, according to any of the three variants of the present invention, may be embodied in such way that linear bearing structure is embodied as units interconnected by bellows.
General planetary geospatial transportation complex by Yunitski, according to the second variant of the present invention, may be embodied in such way that launch density ρ1v, kg/m3, of general planetary vehicle is secured by pontoon means, responsible for fastening linear bearing structure in liquid of ocean at depth hv, m.
General planetary geospatial transportation complex by Yunitski, according to the third variant of the present invention, may be embodied in such way that launch density ρ1l, kg/m3, of general planetary vehicle is secured by balloons, responsible for fastening linear bearing structure in gaseous environment at altitude hl, m.
Achieving the defined goals according to any of the three variants of the present invention is guaranteed also by the fact that the general planetary geospatial transportation complex by Yunitski is equipped by fixing locks of linear bearing structure at launch altitude h, m, or hv, m, or hl, m, respectively in elevated structure (overpass), in liquid of ocean or in gaseous environment of planet, along the entire length L0, m, thereof.
Achieving the defined goals is also secured by the method for planet surface to circular orbit payload insertion, according to which:
The specified result is achieved also due to the fact that linear force N1, N/m, of acceleration and/or deceleration of linear flywheels is applied uniformly along entire length thereof via linear electromagnetic drives.
The specified result is guaranteed also due to the fact that during operation of general planetary vehicle, along the entire length of its linear flywheels, linear force N1, N/m, of their acceleration and/or deceleration, is regulated with regard to the rated value of that linear force N0, N/m, within the range determined by the ratio:
0.9≤N1/N0≤1.1 (12).
Attaining the given task is secured by the fact that, as part of payload, in the amount of 0.1-10% of its mass m3, kg, liquid and/or gaseous ballast uniformly loaded along the entire length L0, m, of linear bearing structure, is used.
The specified result is achieved also due to the fact that, as ballast, ecologically friendly to planet Earth substances and materials are used: water and/or compressed, and/or liquid air and/or oxygen, and/or nitrogen.
Additional subject of the present invention is use of ballast during lifting (ascent) of general planetary vehicle, according to technical solution according to any of claims 11, 12 and 13, onto circular orbit of altitude H, m, to restore the ozone hole, improve weather and stabilize climate on Earth as a result of its spraying in planetary atmosphere.
The essence of the present invention is clarified with use of drawings,
Item numbers on drawings:
1—planet 1;
2—section line of planet surface received by plane parallel to plane of the equator;
3—plane parallel to plane of the equator;
4—plane of the equator;
4.1—the equator of planet;
5—general planetary vehicle (GPV);
6—launch overpass;
6.1—pillars—supports;
6.2—superstructures;
6.3—network passages;
6.4—floating support;
6.5—counterweight;
6.6—tension cable;
7—linear bearing structure of GPV, encircling the planet;
8—pressure hull of GPV;
9—vacuum channel of linear bearing structure of GPV;
9.1—first vacuum channel;
9.2—second vacuum channel;
10—endless linear flywheel, encircling the planet;
10.1—first endless linear flywheel;
10.2—second endless linear flywheel;
10.3—closed multilayer endless flywheel belt;
11—system of magnetic and/or electromagnetic suspension of endless linear flywheel;
11.1—system of magnetic and/or electromagnetic suspension of first endless linear flywheel;
11.2—system of magnetic and/or electromagnetic suspension of second endless linear flywheel;
12—system of linear electromagnetic drive of endless linear flywheel;
12.1—system of linear electromagnetic drive of first endless linear flywheel;
12.2—system of linear electromagnetic drive of second endless linear flywheel;
13—planned circular orbit;
14—payload of GPV;
15—transportation compartments of GPV;
15.1—built-in transportation compartments;
15.2—detachable (mounted) transportation compartments;
16—linear power supply source;
17—control system;
18—energy communications system;
19—locks for fixing of linear bearing structure;
20—liquid of planetary ocean;
21—planetary ocean bed;
21.1—anchoring block on planetary ocean bed;
21.2—anchoring block on hard surface of planet;
22—pontoon means;
23—gaseous environment of planetary atmosphere;
24—balloon;
25—linear ballast system, covering the planet;
26—ballast;
27—unit of pressure hull of GPV;
28—telescopic connection of units of pressure hull of GPV;
29—bellow;
30—orbital circular (ringing around planet) complex.
h, m—altitude of launch overpass;
H, m—altitude of planned circular orbit;
L0, m—length of linear bearing structure;
R, m—radius of planet in plane of arranging launch overpass;
Veh, m/sec—first cosmic velocity at altitude h, m;
V1H, m/sec—first cosmic velocity at altitude H, m
hv, m—launch depth of GPV at launch in liquid of planetary ocean;
Rv, m—radius of planet in plane of arranging GPV in liquid of planetary ocean;
Vvh, m/sec—first cosmic velocity at launch depth hv, m;
ρ1v, kg/m3—launch density of GPV at launch depth hv, m;
ρ2, kg/m3—density of liquid of planetary ocean at launch depth hv, m;
hl, m—launch altitude of GPV at launch in gaseous environment of planetary atmosphere;
Rl, m—radius of planet in plane of arranging GPV in gaseous environment of planetary atmosphere;
Vlh, m/sec—first cosmic velocity at launch altitude hl, m;
ρ1l, kg/m3—launch density of GPV at launch altitude hl, m;
ρ3, kg/m3—density of gaseous environment of planetary atmosphere at launch altitude hl, m;
V0, m/sec—acceleration rate of one of linear flywheels;
P, N,—centrifugal force;
N, N—force of longitudinal stretching of GPV;
rp,—reference radius of orbit of one of linear flywheels;
Re, m,—radius of the equator of planet 1;
φ, rps,—angular velocity of one of linear flywheels;
{dot over (r)}p, m/sec,—radial velocity of GPV;
φ, °,—turning angle of orbit of one of linear flywheels;
δ, °,—center angle;
F1, N, and F2, N,—elastic forces, acting on ends of a member corresponding to arc with center angle δ, °, of linear bearing structure of GPV;
F, N,—equivalent elastic force in element corresponding to arc with center angle δ, °, of linear bearing structure of GPV;
G, N,—planetary gravity force;
Q, N,—drag force of gaseous environment of planetary atmosphere;
X and Y—x-axis and y-axis, respectively.
The essence of the claimed invention is further presented in a closer detail as follows.
The claimed general planetary geospatial transportation complex by Yunitski (see
10−7≤h/R≤10−4, (1)
where R, m,—radius of planet 1 in plane 3 of arranging launch overpass 6.
Alternatively, specific launch overpass 6 can be constructed according to any existing technologies of building overpasses, for example, manufactured according to SkyWay technology, which is based on use, as bearing structure, of continuous prestressed track structure, positioned along the equator 4.1. Altitude of launch overpass 6 depending on relief varies from several meters to several hundred meters and may include (see
Optimal altitude h, m, of launch overpass 6 is the value determined by the ratio (1). Under these conditions, the costs of manufacturing, maintenance and operation of general planetary vehicle 5 are minimized.
Decrease in altitude h, m, of launch overpass 6 below the lower boundary of value h/R=10−7, defined by the ratio (1), i.e. at h/R<10−7, does not allow to meet requirements on reduction of costs for construction of launch overpass 6 while adhering to the design assignment of general planetary vehicle 5, whereas increase of its altitude h, m, above the upper boundary of value h/R=10−4, defined by the ratio (1), i.e. at h/R>10−4, does not allow to reach maximum altitude of positioning launch overpass 5 above surface of planet 1 (see
Hereby, general planetary vehicle 5 (see
By linear flywheel 10, is meant a seizing planet 1 giant annular closed rim in the form of open torus rotatably mounted around the joint with planet 1 center of mass. Linear flywheel 10 may be realized in various technical embodiments, for instance, as closed multilayer endless belt 10.3, which represents a kind of rotor of linear electromagnetic motor with linear electromagnetic drive (see
Both linear flywheels 10.1 and 10.2 are contactlessly positioned in relation to walls of the relevant vacuum channel 9.1 or 9.2, and equipped with the systems of magnetic and/or electromagnetic suspension 11, respectively 11.1 and 11.2, and linear electromagnetic drives 12, accordingly, 12.1 and 12.2. Hereby, systems of magnetic and/or electromagnetic suspension 11 and linear electromagnetic drives 12 are configured to accelerate linear flywheels 10 up to velocity V0, m/sec, determined by the ratio:
1.1≤V0/Veh≤5, (2)
where Veh, m/sec,—first cosmic velocity at altitude h, m.
Acceleration of at least one of linear flywheels 10 up to velocity V0, m/sec, determined from ratio (2), makes it possible to achieve, at minimum required energy consumption, balancing of attraction force from planet towards general planetary vehicle 5 and its subsequent launch into space with lifting to planned circular orbit 13 of altitude H, m, and reaching of first cosmic (circumferential around planet 1) velocity V1H, m/sec, by pressure hull 8 of linear bearing structure 7 of general planetary vehicle 5 at planned circular orbit 13 of altitude H, m.
Thus, the optimum velocity V0, m/sec, of acceleration of at least one of linear flywheels 10 to provide accumulation of kinetic energy and the launch amount (angular momentum) of motion sufficient to launch general planetary vehicle 5 and ensure it enters space into planned circular orbit 13 with payload 14 (see
Reduction in velocity V0, m/sec, of acceleration of at least one of linear flywheels 10 below the lower boundary V0/Veh=1.1, determined by the ratio (2), i.e. at V0/Veh<1.1, does not allow to meet the requirements of stable and reliable operation of general planetary vehicle 5 at launch, in dense atmosphere, as well as limits the altitude of cosmic orbit on which general planetary vehicle 5 can be inserted, as well as the circumferential (orbital) velocity of linear bearing structure 7, and, correspondingly, mass of payload 14—passengers and cargoes—inserted into planned circular orbit 13 (see
Increase in velocity V0, m/sec, of acceleration of at least one of linear flywheels 10 above the upper boundary of value V0/Veh=5, determined by the ratio (2), that is, at V0/Veh>5, leads to unjustified increase in energy costs required to ensure the operability of general planetary vehicle 5 in accordance with the design assignment. This is due to excess kinetic energy of flywheels 10 at launch, which can lead to the destruction of linear structure 7 due to its excessive elongation (increase in the diameter of ring encircling planet 1) in the process of entering a critically high orbit, that is, due to excessive increase in altitude of cosmic orbit onto which general planetary vehicle 5 and, accordingly, the payload 14 can be inserted.
Linear bearing structure 7 is equipped with transportation compartments 15, both built-in—15.1, and detachable (mounted)—15.2 (see
1.01≤LH/L0≤1.25, (3)
where LH, m,—length of linear bearing structure 7 on planned circular orbit 13 of altitude H, m.
The range of elastic extension of linear bearing structure 7 without loss of continuity indicated in the ratio (3) is due to the range of change in length L0, m of linear bearing structure 7 in launch state and length LH, m, of this linear bearing structure 7 on planned circular orbit 13 of altitude H,
Embodiment of linear bearing structure 7 and, accordingly, of general planetary vehicle 5 with possibility of their elastic extension without loss of continuity with values of ratio (3) LH/L0<1.01, does not allow to put linear bearing structure 7 to planned circular orbit 13 of assigned altitude H,
In its turn, linear flywheels 10, respectively, 10.1 and 10.2, have corresponding masses m1 and m2, kg, defined from the ratio:
0.1≤m1/m2≤10; (4)
Embodiment of linear flywheels 10.1 and 10.2 with corresponding masses m1m2, kg, specified in the ratio (4), is conditioned by the modes of realization of processes of launch into space and return landing on planet 1 of general planetary vehicle 5 with use of launch kinetic energy accumulated therein and launch amount (angular momentum) of motion.
Optimal for carrying out launch of general planetary vehicle 5 into space on planned circular orbit 13 of assigned altitude H, m, and ensuring all stages of its motion, including launch, lifting, hovering on planned circular orbit 13 with the planned circumferential (orbital) velocity V1H, m/sec, and return to planet 1, appears to be embodiment of linear flywheels 10.1 and 10.2 with corresponding masses m1 and m2, kg, indicated in the ratio (4).
Embodiment of linear flywheels 10.1 and 10.2 with masses m1 and m2, kg, ratio of which is less than 0.1 or more than 10, leads either to reduction in efficiency of general-planet vehicle 5 as a whole, or to significant and impractical increase of velocity (rotation) of at least one of linear flywheels at the moment of launch of general planetary vehicle 5 from planet 1, which causes considerable complication and increase of cost of realization of the entire project on transportation complex. In addition, this will lead to additional losses of significant portion of energy when it is switched from one flywheel, which is slowed, with its drive is operating in generator mode, to another flywheel, which at this time accelerates in counter-direction.
Systems 11 of magnetic and/or electromagnetic suspension and drives 12 of linear flywheels 10 along their entire length L0 are connected to linear power supply source 16, embodied, for example, in the form of linear (running along linear bearing structure 7) power supply system, capable of including a variety of possible combinations of generating power systems available on planet 1, through control system 17 and power communication system 18 (see
General planetary vehicle 5 is also equipped with fixing locks 19 for fastening linear bearing structure 7 to the launch overpass 6 along the entire length L0, m, which automatically operate and release linear bearing structure 7 at the moment of its launch from planet 1 and fix the position of linear bearing structure 7 of general planetary vehicle 5 in the initial position when it returns to planet 1 (see
The above mentioned result is also achieved by the fact that the claimed general planetary geospatial transportation complex by Yunitski (see
10−7≤hv/Rv≤10−4, (5)
where Rv, m,—radius of planet 1 in plane 3 of arranging general planetary vehicle 5 in liquid 20 of ocean of planet 1.
Location of general planetary vehicle 5 in liquid 20 of ocean of planet 1 at launch depth hv, m, indicated in the ratio (5) is due to optimization of technology for construction and maintenance of general planetary vehicle 5 at its launch from liquid 20 of ocean.
Optimal value of launch depth hv, m, of immersion of general planetary vehicle 5 into liquid 20 of planet 1 ocean is the value determined by the ratio (5). Under these conditions, the manufacturing, maintenance and operation costs of general planetary vehicle 5 are minimized and buoyancy of liquid 20 is maximized.
Decrease in launch depth hv, m, of submerging general planetary vehicle 5, below the lower boundary of the ratio (5) hv/Rv=10−7, that is, when it will have value lower than 10−7, does not allow to eliminate possible negative impact on operation of general planetary vehicle 5 as a result of possible atmospheric wind, seismicity, and other natural factors that may cause, inter alia, roughness of liquid 20 on the ocean surface, and increase of its value above the upper boundary, determined by the ratio (5), of the ratio (5) hv/Rv=10−4, i.e. when it will have value above 10−4, does not allow to effectively perform, at such substantial depth, high-tech maintenance of general planetary vehicle 5 and meet the requirement to reduce the cost of its operation.
At the same time, similar to the first variant of the claimed invention, it is characteristic that general planetary vehicle 5 is, in this case, represents a linear bearing structure 7 of length L0, m, encircling the planet 1, comprising pressure hull 8 with at least two vacuum channels 9, respectively, 9.1 and 9.2, also encircling planet 1, with endless linear flywheels 10 fastened therein. Hereby, first linear flywheel 10.1 is arranged in first vacuum channel 9.1 and second linear flywheel 10.2 is arranged in second vacuum channel 9.2.
By linear flywheel 10, as in the first embodiment of the invention, is meant a seizing planet 1 giant annular closed rim in the form of open torus rotatably mounted around the joint with planet 1 center of mass.
Both linear flywheels 10.1 and 10.2 are contactlessly positioned in relation to walls of the relevant vacuum channel 9.1 or 9.2, and equipped with the systems of magnetic and/or electromagnetic suspension 11, respectively 11.1 and 11.2, and linear electromagnetic drives 12, accordingly, 12.1 and 12.2, of first and second linear flywheels 10.1 and 10.2, respectively (see
1.1≤V0/Vvh≤5, (6)
where Vvh, m/sec,—first cosmic velocity at launch depth hv, m.
Acceleration of at least one of linear flywheels 10 up to velocity V0, m/sec, determined from ratio (6), makes it possible to achieve balancing of attraction force from planet 1 towards general planetary vehicle 5 and its launch into space at minimum required energy consumption.
Thus, the optimum velocity V0, m/sec, of acceleration of at least one of linear flywheels 10 to provide accumulation of kinetic energy and the launch amount (angular momentum) of motion sufficient to launch general planetary vehicle 5 and ensure it enters space into planned circular orbit 13 from thickness of liquid 20 of ocean of planet 1, is a value determined by the ratio (6). Under the specified limits, energy costs necessary to ensure the operability of general planetary vehicle 5 are minimized.
Reduction in velocity V0, m/sec, of acceleration of at least one of linear flywheels 10 below the lower boundary V0/Vvh=1.1, determined by the ratio (6), i.e. at V0/Vvh<1.1, does not allow to meet the requirements of stable and reliable operation of general planetary vehicle 5 at launch, in thickness of liquid 20, in dense atmosphere, as well as limits the altitude of cosmic orbit on which general planetary vehicle 5 can be inserted, as well as the circumferential (orbital) velocity V1H, m/sec, of linear bearing structure 7.
Increase in velocity V0, m/sec, of acceleration of at least one of linear flywheels 10 above the upper boundary V0/Vvh=5, determined by the ratio (6), i.e. at V0/Vvh>5, leads to unjustified hike in energy costs required to ensure the operability of general planetary vehicle 5 according to the design assignment and excessively increases altitude H, m, of planned circular orbit 13.
Linear bearing structure 7, similar to the first embodiment of the invention, is also provided (see
1.01≤LH/L0≤1.25;
Substantiation of the range of elastic extension of linear bearing structure 7 without loss of continuity indicated in the ratio (3) is similar to the justification of this range given as such for the first embodiment and due to the range of change of length L0, m, of linear bearing structure 7 in launch state at launch depth hv, m, and length LH, m, of this linear bearing structure 7 on planned circular orbit 13 of altitude H,
In turn, linear flywheels 10, respectively, 10.1 and 10.2, by analogy with justification of the choice of value of their masses m1 and m2, kg, specified in the first variant of embodiment of general planetary vehicle 5, have the corresponding masses m1 and m2, kg, defined by the ratio (4):
0.1≤m1/m2≤10;
Embodiment of linear flywheels 10.1 and 10.2 with masses m1 and m2, kg, ratio of which is less than 0.1 or more than 10, leads either to reduction of efficiency of general planetary vehicle 5, or to significant and impractical increase of velocity (rotation) of at least one of linear flywheels at the moment of launch of general planetary vehicle 5 from planet 1, which leads to considerable complication and increase of cost of realization of the entire project on transportation complex.
Hereby, general planetary vehicle 5, according to the second variant of the claimed invention, is embodied with launch density ρ1v, kg/m3, defined by the ratio:
0.5≤ρ2/ρ1v≤2, (7)
where ρ2, kg/m3,—density of liquid 20 of ocean of planet 1 at launch depth hv, m.
In this case, launch density ρ1v, kg/m3, of general planetary vehicle 5 should be understood to mean the mass of the structure in unit volume of general planetary vehicle 5 in its prelaunch state at launch depth hv, m, in liquid 20 of ocean of planet 1.
Embodiment of general planetary vehicle 5 with launch density ρ1v, kg/m3, indicated in the ratio (7), is due to optimization of technology for construction and maintenance of general planetary vehicle 5 while ensuring its location in liquid 20 at assigned launch depth hv, m, in global ocean.
Optimum launch density ρ1v, kg/m3, for the second embodiment of general planetary vehicle 5 is the value determined by the ratio (7). Under these conditions, the costs of manufacturing, maintenance and operation of general planetary vehicle are minimized 5.
Reduction in launch density ρ1v, kg/m3, of general planetary vehicle 5 beyond the upper boundary of the ratio (7) ρ2/ρ1v=2, that is at ρ2/ρ1v>2, does not allow efficient use for prelaunch maintenance of general planetary vehicle 5 at assigned launch depth hv, m, due to its excessive buoyancy (floatation miss), thereby increasing the likely negative impact thereon from possible roughness on the ocean surface, whereas increasing launch density ρ1v, kg/m3, below the lower boundary of the ratio (7) ρ2/ρ1v=0.5, that is at ρ2/ρ1v<0.5, does not allow to meet requirements on reduction of costs for maintenance of general planetary vehicle 5 at a considerable depth in the ocean of planet 1 because of its insufficient (negative) buoyancy.
In this embodiment, drives 12 of linear flywheels 10 are also connected to power supply source 16 through control system 17 and power communication system 18 (see
Besides, similar to the first variant of the claimed invention, general planetary geospatial transportation complex by Yunitski, as per its second embodiment, is also equipped with fixing locks 19 (see
According to the second variant of the claimed invention, it is expedient that launch density ρ1v, kg/m3, of general planetary vehicle 5 was secured with pontoon means 22 connected with fixing locks 19 of linear bearing structure 7 installed all over its length L0, m, and which are fastened in liquid 20 of ocean and/or at its bed 21 by anchors 21.1 (see
The use of pontoon means 22 to compensate launch density ρ1v, kg/m3, of general planetary vehicle 5 up to design limits indicated in the ratio (7) makes it possible to simplify its design and increase its technological effectiveness and efficiency (see
The above result is also achieved thanks to the fact that the proposed general planetary geospatial transportation complex of Yunitski includes general planetary vehicle 5, covering planet 1 along the line 2 of surface section of planet 1 by the plane 3 parallel to the plane 4 of the equator 4.1, fixed, according to the third variant of the invention (see
10−7≤hl/Rl≤10−2, (8)
where Rl, m,—radius of planet 1 in plane 3 of arranging general planetary vehicle 5 in gaseous environment 23 of atmosphere of planet 1.
Positioning of general planetary vehicle 5 in gaseous environment 23 of atmosphere of planet 1 at launch altitude hl, m indicated in the ratio (8), is due to optimization of technology of construction and maintenance of general planetary vehicle 5 at its “atmospheric” launch.
Optimal value of launch altitude hl, m, of lifting general planetary vehicle 5 above surface of planet 1 is the value determined by the ratio (8). Under these conditions, the costs of manufacturing, maintenance and operation of general planetary vehicle 5 are minimized.
Decrease in value of launch altitude hl, m, of location of general planetary vehicle 5 above the surface of planet 1 below the lower boundary of the ratio (8) hl/Rl=10−7, that is, at hl/Rl<10−7, does not allow to reduce negative impact on operation of general planetary vehicle 5 due to inhomogeneity of surface relief of planet 1 along the launch location of linear bearing structure 7 throughout its length, and increase of its value above the upper boundary of the ratio hl/Rl=10−2, i.e. at hl/Rl>10−2, determined by the ratio (8), does not allow to effectively reduce the costs of pre-launch preparation, maintenance and loading of general planetary vehicle 5 at high altitude in more rarefied atmosphere layers of planet 1.
At the same time, according to third variant of the invention, for general planetary geospatial transportation complex by Yunitski, however, similar to both its first and second variants, it is characteristic that general planetary vehicle 5 is, in this case, represents a linear bearing structure 7 of length L0, m, encircling the planet 1, comprising pressure hull 8 with at least two vacuum channels 9, respectively, 9.1 and 9.2, also encircling planet 1, with endless linear flywheels 10 placed therein. Hereby, first linear flywheel 10.1 is arranged in first vacuum channel 9.1 and second linear flywheel 10.2 is arranged in second vacuum channel 9.2.
By linear flywheel 10, as in the first two embodiments of the invention, is meant a seizing planet 1 giant annular closed rim in the form of open torus rotatably mounted around the center of mass of planet 1.
Both linear flywheels 10.1 and 10.2 are contactlessly positioned in relation to walls of the relevant vacuum channel 9.1 or 9.2, and equipped with the systems of magnetic and/or electromagnetic suspension 11, respectively 11.1 and 11.2, and linear electromagnetic drives 12, accordingly, 12.1 and 12.2, of first and second linear flywheels 10.1 and 10.2, respectively (see
1.1≤V0/Vlh≤5, (9)
where Vlh, m/sec,—first cosmic velocity at launch altitude hl, m.
Acceleration of at least one of linear flywheels 10 up to velocity V0, m/sec, determined from ratio (9), makes it possible to achieve balancing of attraction force from planet towards general planetary vehicle 5 and its launch into space at minimum required energy consumption.
Thus, the optimum velocity V0, m/sec, of acceleration of at least one of linear flywheels 10 to provide accumulation of kinetic energy and the amount (angular momentum) of motion sufficient to launch general planetary vehicle 5 and ensure it enters space into planned circular orbit 13 from gaseous environment 23 of atmosphere of planet 1, is a value determined by the ratio (9). Under the specified limits, energy costs necessary to ensure the operability of general planetary vehicle 5 are minimized.
Reduction in velocity V0, m/sec, of acceleration of at least one of linear flywheels 10 below the lower boundary V0/Vvh=1.1, determined by the ratio (9), does not allow to meet the requirements of stable and reliable operation of general planetary vehicle 5 at launch, in dense atmosphere, and also limits the altitude of cosmic orbit on which general planetary vehicle 5 can be inserted, as well as the circumferential (orbital) velocity V1H, m/sec, of linear bearing structure 7.
Increase in velocity V0, m/sec, of acceleration of at least one of linear flywheels 10 above the upper boundary V0/Vvh=5, determined by the ratio (9), leads to unjustified hike in energy costs required to ensure the operability of general planetary vehicle 5 according to the design assignment and excessively increases altitude H, m, of planned circular orbit 13.
According to the third embodiment of the present invention, linear bearing structure 7, similar to the first two embodiments of the invention, is provided with transportation compartments 15 (see
1.01≤LH/L0≤1.25;
Substantiation of the range of elastic extension of linear bearing structure 7 without loss of continuity indicated in the ratio (3) is similar to the justification of this range given as such for the first two embodiments of the installation and due to the range of change of length L0, m, of linear bearing structure 7 in launch state (see
In turn, linear flywheels 10, respectively, 10.1 and 10.2, by analogy with justification of the choice of value of their masses m1 and m2, kg, specified in the first two variants of embodiment of general planetary vehicle 5, have the corresponding masses m1 and m2, kg, defined by the ratio (4):
0.1≤m1/m2≤10;
Embodiment of linear flywheels 10.1 and 10.2 with masses m1 and m2, kg, ratio of which is less than 0.1 or more than 10, leads either to reduction of efficiency of general planetary vehicle 5, or to significant and impractical increase of velocity (rotation) of at least one of linear flywheels at the moment of launch of general planetary vehicle 5 from planet 1, which leads to considerable complication and increase of cost of realization of the entire project on transportation complex.
Hereby, general planetary vehicle 5 is embodied with launch density ρ1l, kg/m3, determined by the ratio:
0.1≤ρ3/ρ1l≤2, (10)
where ρ3, kg/m3,—density of gaseous environment 23 of atmosphere of planet 1 at launch altitude hl
Implementation of general planetary vehicle 5 with launch density ρ1l, kg/m3, indicated in the ratio (10), determined by optimization of technology for construction and maintenance of general planetary vehicle 5 while ensuring its location in gaseous environment 23 of atmosphere of planet 1 at assigned launch altitude hl, m.
The optimum launch density ρ1l, kg/m3, for the third embodiment of general planetary vehicle 5, is value determined by the ratio (10). Under these conditions, the costs of manufacturing, maintenance and operation of general planetary vehicle 5 are minimized.
Increase in launch density ρ1l, kg/m3, of general planetary vehicle 5, beyond the lower boundary of the ratio (10) ρ3/ρ1l=0.1, that is at ρ3/ρ1l<0.1, does not allow to effectively use technical parameters of general planetary vehicle 5 for its maintenance in prelaunch state at assigned launch altitude of hl, m, in gaseous environment 23 of atmosphere of planet 1 because of complication in processes of maintenance of general planetary vehicle 5 at considerable altitude (in upper, more rarefied atmosphere layers), and decrease of launch density, ρ1l, kg/m3, beyond the upper boundary of the ratio (10) ρ3/ρ1l=2, that is, at ρ3/ρ1l>2, determined by the ratio (10), does not allow to reduce negative impact which is rendered on operation of general planetary vehicle 5 by inhomogeneity of surface relief of planet 1 along launch location of linear bearing structure 7 throughout thereof.
Furthermore, in the third embodiment, similar to the first above described two embodiments, drives 12 of linear flywheels 10 are also connected to power supply source 16 through control system 17 and power communication system 18 (see
Similar to the first two variants of the invention, general planetary geospatial transportation complex by Yunitski according to third variant, also equipped by fixing locks 19 (see
According to the third embodiment (variant) of the invention, it is advantageous that launch density, ρ1v, kg/m3, of general planetary vehicle 5 was secured, for example, with balloons 24, connected to fixing locks 19 of linear bearing structure 7 and fixed, for example, in gaseous environment 23 of atmosphere of planet 1, and/or in liquid 20 of ocean, and/or on hard surface of planet 1, respectively, on balloons 24, floating supports 6.4 and/or anchors 21.1, and/or anchors 21.2 along its entire length L0, m, of linear bearing structure 7 and performing pre-launch positioning of general planetary vehicle 5 in gaseous environment 23 of atmosphere of planet 1 at launch altitude hl
Using balloons 24 to compensate launch density ρ1l, kg/m3, of general planetary vehicle 5 to design limitations, specified in the ratio (10) will simplify its design and increase its technological efficiency and efficiency (see
For general planetary geospatial transportation complex by Yunitski according to any of the three variants of the present invention, it is distinguishable that transportation compartments 15 may be placed both inside pressure hull 8 of linear bearing structure 7, or fastened outside thereupon, correspondingly, those are built-in transportation compartments 15.1 and detachable transportation compartments 15.2 (see
Using outside detachable transportation compartments 15.2 will allow to increase efficiency and lower costs of their maintenance on stages of loading and unloading of general planetary vehicle 5.
It is advantageous to embody general planetary geospatial transportation complex by Yunitski in such a way that general planetary vehicle 5 is provided with a linear ballast system 25 covering the planet 1 and uniformly loaded along its entire length with liquid and/or gaseous ballast 26 (see
As structure of linear ballast system 25, a portion of interconnected along the entire length L0, m, transportation compartments 15 of linear bearing structure 7 of general planetary vehicle 5, can be used.
Equipping of general planetary vehicle 5 with linear ballast system 25, covering the planet 1 and uniformly loaded along its entire length with liquid and/or gaseous ballast 26, provides balancing of the whole structure and excludes its vibrations at operation during motion of general planetary vehicle 5 from launch moment to rise to planned circular orbit 13 of altitude H, m.
General planetary geospatial transportation complex by Yunitski according to any of the three variants may be embodied in such way, that linear bearing structure 7 of general planetary vehicle 5 is made elastically of elastically deformable material with modulus of elasticity E, Pa, within the following range:
108≤E≤5×1011 (11).
The range of the modulus of elasticity E, Pa is selected on the basis of strength conditions stipulated by design assignment and the possibility of providing elastic deformation of pressure hull 8 of linear bearing structure 7 without loss of continuity within the range of change of length L0, m, of linear bearing structure 7 from launch state up to its length LH, m, on planned circular orbit 13 of altitude H,
Embodiment of linear bearing structure 7 and, accordingly, of general planetary vehicle 5 as a whole, from materials with values of modulus of elasticity E, Pa, less than 108 does not allow to ensure their required strength and rigidity.
Embodiment of linear bearing structure 7 and, accordingly, of general planetary vehicle 5 as a whole with possibility of their elastic extension without loss of continuity, from materials with values of modulus of elasticity E, Pa, more than 5×1011, leads to significant increase of costs for elastic deformation of structural members of general planetary vehicle 5 and reduction of operation efficiency thereof.
Further, according to any of the three variants of the invention, general planetary geospatial transportation complex by Yunitski can be realized in such a way that pressure hull 8 of linear bearing structure 7 of general planetary vehicle 5 is embodied in the form of units 27 joined to each other by telescopic connections 28 (see
Embodiment of pressure hull 8 of linear bearing structure 7 of general planetary vehicle 5 in the form of units 27 integrated with each other along the length of telescopic connections 28 allows to reduce power consumption required to provide elastic deformation in longitudinal direction of structural members of general planetary vehicle 5 and expand the range of materials used for manufacture thereof.
Alternatively, general planetary geospatial transportation complex by Yunitski according to any of the three variants can be realized in such a way that pressure hull 8 of linear bearing structure 7 of general planetary vehicle 5 is embodied in the form of units 27 interconnected with each other by bellows 29 (see
The use of bellows 29 as structural members for interconnecting units 27 of general planetary vehicle 5 also leads to reduction in power consumption, required to ensure linear elastic deformation of structure of pressure hull 8 of general planetary vehicle 5 during its lifting to planned circular orbit 13 of altitude H, m, and increases reliability and durability of the structure as a whole while simplifying it.
In accordance with the initial technical requirements of specific design solution, the achievement of the required value of elasticity of elastically deformable linear bearing structure 7 of general planetary vehicle 5 can be embodied both with combination of the specified structural and technological solutions, and by other known and tested in the art techniques.
The above mentioned result is also achieved by the method of inserting payload from surface of planet 1 into circular orbit of altitude H, m, according to which:
First, the presence of general planetary geospatial transportation complex by Yunitski is guaranteed, including seizing the planet 1 along the line 2 of cross-section of surface of planet 1 by plane 3 parallel to the plane of the equator 4, general planetary vehicle 5 embodied according to any claims 1, 2 and 3;
General planetary vehicle 5, as noted above, is a self-supporting aircraft made in the form of a torus with cross section of up to a few meters, encircling the planet 1 in a plane 3 parallel to the plane of the equator 4. It can exit into space, overcoming the attraction of planet 1, using only the internal forces of the system, without any energetic, mechanical, chemical and other types of environmentally harmful interaction with the environment, that is, it will be extremely environmentally friendly.
Only tensile cord having infinitesimal cross sizes in relation to length (a ratio about 1:10.000.000), can be a steady self-bearing structure, hence, general planetary vehicle 5 in the longitudinal direction will be always stretched by force N, N (see
The optimal version of operation of general planetary vehicle 5, which has entered planned circular orbit 13 of altitude H, m, is the state of equilibrium, therefore, all members of its structure as a whole should be in the state of weightlessness. For this purpose, in optimal versions of operation, each linear member of general planetary vehicle 5 must have first cosmic velocity V1H, m/sec, on planned circular orbit 13 at altitude H, m.
When general planetary vehicle 5 is lifted into space (see
Prior to launch of general planetary vehicle 5, linear flywheels 10.1 and/or 10.2 should have sufficient initial kinetic energy and launch amount (kinetic momentum) of motion to provide (see
Accordingly, the kinetic energy K, J, of at least one of linear flywheels 10 required to lift general planetary vehicle 5 to planned circular orbit 13 of altitude H, m is determined by the dependence:
κ=½(rp2φ2+m0{dot over (r)}p2), (12)
where , kg,—weight of at least one of linear flywheels 10;
rp, m,—current orbit radius of at least one of linear flywheels 10;
φ, rps,—angular velocity of at least one of linear flywheels 10;
m0, kg,—mass of general planetary vehicle 5;
{dot over (r)}p, m/sec,—radial velocity of general planetary vehicle 5;
and it must be greater than the attractive force to the center of planet 1, the elastic force acting on the members of linear bearing structure 7 during lifting of general planetary vehicle 5 and the resistance force of gaseous environment 23 of atmosphere of planet 1 (see
G=m
0
gR
e
2
/r
p
2 (13)
F=2πcl(rp/Re−1) (14)
Q=k
fρ0{dot over (r)}p2 exp(−αn(rp/Re−1)) (15)
where, respectively, G, H,—attractive force of planet 1 (e.g., Earth);
g, m/sec2,—gravitational acceleration at the equator;
Re, m,—radius of the equator of the planet 1;
F, N,—elastic total force in a member of linear bearing structure 7 of general planetary vehicle 5;
c, N/m,—total rigidity of linear bearing structure 7 of general planetary vehicle 5;
l, m,—length of linear bearing structure 7 of general planetary vehicle 5 at the current orbit radius;
Q, N,—drag force of gaseous environment 23 of planetary 1 atmosphere;
kf—factor depending on shape of shell of general planetary vehicle 5;
ρo, kg/m3,—density of gaseous environment 23 of atmosphere of planet 1 on its surface;
αn—exponent degree index, which determines decreasing density of atmosphere with height.
Second, general planetary vehicle 5 is held along its entire length L0, m, on launch overpass 6 of altitude h, m, and/or in liquid 20 of ocean at launch depth hv, m, and/or in gaseous environment 23 of planetary 1 atmosphere at launch altitude hl, m, by means of fixing locks 19 of linear bearing structure 7 in the corresponding initial launch position (see
At the same time, depending on the design solution, various design versions of both locks 19 themselves and combinations of their anchoring schemes on planet 1, known in modern art, are possible.
Third—payload 14 of total mass m3, kg, including ballast 26, is placed uniformly along the entire length L0, m, of linear bearing structure 7 in transportation compartments 15;
Ballast 26 performs several important functions for operation of general planetary vehicle 5.
It provides for:
Fourth, at least one linear flywheel 10 is accelerated in the co-rotational direction regarding the planet 1 to velocity V0, m/sec, exceeding first cosmic velocity Veh, m/sec, at altitude h, m, of launch overpass 6, and/or Vvh, m/sec,—first cosmic velocity in liquid of ocean at launch depth hv, m, and/or Vlh, m/sec,—first cosmic velocity in gaseous environment of planetary atmosphere at launch altitude hl, m, by at least 10%.
At least one of linear flywheels 10 is accelerated along the corresponding vacuum channel 9, wherein that linear flywheel 10 does not experience motion resistance and is rotated around the planet 1 with an axis of rotation passing through the center of mass of planet 1. As velocity increases, at least one of linear flywheels 10 accumulates the required amount of kinetic energy K, J, the pulse (angular momentum) which is necessary for general planetary vehicle 5 to reach planned circular orbit 13 at a given orbital velocity V1H, m/sec.
Hereby, since acceleration path of linear flywheels 10 is infinite, therefore, the charging time of general planetary vehicle 5 is not limited to the necessary energy even under the condition of low power of linear electromagnetic drive 12. Efficiency of linear electromagnetic drives 12 of general planetary vehicle 5 is not less than 95%, that is, it will be about one hundred times higher than that of rocket (missile) (taking into account pre-launch and launch costs and energy losses, including for obtaining rocket fuel), energy efficiency of modern rocket carriers is less than 1%. Therefore, with the same drive capacity as heavy launch vehicle (about 100 million kilowatts), it will be possible to take into space not just tens of tons, but millions of tons of payload 14 per flight.
Various structural and operational characteristics of general planetary vehicle 5 with different combinations of weights of linear flywheels 10 are possible (with equal masses, or when one linear flywheel 10 is heavier and the other is lighter), with different launch acceleration modes of linear flywheels 10 (both linear flywheels 10 are accelerated on planet 1 either in one direction, or one flywheel in one direction, the other flywheel in the other direction), etc.
Fifth, general planetary vehicle 5 is launched by detaching along its entire length L0, m, of fixing locks 19 of linear bearing structure 7.
When at least one of linear flywheels 10, encircling the planet 1, reaches first cosmic velocity Veh, m/sec, in vacuum channel 9, for example, when starting from launch overpass 6 of altitude h, m, it will become weightless. As velocity of this linear flywheel 10 increases, the centrifugal force acting vertically (that is, from the center of planet 1 along its radius) will exceed its weight, that is, it will try to break it off from planet 1. When centrifugal forces from the accelerated linear flywheel 10 exceed the specific gravity of general planetary vehicle 5 (for example, equal to 1000 kgf/m), the entire system will become conditionally weightless (the weight of general planetary vehicle 5 will become zero, that is, it will stop pressing on launch overpass 6. If such linear flywheel 10 is accelerated to even higher velocity, there will be excessive lifting force sufficient to lift entire general planetary vehicle 5 together with payload 14 to planned circular orbit 13.
By simultaneously solving the equations (12), (13), (14) and (15), an expression is obtained for determining the acceleration from the centrifugal force of inertia of at least one of linear flywheels 10 when the above-mentioned forces are applied to general planetary vehicle 5 (see
a=/m0rφ2−gRe2/rp2−2πcl/m0(rp/Re−1)−kfρ0/m0{dot over (r)}p2 exp(−αn(r/Re−1)) (16)
Which suggests the condition for beginning of radial movement upwards general planetary vehicle 5, defined by the expression:
V
0
>V
1h√(1+m0/), (17)
where, depending on initial start (launch) position, V1h, m/sec, respectively—Veh, m/sec, or Vvh, m/sec, or Vlh, m/sec.
Thus, as can be seen from the expressions (16) and (17), the following data are necessary to calculate the implementation of the start (launch) process, for example from the Earth, of general planetary vehicle 5 and its insertion into planned circular orbit 13 of altitude H, m:
1) Initial constant parameters for launch of general planetary vehicle 5 from the surface of Earth in the equator region, are as follows:
2) Parameters determining the position of planned circular orbit; value of corresponding launch velocity of at least the first linear flywheel 10.1, its length, weight and mechanical properties; specific mass of linear meter of general planetary vehicle 5; aerodynamic characteristics of the outer shell of general planetary vehicle 5.
3) Parameters determining the position of the elastic and friction expansion sections of at least the first linear flywheel 10.1; iteration step on each section; radial velocity reduction factors at the end of friction sections.
Sixth, payload 14 of total mass m3, kg, is lifted by means of linear bearing structure 7 of general planetary vehicle 5 to planned circular orbit 13 of altitude H, m, under action of centrifugal forces of at least one of linear flywheels 10;
Seventh, linear bearing structure 7 of general planetary vehicle 5 is guaranteed to attain circumferential velocity around planet 1 in co-rotational direction re planet 1, equal to first cosmic velocity V1H, m/sec, on planned circular orbit of altitude H, M, above planet surface, by decelerating the first linear flywheel 10.1 and transmitting, respectively, according to law of conservation of angular momentum in closed system, the motion pulse from linear flywheel 10 of linear bearing structure 7 of general planetary vehicle 5, whereas energy generated during deceleration of the first linear flywheel 10.1—for acceleration in counter-direction of the second linear flywheel 10.2;
Eighth, linear electromagnetic drives 12 of both linear flywheels 10 are turned off in planned circular orbit 13 of altitude H, m, above surface of planet 1, and general planetary vehicle 5 is unloaded, for example, into orbital circular (seizing the planet) complex 30 (see
At this stage, alternatively, launch of classic interplanar rocket-type satellite (not shown in the figures), fixed on the outer part of pressure hull 8 of linear bearing structure 7 similar to transportation compartments 15.2, can be carried out from general planetary vehicle 5 inserted on planned circular orbit 13 of altitude H, m, above the surface of planet 1.
Ninth, general planetary vehicle 5 is returned to the initial launch position by lowering the altitude of linear bearing structure 7 of general planetary vehicle 5 from planned circular orbit 13 of altitude H, m, above the surface of planet 1 to h, m, or hv, m, or hl, m, respectively, on launch overpass 6, in liquid 20 of ocean or in gaseous environment 23 of planetary 1 atmosphere, by decelerating one of linear flywheels 10 and accelerating the other linear flywheel 10 in opposite direction until linear bearing structure 7 has a zero circumferential velocity relative to planet 1.
Tenth—upon return of general planetary vehicle 5 into initial launch position by means of fixing locks 19 (see
Modes of smooth acceleration and/or deceleration of linear flywheels 10 are secured thanks to action of adjustable linear force N0, N/m, thereon, coming from all uniformly distributed over the entire length L0, m, of linear bearing structure 7 of general planetary vehicle 5 of subsystems of the system of linear electromagnetic drives 12, as well as by maintaining the standard operation of subsystems of the system of magnetic and/or electromagnetic suspension 11, respectively, together with the system of linear electromagnetic drives 12. Operation of linear electromagnetic drives 12, in turn, is controlled and coordinated by control system 17 connected with them by means of communication system 18 equipped with feedback and technical parameters monitoring subsystems (see
Control of motion of linear flywheels 10 and coordination of value of linear force N1, N/m, acting on each individual section thereof, are performed so that all members of linear bearing structure 7 of general planetary vehicle 5 move uniformly, excluding occurrence of longitudinal vibrations and other possible disturbances in motion of members of its structure.
For this purpose, during operation of general planetary vehicle 5, throughout its linear flywheels 10, linear force N1, N/m, their acceleration and/or deceleration are adjusted relative to the nominal value of that linear force N0, N/m, within the boundaries, determined from the ratio:
0.9≤N1/N0≤1.1 (12)
Range of ratio of linear force N1, N/m, of acceleration and/or deceleration of linear flywheels 10 to nominal value of that linear force N0, N/m, is selected on the basis of conditions of operation reliability of general planetary vehicle 5, stipulated by the design assignment, and possibility of achieving of the required velocity, including launch velocity, of linear flywheels 10 without possible disturbances in motion of members of general planetary vehicle 5.
In case the ratio (12) is equal to 1, the whole structure and all systems of general planetary vehicle 5 will have increased parameters for reliability and stability of their operation, however, at the same time, the cost of achieving this result will significantly increase.
In cases, when values of the ratio (12) are less than 0.9 or more than 1.1, the tasks of prevention of longitudinal vibrations and elimination of possibility of occurrence of other disturbances during free motion of extended linear members of general planetary vehicle 5 will become complicated to tackle, which is unacceptable, as it can lead to a penalized reliability and deteriorated stability of functioning thereof.
To carry out all transportation and insert into calculated orbit, for example, in the conditions of planet Earth, at altitude of 400 km, the payload 14 (passengers and cargoes), at least one of linear flywheels 10 of general planetary vehicle 5,—which has operational weight, e.g., 40 million tons (and, accordingly, specific weight—approximately 1000 kg/m),—should accumulate kinetic energy in the amount of 1.25×1018 J (around 3.5×1011 kW×h). Taking into account energy losses and expenditures when entering circular orbit 13 (in particular, due to efficiency of linear electromagnetic drives 12 in order of 95%), the initial energy reserves should be at least by 10% more, that is, will be around 1.4×1018 J (3.9×1011 kW×h). Then, when connecting the power of general planetary vehicle 5, which is equal to less than 2% of the capacity of the world's power plants, to the external power system (Earth grid) of 100 million kW (or 2.5 kW per meter of length of linear bearing structure 7 of general planetary vehicle 5), initial charging time of the general planetary geospatial transportation complex—acceleration of at least one of linear flywheels 10 up to calculated velocity of V0, m/sec—will take 420 hours (17.5 days).
After calculated velocity V0, m/sec, is reached by at least one of linear flywheels 10, general planetary vehicle 5 of total mass of 40 million tons, of which 20 million tons are for linear flywheels 10, is ready for launch. But it is kept from lifting along its entire length L0, m, by means of fixing locks 19 of linear bearing structure 7 of general planetary vehicle 5, for example, to launch overpass 6.
After payload 14 has been placed on general planetary vehicle 5, it is released by locks 19 along the entire length L0, m, of linear bearing structure 7, and general planetary vehicle 5 is no longer kept by anything on planet 1.
Since flywheels are accelerated to velocities that allow the centrifugal forces to exceed the weight of each linear meter of general planetary vehicle 5, each of its linear meters begins to move from the center of rotation of linear flywheels 10, that is, to rise vertically upwards in plane of the equator passing through the center of mass of the Earth. At the same time, the ring (circle) of general planetary vehicle 5 will increase in diameter symmetrically in all directions relative to the center, and its body—elongate, stretch, without any displacement of the center of mass of this giant ring, which, according to law of conservation, will always coincide, in this case, with the center of mass of the planet Earth.
The acceleration of climbing into space depends on excessive centrifugal forces. For example, if lifting force acting on each linear meter of general planetary vehicle 5 is bigger than the weight of each linear meter thereof by 5%, general planetary vehicle 5 will start to climb up with a comfortable acceleration of 0.5 m/sec2, or equal to 5% of gravitational acceleration. When moving with this acceleration, general planetary vehicle 5 will rise (expand in plane of the Earth's equator) to altitude of 100 km in 5 minutes 16 seconds and will have a vertical lift velocity at this altitude of 570 km/h.
During lifting for every 100 km above the Earth, the hull of general planetary vehicle 5 should extend by 1.57%. Accordingly, the diameter of pressure hull 8 of general planetary vehicle 5 will also increase by 1.57%, which is easily achievable by structural and technological solutions such as telescopic connections 28 along the length of the rigid units 27 of linear bearing structure 7 of general planetary vehicle 5, or by uniting them with each other by means of bellows 29 (spring tabs) and other proven techniques known from the art.
After leaving the dense atmosphere of the Earth (at altitudes of more than 10 km), the braking (generator) mode is activated on linear electromagnetic drive 12.1 of the first linear flywheel 10.1, accelerated at the surface of the Earth to cosmic velocity V0, m/sec, in co-rotational direction of planet 1. The generated power is transmitted by means of control system 17 and communication system 18 to acceleration of the second linear flywheel 10.2 in the counter-direction in relation to the first linear flywheel 10.1. As a result, general planetary vehicle 5 receives a double pulse and begins to rotate towards the rotation of the Earth. If the acceleration of rotation is the same comfortable 0.5 m/sec2, general planetary vehicle 5, and the entire payload 14 located therein (or thereon), will gain an estimated orbital, i.e. circular, velocity, for example, of 7671 m/sec (for an altitude of 400 km) after 4 hours.
The climbing and orbital velocity modes are selected so that general planetary vehicle 5 at a given altitude has an appropriate orbital velocity and is in equilibrium and its vertical (radial) velocity is zero. For this purpose, a special ballast system 25 is used in the process of entering space, if necessary. As part of payload 14, in amount of 0.1-10%, liquid and/or gaseous ballast 26 is used, uniformly arranged along the whole length L0, m, of linear bearing structure 7.
In order to lift general planetary vehicle 5, it is necessary to have either initial excess of kinetic energy (linear flywheels 10 are accelerated on Earth, before launch, to a higher velocity) or, during lifting, it is required to reduce weight of general planetary vehicle 5 by dropping ballast 26. Most preferred is combination of these techniques.
With ballast 26 reserve of less than 0.1% of mass of payload 14, a significant increase in the velocity of rotation of linear flywheels 10 at launch is required in order to improve stabilization of general planetary vehicle 5 when it is lifted into space (to use the gyroscopic effect), resulting in unduly high energy costs and additional structural difficulties.
With ballast 26 reserve exceeding 10% of payload 14′ mass, the share of payload 14 placed by linear bearing structure 7 of general planetary vehicle 5 into circular orbit 13 of altitude H, m, above the surface of planet 1, is significantly reduced, which leads to penalized efficiency of operation of the whole complex.
The total consumption of ballast 26 during lifting will be about 10-100 kilograms per linear meter of general planetary vehicle 5 (for the above cited input data).
Hereby, as ballast 26, ecologically friendly to Planet Earth substances and materials are used: water and/or compressed, and/or liquid air and/or oxygen, and/or nitrogen.
If such ballast 26 is sprayed in a predetermined amount in the ozone layer of planet 1 and above (altitudes from 10 to 60 km), it will be possible to regulate the oxygen and ozone content in the upper atmosphere and to “heal” the ozone holes, as well as ecologically safely manage the weather and climate on planet Earth.
It is also an object of the claimed invention to use ballast 26 when lifting general planetary vehicle 5 into planned circular orbit 13 of altitude H, m to restore the ozone layer, improve weather and stabilize the climate on Earth by spraying the it in the atmosphere of planet 1, which is also a new essential feature corresponding to the inventive step.
Similar to the described example, launch of general planetary vehicle 5 placed in liquid 20 of the ocean of planet 1 at launch depth of hv, m, and/or in gaseous environment 23 of planetary 1 atmosphere at launch altitude of hl, m (see
After reaching planned circular orbit 13 and stabilizing general planetary vehicle 5 along the entire length L0, m, of linear bearing structure 7 (no local vibrations) relative to the ideal orbit), the payload 14 is unloaded, for example, into the orbital circular (seizing the planet) complex 30 (see
The load-carrying capacity of the described variant of general planetary vehicle 5 is 250 kg/m under Earth conditions, or 10 million tons of payload 14.
The cost of geospatial transportation by general planetary vehicle 5 along the routes Earth-Orbit and Orbit-Earth consists of three main components:
1) Energy costs of operation of all systems of general planetary vehicle 5, first of all —linear electromagnetic drives 12 and systems of magnetic and/or electromagnetic suspension 11 of linear flywheels 10, which consumes more than 95% of energy consumed by the whole general planetary geospatial transportation complex;
2) Depreciation charges;
3) Overhead costs for maintenance of the general planetary geospatial transportation complex.
Initial energy supply required to lift general planetary vehicle 5 with total mass of m0, kg, e.g. 40 million tons, into space, and return to Earth without payload 14, of total mass of m3, kg, e.g. 10 million tons left in orbit (for example, in orbital circular complex 30—see
420 000 000 000 kW×hour×0.05 USD/kW×hour=21 000 000 000 USD, or:
E
0=2 100 USD/t.
Therefore, on trips with the preferred one-way direction of the cargo traffic from planet 1 to planned circular orbit 13, it will be necessary to compensate in each trip only for the energy costs of the payload 14 delivered to space, the total mass m3, kg, of which (loading factor) makes 25% of gross mass of general planetary vehicle 5. Thus, during this period of operation of general planetary vehicle 5 (in the first year), the delivery of one ton of cargo to planned circular orbit 13 of the Earth will require energy costs as follows: E1=2 100 USD/t×0.25=525 USD/t.
Hereby, once accelerated, linear flywheels 10 can rotate inside vacuum channels 9 for years, as the magnetic cushion of the magnetic and/or electromagnetic suspension system 11, like the vacuum of vacuum channels 9, will not create resistance when they travel at space velocities.
At equal Earth-Orbit and Orbit-Earth cargo traffic volumes, which will have been established approximately at the 10th year of operation of general planetary vehicle 5, additional energy will be necessary only for compensation of energy dissipation in linear electromagnetic drives 12 of linear flywheels 10. The total energy loss within general planetary vehicle 5 is less than 10%, so the cost of shipping a ton of cargo to orbit in this case (and, accordingly, to descend a ton of cargo to the surface of planet) will be: E2=2 100 USD/T×0.1=210 USD/t.
Once the orbital space industry is fully operational, and commercial exploitation of asteroids and the Moon as sources of raw materials has started, the need to deliver raw materials from Earth to planned circular orbit 13 will be significantly reduced. At the same time, the return cargo traffic from planned circular orbit 13 to the planet will significantly exceed the direct (one-way), as the main part of industrial production for earth-based citizens will be delivered from space. Even if in future the space-based industrial products of much higher quality (than that of the existing) will be produced by order less per capita than the current production on the planet, the annual volume of transportation on the route Orbit-Earth will reach 500 million tons after 10 years of operation of general planetary vehicle 5, which would require 50 launches into planned circular orbit 13 (approximately one launch per week). Hereby, general planetary vehicle 5 will insert less payload 14 into planned circular orbit 13 (it will make an outbound trip loaded of about 20% only), mainly because it will primarily shuttle into space to take the products manufactured there to deliver them to our planet to consumers—by then about 10 billion earthlings. This will make it possible to convert the potential and kinetic energy of space cargo delivered to Earth into electricity and annually provide the Earth's energy system with the equivalent of energy of 1 billion tons of oil. At that stage and the subsequent stages, energy costs will have negative value, and general planetary vehicle 5 will operate in the mode of a power plant making profit amounted to: 500,000,000 tons/year×8000 kW×hour/t×0.05 USD/kW×hour=200 billion. USD/year, or, net, 400 USD for each excess ton of cargo delivered from planned circular orbit 13 to Earth.
At the same time, part of the energy will be spent on the own needs of general planetary vehicle 5 (around half), so each ton of excess cargo delivered to the planet from space will yield a net energy profit of: E3=200 USD/t.
The capital costs for development (design and construction) of general planetary vehicle 5 can be estimated similarly to contemporary, high-potential electric vehicles, in which the majority of the cost comes from electrical equipment. In terms of complexity of equipment and composition of components, general planetary vehicle 5 is also approximately equivalent to electric vehicle (even less sophisticated) and will cost about the same amount, in terms of the cost of one ton of construction—not more than 25,000 USD/ton. Since mass of the loaded general planetary vehicle 5 (without payload 14) will be, in the described embodiment, 30 million tons, its estimated cost will be: 30 000 000 t×25 000 USD/t=750 billion USD.
A large hadron collider of 26.5 km, built on the border between Switzerland and France and located underground in a special tunnel of large diameter, is certainly a more technically complex product, in which the velocity of acceleration of elementary particles reaches light velocity (not 10-15 km/s, as for linear flywheels of general planetary vehicle), cost more than 6 billion USD—which also confirms justification of above stated estimated value of general planetary vehicle 5.
General planetary vehicle 5 is designed for 10,000 space launches and return landings. During that time, it will carry 100 billion tons of cargo. At the same time, depreciation charges per 1 ton of cargo from capital investments in general planetary vehicle 5 will be:
C
OTC=750 000 000 000 USD/100 000 000 000 t=7.5 USD/t.
The length of the equatorial complex of launch overpass 6 of general planetary vehicle 5 will be 40,076 km, of which about 20% will be for land sections and 80% for sea sections.
Launch overpass 6 of general planetary vehicle 5, located along the equator 4.1, will represent transport and infrastructure communicator. Power transmission lines and communication lines will also be integrated into launch overpass 6 (not shown).
The cost of the support and communication part based on launch overpass 6 located along the equator 4.1 can be estimated at 1.320 billion USD, provided that, on average, it will cost 25 million USD/km on land sections and 35 million USD/km—on sea sections.
Accordingly, depreciation charges per 1 ton of cargo from capital investments in transport and communication part at the equatorial basing of launch overpass 6 will amount to:
C
CT=1 320 000 000 000 USD/100 000 000 000 T=13.2 USD/t.
Whereby total depreciation charges will be:
=C
omc
+C
cm=7.5 USD/t+13.2 USD/t=20.7 USD/t.
Analysis of data presented in Table 1 allows to draw the following conclusions:
1) The highest net cost of geospatial cargo traffic—700 USD/t—in the first year of operation, is driven by the need to initially accelerate linear flywheels 10 with substantial energy consumption required therefor, as well as—relatively low volume of annual traffic.
2) Over the years, as the volume of traffic increases, both direct and return, their cost decreases significantly.
3) On the 9th year of operation, when return cargo traffic (planned circular orbit 13 to planet 1) will substantially exceed direct cargo traffic (planet 1 to planned circular orbit 13), the net cost of traffic will become negative. This means that general planetary geospatial transportation complex will become profitable not only as a transport, but also as a giant power plant with a length of more than 40 thousand kilometers.
Development of general planetary geospatial transportation complex in conditions of planet Earth includes the following basic directions (stages):
1) Engineering research and design development of equatorial launch overpass 6 with transportation-communication part of general planetary geospatial transportation complex;
2) Preparation and realization (construction) of the equatorial launch overpass 6, with corresponding communication system (not shown on figures).
3) Manufacture and installation of general planetary vehicle 5 (length 40 076 km, total mass, without payload—30 million tons), commissioning. The entire totality of works related to realization of general planetary geospatial transportation complex is planned to have been completed during 20 years—by 2038.
The cost of realization general planetary geospatial transportation complex and related works, until 2037 inclusive, is shown in Table 2. It should be noted that the maximum of future annual costs, i.e. 260 billion USD for the period 2032-2037, for example, is about 2 times less than the current US military budget. It also proves that the program of creating general planetary geospatial transportation complex can be implemented, based on their budgets for these years, by countries such as the USA, China, Russia, India and even Brazil, all on their own.
Total cost of realization of general planetary geospatial transportation complex during 20 years comparable to possible global spending in 2030 (i.e. in one year) on existing traditional space programs using rocket carriers (launch vehicles).
Currently, capacity of world market of space services amounts to, according to various estimates, 300-400 billion USD a year. The commercial component reaches 75%, and the state segment is about 25%. The volume of this market grows by 4-5% annually. Based on the level of development of existing space programs, experts predict acceleration of growth of market of space products and services.
By 2030, the market for space products and services could grow to about USD 1.5 trillion. There is a number of prerequisites for such significant growth.
Due to high cost of cargo shipments from Earth to space and back (about 10 million USD/t), at this stage of technology development, the industrial production in space is physically impossible and economically impractical. However, with a transportation system capable of providing cargo turnover between the Earth surface and the orbit in the amount of about 100 million tons per year and more at a low cost of delivery of 1 ton of cargo—about 1000 USD/ton or less—many Earth technologies will be able to reach a new level.
A variant of embodiment of the proposed solution on the planet Earth, according to one version of its design with load capacity of about 100 million tons, is as follows: general planetary vehicle 5 represents a closed “wheel” (see
The launch process of general planetary vehicle 5 proceeds as follows. When electric power is supplied to the winding of linear electromagnetic drive 12 of at least one of linear flywheels 10, a traveling magnetic field is generated. In vacuum channel 9, located in pressure hull 8 of general planetary vehicle 5, there is a linear flywheel 10 having a magnetic and/or electromagnetic suspension 11 and being a kind of rotor of linear electromagnetic motor. Therein, a current is induced that will interact with the magnetic field which generated it, and linear flywheel 10, which does not experience any resistance (it is placed in vacuum), will come into motion (see
The payload 14 (loads and passengers) is placed into general planetary vehicle 5 being held on launch overpass 6, with the first linear flywheel 10.1 having specific weight of 2 tons per meter, pre-rotated to velocity of 16 km/s, and exactly the same, but quiescent, the second linear flywheel 10.2. The payload 14 is preferably placed on general planetary vehicle 5 prior to the start of linear flywheel 10. The payload 14 is placed both inside and outside pressure hull 8 of general planetary vehicle 5, but so that the load as a whole is evenly distributed along the length of the L0, m, of linear bearing structure 7. After release of the locks 19 (see
Also, upon lifting from launch overpass 6, general planetary vehicle 5 will be subjected to increased impact from the air flows, but they will not have a significant effect on its operation. Calculations show that the non-resting general planetary vehicle 5 has a unique flexural rigidity and stability which not available to static structures due to the rotational movement of linear flywheels 10. Thus, the additional load of 1,000 tons applied to the section of the general planetary vehicle 5 with a length of 1 kilometer, will bend it relative to the ideal circle by no more than 10 centimeters.
Mathematical analysis shows that the lifted general planetary vehicle 5 will be in equilibrium only if its total kinetic energy is equal to that of a body of the same mass moving at the first cosmic velocity. If the total energy is higher, the diameter of the “ring” of general planetary vehicle 5 will begin to increase, and if lower—to decrease. Then, in order to lift the general planetary vehicle 5, it is necessary to have either initial excess of kinetic energy (linear flywheels 10 are accelerated on Earth, before launch, to a higher velocity), or in the process of lifting, it is necessary to reduce the mass of the general planetary vehicle 5 by dropping ballast 26. The preferred is the combination of these techniques.
As ballast 26, ecologically friendly to Planet Earth substances and materials are used: water or pre-liquefied air, oxygen or nitrogen.
The tension of pressure hull 8 of general planetary vehicle 5, as its diameter increases, will be relatively small: its length under Earth conditions will increase by 1.57% per each 100 kilometers of lifting. Elongation of pressure hull 8 is compensated by moving its rigid units 27 relative to each other, the ends of which, for example, telescopically fit into each other and are interconnected, for example, by hydraulic cylinders (not shown on figures). Linear flywheel 10, for example, in the form of a closed multilayer endless belt, which represents a kind of rotor of linear electromagnetic motor, will be extended by elastic stretching or slight displacement of the layers of the forming belt with respect to each other (see
The lifting velocity of general planetary vehicle 5 at any section of the track can be set within wide limits, from pedestrian speed to aircraft velocity. General planetary vehicle 5 passes through atmospheric section at minimum possible radial velocities.
After leaving the dense atmosphere, the reversible mode of linear electromagnetic drive 12.1 of the first linear flywheel 10.1 is switched on to generator mode. Linear flywheel 10.1 will start to brake and linear electromagnetic drive 12.1 will generate electric current. This energy is transmitted through control system 17 and communication system 18 to linear electromagnetic drive 12.2 of the second linear flywheel 10.2, which is accelerated in counter direction to the movement of the first linear flywheel 10.1 (see
As a result, the second linear flywheel 10.2, having, for example, same mass as the first linear flywheel 10.1, previously stationary with respect to pressure hull 8 of linear bearing structure 7 of general planetary vehicle 5, starts to rotate in reverse direction relative to the first linear flywheel 10.1. This ensures the law of energy conservation, in the process of insertion of payload 14 from surface of planet 1 into planned circular orbit 13 and stability of kinetic energy of members of general planetary vehicle 5 rotating around planet 1.
Pressure hull 8 of general planetary vehicle 5 and everything inside therein, and all that is attached to it from the outside—linear electromagnetic drives 12 with linear flywheels 10, as well as detachable transportation compartments 15.2 with payload 14 and the like—subject to law of conservation of angular momentum of the system, will come into rotation. It will start rotating in the same direction as the first linear flywheel 10.1 until it reaches a circumferential velocity equal to the first cosmic velocity. Radial velocity of general planetary vehicle 5 will fall to zero. Thereafter, at altitude of, for example, 400 kilometers, the payload 14 (cargo and passengers), delivered to destination, is unloaded, for example, into orbital circular (seizing the planet) complex 30 located at altitude H, m, of planned circular orbit 13 of planet 1 (see
Landing of general planetary vehicle 5 on Earth is performed in reverse order.
In this way, general planetary vehicle 5 will be put into near space in few hours if overloads therein are assumed at the level of the modern aerobus at the moment of its take-off (acceleration around 1-2 m/sec2).
During transportation loop of general planetary vehicle 5, it will not require any outside power supply. General planetary vehicle 5 will consume the initial kinetic energy reserve, which from the first linear flywheel 10.1, during launch of general planetary vehicle 5, will be redistributed to its pressure hull 8, and upon return to the planet 1, will be redistributed again between linear flywheels 10.1 and 10.2, for example, partially transmitted to at least the second linear flywheel 10.2. To the internal energy of the system of general planetary vehicle 5, space cargo energy will be added,—payload 14, delivered from space to Earth. For example, delivering a ton of cargo from the Moon will produce the same amount of energy as a ton of oil (the lunar cargo with respect to Earth has kinetic and potential energy which are utilized by general planetary vehicle 5 and converted into electrical form).
On the way to space and back, general planetary vehicle 5 will receive such amount of cheap energy that will satisfy both its own needs and a large part of the energy needs of mankind as a whole. In addition to the described energy source—space cargo energy, there are at least three other energy sources suitable for use by the proposed general planetary geospatial transportation complex: solar energy obtained, for example, through solar panels, which can be fixed on the pressure hull 8; ionosphere currents and the Earth's rotational energy around its axis (not shown). The energy thus obtained by general planetary vehicle 5 will be either accumulated in its linear flywheels 10 or transferred to planet Earth.
It is estimated that the gross launch mass of general planetary vehicle 5 in the described example could be 400 million tons (10 tons per linear meter), payload 14 will be 100 million tons (2.5 tons per linear meter), passenger capacity—100 million people.
As shown by the examples of calculation of process of payload 14 insertion from Earth's surface to planned circular orbit 13 of altitude H, m, the method and variants of embodiment of the invention, specified in the disclosed materials, the technical and economic parameters of the general planetary geospatial transportation complex by Yunitski, are optimized and ensure the industrialization of near space in the foreseeable future with the aim of taking the environmentally dirty earth-based manufacturing industry outside the biosphere.
Similar to the described embodiment of general planetary geospatial transportation complex by Yunitski on planet Earth, it is possible to implement it, for example, on the Moon, Mars, or on another planet, as well as on gaseous atmosphere giants such as Jupiter and Saturn, and on planets that have no land, but have an ocean.
Variants of the described design of general planetary geospatial transportation complex by Yunitski, as well as the method for planet 1 surface to its circular orbit payload insertion, possess novelty and meet the criterion of “distinctive features”, at the same time allow to create an effective geospatial transportation system ensuring achievement of all the set goals.
| Number | Date | Country | Kind |
|---|---|---|---|
| 201800525 | Aug 2018 | EA | regional |
This application is a National Phase Entry of International Patent Application No. PCT/BY2019/000014, filed on Sep. 27, 2019, which claims priority to Eurasian Patent Application No. 201800525, filed on Aug. 1, 2018, both of which are incorporated by reference herein.
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/BY2019/000014 | 9/27/2019 | WO | 00 |
