The present disclosure generally relates to Earth orbiting satellites, and more particularly, but not exclusively, to low Earth orbiting satellites having unique vehicle configurations.
Operating a spacecraft in relatively very low orbit, even though the atmosphere is rarefied, can result in the production of atmospheric drag, which can reduce spacecraft velocity and ultimately contribute to orbital decay. The level of atmospheric drag in very low orbit can be sufficient to deorbit conventional spacecraft geometries in extremely short periods of time. Further, the configuration of at least certain types of sensing systems and the associated size of the spacecraft that contains such remote sensing systems can contribute to the level of atmospheric drag that can be experienced by the spacecraft. Further, operation of at least certain components of such sensing systems can impart undesirable torque, as well as altitude disturbances, that can further contribute to an increase in atmospheric drag. Some existing systems have various shortcomings relative to certain applications. Accordingly, there remains a need for further contributions in this area of technology.
One embodiment of the present disclosure is a unique low Earth orbiting satellite. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for configuring a low Earth orbiting satellite. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.
For the purposes of promoting an understanding of the principles of the invention, reference will now be made to the embodiments illustrated in the drawings and specific language will be used to describe the same. It will nevertheless be understood that no limitation of the scope of the invention is thereby intended. Any alterations and further modifications in the described embodiments, and any further applications of the principles of the invention as described herein are contemplated as would normally occur to one skilled in the art to which the invention relates.
With reference to
The satellite 50 can be constructed for operation at low Earth orbit altitudes in the thermosphere, anywhere at altitudes ranging from at least 50 miles and beyond, including but not limited from 50 miles to 600 miles, and in some situations preferably from 50 miles to 23,000 miles, where images or other sensory information of Earth can be obtained through any variety of sensors. In some forms the satellite 50 is configured to transmit data in real time, but in other forms and/or modes of operation the satellite 50 can process information onboard and transmit a reduced data set.
The satellite 50 generally includes a longitudinally oriented body (or fuselage) 52, one or more fins 54 that can be used as solar arrays and/or antennas, and an electric rocket engine 56, also referred to herein as a rocket thruster, useful to assist in countering the effects of drag while operating in low Earth orbit. The body 52 is sized to accommodate a payload 58 that can include, at least in part, a remote sensing system, such as, that can include several different components (some of which may be described and/or illustrated later in the application). According to certain embodiments, the payload 58 is a telescopic payload.
The rocket thruster 56 can take a variety of forms. For example, according to certain embodiments the rocket thruster 56 is an ion thruster, including, for example, a Hall-effect thruster. While reference may be made below to particular types of electronic rocket thrusters 56, such as, for example, Hall-effect thrusters, no limitation is hereby intended that the rocket thruster 56 in any given embodiment be limited to being a Hall-effect thruster, or any other type of thruster, unless indicated explicitly to the contrary. Further, although the illustrated embodiment depicts a single block to represent a rocket thruster 56, it will be appreciated that additional rocket thrusters 56 can be used on the satellite 50. For example, multiple rocket thrusters 56 can be used at the location of the single block represented in the figures. Additionally, one or more rocket thrusters 56 can be located elsewhere around the satellite 50. For example, multiple rocket thrusters 56 can be festooned at multiple locations and/or on multiple surfaces to provide specific thrust vectors with regard to the bulk motion of the satellite 50. As will be appreciated, the rocket thruster 56 can be used to enable efficient orbital maneuvers, one example of which includes drag makeup in very low Earth orbit missions.
To aid in some of the discussion herein, a Cartesian coordinate system has been illustrated in
As will be appreciated, the origin of the axis system can be anywhere in the satellite and for purposes of illustration is forward of the center of mass (CoM) 60 as shown in
As seen in
Various embodiments disclosed herein can have features to maximize the ballistic coefficient of the satellite 50. In some forms, the ballistic coefficient can be maximized while maximizing payload volume. In one non-limiting embodiment, the satellite 50 has a ballistic coefficient of 100 kg/m2 (about 4.2 lb./ft2). Some shapes contemplated for the fuselage 52 include cigar shapes, fish shapes, and missiles.
The payload 58, such as, for example, a telescopic payload, can be arranged along the longitudinal extension of the fuselage 52. As will be described further below, according to certain embodiments in which the payload 58 is a telescopic payload, the payload 58 can include an angled mirror to image the Earth below the orbiting satellite 50. Such angled mirror can be located in forward of, or aft of, an imager used in the telescopic payload 58 used to convert a visual image to digital information. The shape of the structure and relative placement of various components in some embodiments can create a relative placement of the center of mass 60 of the satellite 50 being in a position forward of a center of drag of the satellite 50. Configurations can be provided to include a mixture of construction materials for structural members as well as non-structural members having chemical/compositional/material properties selected to survive the harsh environment in the thermosphere. For various embodiments herein it is envisioned that the mission length in orbit is multiple months up to one or more years.
Various configurations are depicted in
Turning now to
The memory device 106 of the illustrative controller 102 can be embodied as any type of volatile (e.g., dynamic random access memory (DRAM), etc.) or non-volatile memory capable of storing data therein. Volatile memory may be embodied as a storage medium that requires power to maintain the state of data stored by the medium. Non-limiting examples of volatile memory may include various types of random access memory (RAM), such as dynamic random access memory (DRAM) or static random access memory (SRAM). One particular type of DRAM that may be used in a memory module is synchronous dynamic random access memory (SDRAM).
In some embodiments, the memory device 106 may be embodied as a block addressable memory, such as those based on NAND or NOR technologies. The memory device 106 may also include future generation nonvolatile devices, such as a three dimensional crosspoint memory device (e.g., Intel 3D XPoint™ memory), or other byte addressable write-in-place nonvolatile memory devices. In some embodiments, the memory device 106 may be embodied as, or may otherwise include, chalcogenide glass, multi-threshold level NAND flash memory, NOR flash memory, single or multi-level Phase Change Memory (PCM), a resistive memory, nanowire memory, ferroelectric transistor random access memory (FeTRAM), anti-ferroelectric memory, magnetoresistive random access memory (MRAM) memory that incorporates memristor technology, resistive memory including the metal oxide base, the oxygen vacancy base and the conductive bridge Random Access Memory (CB-RAM), or spin transfer torque (STT)-MRAM, a spintronic magnetic junction memory based device, a magnetic tunneling junction (MTJ) based device, a DW (Domain Wall) and SOT (Spin Orbit Transfer) based device, a thyristor based memory device, or a combination of any of the above, or other memory. The memory device may refer to the die itself and/or to a packaged memory product. In some embodiments, 3D crosspoint memory (e.g., Intel 3D XPoint™ memory) may comprise a transistor-less stackable cross point architecture in which memory cells sit at the intersection of word lines and bit lines and are individually addressable and in which bit storage is based on a change in bulk resistance.
The remote sensing system 100 can also include detection system 108 that is used to images or other sensory information of Earth obtain. The components of the detection system 108 can vary based on the type of image or sensory information that is being obtained. For example, according to certain embodiments, the detection system 108 can be a camera system or a telescopic system 110 or other optical system that is used in connection with detection using visible light. Such a telescopic system 110 can include one or more mirrors 112 for at least one of, if not both, redirection of light and/or optical gain, including with respect to increasing optical power. As discussed below, such a mirror 66 may, or may not, be used in connection with other mirrors. Further, the mirror(s) 66 can have a variety of shapes and configurations, including, for example, having a relatively flat or curved reflective surface. As discussed below, the mirror 66 can also be configured, including oriented, to redirect light in a direction that can assist in minimizing the cross sectional size of the body or fuselage 52, and thereby assist in minimizing atmospheric drag on the satellite 50. Further, as discussed below, according to certain embodiments, the detection system 108 can include, or be operably coupled to, one or more actuators 72 that can assist in selectively displacing the payload 58 or portions of the payload 58, including, for example, the mirror 66, telescopic system 110, and/or detection system 108, among other portions of the payload 58. The telescopic system 110 can also include one or more lenses 112, including, for example, one or more objective lenses that can assist with focusing an image(s) being obtained via use of the telescopic system 110, and one or more magnification lenses that can assist with magnification of such an image(s). Additionally, while
Additionally, or alternatively, the detection system 108 can include a sensor system 114 that is configured to obtain images using, for example, the infrared, near visible, and/or electromagnetic spectrums. For example, according to certain embodiment, the sensor system 114 can one or more of a LIDAR system, a radar detection system, and/or an ultrasonic detection system, among other sensor systems. Thus, for example, according to certain embodiments, the sensor system 114 can include an emitter 116 that can emit a signal or energy, including, for example, light, radio waves, and/or ultrasonic sound waves, among other outputs, and a detector or receiver 118 can detected a corresponding response or return signal.
Images and/or other information obtained via use of the detection system 108 can be digitized by the controller 102, and stored in the memory device 106 and/or communicated to a remote host system 120. According to certain embodiments, the remote host system 120 can be located on Earth and can wirelessly receive and/or communicate transmissions to/from via the remote sensing system 100 via a communication interface 122 of the remote sensing system 100. Thus, for example, the remote sensing system 100 can include one or more antennas and/or transceivers. The host system 120 can also be adapted to control certain aspect of the operation of satellite 50 and/or remote sensing system 100, including, for example, control the direction of travel, altitude, and speed of the satellite 50 and/or the actuator(s) 72 of the remote sensing system 100, among other aspects of the satellite 50 and/or the remote sensing system 100.
The controller 102 can also include a location system 124, such as, for example, a global positioning system, that can not only assist in guidance of the satellite 50, but also provide an indication of a corresponding location for the images or information obtained via use of the detection system 108, and/or information indicative used to determine when, and if, the mirror(s) 66 and/other portions of the payload 58 are to be displaced via operation of the associated actuator(s) 72.
As seen in
In the illustrated embodiment, a field of view 64 of the detection system 108, including the direction at which light or other energy at least enters into the detection system 108 can be at an angle that is not parallel to the axis of extension 84, x-axis, and/or the direction of travel of the satellite 50a. Moreover, the field of view 64 can extend out through a covered or uncovered opening 90 in the fuselage 52, and can extend in a generally downward direction toward Earth, such as in generally in the z-direction. While the field of view 64 can be located at a variety of locations forward of the rocket thruster 56, according to certain embodiments the field of view 64 can extend from a location of the satellite 50 that is forward of, as well as located in proximity to, the rocket thruster 56 and at an angle relative to elongated fuselage 52.
The fuselage 52 can be symmetrically disposed and extend along a geometrically identified axis (as illustrated in the embodiment in
The mirror 66 depicted in
Unlike the mirror 66 shown in
The ability to selectively displace the mirror 66 can permit relative placement between the body or fuselage 52 and mirror 66 to optimize the attitude of the vehicle 50 (e.g. to minimize drag) while still capturing a relevant field of view of the Earth below. Further, according to certain embodiments, operation of the actuator 72 so as to displace the mirror 66 can be in response to a location of the satellite 50d, such as, for example, in response to a decision by the controller 102 based, at least in part, on location information provided by the location system 124 and/or detection of by the remote sensing system 100 of a the detection system 108 capturing an image(s) or other information pertaining to a phenomenon or predetermined trigger condition. Alternatively, or optionally, operation of the actuator 72 can be based on an operator command, such as, for example, a command communicated to the remote sensing system 100 from an operator at the host system 120. Additionally, or alternatively, according to other embodiments, selective displacement of the mirror 66, such as, for example, via control the actuator 72, can be performing using an artificial intelligence engine and/or a neural network of the remote sensing system and/or the host system 120.
According to the illustrated embodiment, the payload 58 can be rotatingly coupled to the fuselage 52 such that relative motion is permitted between the two. As depicted in
Although the rectangular block depicted in
In some forms the payload 58, or portions thereof, can be supported at just one location, whether that location is at an axial end of the payload 58 or intermediate the forward and aft axial end. The coupling between the payload 58, or portions thereof, and the fuselage 52 can be accomplished using any variety of bearing arrangement, including a plain bearing, ball bearing, magnetic bearing, flexture, etc. While the shaft 68 can be a singular elongate shaft extending through the payload 58, in some form multiple shafts 68 are utilized, whether or not physically connected together or simply coupled together via other structure in the payload 58. Allowing the payload 58 to rotate freely relative to the longitudinal body 58 permits a relatively large range of lateral motion in the field of view 64, as depicted in
The first mirror 66 is not illustrated in
The movable mirror 66, such as, for example, the moveable mirrors 66 discussed above with respect to at least
The embodiments of
In one aspect the present application provides an apparatus comprising: an orbital vehicle structured to operate at orbital altitudes between 50 miles and 23,000 miles above the Earth, the orbital vehicle having at least one fin and a fuselage structured to contain at least part of a telescopic payload, the at least one fin having a swept configuration between a forward end and a rearward end of the orbital vehicle, and a Hall-effect thruster coupled with the orbital vehicle and capable of producing thrust sufficient to discourage orbital decay of the orbital vehicle when operating at orbital altitude, wherein the telescopic payload is constructed to image the Earth along a path oriented at an angle transverse to an axis of extension of the fuselage, which further includes a first mirror that turns the path transverse to the axis of extension to an angular direction in proximity to the axis of extension, wherein the angle transverse to the axis of extension is larger than the angular direction in proximity to the axis of extension.
One feature of the present application includes wherein the first mirror is a simple flat mirror.
Another feature of the present application includes wherein the first mirror is a powered mirror.
Yet another feature of the present application includes wherein the first mirror is moveable relative to the fuselage of the orbital vehicle.
Still another feature of the present application includes wherein the first mirror is structured to rotate about an axis to change a relative angle between an optical path produced by the first mirror and the axis of extension of the fuselage.
Still yet another feature of the present application includes wherein the optical telescope includes a plurality of components, the plurality of components including the first mirror, and wherein at least one component of the plurality of components is structured to rotate about the axis of extension such that a viewing angle of the optical telescope can be moved laterally relative to the axis of extension.
Yet still another feature of the present application further includes an inertia nulling mechanism coupled with the first mirror such that when the first mirror is moved the inertia nulling mechanism provides a counter movement to produce a counter torque to a torque produced when the first mirror is moved.
Yet still another feature of the present application includes wherein the inertia nulling mechanism includes a counterweight.
Yet still another feature of the present application includes wherein the counterweight is mechanically coupled with the movable mirror through at least one mechanical link.
Yet still another feature of the present application includes wherein the counterweight is mechanically isolated from an actuator that drives the first mirror, and wherein the counterweight is movable via a counterweight actuator.
Yet still another feature of the present application includes wherein the counterweight actuator is coupled with both the movable mirror and the counterweight.
Yet still another feature of the present application includes wherein the telescopic payload is oriented toward the forward end of the orbital vehicle such that a center of mass of the orbital vehicle is forward of a center of drag when operating the orbital vehicle at the orbital altitude.
Yet still another feature of the present application includes wherein the at least one fin includes an extension on opposing lateral sides of the orbital vehicle.
Yet still another feature of the present application includes wherein the at least one fin includes at least one of a solar array and an antenna.
Yet still another feature of the present application includes wherein at least one fin includes a material composition structured to discourage degradation from energetic particles at orbital altitudes.
Yet still another feature of the present application includes wherein the Hall-effect thruster can be operated in a mode to alter the local plasma environment.
Yet still another feature of the present application includes wherein the at least one fin can be a single construction affixed to a top of the orbital vehicle and which extends past lateral edges of the fuselage.
Yet still another feature of the present application includes wherein the at least one fin can be oriented at an angle to a lateral axis of the orbital vehicle such that it has an anhedral arrangement relative to the direction of travel and the location of Earth during orbit.
Yet still another feature of the present application includes wherein the at least one fin is a single fin, and wherein the single fin protrudes laterally from the fuselage.
Yet still another feature of the present application includes wherein the at least one fin includes three separate fins arranged about the circumferential periphery of the fuselage.
Yet still another feature of the present application includes wherein the at least one fin extends out the top of the fuselage.
Yet still another feature of the present application includes wherein the at least one fin extends out the rear of the fuselage to form a shuttlecock configuration.
Another aspect of the present application includes an apparatus comprising: an orbital vehicle having swept fin and a longitudinally oriented body structured to contain at least part of a telescopic payload, a Hall-effect thruster at least partially disposed within the orbital vehicle and capable of producing thrust to counter atmospheric drag at an orbital altitude, wherein the telescopic payload is constructed to image the Earth at a right angle to the longitudinally oriented body, wherein a first mirror of the telescopic payload turns the optical path from the right angle to an angular direction along the longitudinally oriented body.
A feature of the present application includes wherein the first mirror is one of a simple flat mirror and a powered mirror.
Another feature of the present application includes wherein the first mirror is structured to be moveable relative to the longitudinally oriented body of the orbital vehicle.
Yet another feature of the present application includes wherein the first mirror is structured to rotate about the longitudinally oriented body to change a relative angle between an optical path produced by the first mirror and the longitudinally oriented body.
Still another feature of the present application includes wherein the telescopic payload includes a plurality of components including at least an imager and an optical element, the plurality of components including the first mirror, and wherein at least one component of the plurality of components is structured to rotate about the longitudinally oriented body such that a viewing angle of the telescopic payload can be moved.
Still yet another feature of the present application further includes an inertia nulling mechanism coupled with the first mirror such that when the first mirror is moved the inertia nulling mechanism provides a counter movement to produce a counter torque to a torque produced when the first mirror is moved.
Yet still another feature of the present application includes wherein the inertia nulling mechanism includes a counterweight.
Yet still another feature of the present application includes wherein the counterweight is mechanically coupled with the movable mirror through at least one mechanical link.
Yet still another feature of the present application includes wherein the counterweight is mechanically isolated from an actuator that drives the first mirror, and wherein the counterweight is movable via a counterweight actuator.
Yet still another feature of the present application includes wherein the counterweight actuator is coupled with both the movable mirror and the counterweight.
Yet still another feature of the present application includes wherein the telescopic payload is oriented toward a forward end of the orbital vehicle such that a center of mass of the orbital vehicle is forward of a geometric center determined from a planform shape of the orbital vehicle.
Yet still another feature of the present application includes wherein the at least one fin includes an extension on opposing lateral sides of the orbital vehicle.
Yet still another feature of the present application includes wherein the at least one fin includes at least one of a solar array and an antenna.
Yet still another feature of the present application includes wherein at least one fin includes a material composition structured to discourage degradation from energetic particles at orbital altitudes.
Yet still another feature of the present application includes wherein the Hall-effect thruster can be operated in a mode to change the charge potential of the orbital vehicle.
Yet still another feature of the present application includes wherein the at least one fin can be a single construction affixed to a top of the orbital vehicle and which extends past lateral edges of the longitudinally oriented body.
Yet still another feature of the present application includes wherein the at least one fin can be oriented at an angle to a lateral axis of the orbital vehicle such that it has an anhedral arrangement relative to the direction of travel and the location of Earth during orbit.
Yet still another feature of the present application includes wherein the at least one fin is a single fin, and wherein the single fin protrudes laterally from the longitudinally oriented body.
Yet still another feature of the present application includes wherein the at least one fin includes three separate fins arranged about the circumferential periphery of the longitudinally oriented body.
Yet still another feature of the present application includes wherein the at least one fin extends out the top of the longitudinally oriented body.
Yet still another feature of the present application includes wherein the at least one fin extends out the rear of the longitudinally oriented body to form a shuttlecock configuration.
Yet another aspect of the present application includes a method comprising: propelling an orbital vehicle with a Hall-effect thruster along a path of flight of the orbital vehicle, the orbital vehicle having a telescopic payload disposed in an interior of the orbital vehicle that extends along a longitudinal axis of the orbital vehicle, the telescopic payload located toward a forward end of the orbital vehicle such as to create a stabilizing location of the center of mass, and imagining the Earth with the telescopic payload as the orbital vehicle is orbiting, wherein the imaging the Earth includes viewing the Earth with the telescopic payload at a right angle direction to the longitudinal axis, and turning an optical path from the right angle direction to the longitudinal axis using a first mirror.
A feature of the present application includes wherein the first mirror is one of a simple flat mirror and a powered mirror, and which further includes moving the first mirror relative to the longitudinally oriented body of the orbital vehicle.
Another feature of the present application further includes rotating the first mirror about the longitudinally oriented body to change a relative angle between an optical path produced by the first mirror and the longitudinally oriented body.
Still another feature of the present application further includes operating an inertia nulling mechanism which is coupled with the first mirror such that when the first mirror is moved the inertia nulling mechanism provides a counter movement to produce a counter torque to a torque produced when the first mirror is moved.
Yet another feature of the present application includes wherein the inertia nulling mechanism includes a counterweight.
Still yet another feature of the present application includes wherein the counterweight is mechanically coupled with the movable mirror through at least one mechanical link.
Yet still another feature of the present application includes moving the counterweight in a configuration in which the counterweight is mechanically isolated from an actuator that drives the first mirror, and wherein the counterweight is movable via a counterweight actuator.
Yet still another feature of the present application includes wherein the counterweight actuator is coupled with both the movable mirror and the counterweight.
Yet still another feature of the present application includes wherein the at least one fin includes an extension on opposing lateral sides of the orbital vehicle.
Yet still another feature of the present application includes wherein the at least one fin includes at least one of a solar array and an antenna.
Yet still another feature of the present application includes wherein at least one fin includes a material composition structured to discourage degradation from energetic particles at orbital altitudes.
Yet still another feature of the present application further includes operating the Hall-effect thruster in a mode to change the charge potential of the orbital vehicle.
While embodiments of the disclosure have been illustrated and described in detail in the drawings and foregoing description, the same is to be considered as illustrative and not restrictive in character, it being understood that only the preferred embodiments have been shown and described and that all changes and modifications that come within the spirit of the inventions are desired to be protected. It should be understood that while the use of words such as preferable, preferably, preferred or more preferred utilized in the description above indicate that the feature so described may be more desirable, it nonetheless may not be necessary and embodiments lacking the same may be contemplated as within the scope of the invention, the scope being defined by the claims that follow. In reading the claims, it is intended that when words such as “a,” “an,” “at least one,” or “at least one portion” are used there is no intention to limit the claim to only one item unless specifically stated to the contrary in the claim. When the language “at least a portion” and/or “a portion” is used the item can include a portion and/or the entire item unless specifically stated to the contrary. Unless specified or limited otherwise, the terms “mounted,” “connected,” “supported,” and “coupled” and variations thereof are used broadly and encompass both direct and indirect mountings, connections, supports, and couplings. Further, “connected” and “coupled” are not restricted to physical or mechanical connections or couplings.
The present application claims the benefit of U.S. Provisional Patent Application Ser. No. 63/279,872, filed Nov. 16, 2021, which is incorporated herein by reference in its entirety.
Number | Date | Country | |
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63279872 | Nov 2021 | US |