The present invention relates to space transport, and more particularly, to transporting or delivering mass from Earth to space and beyond.
When the United States sent men to the Moon in the 1960s and 1970s, the architecture consisted of the following steps. First, the launch vehicle (Saturn V) and upper stage launched the Command and Service Module (CSM) and the Lunar Module (LM) onto a trajectory to arrive at the Moon. Three (3) days later, they arrive at the far side of the Moon and a lunar orbit insertion maneuver is performed to put the CSM and LM into orbit around the Moon. The LM is then undocked from the CSM and landed on the surface of the Moon. A day later, the LM ascends from the surface of the Moon and docks with the CSM. The astronauts all move aboard the CSM, and the LM is jettisoned to be discarded. The CSM then performs a maneuver to return to the Earth. At Earth, the Command Module, containing the astronauts, separates from the Service Module, and the Command Module then reenters the atmosphere.
Architectures to transport humans and cargo to the Moon that are currently being considered are slightly more complex, but not all that different from the Apollo era architecture. For example, the Artemis architecture (missions being prepared to go to the Moon in 2024 timeframe) is as follows:
These Apollo and Artemis architectures are appropriate for sending a handful of missions to the Moon. Apollo performed 6 manned landings on the Moon, and the Artemis project's current plans for approximately the same number of landings on the Moon. The end goal of Artemis (and other proposed lunar missions), however, is to establish a permanent human presence on the Moon. After this presence is established, there needs to be a system to regularly and efficiently transport humans from the surface of the Earth to the surface of the Moon and back. Thus, a space transport system is needed.
Certain embodiments of the present invention may provide solutions to the problems and needs in the art that have not yet been fully identified, appreciated, or solved by current space transport technologies. Some embodiments generally pertain to a space transport system configured to deliver mass, such as cargo, payload, satellites, and/or passengers, from Earth to space and beyond. For example, the space transport system may deliver humans, cargo, and/or satellites from the surface of the Earth to LEO, GEO, Lunar Orbit, and/or the Lunar surface with the option and/or capability to return humans, cargo, and/or satellites to the surface of the Earth.
In an embodiment, a space transport system includes one or more cyclers orbiting between a first planetary body and another planetary body. The space transport system also includes one or more taxi vehicles, each of which carry cargo, humans, or both. The one or more taxi vehicles dock with the one or more cyclers and undock with the one or more cyclers when landing on the first planetary body or the second planetary body.
In another embodiment, a process for transporting or delivering cargo, humans, or both between a first planetary body and a second planetary body includes launching one or more cyclers from Earth and into space. The process also includes configuring the one or more cyclers to enter a cycling trajectory between Earth or a first planetary body and a second planetary body, and docking a taxi vehicle with the one or more cyclers to transport the taxi vehicle from Earth or the first planetary body and to the second planetary body.
In order that the advantages of certain embodiments of the invention will be readily understood, a more particular description of the invention briefly described above will be rendered by reference to specific embodiments that are illustrated in the appended drawings. While it should be understood that these drawings depict only typical embodiments of the invention and are not therefore to be considered to be limiting of its scope, the invention will be described and explained with additional specificity and detail through the use of the accompanying drawings, in which:
Some embodiments generally pertain to a space transport system that uses one or more cycler vehicles (hereinafter “cyclers”) on a cycling trajectory to repeatedly deliver and return humans and cargo to and from a lunar planet. The cyclers are designed to safely transport humans, clean air, and water, and provide ample radiation protection to the cargo, humans, or both. The cyclers may autonomously perform any and all propulsive maneuvers required for station keeping purposes.
In some embodiments, the cycler may contain mass required of a transport, but only needs to be launched once. That is, the cycler is reusable for multiple missions to and from the Moon. Further, multiple cyclers may be launched in space and designed to follow the similar orbit as the other cyclers. This may allow for frequent transport of smaller taxi vehicles. The smaller taxi vehicles may carry crew or cargo to and from the cycler. These taxi vehicles are smaller in size than spacecraft usually required to deliver humans and cargo from the Earth to the Moon, thus reducing the amount of propellant.
The launch of multiple taxi vehicles and cyclers may be referred to as string of pearls. For example, the string of pearls concept means that there are multiple cyclers on the cycling trajectory, just at different times. This way, the cyclers can transport multiple taxi vehicles.
Relay to Mars
Once the cycler vehicle is on its lunar cycling trajectory, if it is desirable to send it to Mars, a flyby of the Moon can be targeted that will impart energy to help the vehicle escape the Earth's gravity and transition to an orbit around the Sun. It will take more energy to get the vehicle onto the proper Mars cycling orbit, so the vehicles engines will be used to impart that energy. It will not be orbiting Mars, instead it will be on an Earth-Mars cycling trajectory (similar to the Earth-Moon cycling trajectory it was originally used for). An Earth-Mars cycling trajectory is an orbit around the Sun that encounters the Earth and Mars regularly. The Earth-Mars orbit can vary, but in general it will take about 6 months to get from the Earth to Mars and the period of the orbit is 2 1/7 years.
Cycler
In some embodiments, cycler 900 includes a flight control compartment 902, a storage compartment 904, and a cabin 906 for passengers. Cycler may also include a hull 908. Although this embodiment illustrates a flight control compartment 902 for human pilots; other embodiments may be fitted with autopilot controls. Storage compartment 904 may be used for holding science experiments, extra equipment, consumables for the crew, items to be discarded, or any other item that does not have a permanent place onboard. Cabin 906 may include one or more sleeping cabins for the passenger(s).
In certain embodiments, a radiation shield 910 surrounds cycler 900 to protect passengers and/or cargo from radiation (e.g., Van Allen radiation belts). Radiation shield 910 is a passive shield in so far that it includes a mass between the radiation sources and the crew. Radiational shield 910 may be composed of water, e.g., one or more separated layers of drinking water and water that has yet to be recycled. In another embodiment radiation shield 910 may be composed of one or more separated layers of metals such as aluminum, copper, tantalum, etc. Radiation shield 910 is sufficient to reduce the radiation that a person would otherwise be exposed to from the Van Allen radiation belts to acceptable levels. In some additional embodiments, cycler 900 may include a smaller, more heavily shielded area in or near cabin 906 for higher level radiation events such as a solar flare.
Near the front end of cycler 900 are additional storage compartments 912 and a waste and hygiene compartment 914. Additional storage compartments 912 may serve a similar purpose as storage compartment 904.
Near the rear of cycler 900 are a plurality of propellant tanks 916. Thrusters 918 protruding from rear of cycler 900 may provide directional thrust.
Solar arrays 920 are also included on cycler 900. These solar arrays 920 may provide power to run the spacecraft subsystems, such as life support and propulsion. In other embodiments, a nuclear reactor may be used to provide power. In some embodiments, cycler 900 may include four solar arrays sized for a 20 percent end-of-life (EOL) power margin.
Taxi Vehicle
In certain embodiments, taxi vehicle 1000 can be used as extra space during the journey between the Earth and the Moon. Further, taxi vehicle 1000 is reusable for many missions between the cycler and the surface of a planetary body. Embodiments may require propellants to be supplied at regular intervals.
Taxi vehicle 100 may rendezvous with the cycler directly from the Earth after being launched on a launch vehicle. In another embodiment, taxi vehicle 1000 may ferry crew between space stations in orbit of the Earth or Moon to the cycler vehicle.
In
Depending on the embodiment, when taxi 1104 rendezvous with cycler 1102, the change in velocity (ΔV) required to be performed by taxi 1104 to rendezvous with the cycler 1102 may be 3.41 km/s. This change is velocity is dependent on several factors, including the initial and final orbit altitudes of taxi 1104 and the velocity of cycler 1102. The maneuvers undertaken by taxi 1104 include, but are not limited to, raising the altitude of its orbit to correspond to the same orbit altitude of the cycler 1102 and to match the velocity and position of the cycler 1102. Once the velocity and position of cycler 1102 and taxi 1104 are the same, the two spacecraft will physically attach via a mechanical interface.
Depending on the embodiment, when cycler 1102 is proximate to another low orbit station 1108 or another planetary object, taxi 1104 may undock from cycler 1102 and dock with another low orbit station 1108 or begin decent into the atmosphere of the other planetary object. In this embodiment, the lunar orbit (LO) altitude of station 1108 may be 100 km. Again, this altitude may depend on the size of the planet and orbit of the cycler.
The rendezvous of taxi 1104 and station 1108 may require taxi 1104 to perform a ΔV of 1.55 km/s. When taxi 1104 docks with station 1108, taxi 1104 may refuel, allowing taxi 1104 to have sufficient amount of fuel to land on the surface of the other planet and return to station 1108. The lunar landing speed of taxi may require a ΔV at 1.95 km/s.
Sometime later, when cycler 1102 has completed a number of orbits around the Earth and returns to the Moon, taxi 1104 may depart from the surface of the Moon to begin the return to Earth in the reverse order of events required to deliver it to the surface of the Moon. for example, taxi 1104 docks with station 1108 and then refuels. Taxi 1104 may then depart from station 1108 to rendezvous and dock with cycler 1102. When cycler 1102 and taxi 1104 return to the vicinity of the Earth, taxi 1104 undocks from cycler 1102 and perform a ΔV to return to the surface of the Earth.
The rear of cycler 1400 comprises propellant tank(s) 1404. In an embodiment, electric propulsion is used with a propellant such as xenon. The advantages of electric propulsion are its efficiency (requiring less propellant mass than other propulsion methods for some orbits) and the ease of propellant storage. In another embodiment, a chemical rocket engine is used with a combination of liquid hydrogen and liquid oxygen as propellant. The advantage of this chemical engine is that very high values of thrust can be imparted upon the spacecraft.
Some embodiments generally pertain to one or more cyclers orbiting between a first planetary body and second planetary body. In some further embodiments, one or more taxi vehicles carrying cargo, humans, or both, dock with the one or more cyclers and undock with the one or more cyclers when landing on the first planetary body or the second planetary body.
It will be readily understood that the components of various embodiments of the present invention, as generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations. Thus, the detailed description of the embodiments, as represented in the attached figures, is not intended to limit the scope of the invention as claimed, but is merely representative of selected embodiments of the invention.
The features, structures, or characteristics of the invention described throughout this specification may be combined in any suitable manner in one or more embodiments. For example, reference throughout this specification to “certain embodiments,” “some embodiments,” or similar language means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment of the present invention. Thus, appearances of the phrases “in certain embodiments,” “in some embodiment,” “in other embodiments,” or similar language throughout this specification do not necessarily all refer to the same group of embodiments and the described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.
It should be noted that reference throughout this specification to features, advantages, or similar language does not imply that all of the features and advantages that may be realized with the present invention should be or are in any single embodiment of the invention. Rather, language referring to the features and advantages is understood to mean that a specific feature, advantage, or characteristic described in connection with an embodiment is included in at least one embodiment of the present invention. Thus, discussion of the features and advantages, and similar language, throughout this specification may, but do not necessarily, refer to the same embodiment.
Furthermore, the described features, advantages, and characteristics of the invention may be combined in any suitable manner in one or more embodiments. One skilled in the relevant art will recognize that the invention can be practiced without one or more of the specific features or advantages of a particular embodiment. In other instances, additional features and advantages may be recognized in certain embodiments that may not be present in all embodiments of the invention.
One having ordinary skill in the art will readily understand that the invention as discussed above may be practiced with steps in a different order, and/or with hardware elements in configurations which are different than those which are disclosed. Therefore, although the invention has been described based upon these preferred embodiments, it would be apparent to those of skill in the art that certain modifications, variations, and alternative constructions would be apparent, while remaining within the spirit and scope of the invention. In order to determine the metes and bounds of the invention, therefore, reference should be made to the appended claims.
This application claims the benefit of U.S. Provisional Application No. 62/899,221, filed on Sep. 12, 2019. The subject matter thereof is hereby incorporated herein by reference in its entirety.
Number | Date | Country | |
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62899221 | Sep 2019 | US |