INTERPLANETARY SPACECRAFT

Abstract

Disclosed is a modular, human-crewed interplanetary spacecraft that is assembled in cislunar space. It is primarily comprised of a hollowed-out asteroid; five expandable habitation modules, one of which is expanded inside the asteroid cavity; two docking and airlock nodes; two landing craft suitable for exploring celestial bodies; structural support members; truss structures; robotic arms; a propulsion module; and shielding curtains that are filled with pulverized asteroidal material and attached to the truss structure. This configuration provides substantial radiation and meteoroid shielding. Upon completion of their mission, the crew will use the robotic arms to disconnect and mate (1) the asteroid containing the control module, (2) the forward docking and airlock node, and (3) the propulsion module. This crew-return vehicle will return to cislunar space. The remaining expandable modules with trusses, robotic arms, and landing craft will remain in the destination orbit to serve as a space station for future missions.

Claims

1. A human-crewed interplanetary spacecraft that is capable of being launched from an Earth-Moon Lagrangian point to an orbit around a celestial body such as the Moon or Mars, comprising: a hollowed-out asteroid with walls at least two meters thick; five expandable habitation modules, one of which (Module #1) is expanded inside the asteroid cavity and mated to a forward docking-and-airlock node which is described below, the opposite side of said forward docking-and-airlock node being docked and mated to Module #2, the opposite end of said Module #2 being docked and mated to Module #3, the opposite end of said Module #3 being docked and mated to Module #4, the opposite end of said Module #4 being docked and mated to the aft docking-and-airlock node, the opposite side of said aft docking-and-airlock node being docked and mated to Module #5, the opposite end of said Module 5# being mated to the propulsion mounting plate which is described below; two identical docking-and-airlock nodes that include an airlock at the zenith of the node, two docking ports that are compatible with the NASA Docking System/International Docking Standard, one on each side of the node, and two docking ports that are capable of docking and mating with the expandable modules, one on each end of the node, said docking and airlock nodes being docked and mated between habitation Modules #1 and #2 (forward docking-and airlock node), and between Modules #4 and #5 (aft docking-and-airlock node); A mounting plates that is affixed to the inside of the asteroid to support the forward end of Module #1; A mounting plate that is attached to the propulsion module which is described below, said mounting plate having four openings such that one truss can be passed through each opening, said trusses then being attached to the sides of the propulsion module; a sealing plate having four openings such that one truss can be passed through each opening, and an opening in the center that will support the aft end of Module #1, said sealing plate being affixed to the asteroid to seal the expandable Module #1 inside the asteroid; deployable structural support members that are mounted on the aft end of Module #1, and mounted on both ends of Modules #2, #3, #4, and #5; trusses similar or identical to those used on the International Space Station; two Mobile Transporter Carts, and the attached Mobile Remote Servicer Base Systems (MBS) similar or identical to those used on the International Space Station, said Mobile Transporter Carts and MBSs being attached to and capable of moving along rails attached to the upper trusses on the starboard side of the spacecraft; two robotic arms similar or identical to the International Space Station Canadarm 2, each of said robotic arms being attached to a Mobile Remote Servicer Base System, which in turn is supported by the Mobile Transporter Cart, said robotic arms and support systems being capable of moving along rails affixed to the spacecraft's upper truss structure on the starboard side of the spacecraft, thereby permitting the forward robotic arm to be positioned anywhere from the center of the spacecraft to the forward end of Module #2, and the aft robotic arm to be positioned anywhere from the center of the spacecraft to the aft end of Module #5; two dexterous end-effectors that can be attached to the ends of the robotic arms, similar or identical to the Special Purpose Dexterous Manipulator (SPDM, also known as Dextre) used on the International Space Station; grapple fixtures attached to various points on the spacecraft that permit the robotic arms to attach to the grapple fixtures during spacecraft maintenance and operational activities, including without limitation, for the purposes of detaching from the spacecraft, docking, and mating, in respective order from forward to aft, the asteroid and control Module #1, the forward docking and airlock node, and the propulsion Module #6, to form a Crew Return Vehicle; two vehicles suitable for landing on the surface of celestial bodies that are docked to the port and starboard sides of the aft docking and airlock node; primary solar arrays that are attached to the lower trusses adjacent to the junction of habitation modules #3 and #4; secondary solar arrays that are attached to the lower trusses on the port and starboard sides of the asteroid superstructure; sensors, communications equipment, and cameras; a primary computer network that is installed in the control module and connected to all spacecraft systems; a secondary computer networks that is installed in Module #3 and connected to all spacecraft systems; spherical storage tanks that are attached to the rear trusses in the asteroid superstructure, and attached to the four trusses immediately forward of the propulsion mounting plate; attitude control thrusters mounted on the asteroid truss superstructure, and at various other points on the trusses as are necessary to maneuver the spacecraft; a propulsion module that incorporates the propulsion technology or technologies best-suited to accomplish the spacecraft's missions, mounted on the aft side of the propulsion mounting plate and affixed to the four trusses that pass through the mounting plate; and four channeled radiation-shielding curtains that are filled with pulverized asteroidal material and attached to the spacecraft trusses on all four sides of the spacecraft aft of the control module sealing plate.

2. A modular interplanetary spacecraft according to claim 1, wherein the expandable habitation modules can be docked and mated utilizing a transporter tug.

3. A modular interplanetary spacecraft according to claim 1, wherein the expandable habitation modules can autonomously dock and mate.

4. A modular interplanetary spacecraft according to claim 1, wherein some or all of the spacecraft assembly tasks are performed by robots.

5. A modular interplanetary spacecraft according to claim 1, wherein said spacecraft includes chemical propulsion.

6. A modular interplanetary spacecraft according to claim 1, wherein said spacecraft includes solar electric propulsion.

7. A modular interplanetary spacecraft according to claim 1, wherein said spacecraft includes beamed energy propulsion.

8. A modular interplanetary spacecraft according to claim 1, wherein said spacecraft includes solid-fuel booster rockets that are attached to the outside of the propulsion module and utilized as a supplemental form of propulsion to attain initial velocity, said booster rockets then being jettisoned after firing.

9. A modular interplanetary spacecraft according to claim 1, wherein said spacecraft includes a magnetic field generator that provides additional radiation shielding for the spacecraft and its crew.

10. A modular interplanetary spacecraft according to claim 1, wherein one habitation module includes greenhouse equipment suitable for growing plants.

11. A modular interplanetary spacecraft according to claim 1, wherein one habitation module includes scientific equipment, equipment racks, benches, and specimen containers suitable for use as a laboratory.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0052] FIG. 1 is a cross-sectional view of the hollowed-out asteroid with the expandable control module mounted inside the asteroid, in its un-expanded mode.

[0053] FIG. 2 is a cross-sectional view of the hollowed-out asteroid with the expandable module in its expanded mode.

[0054] FIG. 3 is a front view of the control module sealing plate.

[0055] FIG. 4 is a top view of the hollowed-out asteroid and expandable module, with truss superstructure, solar panels, and external equipment.

[0056] FIG. 5A. is a front view of the module structural support member in its stowed position. FIG. 5B is a front view of the module structural support member in its deployed position.

[0057] FIG. 6 is a top view of modules #2 through #5, with truss structure, docking nodes, landers, and robotic arms.

[0058] FIG. 7A is a top view of the propulsion module, and FIG. 7B is a front view of the propulsion mounting plate.

[0059] FIG. 8 is a top view of the assembled spacecraft.

[0060] FIG. 9A is a top view of the assembled spacecraft with channeled shielding curtains attached to the truss structure. FIG. 9B is a front view of a portion of the channeled shielding curtain.

[0061] FIG. 10 is a top view of the robotic arms disconnecting the control module, the forward docking and airlock node, and the propulsion module.

[0062] FIG. 11 is a top view of the robotic arms mating the command module and docking assembly to the propulsion module, comprising the Crew-Return Vehicle. FIG. 11 also shows the remaining modules, support members, trusses, nodes, landers, and robotic arms that will remain at the destination orbit to serve as a space station.

DETAILED DESCRIPTION OF THE INVENTION

1. Definition

[0063] The American Heritage Science Dictionary defines “Lagrangian Point” as “A point in space where a small body with negligible mass under the gravitational influence of two large bodies will remain at rest relative to the larger ones. In a system consisting of two large bodies (such as the Sun-Earth system or the Moon-Earth system), there are five Lagrangian points (L1 through L5). Knowledge of these points is useful in deciding where to position orbiting bodies” (http://www.dictionary.com/browse/Lagrangian-point accessed May 24, 2017).

2. Best Mode of the Invention

[0064] FIG. 8 shows a top view of the fully-assembled spacecraft with channeled shielding curtains attached to the truss structure. FIG. 11 is a top view of the robotic arms mating the command module and docking and airlock node to the propulsion module to form a Crew-Return Vehicle, and the remaining modules, support members, trusses, nodes, landers, and robotic arms that will remain at the destination orbit to serve as a space station. Together these figures illustrate the best mode contemplated by the inventor, according to the concepts of the present invention.

3. How to Make the Invention

[0065] Pursuant to a prize competition or contract, a commercial space-mining company or other organization will hollow-out an asteroid with walls a minimum of 2 meters thick 4, and will transport the hollowed-out asteroid 4 to the Staging and Assembly area.

[0066] Launch vehicles will transport five expandable habitation modules 1 from the surface of the Earth to the Staging and Assembly area, with a mounting plate 5 and a sealing plate 2 attached to module #1, as shown in FIG. 2, and stowed structural support members 12 attached to both ends of modules #2 through #5.

[0067] The expandable module operator will maneuver Module #1 and the attached mounting plate 5 and sealing plate 2 so that the expandable module is beside the asteroid. The spacecraft assembly crew will remove the mounting plate 5 from module #1, and securely attach the mounting plate 5 to the inside of the hollow asteroid 4, as shown in FIG. 1.

[0068] The expandable module operator will then maneuver unexpanded module #1 so that it is firmly seated inside the mounting plate 5, and the sealing plate 2 is lined up so that the truss beams 3 can pass through the holes in the sealing plate 2. The assembly crew will then pass the trusses 3 through the sealing plate 2, and attach the sealing plate 2 so that it is flush with the outside of the asteroid, as shown in FIG. 1.

[0069] The spacecraft assembly crew will then dock and mate the forward docking and airlock node 17 to module #1, and attach the trusses that pass through the sealing plate 2 to the docking and airlock node 17, as shown in FIG. 7.

[0070] The expandable module operator will maneuver or initiate maneuver of modules #2 through #4, one at a time, so that module #2 docks and mates with the forward docking and airlock node 17, module #3 docks and mates with module #2, and module #4 docks and mates with module #3, as shown in FIG. 7.

[0071] The spacecraft assembly crew will then dock and mate the aft docking and airlock node 17 with module #4, and maneuver module #5 so that it docks and mates with the aft docking and airlock node 17, as shown in FIG. 7.

[0072] The expandable module operator will then pressurize each module, beginning with the control module, and then sequentially pressurizing modules #2 through #5.

[0073] Launch vehicles will transport to the Staging and Assembly area trusses 3, sensors 6, imaging cameras 7, communications equipment 8, attitude control thrusters 9, secondary solar arrays 11, spherical storage tanks 20, and components of the primary computer network 23 and secondary computer network 24.

[0074] As shown in FIG. 4B, the expandable module operator will then deploy the structural support members 12 that are attached to modules #2 through #5.

[0075] The spacecraft assembly crew will then attach trusses 3 to the deployed structural support members 12 on modules #2 through #5, as shown on FIG. 7. The assembly crew will also attach the trusses 3 to the aft docking and airlock node 17.

[0076] The assembly crew will then attach the secondary solar arrays 11 to the lower trusses in the asteroid truss superstructure, as shown in FIG. 4.

[0077] The assembly crew will then attach and install sensors 6, communications equipment 8, imaging cameras 7, attitude control thrusters 9, and spherical storage tanks 20.

[0078] A launch vehicle will transport the primary solar arrays 16 to the Assembly and Staging Area.

[0079] The assembly crew will then attach the primary solar arrays 16 to the lower trusses 3 adjacent to the junction of habitation modules #3 and #4, as shown in FIG. 8.

[0080] A launch vehicle will transport the propulsion module 19 and propulsion mounting plate 21, as shown in FIGS. 7A and 7B, to the Staging and Assembly area.

[0081] The spacecraft assembly crew will then maneuver the propulsion module 19 and propulsion mounting plate 21 so that the four trusses 3 attached to the module #5 structural support members 12 pass through the openings in the propulsion mounting plate 21. The assembly crew will then attach the four trusses 3 to the sides of the propulsion module 19, as shown in FIGS. 7A and 8.

[0082] The assembly crew will then install primary computer network 23 in the control module, and the secondary computer network 24 in Module #3. They will then install various software packages, wire the various systems together, power all of the systems, and test them. Each of the computer networks will be capable of controlling all of the spacecraft's systems, providing redundancy until the modules are separated during the process of docking and mating the elements of the Crew Return Vehicle. Thereafter, the primary computer network will control the Crew Return Vehicle, and the secondary computer network will control the remaining modules that remain in the destination orbit.

[0083] One or more launch vehicles will transport scientific equipment, experiments, food, water, and other supplies to the Staging and Assembly area.

[0084] The assembly crew will then load the equipment, experiments, and supplies into modules #1 through #5.

[0085] Finally, the spacecraft assembly crew will fuel the spacecraft. If chemical propulsion is used, liquid hydrogen and oxygen may be purchased from a commercial space mining and processing company, or purchased from the operator of a fuel depot at the Staging and Assembly area. The interplanetary spacecraft is now ready to embark upon a historic journey.

4. How to Use the Invention

[0086] The assembled spacecraft can be used to safely transport humans from Earth-Moon Lagrangian points L4 or L5 to deep-space destinations such as the Moon and Mars. During the flight through deep space, the crew and passengers will primarily inhabit the expandable control module #1 inside the asteroid 4, for maximum radiation protection.

[0087] Upon arrival at their destination, the crew and passengers can utilize the lander spacecraft 15 docked to the aft docking node 17 for short-term trips to neighboring celestial bodies, which might include the Moon, Phobos, Deimos, and/or Mars.

[0088] Owner/operators of the interplanetary spacecraft may offer a prize for, or execute a contract with a commercial space mining company or other organization to deliver an ice-bearing asteroid with attached in situ resource utilization (ISRU) equipment to the interplanetary spacecraft's destination orbit, prior to arrival of the interplanetary spacecraft. Either during transport from cislunar space, or at the destination orbit, the ISRU equipment can remove water from the asteroid and break it up into hydrogen and oxygen for use as rocket fuel for the Crew-Return Vehicle. In the alternative, the commercial mining company or other organization could mine and process the water at the asteroid's original location, and then deliver tanks of hydrogen and oxygen to the interplanetary spacecraft's destination orbit.

[0089] Upon completion of their work at the destination orbit, as shown in FIG. 10, the crew of the interplanetary spacecraft will use the forward robotic arm 18 and grapple fixtures 10 to detach from module #2 the asteroid 4 containing the control module 1 and the attached forward docking and airlock node 17. The crew will use the aft robotic arm 18 and grapple fixtures 10 to detach the propulsion module 19 and propulsion mounting plate 21 from module #5. As shown in FIG. 11, the crew will then use the robotic arms 18 and grapple fixtures 10 to maneuver and mate the propulsion module 19 and mounting plate 21 to the forward docking and airlock node 17, with attached asteroid 4 and control module 1. These three modules (asteroid/control module+docking and airlock node+propulsion module) will comprise a Crew-Return Vehicle that will return the crew to the Staging and Assembly area.

[0090] After mating the Crew-Return Vehicle modules, the crew will refuel the propulsion module, if the module includes chemical propulsion. The crew will then return to the Staging and Assembly area in the Crew-Return Vehicle.

[0091] A space capsule launched from Earth will rendezvous and dock with the crew-return vehicle at the Staging and Assembly area. The crew will then return to the Earth's surface in the capsule. The crew-return vehicle will remain at the Staging and Assembly area for use in future missions.

5. Examples of the Invention

[0092] Thus it will be appreciated by those skilled in the art that the present invention is not restricted to the particular best mode embodiments described with reference to the drawings, and that variations may be made therein without departing from the scope of the present invention as defined in the appended claims and equivalents thereof.