Classifications

• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
  • B64G1/00—Cosmonautic vehicles
  • B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
  • B64G1/1085—Swarms and constellations
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
  • B64G1/00—Cosmonautic vehicles
  • B64G1/002—Launch systems
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
  • B64G1/00—Cosmonautic vehicles
  • B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
  • B64G1/105—Space science
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
  • B64G1/00—Cosmonautic vehicles
  • B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
  • B64G1/105—Space science
  • B64G1/1064—Space science specifically adapted for interplanetary, solar or interstellar exploration
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
  • B64G1/00—Cosmonautic vehicles
  • B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
  • B64G1/105—Space science
  • B64G1/1064—Space science specifically adapted for interplanetary, solar or interstellar exploration
  • B64G1/1071—Planetary landers intended for the exploration of the surface of planets, moons or comets
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
  • B64G1/00—Cosmonautic vehicles
  • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
  • B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
  • B64G1/244—Spacecraft control systems
  • B64G1/247—Advanced control concepts for autonomous, robotic spacecraft, e.g. by using artificial intelligence, neural networks or autonomous agents
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
  • B64G4/00—Tools specially adapted for use in space
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
  • B64G1/00—Cosmonautic vehicles
  • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
  • B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
  • B64G1/242—Orbits and trajectories
  • B64G1/2427—Transfer orbits

Definitions

• This invention relates to a Space Transport Architecture (STA) for robotic planetary operations.
• STA Space Transport Architecture
• the invention pertains to a space transport method for such operations.
• the invention pertains to an STA and method especially adapted for planetary exploration missions.
• the invention provides an architecture and method for carrying out short-term loosely coupled missions to a variety of planetary landing sites on each mission, e.g., sites which are local, regional or global.
• the invention provides for planetary exploration by a variety of robotic operational platforms using a variety of sensors, cameras, seismic devices and other payloads such as for sampling operations and the like.
• the invention relates to STAs and methods especially adapted for robotic collection of planetary geologic samples and for returning such samples to Earth.
• NASA developed methods and techniques- of scientific investigation on the surface of a planet based on, for the most part, the facilities and capabilities of human beings in situ. Robotics, at the time, had not evolved to the point of being able to challenge the facilities and capabilities of humans.
• Such architecture would include not only flexible mobile, and responsive platforms on the surface, which apply the proven methods and techniques of Apollo scientific investigations, but also a low-cost, near-term, reliable space transportation system.
• the principal object of the present invention is to provide a space transport architecture (STA) for robotic planetary operations.
• STA space transport architecture
• Another object of the invention is to provide a transport method for carrying out such robotic planetary operations.
• Still another object of the invention is to provide a space transport architecture and method which is specially adapted to carry out robotic exploration of planets.
• Still another and more particular object of the invention is to provide a space transportation architecture and method for conducting planetary geophysical exploration.
• a further and still more specific object of the invention is to provide a space transportation architecture and method for robotically collecting planetary geophysical specimens and samples and returning them to the Earth.
• Fig. 1 is a partially cut away view of assembled components which typify the space transport architecture of the invention, according to one embodiment of the invention
• Fig. 2 is a schematic representation of the components of the assembled STA of Fig. 1;
• Fig. 3 illustrates a typical mission scenario utilizing the STA and method of the invention to conduct robotic planetary operations
• Fig. 4 depicts typical orbital mechanics applications for conducting robotic planetary surface operations at local, regional and global landing sites
• Fig. 5 depicts a typical mission scenario utilizing the STA and method of the present invention to dispense multiple robotic operational platforms at a plurality of sites on a planet;
• Fig. 6 illustrates a typical mission scenario involving collection and return to earth of planetary geologic samples.
• ELV earth launch vehicle
• LEO low earth orbit
• Such ELVs are constructed to withstand dynamic atmospheric effects such as wind, rain, turbulence, ice, shear and lightening, and the pressure and thermal effects of atmospheric drag during earth ascent.
• ELVs include rocket systems which may consist of two or more "stages", each of which is dropped during the ascent phase of the launch sequence when its propellant is expended, thus reducing the dead weight of the vehicle. These stages may be mounted in tandem or "strapped-on" the outside of the core first stage.
• Most ELVs presently used commercially are either duplicates or derivatives of Intercontinental Ballistic Missiles (ICBMS) developed during the 1950's and 1960's and which were designed to deliver a payload to a ballistic space trajectory or to LEO.
• IBMS Intercontinental Ballistic Missiles
• space transfer vehicle means a rocket vehicle, typically including a main engine, attitude control, guidance and communications systems, fuel supplies, etc., usually constructed as an exoatmospheric vehicle because it is only subjected to relatively static conditions in space such as radiation from the sun and bombardment by my new particular matter.
• STVs are adapted to carry payloads from LEO to other space trajectories, including transplanetary trajectories and planetary orbit insertion and maybe configured for planetary descent and ascent operations.
• Typical STVs include the Viking Orbiter, Peacekeeper Stage IV, and the Satellite Transfer Vehicles disclosed in U.S. Patents 4,896,848 and 4,664,343.
• the ELV-STV components of the STA are those disclosed in pending USA application S/N 472,395, filed January 30, 1990 entitled "Space Transfer Vehicle and Integrated Guidance Launch System".
• planetary lander means apparatus for carrying payloads distributed from an STV in planetary orbit to a landing on the surface of the plant and includes both ballistic vehicles such as the Ranger V Lunar Landing Capsule and maneuverable vehicles, for example, an STV adapted or planetary descent and landing or the Rockwell "lightweight exoatmospheric projectile" known as LEAP-I developed in the SDI program.
• ballistic vehicles such as the Ranger V Lunar Landing Capsule and maneuverable vehicles, for example, an STV adapted or planetary descent and landing or the Rockwell "lightweight exoatmospheric projectile" known as LEAP-I developed in the SDI program.
• the robotic operational platforms used in accordance with the present invention may, illustratively, include both mobile and fixed platforms.
• mobile platforms include the rovers described in the paper entitled “Mini-Rovers for Mars Exploration", proceedings of the Vision-21 Symposium, Cleveland, Ohio, April, 1990. And the papers therein cited. • Further examples of mobile rovers include the “ROBBY” developed by JPL.
• fixed robotic operational platforms include "MESUR”, proposed by NASA for the Mars scientific station and pentatrometers used on the USSR Mars Probe.
• I provide a space transport architecture (STA) for robotic operations on a planet.
• the STA comprises an earth launch vehicle (ELV) , adapted to carry a space transfer vehicle (STV) and associated payloads into low earth orbit (LEO) .
• the space transfer vehicle (STV) carried by the ELV, is adapted to carry associated payloads from LEO into planetary orbit and to dispense these payloads from planetary orbit for landing in the locus of at least one planetary exploration site.
• At least one planetary lander is carried by the STV.
• the lander is adapted to carry a plurality of robotic operational platforms and deploy these platforms in the locus of the exploration site.
• a plurality of robotic operational platforms is carried by each of the landers.
• the STV comprises at least two stages, a first stage (STV-1) for insertion into transplanetary trajectory and an upper stage STV-2 for planetary orbit insertion.
• the STV-2 is the lander and is adapted for planetary descent, planetary touch down and platform deployment.
• the STA includes a plurality of landers and the STV is adapted to dispense each of said landers for landing in the locus of a different planetary exploration site.
• the STA includes a planetary ascent vehicle carried by the lander.
• the planetary ascent vehicle (PVA) is adapted to rendezvous in planetary orbit with an earth return vehicle (ERV) .
• the ERV is integral with the STV.
• the STA is adapted for geophysical exploration of the planet.
• at least one of the robotic operational platforms is adapted to obtain and deliver an geologic sample to the PAV and the PAV is adapted to deliver the sample to the ERV.
• I provide a method for conducting robotic planetary operations comprising launching from the earth a payload comprising a plurality of planetary landers, each lander carrying a plurality of robotic planetary operations platforms.
• the payload is inserted into planetary orbit and the landers are dispenses for landing at a plurality of sites on the planet. After landing, the plurality of robotic platforms are deployed from each lander at each of the exploration sites.
• a planetary geologic sample is collected by at least one of the robotic platforms and is transferred from the platform to an earth return vehicle.
• Fig. 1 and 2 depict an assembly of components which illustrate the STA.
• the ELV 10 illustratively a Delta II, comprises a first stage 11, a second stage 12 and thrust augmentation solid rocket motors 13, STV-1 14 and STV-2 15 are carried on ELV 10 within a protective payload faring 16.
• STV-1 14 is the STV disclosed in the '848 and '343 patents, identified above, and the STV-2 is the NASA Mars Viking Orbiter.
• Landers 17 can illustratively comprise a plurality of Rockwell LEAP-1 STV vehicles, each carrying a plurality of behavior controlled robotic mini rovers of the type described in the Vision 21 Symposium paper by David P. Miller of the JPL.
• Fig. 3 illustrates a typical mission scenario utilizing the STA of Fig. 1-2 according to the method of the invention.
• EALV propels the SDA through earth launch 31 into LEO 32.
• the STV is supported from the EALV and transports the associated payloads from LEO 32 in to transplanetary trajectory 33 and into planetary orbit 34.
• a lander is dispensed by the STV in to landing trajectory 35 for landing on the planet 36.
• planetary orbit 41 provides for a "local" landing site, 42, i.e., a single specific site for landing the maximum number of operational platforms.
• the number of platforms is maximized by minimizing the energy requirements to reach that site by proper selection of the inclination of the orbit 41, the launch window and other recognized factors.
• a higher orbit 43 is selected to provide "regional" landing sites 44 in an area 45, e.g., 1-4,000 Km of the planetary surface, each landing site accommodating a variable number of platforms, all near the path of the same orbital trajectory 43, disbursed by planetary rotation under the orbit 43.
• Global landing sites 46 are provided by selecting a polar or high inclination orbit 47. This orbit has the highest energy requirement thus lowest total launch mass of landers and platforms, dispersed by planetary rotation under the orbit 47.
• Fig. 5 further illustrates a mission scenario for distributing a plurality of platforms at global landing sites.
• the STA 51 is launched from earth 52 and the STV 53 carries multiple landers 54 through transplanetary trajectory 55 and accomplishes insertion into planetary orbit 56.
• a plurality of landers 57a - 57e are dispensed by STV 53 to a plurality of landing sites.
• a plurality of robotic operational platforms, e.g., mini rovers 58 are deployed to accomplish ultimate mission objectives, e.g., visual, seismic, geological and chemical investigations.
• Fig. 6 illustrates a typical mission scenario for geologic exploration of a planet 61.
• One or more STAs 62 are launched from earth, each carrying an STV 63 which distributes landers 64 at one or more planetary sites.
• the landers 64 are STVs which can accomplish planetary descent as indicated at 64a.
• the landers deploy mobile operational platforms 66.
• One or more of the platforms 66 collects geologic samples which are returned to the landers 66.
• a planetary ascent vehicle (PAV) 67 e.g., LEAP-1 carries the samples into planetary orbit, as indicated at 67a.
• PAV planetary ascent vehicle
• one or more STVs which function as Earth Return Vehicles (ERVs)
• ELVs Earth Return Vehicles
• the PAVs 67a - 67c rendezvous with the ERV 68 in planetary orbit 69, which collects the samples and returns the sample containers into LEO 70 from which that are ejected for parachute return 71 into the earth's atmosphere for recovery my high altitude aircraft 72.
• the STV 63 includes an ERV which functions both as the PAV and the ERV.

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• Engineering & Computer Science (AREA)
• Remote Sensing (AREA)
• Physics & Mathematics (AREA)
• Astronomy & Astrophysics (AREA)
• General Physics & Mathematics (AREA)
• Aviation & Aerospace Engineering (AREA)
• Automation & Control Theory (AREA)
• Life Sciences & Earth Sciences (AREA)
• Sustainable Development (AREA)
• Medical Informatics (AREA)
• Artificial Intelligence (AREA)
• Evolutionary Computation (AREA)
• General Health & Medical Sciences (AREA)
• Health & Medical Sciences (AREA)
• Robotics (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Radar, Positioning & Navigation (AREA)
• Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
• Warehouses Or Storage Devices (AREA)

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• 1991
  • 1991-05-28 JP JP4505127A patent/JPH05509057A/ja active Pending
  • 1991-05-28 EP EP92905495A patent/EP0596886A1/de not_active Withdrawn
  • 1991-05-28 WO PCT/US1991/003747 patent/WO1992021561A1/en not_active Application Discontinuation

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