WO2005073085A1 - Transport spatial en orbite et systeme de recuperation - Google Patents

Transport spatial en orbite et systeme de recuperation Download PDF

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Publication number
WO2005073085A1
WO2005073085A1 PCT/GB2004/000378 GB2004000378W WO2005073085A1 WO 2005073085 A1 WO2005073085 A1 WO 2005073085A1 GB 2004000378 W GB2004000378 W GB 2004000378W WO 2005073085 A1 WO2005073085 A1 WO 2005073085A1
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WO
WIPO (PCT)
Prior art keywords
satellite
orbit
recited
earth
spacecraft
Prior art date
Application number
PCT/GB2004/000378
Other languages
English (en)
Inventor
Robert F. D'ausilio
Roger X. Lenard
Mari M. Southard
James R. Stuart
Chauncey W. Uphoff
Frank H. Williams
Original Assignee
Iostar Corporation
Jehan, Robert
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Iostar Corporation, Jehan, Robert filed Critical Iostar Corporation
Priority to PCT/GB2004/000378 priority Critical patent/WO2005073085A1/fr
Publication of WO2005073085A1 publication Critical patent/WO2005073085A1/fr

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Classifications

    • 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
    • B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
    • B64G1/646—Docking or rendezvous systems
    • 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
    • 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
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B64G1/411—Electric propulsion
    • B64G1/413—Ion or plasma engines
    • 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
    • B64G1/42—Arrangements or adaptations of power supply systems
    • B64G1/421—Non-solar power generation
    • B64G1/422—Nuclear power generation
    • G—PHYSICS
    • G21—NUCLEAR PHYSICS; NUCLEAR ENGINEERING
    • G21D—NUCLEAR POWER PLANT
    • G21D5/00—Arrangements of reactor and engine in which reactor-produced heat is converted into mechanical energy
    • G21D5/02—Reactor and engine structurally combined, e.g. portable
    • 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
    • B64G1/1078—Maintenance satellites
    • 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
    • B64G1/1078—Maintenance satellites
    • B64G1/1081—Maintenance satellites for debris removal
    • 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
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B64G1/408—Nuclear spacecraft propulsion
    • 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
    • B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
    • B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
    • B64G1/503—Radiator panels
    • 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
    • B64G1/52—Protection, safety or emergency devices; Survival aids
    • B64G1/54—Protection against radiation
    • B64G1/543—Protection against radiation protecting the crew in manned spacecraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E30/00—Energy generation of nuclear origin

Definitions

  • Figures 1A & IB present top and end views of one of the preferred embodiments of the In Orbit Space Transportation & Recovery System (IOSTAR) vehicle in its fully deployed, orbital configuration.
  • Figure 2 depicts a separate service and refueling vehicle.
  • Figure 3 is a side view of the present invention in its fully deployed configuration.
  • Figure 4 reveals the present invention in a folded and collapsed configuration that may be loaded aboard a launch vehicle.
  • Figures 5, 6, 7 and 8 present side and end views of preferred embodiments of the present invention stowed aboard a launch vehicle.
  • the ion engines 12 employ xenon ions, so the tank is filled with xenon.
  • the ion propulsion system 12 includes a Hall thruster.
  • Other embodiments of the invention may employ different fuels, and may utilize multiple fuels.
  • the system may utilize any tank means which holds, envelopes or stores suitable propellants.
  • the tank 13 is refillable, and may be refilled in a relatively low or zero gravity environment.
  • One embodiment of the invention includes one or more tanks that provides the propulsion system with propellant.
  • the tank may be refilled by a separate, automatic, unmanned spacecraft as shown in Figure 2.
  • the IOSTAR vehicle runs low on propellant, it will be replenished by a servicing vehicle that either transfers all its propellant and is then released; or transfers its propellant gradually and is released when empty.
  • the IOSTAR will have a lower pressure tank so that pumping is kept to a minimum or eliminated.
  • the size of the lower pressure tank is smaller, and includes limited life thrusters attached to the servicing vehicle. The electric thrusters on the service vehicle can be operated at higher power than the rest of the thrusters on the IOSTARTM to enhance performance since the high power reduces lifetime, the thrusters are replaced with the next service vehicle.
  • the radiation shield 20 incorporates multiple zone shielding to minimize mass.
  • the radiation shield includes a recuperator that is also employed as a gamma shield.
  • from 250kW to 500kW of sustained electrical power may be generated aboard an IOSTAR, which vastly exceeds the sustained power generating capabilities of any prior man-made satellite or spacecraft.
  • This power generation capacity is huge when compared to the power levels of conventional satellites and spacecraft, which typically operate with less than 20kW of power.
  • This immense on- orbit power generating capacity enables the IOSTAR to conduct missions which are not feasible using conventional satellites.
  • the reactor 19 is also coupled to an energy converter 22 which converts heat to electrical energy.
  • the energy converter 22 includes a turbine driven by fluid that is heated by the reactor 19 to produce a large amount of electrical power.
  • the converter 22 is coupled to the boom 11, next to the radiation shield 20.
  • An energy converter may be an direct converter, which converts heat directly to electricity.
  • IOSTAR Missions & Operations The system disclosed herein is different from conventional orbital systems, in that it will be capable of accomplishing many missions over a long life.
  • the IOSTAR will be reusable, in one embodiment the entire system will be capable of being launched using a single launch vehicle, preferably the United States Space Shuttle. Other launch vehicles that are reusable or expendable may also be employed.
  • the first implementation of the IOSTAR will be constructed primarily or entirely on the Earth's surface, and then will be launched into orbit. Later implementations may be partially or completely constructed in orbit.
  • the IOSTAR may be controlled from a terrestrial operations center, or may operated by an on-orbit controller. In general, the system is fully extended after launch, and is then ready for operations.
  • Satellites Supply on-orbit power to another spacecraft
  • Provide services to a spacecraft manufacturer Provide services to a spacecraft user Provide services to a government agency
  • Frequency band 11 extends from 30 to 300 GigaHertz, and is also referred to by the term "millimetric waves.”
  • Frequency band 12 extends from 300 to 3000 GigaHertz or 3 TeraHertz, and is also referred to by the term decimillimetric waves. This nomenclature of frequency bands was adopted in the Radio Regulations of the International Telecommunication Union, Article 2, Section 11, Geneva; 1959. These direct communication services will generally be enabled by IOSTAR's enormous power generating capabilities.
  • Figure 24 is a perspective view of a satellite having an array of antennas which may be used in combination with an IOSTAR to provide a direct broadcast system 52. Since the IOSTAR can generate very high levels of electrical power compared to conventional satellites 15, it may be used to transmit direct broadcast signals at extremely high frequencies.
  • a conductor in orbit is used to generate electrical energy.
  • the conductor acts like a dynamo circuit or an electric motor.
  • the return current flows in the Earth's ionosphere, which conducts electricity.
  • the electrical current is generated at the expense of the kinetic energy of the conductor in orbit, since the magnetic force on the conductor opposes its orbital motion and slows it down.
  • the process is also reversible- when an electric current is pumped into the conductor or tether, the magnetic force boosts the orbital motion and raises the orbit to a higher altitude. See: http://www-istp.gsfc.nasa.gov/Education/wtether.html
  • portions of the boom 11 and radiator 16 contain a conductor 21 or conductive elements capable of carrying electric current.
  • This conductor 21 may comprise a wire, cable, line, linkage, mesh, strut, support, structural member, tether, protuberance, applied conductive layer or film, or any other conductive feature or surface.
  • a current may be passively generated by the orbital motion of the boom 11 and or the radiator 16, which cut through the magnetic field lines of the celestial body being orbited. This motion induces a voltage along the length of the boom 11 and radiator 16.
  • Current can be generated with a conductive element loop along the boom 11 and/or radiator 16.
  • Current may also be generated using plasma contactors 23, which are field effect devices having many sharp points or hollow cathodes.
  • contactors 23 are shown in Figure 1 , and are depicted on the ends of the boom 11 in Figure 25.
  • the contactors 23 enable the spacecraft to "contact” or interact with the plasma of the orbited celestial body.
  • contactors are placed on each end of the boom 11.
  • the same conductor 21 in orbit may use electric power from the reactor 19 and energy converter 22 to drive current into the conductor.
  • the current in the conductive elements 21 of the boom 11 and/or radiator 16 can "push" against the celestial body's magnetic field to increase the spacecraft's orbital energy and raise the spacecraft's orbit altitude.
  • Conventional rockets push against their own exhaust, but this embodiment allows the IOSTARTM spacecraft to push against the orbited celestial body's magnetic field.
  • the IOSTAR system provides a more reliable lower cost means for transporting payloads from Low to Medium or Geostationary Earth Orbits (LEO to MEO or GEO).
  • LEO Low to Medium or Geostationary Earth Orbits
  • IOSTAR satellites destined for MEO or GEO are initially launched to LEO using smaller less complex launch vehicles or multi-manifested on larger vehicles increasing their capacity (roughly a factor of five more mass can be launched to LEO than GEO). Once in LEP the IOSTAR vehicle completes the transfer to MEO or GEO.
  • IOSTAR offers a unique orbit correction service to reposition the 1 to 4 satellites placed in incorrect low orbits per year, to their intended high (e.g. GEO and MEO) orbit.
  • IOSTAR provides video inspection services (at both visual and thermal IR wavelengths) to inspect satellites and provide valuable information to help assess and mitigate failures in-orbit. This service also provides valuable information on how to better design future satellites. In addition, since clear proof of certain failure modes can be determined, this service enables insurers to reduce premiums by exempting certain types of failures from coverage.
  • IOSTAR In-Orbit Repair Services and Products
  • External mechanism failures such as stuck solar arrays and antennas
  • IOSTAR can also transport special modules, which latch onto a satellite and remedy, e.g., inadvertent fuel consumption and certain attitude control failures.
  • the satellite Retrieval service addresses the retrieval of a malfunctioning satellite and transporting it to an orbit reachable by the space shuttle or other space systems for subsequent repair, upgrade and refueling.
  • the satellite is subsequently relaunched with the IOSTAR New Launch service more quickly, reliably and less expensively than a new replacement satellite.
  • the IOSTAR New Launch service significantly broadens the options available to inte ⁇ lanetary mission planners. With the IOSTAR New Launch service inte ⁇ lanetary spacecraft can be placed into a high Earth orbit to minimize on-board fuel requirements.
  • IOSTAR can extend the lifetime of very high value reconnaissance satellites by providing a transportation service to change orbital elements. By taking advantage of this transportation service, less on-board fuel is required to change a satellites ground track (i.e. are of coverage), thereby extending satellite operational life. In addition, much larger changes of orbital elements are possible with IOSTAR enabling existing reconnaissance satellites unconstrained and timely access to a multitude of coverage areas. Flexible U.S. Launch Site Service
  • GPS constellation launch costs alone Additional savings may be realized since the GPS satellites would no longer require a kick motor and some aspects of the propulsion system may potentially be simplified since IOSTAR places the satellites precisely into the intended orbit.
  • IOSTAR more than doubles the existing and planned ELV launch mass limits to MEO and GEO enabling the launch of more capable satellites to high orbits.
  • Existing launch vehicles can transport far more mass to a LEO orbit than MEO and GEO; payload subsequently transports the heavy payload to MEO and/or GEO.
  • IOSTAR enables very high performance highly powerful space based RADAR systems. In addition, with IOSTAR these systems can be mobile to avoid potential threats and adjust orbital elements on-demand for enhanced coverage. IOSTAR also enables very high bandwith EHF military satellite communication systems. Adaptive Constellation Service
  • Precision Graveyard Service It requires excessive fuel to maneuver satellites in higher orbits, at the end of their life, to a low orbit for eventual burn-up to eliminate future security and/or uncontrolled reentry concerns.
  • IOSTAR enables the cost effective permanent disposal of satellites in any orbit. By transporting a satellite from higher orbits to a low orbit a controlled re-entry can subsequently be executed to permanently remove the satellite from orbit.

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Plasma & Fusion (AREA)
  • High Energy & Nuclear Physics (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • General Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Plasma Technology (AREA)

Abstract

La présente invention concerne un transport spatial en orbite et un système de récupération (10). Un mode préféré de réalisation de cette invention comprend un remorqueur spatial mu par un réacteur nucléaire (19). Ce système comprend un bras télescopique (112) connecté à une extrémité d'un réservoir de poudre propulsive (13) qui stocke le combustible du système de propulsion électrique (12). L'extrémité de ce bras (11) est équipé d'un matériel d'arrimage (14) capable d'attraper et de retenir un satellite (15) et de servir à remplir le réservoir (13). Des panneaux de radiateur (16) montés sur un bras (11) dissipent la chaleur du réacteur (19). Un écran antirayonnement (20) est situé à côté du réacteur (19) de façon à protéger la charge utile du satellite (15) à l'autre extrémité du bras (11). Ce système (10) sera capable d'accomplir des manoeuvres de rendez-vous et d'arrimage qui permettront de déplacer le vaisseau spatial entre une orbite terrestre de stationnement basse et des positions orbitales plus hautes ou vers d'autres localisations de notre système solaire.
PCT/GB2004/000378 2004-01-29 2004-01-29 Transport spatial en orbite et systeme de recuperation WO2005073085A1 (fr)

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Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8515609B2 (en) 2009-07-06 2013-08-20 Honeywell International Inc. Flight technical control management for an unmanned aerial vehicle
FR2996527A1 (fr) * 2012-10-08 2014-04-11 Centre Nat Etd Spatiales Engin spatial a propulsion nucleaire electrique comprenant un bouclier de protection a extensions
RU2636453C2 (ru) * 2016-02-25 2017-11-23 Акционерное общество "Информационные спутниковые системы" имени академика М.Ф. Решетнёва" Межпланетный космический корабль
US20190248517A1 (en) * 2016-08-10 2019-08-15 ispace, inc. Exploration method, exploration system, probe, hydrogen supply method, and image processing method
CN110489779A (zh) * 2019-07-03 2019-11-22 上海卫星工程研究所 一种木星探测借力飞行轨道优化设计方法
CN110844121A (zh) * 2019-10-22 2020-02-28 西北工业大学深圳研究院 一种在轨装配航天器协同运输的合作博弈控制方法
US10611504B2 (en) 2014-08-26 2020-04-07 Effective Space Solutions Ltd. Docking system and method for satellites
US10625882B2 (en) 2017-03-06 2020-04-21 Effective Space Solutions Ltd. Service satellite for providing in-orbit services using variable thruster control
RU2743117C1 (ru) * 2020-02-07 2021-02-15 Владимир Владимирович Кудинов Ядерный реактор для космического аппарата
CN114922788A (zh) * 2022-03-29 2022-08-19 哈尔滨工业大学 一种满足月球基地昼夜热电需求的太空储能发电系统
CN115230996A (zh) * 2022-09-21 2022-10-25 北京星河动力装备科技有限公司 留轨末级控制方法、装置、系统、电子装置和存储介质
US11975870B2 (en) 2022-06-22 2024-05-07 Blue Origin, Llc Nuclear thermal propulsion system with reactor direct drive of cryocooler turbine

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3825211A (en) 1972-06-19 1974-07-23 Phaser Telepropulsion Inc Laser rocket
US4471926A (en) 1979-10-29 1984-09-18 Trw Inc. Transfer vehicle for use in conjunction with a reusable space shuttle
US4575029A (en) 1979-10-30 1986-03-11 Trw Inc. Spacecraft for use in conjunction with a reusable space shuttle
US4664344A (en) 1985-11-07 1987-05-12 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Apparatus and method of capturing an orbiting spacecraft
US4754601A (en) 1984-12-18 1988-07-05 Minovitch Michael Andrew Self-refueling space propulsion system and operating method
US4943014A (en) 1979-10-30 1990-07-24 Trw Inc. Soft ride method for changing the altitude or position of a spacecraft in orbit
US5260639A (en) 1992-01-06 1993-11-09 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Method for remotely powering a device such as a lunar rover
RU2040445C1 (ru) * 1992-05-22 1995-07-25 Головное конструкторское бюро научно-производственного объединения "Энергия" им.акад.С.П.Королева Объединенная электрореактивная двигательная установка космического аппарата, способ создания управляющих моментов по каналам тангажа и рыскания космического аппарата с указанной двигательной установкой и трехканальный электрореактивный двигатель
US6213700B1 (en) 1999-12-21 2001-04-10 Illinois Tool Works Inc. Screw installed grommet
US6357700B1 (en) 2000-10-02 2002-03-19 Anthony Italo Provitola Electrically powered spacecraft/airship
US6478257B1 (en) 2001-06-15 2002-11-12 Space Systems/Loral, Inc. Phase change material thermal control for electric propulsion

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3825211A (en) 1972-06-19 1974-07-23 Phaser Telepropulsion Inc Laser rocket
US4471926A (en) 1979-10-29 1984-09-18 Trw Inc. Transfer vehicle for use in conjunction with a reusable space shuttle
US4575029A (en) 1979-10-30 1986-03-11 Trw Inc. Spacecraft for use in conjunction with a reusable space shuttle
US4943014A (en) 1979-10-30 1990-07-24 Trw Inc. Soft ride method for changing the altitude or position of a spacecraft in orbit
US4754601A (en) 1984-12-18 1988-07-05 Minovitch Michael Andrew Self-refueling space propulsion system and operating method
US4664344A (en) 1985-11-07 1987-05-12 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Apparatus and method of capturing an orbiting spacecraft
US5260639A (en) 1992-01-06 1993-11-09 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Method for remotely powering a device such as a lunar rover
RU2040445C1 (ru) * 1992-05-22 1995-07-25 Головное конструкторское бюро научно-производственного объединения "Энергия" им.акад.С.П.Королева Объединенная электрореактивная двигательная установка космического аппарата, способ создания управляющих моментов по каналам тангажа и рыскания космического аппарата с указанной двигательной установкой и трехканальный электрореактивный двигатель
US6213700B1 (en) 1999-12-21 2001-04-10 Illinois Tool Works Inc. Screw installed grommet
US6357700B1 (en) 2000-10-02 2002-03-19 Anthony Italo Provitola Electrically powered spacecraft/airship
US6478257B1 (en) 2001-06-15 2002-11-12 Space Systems/Loral, Inc. Phase change material thermal control for electric propulsion

Non-Patent Citations (9)

* Cited by examiner, † Cited by third party
Title
BRUNO C, LENARD R, FEARN D, HANSSON A, ROUX J-P, GAFAROV A, FRISCHAUF N, VALENTIAN D ET AL: "Sub-Workshop no. 5: Nuclear Propulsion (Joint IAF/IAA/AAAF Workshop)", BUILDING ROADMAPS FOR SPACE TRANSPORTATION OF THE XXI CENTURY - WORKSHOP, 17 May 2002 (2002-05-17), VERSAILLES, FRANCE, XP002299652, Retrieved from the Internet <URL:http://www.snecma.com/en/group/symposiums/aaaf_propulsion/workshops/upload/ws5.pdf> [retrieved on 20040924] *
DEININGER W D ET AL: "ARCJET PROPULSION SYSTEM FOR AN SP-100 FLIGHT EXPERIMENT", JOURNAL OF SPACECRAFT AND ROCKETS, AMERICAN INSTITUTE OF AERONAUTICS AND ASTRONAUTICS. NEW YORK, US, vol. 25, no. 6, 1 November 1988 (1988-11-01), pages 427 - 432, XP000026087, ISSN: 0022-4650 *
GRYAZNOV G M, ZHABOTINSKI E E, ANDREEV P V, ZARITSKI G A, KOROTEEV A S, MARTISHIN V M, AKIMOV V N, PONOMAREV-STEPNOI N N, BRITT E: "A Power Propulsion System Based on a Second-Generation Thermionic NPS of the "Topaz" Type", PROCS. OF THE 9TH SYMPOSIUM ON SPACE NUCLEAR POWER SYSTEMS, 1992, ALBUQUERQUE, NM, USA, XP008035354 *
JAFFE L D: "NUCLEAR-ELECTRIC REUSABLE ORBITAL TRANSFER VEHICLE", JOURNAL OF SPACECRAFT AND ROCKETS, AMERICAN INSTITUTE OF AERONAUTICS AND ASTRONAUTICS. NEW YORK, US, vol. 25, no. 5, 1 September 1988 (1988-09-01), pages 375 - 381, XP000030181, ISSN: 0022-4650 *
LENARD R X: "Nuclear Electric Propulsion for Enhanced Mars Sample Return Missions", PROCS. OF THE 53RD ANNUAL INTERNATIONAL ASTRONAUTICAL CONGRESS, 10 October 2002 (2002-10-10), HOUSTON, TX, USA, XP008035328 *
LOEB H W, POPOV G A: "A Nuclear-Electric Propulsion Module for Advanced Solar System Exploration Program", ACTA ASTRONAUTICA, vol. 37, 1995, pages 153 - 166, XP002299653 *
MARTIN A R: "NUCLEAR ELECTRIC PROPULSION OF SPACECRAFT", JOURNAL OF THE BRITISH INTERPLANETARY SOCIETY, BRITISH INTERPLANETARY SOCIETY. LONDON, GB, vol. 48, no. 12, 1 December 1995 (1995-12-01), pages 517 - 524, XP000539078, ISSN: 0007-084X *
SCHALL W O: "LASER RADIATION FOR CLEANING SPACE DEBRIS FROM LOWER EARTH ORBITS", JOURNAL OF SPACECRAFT AND ROCKETS, AMERICAN INSTITUTE OF AERONAUTICS AND ASTRONAUTICS. NEW YORK, US, vol. 39, no. 1, January 2002 (2002-01-01), pages 81 - 91, XP001077695, ISSN: 0022-4650 *
SHEPHERD L R: "PERFORMANCE CRITERIA OF NUCLEAR SPACE PROPULSION SYSTEMS", JOURNAL OF THE BRITISH INTERPLANETARY SOCIETY, BRITISH INTERPLANETARY SOCIETY. LONDON, GB, vol. 52, no. 9/10, September 1999 (1999-09-01), pages 328 - 335, XP000849482, ISSN: 0007-084X *

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US10611504B2 (en) 2014-08-26 2020-04-07 Effective Space Solutions Ltd. Docking system and method for satellites
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US20190248517A1 (en) * 2016-08-10 2019-08-15 ispace, inc. Exploration method, exploration system, probe, hydrogen supply method, and image processing method
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US10625882B2 (en) 2017-03-06 2020-04-21 Effective Space Solutions Ltd. Service satellite for providing in-orbit services using variable thruster control
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