WO2005118394A1 - Unite de propulsion pour astronef, systeme de services effectuant des operations de service dans l'espace et astronef modulaire - Google Patents

Unite de propulsion pour astronef, systeme de services effectuant des operations de service dans l'espace et astronef modulaire Download PDF

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Publication number
WO2005118394A1
WO2005118394A1 PCT/EP2005/006069 EP2005006069W WO2005118394A1 WO 2005118394 A1 WO2005118394 A1 WO 2005118394A1 EP 2005006069 W EP2005006069 W EP 2005006069W WO 2005118394 A1 WO2005118394 A1 WO 2005118394A1
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WO
WIPO (PCT)
Prior art keywords
propulsion unit
docking
spacecraft
servicing
propulsion
Prior art date
Application number
PCT/EP2005/006069
Other languages
English (en)
Inventor
Charalampos Kosmas
Original Assignee
Intersecure Logic Limited
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 Intersecure Logic Limited filed Critical Intersecure Logic Limited
Publication of WO2005118394A1 publication Critical patent/WO2005118394A1/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
    • B64G1/24—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
    • B64G1/10—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
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B64G1/402—Propellant tanks; Feeding propellants
    • B64G1/4024—Propellant tanks; Feeding propellants refuelling 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
    • B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
    • B64G1/646—Docking or rendezvous systems
    • B64G1/6462—Docking or rendezvous systems characterised by the means for engaging other vehicles

Definitions

  • Propulsion Unit for spacecraft, servicing system for providing in-space service operations, and modular spacecraft
  • the invention relates to a propulsion unit for attachment to a selected spacecraft. It furthermore relates to a servicing system for providing in-space service operations, to a modular spacecraft and to a method for operating a servicing system of this kind.
  • Spacecraft such as artificial satellites typically are intended to orbit a specific celestial body in order to provide their particular service or mission. In the majority of cases, satellites are used in the proximity of earth and in particular in a proximity the teller operation capability is not hindered by long electromagnetic wave propagation times.
  • a spacecraft to be used in this configuration i. e. in order to serve as a telecommunication satellite, a ground observation satellite or the like, typically is equipped with a number of thrusters or other propulsion means that may be used to keep the spacecraft in a desired target position and attitude.
  • Satellites or other payloads especially for GEO orbit space applications typically used to be lifted into orbit in a two stage process, wherein in a first step the satellite is lifted from earth to an intermediate orbit by a rocket or other type of launcher. In the second step, by using a so-called apogee kick motor, which basically was a propulsion unit for the satellite, the satellite was moved to a stable or circular orbit.
  • a so-called apogee kick motor which basically was a propulsion unit for the satellite
  • UPS Unified Propulsion Subsystems
  • a binary propulsion subsystem comprising two totally separate units.
  • a first propulsion unit is provided in addition to a second propulsion unit for the routine less fuel demanding and less thrust demanding station- keeping manoeuvers.
  • the station-keeping manoeuver performing propulsion today is often based upon the concept of ion propulsion which depends on low thrust but high specific impulse Xenon gas.
  • the GTO to GEO transfer is performed with so called hy- pergolic or storable propelants of high thrust but lower specific impulse. Accordingly, in view of the different performances and specific requirements the two propulsion modules are totally separate.
  • This spent propulsion module consist of mainly dry mass and it is deactivated completely.
  • This propulsion unit typically consists of fuel tanks, pressurant tanks, one thruster, valves, filters, pipes, structure and harness and the associated sensors for pressure and temperature and heating elements plus cabling for power distribution and sensors. Consequently, it consists of non functional mass with respect to the remaining mission, but is carried uselessly by the spacecraft during its rest of lifetime penalizing each and every station keeping or repositioning manoeuver.
  • a propulsion unit for complementing attachment to a selected spacecraft comprising a number of thrusters, a number of propellant storage tanks, and a docking facilitation system, said docking facilitation system being set up to be removeably connectable to corresponding docking means of a further spacecraft.
  • the invention is based upon the concept that in order to keep the generation of space debris low and at the same time to provide for very efficient manoeuvering capabilities, in contrast to state of the art systems of integrated designs, the propulsion unit should be designed as a separate, detachable unit that may be removed from the target satellite after performing its functions.
  • the propulsion unit after detachment from the satellite may be handled independently from the satellite, thus automatically decreasing the necessary effort and resources required to manoeuver the satellite unit.
  • the present concept avoids further contributions to space debris that might possibly hinder future space missions due to enhanced danger of collisions with used components by offering means for controllable handling of the propulsion unit after it gets disconnected from the modular satellite in consideration.
  • the propulsion unit after detachment may be positioned in space in reserved zones or even free outer space where it would not create debris problems. Alternatively, it may be reused for further propulsion missions for other satellites, especially after refuelling.
  • the propulsion unit is equipped with a docking facilitation system that allows for safe approachingh, for electrical and/or mechanical connection to other spacecraft that may be used to manoeuver or control the propulsion unit.
  • the docking facilitation system preferably comprises means for assisting the approach when connecting to the target spacecraft, such as re- troreflectors for approach locking, a video camera for manual backup, and/or a proximity laser for final close loop after locking.
  • the docking facilitation system provided for the propulsion unit allows for in-space connection with another component, in particular an active component having control means and the like, rendering the formerly detached propulsion unit controllable and ma- neuverable.
  • the spent propulsion unit may be moved for disposal purposes to a space region where debris issues are not problematic (the so-called mecanicgra- veyard orbit", agreed today to be 300 km above GEO). It may also be attached to other pieces of debris similarly equipped, thus allowing for a joint handling of those pieces for easier control and unitary and combined transportation to the graveyard.
  • the docking facilitation system may be designed in order to allow for interconnection between a plurality of propulsion units, in order to achieve an arrangement of a stacked type in which several propulsion units as a combined stack may be manoeuvered to a predefined graveyard position.
  • the docking facilitation system comprises so- called male and female connectors that may be used to connect to each other.
  • the propulsion unit equipped with the docking means may be connected to active components in order to render the propulsion unit reusable for other purposes.
  • the docking facilitation system in this context comprises a piece of equipment for the propulsion unit that allows for connection or docking of other components in outer space.
  • the docking facilitation system in an examplary embodiment may comprise a mechanical system, preferrably based upon a clamping mechanism, a magnetic system or an electro-magnetic system.
  • the docking facilitation system comprises docking safeing means for mechanical latching to firmly attach the propulsion unit to the target spacecraft.
  • the docking facilitation system for the propulsion unit allows the propulsion unit to be connected with an active component having control means and the like, rendering the formerly (in old days) detached propulsion unit controllable and manoeuverable.
  • the used-up propulsion unit for disposal may be moved into a position in space where debris issues are not problematic. Alternatively, it might be attached to other pieces of debris for combined and thus more efficient further handling.
  • the propulsion unit via its docking system may be attached to an active component for reusing for other purposes such as a tanker base or a utility base for providing in-space refuelling and other service functions to other spaceship.
  • the docking facilitation system comprises a propel- lant transfer port or unit, allowing for refueling of the propulsion unit, thus rendering it reusable for further missions or applications, and/or allowing for emptying the on-board fuel tanks of the propulsion unit to retrieve unspent fuel reserves for transfer to other spacecraft.
  • the propulsion unit may be used as a temporary tanker or fuel storage base only, it preferably is equipped with fuel transfer ports that allow to empty the onboard tanks to a visiting spacecraft, thus retrieving the unspent fuel from the propulsion unit.
  • type of fuel and design of propulsion unit allow for the use of the propulsion unit as a long-term accumulative tanker, it preferably is set up in order to allow for multiple access and interaction with servicing vehicles.
  • the propulsion unit preferably is equipped with a data port for transferring data (in particular test data/control data) and/or solar panels for power generation. These preferably are used to maintain a desired fuel temperature, thus rendering the propulsion unit into a potential long term fuel storage base.
  • the docking facilitation system in the reuse mode for the propulsion unit, is designed to be controllable or remotely accessible, e. g. in a mechanical (clamp-type) or electro-magnetical design or a combination thereof.
  • the propulsion unit is used in the context of a modular spacecraft consisting of a payload and the (separable) propulsion module for orbit raising.
  • the modular spacecraft is equipped with a satellite bus based upon ion propulsion (electrical or otherwise high specific impulse thruster as compared to chemical thrusters).
  • the object identified above is achieved with a propulsion unit according to one concept as described above, and with a separable servicing vehicle, in which the docking facilitation system is set up to establish a removable connection between the propulsion unit and the servicing vehicle, said servicing vehicle being equipped with communication means for establishing a communication channel through said propulsion unit and modular spacecraft and a remote control module.
  • the servicing vehicle is considered the further or selected spacecraft the docking facilitation means are designed to connect the propulsion unit to.
  • the servicing vehicle itself contains all relevant means and features to render it a completely independent and operable spacecraft, in particular on-board thrusters, manoeuvering equipment and communication means.
  • the propulsion unit may be designed without specific on-board communication means, accordingly saving the corresponding budgets in view of weight etc.
  • the on-board equipment of this unit is made available to establish control on the propulsion unit as well.
  • the servicing vehicle may also be referred to as a utility agent.
  • the servicing system comprises a redockable ejectable propulsion unit which is equipped with a number of docking bays for temporarily containing said servicing vehicle.
  • the servicing vehicle In case the propulsion unit is intended to be docked upon by the servicing spacecraft in order to be moved to a graveyard position, in particular after consumption of all the onboard fuel reserves, the servicing vehicle preferrably is equipped with on-board propulsion means such as thrusters designed with sufficient capacity to propel the rejectable propulsion module to the intended graveyard position.
  • the communication module When operating the servicing system as described above, the communication module preferrably is connected to the propulsion unit, and controls the propulsion unit. Accordingly, on-board communication means for the propulsion unit are rendered obsolete.
  • the family of new apogee kick motors (AKM) or propulsion units according to the invention is being defined to :
  • Fig.1 schematically shows a rocket system with a satellite payload.
  • Fig. 2 through 5 each show a propulsion module for the modular satellite in Fig. 1.
  • the rocket 1 in Fig. 1 comprises a thruster 2 for launching purposes.
  • a modular satellite 6 comprising a payload (including a bus for station keeping) 8 equipped with a detachable propulsion unit 10 is positioned.
  • the propulsion unit 10 is designed such that before detachment from the modular spacecraft 8, in order to avoid unnecessary debris in a particularly cost- and fuel-effective manner, it may be connected to/by other active components for gaining control and manoeuverability.
  • the propulsion unit 10 is equipped with a docking facilitation system 14.
  • This system comprises, among potentially other elements, a connector 13 to the other module of the spacecraft 6, i. e. the payload 8 with the bus system.
  • the connector 13 comprises an electrical part for transmitting signals and/or power and a mechanical part for attaching and/or fuel transfer.
  • the docking facilitation system 14 further comprises an avionics module 15 used for proximity operations, comprising e. g. retroreflectors, a video camera for manual backup, and/or a proximity laser for final close loop after lok- king.
  • system 14 comprises male and female (16) mechanical connectors designed to allow for stacking of a plurality of propulsion units 10. Connectors 13 and 14 may be combined.
  • Version one (SINGLE USE AKM mode) comprising.
  • the docking bay being centrally located (to the Center of Gravity CoG) of the propulsion unit 10.
  • Optionally - permanent magnet based docking mechanism male
  • single- point or multi-point preferably at the side of separation with the satellite, so that it can be used after the separation for docking permanently to another passive space object equipped with permanent magnetic material. Or temporarily to an object possessing electromagnet based docking.
  • the docking bay 26 being in the opposite direction from the satellite it caries, to allow a Utility Agent to dock before the separation (ie before it become uncontrollable).
  • the docking facilitation means comprise:
  • Visual aid means to assist automatic docking of a utility agent like retro-reflectors.
  • avionics for exchanging signals with the utility agent at approach. These signals can be converted to appropriate telemetry that is routinely transmitted by the satellite.
  • a camera for capturing live image video of the approaching utility agent. The video stream can be feed to the satellite for transmission directly on earth through its standard downlink transmission capabilities.
  • a capturing mechanism (as proposed in copending patent) that can extend lengthily enough to capture the utility agent and pull in the bay cavity to dock.
  • the propulsion unit 10 until its separation from the spacecraft has stable attitude, power and telecommand feed from, telemetry feed to and all the elements that can characterize it as cooperative-target, by the terminology of the OOS.
  • the propulsion unit 10 can even move by the help of the spacecraft through active thrusts or use of the momentum wheels to perform collision avoidance manoeuvres if a risk is detected during approach of the docking spacecraft (utility agent, servicing vehicle). It can also perform a formation-flying process to synchronize the approach with the utility agent to increase the speed and accuracy of the docking operation.
  • SINGLE USE AKM can incorporate a porting cavity that can carry a plurality of utility agents of either chemical propellants or of Electrical propulsion.
  • the utility agent can port for disposal of the propulsion unit 10 after separation at a desired orbit in a slow but economical way and then separate from it to become available for performing other OOS missions,
  • Pipe connector interface serving as a propellant transfer port 22 in the dok- king bay for filling or draining propellant.
  • the PASSIVE TANKER can be used before separation to provide fuel supplies to one or more visiting utility agents in successive refuelling sessions.
  • a number of docking bays 26 sufficiently large in size to encapsulate and port one active spaceship for use as utility agent or communcation unit for performing servicing functions and the like to other spaceships.
  • the propulsion unit 10 may be beneficially used together with a modular spacecraft that has been designed to make use of a rejectable AKM or propulsion unit 10.
  • fuel trading between the spacecraft and the propulsion unit 10 is considered.
  • the spacecraft preferrably is equipped with easily connectable fill/drain valves, preferably by using quick couplers, and an appropriate dockig interface of a utility agent for performing fuel trading.
  • This concept takes into consideration that almost 50% of the satellites have a major malfunction before their nominal end-of life. These malfuctions are associated in many cases with failure of electronics or failure of an electrical or another subsystem, while the propellant storage subsystem still functions.

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Astronomy & Astrophysics (AREA)
  • General Physics & Mathematics (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Abstract

L'invention concerne une unité de propulsion (10) fixée à un astronef cible sélectionné, comprenant un certain nombre de propulseurs (12), un certain nombre de réservoirs de stockage (20) d'agent propulsif et un système (14) facilitant l'amarrage, ledit système (14) étant réglé afin d'être connecté de manière libérable à un organe d'amarrage correspondant d'un autre aéronef. Ledit système (14) facilitant l'amarrage prévu pour l'unité de propulsion (10) permet la connexion dans l'espace avec un autre composant, en particulier, un composant actif doté d'un organe de commande et analogue, ce qui rend l'unité de propulsion (10) antérieurement détachée contrôlable et manoeuvrable.
PCT/EP2005/006069 2004-06-04 2005-06-06 Unite de propulsion pour astronef, systeme de services effectuant des operations de service dans l'espace et astronef modulaire WO2005118394A1 (fr)

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DE102004027405 2004-06-04

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Cited By (19)

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WO2007117373A1 (fr) * 2006-03-31 2007-10-18 The Boeing Company Systeme vehicule de maintenance d'astronef en deux parties dote d'adaptateurs, d'outils et de mecanismes de fixation
FR2902762A1 (fr) * 2006-06-27 2007-12-28 Eads Astrium Sas Soc Par Actio Procede de mise en orbite operationnelle d'un satellite artificiel et dispositif de propulsion associe.
US7861975B2 (en) 2006-03-31 2011-01-04 The Boeing Company Two part spacecraft servicing vehicle system with universal docking adaptor
US8998146B2 (en) 2012-11-21 2015-04-07 Space Systems/Loral, Llc Spacecraft momentum unload and station-keeping techniques
US9231323B1 (en) 2014-07-28 2016-01-05 NovaWurks, Inc. Spacecraft docking connector
US9394065B2 (en) 2012-05-11 2016-07-19 The Boeing Company Multiple space vehicle launch system
EP3121122A4 (fr) * 2014-03-18 2017-11-15 Astroscale Japan Inc. Dispositif à des fins d'utilisation dans l'espace, système d'élimination de débris, et procédé d'élimination de débris
WO2018190944A1 (fr) 2017-04-13 2018-10-18 Orbital Atk, Inc. Systèmes de capture d'un véhicule client et procédés associés
WO2019018819A1 (fr) 2017-07-21 2019-01-24 Nicholson James Garret Dispositifs d'entretien d'engin spatial, ensembles, systèmes et procédés associés
EP3483074A1 (fr) * 2017-11-13 2019-05-15 ArianeGroup GmbH Véhicule lanceur à cellules solaires, procédé de fabrication et procédé de transport
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
WO2020150242A1 (fr) 2019-01-15 2020-07-23 Northrop Grumman Innovation Systems, Inc. Dispositifs d'entretien d'engin spatial et ensembles, systèmes et procédés associés
CN111891391A (zh) * 2020-08-11 2020-11-06 中国科学院微小卫星创新研究院 卫星推进模块及其分离方法
WO2021225701A1 (fr) 2020-05-04 2021-11-11 Northrop Grumman Systems Corporation Ensembles de capture de véhicule et dispositifs, systèmes et procédés associés
US11459133B2 (en) 2019-05-08 2022-10-04 NovaWurks, Inc. Method of aligning a spacecraft frame
US11708181B2 (en) 2012-05-11 2023-07-25 The Boeing Company Methods and apparatus for performing propulsion operations using electric propulsion systems
US11827386B2 (en) 2020-05-04 2023-11-28 Northrop Grumman Systems Corporation Vehicle capture assemblies and related devices, systems, and methods
DE102022130071A1 (de) 2022-11-14 2024-05-16 Gate Space Innovation Gmbh Auf dem Rückstoßprinzip basierende Antriebseinheit für eine Nutzlast im Weltall

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US7823837B2 (en) 2006-03-31 2010-11-02 The Boeing Company Two part spacecraft servicing vehicle system with adaptors, tools, and attachment mechanisms
US7861975B2 (en) 2006-03-31 2011-01-04 The Boeing Company Two part spacecraft servicing vehicle system with universal docking adaptor
WO2007117373A1 (fr) * 2006-03-31 2007-10-18 The Boeing Company Systeme vehicule de maintenance d'astronef en deux parties dote d'adaptateurs, d'outils et de mecanismes de fixation
FR2902762A1 (fr) * 2006-06-27 2007-12-28 Eads Astrium Sas Soc Par Actio Procede de mise en orbite operationnelle d'un satellite artificiel et dispositif de propulsion associe.
WO2008001002A1 (fr) * 2006-06-27 2008-01-03 Astrium Sas Procede de mise en orbite operationnelle d'un satellite artificiel et dispositif de propulsion associe
US8136765B2 (en) 2006-06-27 2012-03-20 Astrium Sas Method of launching into operational orbit an artificial satellite and associated propulsion device
US11286066B2 (en) 2012-05-11 2022-03-29 The Boeing Company Multiple space vehicle launch system
US11708181B2 (en) 2012-05-11 2023-07-25 The Boeing Company Methods and apparatus for performing propulsion operations using electric propulsion systems
US9394065B2 (en) 2012-05-11 2016-07-19 The Boeing Company Multiple space vehicle launch system
US9957068B2 (en) 2012-05-11 2018-05-01 The Boeing Company Multiple space vehicle launch system
US8998146B2 (en) 2012-11-21 2015-04-07 Space Systems/Loral, Llc Spacecraft momentum unload and station-keeping techniques
EP3121122A4 (fr) * 2014-03-18 2017-11-15 Astroscale Japan Inc. Dispositif à des fins d'utilisation dans l'espace, système d'élimination de débris, et procédé d'élimination de débris
RU2678392C2 (ru) * 2014-03-18 2019-01-28 Астроскейл Джапан Инк. Устройство для применения в космосе, система удаления мусора и способ удаления мусора
US10464696B2 (en) 2014-03-18 2019-11-05 Astroscale Japan Inc. Space device, debris removal system, and method for removing debris
US9231323B1 (en) 2014-07-28 2016-01-05 NovaWurks, Inc. Spacecraft docking connector
US10611504B2 (en) 2014-08-26 2020-04-07 Effective Space Solutions Ltd. Docking system and method for satellites
US11286061B2 (en) 2017-03-06 2022-03-29 Astroscale Israel, Ltd. Service satellite for providing in-orbit services using variable thruster control
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