Source: http://www.google.com/patents/US6539703?ie=ISO-8859-1
Timestamp: 2014-03-07 15:50:01
Document Index: 58421093

Matched Legal Cases: ['art 22', 'art 23', 'art 22', 'art 22', 'art 23', 'art 22', 'arts 22', 'art 24', 'art 22', 'art 22', 'art 23', 'art 24', 'art 23', 'art 24']

Patent US6539703 - Spacecraft component with microthruster actuation and operation thereof - Google PatentsSearch Images Maps Play YouTube News Gmail Drive More »Sign inAdvanced Patent SearchPatentsA spacecraft component (20) includes a plurality of parts, e.g., a first part (22) and a second part (23) connected to one another, at least the first part (22) being mounted for movement with respect to another of the parts, e.g., the second part (23). At least one microthruster (27) is provided on...http://www.google.com/patents/US6539703?utm_source=gb-gplus-sharePatent US6539703 - Spacecraft component with microthruster actuation and operation thereofAdvanced Patent SearchPublication numberUS6539703 B1Publication typeGrantApplication numberUS 09/948,035Publication dateApr 1, 2003Filing dateSep 5, 2001Priority dateSep 5, 2001Fee statusPaidPublication number09948035, 948035, US 6539703 B1, US 6539703B1, US-B1-6539703, US6539703 B1, US6539703B1InventorsPeter D. Lohn, David H. LewisOriginal AssigneeTrw Inc.Export CitationBiBTeX, EndNote, RefManPatent Citations (4), Non-Patent Citations (2), Referenced by (4), Classifications (8), Legal Events (6) External Links: USPTO, USPTO Assignment, EspacenetSpacecraft component with microthruster actuation and operation thereofUS 6539703 B1Abstract A spacecraft component (20) includes a plurality of parts, e.g., a first part (22) and a second part (23) connected to one another, at least the first part (22) being mounted for movement with respect to another of the parts, e.g., the second part (23). At least one microthruster (27) is provided on the first part for actuation thereof and includes a chamber (2, 14), a fluid provided in the chamber and a diaphragm (3, 13) covering an opening in the chamber (2, 14).
CROSS-REFERENCE TO RELATED APPLICATION Reference is made to commonly assigned U.S. patent application Ser. No. 08/912,709, filed Aug. 18, 1997 for Integrated Pulsed Propulsion and Structural Support System for Microsatellite (now U.S. Pat. No. 6,131,385), and U.S. patent application Ser. No. 09/449,427, filed Nov. 24, 1999 (now U.S. Pat. No. 6,487,844) for Aerospike Augmentation of Microthruster Impulse, the disclosures of each of which are hereby incorporated by reference.
BACKGROUND OF THE INVENTION In the space environment, it is of utmost importance that spacecraft components be deployed, moved, oriented and actuated in a reliable, fine-tuneable and fail-safe manner. Many spacecraft components, e.g., spacecraft booms, solar panels, antennas, payloads, instruments, sensors, satellite modules, separated hardware and star trackers, have parts which must be moved, either in a linear or pivoting manner with respect to other parts. In moving the parts with respect to one another, conventional, mechanical actuation is the current standard. However, it is desired to provide a more flexible and reliable operation in the space environment.
SUMMARY OF THE INVENTION According to the present invention, microthrusters, which have previously been proposed as a propulsion system for microsatellites, are used in spacecraft components to move parts of the spacecraft components with respect to one another. According to the present invention, the term �spacecraft component� encompasses, but is not limited to spacecraft booms, solar panels, antennas, payloads, instruments, sensors, satellite modules, separated hardware and star trackers. Such components have a plurality of parts connected to one another, at least a first part being mounted with respect to another of the parts. According to the present invention, at least one microthruster is provided on a first part and comprises a chamber, fluid provided in the chamber and a diaphragm covering an opening in the chamber. An array of such microthrusters can be used to provide a reliable and fine-tuneable movement or actuation system.
BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a schematic illustration of a spacecraft component having parts mounted for pivoting motion by use of a microthruster.
DETAILED DESCRIPTION OF DISCLOSED EMBODIMENT FIG. 1 is a schematic illustration of a spacecraft component generally designated by the reference numeral 20. The spacecraft component can be, but is not limited to, spacecraft booms, solar panels, antennae, payloads, instruments, sensors, satellite modules, separated hardware and star trackers. Based on the following description, one skilled in the art would understand that other spacecraft components fall within the scope of the present invention. FIGS. 1 and 2 of the subject application show the spacecraft components 20 or 20′ generically illustrated, such generic illustrations being intended to represent any of the aforementioned spacecraft components.
In order to actuate the pivoting movement of first part 22 with respect to second part 23 about pivot 25, a microthruster or microthruster array 27 is provided on first part 22. Actuation of microthruster or microthruster array 27 in the manner described hereinafter creates a thrust in the direction T to move first part 22 about pivot 25 with respect to second part 23. A second microthruster or microthruster array 28 can also be provided on first part 22 in order to generate a thrust to cause first and second parts 22 and 23 to pivot about pivot 26 and move with a pivoting motion with respect to third part 24. In this manner, the first part 22 can be pivoted about two pivot axes orthogonal to one another. Of course, other pivoting mechanisms known in the art could be used to provide the same range of pivoting motion. For example, the first part 22 could be connected to the second part 23 or third part 24 with a ball and socket joint. The microthrusters or microthruster arrays 27, 28 can be used in place of or in addition to conventional mechanical actuators 271, 281. That is, the microthrusters or microthruster arrays 27, 28 can be used as the primary actuator for the spacecraft component 20 (in which case the conventional mechanical actuators 271, 281 are not included) or to fine-tune the mechanical activation of the conventional mechanical actuators 271, 281. Alternatively, the microthrusters or microthruster arrays 27, 28 can be used as a backup to the conventional mechanical actuators 271, 281. For example, the microthrusters or microthruster arrays 27, 28 can act as a �hammer tap� in space to provide a redundant system.
In the embodiment shown in FIG. 2, the second part 23′ is mounted for pivoting movement with respect to the third part 24′ about pivot 26′. The microthruster array 27′ can be used to generate a thrust force in the direction T to cause this pivoting motion. The microthrusters or microthruster arrays 27′, 28′ can be used in place of or in addition to conventional mechanical, actuators 271′, 281′. That is, the microthrusters or microthruster arrays 27′, 28′ can be used as the primary actuator for the spacecraft component 20′ (in which case the conventional mechanical actuators 271′, 281′ are not included) or to fine-tune the mechanical activation of the conventional mechanical actuators 271′, 281′. Alternatively, the microthrusters or microthruster arrays 27′, 28′ can be used as a backup to the conventional mechanical actuators 271′, 281′. For example, the microthrusters or microthruster arrays 27′, 28′ can act as a �hammer tap� in space to provide a redundant system.
The microthruster 11 illustrated in FIGS. 4 and 6 of the drawings addresses two requirements for microthruster development: production of greater impulse and more controllable impulse as compared with that obtained with a microthruster with no thrust augmentation as in FIGS. 3 and 5. According to this embodiment, an aerospike 12 is formed integrally with the microthruster in the center of an exit section 13 of the chamber 14 of the microthruster. The exit section 13 is opened by use of two burst disks 15 and 16, which allow exit flow on either side of the body of the aerospike 12 to produce a higher impulse as compared with the microthruster shown in FIGS. 3 and 5. It has been calculated that the impulse of the microthruster 11 is 19% greater than that with the microthruster 1 in FIGS. 3 and 5 having only a simple nozzle opening. In addition, it has been found that the gas dynamics of the aerospike 12 provide more uniform impulse performance over a) altitude variations�the bit impulse will be relatively altitude-independent; and b) under an array configuration consisting of numerous linear impulse bits stacked together side by side�the inner array and outer arrays (which see different external pressure) will produce more uniform thrust and, hence, be more controllable, as compared with an array configuration of microthrusters without thrust augmentation.
According to the present invention, the microthruster or microthruster array can be used as the primary actuator for the spacecraft component; that is, the movement, linear and/or pivoting, can be actuated solely by the microthruster or preferably, a microthruster array. This combines a reliable and flexible primary actuator and allows fine-tuning. By combining two pivot directions with linear movement, three dimensional deployment capability is achieved. The use of a microthruster or microthruster array can, according to the present invention, also augment or provide a back-up for mechanical actuation in the event a failure of the mechanical actuator is sensed. That is, the spacecraft component can be operated by actuating the mechanical actuator, determining whether the mechanical actuator provided a predetermined movement of at least the first part with respect to another of the parts, and, if the mechanical actuator has not successfully provided the predetermined movement of at least the first part with respect to another of the parts, actuating the at least one microthruster to provide a thrust to move at least the first part with respect to another of the parts. In augmenting mechanical activation, the microthruster array can be used to fine-tune the mechanical activation. As a backup, the microthruster or microthruster array can act as a �hammer tap� in space to provide a redundant system.
Patent CitationsCited PatentFiling datePublication dateApplicantTitleUS6131385Aug 18, 1997Oct 17, 2000California Institute Of TechnologyIntegrated pulsed propulsion system for microsatelliteUS6263665 *Jun 4, 1999Jul 24, 2001The United States Of America As Represented By The Secretary Of The Air ForceMicrothruster for heating a propellant, driving the vapors produced to a discharge sectionUS6378292 *Nov 10, 2000Apr 30, 2002Honeywell International Inc.MEMS microthruster arrayUS6487844Nov 24, 1999Dec 3, 2002Trw Inc.Aerospike augmentation of microthruster impulse* Cited by examinerNon-Patent CitationsReference1"Fomenting A Revolution, In Miniature", Oct. 16, 1998, vol. 282 Science.2"Little Bangs", Scientific American Nov. 1998.Referenced byCiting PatentFiling datePublication dateApplicantTitleUS6892525 *Jun 6, 2003May 17, 2005Honeywell International Inc.Micropump-based microthrusterUS7690187 *Sep 26, 2006Apr 6, 2010The Aerospace CorporationModular micropropulsion device and systemUS8613188May 14, 2009Dec 24, 2013Purdue Research FoundationMethod of enhancing microthruster performanceWO2010068174A1 *Dec 10, 2008Jun 17, 2010Guilio ManzoniA microsatellite comprising a propulsion module and an imaging device* Cited by examinerClassifications U.S. Classification60/203.1, 60/204International ClassificationB64G1/26, F02K9/94Cooperative ClassificationB64G1/26, F02K9/94European ClassificationF02K9/94, B64G1/26Legal EventsDateCodeEventDescriptionSep 21, 2010FPAYFee paymentYear of fee payment: 8Feb 10, 2010ASAssignmentOwner name: NORTHROP GRUMMAN SYSTEMS CORPORATION,CALIFORNIAFree format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:NORTHROP GRUMMAN SPACE & MISSION SYSTEMS CORP.;US-ASSIGNMENT DATABASE UPDATED:20100212;REEL/FRAME:23915/446Effective date: 20091210Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:NORTHROP GRUMMAN SPACE & MISSION SYSTEMS CORP.;US-ASSIGNMENT DATABASE UPDATED:20100216;REEL/FRAME:23915/446Free format text: ASSIGNMENT OF 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