WO2000034125A1 - Dispositif de maintien en position et de declenchement pour composants satellites deployables - Google Patents

Dispositif de maintien en position et de declenchement pour composants satellites deployables Download PDF

Info

Publication number
WO2000034125A1
WO2000034125A1 PCT/EP1999/009508 EP9909508W WO0034125A1 WO 2000034125 A1 WO2000034125 A1 WO 2000034125A1 EP 9909508 W EP9909508 W EP 9909508W WO 0034125 A1 WO0034125 A1 WO 0034125A1
Authority
WO
WIPO (PCT)
Prior art keywords
hold
sleeve
release device
housing
bandage
Prior art date
Application number
PCT/EP1999/009508
Other languages
German (de)
English (en)
Inventor
Dieter Pfefferkorn
Original Assignee
Astrium Gmbh
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 Astrium Gmbh filed Critical Astrium Gmbh
Priority to AU15590/00A priority Critical patent/AU1559000A/en
Priority to JP2000586586A priority patent/JP2002531328A/ja
Priority to EP99958165A priority patent/EP1137573A1/fr
Publication of WO2000034125A1 publication Critical patent/WO2000034125A1/fr

Links

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
    • B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
    • B64G1/2228—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state characterised by the hold-down or release mechanisms
    • 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
    • B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
    • B64G1/2221—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state characterised by the manner of deployment
    • B64G1/2222—Folding
    • 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
    • B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
    • B64G1/443—Photovoltaic cell arrays

Definitions

  • the invention relates to a hold-down and release device for deployable satellite components such as e.g. Solar generators, antennas, etc.
  • Hold-down and release devices for deployable components of satellites are intended to hold the satellite components in their retracted position and to release them in space due to a control requirement for deployment.
  • Hold-down and release devices of this type are known with a prestressed tie rod or a separable holding sleeve which, by means of its pretensioning force, holds the part to be held in position up to the point of deployment by means of a fastening or hold-down pin held in the holding device.
  • the fastening part is e.g. cut with a pyrotechnically operated cutting edge, or the holding device is released pyrotechnically.
  • a disadvantage of these devices is that the pyrotechnic actuation causes shock loads on the components to be held and in particular on their bearings, which damage the parts to be held or other satellite parts and can impair their function or service life.
  • EP 0 716 982 B2 describes a device in which a sleeve is wrapped in a bundle of loops which is cut through with a breaking device.
  • DE 196 49 739 C2 comprises a device in which a holding sleeve is wrapped with a wire, whereby after the wire has melted through, this wire loosens at one point and releases the sleeve.
  • a disadvantage of these devices is that no safe, defined triggering and opening of the device is guaranteed, and there is therefore a risk of the device jamming, which is the case when used with satellites, e.g. for the development of solar generators in orbit, would have fatal consequences.
  • Claims 1 and 3 each include a hold-down and release device for positive locking and triggering of a hold-down pin for parts of a satellite to be unfolded, which has a sleeve for positive locking of the hold-down pin, which is formed from at least two sleeve parts which are wrapped with a tensioning element, wherein at least one release element with a cutting edge is arranged on the hold-down and release device, which is moved in the direction of the clamping element due to a control specification in order to cut it.
  • the sleeve is arranged in a housing and the sleeve parts are biased against the housing.
  • This pretensioning ensures that the tensioning element is always kept under tension during cutting, which facilitates the cutting of the tensioning element. If the tensioning element is finally cut through, the sleeve is opened in a defined manner due to the prestressing of the sleeve parts and thus a reliable release of the hold-down pin is guaranteed.
  • the pretension does not act, as in the prior art, only between the individual parts of the sleeve, which under certain circumstances could still lead to jamming and thus to failure of the mechanism.
  • each of the sleeve parts is prestressed against the housing independently of the other sleeve part, so that the opening movements of the sleeve parts run independently of one another and thus greater security when opening the sleeve is guaranteed.
  • the sleeve parts can be biased in particular towards the housing by spring elements. This can be done, for example, by means of radially acting spring elements which, after the tensioning element has been cut, move the sleeve parts radially outward towards the housing.
  • the alternative teaching according to claim 3, which can also be used in combination with the above teaching, comprises a hold-down and release device described above, but now instead of or in addition to a bias of the sleeve parts against a housing is provided that the clamping element as Bandage is formed from several individual turns of a fiber, wherein the individual turns of the bandage are glued together.
  • the bandage is thus not, as in the prior art, designed as a loose loop bundle, but rather, by bonding the individual turns of the fiber at least in partial areas of the wrapping or the bandage, a composite material in the manner of a laminate is built up at least in these partial areas, which during the cutting process continues to largely maintain the clamping force generated by the clamping element.
  • the gluing of the individual turns guarantees that the remaining turns continue to hold the sleeve parts together and that the sleeve parts are only released when the last single turn is cut and the hold-down pin is triggered.
  • a defined triggering is achieved when cutting through the last turn of the fiber and, on the other hand, a safe opening, since after cutting the last turn there are no more windings of the fiber around the sleeve parts that could prevent the sleeve from being opened safely.
  • the individual turns of the bandage are glued together at two points on the circumference of the bandage.
  • the bond is to be arranged so that the cutting edge can cut the bandage in the area of a dividing line of the sleeve parts.
  • the bandage can be formed from an aramid fiber, for example.
  • Fig. 3 is a side view of the hold-down and release device
  • Fig. 6 is an exploded view of the hold-down and release device.
  • the hold-down and release device 1 has a substantially cylindrical housing 2 and also a substantially rotationally symmetrical, divisible holding sleeve or sleeve 3, which in its assembled state receives the end piece 4 of a holding-down pin 5.
  • the holding sleeve 3 is preferably designed as a two- (or more) divided rotationally symmetrical body with a first sleeve half or a first sleeve part 3a and a second sleeve half or a second sleeve part 3b, the two sleeve parts 3a, 3b having essentially the same shape .
  • the housing 2 rests with its first end 2a on the outer wall of a satellite (not shown), while its second end 2b faces the satellite part to be held.
  • the hold-down pin 6 is preferably screwed into an internal thread or nut thread 8 of the holding sleeve 3 arranged concentrically to the longitudinal axis 7 of the holding sleeve 3.
  • the hold-down pin 6 can also interact with the holding sleeve 3 in a form-fitting manner.
  • a housing cone or cone 9 is screwed into the housing 2 on the side facing the satellite components to be held.
  • the cone 9 lies in the screwed-in state with a conical contact surface 11 on a corresponding conical contact surface 12 of the sleeve 3. The ones to be kept towards
  • the end face of the cone 9 located on the satellite components preferably has a flange 15 with a bearing surface 16 for the satellite part to be fastened.
  • the housing 2 has holes 18 distributed in its circumferential direction and extending in the axial direction, through which a screw 19 projects in each case.
  • the screws 19 are in an outer wall of the satellite or a corresponding one
  • Fastening device of the same screwed in to fasten the hold-down and release device 1 thereon.
  • the housing 2 has a centering on its inner wall on the satellite wall, which accommodates a housing bridge 20.
  • the housing bridge 20 centers the housing to a hole in the satellite wall (not shown) by means of a centering pin 20a.
  • the holding sleeve 3 is a radially symmetrical body, preferably divided in two at 180 °, with a cylindrical outer surface, the conical contact surface 12 and the central nut thread 8.
  • the holding sleeve 3 can also be designed from more than two parts.
  • the holding sleeve 3 is held together by a bandage 29 in the circumferential direction.
  • the bandage 29 is pretensioned so that the sleeve parts 3a, 3b also lie without a gap under the radial forces which the hold-down pin 6 exerts on the two sleeve halves 3a, 3b due to a tensile load when the solar generators are held.
  • the prestress is permanently retained in the bandage 29, since the individual turns of the bandage 29 are glued together at two points on the circumference of the bandage.
  • Two fixing pins 20b, 20c which sit in the bridge part of the housing 2, engage in bores in the holding sleeve 3. They position the holding sleeve 3 in the housing 2 and act as an anti-rotation device for the holding sleeve 3 when the hold-down pin 6 is screwed in.
  • the bores lie in the parting plane of the sleeve halves 3a, 3b of the holding sleeve 3 and This does not hinder the separation of the hold-down and release device 1.
  • the holding sleeve 3 thus represents a rigid body, by means of which the holding-down pin 6 is supported on the conical contact surface 12 of the holding sleeve 3 on the housing cone 11.
  • the sleeve halves 3a, 3b are held in the housing 2 by means of screws 21, 23, which are screwed radially into this perpendicular to the parting plane of the holding sleeve 3, with retraction springs 22 in the axial direction and are pretensioned perpendicular to the parting plane in the direction of pulling apart the sleeve halves 3a, 3b.
  • the return springs 22 are preferably arranged between the screw head 23 and the bottom surface of an insert 24 inserted into corresponding bores in the housing 2 and are designed as coil springs.
  • Two screws 21, 23 are preferably provided for each sleeve part, which are screwed into the middle of the respective sleeve part 3a, 3b.
  • the hold-down and release device 1 has at least one release element 30 which cuts the bandage 29 on the basis of a control specification.
  • Two or more release elements 30 are preferably provided, each of which acts on the bandage 29 on the dividing line on the circumference of the holding sleeve 3 in order to cut through it.
  • Each trigger element 30 has a pressure spring 39 fastened to the housing 2 by means of connecting elements 32, a guide element 36 and a heat meter 37 a cutting edge 37a.
  • the cutting edge 37a is pretensioned by means of at least one leaf spring 39 fastened to the housing 2 by fastening elements 32.
  • the bandage 29 is preferably formed from an aramid fiber. They are severed by strong local heating under tension, which is present in the bandage 29.
  • the non-meltable and flame-retardant aramid fiber degrades beyond about 500 ° C in its strength properties so strongly that it affects its inner Preload as well as by the spring preload applied to the sleeve halves 3a, 3b at the heated point.
  • the bandage 29 is locally heated by an all-ceramic heating element 37 which heats the bandage 29.
  • the heating element 37 has the shape of a small plate and is pressed against the bandage 29 with a narrow side or cutting edge 37a for concentrated heat transfer.
  • the heating element 37 consists of an electrical resistance conductor made of doped ceramic, which is partially sintered with electrically insulated ceramic. Highly conductive ceramic contacts are guided to the surface of the heating elements 37 and connected to supply lines.
  • the heating element 37 is fastened in a thermally insulating holder 36, through which the electrical feed lines are also guided.
  • the holder 36 is guided in an opening of the housing 2 radially zir holding sleeve 3.
  • a preloaded spring 39 presses the heating element 37 radially onto the bandage 29.
  • the holding sleeve 3 is severed on the basis of a control specification by means of the trigger elements 30.
  • the radially preloaded screws 23 with the return springs 22 pull the sleeve halves 3a, 3b away from the hold-down pin 6 in the direction of the housing 2.
  • the positive locking of the internal thread 8 with the corresponding thread of the hold-down pin 6 is released and the hold-down pin 6 can be threaded through the bores of the housing cone 9 for the deployment of the satellite part to be held. Since the bandage 29 is not glued to the sleeve halves 3a, 3b, the severed bandage 29 can move freely on the lateral surface of the holding sleeve 3. The severed bandage 29 cannot hinder the separating movement of the sleeve halves 3a, 3b.

Landscapes

  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Clamps And Clips (AREA)

Abstract

L'invention concerne un dispositif de maintien en position et de déclenchement (1) pour le maintien à l'arrêt et le déclenchement, par liaison de forme, d'une tige de maintien (6) pour des éléments à déployer d'un satellite, caractérisé en ce qu'il comprend un boîtier (2) avec un manchon (3) disposé à l'intérieur, en ce que ledit manchon (3) est formé d'au moins deux éléments (3a, 3b) entourés d'une garniture (29) en fibres éventuellement collées entre elles, de préférence précontraints à l'encontre du boîtier (2), et en ce qu'il est prévu sur le boîtier (2) au moins un élément de déclenchement (30) muni d'une lame (37) qui est déplacée, par des moyens de commande, en direction de la garniture (29) en vue de découper cette dernière.
PCT/EP1999/009508 1998-12-08 1999-12-06 Dispositif de maintien en position et de declenchement pour composants satellites deployables WO2000034125A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
AU15590/00A AU1559000A (en) 1998-12-08 1999-12-06 Hold-down and triggering device for satellite components which fold out
JP2000586586A JP2002531328A (ja) 1998-12-08 1999-12-06 展張可能な人工衛星構造体用抑止・解放機構
EP99958165A EP1137573A1 (fr) 1998-12-08 1999-12-06 Dispositif de maintien en position et de declenchement pour composants satellites deployables

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19856446.5 1998-12-08
DE19856446A DE19856446C2 (de) 1998-12-08 1998-12-08 Niederhalte- und Auslösevorrichtung für entfaltbare Satellitenkomponenten

Publications (1)

Publication Number Publication Date
WO2000034125A1 true WO2000034125A1 (fr) 2000-06-15

Family

ID=7890285

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP1999/009508 WO2000034125A1 (fr) 1998-12-08 1999-12-06 Dispositif de maintien en position et de declenchement pour composants satellites deployables

Country Status (5)

Country Link
EP (1) EP1137573A1 (fr)
JP (1) JP2002531328A (fr)
AU (1) AU1559000A (fr)
DE (1) DE19856446C2 (fr)
WO (1) WO2000034125A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108995830A (zh) * 2017-11-07 2018-12-14 北京微分航宇科技有限公司 一种四点联动式压紧释放装置

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3924688A (en) * 1974-04-05 1975-12-09 G & H Technology Fire fighting system
EP0716982A1 (fr) * 1994-12-14 1996-06-19 FOKKER SPACE & SYSTEMS B.V. Système pour retenir et séparer des éléments de construction
DE19649739A1 (de) * 1996-11-30 1998-06-04 Daimler Benz Aerospace Ag Freigabevorrichtung für Niederhalter z. B. an Solargeneratoren

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3924688A (en) * 1974-04-05 1975-12-09 G & H Technology Fire fighting system
EP0716982A1 (fr) * 1994-12-14 1996-06-19 FOKKER SPACE & SYSTEMS B.V. Système pour retenir et séparer des éléments de construction
EP0716982B1 (fr) 1994-12-14 1999-09-15 Fokker Space B.V. Système pour retenir et séparer des éléments de construction
DE19649739A1 (de) * 1996-11-30 1998-06-04 Daimler Benz Aerospace Ag Freigabevorrichtung für Niederhalter z. B. an Solargeneratoren
DE19649739C2 (de) 1996-11-30 1998-11-12 Daimler Benz Aerospace Ag Freigabevorrichtung für Niederhalter z. B. an Solargeneratoren

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108995830A (zh) * 2017-11-07 2018-12-14 北京微分航宇科技有限公司 一种四点联动式压紧释放装置
CN108995830B (zh) * 2017-11-07 2023-06-30 北京微分航宇科技有限公司 一种四点联动式压紧释放装置

Also Published As

Publication number Publication date
JP2002531328A (ja) 2002-09-24
EP1137573A1 (fr) 2001-10-04
DE19856446A1 (de) 2000-06-21
DE19856446C2 (de) 2001-01-25
AU1559000A (en) 2000-06-26

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