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WO2003033349A1 - Couplage pour vaisseau spatial - Google Patents

Couplage pour vaisseau spatial Download PDF

Info

Publication number
WO2003033349A1
WO2003033349A1 PCT/SE2002/001801 SE0201801W WO03033349A1 WO 2003033349 A1 WO2003033349 A1 WO 2003033349A1 SE 0201801 W SE0201801 W SE 0201801W WO 03033349 A1 WO03033349 A1 WO 03033349A1
Authority
WO
WIPO (PCT)
Prior art keywords
coupling
inner flange
protective envelope
vessel
vessel part
Prior art date
Application number
PCT/SE2002/001801
Other languages
English (en)
Inventor
Torbjörn Andersson
Original Assignee
Saab Ericsson Space Ab
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 Saab Ericsson Space Ab filed Critical Saab Ericsson Space Ab
Publication of WO2003033349A1 publication Critical patent/WO2003033349A1/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
    • B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
    • B64G1/641—Interstage or payload connectors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/002—Launch systems

Definitions

  • the invention concerns a coupling for a space vessel, which coupling is intended to hold together a vessel part and a protective envelope that is separable from the space vessel. More specifically, the invention concerns a separable coupling that comprises a number of clamps by means of which an encircling strap is pressed against flanges on the vessel part and the protective envelope. The vessel part and the protective envelope are held together by the encircling strap. When the encircling strap is released, the protective envelope separates from the vessel part.
  • the protective envelope When satellites are launched for placement into orbit around the earth, the sensitive satellite equipment is protected from the atmosphere by a protective envelope, or "fairing". This envelope is fastened to the launch rocket or a so-called a "launcher part" of the launch rocket.
  • the protective envelop consists of two or more parts, which are joined by means of a coupling device. When the parts of the protective envelope are separated from the rocket, all acceleration of said parts ceases, while the acceleration of the rocket continues. The parts of the protective envelope fall down toward the atmosphere and burn up.
  • the coupling device constitutes an important structural element for absorbing the forces at work between the vessel part and the protective envelope during the launch of the space vessel.
  • the coupling device must be of low weight, and it must be designed for extremely high reliability, given the extremely high cost of such launches. Any faults that might arise once the vessel has left the group are impossible to rectify.
  • the coupling devices must be designed so that, up to the time of separation, they hold the vessel part and the protective envelope together with such force that the mutual movement between these two components is minimized.
  • the current art utilizes a pyrotechnical linear charge around the circumference in order to shear off the structural element. These charges must be oversized in order to achieve satisfactory reliability. This result in major shock effects when the coupling is released, which can result in damage to sensitive electronics in the satellites.
  • a technique involving tension straps is currently used for separating satellites. This technique does not currently work satisfactorily for securing a protective envelope to a vessel part. This is due mainly to the large circumference of the space vessel, which entails that extremely high tension would be necessary in the tension strap to hold the envelope in place securely.
  • the object of the invention is to solve one or more of the aforementioned problems. This is achieved by means of a device according to claim 1.
  • a vessel part and a protective envelope that is separable from the vessel part are held together by a coupling, which comprises a first outer flange arranged on the vessel part, a second outer flange arranged on the protective envelope, a number of clamps, and a tension element surrounding said clamps.
  • the vessel part further comprises a radially inwardly oriented first inner flange. This is integrally realized with one or more surrounding elements, which at least partially surround a radially inwardly oriented second inner flange on the protective envelope.
  • the surrounding element extends uninterrupted along a periphery of the vessel part, and is in engagement with the first inner flange along the entire extent of the flange.
  • the surrounding element is in engagement with the first inner flange in a plurality of areas distributed along the periphery of the flanges, which areas are separate from one another.
  • said surrounding elements comprise a plurality of clamping lips.
  • the clamping lips When the tension element is mounted around the clamps, the clamping lips are pressed against corresponding upper contact surfaces on the second inner flange of the protective envelope.
  • the surrounding element with its clamping lips contributes to fixedly secure the inner flange of the envelope in both the radial direction and the longitudinal direction.
  • the protective envelope may surround one or more satellites, which are held together with the vessel part.
  • the purpose of the coupling is to absorb divisive forces that arise between the vessel part and the protective envelope during launching of the space vessel, and while maneuvering in orbit up until the moment of separation.
  • Designing inner flanges with an integrated surrounding element produces a coupling in which coherence and separation can be achieved without overly high stress in the surrounding tension element. Owing to the design of the surrounding element, the inner flanges constitute a new supporting and load- bearing element in the coupling.
  • a space vessel is generally designated by 1 in the drawing.
  • the vessel comprises a protective envelope 3 that is separable from a vessel part 2, which envelope is arranged so as to surround satellite equipment arranged on the vessel part.
  • a coupling 4 is arranged so as to hold together the two parts 2, 3 during the portion of the time the coupling is used.
  • the coupling 4 has a first outer flange 5 on an upper part of the vessel part 2 and a second outer flange 6 on a lower part of the protective envelope 3. These flanges are radially outwardly oriented relative to a centerline through the space vessel.
  • the coupling further has one or more clamps 7 distributed about the periphery of the flanges 5, 6.
  • a tension element 8 runs around or through the clamps 7 and presses them radially inward against the flanges 5, 6.
  • the clamps 7 are arranged so as to connect the outer flanges 5, 6 when the clamps are conveyed in over the flanges. The clamps are pressed radially inward against the outer flanges 5, 6 by applying a force to the tension strap 8.
  • the radial force is transferred by the tension strap 8 as a clamping force, which clamps the flanges 5, 6 against one another.
  • the radially active force is transferred in that the inner surfaces of the clamps have outwardly inclined relief angles.
  • the outer surfaces of the flanges should be inclined somewhat so that they fit by conformity into the inner surfaces of the clamps.
  • the coupling also has a first inner flange 9 arranged on the vessel part, and a second inner flange 11 arranged on the protective envelope. These flanges extend radially in toward an imaginary centerline through the space vessel.
  • a surrounding element 10 is integrally realized with the first inner flange 9 and comprises a clamping lip 10a, which at least partly abuts an upper contact surface 1 la on the second inner flange 11.
  • the second inner flange 11 is surrounded on each side by the combination of the first inner flange 9 and the surrounding element 10.
  • the first inner flange 9 extends in essentially the same plane as the first outer flange 5.
  • a support surface is thereby formed on the top of the first outer flange and on the first inner flange.
  • a lower contact surface 1 lb on the second inner flange 11 rests on that part of the support surface that is formed by the first inner flange.
  • the clamping lip 10a is essential for fixedly securing the second inner flange in both the radial direction and the longitudinal direction.
  • the clamping lip is allowed to abut against the upper contact surface 1 la of the second inner flange.
  • Both the surface of the clamping lip 10a that faces the second inner flange 11 and the upper contact surface 1 la are oriented at the angle ⁇ relative
  • the angle ⁇ can be varied, assuming that measures are taken to eliminate the risk of self-locking in the mounted state.
  • the two surfaces can also exhibit different angles relative to the normal plane.
  • the protective envelope 3 can be divided into at least two separable parts along a longitudinal direction of the protective envelope 3. Separation of these protective element parts begins upon the release of the tension strap 8. This movement is possible because the protective envelope 3 can be separated into at least two separate parts.
  • the vessel part 2 continues along the planned orbit, while the released protective envelope 3 simultaneously falls down toward the atmosphere in at least two separate parts.

Landscapes

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

Abstract

Cette invention concerne un couplage (4) destiné à un vaisseau spatial (1) permettant d'assembler une partie d'un vaisseau (2) et une enveloppe protectrice (3) qui peut être séparée de ladite partie du vaisseau (2). Le couplage comprend un premier rebord externe (5) disposé sur la partie du vaisseau (2), et un second rebord externe (6) disposé sur l'enveloppe protectrice. Ce couplage comporte, en outre, un certain nombre de fixations (7) qui sont distribuées le long de la périphérie des rebords (5, 6), de manière à transférer des forces radiales à partir d'un élément de tension entourant les fixations (5, 6). Les rebords externes sont joints par la combinaison de fixations et d'éléments de tension. Ce couplage comprend également un second rebord interne orienté radialement vers l'intérieur (11), disposé sur la partie du vaisseau (2). Ce premier rebord interne (9) est intégralement constitué d'au moins un élément environnant (10) qui entoure au moins partiellement le second rebord interne (11).
PCT/SE2002/001801 2001-10-19 2002-10-03 Couplage pour vaisseau spatial WO2003033349A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
SE0103508-8 2001-10-19
SE0103508A SE0103508L (sv) 2001-10-19 2001-10-19 Förband vid en rymdfarkost

Publications (1)

Publication Number Publication Date
WO2003033349A1 true WO2003033349A1 (fr) 2003-04-24

Family

ID=20285720

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/SE2002/001801 WO2003033349A1 (fr) 2001-10-19 2002-10-03 Couplage pour vaisseau spatial

Country Status (2)

Country Link
SE (1) SE0103508L (fr)
WO (1) WO2003033349A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107532923A (zh) * 2015-04-30 2018-01-02 沃尔德伍卫星有限公司 用于装配和部署卫星的系统和方法
CN107954006A (zh) * 2017-11-23 2018-04-24 北京宇航系统工程研究所 刚性包带释放装置
EP3517448A1 (fr) * 2017-05-10 2019-07-31 RUAG Space AB Joint de charge utile

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5649680A (en) * 1994-06-14 1997-07-22 Saab-Scania Combitech Aktiebolag Joint for dismountably attaching adapter to a launcher with satellite
US6290182B1 (en) * 1999-02-03 2001-09-18 Saab Ericsson Space Ab Joint for space vehicle

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5649680A (en) * 1994-06-14 1997-07-22 Saab-Scania Combitech Aktiebolag Joint for dismountably attaching adapter to a launcher with satellite
US6290182B1 (en) * 1999-02-03 2001-09-18 Saab Ericsson Space Ab Joint for space vehicle

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107532923A (zh) * 2015-04-30 2018-01-02 沃尔德伍卫星有限公司 用于装配和部署卫星的系统和方法
EP3289313A4 (fr) * 2015-04-30 2018-08-08 Worldvu Satellites Limited Système et procédé pour assembler et déployer des satellites
EP3517448A1 (fr) * 2017-05-10 2019-07-31 RUAG Space AB Joint de charge utile
US10518912B2 (en) 2017-05-10 2019-12-31 Ruag Space Ab Payload joint
EP3635265A4 (fr) * 2017-05-10 2021-01-13 RUAG Space AB Joint et égreneur
US11447276B2 (en) 2017-05-10 2022-09-20 Ruag Space Ab Joint and payload dispenser
CN107954006A (zh) * 2017-11-23 2018-04-24 北京宇航系统工程研究所 刚性包带释放装置

Also Published As

Publication number Publication date
SE0103508D0 (sv) 2001-10-19
SE518171C2 (sv) 2002-09-03
SE0103508L (sv) 2002-09-03

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