WO2014019330A1 - Dispositif de raccordement et de déverrouillage de courroie à faible impact - Google Patents

Dispositif de raccordement et de déverrouillage de courroie à faible impact Download PDF

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Publication number
WO2014019330A1
WO2014019330A1 PCT/CN2013/000099 CN2013000099W WO2014019330A1 WO 2014019330 A1 WO2014019330 A1 WO 2014019330A1 CN 2013000099 W CN2013000099 W CN 2013000099W WO 2014019330 A1 WO2014019330 A1 WO 2014019330A1
Authority
WO
WIPO (PCT)
Prior art keywords
strips
strip
unlocking device
satellite
strap
Prior art date
Application number
PCT/CN2013/000099
Other languages
English (en)
Chinese (zh)
Inventor
康士朋
任海辽
唐杰
张醒
吴昊
Original Assignee
上海宇航系统工程研究所
中国长城工业集团有限公司
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 上海宇航系统工程研究所, 中国长城工业集团有限公司 filed Critical 上海宇航系统工程研究所
Publication of WO2014019330A1 publication Critical patent/WO2014019330A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
    • 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
    • B64G1/642—Clamps, e.g. Marman clamps

Definitions

  • the invention relates to a star-and-arrow connection unlocking device for a launch vehicle, in particular to a low-impact ⁇ 937 strap connection unlocking device which can be applied to a Chinese aerospace CZ-2, CZ-4 and other launch vehicles. Background technique
  • the star arrow connection unlocking device is an important part of the payload carrier of the launch vehicle and the upper stage.
  • the commonly used star arrow connection unlocking device at home and abroad is a strap connection unlocking device. Based on the advantages of reliability and high connection rigidity, the strap connection is unlocked.
  • the device has been widely used in the aerospace field at home and abroad, and is currently the preferred connection and unlocking method for spacecraft at home and abroad.
  • the conventional strap connection unlocking device is shown in FIG. 1, FIG. 2 and FIG. 3, and is generally composed of a strip 100, a clamp block 200, a separate fire component 300 (generally the explosion bolt shown in FIG. 3), and a tension spring 500.
  • the limit reed 400 and the like are composed.
  • the two strips 100 each have a half circumference and then have their openings arranged oppositely.
  • the two strips 100 are evenly spaced on the inner side of the circumference to be provided with a plurality of clips 200, and the satellites are passed through the V-shaped surface on the inner side of the clip 200.
  • the respective ends of the two strips 100 are joined by providing a separate fire element 300 at the tight band 130 at the end of the strip 100.
  • the pre-tightening force is applied to the strip 100 by tightening the splitting fire component 300, so that the strip 100 can be tightened at the periphery of the docking frames 600 and 700 for the purpose of reliably connecting the satellite to the rocket.
  • the control system Upon reaching the satellite entry point, the control system detonates the split firework component 300. At the same time as the strip 100 is opened, the strip 100 is pulled toward the rocket by the tension spring 500. At this time, the strap connection unlocking device Separating impact is generated under the impact force of the split fire component 300, and the connection and unlocking of the star arrow are achieved.
  • the limit reed 400 is disposed on the outer side of the circumference of the joint of the two strips 100 to limit the maximum diameter of the strip 100 when it is opened, to avoid damaging other components on the satellite body.
  • ⁇ 937 strap connection unlocking device refers to the star arrow connection unlocking device with a diameter of ⁇ D930mm, which is generally used for medium-sized and large-scale satellite launching tasks. Separating the pyrotechnic components as an important part of the strap connection unlocking device, the performance of the product will greatly affect the separation time of the strap connecting and unlocking device Shock.
  • the conventional ⁇ 937 belt connection unlocking device uses a split fire-fighting element with an axial load capacity of 6t, which has a high drug content and a large separation impact.
  • the object of the present invention is to provide a low-impact ⁇ 937 strap connection unlocking device applied to the field of rocket rocket arrow and arrow connection.
  • the optimization of the separation of the fire component is optimized. Replacing the original 6t split fire-fighting component with a split-fire component with an axial load capacity of 3t to reduce the separation shock caused by the unlocking of the strap connection unlocking device, thereby reducing the impact of the separation impact belt on the satellite product .
  • the technical solution of the present invention is to provide a low impact strap connection unlocking device, which mainly comprises two strips, a plurality of clips, and two separate pyrotechnic components; each of the separated fire components
  • the axial load carrying capacity is 3t;
  • the two strips respectively form a half circumference on the periphery of the docking frame of the satellite and the rocket, so that the first ends of the two strips are opposite each other, and the second ends of the two strips are also opposite Connecting the first ends of the two strips by a first split fire element, and connecting the second ends of the two strips by a second split fire element;
  • a V-shaped surface is opened on one side of each of the clamping blocks, and a side opposite to the V-shaped surface is fixedly connected to an inner side of the strip through the clamping block, and the plurality of the clamping blocks are evenly spaced and disposed at intervals Two inner sides of the circumference of the strip;
  • the split firework component By tightening the split firework component, sufficient preloading force is applied to the strip to enable the strip to be tightened around the satellite and rocket docking frame, and to simultaneously mesh the satellite and the arrow through the V-shaped surface of the clamp.
  • the docking frame enables a reliable connection between the satellite and the rocket; by detonating at least one of the separate pyrotechnic components to break it, the unlocking separation of the two strips can be achieved.
  • the first end and the second end of each of the strips are respectively provided with an annular gap, and a tight band column is disposed correspondingly in the gap; and a through opening is also formed in the gap position of each strip.
  • a connecting hole is formed in a position corresponding to the opening on each of the tight band columns; so that any one of the separation fires is One end of the component can pass through the opening of the strip and the connecting hole of the strap, so that the corresponding connection of the two strips is achieved.
  • Each of the separated fire-fighting elements is provided with a connecting portion, a limiting portion, and an initiating portion; wherein the connecting portion is surrounded by a groove as a breaking position when unlocking;
  • the first one of the separated fire-fighting elements is provided with one end of the connecting portion, which can sequentially pass through the opening of the first end of the first strip, the connecting strip of the first strip of the first strip, the second strip a connecting hole of the first end of the strip, and an opening of the first end of the second strip, at which time the connection of the limiting portion of the separated fire element to the tight band of the first strip
  • the limiting action at the hole is such that the limiting portion and the other end of the detonating portion are left outside the opening of the first end of the first strip; by matching the lock nut and separating the pyrotechnics
  • the connecting portion of the component is fastened to realize the connection of the first ends of the two strips; the second splitting fire-fighting component is connected to the second end of the two strips and the locking posts of the second ends of the two strips
  • the structure is the same.
  • each of the separate pyrotechnic elements is provided with a plurality of redundant igniters.
  • the low-impact strap connection unlocking device further comprises two limiting springs, each of the limiting springs is provided with two connecting segments, each connecting segment comprising a top surface, a side surface and a connecting type "" a bottom surface; between the two sides of the connecting section is further provided with a stretching section, the stretching section is W-shaped;
  • the top surface and the bottom surface of the first set of connecting segments in the first limiting strip are fixedly connected to the top surface and the bottom surface of the tight strip column at the first end of the first strip; the limiting reed The top surface and the bottom surface of the second set of connecting segments are correspondingly connected with the top surface and the bottom surface of the tight strip column at the first end of the second strip; and the sides and the stretching of the two connecting segments of the limiting spring
  • the segments are located on the outer side of the circumference of the first end of the two strips; the second limit spring is identical in structure to the tight band of the second end of the two strips;
  • a stretched section of a limit reed corresponding to the outer side of the separate fire-fighting element is elongated under the action of the separation force, and passes through the limit reed Simultaneously connect the two strips after unlocking.
  • the low-impact ⁇ 937 strap connection unlocking device of the invention conforms to the development requirements of the satellite technology, and replaces the original 6t split fire-fighting component by using a split-fire component with an axial load-bearing capacity of 3t, and the 3t separation of the present invention
  • the fire-fighting component can obtain the following beneficial effects: 1.
  • the structural form has a large change; 2.
  • the igniter adds redundant design, which improves the reliability of the separated fire-fighting component; 3.
  • the charge is reduced, and the residual energy is reduced after separation. . Therefore, on the basis of realizing the reliable connection of the star arrow, the star arrow is reduced. Off-time impact force, reducing the impact of the separation of the star and arrow on the satellite
  • FIG. 1 is a schematic view showing the overall structure of a conventional strap connection unlocking device
  • Figure 2 is a cross-sectional view taken along the line A-A when the strap connection unlocking device shown in Figure 1 is used;
  • FIG. 3 is a schematic structural view of a single 6t split fire-fighting component in a conventional 937 strap connection unlocking device
  • FIG. 4 is a schematic overall structural view of the low-impact strap connection unlocking device of the present invention
  • FIG. 5 is a low-impact package shown in FIG.
  • FIG. 6 is a schematic structural view of a single clip in the low-impact strap connection unlocking device shown in FIG. 4
  • FIG. 7 is a single diagram in the low-impact strap connection unlocking device shown in FIG. Schematic diagram of the 3t separation of the firework components;
  • Figure 8 is a schematic view showing the structure of a single limit reed in the low-impact strap connection unlocking device shown in Figure 4;
  • Figure 9 is a structure of the separation of the fire-fighting component and the strip in the low-impact strap connection unlocking device of the present invention; Enlarged schematic diagram;
  • Fig. 10 is an enlarged schematic view showing the structure of the low-impact belt connecting and unlocking device of the present invention on the basis of the connection separating the fire-fighting elements and the strips shown in Fig. 9, and further connecting the limiting reeds. The best way to implement the invention
  • the low-impact ⁇ 937 strap connection unlocking device of the present invention comprises two strips 10, a plurality of clips 20 (for example, 32), two limit reeds 40, and two separates. Firework component 30.
  • the strip 10 is made of titanium alloy plate TB2 and has a thickness of 1.8 mm.
  • the first end and the second end of each strip 10 are respectively bent to form an annular gap 11 so that the tight band 13 is correspondingly disposed in the gap 11; and the opening 12 extending horizontally is also provided at the position of the gap 11;
  • the two strips 10 each enclose a half circumference and have their half-circumferential openings opposed, one end of the split fire element 30 can be passed through the opening 12 at the end of the strip 10 and the connection through the strap 13
  • the holes realize the corresponding connections of the two strips 10 (the connection of these parts will be specifically described below).
  • the material of the clamp 20 is selected from forging LD10, in order to ensure the star
  • the reliable connection of the arrows, usually on the inside of the clamp 20, is machined by a special milling cutter to form a V-shaped face 21 through which the docking frame connecting the satellite and the rocket is engaged.
  • a plurality of the clips 20 are fixedly coupled to the inner side of the strip 10 on the outer side thereof (ie, the side opposite to the V-shaped surface 21) such that the clips 20 are evenly spaced and distributed around the two strips 10 Inside the circumference.
  • the split fire component 30 is used to connect and unlock the two strips 10 in the strap connection unlocking device, which is an important component that constitutes the strap connection unlocking device.
  • the split fire-fighting elements 30 in this embodiment are sequentially disposed as a connecting portion 31, a limiting portion 32, and an initiating portion 33.
  • the connecting portion 31 is a columnar body, and a groove 311 is formed on the upper surface as a breaking position at the time of unlocking.
  • the stopper portion 32 is provided with a plurality of columns having a step shape, and the diameters of the columns are larger than the diameter of the columnar body of the connecting portion 31.
  • the detonating portion 33 is provided with a plurality of redundant igniters (for example, two).
  • the substance for detonating may be distributed throughout the connecting portion 31, the limiting portion 32 and the detonating portion 33 of the separating pyrotechnic component 30.
  • the split fire element 30 has an axial load carrying capacity of 3t.
  • the split firework component 30 can reduce the charge amount to reduce the residual energy after the separation of the star arrow. Therefore, when the first split firework component 30 is provided with one end of the columnar body, the first strip 10 is sequentially passed through.
  • the opening 12 of the end, the connecting hole of the tight band 13 at the first end of the first strip 10, the connecting hole of the tight band 13 at the first end of the second strip 10, and the first strip 10 first
  • the limiting portion 32 of the split-fire element 30 is just caught at the connecting hole of the strap 13 of the first strip 10, that is, the limit is set on the split-fire element 30.
  • the other end of the portion 32 and the detonating portion 33 is left outside the opening 12 of the first strip 10; the locking nut 34 is then fastened at the connecting portion 31 of the split fire element 30 to achieve the first strip 10
  • One end of the connection The second ends of the two strips 10 are joined in the same manner by a second split fire element 30, and will not be described again.
  • the split fire element 30 By tightening the split fire element 30, sufficient preloading force can be applied to the strip 10 to enable the strip 10 to be tightened around the satellite and rocket docking frames for a reliable connection.
  • the separation of the two strips 10 is achieved by detonating at least one of the separate pyrotechnic elements 30 to break it.
  • the limiting reed 40 is usually formed by bending a 0.5 mm steel plate, and each limiting reed 40 is provided with two connecting segments, and each connecting segment includes a connection.
  • the top surface 41, the side surface 43, and the bottom surface 42 of the "" type; between the side faces 43 of the two sets of connecting sections are further provided with a stretched section 44, which is W-shaped.
  • the top surface 41 and the bottom surface 42 of one of the connecting segments of the limiting reed 40 are connected to the top and bottom surfaces of the strap 13 of one of the strips 10; and the other connecting portion of the limiting reed 40
  • the top surface 41 and the bottom surface 42 are similarly connected to the top and bottom surfaces of the strap 13 of the other strip 10.
  • the side 43 and the stretched section 44 of the limiting spring 40 are located in two strips. The outer side of the circumference of the belt 10 joint. After the split firework element 30 is unlocked, the stretched section 44 of the limit spring 40 is elongated under the action of the splitting force and simultaneously connects the unlocked two strips 10.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Remote Sensing (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Clamps And Clips (AREA)

Abstract

L'invention concerne un dispositif de raccordement et de déverrouillage de courroie à faible impact. Lorsque deux bandes (10) forment respectivement des demi-circonférences, des premières extrémités des deux bandes (10) sont raccordées en conséquence par un élément de feu d'artifice permettant la séparation (30) et des secondes extrémités des bandes (10) sont raccordées en conséquence par un autre élément de feu d'artifice permettant la séparation (30). Une pluralité de blocs de serrage (20) est répartie à intervalles réguliers sur le côté interne de la circonférence formée par les deux bandes (10). Une force de pré-serrage suffisante est exercée sur les bandes (10) par le vissage des éléments de feu d'artifice permettant la séparation (30) de sorte que les bandes (10) puissent être serrées sur la périphérie d'une structure d'amarrage d'un satellite et d'une fusée, et des surfaces en V (21) des blocs de serrage (20) sont simultanément engrenées avec la structure d'amarrage du satellite et de la fusée afin d'obtenir un raccordement fiable entre le satellite et la fusée. Les deux bandes (10) peuvent être déverrouillées et séparées l'une de l'autre par la détonation d'au moins l'un des éléments de feu d'artifice permettant la séparation (30) pour la fracturation de celui-ci. Des feuilles de ressort de limitation (40) sont disposées sur l'extérieur des sections de raccordement des deux bandes (10) pour raccorder les deux bandes (10) qui ont été déverrouillées. Le dispositif de raccordement et de déverrouillage de courroie à faible impact présente les avantages suivants : la réduction de la force d'impact générée lorsque le satellite est séparé de la fusée et la réduction de l'influence de l'impact de séparation sur le satellite sur la base d'un raccordement fiable entre le satellite et la fusée.
PCT/CN2013/000099 2012-07-30 2013-01-30 Dispositif de raccordement et de déverrouillage de courroie à faible impact WO2014019330A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201210266549.6 2012-07-30
CN201210266549.6A CN102767996B (zh) 2012-07-30 2012-07-30 低冲击包带连接解锁装置

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018115540A1 (fr) * 2016-12-22 2018-06-28 Airbus Defence and Space S.A. Dispositif de liaison/séparation pour séparer des satellites de navettes ou de lanceurs de satellites
CN111619831A (zh) * 2020-04-29 2020-09-04 航天东方红卫星有限公司 一种连杆式星箭分离机构
FR3096033A1 (fr) * 2019-05-14 2020-11-20 Spirit Technologies Système d’accouplement circonférentiel, notamment pour un accouplement d’un satellite et d’un porte-satellite

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CN102767996B (zh) * 2012-07-30 2014-08-27 上海宇航系统工程研究所 低冲击包带连接解锁装置
CN103335565B (zh) * 2013-06-18 2015-11-18 上海宇航系统工程研究所 一种包带连接解锁装置
CN103673789B (zh) * 2013-11-18 2015-07-08 北京宇航系统工程研究所 一种分离螺母解锁临界装药量的确定方法
CN103673786B (zh) * 2013-11-26 2015-07-08 北京宇航系统工程研究所 一种小直径助飞火箭用降冲击尾段线性爆炸分离装置
CN104760709A (zh) * 2015-03-30 2015-07-08 中国科学院长春光学精密机械与物理研究所 爆炸螺栓驱动的包带式解锁分离装置
RU2648522C2 (ru) * 2015-11-06 2018-03-26 Акционерное общество "Информационные спутниковые системы" имени академика М.Ф. Решетнёва" Устройство отделения полезной нагрузки
CN107954006B (zh) * 2017-11-23 2019-12-20 北京宇航系统工程研究所 刚性包带释放装置
CN110254747B (zh) * 2019-05-27 2020-12-01 北京强度环境研究所 一种基于包带的测力支撑装置
CN110285176B (zh) * 2019-07-19 2024-06-18 厦门大学 基于反波长特性的火工分离降冲击装置及其制备工艺
US11787570B2 (en) * 2020-08-06 2023-10-17 Raytheon Company Multi-part Marman band clamp with retainer
CN117208237B (zh) * 2023-10-12 2024-02-09 大连理工大学 星箭解锁分离包带的安装调整方法、装置及系统
CN117663899A (zh) * 2023-12-29 2024-03-08 北京天兵科技有限公司 一种快速自动脱落的连接器、设计方法和火箭发射系统

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN87103835A (zh) * 1986-05-27 1987-12-09 休斯航空公司 航天飞行器用的夹紧连接装置
CN1212940A (zh) * 1997-09-26 1999-04-07 建筑航空股份有限公司 一种用于固定和分离人造卫星的系统
WO2001085542A1 (fr) * 2000-05-10 2001-11-15 Saab Ericsson Space Ab Dispositif et procede permettant de relier deux parties d'un a craft
EP2325086A1 (fr) * 2009-11-18 2011-05-25 RUAG Schweiz AG Système de séparation de choc zéro
WO2011102448A1 (fr) * 2010-02-19 2011-08-25 三菱重工業株式会社 Dispositif, système et procédé d'assemblage/libération
CN102767996A (zh) * 2012-07-30 2012-11-07 上海宇航系统工程研究所 低冲击包带连接解锁装置
CN202814245U (zh) * 2012-07-30 2013-03-20 上海宇航系统工程研究所 低冲击包带连接解锁装置

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN87103835A (zh) * 1986-05-27 1987-12-09 休斯航空公司 航天飞行器用的夹紧连接装置
CN1212940A (zh) * 1997-09-26 1999-04-07 建筑航空股份有限公司 一种用于固定和分离人造卫星的系统
WO2001085542A1 (fr) * 2000-05-10 2001-11-15 Saab Ericsson Space Ab Dispositif et procede permettant de relier deux parties d'un a craft
EP2325086A1 (fr) * 2009-11-18 2011-05-25 RUAG Schweiz AG Système de séparation de choc zéro
WO2011102448A1 (fr) * 2010-02-19 2011-08-25 三菱重工業株式会社 Dispositif, système et procédé d'assemblage/libération
CN102767996A (zh) * 2012-07-30 2012-11-07 上海宇航系统工程研究所 低冲击包带连接解锁装置
CN202814245U (zh) * 2012-07-30 2013-03-20 上海宇航系统工程研究所 低冲击包带连接解锁装置

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018115540A1 (fr) * 2016-12-22 2018-06-28 Airbus Defence and Space S.A. Dispositif de liaison/séparation pour séparer des satellites de navettes ou de lanceurs de satellites
US11247788B2 (en) 2016-12-22 2022-02-15 Airbus Defence and Space S.A. Connection/separation device for separating satellites from shuttles or from satellite dispensers
FR3096033A1 (fr) * 2019-05-14 2020-11-20 Spirit Technologies Système d’accouplement circonférentiel, notamment pour un accouplement d’un satellite et d’un porte-satellite
CN111619831A (zh) * 2020-04-29 2020-09-04 航天东方红卫星有限公司 一种连杆式星箭分离机构

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CN102767996B (zh) 2014-08-27

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