JPH0439200A - Launch-lock system applied to small pocket/micro-gravity experimental device - Google Patents
Launch-lock system applied to small pocket/micro-gravity experimental deviceInfo
- Publication number
- JPH0439200A JPH0439200A JP2146121A JP14612190A JPH0439200A JP H0439200 A JPH0439200 A JP H0439200A JP 2146121 A JP2146121 A JP 2146121A JP 14612190 A JP14612190 A JP 14612190A JP H0439200 A JPH0439200 A JP H0439200A
- Authority
- JP
- Japan
- Prior art keywords
- support
- experimental device
- base plate
- electromagnetic
- launch
- Prior art date
- Legal status (The legal status 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 status listed.)
- Granted
Links
- 230000005486 microgravity Effects 0.000 title claims abstract description 24
- 239000002184 metal Substances 0.000 abstract 2
- 230000008878 coupling Effects 0.000 abstract 1
- 238000010168 coupling process Methods 0.000 abstract 1
- 238000005859 coupling reaction Methods 0.000 abstract 1
- 238000012423 maintenance Methods 0.000 description 9
- 230000001133 acceleration Effects 0.000 description 5
- 238000002474 experimental method Methods 0.000 description 5
- WABPQHHGFIMREM-UHFFFAOYSA-N lead(0) Chemical compound [Pb] WABPQHHGFIMREM-UHFFFAOYSA-N 0.000 description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000007613 environmental effect Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000009835 boiling Methods 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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
- B64G1/645—Separators
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Lock And Its Accessories (AREA)
- Testing Of Engines (AREA)
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は小型ロケット・微小重力維持技術実験装置に適
用されるＬＡＵＮＣＨ−ＬＯＣＫＩｌ横に関する。DETAILED DESCRIPTION OF THE INVENTION [Industrial Application Field] The present invention relates to a LAUNCH-LOCK Il side applied to a small rocket/microgravity maintenance technology experimental device.
〔従来の技術］
従来、小型ロケット・微小重力維持技術実験装置は第７
図に示すように小型ロケント実験機器部の中央部のステ
ージ３０に囲まれた場所に設置され、宇宙（微小重力）
環境下でのプール沸騰実験、気泡挙動観察実験及び気泡
操作実験等に用いられている。第８図に示すように実験
装置の上下方向の移動はＡＩＲ−？ｌＡＴ支持具３４で
止め、左右方向の移動は実験装置左右移動止め金具３５
によって止めている。[Conventional technology] Previously, the small rocket/microgravity maintenance technology experimental equipment was
As shown in the figure, it is installed in a place surrounded by the stage 30 in the center of the small Rokent experimental equipment department.
It is used for environmental pool boiling experiments, bubble behavior observation experiments, bubble manipulation experiments, etc. As shown in Figure 8, the vertical movement of the experimental apparatus is AIR-? It is stopped by the lAT support 34, and the left and right movement of the experimental equipment is stopped by the left and right movement stopper 35 of the experimental equipment.
It is stopped by.
なお、第７図、第８図において、１は上部防振材支持プ
レート、２は上部防振材、３はカバー４は支持ベースプ
レート、５はＬＡＵＮＣ）Ｉ −ＬＯＣＫ機構、６は主
ベースプレート、２７は微小重力実験装置、２８は小型
ロケット実験機器部、２９は水密隔壁、３２はＡＩＲ−
ＭＡＴである。7 and 8, 1 is an upper vibration isolator support plate, 2 is an upper vibration isolator, 3 is a cover 4 is a support base plate, 5 is a LAUNC) I-LOCK mechanism, 6 is a main base plate, 27 28 is the small rocket experimental equipment department, 29 is the watertight bulkhead, 32 is the AIR-
It is MAT.
〔発明が解決しようとする課題］
上記従来の小型ロケット・微小重力維持技術実験装置に
は解決すべき次の課題があった。[Problems to be Solved by the Invention] The above-mentioned conventional small rocket/microgravity maintenance technology experimental device had the following problems to be solved.
即ち、微小重力維持技術実験装置のＬＡｔｌＮＣＨＬＯ
ＣＫ機構に要求される技術的課題は下記イ〜ホに示す通
りであるにも拘らず、従来のＡＩＲ−ＭＡＴ式は環境温
度の変化に伴ない、内部気体の体積が変化して、それに
取付けられた実験装置が応動し、確実にＬＯＣＫ出来な
いという問題があった。That is, LAtlNCHLO, a microgravity maintenance technology experimental device.
Although the technical issues required for the CK mechanism are as shown in A to E below, the conventional AIR-MAT type is difficult to install because the internal gas volume changes with changes in the environmental temperature. There was a problem in that the experimental equipment reacted when the device was locked and could not be reliably locked.
イ、長時間ＬＡＵＮＣＨ−ＬＯＣＫ機構を作動させるこ
と。B. Operate the LAUNCH-LOCK mechanism for a long time.
口、設計制限荷重・設計終極荷重に耐えられる構造であ
ること。The structure must be able to withstand the design limit load and design ultimate load.
ハ、なめらかに不要な重力加速度が発生することなく
ＵＮＬＯＣＫＩＮＧ出来る構造であること。Ha, smoothly without unnecessary gravitational acceleration
It must have a structure that allows UNLOCKING.
二、ＵＮＬＯＣＫＩＮＧ後、不要な重力加速度がかから
ないこと。2. After UNLOCKING, no unnecessary gravitational acceleration is applied.
ホ、確実にＲＥＬＯＣＫ出来ること。Ho, you can definitely RELOCK.
［課題を解決するための手段］
本発明は上記課題の解決手段として、ロケットの機軸に
対し直交方向に設けられて微小重力実験装置を支持する
支持ベースプレートと、ロケットの機体側に回動可能に
枢支されその先端を上記機軸にほぼ対称にかつ上記支持
ベースプレートに係脱可能に設けられた複数の支持レバ
ーと、同支持レバーを一方へ回動させるハネと、同支持
レバーを他方へ回動させる側の回動面内に上記支持ベー
スプレートとほぼ平行に所定の間隔を保って機体側に設
けられた２個の１を磁クサビと、同２個の電磁クサビの
各感応片を連結する引張りバネと、上記各感応片のうち
上記支持レバーに近い側の感応片と上記支持レバーとを
連結する駆動棒とを具備してなることを特徴とする小型
ロケット・微小重力実験装置に適用されるＬＡＩＩＮＣ
Ｈ−ＬＯＣＫ機構を提供しようとするものである。[Means for Solving the Problems] As a means for solving the above problems, the present invention provides a support base plate that is provided in a direction orthogonal to the axis of a rocket and supports a microgravity experimental device, and that is rotatable toward the body side of the rocket. a plurality of support levers that are pivotally supported and whose tips are substantially symmetrical to the machine axis and are removably connected to the support base plate; a spring that rotates the support lever in one direction; and a spring that rotates the support lever in the other direction. Two magnetic wedges are provided on the fuselage side at a predetermined interval in the rotating plane of the supporting base plate, and a tension connecting each sensitive piece of the two electromagnetic wedges. Applied to a small rocket/microgravity experimental device characterized by comprising a spring and a drive rod connecting the sensing piece on the side closer to the support lever among the sensing pieces and the support lever. LAINC
It is intended to provide an H-LOCK mechanism.
〔作用］
本発明は上記のように構成されるので次の作用を有する
。[Function] Since the present invention is configured as described above, it has the following function.
即ち、微小重力実験装置を支持する支持ベースプレート
を、機体側に対称枢支された複数の支持レバーが対称に
係脱するので、係合している場合は支持ベースプレート
と機体側とが支持レバーによってメカニカルに連結、固
定される。従って微小重力実験装置が機体側に固定され
る。また、保合を離脱させた場合は微小重力実験装置は
自由状態となる。支持レバーと支持ベースプレートとの
保合は、支持レバーを一方へ回動させるバネによる。離
脱は支持レバーから遠い方の電磁クサビを作動させてそ
ちら側の感応片を固定、反対側の、支持レバーと駆動棒
で連結する電磁クサビを解放させて感応片を自由状態に
すると、感応片は引張バネに引かれて固定側へ移動する
ので、駆動棒が支持レバーを引いて、離脱側へ回動し、
支持ベースプレートを自由状態にする。In other words, the support base plate that supports the microgravity experimental device is symmetrically engaged and disengaged by a plurality of support levers that are symmetrically supported on the aircraft body side, so when they are engaged, the support base plate and the aircraft body side are Mechanically connected and fixed. Therefore, the microgravity experimental device is fixed to the fuselage side. Furthermore, when the bond is released, the microgravity experimental device becomes free. The support lever and the support base plate are held together by a spring that rotates the support lever in one direction. To detach, activate the electromagnetic wedge on the far side from the support lever to fix the sensing piece on that side, and release the electromagnetic wedge on the opposite side, which is connected to the support lever with the drive rod, to free the sensing piece. is pulled by the tension spring and moves to the fixed side, so the drive rod pulls the support lever and rotates to the detached side,
Free the supporting base plate.
本発明の一実施例を第１図〜第６区により説明する。な
お、従来例と同様の構成部材には同符号を付し、説明を
省略する。An embodiment of the present invention will be described with reference to FIGS. 1 to 6. Note that the same reference numerals are given to the same constituent members as in the conventional example, and the explanation thereof will be omitted.
第１図は本実施例に係るＬＯＣＫ機構（ＬＡＵＮＣＨＬ
ＯＣＫ機構）５が小型ロケット微小重力維持技術実験装
置１００をＬＯＣＫ している状態の斜視図、第２図は
本実施例のＬＯＣｌ［！［５の側面図（ＬＡＵＮＣＨ−
ＬＯＣＫ時）、第３日は第２図の平面図、第４図はＬＯ
ＣＫ＠構５のＵＮＬＯＣＫ ＩＮＧ時の側面図、第５図
はＬＯ（Ｊ機構５のＲＥ−ＬＯＣＫＩＮＧ時の側面図、
第６図はＬＯＣＫ機構５の電磁クサビ１０１ｂの詳細図
で（ａ）はその側面図、（ｂ）は（ａ）のｂ−ｂ矢視図
である。なお、第１図ではＬＯＣＫ４１！構５は複数個
組込まれているが、複数個の場合も再び包括的にＬＯＣ
Ｋ機構５として呼び出しである。FIG. 1 shows the LOCK mechanism (LAUNCHL) according to this embodiment.
FIG. 2 is a perspective view of the state in which the small rocket microgravity maintenance technology experimental device 100 is locked by the OCK mechanism) 5, and FIG. 2 is a perspective view of the LOCl[! [Side view of 5 (LAUNCH-
LOCK time), the 3rd day is the plan view of Figure 2, and Figure 4 is the LO
A side view of CK @ mechanism 5 when UNLOCKING, Figure 5 is a side view of LO (J mechanism 5 when RE-LOCKING,
FIG. 6 is a detailed view of the electromagnetic wedge 101b of the LOCK mechanism 5, in which (a) is a side view thereof, and (b) is a view taken along the line bb in (a). In addition, in Figure 1, LOCK41! Although multiple structures 5 are incorporated, in the case of multiple structures, comprehensive LOC is also performed.
It is called as K mechanism 5.
これらの図において、１００は小型ロケット微小重力維
持技術実験装置（以降、単に実験装置という）であり、
この実験装置１００は複数のベースプレートの取付ポル
ト３３によりロケット側のステージ３０に固定された主
ベースプレート６、同主ベースプレート６上に設けられ
たＬＯＣＫ機構５、支持ベースプレート４を介して取付
けられており、上部防振材支持プレート１、上部防振材
２、実験装置１００を収納したカバー３、横防振材８を
貼付した横防振材支持構造７で構成されている。ＬＯＣ
Ｋ機構５の主ベースプレート６上部には支持レバー取付
金具１２とばね取付金具１５が溶接により固定されてい
て、支持レバー取付金具１２に軸１３によって揺動自在
に枢支された支持レバー９の先端部には実験装置支持金
具１１が支持ベースプレート４の下方に取付けられ、係
止部３１を有した実験装置支持金具１１に支持レバー９
が係合して実験装置支持金具１１をＬＯＣＨするよう構
成されている。支持レバー９の先端部の一方の側には一
端かばね取付金具１５に固定され、支持レバー９を実験
装置支持金具１１に係合させる向きに働くばね１４が取
付けられており、他方の側は駆動棒１０を介してシリン
ダ１８の取付軸２６に連結されている。シリンダ１８は
第２図〜第５図等に図示のように長手方向の両周面に摺
動溝３６を有する円筒形をなし、主ベースプレート６に
シリンダ取付金具２０を介して固着されている。摺動溝
３６には、直交方向に貫通する取付軸１９．２６が、摺
動溝３６の長手方向に摺動可能に設けられており、取付
軸１９には第５、第６図に示すように電磁気に感応する
軟鉄等よりなるピストン状の感応片１９ａが固設され、
同じく取付軸２６には第４図に示すように感応片２６ａ
が固設されている。取付軸１９と同２６との間は引張ば
ねの作用をなすばねＩ７によって連結されており、後述
の通り、ソレノイドをなす電磁クサビ１０１ａ、 １０
１ｂが通電されている場合はシリンダ１８の両端にそれ
ぞれ！磁力によって引きつけられた取付軸１９及び同２
６を相互に引張る働きをし、通電が遮断されてｔ磁力が
消えた場合は取付軸１９と同２６とはばね１７によって
近接し、自由状態となる。但し、取付軸２６は上述の通
り、駆動棒１゜に連結されているので完全に自由状態と
なることは困難である。シリンダ１８の両端にはコイル
１６゜２３が巻かれ、それぞれはリード線２１ａ、２１
ｂ、スイッチ２４．２５を介して電源２２に連通されて
おり、スイッチ２４．２５のＯＮ、ＯＦＦによってコイ
ル１６．２３がソレノイドとして働き、取付軸２６と一
体の感応片２６ａ、取付軸１９と一体の感応片１９ａを
それぞれ電磁力によって固定し、電磁クサビ１０１ａ、
１０１ｂを形成する。In these figures, 100 is a small rocket microgravity maintenance technology experimental device (hereinafter simply referred to as the experimental device);
This experimental device 100 is attached via a main base plate 6 fixed to the rocket-side stage 30 by a plurality of base plate attachment ports 33, a LOCK mechanism 5 provided on the main base plate 6, and a support base plate 4. It consists of an upper vibration isolator support plate 1, an upper vibration isolator 2, a cover 3 housing an experimental device 100, and a lateral vibration isolator support structure 7 to which a lateral vibration isolator 8 is attached. LOC
A support lever mounting bracket 12 and a spring mounting bracket 15 are fixed to the upper part of the main base plate 6 of the K mechanism 5 by welding. An experimental device support fitting 11 is attached below the support base plate 4, and a support lever 9 is attached to the experimental device support fitting 11 having a locking portion 31.
is configured to engage and LOCH the experimental apparatus support fitting 11. A spring 14 is attached to one end of the tip of the support lever 9 and is fixed to a spring fitting 15, and acts in a direction to engage the support lever 9 with the experimental equipment support fitting 11, and the other side is fixed to a spring fitting 15. It is connected to the mounting shaft 26 of the cylinder 18 via the rod 10. As shown in FIGS. 2 to 5, the cylinder 18 has a cylindrical shape with sliding grooves 36 on both circumferential surfaces in the longitudinal direction, and is fixed to the main base plate 6 via a cylinder mounting bracket 20. The sliding groove 36 is provided with a mounting shaft 19.26 that penetrates in the orthogonal direction and is slidable in the longitudinal direction of the sliding groove 36. A piston-shaped sensing piece 19a made of soft iron or the like that is sensitive to electromagnetism is fixed to the
Similarly, the mounting shaft 26 has a sensing piece 26a as shown in FIG.
is permanently installed. The mounting shaft 19 and the mounting shaft 26 are connected by a spring I7 which acts as a tension spring, and as described later, electromagnetic wedges 101a and 10 which form a solenoid.
If 1b is energized, both ends of the cylinder 18! Mounting shaft 19 and 2 attracted by magnetic force
When the current is cut off and the magnetic force disappears, the mounting shaft 19 and the mounting shaft 26 are brought close to each other by the spring 17, and are in a free state. However, as mentioned above, since the mounting shaft 26 is connected to the drive rod 1°, it is difficult to be in a completely free state. Coils 16°23 are wound around both ends of the cylinder 18, and each lead wire 21a, 21
b. It is connected to the power supply 22 via the switch 24.25, and the coil 16.23 works as a solenoid by turning the switch 24.25 ON or OFF. The sensitive pieces 19a of are fixed by electromagnetic force, and the electromagnetic wedges 101a,
101b.
次に第２図及び第３図によりＬＡＵＮＣＨ−ＬＯＣＫ時
（小型ロケント打上げ時）について説明する。Next, the LAUNCH-LOCK time (when launching a small Rokento) will be explained with reference to FIGS. 2 and 3.
ＬＡ［ＩＮＣＨ−ＬＯＣＫ時には取付軸１９及び取付軸
２６を摺動溝３６の両端に移動させて、スイッチ２４２
５をＯＮにする。すると電磁クサビ１０１ａ、 １０１
ｂが作動し、電磁力によって取付軸１９．２６が固定さ
れる。取付軸１９．２６が摺動溝３６の両端に固定され
ると支持レバー９によりＬＡＵＮＣＩＩ −Ｌｏｃｋ機
能が作動する。When LA[INCH-LOCK is selected, the mounting shaft 19 and the mounting shaft 26 are moved to both ends of the sliding groove 36, and the switch 242 is
Turn on 5. Then, the electromagnetic wedges 101a, 101
b is activated, and the mounting shaft 19.26 is fixed by electromagnetic force. When the mounting shaft 19.26 is fixed to both ends of the sliding groove 36, the support lever 9 activates the LAUNCII-Lock function.
次にＵＮＬＯＣＫＩＮＧ時（微小重力始業時）について
第４図により説明する。小型ロケット打上げ後、微小重
力始業時に地上コントロール室からリモートコントロー
ルによりスイッチ２４を切るとリード線２１ａを介して
支持レバー９例の電磁クサビ１０１ａが作動しなくなり
、ばね１７の力により支持レバー９はばね１４に抗して
シリンダ１８側に回転して、実験装置支持金具１１から
離れ、実験装置１００は実験装置支持金具１１と共にフ
リーの状態になり宇宙（微小重力）環境下における実験
に入る。なお、ばねの張力は「ばね１７の張力〉ばね１
４の張力」になるように定める。Next, the UNLOCKING time (microgravity starting time) will be explained with reference to FIG. After the launch of a small rocket, when the switch 24 is turned off by remote control from the ground control room at the start of microgravity operation, the electromagnetic wedges 101a of the support levers 9 will no longer operate via the lead wires 21a, and the support levers 9 will be released by the force of the spring 17. 14 and rotates toward the cylinder 18 side, away from the experimental apparatus support fitting 11, the experimental apparatus 100 becomes free together with the experimental apparatus support fitting 11, and enters an experiment in a space (microgravity) environment. In addition, the tension of the spring is "Tension of spring 17> Spring 1
4 tension.
次にＲＥ−ＬＯＣＫＩＮＧ時（微小重力終了時）につい
て第５図により説明する。微小重力終了後、地上コント
ロール室からリモートコントロールにより、スイッチ２
５を切ると他方の電磁クサビ１０１ｂが作動しなくなり
、ばね１７、取付軸１９はフリーの状態になり、ばね１
４の力により支持レバー９は実験装置支持金具１１側に
回転し実験装置支持金具１１によって係止される。この
時、地上のコントロール室からリモートコントロールに
よりスイッチ２４をＯＮにしてリード線２１ａを介して
１１クサビ１０１ａが作動し、電磁力によって感応片２
６ａと一体の取付軸２６が固定されＲＥ −Ｌｏｃｋ状
態になる。Next, the time of RE-LOCKING (at the end of microgravity) will be explained with reference to FIG. After microgravity ends, switch 2 is turned on by remote control from the ground control room.
5, the other electromagnetic wedge 101b will not operate, the spring 17 and the mounting shaft 19 will be free, and the spring 1
4, the support lever 9 rotates toward the experimental apparatus support fitting 11 and is locked by the experimental apparatus support fitting 11. At this time, the switch 24 is turned ON by remote control from the control room on the ground, and the wedge 101a is operated via the lead wire 21a, and the sensing piece 2 is moved by electromagnetic force.
The mounting shaft 26, which is integral with 6a, is fixed and enters the RE-Lock state.
以上、実施例はＬＯＣＸ機構５の１組の例で説明したが
、第１図に示すようにＬＯＣＫ機構５は実験装置１００
に対し、ロケットの機軸方向である上下方向に見て左右
対称に各一対をなして、たとえば２対４組というふうに
設けられているので、第２図〜第５図に例示するＬＯ（
Ｊ機構５に対して、図示しない対側のＬＯＣＫ機構５は
対称の作動を行なっており、左右はもとより図の前後方
向をも含めて水平方向の全方位に対して実験装置１００
は完全にＬＯＣＫＬＩＮＬＯＣＫ、 ＲＥ−ＬＯＣＫが
果たされる。また図の上下方向に対しても、支持レバー
９が実験装置支持金具１１の係止部３１に対し、水平方
向に喰込むがたちで係合するので、ＬＯＣＫ時は上下移
動が生ぜず、実験装置１００は結局、ロケットの機軸方
向及び機軸と直交方向の全方向に対し、完全ロックされ
ると共に任意に解放され得る。The embodiment has been described above with reference to one set of LOCX mechanism 5, but as shown in FIG.
On the other hand, since they are provided in pairs symmetrically on the left and right when viewed in the vertical direction, which is the axis direction of the rocket, for example, 2 to 4 pairs, the LO (LO) shown in FIGS.
The LOCK mechanism 5 on the opposite side (not shown) operates symmetrically with respect to the J mechanism 5, and the experimental apparatus 100 is operated in all directions in the horizontal direction, including not only the left and right sides but also the front and rear directions in the figure.
LOCKLINLOCK, RE-LOCK is fully fulfilled. Also, in the vertical direction in the figure, the support lever 9 engages with the locking part 31 of the experimental device support fitting 11 in a horizontal direction, so there is no vertical movement when LOCKed, and the experiment In the end, the device 100 is completely locked in the rocket axis direction and in all directions orthogonal to the rocket axis, and can be released at will.
以上の通り、本実施例によればロケットに対し、実験装
置１００を完全にＬＯＣＫ、 ＩＩＮＬＯｃＫできると
ともに、ＬＯＣＫ ＵＮＬＯＣＫの作動は電気的に行
なうものの、直接の固定は支持レバー９と実験装置支持
金具１１とがメカニカルに行なうので大荷重に耐えるこ
とができ、かつ、電源２２の容量が許す限り、長時間使
用できるという利点がある。また、ＬＯＣＫ。As described above, according to this embodiment, the experimental apparatus 100 can be completely LOCKed and IINLOCKed to the rocket, and although the LOCK UNLOCK operation is performed electrically, direct fixation is performed using the support lever 9 and the experimental apparatus support fitting 11. Since this is done mechanically, it has the advantage that it can withstand a large load and can be used for a long time as long as the capacity of the power source 22 allows. Also, LOCK.
ＵＮＬＯＣＫの作動はＬＯＣＫ機構５の内力系の動作の
みによって行なわれるので実験装置１００に不要な重力
加速度がかからないという利点がある。Since the UNLOCK operation is performed only by the operation of the internal force system of the LOCK mechanism 5, there is an advantage that unnecessary gravitational acceleration is not applied to the experimental apparatus 100.
本発明は上記のように構成されるので次の（１）〜（４
）の効果を有する。Since the present invention is configured as described above, the following (1) to (4)
) has the effect of
（１）長時間にわたり実験装置をＬＡＵＮＣ）Ｉ −Ｌ
ＯＣＫ機構により確実に固定できる。(1) LAUNCH the experimental equipment for a long time
It can be securely fixed by the OCK mechanism.
（２） ＬＡＩＩＮＣＩＩＬＯＣＫＩ！構は所要の設
計荷重に充分耐えられる構造に出来る。(2) LAINCIILOCKI! The structure can be constructed to sufficiently withstand the required design load.
（３）実験装置に不要な重力加速度がかかることなく
ＵＮＬＯＣＲＩＮＧ及びＲＥＬＯＣＫ出来る。(3) No unnecessary gravitational acceleration is applied to the experimental equipment
Can UNLOCRING and RELOCK.
（４） ＵＮＬＯＣＲＩＮＧ後も不要な重力加速度が
かからない構造である。(4) The structure does not apply unnecessary gravitational acceleration even after UNLOCRING.
第１図は本発明の一実施例のＬＯＣＫ機構５によって小
型ロケット・微小重力維持技術実験装置１００をＬＯＣ
Ｋ している状態の斜視図、第２図は上記実施例のＬＯ
ＣＫ機構５の側面図（ＬＡＵＮＣＨ−ＬＯＣＫ時）、第
３図は第２図の平面図、第４図は上記実施例のＬＯＣＫ
機構５のＵＮＬＯＣＫ時の側面図、第５図は上記実施例
のＬＯＣＫ機構５のＲＥ−ＬＯＣＫＩＮＧ時の側面図、
第６図はＬＯＣＫ機構５の電磁クサビ１０１ｂの詳細図
で（ａ）はその側面図、ら）は（ａ）のｂ−ｂ矢視図、
第７図は従来の小型ロケット・微小重力維持技術実験装
置がロケット内に搭載されている状態を模式的に示した
側面図、第８図は小型ロケット・微小重力維持技術実験
装置をロケット内で支持する従来のＡＩＲ−ＭＡＴ支持
具等の縦断面図である。
１・・・上部防振材支持プレート（上部防振材を貼付）
、２・・・上部防振材、 ３・・・カバー４・
・・支持ベースプレート、 ５・・・ＬＯＣＫ機構、
６・・・主ベースプレート、
７・・・横防振材支持構造（横防振材を貼付）、８・・
・横防振材、 ９・・・支持レバー１０・・・
駆動棒、 １１・・・実験装置支持金具、１２
・・・支持レバー取付金具、１３・・・軸、１４・・・
ばね、 １５・・・ばね取付金具、１６・
・・コイル、 １７・・・ばね、１８・・・
シリンダ、 １９・・・取付軸、１９ａ・・・感
応片、 ２０・・・シリンダ取付金具、２１ａ
２１ｂ・・・リード線、 ２２・・・電源、２３・
・・コイル、 ２４ 、２５・・・スイッチ
、２６・・・取付軸、 ２６ａ・・・感応片、
２７・・・微小重力実験装置、３１・・・係止部、３３
・・・取付ボルト、 ３６・・・摺動溝、１０１ａ
、 １０１ｂ・・・電磁クサビ。
代理人 弁理士 坂 間 暁
外２名
第６図FIG. 1 shows a small rocket/microgravity maintenance technology experimental device 100 being LOCKed by a LOCK mechanism 5 according to an embodiment of the present invention.
K is a perspective view of the state in which the
A side view of the CK mechanism 5 (at LAUNCH-LOCK), FIG. 3 is a plan view of FIG. 2, and FIG. 4 is a LOCK of the above embodiment.
FIG. 5 is a side view of the mechanism 5 at the time of UNLOCK, and FIG. 5 is a side view of the LOCK mechanism 5 of the above embodiment at the time of RE-LOCKING.
FIG. 6 is a detailed view of the electromagnetic wedge 101b of the LOCK mechanism 5, (a) is a side view thereof,
Figure 7 is a side view schematically showing the conventional small rocket/microgravity maintenance technology experimental device mounted inside the rocket, and Figure 8 is a side view schematically showing the conventional small rocket/microgravity maintenance technology experimental equipment mounted inside the rocket. It is a longitudinal cross-sectional view of the conventional AIR-MAT support etc. which support. 1... Upper vibration isolator support plate (upper vibration isolator attached)
, 2... Upper vibration isolating material, 3... Cover 4.
...Support base plate, 5...LOCK mechanism,
6... Main base plate, 7... Lateral vibration isolator support structure (lateral vibration isolator attached), 8...
・Horizontal vibration isolation material, 9...Support lever 10...
Drive rod, 11... Experimental equipment support fitting, 12
...Support lever mounting bracket, 13...shaft, 14...
Spring, 15... Spring mounting bracket, 16...
...Coil, 17...Spring, 18...
Cylinder, 19... Mounting shaft, 19a... Sensing piece, 20... Cylinder mounting bracket, 21a
21b...Lead wire, 22...Power supply, 23.
...Coil, 24, 25...Switch, 26...Mounting shaft, 26a...Sensing piece,
27... Microgravity experimental device, 31... Locking part, 33
...Mounting bolt, 36...Sliding groove, 101a
, 101b...electromagnetic wedge. Agent: Patent Attorney Akigai Sakama (2 persons) Figure 6
Claims (1)
験装置を支持する支持ベースプレートと、ロケットの機
体側に回動可能に枢支されその先端を上記機軸にほぼ対
称にかつ上記支持ベースプレートに係脱可能に設けられ
た複数の支持レバーと、同支持レバーを一方へ回動させ
るバネと、同支持レバーを他方へ回動させる側の回動面
内に上記支持ベースプレートとほぼ平行に所定の間隔を
保って機体側に設けられた２個の電磁クサビと、同２個
の電磁クサビの各感応片を連結する引張りバネと、上記
各感応片のうち上記支持レバーに近い側の感応片と上記
支持レバーとを連結する駆動棒とを具備してなることを
特徴とする小型ロケット・微小重力実験装置に適用され
るＬＡＵＮＣＨ−ＬＯＣＫ機構。A support base plate is provided in a direction perpendicular to the axis of the rocket and supports a microgravity experimental device, and a support base plate is rotatably pivoted to the body side of the rocket, and its tip is approximately symmetrical to the axis and engages and disengages from the support base plate. a plurality of support levers that can be provided, a spring that rotates the support lever in one direction, and a predetermined interval approximately parallel to the support base plate within the rotation plane of the side that rotates the support lever in the other direction; two electromagnetic wedges provided on the fuselage side, a tension spring connecting each sensitive piece of the two electromagnetic wedges, the sensitive piece on the side closer to the support lever among the above-mentioned respective sensitive pieces, and the above-mentioned support. A LAUNCH-LOCK mechanism applied to a small rocket/microgravity experimental device, characterized by comprising a drive rod connected to a lever.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2146121A JP2737061B2 (en) | 1990-06-06 | 1990-06-06 | Lock mechanism at launch applied to a small rocket microgravity experimental device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2146121A JP2737061B2 (en) | 1990-06-06 | 1990-06-06 | Lock mechanism at launch applied to a small rocket microgravity experimental device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH0439200A true JPH0439200A (en) | 1992-02-10 |
| JP2737061B2 JP2737061B2 (en) | 1998-04-08 |
Family
ID=15400630
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2146121A Expired - Fee Related JP2737061B2 (en) | 1990-06-06 | 1990-06-06 | Lock mechanism at launch applied to a small rocket microgravity experimental device |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2737061B2 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2014113938A (en) * | 2012-12-11 | 2014-06-26 | Ihi Aerospace Co Ltd | Holding/release mechanism |
| CN114563202A (en) * | 2022-02-15 | 2022-05-31 | 中国航天标准化研究所 | Cable disengagement system of rocket root bending moment monitoring system |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102229363B (en) * | 2011-05-11 | 2013-04-03 | 北京航空航天大学 | Atmospheric drag passive aberrance device and method applied to medium-low orbital rocket tail stage |
-
1990
- 1990-06-06 JP JP2146121A patent/JP2737061B2/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2014113938A (en) * | 2012-12-11 | 2014-06-26 | Ihi Aerospace Co Ltd | Holding/release mechanism |
| CN114563202A (en) * | 2022-02-15 | 2022-05-31 | 中国航天标准化研究所 | Cable disengagement system of rocket root bending moment monitoring system |
| CN114563202B (en) * | 2022-02-15 | 2023-10-27 | 中国航天标准化研究所 | Cable disconnection system of rocket root bending moment monitoring system |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2737061B2 (en) | 1998-04-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| KR950028227A (en) | Control device of electronic device | |
| US3620560A (en) | Vehicle closure latch | |
| US4299361A (en) | Protective device for instruments and locking of aircraft controls | |
| CN101801832B (en) | Electric motor | |
| JPH0439200A (en) | Launch-lock system applied to small pocket/micro-gravity experimental device | |
| US4946207A (en) | Electrically controlled locks | |
| US5437420A (en) | High torque double gimbal control moment gyro | |
| KR960022232A (en) | Elevator | |
| US4428607A (en) | Latching assembly | |
| US4141520A (en) | Fail-safe lock for an airplane rudder | |
| EP4092231B1 (en) | Fast acting electro-mechanical unlocking device and method of actuating an electro-mechanical unlocking device | |
| CN109827036A (en) | A kind of damping device that can switch between damping state and locking state | |
| US12000179B1 (en) | Lock with single-sided automatic locking | |
| JP2950044B2 (en) | Sliding door closing device for vehicles | |
| EP0916576B1 (en) | High torque double gimbal control moment gyro | |
| JP5364899B2 (en) | Storage fixtures | |
| CN109421615A (en) | Storage case and safety hammer component, the vehicle for using the storage case | |
| JP7466073B1 (en) | Hoist hook and method for transporting items using the hoist hook | |
| US3075356A (en) | Fluid-operable actuating system in a motor vehicle | |
| JP2004533565A (en) | Electromechanical locking method and device | |
| JPH09175498A (en) | Parachute door releasing mechanism | |
| JPH07293057A (en) | Unlocking preventative function-attached lock | |
| CN117682082A (en) | Lock release mechanism, method and aircraft | |
| WO1984001180A1 (en) | Latching assembly | |
| KR100233066B1 (en) | Door locking device for a vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| LAPS | Cancellation because of no payment of annual fees |