CN106482970A - A kind of spacecraft Explosive separation guide type safe retrieving assay device - Google Patents
A kind of spacecraft Explosive separation guide type safe retrieving assay device Download PDFInfo
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- CN106482970A CN106482970A CN201610868556.1A CN201610868556A CN106482970A CN 106482970 A CN106482970 A CN 106482970A CN 201610868556 A CN201610868556 A CN 201610868556A CN 106482970 A CN106482970 A CN 106482970A
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- main binding
- binding apparatus
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
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Abstract
The invention belongs to structure dynamics of spacecraft experimental technique field, a kind of spacecraft Explosive separation guide type safe retrieving assay device, it is characterized in that including aircraft main binding apparatus linkage section, main binding apparatus, aircraft main binding apparatus linkage section top is connected with boundary condition simulation device by bay section switching tooling, main binding apparatus one end is connected with aircraft binding, the other end is connected with guide type retracting device top, and guide type retracting device bottom is passed through on hinge fixed bottom boundary；In aircraft main binding apparatus linkage section, sensor is installed, sensor is connected with test system；Ground laying buffering reclaims pad；After on-test, main binding apparatus unblock separates, and the main binding apparatus after separating and guide type retracting device rotate along hinge.
Description
Technical field
The invention belongs to structure dynamics of spacecraft experimental technique field is and in particular to a kind of spacecraft Explosive separation guides
Formula safe retrieving assay device.
Background technology
Various separating actions during rocket flight, such as stage separation, the satellite and the rocket separate, trouserss separate, main binding
Device unblock etc. will realize unblock by priming system blast.The size of explosive force, the accuracy of burst period directly affects point
From effect and gesture stability, and the strong high-frequency percussion environment that priming system itself produces affects the work of instrument and equipment on arrow
Performance.From angle of overall, need the Explosive separation state in simulated flight on the ground, comprehensive study Explosive separation
Present in environmental problem, under design problem and weightlessness the problems such as the separation attitude of each level segment.
The main strap-on structure of CZ-7 is inherited in jump fire arrow scheme, but the installation site of ball and socket base is adjusted to rear transition from rear
Section.When the main binding apparatus of jump fire arrow unlock, percussion need to be by the interface of rear changeover portion and rear, after being just delivered to
On changeover portion.During CZ-7 main binding unblock, rear changeover portion will be directly subjected to the shock environment of Explosive separation, and this shock environment can
Structure on arrow and product can be constituted and damage, directly result in flight failure.After CZ-7 changeover portion instrument and equipment species and quantity many,
Multiple composites gas cylinders are installed, the safety in separation process is proposed higher requirement.
In existing experimental technique, two classes are mainly included to the wire examination method of main binding apparatus：Booster separation test and
Single main binding apparatus Release separation test, this two class test all can only examine single main binding apparatus separating property it is impossible to
The fully examination impact to instrument and equipment for the pyroshock environment.According to the feature of CZ-7 model, changeover portion after needing to examine on arrow
Service behaviour under pyroshock environment for the equipment such as gas cylinder, instrument and equipment and retro-rocket and reliability, so directly utilize
The system-level Release separation test that true priming system carries out all main binding apparatus participation is very necessary.
After CZ-7 one-level, changeover portion main binding apparatus unblock impact test is system-level certification test, adopts whole four first
Individual main binding apparatus are unlocked simultaneously and separate, and firer's dose is as many as 10 times of related model same device in the past, lead to rush
Amount is big, and test is implemented and safe retrieving difficulty is big.System-level main binding apparatus Release separation test implements technical difficulty height, reclaims
Main binding apparatus after process is complicated, and the test of this model clearly proposes unblock is separated carry out safe retrieving.Due to main binding
Device separation momentum it is necessary to move to the main binding apparatus after separation into row constraint and braking, protects the same of main binding apparatus greatly
When prevent to surrounding devices facility produce damage；And main binding apparatus are bulb bolt and bulb bolt seat damascene structures, on ground
In test, bulb bolt is separated with bulb bolt seat, is easily caused the translation between them or rotation and produces clamping stagnation in separation process.
Content of the invention
(1) technical problem solving
Present invention solves the technical problem that being：In order to overcome the deficiencies in the prior art, the present invention provides a kind of spacecraft quick-fried
Fried separation guide type safe retrieving assay device, guides recovery test device safely using " rotary steering+sliding pair ", makes to separate
Bulb bolt afterwards slidably and by buffering recovery pad can be braked safety time along adjustable type screw rod while rotation
Receive, braking and removal process adapt to bulb bolt isolated movement track automatically, solve penetration between bulb bolt and bulb bolt seat and produce
Raw clamping stagnation, and lead to not the detached difficult problem of normal release.
(2) technical scheme
The present invention relates to a kind of spacecraft Explosive separation guide type safe retrieving assay device, including aircraft main binding dress
Put linkage section, main binding apparatus, bay section switching tooling and boundary condition simulation device are passed through in aircraft main binding apparatus linkage section top
Connect, main binding apparatus one end is connected with aircraft binding, and the other end is connected with guide type retracting device top, and guide type reclaims
Device bottom is passed through on hinge fixed bottom boundary；In aircraft main binding apparatus linkage section, sensor, sensor and survey are installed
Test system connects；Ground laying buffering reclaims pad；After on-test, main binding apparatus unblock separates, the main binding after separating
Device and guide type retracting device rotate along hinge.
Further, described main binding apparatus and 4 sets of guide type retracting device are symmetrically distributed in the main binding apparatus of aircraft
Linkage section periphery.
Further, described boundary condition simulation device includes pedestal, post block and crossbeam, wherein pedestal respectively with post block and ground
Basis connects, and post block is connected with crossbeam.
Further, described buffering reclaims pad and is formed by air bag, sponge and rubber layering place mat, and air bag is located at centre,
Rubber and sponge are located at the upper and lower respectively.
Further, described guide type safe recovery device include connecting support seat, regulatable sleeve, rod-pulling type ears,
Hinge, support connect base；Described main binding apparatus are connected with connecting support seat top, and sliding pair is provided therebetween, under
Portion is enclosed within inside regulatable sleeve；Regulatable sleeve is enclosed within outside rod-pulling type ears, rod-pulling type ears top and regulatable sleeve
It is connected, bottom connects hinge, hinge is connected with supporting connect base, supports connect base to be fixed on ground；Described cunning
Dynamic secondary function is that adjust automatically reclaims guiding pole length in the unblock separation process of main binding apparatus, thus avoid bulb bolt with
Clamping stagnation problem between bulb two-seater.
Further, described connecting support seat includes adjustable type screw rod, interface, butt hole, wherein adjustable type screw rod with
Interface is vertically fixed, and adjustable type screw rod is nested in inside regulatable sleeve, and main binding apparatus pass through butt hole and connect support
Seat top connects, and arranges sliding pair at interface.
Further, described regulatable sleeve two ends are to connect upper screw and connect lower screw, and middle is pull bar regulatory region,
In connection, screw and the lower screw of connection are respectively left-handed and dextrorotation.
Further, described rod-pulling type ears are the second adjustable type screw rod by top, and bottom is ears, and ears are provided with double
Ear pin-and-hole, the wherein second adjustable type screw rod is connected for nested type with regulatable sleeve.
Further, described support connect base includes ground interface, and ground interface is provided with ground butt hole, ground
Face butt hole is connected with ground base, and monaural is vertically fixed at the back side, and monaural is provided with monaural pin-and-hole, monaural pin-and-hole and ears pin-and-hole
By pin connection.
Working mechanism：
In main binding apparatus unblock separation process, main binding apparatus separate and move out, main binding in motor process
Device passes through relative position along adjustable type screw slide and between automatic synchronization bulb bolt and bulb bolt seat for the sliding pair it is ensured that two
Person smoothly departs from；After bulb bolt and bulb bolt seat completely disengage from, main binding apparatus are in the second adjustable type screw rod and regulatable sleeve
Constraint lower edge hinge moves in a circle；It is buffered recovery pad braking to reclaim, thus realizing main bundle after moving to suitable position
The brake safe guiding tying up device 4 reclaims.
(3) beneficial effect
(1) it is ensured that the guide type safe retrieving of segregation apparatuss by the way of " rotary steering+sliding pair "；
(2) be capable of and main binding apparatus Coordinative assembling, adjustable joint gap and height；
(3) the unblock separation of no clamping stagnation and the edge that achieve rear changeover portion main binding apparatus system for unlocking level certification test are predetermined
The failure to the safe side of track reclaims, and solves the difficult problems such as big momentum, the braking of high-risk chorista and safe retrieving；
(4) braking and removal process is made automatically to adapt to main binding apparatus bulb bolt isolated movement track；
Brief description
Fig. 1：Explosive separation guide type safe retrieving assay device structure chart
Wherein, the main binding of the main binding apparatus linkage section 4- of 1- boundary condition simulation device 2- bay section switching tooling 3- aircraft
Device 5- sliding pair 6- connecting support seat 7- regulatable sleeve 8- rod-pulling type ears 9- hinge, 10- supports connect base
11- buffering reclaims pad 12- measuring system；
Fig. 2：Connecting support seat structure chart
Wherein, 601- adjustable type screw rod, 602- interface, 603- butt hole.
Fig. 3：Regulatable sleeve structure chart
Wherein, screw in 701- connection, 702- connects lower screw, 703- pull bar regulatory region
Fig. 4：Rod-pulling type ears structure chart
Wherein, 801- the second adjustable type screw rod, 802- ears, 803- ears pin-and-hole
Fig. 5：Support connect base structure chart
Wherein, 1001- ground interface, 1002- ground butt hole, 1003- monaural pin-and-hole, 1004- monaural
Specific embodiment
Except embodiment described below, the present invention can also have other embodiments or to implement by different way.Therefore,
It should be known that the invention is not limited in the detailed of the structure of described in the following description or shown in the accompanying drawings part
Situation.When only introducing an embodiment here, claim is not limited to this embodiment.
A kind of the present embodiment spacecraft Explosive separation guide type safe retrieving assay device, including the main binding apparatus of aircraft
Linkage section 3, main binding apparatus 4, bay section switching tooling 2 and boundary condition simulation dress are passed through in aircraft main binding apparatus linkage section 3 top
Put 1 connection, main binding apparatus 4 and 4 sets of guide type retracting device are symmetrically distributed in aircraft main binding apparatus linkage section 3 periphery；
The binding of the main binding apparatus of every suit 4 one end and aircraft main binding apparatus linkage section 3 is connected, the other end and guide type retracting device
Top connects, and guide type retracting device bottom is passed through on hinge 9 fixed bottom boundary；Pacify in aircraft main binding apparatus linkage section 3
Equipped with sensor, sensor is connected with test system；Ground laying buffering reclaims pad 11；After on-test, main binding apparatus 4
Unblock separates, and the main binding apparatus 4 after separating and guide type retracting device rotate along hinge 9.
Boundary condition simulation device 1 includes pedestal, post block and crossbeam, and wherein pedestal is connected with post block and ground base respectively, post
Block is connected with crossbeam.
Buffering reclaims pad and is formed by air bag, sponge and rubber layering place mat, and air bag is located at centre, rubber and sponge position respectively
In the upper and lower.
Guide type retracting device includes connecting support seat 6, regulatable sleeve 7, rod-pulling type ears 8, supports connect base 10；
Described main binding apparatus 4 are connected with connecting support seat 6 top, sliding pair 5 are provided therebetween, bottom is enclosed within regulatable sleeve
Inside 7；Outside rod-pulling type ears 8, rod-pulling type ears 8 top and regulatable sleeve 7 are connected regulatable sleeve set 7, under
Portion's connects hinge 9, hinge 9 is connected with supporting connect base 10, supports connect base 10 to be fixed on ground；Described sliding pair 5
Function be main binding apparatus 4 unblock separation process in adjust automatically reclaim guiding pole length, thus avoiding bulb bolt and ball
Clamping stagnation problem between head two-seater.
Connecting support seat 6 includes adjustable type screw rod 601, interface 602, butt hole 603, wherein adjustable type screw rod 601 with
Interface 602 is vertically fixed, and adjustable type screw rod 601 is nested in inside regulatable sleeve 7, and main binding apparatus 4 pass through butt hole 603
Connect with connecting support seat 6 top, sliding pair is set at interface 602.
Regulatable sleeve 7 two ends are to connect upper screw 701 and connect lower screw 702, and middle is pull bar regulatory region 703, even
Connect screw 701 and connect lower screw 702 respectively left-handed and dextrorotation.
Rod-pulling type ears 8 are the second adjustable type screw rod 801 by top, and bottom is ears 802, and ears 802 are provided with ears
Pin-and-hole 803, the wherein second adjustable type screw rod 801 is connected for nested type with regulatable sleeve 7.
Connect base 10 is supported to include ground interface 1001, ground interface 1001 is provided with ground butt hole 1002,
Connect base 10 is supported to be connected with ground base by ground butt hole 1002, reverse side vertically fixes monaural 1004, monaural 1004
It is provided with monaural pin-and-hole 1003, monaural pin-and-hole 1003 and ears pin-and-hole 803 pass through to rotate pin connection.
Working mechanism：
In main binding apparatus 4 unblock separation process, main binding apparatus 4 separate and move out, main bundle in motor process
Tie up device 4 and pass through sliding pair 5 along the adjustable type screw rod 601 slip simultaneously relative position between automatic synchronization bulb bolt and bulb bolt seat
Put it is ensured that the two smoothly departs from；After bulb bolt and bulb bolt seat completely disengage from, main binding apparatus are in the second adjustable type screw rod 801
Constrain lower edge hinge 9 with regulatable sleeve 7 to move in a circle；It is buffered recovery pad 11 to brake back after moving to suitable position
Receive, thus the brake safe guiding realizing main binding apparatus 4 reclaims.
The method can be applicable to each model main binding apparatus unblock certification test in, apply also for big momentum, high-risk point
In in vitro braking and safe retrieving explosion separation test.
Above in conjunction with drawings and Examples, the present invention is explained in detail, but the present invention is not limited to above-mentioned enforcement
Example, in the ken that those of ordinary skill in the art possess, can also do on the premise of without departing from present inventive concept
Go out various change.The content not being described in detail in the present invention all can adopt prior art.
Claims (9)
1. a kind of spacecraft Explosive separation guide type safe retrieving assay device is it is characterised in that include the main binding apparatus of aircraft
Linkage section, main binding apparatus, bay section switching tooling is passed through with boundary condition simulation device even in aircraft main binding apparatus linkage section top
Connect, main binding apparatus one end is connected with aircraft binding, and the other end is connected with guide type retracting device top, and guide type reclaims dress
Put bottom to pass through on hinge fixed bottom boundary；In aircraft main binding apparatus linkage section, sensor, sensor and test are installed
System connects；Ground laying buffering reclaims pad；After on-test, main binding apparatus unblock separates, the main binding dress after separating
Put and rotate along hinge with guide type retracting device.
2. spacecraft Explosive separation guide type safe retrieving assay device as claimed in claim 1 is it is characterised in that 4 sets of main bindings
Device and guide type retracting device are symmetrically distributed in aircraft main binding apparatus linkage section periphery.
3. spacecraft Explosive separation guide type safe retrieving assay device as claimed in claim 1 or 2 is it is characterised in that described side
Boundary's analog includes pedestal, post block and crossbeam, and wherein pedestal is connected with post block and ground base respectively, and post block is with crossbeam even
Connect.
4. spacecraft Explosive separation guide type safe retrieving assay device as claimed in claim 1 or 2 is it is characterised in that described
Buffering reclaims pad and is formed by air bag, sponge and rubber layering place mat, and air bag is located at centre, rubber and sponge be located at respectively upper strata and
Lower floor.
5. spacecraft Explosive separation guide type safe retrieving assay device as claimed in claim 1 or 2 is it is characterised in that described lead
Include connecting support seat, regulatable sleeve, rod-pulling type ears, hinge, support connect base to formula retracting device；Described main binding
Device is connected with connecting support seat top, and sliding pair is provided therebetween, and bottom is enclosed within inside regulatable sleeve；Adjustable set
Outside rod-pulling type ears, rod-pulling type ears top is connected jacket casing with regulatable sleeve, bottom connects hinge, hinge with
Support connect base connects, and supports connect base to be fixed on ground.
6. spacecraft Explosive separation guide type safe retrieving assay device as claimed in claim 5 is it is characterised in that described connection
Support base includes adjustable type screw rod, interface, butt hole, and wherein adjustable type screw rod is vertical with interface fixes, adjustable type screw rod
It is nested in inside regulatable sleeve, main binding apparatus pass through butt hole and connecting support seat top connects, setting at interface is slided
Dynamic pair.
7. spacecraft Explosive separation guide type safe retrieving assay device as claimed in claim 5 is it is characterised in that described adjustable
Formula sleeve two ends are to connect upper screw and the lower screw of connection, and middle is pull bar regulatory region, and in connection, screw and the lower screw of connection divide
Wei not left-handed and dextrorotation.
8. spacecraft Explosive separation guide type safe retrieving assay device as claimed in claim 5 is it is characterised in that described pull bar
Formula ears are the second adjustable type screw rod by top, and bottom is ears, and ears are provided with ears pin-and-hole, wherein adjustable type screw rod with can
Mode sleeve connects for nested type.
9. spacecraft Explosive separation guide type safe retrieving assay device as claimed in claim 5 is it is characterised in that described support
Connect base includes ground interface, and ground interface is provided with ground butt hole, and ground butt hole is connected with ground base, the back of the body
It is vertically and fixedly provided with monaural to face, monaural is provided with monaural pin-and-hole, monaural pin-and-hole and ears pin-and-hole pass through to rotate pin connection.
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| CN201610868556.1A CN106482970B (en) | 2016-09-30 | 2016-09-30 | A kind of spacecraft Explosive separation guide type safe retrieving experimental rig |
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|---|---|---|---|
| CN201610868556.1A CN106482970B (en) | 2016-09-30 | 2016-09-30 | A kind of spacecraft Explosive separation guide type safe retrieving experimental rig |
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| CN106482970B CN106482970B (en) | 2018-11-06 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109018452A (en) * | 2018-07-27 | 2018-12-18 | 北京航天长征飞行器研究所 | A kind of tracking of rocket bay section drop point site and search system |
| CN110940531A (en) * | 2019-12-01 | 2020-03-31 | 西安航天动力测控技术研究所 | Test device and method for researching unlocking separation time sequence and separation reliability of aircraft cabin |
| CN112014080A (en) * | 2020-07-17 | 2020-12-01 | 沈阳航天新光集团有限公司 | Inter-device connection and separation device assembling and testing simulation tool and assembling and testing method |
| CN112254923A (en) * | 2020-09-22 | 2021-01-22 | 北京强度环境研究所 | Binding connecting rod simulation device for core-level supporting binding rocket scaling model |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110940531A (en) * | 2019-12-01 | 2020-03-31 | 西安航天动力测控技术研究所 | Test device and method for researching unlocking separation time sequence and separation reliability of aircraft cabin |
| CN112014080A (en) * | 2020-07-17 | 2020-12-01 | 沈阳航天新光集团有限公司 | Inter-device connection and separation device assembling and testing simulation tool and assembling and testing method |
| CN112254923A (en) * | 2020-09-22 | 2021-01-22 | 北京强度环境研究所 | Binding connecting rod simulation device for core-level supporting binding rocket scaling model |
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| Publication number | Publication date |
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| CN106482970B (en) | 2018-11-06 |
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