CN100427360C - Microgravity simulating spacecraft ground emitting and testing device - Google Patents
Microgravity simulating spacecraft ground emitting and testing device Download PDFInfo
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- CN100427360C CN100427360C CNB2007100350236A CN200710035023A CN100427360C CN 100427360 C CN100427360 C CN 100427360C CN B2007100350236 A CNB2007100350236 A CN B2007100350236A CN 200710035023 A CN200710035023 A CN 200710035023A CN 100427360 C CN100427360 C CN 100427360C
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- flat pad
- space vehicle
- test device
- slip flat
- vehicle ground
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Abstract
The invention relates to an analog micro weight space crafter land emitting testing device that comprises the bracket, emission barrel, fixture, erecting linear guide track at one side of the bracket, sliding emission platform on the linear guiding track, with the emission barrel fixed on the sliding emission platform through the fixture, with buffer set under the platform. It has imitable analog micro weight environment, being able to finish the traditional land emitting, with instant parameter testing function, integrating the testing device with the emission platform, strong in impact resistance ability.
Description
Technical field
The present invention relates to the ground launching test device of space vehicle, relate in particular to the space vehicle ground launching test device of simulated microgravity.
Background technology
The mode of tradition fixed point launching test can not adapt to the requirement of advanced space vehicle development to ground experiment owing to do not break away from the influence of action of gravity.For a long time, the ground-test plant of space vehicle is to be undertaken by manually building the mode that emission support, fixed point emission, the combination of various test apparatus measure.It is long that this mode exists feedway, proving installation to build the cycle, the emission of can only fixing a point, shortcoming such as firing altitude can not be adjusted, and instrument is various mixed and disorderly, and the experimental set-up recycling rate of waterused is low.Therefore, realize the test system and test integration of function, the variation of tested object, the modularization of test equipment, the automation of test experiments has realistic meaning, and the test of carrying out space vehicle launch and flight performance under the ground simulation space microgravity environment has become important research direction.Microgravity is called zero gravity, weightlessness or loss of weight power again.Ground realizes that the method for microgravity mainly contains: the fall well or the tower method that falls, and slow gyrator method, the free fall object method that aerostat discharges is made the aircraft method of parabolic flight.At present, the microgravity level height of the fall tower or the well that falls, cheap, easy realization become the microgravity test facility of main flow.Units such as country of Chinese Academy of Sciences microgravity experiment chamber all have high-level microgravity experiment facilities such as tower, and tower is set up for the test of background sciences such as biomechanics, microgravity fluid mechanics, calorifics, space material, nano biological and biomedicine but these fall.There is very strong impulsive force the space vehicle T-time.At present, free-falling body was still directly from eminence free-falling body scheme after no matter the tower method that falls adopted upthrow, and the impact of emissivity all can not be resisted in the drop tower test cabin.And, record the emission component of force and necessarily require force gauge to be installed on the benchmark of certain rigidity, the existing tower Laboratory Module that falls is in the installation requirement that free state can not satisfy force gauge at all in dropping process.
Summary of the invention
The technical problem to be solved in the present invention is to overcome the deficiencies in the prior art, but a kind of simulated microgravity environment is provided, can finishes the surface launching of tradition fixed point ground, has the T-time test function, is the strong space vehicle ground launching test device of one, anti-impact force with measure and control device and flat pad collection.
For solving the problems of the technologies described above, the technical scheme that the present invention proposes is: a kind of space vehicle ground launching test device of simulated microgravity, comprise support, canister launcher and anchor clamps, vertically be equiped with line slideway on one side of described support, be equiped with the slip flat pad on the line slideway, canister launcher is fixed on the slip flat pad by anchor clamps, and slip flat pad below is provided with energy disperser.
Be equiped with six component force sensors, electric ignition interface, control module and two high-pressure gas bottles on the described slip flat pad, six component force sensors are installed in slip flat pad central authorities, the axis of six component force sensors is vertical with the slip flat pad, canister launcher is fixed on the slip flat pad by anchor clamps and six component force sensors successively, canister launcher and six component force sensors are coaxially set, electric ignition interface, control module and two high-pressure gas bottles are individually fixed on the slip flat pad, and are arranged in around the six component force sensors.
Described slip flat pad upper end is connected with bont.
Described bont comprises electromagnet, magnet suction piece, stepping motor, rope and pulley, and electromagnet is located at slip flat pad upper end, and magnet is inhaled piece and is located at the electromagnet upper end, and rope is set around on the pulley, and magnet is inhaled piece and linked to each other with stepping motor by rope.
Described frame bottom is provided with fixed base plate.
Described support is provided with roller.
Described support is divided into more than two sections or two sections, and two neighboring sections is fixed by locating dowel pin.
Compared with prior art, advantage of the present invention just is: line slideway and slip flat pad are set on support, canister launcher is fixed on the slip flat pad, slide up and down along the line slideway speed change by control slip flat pad, can be canister launcher simulated microgravity environment, slip flat pad below is provided with energy disperser, and the slip flat pad is played safe recovery effect, improves the recycling rate of waterused of experimental set-up; With six component force sensors, electric ignition interface, control module and two high-pressure gas bottles and slip flat pad collection is one, has simplified experimental facilities, has shortened the test preparatory period; Bont can be sling the slip flat pad to specified altitude assignment or rapid release slip flat pad according to requirement of experiment; Frame bottom is provided with fixed base plate, and support is fixed on the reinforced concrete bed by fixed base plate, and the ability that makes support bear launching shock improves greatly, and support stability is good, is convenient to accurate measurement; Support is provided with that roller, support are divided into more than two sections or two sections, two neighboring sections is fixed by locating dowel pin, and this structure is convenient to moving and dismounting of support.
Description of drawings
Fig. 1 is a main TV structure scheme drawing of the present invention;
Fig. 2 is a left TV structure scheme drawing of the present invention;
Fig. 3 is the partial enlarged drawing of slip flat pad.
Marginal data:
1, support 2, line slideway
3, slip flat pad 4, bont
5, energy disperser 6, canister launcher
7, anchor clamps 11, fixed base plate
12, roller 13, locating dowel pin
31, six component force sensors 32, electric ignition interface
33, control module 34, high-pressure gas bottle
41, electromagnet 42, magnet are inhaled piece
43, stepping motor 44, rope
45, pulley
The specific embodiment
As Fig. 1, Fig. 2 and shown in Figure 3, the space vehicle ground launching test device of simulated microgravity of the present invention, comprise support 1, canister launcher 6 and anchor clamps 7, support 1 bottom is provided with four fixed base plates 11, support 1 is fixed on the reinforced concrete bed by fixed base plate 11, the ability that makes support 1 bear launching shock improves greatly, support 1 good stability, be convenient to accurate measurement, vertically be equiped with line slideway 2 on one side of support 1, be equiped with slip flat pad 3 on the line slideway 2, canister launcher 6 is fixed on the slip flat pad 3 by anchor clamps 7, slip flat pad 3 belows are provided with energy disperser 5, energy disperser 5 is fixed on the reinforced concrete bed by holding-down bolt, slides up and down along line slideway 2 speed changes by control slip flat pad 3, can be canister launcher 6 simulated microgravity environment, 5 pairs of slip flat pads 3 of energy disperser play safe recovery effect, improve the recycling rate of waterused of experimental set-up.By 11 times the squareness that backing plate is adjusted line slideway 2 on the support 1 being set at fixed base plate, support 1 is provided with roller 12, and support 1 is divided into two sections, and fixing by four locating dowel pins 13 between two sections, this structure is convenient to moving and dismounting of support 1.Be equiped with six component force sensors 31 on the slip flat pad 3, electric ignition interface 32, control module 33 and two high-pressure gas bottles 34, six component force sensors 31 are installed in slip flat pad 3 central authorities, the axis of six component force sensors 31 is vertical with slip flat pad 3, canister launcher 6 is fixed on the slip flat pad 3 by anchor clamps 7 and six component force sensors 31 successively, canister launcher 6 and six component force sensors 31 are coaxially set, electric ignition interface 32, control module 33 and two high-pressure gas bottles 34 are individually fixed on the slip flat pad 3, and are arranged in around the six component force sensors 31.High pressure gas in two high-pressure gas bottles 34 provide power for pull pin switch or propelling of the emission of space vehicle, and high pressure gas insert the afterbody of canister launcher 6 by pipeline.Electric ignition interface 32 provides the electric ignition signal for the space vehicle emission, and these interfaces are provided with by associated electrical firing circuit standard.Control module 33 will be controlled the sequential flow process of space vehicle ground emission experiment on the one hand, will gather, write down, store the emissivity signal of the space vehicle T-time of six component force sensors, 31 perception on the other hand.Is one with six component force sensors 31, electric ignition interface 32, control module 33 and two high-pressure gas bottles 34 with slip flat pad 3 collection, has simplified experimental facilities, has shortened the test preparatory period.Slip flat pad 3 upper ends are connected with bont 4, comprise electromagnet 41, magnet suction piece 42, stepping motor 43, rope 44 and pulley 45, electromagnet 41 is located at slip flat pad 3 upper ends, magnet is inhaled piece 42 and is located at electromagnet 41 upper ends, rope 44 is set around on the pulley 45, magnet is inhaled piece 42 and is linked to each other with stepping motor 43 by rope 44, and bont 4 can be sling slip flat pad 3 to specified altitude assignment or rapid release slip flat pad 3 according to requirement of experiment.When using experimental set-up of the present invention,, can record slip flat pad 3 whereabouts acceleration change situations by in the spaceflight body, acceleration pick-up being installed.
Claims (10)
1, a kind of space vehicle ground launching test device of simulated microgravity, comprise support (1), canister launcher (6) and anchor clamps (7), it is characterized in that vertically being equiped with line slideway (2) on the side of described support (1), be equiped with slip flat pad (3) on the line slideway (2), canister launcher (6) is fixed on the slip flat pad (3) by anchor clamps (7), and slip flat pad (3) below is provided with energy disperser (5).
2, space vehicle ground launching test device according to the described simulated microgravity of claim 1, it is characterized in that being equiped with on the described slip flat pad (3) six component force sensors (31), electric ignition interface (32), control module (33) and two high-pressure gas bottles (34), six component force sensors (31) are installed in slip flat pad (3) central authorities, the axis of six component force sensors (31) is vertical with slip flat pad (3), canister launcher (6) is fixed on the slip flat pad (3) by anchor clamps (7) and six component force sensors (31) successively, canister launcher (6) is coaxially set with six component force sensors (31), electric ignition interface (32), control module (33) and two high-pressure gas bottles (34) are individually fixed on the slip flat pad (3), and are arranged in six component force sensors (31) on every side.
3,, it is characterized in that described slip flat pad (3) upper end is connected with bont (4) according to the space vehicle ground launching test device of claim 1 or 2 described simulated microgravities.
4, according to the space vehicle ground launching test device of the described simulated microgravity of claim 3, it is characterized in that described bont (4) comprises electromagnet (41), magnet suction piece (42), stepping motor (43), rope (44) and pulley (45), electromagnet (41) is located at slip flat pad (3) upper end, magnet is inhaled piece (42) and is located at electromagnet (41) upper end, rope (44) is set around on the pulley (45), and magnet is inhaled piece (42) and linked to each other with stepping motor (43) by rope (44).
5,, it is characterized in that described support (1) bottom is provided with fixed base plate (11) according to the space vehicle ground launching test device of the described simulated microgravity of claim 3.
6,, it is characterized in that described support (1) bottom is provided with fixed base plate (11) according to the space vehicle ground launching test device of the described simulated microgravity of claim 4.
7,, it is characterized in that described support (1) is provided with roller (12) according to the space vehicle ground launching test device of the described simulated microgravity of claim 5.
8,, it is characterized in that described support (1) is provided with roller (12) according to the space vehicle ground launching test device of the described simulated microgravity of claim 6.
9, according to the space vehicle ground launching test device of the described simulated microgravity of claim 7, it is characterized in that described support (1) is divided into more than two sections or two sections, two neighboring sections is fixing by locating dowel pin (13).
10, the space vehicle ground launching test device of described simulated microgravity according to Claim 8 is characterized in that described support (1) is divided into more than two sections or two sections, and two neighboring sections is fixing by locating dowel pin (13).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007100350236A CN100427360C (en) | 2007-05-30 | 2007-05-30 | Microgravity simulating spacecraft ground emitting and testing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007100350236A CN100427360C (en) | 2007-05-30 | 2007-05-30 | Microgravity simulating spacecraft ground emitting and testing device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101058341A CN101058341A (en) | 2007-10-24 |
| CN100427360C true CN100427360C (en) | 2008-10-22 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2007100350236A Expired - Fee Related CN100427360C (en) | 2007-05-30 | 2007-05-30 | Microgravity simulating spacecraft ground emitting and testing device |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103472861B (en) * | 2013-08-06 | 2016-12-07 | 总装备部工程设计研究总院 | The space grand micro control system of servo-actuated identical tension |
| CN107554823B (en) * | 2017-08-09 | 2019-08-02 | 湖北航天技术研究院总体设计所 | A kind of large scale segmented rocket has transported perpendicular transmitting girder structure |
| CN108725852B (en) * | 2018-05-30 | 2020-07-17 | 中国科学院空间应用工程与技术中心 | Electromagnetic upward-throwing microgravity device, control method and system |
| CN111746823A (en) * | 2020-07-06 | 2020-10-09 | 北京空间技术研制试验中心 | Test method for verifying ejection separation of cruise aircraft assembly |
| CN112503999B (en) * | 2020-11-07 | 2023-04-14 | 南京理工大学 | Water target way built on stilts gun position structure |
| CN117864442A (en) * | 2023-12-18 | 2024-04-12 | 中国科学院空间应用工程与技术中心 | Underground vacuum tube ejection type microgravity experimental device and experimental method |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4772175A (en) * | 1986-11-13 | 1988-09-20 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Space station erectable manipulator placement system |
| US5974939A (en) * | 1994-05-02 | 1999-11-02 | Lockhead Martin Corporation | Modular launch pad system |
| CN2387033Y (en) * | 1999-08-09 | 2000-07-12 | 中国科学院生物物理研究所 | Multifunctional clinostat for simulating micro-gravity biological effect |
-
2007
- 2007-05-30 CN CNB2007100350236A patent/CN100427360C/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4772175A (en) * | 1986-11-13 | 1988-09-20 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Space station erectable manipulator placement system |
| US5974939A (en) * | 1994-05-02 | 1999-11-02 | Lockhead Martin Corporation | Modular launch pad system |
| CN2387033Y (en) * | 1999-08-09 | 2000-07-12 | 中国科学院生物物理研究所 | Multifunctional clinostat for simulating micro-gravity biological effect |
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| Publication number | Publication date |
|---|---|
| CN101058341A (en) | 2007-10-24 |
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Granted publication date: 20081022 Termination date: 20140530 |