CN109665124A - A kind of spacecraft plate deployable structure thermal environment simulation suspention experimental provision - Google Patents
A kind of spacecraft plate deployable structure thermal environment simulation suspention experimental provision Download PDFInfo
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- CN109665124A CN109665124A CN201910058065.4A CN201910058065A CN109665124A CN 109665124 A CN109665124 A CN 109665124A CN 201910058065 A CN201910058065 A CN 201910058065A CN 109665124 A CN109665124 A CN 109665124A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
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Abstract
The present invention discloses a kind of spacecraft plate deployable structure thermal environment simulation suspention experimental provision, including support bracket, by suspension apparatus be suspended in the underface of support bracket by self-latching hinge connection can plate to unfurl, be fixed on support bracket side be can the folding movement of plate to unfurl the motor drive module of power resources is provided, mounted in the synchronous pulley mechanism that can transmit synchronous folding exhibition movement between windsurfing between plate to unfurl, the front and back two sides for being fixed on support bracket, which is installed, promising can provide the thermal environment simulation device of thermal environment by plate to unfurl.The present invention is capable of the expansion and locking process of Simulated Spacecraft deployable structure, and it is capable of the deformation of simulation space microgravity, heat radiation situation lower face, the kinetic characteristics of deployable structure are tested, design to spacecraft deployable structure and performance has very important significance in orbit.
Description
Technical field
The present invention relates to simulations to suspend experimental provision technical field in midair, more particularly to a kind of spacecraft plate deployable structure heat
Experimental provision is suspended in environmental simulation in midair.
Background technique
Deployable structure is widely used on spacecraft at present, and wherein solar battery array is that the main energetic of spacecraft supplies
To source.The environment such as the space vacuum as locating for solar battery array, microgravity, heat radiation are exceedingly odious, too high or too low temperature
The incident photon-to-electron conversion efficiency that may cause solar panel reduces, and excessive thermal deformation may cause coming unglued and falling off for solar panel,
It even is broken cell array frame, supplies deficiency so as to cause the electric energy of entire spacecraft.Further, since spacecraft exists
Rail will periodically fly through sunshine area and shadow region during running, and the Orbital heat flux and heat radiation situation that it is received can be with tracks
Change in location and constantly change (i.e. the spatial heat environment of alternating hot and cold), this will generate the vibration temperature field that changes over time, when
When the thermal characteristics and elastic property of structure are with change of temperature field, due to Component Flexible and connects hinge gap, often
Cause structure that thermal deformation and thermal-structure coupled vibration occurs, may cause entire spacecraft cisco unity malfunction or needs frequent
Posture is adjusted, the spacecraft service life is reduced, it is also possible to so that satellite equipment equipment precision is reduced or is unable to steady operation, even result in
The failure of entire spacecraft task.Therefore, it is special to fully realize dynamics of the solar battery array in expansion and locking process
Property, and its issuable thermal deformation under spacing high-temperature and low temperature thermal environment is simulated, the structure of solar battery array is designed
Performance has very important significance in orbit.
It is ground currently, having carried out correlation to the ground simulating of spacecraft deployable structure there are many domestic and international researcher
Study carefully, for complicated space flight deployable structure, there are a series of problems for ground simulating.Firstly, existing ground simulation is real
Testing the expansion for being relatively difficult to guarantee deployable structure and collapsing process has synchronism, and the design of part deployable structure is excessively complicated, quality
And it is oversized, expansion motion credibility is poor.Secondly, suspension apparatus cannot achieve expected function, cannot balance can open up knot
The gravity of structure, can not microgravity environment in simulation space.Further, it for the hinge of connection deployable structure, is merely capable of
Realize preliminary folding, self-locking and different gap situation the simulated experiment after can not achieve folding exhibition.Finally, in ground face mould
The day and night temperature in space can be seldom considered in draft experiment, do not provided in corresponding thermal environment simulation device simulation space too
Thermal environment in the case of positive heat radiation, cannot actual conditions in accurate simulation space.
Therefore, microgravity and heat radiation environment in properer simulation space, and spacecraft can be opened up in ground experiment
The comparative experiments of the more detailed folding exhibition procedural test folding malleability energy of structure progress, has the design for instructing spacecraft deployable structure
Significance.
Summary of the invention
In view of the technical drawbacks of the prior art, it is an object of the present invention to provide a kind of spacecraft plates can open up knot
Structure thermal environment simulation suspends experimental provision in midair.
The technical solution adopted to achieve the purpose of the present invention is:
A kind of spacecraft plate deployable structure thermal environment simulation suspends experimental provision in midair, including support bracket and passes through suspention
Device be suspended in below support bracket by self-latching hinge connection can plate to unfurl, electricity is installed in the side of the support bracket
Machine drive module is by that can realize expansion and folding operation by plate to unfurl described in the synchronous pulley mechanism controls that plate connects to unfurl
Synchronism, before and after the support bracket two sides it is promising can to unfurl plate provide thermal environment thermal environment simulation device.
The suspension apparatus includes the slide rail being mounted below the suspention channel steel of support bracket, is cooperated with slide rail
Mobile sliding block, the suspension wire being mounted below mobile sliding block；There are suspention counterweight and pulling force to pass respectively at suspension wire both ends
Sensor；The upper and lower part of the tension sensor is separately connected length adjuster；The length of suspention the V-arrangement hook and lower part
Adjuster connection.
Described can plate include to unfurl three windsurfing bodies formed by the solar energy sailboard that self-latching hinge connects, the windsurfing
One end of body is hingedly connected with connection frame by self-latching hinge, and the connection frame is hingedly connected by self-latching hinge with L-shaped fixed plate
It connects；One end of the L-shaped fixed plate is fixed with the simulation wall on the side for being fixed on support bracket, the side peace of the windsurfing body
Fill synchronous pulley mechanism.
The motor drive module includes motor, and the motor is fixed on the outside of the simulation wall；The motor passes through electricity
Machine shaft coupling connects motor synchronous pulley mechanism, and motor synchronous pulley mechanism includes that the motor that connect with motor coupler is same
Walk the concentric installation of self-latching hinge between belt wheel and L-shaped fixed plate and connection frame motor synchronous pulley and cooperation it is same
Walk band.
The synchronous pulley mechanism includes the transmission V-belt of synchronous pulley and connection, and the synchronous pulley mechanism is three groups,
Two synchronous pulleys of first group of synchronous pulley mechanism self-latching hinge and connection frame between L-shaped fixed plate and connection frame respectively
Self-locking hinge between the first windsurfing connects coaxially arranged；Two synchronous pulleys of second group of synchronous pulley mechanism respectively with connection frame
Self-latching hinge between self-latching hinge between number one windsurfing and number one windsurfing and No. second windsurfing is coaxially arranged；Third
Two synchronous pulleys self-latching hinge and second between number one windsurfing and No. second windsurfing respectively of group synchronous pulley mechanism
Self-latching hinge number between windsurfing and third windsurfing is coaxially arranged.
The self-latching hinge includes the centre drawer hinge and centre drawer hinge bracket to be linked together by hinge pin, is pacified in hinge pin
Fill Varied clearance sleeve；Threaded hole is provided on the centre drawer hinge bracket, card slot pin shaft is installed to centre drawer hinge bracket spiral shell by screw with card slot end cap
On pit；Through-hole is provided on the centre drawer hinge, the card slot pin shaft is installed on centre drawer hinge by nut；Scroll spring passes through bullet
Spring end cap pin shaft is installed to spring terminal and covers；The scroll spring is installed to the centre drawer hinge through-hole by the spring end cap
On.
The thermal environment simulation device includes the fixation bracket of heat radiation lamp and the fixed heat radiation lamp, the fixed branch
Frame is installed to the support bracket front and back by bolt；The heat radiation lamp is mounted on fixed bracket by bolt.
The present invention is capable of the expansion and locking process of Simulated Spacecraft deployable structure, and being capable of simulation space microgravity, heat
The kinetic characteristics of deployable structure are tested in the deformation of radiation event lower face, to the design of spacecraft deployable structure and
Performance has very important meaning in orbit.
Detailed description of the invention
Fig. 1 is the stereoscopic schematic diagram of spacecraft plate deployable structure thermal environment simulation suspention experimental provision of the invention.
Fig. 2 is the top view of spacecraft plate deployable structure thermal environment simulation suspention experimental provision of the invention.
Fig. 3 is the front view of spacecraft plate deployable structure thermal environment simulation suspention experimental provision of the invention.
Fig. 4 is microgravity suspension apparatus schematic diagram of the invention.
Fig. 5 be it is of the invention can plate to unfurl structural schematic diagram.
Fig. 6 is the schematic diagram of motor drive module of the invention.
Fig. 7 is the schematic diagram of self-latching hinge of the invention.
Fig. 8 is self-latching hinge explosive view of the invention.
Appended drawing reference: 1- support bracket, 2- suspension apparatus, 3- can plate to unfurl, 4- motor drive module, 5- synchronous belt turbine
Structure, 6- self-latching hinge, 7- thermal environment simulation device；
1-1 supports square steel, and 1-2 suspends channel steel in midair, and 1-3 levels parallels；
2-1 slide rail, the mobile sliding block of 2-2,2-3 suspension wire, 2-4 suspend counterweight, 2-5 tension sensor, 2-6 length in midair
Adjuster, 2-7 suspend V-arrangement hook in midair；
3-1 L-shaped fixed plate, 3-2 connection frame, 3-3 solar energy sailboard, 3-4 synchronous pulley angle cleat, 3-5 simulation wall,
3-6 fixes end cap；
4-1 motor, 4-2 motor coupler, the synchronous small pulley of 4-3 motor, the fixed angle steel of 4-4 motor, 4-5 motor synchronize greatly
Belt wheel, 4-6 motor big belt wheel roller bearing, 4-7 synchronous belt；
5-1 synchronous pulley, 5-2 fixed pin shaft, 5-3 transmit V-belt；
6-1 centre drawer hinge, 6-2 spring terminal cancelling axis, 6-3 hinge pin, 6-4 Varied clearance sleeve, 6-5 centre drawer hinge bracket, 6-6 card slot
Pin shaft, 6-7 card slot end cap, 6-8 scroll spring, 6-9 spring end cap；
7-1 heat radiation lamp, the fixed bracket of 7-2.
Specific embodiment
The present invention is described in further detail below in conjunction with the drawings and specific embodiments.It should be appreciated that described herein
Specific embodiment be only used to explain the present invention, be not intended to limit the present invention.
As shown in Figure 1, spacecraft plate deployable structure thermal environment simulation of the invention suspends experimental provision in midair, comprising: load-bearing
Bracket 1, suspension apparatus 2 plate 3, motor drive module, 4 synchronous pulley mechanisms 5, self-latching hinge 6, thermal environment simulation can fill to unfurl
Set 7, in the present embodiment, suspension apparatus 2 is mounted on the underface of support bracket 1, can be mounted on suspension apparatus 2 just by plate 3 to unfurl
Lower section, motor drive module 4 are mounted on the side of support bracket 1, and synchronous pulley mechanism 5 and self-latching hinge 6 are arranged in can
To unfurl between the windsurfing of plate 3, thermal environment simulation device 7 is mounted on the front and back two sides of support bracket 1.
As shown in figure 3, support bracket 1 includes support square steel 1-1, parallels 1-2 is leveled, suspends channel steel 1-3 in midair.Support square steel 1-
1 supports the weight of entire simulator stand；Suspention channel steel 1-3 is fixed on the lower section of top braces square steel 1-1, outstanding for installing
Device for hoisting；Leveling parallels 1-2 is placed between longitudinal bracing square steel and top square steel, and it is flat to provide smooth work for suspension apparatus
Face.Wherein, support square steel 1-1 selects square steel, and leveling parallels 1-2 selects fine thread to level parallels, leveling essence with higher
Degree, suspention channel steel 1-3 select square groove steel.Thermal environment simulation device 7 includes heat radiation lamp 7-1 and fixed bracket 7-2, fixed bracket
7-2 is mounted on the front of support bracket 1-1 with below, and heat radiation lamp 7-1 is mounted on fixed bracket 7-2, and direct irradiation can be opened up
Windsurfing, to provide certain working temperature environment.Wherein, heat radiation lamp selects the infrared lamp of temperature-adjustable, and in an experiment
Real-time measurement is carried out with infrared radiation thermometer.
Specifically, support bracket 1 selects the support square steel 1-1 of 100mm × 100mm to be welded, and overall dimensions are
2500mm×1400mm×800mm.It suspends channel steel 1-3 in midair and selects 700mm × 50mm × 25mm channel steel.
As shown in figure 4, suspension apparatus includes slide rail 2-1, mobile sliding block 2-2, suspension wire 2-3 suspend counterweight 2- in midair
4, tension sensor 2-5, length adjuster 2-6, suspention V-arrangement link up with 2-7.Wherein, slide rail 2-1 is mounted on outstanding by bolt
It hangs below channel steel 1-3, mobile sliding block 2-2 is stuck on guide rail by the sliding slot on slide rail 2-1, and can be realized horizontal direction
Sliding, the buckle of fixed wirerope is installed on mobile sliding block 2-2, suspension wire 2-3 can be installed；The suspension wire 2-
3 lower sections hang suspention counterweight 2-4 and tension sensor 2-5 on both sides by roller bearing pulley respectively and realize gravitational equilibrium and reality
When pull force calculation；The tension sensor 2-5 upper and lower side is equipped with length adjuster 2-6 convenient for adjusting the length of suspension wire 2-3
It is short；The suspention V-arrangement hook 2-7 is mounted below tension sensor 2-5, can realize gravitational equilibrium by plate 3 to unfurl to suspend in midair.
Specifically, suspension wire 2-3 use round-strand rope, diameter 3mm, breaking force of rope summation N >
7510N。
As shown in figure 5, can plate include to unfurl L-shaped fixed plate 3-1, connection frame 3-2, solar energy sailboard 3-3, synchronous pulley connects
Meet angle steel 3-4, simulation wall 3-5, fixed end cap 3-6.Wherein, L-shaped fixed plate 3-1 passes through bolt and fixed end cap 3-6 and simulation
Wall 3-5 is fixed, and simulation wall 3-5 is mounted on the side of support bracket 1 by bolt, and motor drive module is installed in the outside of load bearing wall
4；It can plate 3 include to unfurl one piece of connection frame 3-2 and three pieces of solar energy sailboard 3-3, wherein L-shaped fixed plate 3-1 and connection frame, connect
Connect first solar energy sailboard in frame and left side, the first solar energy sailboard and the second intermediate solar energy sailboard, the second solar energy sail
It is connected by two self-latching hinges 6 between plate and the third solar energy sailboard on right side；The angle cleat 3-4 is by synchronous pulley
Mechanism 5 is mounted on can be to unfurl on plate.
It is described can to unfurl plate 3 when folding, by the driving of motor drive module 4 and synchronous pulley mechanism 5 and
The cooperation of self-latching hinge 6 is able to achieve and is folded by zigzag structure.
As shown in figure 5, the synchronous pulley mechanism 5 includes synchronous pulley 5-1, fixed pin shaft 5-2, V-belt 5-3 is transmitted.
Wherein, three synchronous pulley mechanisms 5 can be mounted with altogether in plate 3 to unfurl, is respectively used to transmission connection frame 3-2 and three blocks of solar energy
Movement between windsurfing 3-3；Wherein synchronous pulley 5-1 is mounted on angle cleat 3-4 by fixed pin shaft 5-2；Transmit V-belt 5-
3, for installing two synchronous pulley 5-1 in each synchronous pulley mechanism 5, realize the transmitting of folding exhibition movement；Wherein each synchronization
The self-latching hinge 6 that belt wheel 5-1 is installed respectively between each plate is coaxial, realizes preferable folding exhibition motion state with this.
Specifically, three blocks of solar energy sailboard material selection aluminium alloys or 45# steel, connection frame select 45# Steel material,
In, connection frame is designed and sized to 250mm × 300mm × 10mm, and three pieces of solar energy sailboards are designed and sized to 500mm × 300mm
×20mm.It can according to need to carry out the replacement of windsurfing material and size.
As shown in fig. 6, motor drive module, including motor 4-1, motor coupler 4-2, the synchronous small pulley 4-3 of motor, electricity
Machine fixes angle steel 4-4, motor synchronous big belt wheel 4-5, motor big belt wheel roller bearing 4-6, synchronous belt 4-7.Wherein, motor 4-1
It is mounted on simulation wall 3-5 by the fixed angle steel 4-4 of motor；The synchronous small pulley 4-3 of the motor is pacified by motor coupler 4-2
On motor 4-1 output shaft；The synchronous big belt wheel 4-5 of the motor is mounted on connection frame 3-2 by angle cleat 3-4 bolt
On；The motor big belt wheel roller bearing 4-6 is mounted on the inside of the synchronous big belt wheel 4-5 of motor, realizes that big belt wheel runs well；Institute
Synchronous belt 3-7 is stated to connect the synchronous small pulley 4-3 of motor big belt wheel 4-5 synchronous with motor, the movement of transmitting motor output.
Specifically, motor selects 573P79-5206A model stepper drive motors；Motor coupler 4-2 selects MCO20-
6-8 shaft coupling；Big belt wheel roller bearing 4-6 selects deep groove ball bearing.
As shown in Figure 7 and Figure 8, self-latching hinge includes centre drawer hinge 6-1, spring terminal cancelling axis 6-2, hinge pin 6-3, between change
Gap sleeve 6-4, centre drawer hinge bracket 6-5, card slot pin shaft 6-6, card slot end cap 6-7, scroll spring 6-8, spring end cap 6-9.Female hinge
Chain 6-1 and centre drawer hinge bracket 6-5 is bolted that be mounted on can be to unfurl on plate 3；Hole is opened on the centre drawer hinge 6-1, to install
Spring terminal cancelling axis 6-2 is simultaneously fastened with nut；The scroll spring 6-8 is installed simultaneously by spring end cap 6-9 and end cap pin shaft 6-2
It is fixed on centre drawer hinge 6-1；It is provided with M4 threaded hole on the centre drawer hinge bracket 6-5, to install card slot pin shaft 6-6；The card slot end
Lid 6-7 is mounted on the both ends of card slot pin shaft 6-6, realizes one of card slot pin shaft 6-6 around the rotary motion of another axis；Institute
It is self-locking under the realization scroll spring 6-8 off working state of the screw on card slot pin shaft 6-6 by tightening to state scroll spring 6-8；Institute
Hinge pin 6-3 connection centre drawer hinge 6-1 and centre drawer hinge bracket 6-5 are stated, realizes the rotary motion between two hinges；The Varied clearance set
Cylinder 6-4 is mounted on hinge pin 6-3, to adjust hinge gap.
Specifically, Varied clearance sleeve 6-4 and hinge pin 6-3 selects 45# Steel material, and remaining parts select lighter aluminium
Alloy, to mitigate the overall weight of self-latching hinge；The Varied clearance sleeve 6-4 design size makes the hinge gap variation range to be
0.01mm, 0.02mm, 0.03mm, 0.04mm, 0.05mm, 0.06mm, 0.07mm, 0.08mm, 0.09mm, 0.10mm.To reality
Test tries the influence of hinge gap variation doubling exhibition movenent performance.
Specifically, for the relevant parameter during test experiments, this experimental provision, which can also be, is equipped with resistance-type
Angular displacement sensor, tension sensor, acceleration transducer.The resistance-type angular displacement sensor can be mounted in it is described can
To unfurl between 3 three pieces of solar energy sailboard 3-3 of plate, and it is coaxial with corresponding gap hinge 6, it is used to real-time measurement solar energy sail
Angular displacement between plate 3-3；The tension sensor 2-5 can be mounted on suspension wire 2-3, to real-time measurement steel wire
Rope tension numerical value, model UM-5kgf finely tune suspention counterweight by numerical value, with realize can plate 3 to unfurl microgravity environment；
The acceleration transducer can be mounted at the key point of solar energy sailboard 3-3, to acquire can plate to unfurl acceleration
Data.
The above is only a preferred embodiment of the present invention, it is noted that for the common skill of the art
For art personnel, various improvements and modifications may be made without departing from the principle of the present invention, these improvements and modifications
Also it should be regarded as protection scope of the present invention.
Claims (7)
1. a kind of spacecraft plate deployable structure thermal environment simulation suspends experimental provision in midair, which is characterized in that including support bracket with
And by suspension apparatus be suspended in below support bracket by self-latching hinge connection can plate to unfurl, in the side of the support bracket
Face is equipped with motor drive module by that can realize expansion by plate to unfurl described in the synchronous pulley mechanism controls that plate connects to unfurl
With the synchronism of folding operation, two sides is promising before and after the support bracket to provide the thermal environment simulation of thermal environment by plate to unfurl
Device.
2. spacecraft plate deployable structure thermal environment simulation suspends experimental provision in midair according to claim 1, which is characterized in that institute
Stating suspension apparatus includes the slide rail being mounted below the suspention channel steel of support bracket, the mobile cunning with slide rail cooperation
Block, the suspension wire being mounted below mobile sliding block；There are suspention counterweight and tension sensor respectively at suspension wire both ends；It is described
The upper and lower part of tension sensor is separately connected length adjuster；The suspention V-arrangement hook and the length adjuster of lower part connect
It connects.
3. spacecraft plate deployable structure thermal environment simulation suspends experimental provision in midair according to claim 1, which is characterized in that institute
Stating plate to include to unfurl three windsurfing bodies formed by the solar energy sailboard that self-latching hinge connects, and one end of the windsurfing body is logical
It crosses self-latching hinge and is hingedly connected with connection frame, the connection frame is articulated and connected by self-latching hinge and L-shaped fixed plate；The L shape
One end of fixed plate is fixed with the simulation wall on the side for being fixed on support bracket, and synchronous pulley is installed in the side of the windsurfing body
Mechanism.
4. spacecraft plate deployable structure thermal environment simulation suspends experimental provision in midair according to claim 3, which is characterized in that institute
Stating motor drive module includes motor, and the motor is fixed on the outside of the simulation wall；The motor is connected by motor coupler
Motor synchronous pulley mechanism is met, motor synchronous pulley mechanism includes the motor synchronous pulley and L connecting with motor coupler
The motor synchronous pulley of the concentric installation of self-latching hinge between shape fixed plate and connection frame and the synchronous belt of cooperation.
5. spacecraft plate deployable structure thermal environment simulation suspends experimental provision in midair according to claim 3, which is characterized in that institute
The transmission V-belt that synchronous pulley mechanism includes synchronous pulley and connection is stated, the synchronous pulley mechanism is three groups, first group of synchronization
Two synchronous pulleys of the belt wheel mechanism self-latching hinge between L-shaped fixed plate and connection frame and connection frame and the first windsurfing respectively
Between Self-locking hinge connect it is coaxially arranged；Two synchronous pulleys of second group of synchronous pulley mechanism respectively with connection frame and number one sail
Self-latching hinge between self-latching hinge between plate and number one windsurfing and No. second windsurfing is coaxially arranged；Third group synchronous pulley
Two synchronous pulleys of the mechanism self-latching hinge between number one windsurfing and No. second windsurfing and No. second windsurfing and respectively
Self-latching hinge between three windsurfings is coaxially arranged.
6. spacecraft plate deployable structure thermal environment simulation suspends experimental provision in midair according to claim 1, which is characterized in that institute
Stating self-latching hinge includes the centre drawer hinge and centre drawer hinge bracket to be linked together by hinge pin, and Varied clearance set is installed in hinge pin
Cylinder；Threaded hole is provided on the centre drawer hinge bracket, card slot pin shaft and card slot end cap are installed on centre drawer hinge bracket threaded hole by screw；It is described
Through-hole is provided on centre drawer hinge, the card slot pin shaft is installed on centre drawer hinge by nut；Scroll spring passes through spring terminal cancelling axis
Spring terminal is installed to cover；The scroll spring is installed on the centre drawer hinge through-hole by the spring end cap.
7. spacecraft plate deployable structure thermal environment simulation suspends experimental provision in midair according to claim 1, which is characterized in that institute
The fixation bracket that thermal environment simulation device includes heat radiation lamp and the fixed heat radiation lamp is stated, the fixed bracket passes through bolt
It is installed to the support bracket front and back；The heat radiation lamp is mounted on fixed bracket by bolt.
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| CN110530628A (en) * | 2019-09-30 | 2019-12-03 | 天津大学 | A kind of measuring device and measuring method of simulated machine tool structure thermal deformation |
| CN112033298A (en) * | 2020-08-25 | 2020-12-04 | 大连理工大学 | Spacecraft cabin body weight deformation measurement method based on motionless datum points |
| CN112781900A (en) * | 2020-12-15 | 2021-05-11 | 兰州空间技术物理研究所 | Inflation unfolding test method for flexible spacecraft in thermal vacuum environment |
| CN114379819A (en) * | 2022-03-22 | 2022-04-22 | 中国飞机强度研究所 | Solar radiation test system for airplane test and test method thereof |
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