CN113607391A - Testing device for simulating cubic star weightless ejection - Google Patents
Testing device for simulating cubic star weightless ejection Download PDFInfo
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- CN113607391A CN113607391A CN202110757229.XA CN202110757229A CN113607391A CN 113607391 A CN113607391 A CN 113607391A CN 202110757229 A CN202110757229 A CN 202110757229A CN 113607391 A CN113607391 A CN 113607391A
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- sliding
- ejector
- weightless
- simulating
- frame
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- 238000012360 testing method Methods 0.000 title claims abstract description 30
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims abstract description 28
- 238000000926 separation method Methods 0.000 claims abstract description 16
- 229910052742 iron Inorganic materials 0.000 claims abstract description 14
- 239000000872 buffer Substances 0.000 claims description 10
- 230000003139 buffering effect Effects 0.000 claims description 9
- 238000000034 method Methods 0.000 claims description 5
- 230000002745 absorbent Effects 0.000 claims description 3
- 239000002250 absorbent Substances 0.000 claims description 3
- 238000010521 absorption reaction Methods 0.000 claims description 3
- 238000009434 installation Methods 0.000 claims description 2
- 238000001179 sorption measurement Methods 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 3
- 238000004146 energy storage Methods 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 239000000523 sample Substances 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000007853 buffer solution Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- RKTYLMNFRDHKIL-UHFFFAOYSA-N copper;5,10,15,20-tetraphenylporphyrin-22,24-diide Chemical group [Cu+2].C1=CC(C(=C2C=CC([N-]2)=C(C=2C=CC=CC=2)C=2C=CC(N=2)=C(C=2C=CC=CC=2)C2=CC=C3[N-]2)C=2C=CC=CC=2)=NC1=C3C1=CC=CC=C1 RKTYLMNFRDHKIL-UHFFFAOYSA-N 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000002427 irreversible effect Effects 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
- 230000004580 weight loss Effects 0.000 description 1
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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
- G01M13/00—Testing of machine parts
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Individual Semiconductor Devices (AREA)
Abstract
The invention provides a test device for simulating weightless ejection of a cube, which can avoid artificial influence, can ensure a good initial state of a free falling body, can ensure that an ejector starts to fall and is electrified synchronously or the time difference between the start of falling and the start of electrification can be strictly controlled according to the electrification and unfolding time of the ejector, and can restrain a Pod in a separation direction when the ejector unfolds and ejects the cube, so that the speed of ejecting the cube is ensured to be the same as the actual on-rail separation speed, and the test device comprises the ejector, a vertical frame and a slide rod, wherein the ejector can be used for placing the cube and ejecting the cube out, the slide rod is arranged in the frame, the ejector is slidably arranged on the slide rod through a sliding sleeve and is guided through the slide rod, the iron block is arranged at the top of the ejector, and a sucker magnet assembly which can be adsorbed by the iron block is arranged at the top of the frame, the ejector is suspended at the top of the frame through the adsorption of the sucker magnet assembly and the iron block.
Description
Technical Field
The invention relates to the technical field of auxiliary devices for testing a cube star, in particular to a testing device for simulating weightless ejection of the cube star.
Background
At present, the on-orbit release of the cube star is usually realized by a specially-made ejector (Pod), the Pod is externally installed and fixed on a carrier rocket, and the cube star and a spring energy storage unit can be accommodated in the Pod. When the cube star needs to be released, the Pod end cover is opened, and the cube star is ejected out under the release action of the spring energy storage unit. The volume and weight of Pod is comparable to a cubic star.
Because the cube star is under the vacuum weightlessness condition when in-orbit release, in order to ensure the reliability of the catapult, in the Pod development stage, ground test is required to be carried out to test the performance of the catapult in all aspects.
If the ejection test is carried out under the gravity condition, the gravity of the cube increases the frictional resistance between the cube and the Pod, so that the ejection speed is reduced, and even the cube cannot be ejected, and on the other hand, when the cube is ejected, the ejected part can generate bending moment on the Pod, and influence or even irreversible damage is caused on the flatness of the contact sliding rail inside the Pod. The Pod ejection test needs to be performed under weightless conditions.
At present, no special equipment is used for carrying out ejection test on the Pod, the common method is that the Pod is lifted at a certain height manually, the Pod is allowed to fall freely by releasing hands and powered on at the same time, a Pod end cover is unfolded in the falling process, and the cube star pops up. However, this method has several disadvantages:
1. the initial attitude cannot be guaranteed: due to manual operation, the posture level of the Pod when falling can not be ensured, and even a small horizontal initial speed can be generated manually;
2. the coordination time is difficult to guarantee: because the design expansion time of the Pod is fixed, the Pod is generally in millisecond level, and the height from the ground when the cube is popped up is larger, the longer the pop-up distance when the Pod falls to the ground is, the larger the landing speed is, the safety of a test field and equipment is considered, the test height is generally about 2m, which requires that the Pod begins to fall and the Pod is powered up to be synchronous, because the reaction capacity of people is limited, the asynchronization phenomenon is easy to occur, the Pod is not popped up when falling to the ground because of too early release, the height from the ground when the Pod is popped up because of too late release, the landing speed of the equipment is too large, and the possibility of equipment damage is increased;
3. the separation speed is distinguished from the real situation: when the cuboids are separated in orbit, the Pod is installed on the rocket, the separation condition is regarded as the separation of the cuboids and the rocket, but the weight of the rocket is far larger than that of the cuboids, according to the momentum conservation theorem, the change amount of the speed of the rocket in the separation direction can be ignored to be 0 during the separation, and the separation speed of the cuboids is larger at the moment; in the manual free fall test, the separation condition is regarded as the separation of the cube star and the Pod, the weight difference between the cube star and the Pod is not large, according to the law of conservation of momentum, the Pod can obtain a certain separation speed in the separation direction, and the separation speed of the cube star is nearly half smaller than the real condition.
In summary, the conventional free fall test by manual throwing can simulate the weightless condition, but cannot truly simulate the on-orbit ejection condition of Pod.
Disclosure of Invention
The invention aims to overcome the defects of the prior art, adapt to the practical requirements and provide a test device for simulating the weightless ejection of a cube satellite.
In order to realize the purpose of the invention, the technical scheme adopted by the invention is as follows:
designing a test device for simulating weightless ejection of a cube satellite, which comprises an ejector, wherein the cube satellite can be placed in the ejector and ejected out; still include the frame of vertical type, install the slide bar in the frame, the catapult pass through sliding sleeve slidable mounting in on the slide bar and pass through the slide bar guide, still including install in the iron plate at catapult top, the top of frame install can with the absorbent sucking disc magnet subassembly of iron plate, the catapult passes through the absorption of sucking disc magnet subassembly and iron plate is unsettled in the frame top.
The side part of the ejector is provided with sliding sleeves in one-to-one correspondence with the sliding rods, the sliding sleeves are slidably sleeved on the sliding rods, and the sliding sleeves are fixedly installed on the installation plate of the side part of the ejector.
The frame comprises four longitudinal guide rail beams forming a vertical square shape and four transverse guide rail beams respectively positioned at two ends of the four longitudinal guide rail beams, and the upper end and the lower end of each sliding rod are respectively arranged on the transverse guide rail beams at the corresponding ends.
The ejector is characterized in that a buffering base is arranged at the bottom of the frame below the ejector, the buffering base comprises a bottom plate fixed to the bottom of the frame and a plurality of buffers arranged on the bottom plate, the buffers can adopt pneumatic resistance springs, the pneumatic resistance springs are longitudinally fixed on the bottom plate, stress rods of the pneumatic resistance springs are upwards arranged, and rubber buffering stress blocks are arranged at the end parts of the stress rods of the pneumatic resistance springs.
The upper end and the lower end of the sliding rod are respectively connected with a sliding adjusting component, and the sliding rod is arranged on the transverse guide rail beam through the sliding adjusting component; a sliding groove is formed in the side face of the transverse guide rail beam opposite to the end part of the sliding rod, the sliding adjusting assembly comprises a sliding block fixed at the end part of the sliding rod, two threaded holes are formed in the sliding block and located above the sliding groove in the transverse guide rail beam, a locking bolt is arranged in each threaded hole, and the end part of each locking bolt extends into the corresponding sliding groove; the opening end of the sliding groove is provided with a limiting part which is bent inwards, and a nut is further arranged in the sliding groove. The locking bolt is connected with the nut in a threaded mode after entering the sliding groove, the nut can be limited by the limiting portion, and the nut can slide in the sliding groove.
The connecting plate is used for connecting the two sliding blocks at the same end.
The sucker magnet assembly comprises a direct-current type sucker electromagnet and an upper supporting plate transversely arranged on a beam at the top of the frame, and the direct-current type sucker electromagnet is fixed on the upper supporting plate.
The direct current type sucker electromagnet and the ejector are connected with the programmable controller.
The slide bar is of a circular columnar structure.
The number of the sliding rods is at least three, and the sliding rods are symmetrically distributed around the ejector.
The invention has the beneficial effects that:
1. the design can ensure the initial posture of the ejector through the guidance of the four sliding rods;
2. according to the design, the plurality of buffers are arranged at the lower end of the bottom of the frame, so that the impact force on the probe when the probe falls to the ground can be relieved;
3. the design adopts the sliding adjusting component, the ejector can move back and forth when in use, and the ejector can be adapted to ejectors with different shapes and sizes; 4. the design adopts the cylindrical linear guide rail, has small resistance, can simulate the free falling state of equipment, realizes the restraint on the separation direction of the ejector, and reflects the real on-track separation condition;
5. this design adopts sucking disc formula electro-magnet to realize the release to the catapult, and simple structure can accurate control release time through adding electrical signal, cooperates programmable controller, can accurate control electro-magnet release and the time synchronization or the time difference that the catapult adds electrical.
Drawings
FIG. 1 is a schematic diagram of the main structure of the present invention;
FIG. 2 is a partial structural view of the bottom of the frame of the present design;
FIG. 3 is a partial schematic view of the ejector in this design after engagement with the frame at the top position;
FIG. 4 is another schematic view of the partial structure of the bottom of the frame in the present design;
FIG. 5 is a schematic diagram of the main structure of the transverse guide rail beam in the present design;
FIG. 6 is a schematic diagram of the external structure of the programmable controller in the present design;
fig. 7 is a schematic view of another main structure of the present invention.
Detailed Description
The invention is further illustrated with reference to the following figures and examples:
example 1: a test device for simulating weight loss ejection of a cube star, which is shown in fig. 1 to 7.
It comprises an ejector 6 (prior art) which can place a cube star inside and eject the cube star; still include the frame of vertical type, install slide bar 3 in the frame, specifically, the frame is including four longitudinal guide roof beams 2 and four transverse guide roof beams 1 that are located four longitudinal guide roof beams 2 both ends respectively of constituteing vertical tetragonal form, slide bar 3 is circular columnar structure and is four, and symmetric distribution around catapult 6, the upper and lower both ends of slide bar 3 are installed respectively in corresponding end on the transverse guide roof beam 1.
In the design, the ejector 6 is slidably mounted on the sliding rod 3 through a sliding sleeve 32 and guided by the sliding rod 3, the sliding sleeve 32 is slidably sleeved on the sliding rod 3, and the sliding sleeve 31 is fixedly mounted on a mounting plate 61 at the side part of the ejector.
Furthermore, the upper end and the lower end of the sliding rod 3 in the design are respectively connected with a sliding adjusting component, and the sliding rod is arranged on the transverse guide rail beam through the sliding adjusting component and can slide left and right; in the design, a sliding groove 21 is arranged on the side surface of the transverse guide rail beam 2 opposite to the end part of the sliding rod, the sliding adjusting component comprises sliding blocks 12 and 15 fixed at the end part of the sliding rod, two threaded holes 22 are arranged on the sliding block 12, the two threaded holes 22 are positioned above the sliding groove 21 on the transverse guide rail beam, locking bolts are arranged in the threaded holes, and the end parts of the locking bolts extend into the sliding groove; the opening end of the sliding groove is provided with a limiting part 23 which is bent inwards, and a nut is further arranged in the sliding groove. The locking bolt gets into back in the spout with nut threaded connection, just the nut can by spacing portion is spacing, the nut can slide in the spout, through the slider can slide on the transverse guide rail roof beam, through the straightness that hangs down of the adjustable each slide bar of slide adjusting part at slide bar both ends, still include two that will be located the same end of frame the connecting plate 4 that the slider is connected.
Still including install in the iron plate 53 at 6 tops of catapult, the top of frame install can with the absorbent sucking disc magnet subassembly 5 of iron plate, the catapult passes through sucking disc magnet subassembly 5 is unsettled in the frame top with the absorption of iron plate 53, in this design, it sucking disc magnet subassembly 5 includes straight-flow sucking disc electro-magnet 52, transversely installs the backup pad on the frame top crossbeam, straight-flow sucking disc electro-magnet 52 is fixed in go up on the backup pad.
Further, the design is that a buffering base 7 is further arranged at the bottom of the frame below the ejector 6, the buffering base 7 comprises a bottom plate 72 fixed at the bottom of the frame and a plurality of buffers 71 arranged on the bottom plate 72, in this embodiment, the buffers 71 can adopt pneumatic resistance springs, the pneumatic resistance springs are longitudinally fixed on the bottom plate, stress rods of the pneumatic resistance springs are arranged upwards, rubber buffering stress blocks are arranged at the end parts of the stress rods of the pneumatic resistance springs, the pneumatic resistance springs can buffer the ejector 6 falling freely, and in actual use, a plurality of buffers can be arranged or positions among the buffers can be adjusted according to the size and weight of the ejector 6.
The device also comprises a programmable controller 4 which is provided with an electrifying key 41 and a power-off case 42 for realizing electrifying or powering off the direct current type sucker electromagnet 52, wherein the direct current type sucker electromagnet and the ejector are both connected with the programmable controller.
When the testing device for simulating the weightless ejection of the cube star is used, the ejector 6 is firstly moved to the uppermost end of the sliding rod, then the power-on key 41 of the programmable controller 4 is pressed to realize the power-on of the direct current type sucker electromagnet 52, at the moment, the direct current type sucker electromagnet 52 and the iron block 53 are adsorbed together, at the moment, the catapult 6 is adsorbed at the uppermost part of the frame, at the moment, the cube star is positioned in the catapult, then the power-off button 42 of the programmable controller 4 is pressed, at this time, the straight-flow type suction cup electromagnet 52 is powered off, the ejector 6 begins to fall down, after a set time, the programmable controller 4 supplies power to the ejector 6, the inside of the ejector 6 is unlocked according to the internal setting, the cube star stored in the ejector 6 is ejected in the falling process, and the ejector falls onto the buffer base 7 after being ejected, so that the test can be completed after the actions.
The embodiments of the present invention are disclosed as the preferred embodiments, but not limited thereto, and those skilled in the art can easily understand the spirit of the present invention and make various extensions and changes without departing from the spirit of the present invention.
Claims (10)
1. A test device for simulating weightless ejection of a cube star comprises an ejector, a control device and a control device, wherein the ejector can be used for placing the cube star inside and ejecting the cube star; the method is characterized in that: still include the frame of vertical type, install the slide bar in the frame, the catapult pass through sliding sleeve slidable mounting in on the slide bar and pass through slide bar guide whereabouts, still including install in the iron plate at catapult top, the top of frame install can with the absorbent sucking disc magnet subassembly of iron plate, the catapult passes through the sucking disc magnet subassembly is unsettled in the frame top with the absorption of iron plate, through right the outage of sucking disc magnet subassembly is realized accomplishing the free fall of catapult with the iron plate separation.
2. The test device for simulating cubic star weightless ejection according to claim 1, wherein: the side part of the ejector is provided with sliding sleeves in one-to-one correspondence with the sliding rods, the sliding sleeves are slidably sleeved on the sliding rods, and the sliding sleeves are fixedly installed on the installation plate of the side part of the ejector.
3. The test device for simulating cubic star weightless ejection according to claim 1, wherein: the frame comprises four longitudinal guide rail beams forming a vertical square shape and four transverse guide rail beams respectively positioned at two ends of the four longitudinal guide rail beams, and the upper end and the lower end of each sliding rod are respectively arranged on the transverse guide rail beams at the corresponding ends.
4. The test device for simulating cubic star weightless ejection according to claim 1, wherein: the ejector is characterized in that a buffering base is arranged at the bottom of the frame below the ejector, the buffering base comprises a bottom plate fixed to the bottom of the frame and a plurality of buffers arranged on the bottom plate, the buffers can adopt pneumatic resistance springs, the pneumatic resistance springs are longitudinally fixed on the bottom plate, stress rods of the pneumatic resistance springs are upwards arranged, and rubber buffering stress blocks are arranged at the end parts of the stress rods of the pneumatic resistance springs.
5. The test device for simulating cubic star weightless ejection according to claim 4, wherein: the upper end and the lower end of the sliding rod are respectively connected with a sliding adjusting component, and the sliding rod is arranged on the transverse guide rail beam through the sliding adjusting component; a sliding groove is formed in the side face of the transverse guide rail beam opposite to the end part of the sliding rod, the sliding adjusting assembly comprises a sliding block fixed at the end part of the sliding rod, two threaded holes are formed in the sliding block and located above the sliding groove in the transverse guide rail beam, a locking bolt is arranged in each threaded hole, and the end part of each locking bolt extends into the corresponding sliding groove; the opening end of the sliding groove is provided with a limiting part which is bent inwards, and a nut is further arranged in the sliding groove. The locking bolt is connected with the nut in a threaded mode after entering the sliding groove, the nut can be limited by the limiting portion, and the nut can slide in the sliding groove.
6. The test device for simulating cubic star weightless ejection according to claim 5, wherein: the connecting plate is used for connecting the two sliding blocks at the same end.
7. The test device for simulating cubic star weightless ejection according to claim 1, wherein: the sucker magnet assembly comprises a direct-current type sucker electromagnet and an upper supporting plate transversely arranged on a beam at the top of the frame, and the direct-current type sucker electromagnet is fixed on the upper supporting plate.
8. The test device for simulating cubic star weightless ejection according to claim 7, wherein: the direct current type sucker electromagnet and the ejector are connected with the programmable controller.
9. The test device for simulating cubic star weightless ejection according to claim 1, wherein: the slide bar is of a circular columnar structure.
10. The test device for simulating cubic star weightless ejection according to claim 1, wherein: the number of the sliding rods is at least three, and the sliding rods are symmetrically distributed around the ejector.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110757229.XA CN113607391A (en) | 2021-07-05 | 2021-07-05 | Testing device for simulating cubic star weightless ejection |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110757229.XA CN113607391A (en) | 2021-07-05 | 2021-07-05 | Testing device for simulating cubic star weightless ejection |
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| Publication Number | Publication Date |
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| CN113607391A true CN113607391A (en) | 2021-11-05 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110757229.XA Pending CN113607391A (en) | 2021-07-05 | 2021-07-05 | Testing device for simulating cubic star weightless ejection |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH068200U (en) * | 1992-07-10 | 1994-02-01 | 石川島播磨重工業株式会社 | Microgravity experimental apparatus equipped with a cooling furnace |
| CN103847984A (en) * | 2014-02-14 | 2014-06-11 | 上海宇航系统工程研究所 | Test device capable of repeatedly simulating weightless environment |
| CN108382615A (en) * | 2018-04-18 | 2018-08-10 | 上海微小卫星工程中心 | A kind of satellite high-precision payload multiple degrees of freedom microgravity debugging device |
| CN210243497U (en) * | 2019-06-03 | 2020-04-03 | 常州星宇车灯股份有限公司 | Laser remote excitation testing device |
| RU2721448C1 (en) * | 2019-09-16 | 2020-05-19 | Акционерное общество «Информационные спутниковые системы» имени академика М.Ф. Решетнёва» | Rotary device with a block and tackle system for weighlessing open structures of a spacecraft |
| CN211346663U (en) * | 2020-03-24 | 2020-08-25 | 中核四达建设监理有限公司 | Verticality detection device |
-
2021
- 2021-07-05 CN CN202110757229.XA patent/CN113607391A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH068200U (en) * | 1992-07-10 | 1994-02-01 | 石川島播磨重工業株式会社 | Microgravity experimental apparatus equipped with a cooling furnace |
| CN103847984A (en) * | 2014-02-14 | 2014-06-11 | 上海宇航系统工程研究所 | Test device capable of repeatedly simulating weightless environment |
| CN108382615A (en) * | 2018-04-18 | 2018-08-10 | 上海微小卫星工程中心 | A kind of satellite high-precision payload multiple degrees of freedom microgravity debugging device |
| CN210243497U (en) * | 2019-06-03 | 2020-04-03 | 常州星宇车灯股份有限公司 | Laser remote excitation testing device |
| RU2721448C1 (en) * | 2019-09-16 | 2020-05-19 | Акционерное общество «Информационные спутниковые системы» имени академика М.Ф. Решетнёва» | Rotary device with a block and tackle system for weighlessing open structures of a spacecraft |
| CN211346663U (en) * | 2020-03-24 | 2020-08-25 | 中核四达建设监理有限公司 | Verticality detection device |
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