CN105292527B - Simulation separation device of pico satellite and nano satellite - Google Patents
Simulation separation device of pico satellite and nano satellite Download PDFInfo
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- CN105292527B CN105292527B CN201510713862.3A CN201510713862A CN105292527B CN 105292527 B CN105292527 B CN 105292527B CN 201510713862 A CN201510713862 A CN 201510713862A CN 105292527 B CN105292527 B CN 105292527B
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- slide rail
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- 238000000926 separation method Methods 0.000 title abstract description 21
- 238000004088 simulation Methods 0.000 title abstract description 19
- 238000005204 segregation Methods 0.000 claims description 20
- 241001633942 Dais Species 0.000 claims description 11
- 239000007787 solid Substances 0.000 claims 1
- 238000011161 development Methods 0.000 abstract description 6
- 238000000034 method Methods 0.000 description 16
- 238000001612 separation test Methods 0.000 description 8
- 238000010586 diagram Methods 0.000 description 7
- 239000000725 suspension Substances 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 4
- 238000012360 testing method Methods 0.000 description 4
- 108091092878 Microsatellite Proteins 0.000 description 3
- 241000894007 species Species 0.000 description 3
- 241001232809 Chorista Species 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 description 2
- 239000003380 propellant Substances 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000012634 fragment Substances 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 239000011435 rock Substances 0.000 description 1
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- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Bearings For Parts Moving Linearly (AREA)
Abstract
The invention discloses a simulation separation device of a pico satellite and a nano satellite. The simulation separation device comprises two support frames, a sliding rail, a sliding seat, a hanging rope and a fixed tool, wherein the sliding rail is horizontally mounted on the support frames; the sliding seat is matched with the sliding rail; one end of the hanging rope is fixedly connected with the sliding seat; the fixed tool is positioned under the sliding rail and is fixedly connected with the separation bottom plate of the satellite; the other end of the hanging rope is fixedly connected with the satellite, the sliding seat slides to drive the satellite to be separated from the separation bottom plate mounted on the fixed tool in the horizontal direction. According to the simulation separation device disclosed by the invention, a purely mechanical structure is used for fixing and separating a mobile satellite, so that the simulation separation device is simple in structure, convenient to assemble and disassemble and reliable to operate, can adapt to high temperature and low temperature environment, can effectively simulate the separation of the satellite, and is low in development cost.
Description
Technical field
The present invention relates to aviation aircraft simulation isolation technics, more particularly to a kind of skin Nano satellite simulation segregation apparatuss.
Background technology
With the development of microsatellite and space technology, microsatellite satellite and the rocket separate mode, segregation apparatuss species become much
Sample, but the pilot system species that at present suitable moonlet simulation is spatially separating is few, device is complicated, and experimentation cost is high and parameter measurement
Limited precision.Thus the research of microsatellite (skin satellite, Nano satellite) Separation Test Technology is gradually concerned.Satellite is sent out
Sufficient simulation separation test before penetrating, can investigate the performance of piece-rate system and separate reliability, especially for quickly receiving
The Modern Small Satellites of new technique.The separate mode of Modern Small Satellites, segregation apparatuss wide variety, did not much carry out in-orbit flight
Checking, therefore it is extremely necessary to carry out abundant ground separation test.
Either traditional large satellite or Modern Small Satellites, are typically necessary development separation test before transmitting, and at present may be used
Few for the pilot system species that is spatially separating of moonlet simulation, device is complicated, high cost and parameter measurement precision is limited, very great Cheng
The development of Small Satellite Technology is constrained on degree.It is both at home and abroad more to carry out the detached theoretical research of satellite, pays green red grade to divide
Process of Piggyback Satellite from inclement condition is object, and its separation process is studied, and gives that various interference factors are coefficient to disturb
Kinetic moment.Tan Xuefeng etc. carries out numerical simulation using ADAMS software platforms to satellite and the rocket unblock separating dynamics, has investigated blast spiral shell
The impact to band envelope such as bolt impact, limit spring rigidity, band pretightning force.Yao Shidong considers the rolling of satellite tank propellant
This disturbance factor is moved, impact of the propellant sloshing quality to separation attitude is analyzed.Shen Xiaofeng etc. divides for moonlet is eccentric
From problem, simulation analysis are carried out to moonlet separating dynamics based on Multi-body Dynamics Theory.Singaravelu etc. is constructed
The simple horizontal and vertical kinetics equation of satellite and the rocket separation phase, and using Taguchi methods to detached safety and reliability
Property is made that indication.Jeyakumar etc. describes the Coordinate Conversion and the equation of motion of satellite and the rocket separation process, and by Runge-
Kutta methods have obtained the nonlinear ordinary differential equation numerical solution of 12 degree of freedom choristas.Roshanian etc. adopts Monte
The method of Carlo Simulation (MCS), analyzes and causes what chorista collided due to segregation apparatuss disturbance factor
Risk.
Simulation separation test typically wants the interface of simulated target body, and to subjects corresponding pretightning force is applied, it is ensured that dress
The trystate put is as consistent as possible with time of day, also needs to simulate space temperature change and high vacuum environment sometimes.To the greatest extent
Separating property test may be carried out under the conditions of simulation real border, while taking protective measure to issuable fragment.According to
GJB2205-1994, for the checking of separating property, typically there is two methods：Pendulum-type method and freely falling body method.Pendulum-type method is simulated
Separation test can examine whether the work of satellite segregation apparatuss is coordinated and reliable, measure separation parameter and shock response, and check
Satellite withstands shocks the ability of environment, and G.D.PALMER etc. has carried out a series of double pendulum separation tests.The test of freely falling body method
Purpose is similar with pendulum-type method, can the reasonability of verifying satellites separation scheme and separation parameter well quality, Tokyo
Polytechnical university is the performance for verifying moonlet segregation apparatuss, has carried out the free shatter test of moonlet, Shenzhou VII accompanying flying moonlet
Separation test checking, also uses this freely falling body method.
Although can effectively be simulated using the simulation separation method of above-mentioned pendulum-type method and freely falling body method,
Often there is simulator complex structure, the shortcomings of test operation difficulty is big.
The content of the invention
The invention discloses a kind of skin Nano satellite simulates segregation apparatuss, simple structure, easy accessibility is reliable, can fit
Answer high and low temperature environment, can effective analog satellite separation, development cost is low.
A kind of skin Nano satellite simulates segregation apparatuss, including bracing frame, the slide rail being horizontally arranged on support frame as described above, with cunning
The slide that rail coordinates, lanyard and base plate fixation company is separated positioned at slide rail lower section and with satellite that one end is fixedly connected with slide
The fixing tool for connecing, the other end of the lanyard is fixedly connected with satellite and drives satellite by the slip of slide and be arranged on institute
The separation base plate stated on fixing tool is separated in the horizontal direction.
When apparatus of the present invention are installed, slide rail is fixed on bracing frame, is consolidated satellite is fixed on the satellite for separating base plate
Determine in frock, satellite to be connected with lanyard, satellite with separate between base plate after unblock, slide drives drawstring with satellite along cunning
Rail is moved, and the simulation for realizing satellite is separated.
The structure of the horizontal fixed satellite of fixing tool is a lot, can be selected according to the structure for separating base plate.
Apparatus of the present invention simulate satellite and the rocket separation using the method for moving horizontally satellite, and process is simple, easily manipulation, device
Entirety is easy to manufacture and is installed, easy to use, low cost of manufacture.
For stable installation slide rail, it is preferred that support frame as described above is provided with two, and the two ends of the slide rail are separately fixed at two
The top of individual bracing frame.
It is further preferred that each bracing frame includes：Base, the support bar being fixed on base and two are in tilted layout
In the locking pull bar of support bar both sides, the one of one end connect base of the locking pull bar, the other end and support bar connecting sliding rail
End connection.The setting of the locking pull bar can effectively improve the intensity of bracing frame, improve the stability that slide rail and slide coordinate.
Pull bar is locked per root to be included：Be arranged on the pull bar suspension ring at two ends, two sections respectively the pull bar of cylinder lever connecting rod suspension ring and
Connect the check lock lever of two pull bars, the check lock lever is used to adjust the elastic of locking pull bar.
For the ease of adjusting the height of bracing frame, it is preferred that the support bar includes upper support bar, lower support bar and company
Connect the connecting rod of support bar and lower support bar.When higher bracing frame is needed, then using connecting rod connection upper support bar and
Lower support bar, it is also possible to remove connecting rod, two support bars is overlapped and installs to shorten the height of bracing frame.
In order to further strengthen the support strength of bracing frame, while the convenient height for adjusting bracing frame, it is preferred that described
Strut also includes being fixed on the dais that adds on upper support bar top, and one end of the slide rail is fixed on the centre for adding dais top surface.Can
Add dais to remove, the two ends of slide rail are directly anchored to the top of the body of rod, shorten the height of bracing frame.
Said structure install when, first lower support bar is fixed on base, then by connecting rod by upper support bar and under
Support bar is connected, and the top for adding dais to be fixed on upper support bar is separately fixed at pull bar suspension ring on upper support bar and base,
Support bar and base are connected come ruggedized construction with pull bar and check lock lever.
In order to improve the support strength of bracing frame, it is preferred that the support bar also includes being fixed on upper support bar top
Transverse support bar, the both sides of the transverse support bar are connected respectively with two locking pull bars, two locking pull bars, support bar and bottom
The upper bottom edge of the isosceles trapezoid that seat connection is formed and the ratio of bottom are 1:5～1:3.Ratio is too little, and stability is reduced, and ratio is too
Greatly, locking the tightening force adjustment of pull bar easily affects the balance of bracing frame.
Install for convenience, reduce the resistance to sliding of slide, it is preferred that the slide includes being located at the rolling above slide rail
Axle, on roller bearing and with slide rail top surface roll coordinate bearing and positioned at the lower section of slide rail and be connected roller bearing two ends use
In the draw ring of fixed lanyard.When drawstring drives satellite to move, in said structure, bearing is rolled on slide rail, reduces frictional force,
Draw ring is used for connection stay cord, can be semicircle ring structure, and now the two ends of the two ends correspondence connection roller bearing of semicircular ring are formed for sliding
The avoidance hole that rail passes through.
Install for convenience, the roller bearing separated formation first roller bearing and the second roller bearing in, first roller bearing and
The open end of the second roller bearing is separately installed with the bearing.Bearing can be installed in gap, install more convenient.
In order that slide is stably moved, it is preferred that the central shaft of the first roller bearing and the second roller bearing intersects.Said structure makes cunning
Seat is difficult to rock, and stably drives satellite movement.
In order to keep slide stably to move, it is further preferred that the central shaft of the first roller bearing and the second roller bearing is crossed to form
Corner dimension be 120～160 °.
In order to reduce the frictional force between slide rail and slide, while reducing matching requirements, it is preferred that the track and bearing
The top surface of cooperation is arc surface.The structure of arc surface is adapted to first roller bearing and the second roller bearing of different corner dimensions, and with
The contact area of bearing reduces, and reduces frictional resistance.
Beneficial effects of the present invention：
The present invention is fixed and separate mobile satellite by pure mechanic structure, and simple structure, easy accessibility is reliable,
Adapt to high and low temperature environment, can effective analog satellite separation, development cost is low.
Description of the drawings
Fig. 1 is the dimensional structure diagram that the skin Nano satellite of the present invention simulates segregation apparatuss.
Fig. 2 is the structural representation that the skin Nano satellite of the present invention simulates segregation apparatuss.
Fig. 3 is the structural representation of the bracing frame of the present invention.
Fig. 4 is the part-structure schematic diagram of the bracing frame of the present invention.
Fig. 5 is the dimensional structure diagram of Fig. 4.
Fig. 6 is the part-structure schematic diagram of the bracing frame of another kind of connected mode of the present invention.
Fig. 7 is the dimensional structure diagram of Fig. 6.
Fig. 8 is the structural representation of the slide of the present invention.
Fig. 9 is the dimensional structure diagram of the slide of the present invention.
Figure 10 is the dimensional structure diagram of the frock of the present invention.
Specific embodiment
As shown in Fig. 1～10, the skin Nano satellite simulation segregation apparatuss of the present embodiment include：Two bracing frames 1, are horizontally mounted
Slide rail 2 on two bracing frames, the slide 3 coordinated with slide rail 2, lanyard 4 that one end is fixedly connected with slide and positioned at slide rail 2
Lower section and separates the fixing tool 5 that base plate 101 is fixedly connected with satellite 10, separating base plate 101 and vertically fixing makes the edge of satellite 10
Horizontal direction movement is separated, and the two ends of slide rail 2 are separately fixed at the top of two bracing frames 1.
Each bracing frame 1 includes：Base 11, fixed support bar 12 on the pedestal 11 and two are in tilted layout and are supporting
The locking pull bar 13 of the both sides of bar 12.
Pull bar 13 is locked per root to be included：The pull bar suspension ring 131 at two ends are arranged on, two section difference cylinder lever connecting rod suspension ring 131
The check lock lever 133 of two pull bars 132 of pull bar 132 and connection, check lock lever 133 coordinates with the screw thread of pull bar 132, and check lock lever 133 is used for
Adjust the elastic of locking pull bar 12.
Support bar 12 includes the company of upper support bar 121, lower support bar 122, connection upper support bar 121 and lower support bar 122
Extension bar 123, the transverse support bar 125 for being fixed on the top of upper support bar 121 and the rectangle that is fixed in transverse support bar 125
Plus dais 124.One end of slide rail 2 be fixed on plus the top margin of dais 124 centre, lock the connection support bar 13 of pull bar 12 one end with
Transverse support bar 125 connects, and the both sides of transverse support bar 125 are connected respectively with two locking pull bars 13, and two lock pull bars 13, prop up
The upper bottom edge of isosceles trapezoid and the ratio of bottom that strut 12 and the connection of base 11 are formed is 1:4.
Slide 3 includes being located at the roller bearing 31 above slide rail, and the axle for coordinating is rolled on roller bearing 31 and with the top surface of slide rail 2
Hold 32 and positioned at the lower section of slide rail 2 and connect the two ends of roller bearing 31 and be used to fix the draw ring 33 of lanyard 4, in the present embodiment, draw
Ring 33 is semicircle ring structure, and now the two ends of the two ends correspondence connection roller bearing 32 of semicircular ring form the avoidance hole passed through for slide rail 2
34。
In the present embodiment, roller bearing 31 the first roller bearing 311 of separated formation and the second roller bearing 312, the He of the first roller bearing 311 in
The open end of the second roller bearing 312 is separately installed with the central shaft of bearing 32, the first roller bearing 311 and the second roller bearing 312 and intersects, and first
The corner dimension that the central shaft of the roller bearing 312 of roller bearing 311 and second is crossed to form is 130 °.
When the present invention is installed, first lower support bar 122 is fixed on the pedestal 11, then by connecting plate 123 by upper support
Bar 121 is connected, and dais 124 will be added to be fixed in transverse support bar 125, and pull bar suspension ring 131 are separately fixed at into transverse support bar
125 and base 11 on, support bar 12 and base 11 are connected come ruggedized construction with pull bar 132 and check lock lever 133, will be equipped with slide rail
2 two ends be fixed on plus dais 124 on, the separation base plate 101 of satellite 10 is fixed on fixing tool 5, with rope by satellite
10 are connected with the hook of drawstring 4, satellite 10 with separate base plate 101 unlock after, drawstring 4 draws and is moved along slide rail 2 with satellite,
The simulation for realizing satellite is separated.
Wherein, the height adjustable of bracing frame 1, can remove plus dais 124, and the fixed seat of slide rail 2 is directly anchored to support
On bar 12.Connecting rod 123 can also be removed, upper support bar 121 and lower support bar 122 are overlapped into installation, as also shown in e.g. figs. 4-7, weight
Folded length difference can further adjust the length of support bar 12.
Claims (8)
1. a kind of skin Nano satellite simulates segregation apparatuss, it is characterised in that including bracing frame, be horizontally arranged on support frame as described above
Slide rail, the slide coordinated with slide rail, lanyard and separate positioned at slide rail lower section and with satellite that one end is fixedly connected with slide
The fixing tool that base plate is fixedly connected, the other end of the lanyard is fixedly connected with satellite and drives satellite by the slip of slide
Separate in the horizontal direction with base plate is separated on the fixing tool；
Slide includes being located at the roller bearing above slide rail, rolls the bearing of cooperation on roller bearing and with slide rail top surface and is located at
The lower section of slide rail and connect the two ends of roller bearing and be used to fix the draw ring of lanyard；
The roller bearing separated open end point for forming the first roller bearing and the second roller bearing, first roller bearing and the second roller bearing in
The bearing is not installed.
2. skin Nano satellite as claimed in claim 1 simulates segregation apparatuss, it is characterised in that support frame as described above is provided with two, institute
The two ends for stating slide rail are separately fixed at the top of two bracing frames.
3. skin Nano satellite as claimed in claim 2 simulates segregation apparatuss, it is characterised in that each bracing frame includes：It is base, solid
The support bar being scheduled on base and two are in tilted layout in the locking pull bar of support bar both sides, and one end of the locking pull bar connects
Connect one end connection of base, the other end and support bar connecting sliding rail.
4. skin Nano satellite as claimed in claim 3 simulates segregation apparatuss, it is characterised in that the support bar includes upper support
The connecting rod of bar, lower support bar and connection upper support bar and lower support bar.
5. skin Nano satellite as claimed in claim 4 simulates segregation apparatuss, it is characterised in that the support bar also includes being fixed on
The add dais, one end of slide rail on upper support bar top is fixed on the centre for adding dais top surface.
6. skin Nano satellite as claimed in claim 5 simulates segregation apparatuss, it is characterised in that the support bar also includes being fixed on
The transverse support bar on upper support bar top, the both sides of the transverse support bar are connected respectively with two locking pull bars, and two lockings are drawn
It is 1 that bar, support bar and base connect the upper bottom edge of the isosceles trapezoid to be formed and the ratio of bottom:5～1:3.
7. skin Nano satellite as claimed in claim 1 simulates segregation apparatuss, it is characterised in that in the first roller bearing and the second roller bearing
Heart axle intersects.
8. skin Nano satellite as claimed in claim 7 simulates segregation apparatuss, it is characterised in that in the first roller bearing and the second roller bearing
The corner dimension that heart axle is crossed to form is 120～160 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510713862.3A CN105292527B (en) | 2015-10-28 | 2015-10-28 | Simulation separation device of pico satellite and nano satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510713862.3A CN105292527B (en) | 2015-10-28 | 2015-10-28 | Simulation separation device of pico satellite and nano satellite |
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| Publication Number | Publication Date |
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| CN105292527A CN105292527A (en) | 2016-02-03 |
| CN105292527B true CN105292527B (en) | 2017-05-03 |
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| CN201510713862.3A Active CN105292527B (en) | 2015-10-28 | 2015-10-28 | Simulation separation device of pico satellite and nano satellite |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106628273B (en) * | 2016-12-14 | 2018-11-13 | 中国科学院国家空间科学中心 | It is a kind of to be used for the in-orbit clamping and releasing device being separated from each other of principal and subordinate's spacecraft |
| CN109335029B (en) * | 2018-09-30 | 2020-08-07 | 哈尔滨工业大学 | Air-floating type aircraft on-orbit separation ground simulation and test device |
| CN115416881B (en) * | 2022-11-03 | 2023-02-17 | 中国人民解放军战略支援部队航天工程大学 | Multi-rope driving system for multi-body allosteric satellite ground simulator |
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| RU2483991C1 (en) * | 2011-12-08 | 2013-06-10 | Федеральное Государственное Унитарное Предприятие "Государственный научно-производственный ракетно-космический центр "ЦСКБ-Прогресс" (ФГУП "ГНПРКЦ "ЦСКБ-Прогресс") | Bench for opening panels of solar battery |
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| CN103466109A (en) * | 2013-09-05 | 2013-12-25 | 哈尔滨工业大学 | Space microgravity environment ground simulation experiment device |
| CN103600856A (en) * | 2013-11-26 | 2014-02-26 | 北京卫星环境工程研究所 | Spacecraft vertical passive separation test equipment |
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| CN102050230A (en) * | 2010-11-10 | 2011-05-11 | 湖北航天技术研究院总体设计所 | Stage separation test device and method for balancing gravity |
| RU2483991C1 (en) * | 2011-12-08 | 2013-06-10 | Федеральное Государственное Унитарное Предприятие "Государственный научно-производственный ракетно-космический центр "ЦСКБ-Прогресс" (ФГУП "ГНПРКЦ "ЦСКБ-Прогресс") | Bench for opening panels of solar battery |
| CN103308339A (en) * | 2013-06-05 | 2013-09-18 | 北京空间飞行器总体设计部 | Suspension releasing system used for lander stability tests |
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