CN108820266A - A kind of lunar surface takes off initial attitude simulator - Google Patents
A kind of lunar surface takes off initial attitude simulator Download PDFInfo
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- CN108820266A CN108820266A CN201810579332.8A CN201810579332A CN108820266A CN 108820266 A CN108820266 A CN 108820266A CN 201810579332 A CN201810579332 A CN 201810579332A CN 108820266 A CN108820266 A CN 108820266A
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- platform
- angle
- simulator
- lunar surface
- main body
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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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- Aviation & Aerospace Engineering (AREA)
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Abstract
A kind of lunar surface takes off initial attitude simulator, including platform (1), main body supporting structure (2), angle adjusting mechanism (3), lockable mechanism (4), drills through a simulator (5).Platform (1) is in supported underneath detector (6) and is mated with.Main body supporting structure (2) is located at below platform (1), is connect by two groups of hinges with platform (1).Angle adjusting mechanism (3) one end connects main body supporting structure (2), other end connecting platform (1), the angle of platform (1) and horizontal plane is adjusted by hydraulic system driving angle regulating mechanism (3), realizes requirement of the detector initial take-off posture to angle.Lockable mechanism (4) is installed under platform (1).A simulator (5) is drilled through to be installed on platform (1).The present invention can be realized lunar surface within the scope of 0 ° to 25 ° and take off the simulation at many attitude angle, and attitude angle degree of regulation is high and can continuously adjust, and can be used for moonscape sampling and returns to detection.
Description
Technical field
The invention belongs to spacecraft ground simulation test design field, it is related to a kind of lunar surface and takes off initial attitude simulation dress
It sets.
Background technique
Reliably, safely realizing that lunar surface takes off is that lunar orbiter completes the acquisition of moon sample and returns to the basic item of task
Part and a key technology of detector development need to carry out true, adequately full physical verification test on ground.Detection
The posture that device lunar surface takes off is the posture that it initially lands, the shadow designed by lunar surface landform, landing parameter and panel detector structure
It rings, which is the parameter that group changes at random.It takes off in ground validation test in lunar orbiter landing, although by true
Landing link can directly obtain the posture taken off, but which is difficult to simulate extreme takeoff condition, and analog parameter with
Machine is not used to the verifying of accurately knowing the real situation to detector plan boundary.Therefore a kind of lunar surface is developed to take off initial attitude simulation dress
It sets and is in urgent need.
Summary of the invention
The technical problem to be solved by the present invention is in view of the deficiencies of the prior art, lunar surface of the present invention takes off initially
Attitude-simulating device has the continuously adjustable function to directive and attitude angle, take-off attitude that can be different with analog prober,
The take off overall structure mechanical characteristic of initial attitude simulator of lunar surface is consistent with detector, can be simulated true lunar surface and be risen
Fly the support performance in situation, helps to smoothly complete the take off ground validation of link of lunar surface using the device and test.
The technical solution of the invention is as follows：A kind of lunar surface takes off initial attitude simulator, including platform, body supports
Structure, angle adjusting mechanism, lockable mechanism；Main body supporting structure is located at below platform, mesa base side and body supports knot
Structure rotation connection, the mesa base other side and angle adjusting mechanism one end are rotatablely connected；Angle adjusting mechanism other end connection master
Support structure passes through the angle of flexible adjustment platform and horizontal plane；Lockable mechanism is installed under platform, when platform is adjusted to institute
It is required that tilt angle when, lockable mechanism is supported and limits to platform.
It further include drilling through a simulator, drilling through a simulator is cylindrical structure, is mounted on platform side, and simulation is practical
Influence of the cylinder to detector take-off attitude is drilled through under lunar surface takeoff condition, material is 20# carbon structure hot rolled steel plate.
The platform is the platform that channel steel and steel plate weld the frame structure to be formed, and Platform center position is reserved engine and led
Discharge orifice, the positive and negative surface of platform spray thermal protection coating respectively, and provide detector, angle adjusting mechanism, drill through a simulating piece
Interface is installed.
The main body supporting structure is parallel chord truss structure, is connect by two groups of hinges with platform, and main body supporting structure is logical
The adjustment that 4 height-adjustable stabilizer blades that lower section is installed realize platforms with respect to the horizontal plane 0 ° of initial angle is crossed, in main body branch
Antistatic rubber traction is installed at support structure lower frame and is grounded.
Described angle adjusting mechanism one end connects main body supporting structure, and other end connecting platform is driven by hydraulic system
The angle of platform and horizontal plane is adjusted, fireproof asbestos cloth is wrapped up on angle adjusting mechanism surface.
The lockable mechanism includes grip block, latch bracket and latch；Latch bracket is mounted on body supports knot
On the frame of structure upper end, latch bracket is provided with pin shaft limiting slot；Grip block is arc, and one end is mounted on mesa base, grip block
Limit hole is distributed with, limit hole is distributed on the circular arc centered on platform and main structure hinge pin；Latch and limit
Hole, the cooperation of pin shaft limiting slot, when platform around hinge pin shaft rotation run-off the straight angle variation, it is corresponding that latch is inserted into grip block
In the pin shaft limiting slot of limit hole and latch bracket, the locking of angle is realized.
Compared with the prior art, the invention has the advantages that：
1) lunar surface of the present invention takes off initial attitude simulator, passes through and keeps integrally-built mechanical characteristic and visit
It is consistent to survey device, and ground take off keep in verification test taking off initial attitude simulator docked with detector after mechanical interface
And mounting means is consistent with the detector of lunar surface takeoff condition, so as to simulate the attitude angle under the true takeoff condition of lunar surface
Characteristic and support performance.
2) present invention adjusts the angle of platform and horizontal plane by angle adjusting mechanism, can connect within the scope of 0 ° to 25 °
The continuous detector that adjusts takes off initial attitude angle, to realize the simulation to a variety of take-off attitudes of lunar orbiter.
3) present invention uses high-precision tilt angle measurement sensor by hydraulic system driving angle regulating mechanism, hydraulic system
Guarantee that the degree of regulation at lunar orbiter take-off attitude angle is better than 0.5 °, hydraulic system passes through automatic controller and high-precision pressure
Sensor steadily boosted, release, to realize impact of the platform to detector in initial attitude angle adjustment process of taking off
Acceleration is less than 0.6g.
4) platform is limited locking by lockable mechanism by the present invention, is locked at any angle within the scope of 0 ° to 25 ° to realize
Only function, prevent platform adjust take off initial attitude angle to detector after unexpected reset.
5) static bearing capacity under the conditions of 0 ° of initial attitude angle of taking off may be implemented by platform and main structure in the present invention
Greater than 1000kg, it may be implemented to take off initial attitude angle in 0 ° to 25 ° range by platform, main structure and angle adjusting mechanism
Dynamic carrying capacity is greater than 1000kg during inside continuously adjusting.
6) present invention can realize detector with the guiding device for being installed on platform by the engine flow guiding hole of Platform center
The downward row of engine gas stream leads, and can be effective against detector by heat protection design platform and angle adjusting mechanism and start
800 DEG C of high temperature resistant requirement is realized in the ablation of machine combustion gas stream.
Detailed description of the invention
Fig. 1 be lunar surface of the present invention take off initial attitude simulator 0 ° of take-off attitude horn shape state schematic diagram；
Fig. 2 is that lunar surface of the present invention takes off the platform structure schematic diagram of initial attitude simulator；
Fig. 3 is that lunar surface of the present invention takes off the agent structure schematic diagram of initial attitude simulator；
Fig. 4 is that lunar surface of the present invention takes off the angle adjusting mechanism schematic diagram of initial attitude simulator；
Fig. 5 is that lunar surface of the present invention takes off the lockable mechanism schematic diagram of initial attitude simulator；
Fig. 6 be lunar surface of the present invention take off initial attitude simulator drill through the quasi- schematic device of cylinder mould；
Fig. 7 be lunar surface of the present invention take off initial attitude simulator drill through a simulator course of work schematic diagram.
Specific embodiment
It takes off initial attitude simulator below in conjunction with the drawings and specific embodiments to a kind of lunar surface according to the present invention
It is further described in detail.
As shown in Figure 1 for lunar surface of the present invention take off initial attitude simulator 0 ° of take-off attitude horn shape state schematic diagram.
A kind of lunar surface provided by the invention takes off initial attitude simulator, which is characterized in that including platform 1, main body supporting structure 2,
Angle adjusting mechanism 3, drills through a simulator 5 at lockable mechanism 4.A kind of lunar surface takes off outside initial attitude simulator
Shape is having a size of 2650mm × 2650mm × 1181mm.
Fig. 2 is that lunar surface of the present invention takes off 1 structural schematic diagram of platform of initial attitude simulator.The platform 1 is slot
The frame structure that steel and steel plate are welded improves the stiffness and strength of platform, the reserved hair in center using floor stringer, muscle
Motivation deflector hole (diameter of phi 700mm), 1 front and back sides of platform spray burn-out proof, grey thermal protection coating resistant to high temperature, and provide spy
Survey device 6, angle adjusting mechanism 3, the installation interface for drilling through a simulating piece 5, mechanical interface and peace after detector 6 is docked with platform 1
The detector 6 that dress mode is taken off with lunar surface is consistent.1 material of platform preferentially selects the high-quality carbon structure hot rolled steel plate (kind of 20#
Specification GB/T709-1988, technical conditions GB/T711-1988), floor stringer, muscle material selection 20# carbon structure hot-rolled steel channel
(description GB/T707-1988, technical conditions GB/T14292-1993).
Fig. 3 is that lunar surface of the present invention takes off the agent structure schematic diagram of initial attitude simulator.2 conduct of main body supporting structure
The supportive body of 6 engine reverse thrust of detector effect when carrying 6 dead load of detector and taking off is located at 1 lower section of platform, passes through
Two groups of hinges are connect with platform 1, the hinge auricle monaural chip architecture that two groups of hinges are connect with platform 1, and each auricle passes through 8
The bolt of M10 is connect with platform 1；The auricle that two groups of hinges are connect with main body supporting structure 2 uses ears chip architecture, two ears
Piece is connect with 2 cruciform bracing of main body supporting structure by welding.4 height are equipped with below main body supporting structure 2 can
Stabilizer blade is adjusted, can be realized the adjustment of the with respect to the horizontal plane 0 ° of initial angle of platform 1, is pacified at 2 lower frame of main body supporting structure
Equipped with antistatic rubber traction and it is grounded.Main body supporting structure 2 uses steel-pipe welding, the preferred 100mm × 100mm of material × 5mm
Seamless cold steel tubes, the trade mark are 20# carbon constructional quality steel (description GB/T3094-1982, technical conditions GB/
T3094-1982).Hinge lug sheet material preferred 20# carbon constructional quality steel hot rolled circular steel (description GB/T702-1986, skill
Art condition GB/T699-1999).
Fig. 4 is that lunar surface takes off the angle adjusting mechanism schematic diagram of initial attitude simulator.The angle adjusting mechanism 3
One end connects main body supporting structure 2, and other end connecting platform 1 adjusts platform 1 by hydraulic system driving angle regulating mechanism 3
With the angle of horizontal plane, requirement of the 6 initial take-off posture of detector to angle is realized, resistance to height is wrapped up on 3 surface of angle adjusting mechanism
The fireproof asbestos cloth of temperature, burn-out proof.Hydraulic system top rod driving stroke determines by following formula, wherein：L is hydraulic system mandril
Driving trip, H are distance of the hydraulic system mandril upper and lower end connecting pin axis center in vertical direction, and d is hydraulic system mandril
Upper and lower end connecting pin axis center distance in the horizontal direction, D are that platform 1 is arrived with 2 connecting pin axis center of main platform body support construction
Platform 1 connect the distance between pin shaft with hydraulic system mandril upper end, and α is the angle of platform 1 and horizontal plane；
Fig. 5 is 4 schematic diagram of lockable mechanism.Lockable mechanism 4 is installed under platform 1, and lockable mechanism 4 includes grip block 7, stop
Pin bracket 8 and latch 9, latch bracket 8 are mounted on 2 upper end frame of main body supporting structure, and latch bracket 8 is provided with pin shaft
Limiting slot；Grip block 7 is arc, and one end is mounted on 1 bottom of platform, and limit hole is distributed in grip block 7, and limit hole is distributed in flat
On circular arc centered on platform 1 and 2 hinge pin of main structure；Latch 9 and limit hole, pin shaft limiting slot cooperate, when platform 1 around
When hinge pin rotates the variation of run-off the straight angle, latch 9 is inserted into the pin of grip block 7 corresponding limit hole and latch bracket 8
In axis limiting slot, the locking of angle is realized.The lock when angle required by launching platform is adjusted to 6 initial take-off posture of detector
Locking mechanism 4 plays the role of support, limit, prevents lunar surface from taking off initial attitude simulator unexpected reset.7 limit hole of grip block
Diameter is Φ 22mm, and 9 diameter of latch is Φ 20mm, and 8 pin shaft limiting slot diameter of latch bracket is Φ 20.5mm.Latch support
8 pin shaft limiting slot centre distance platform 1 of seat and 2 hinge pin center of main platform body structure are 1000mm.7 limit hole of grip block point
Centered on platform 1 and 2 hinge pin of main platform body structure, radius is on the circumference of 1000mm cloth, installation site according to
The position of latch bracket 8 determines.When 1 angle of platform is zero, 7 zero degree limit hole center of grip block and latch bracket 8
Pin shaft limits groove center and is overlapped.When 1 angle of platform changes, any limit hole center of grip block 7 with latch bracket 8
Pin shaft limits groove center and is overlapped, that is, is able to achieve latch functions at any angle.
Fig. 6 is that the cylinder mould that drills through intends schematic device.A simulator 5 is drilled through to use by the flange and support of bottom
6 M6 bolts are installed on platform 1, are simulated and are drilled through influence of the cylinder to 6 take-off attitude of detector under practical lunar surface takeoff condition.
Drill through the preferred 20# of material high-quality carbon structure hot rolled steel plate (description GB/T709-1988, the technology item of a simulator 5
Part GB/T710-1991), with a thickness of 2mm.
The lunar surface take off initial attitude simulator working principle diagram as shown in fig. 7, the working principle of the invention
For：
Lunar surface takes off, and initial attitude simulator is flexible by hydraulic system driving angle regulating mechanism 3 or withdrawal pushes away
Moving platform 1 is around the rotation of fixed pin shaft, and lockable mechanism 4 is fixed (within the scope of 0 ° to 25 °) after rotation to specified take-off attitude angle
Locking, so realize 6 initial take-off attitude angle of detector simulation, lunar orbiter 6 lunar surface take off initial attitude simulation dress
It sets rising of taking off, completes lunar surface and take off the ground validation test of link.
The present invention can be used for moonscape sampling and return to detection, be applied equally to day outside the ground such as Mars, Venus, asteroid
Body sampling returns to detection.
Unspecified part of the present invention belongs to technology well known to those skilled in the art.
Claims (6)
- The initial attitude simulator 1. a kind of lunar surface takes off, which is characterized in that including platform (1), main body supporting structure (2), angle Spend regulating mechanism (3), lockable mechanism (4)；Main body supporting structure (2) is located at below platform (1), platform (1) bottom side and master Support structure (2) rotation connection, platform (1) the bottom other side and angle adjusting mechanism (3) one end are rotatablely connected；Angular adjustment Mechanism (3) other end connects main body supporting structure (2), passes through the angle of flexible adjustment platform (1) and horizontal plane；Lockable mechanism (4) it is installed under platform (1), when platform (1) is adjusted to required tilt angle, lockable mechanism (4) props up platform Support and limit.
- The initial attitude simulator 2. a kind of lunar surface according to claim 1 takes off, which is characterized in that further include drilling through cylinder Simulator (5), drilling through a simulator (5) is cylindrical structure, is mounted on platform (1) side, simulates practical lunar surface and takes off item Influence of the cylinder to detector (6) take-off attitude is drilled through under part, material is 20# carbon structure hot rolled steel plate.
- The initial attitude simulator 3. a kind of lunar surface according to claim 1 or 2 takes off, it is characterised in that：The platform (1) platform for the frame structure to be formed is welded for channel steel and steel plate, engine flow guiding hole, platform are reserved in platform (1) center (1) positive and negative surface sprays thermal protection coating respectively, and provides detector (6), angle adjusting mechanism (3), drills through a simulating piece (5) Installation interface.
- The initial attitude simulator 4. a kind of lunar surface according to claim 3 takes off, which is characterized in that the body supports Structure (2) is parallel chord truss structure, is connect by two groups of hinges with platform (1), main body supporting structure (2) is installed by lower section 4 height-adjustable stabilizer blades realize the adjustment of platform (1) with respect to the horizontal plane 0 ° of initial angle, in main body supporting structure (2) Antistatic rubber traction is installed at lower frame and is grounded.
- The initial attitude simulator 5. a kind of lunar surface according to claim 4 takes off, which is characterized in that the angular adjustment Mechanism (3) one end connects main body supporting structure (2), other end connecting platform (1), drives adjustment platform (1) by hydraulic system With the angle of horizontal plane, fireproof asbestos cloth is wrapped up on angle adjusting mechanism (3) surface.
- The initial attitude simulator 6. a kind of lunar surface according to claim 1 or 2 takes off, which is characterized in that the locking Mechanism (4) includes grip block (7), latch bracket (8) and latch (9)；Latch bracket (8) is mounted on main body supporting structure (2) on the frame of upper end, latch bracket (8) is provided with pin shaft limiting slot；Grip block (7) is arc, and one end is mounted on platform (1) bottom Limit hole is distributed in portion, grip block (7), and limit hole is distributed in the circle centered on platform (1) and main structure (2) hinge pin On arc；Latch (9) and limit hole, pin shaft limiting slot cooperate, when platform (1) around hinge pin shaft rotation run-off the straight angle variation When, latch (9) is inserted into the pin shaft limiting slot of grip block (7) corresponding limit hole and latch bracket (8), realizes angle Locking.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810579332.8A CN108820266B (en) | 2018-06-07 | 2018-06-07 | Lunar surface takeoff initial attitude simulation device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810579332.8A CN108820266B (en) | 2018-06-07 | 2018-06-07 | Lunar surface takeoff initial attitude simulation device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108820266A true CN108820266A (en) | 2018-11-16 |
| CN108820266B CN108820266B (en) | 2021-03-26 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810579332.8A Active CN108820266B (en) | 2018-06-07 | 2018-06-07 | Lunar surface takeoff initial attitude simulation device |
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| CN (1) | CN108820266B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109633194A (en) * | 2018-12-17 | 2019-04-16 | 北京卫星制造厂有限公司 | A kind of low gravitation sample container transmission accuracy test system and method |
| CN112903330A (en) * | 2021-02-25 | 2021-06-04 | 北京空间飞行器总体设计部 | Method for verifying stable takeoff of spacecraft on lunar surface |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103605372A (en) * | 2013-08-19 | 2014-02-26 | 北京卫星环境工程研究所 | Inclination angle automatic adjustment platform for thermal test under vacuum low-temperature environment |
| CN203798533U (en) * | 2014-03-24 | 2014-08-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Angle-adjustable balance plate device |
| US9141113B1 (en) * | 2012-04-26 | 2015-09-22 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Probabilistic surface characterization for safe landing hazard detection and avoidance (HDA) |
| CN106628280A (en) * | 2016-11-23 | 2017-05-10 | 南京航空航天大学 | Soft landing simulation experimental device and simulation method for Spacecraft |
-
2018
- 2018-06-07 CN CN201810579332.8A patent/CN108820266B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9141113B1 (en) * | 2012-04-26 | 2015-09-22 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Probabilistic surface characterization for safe landing hazard detection and avoidance (HDA) |
| CN103605372A (en) * | 2013-08-19 | 2014-02-26 | 北京卫星环境工程研究所 | Inclination angle automatic adjustment platform for thermal test under vacuum low-temperature environment |
| CN203798533U (en) * | 2014-03-24 | 2014-08-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Angle-adjustable balance plate device |
| CN106628280A (en) * | 2016-11-23 | 2017-05-10 | 南京航空航天大学 | Soft landing simulation experimental device and simulation method for Spacecraft |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109633194A (en) * | 2018-12-17 | 2019-04-16 | 北京卫星制造厂有限公司 | A kind of low gravitation sample container transmission accuracy test system and method |
| CN112903330A (en) * | 2021-02-25 | 2021-06-04 | 北京空间飞行器总体设计部 | Method for verifying stable takeoff of spacecraft on lunar surface |
| CN112903330B (en) * | 2021-02-25 | 2022-07-01 | 北京空间飞行器总体设计部 | Method for verifying stable takeoff of spacecraft on lunar surface |
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