CN108168878A - Spatial rotational mechanism floor synthetic verification test system based on the moment of reaction - Google Patents
Spatial rotational mechanism floor synthetic verification test system based on the moment of reaction Download PDFInfo
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- CN108168878A CN108168878A CN201711344669.2A CN201711344669A CN108168878A CN 108168878 A CN108168878 A CN 108168878A CN 201711344669 A CN201711344669 A CN 201711344669A CN 108168878 A CN108168878 A CN 108168878A
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention discloses a kind of spatial rotational mechanism floor synthetic verification test system based on the moment of reaction, including empty set system, cryogenic system, temperature control system, turret systems and fixture system；Wherein, vacuum system mainly includes vacuum tank, low vacuum system, high vacuum system, and turret systems are single axle table system or three axis table system；Fixture system is made of docking trolley, heater element fixing tool, product fixed tooling.The configuration of the present invention is simple is moved easily, installs, debugs and fixes, and is easily manipulated, it is possible to provide vacuum+high temperature/low temperature/temperature change+moment of reaction combined stress experimental enviroment.
Description
Technical field
The invention belongs to spacecraft reliability strenuous test technical field, in particular it relates to which a kind of space turns
Motivation structure floor synthetic verification test system.
Background technology
In space technology field, spacecraft generally works in two or more environment with the rotating mechanism in-orbit military service stage should
In the coupling environment that power acts on simultaneously, such as vacuum+high temperature, vacuum+low temperature, vacuum+temperature change.Especially for inside
Containing rotating mechanism while there is higher pointing accuracy requirement or the space flight electronic product of torque output characteristics (such as momenttum wheel, control
Moment gyro processed etc.), during spacecraft attitude adjusts, also subject to the motor-driven anti-work being applied on product of satellite posture adjustment
Use torque.Therefore, this kind of product is comprehensive often in the multi-environment stress of vacuum+high temperature/low temperature/temperature change+moment of reaction
Under cooperation is used.But in terms of current ground environment experiment, due to the missing of test complex, normally only in vacuum thermal test
Tolerance of such product to vacuum+high temperature/low temperature/temperature change environmental stress coupling is examined in equipment, it temporarily can not
The pilot system of applying vacuum+high temperature/low temperature/temperature change+moment of reaction synthetic chemistry laboratory simultaneously.Existing research knot
Fruit is it has been shown that influence of the moment of reaction factor to above-mentioned electronic product performance cannot be ignored.And American army mark 810 and national military standard
150A is explicitly pointed out：" combined environment test may can more represent actual environment effect than a series of continuous single tests.Make
It during with encountering these conditions in environment, encourages to carry out combined environment test ".It is contemplated that in the new stage of space flight development, instrument
Equipment will be more complicated and advanced, and the sensibility of environment will further enhance, and more stress resultant action effects are to product task
The influence of reliability will be highlighted further.For the demand adapted to this development, space product is avoided to be examined during experiment
It is insufficient, it is impossible to abundant exposing product design and manufacturing defect, it is highly desirable develop it is a set of can carry out vacuum+high temperature/low temperature/
The pilot system of temperature change+moment of reaction synthetic chemistry laboratory Combined Loading.
Invention content
Based on this, the purpose of the present invention is to provide one kind can carry out vacuum+high temperature/low temperature/temperature change+reaction
The device of torque synthetic chemistry laboratory Combined Loading, for carrying out the examination of the ground validation of the space flight electronic product containing rotating mechanism
It tests.
The present invention is achieved through the following technical solutions：
Spatial rotational mechanism floor synthetic verification test system based on the moment of reaction, for vacuum+high temperature+reaction
The compbined test environment of torque, low temperature+temperature change+moment of reaction, including：Vacuum system, cryogenic system, temperature control system,
Turret systems and fixture system；
Wherein, vacuum system mainly includes vacuum tank, low vacuum system, high vacuum system, and vacuum tank is used to form
Confined space, low vacuum system are used to the air pressure in vacuum tank being down to 3Pa levels；High vacuum system is used for vacuum tank
Interior air pressure is down to by 3Pa levels better than 1.33 × 10-3Pa is horizontal；
Cryogenic system mainly includes Dewar container for liquefied nitrogen, heat sink, associated ping and valve, and Dewar container for liquefied nitrogen is mainly used for depositing for liquid nitrogen
Storage, associated ping by Dewar container for liquefied nitrogen and it is heat sink connect, by the open and close of valve control piper, by liquid nitrogen from Dewar container for liquefied nitrogen
It is introduced into heat sink；Heat sink close vacuum tank inner surface arrangement, forms " liner " of approximate closing, is pipeline+web structure,
When there is liquid nitrogen in heat sink interior flowing, simulation space low temperature environment is provided for tested products；
Turret systems are single axle table system or three axis table system；
Wherein, fixture system is made of docking trolley, heater element fixing tool, product fixed tooling；Docking trolley is set
It puts on the guide rail in vacuum tank, the immobilizing foundation as remaining equipment in vacuum tank, convenient for inside and outside in vacuum tank
It is mobile；Turret systems are bolted on docking trolley, and product fixed tooling is arranged on the turntable table top of turret systems,
And connect with tested products, ensure that tested products are fixed on specific posture on turntable；Heater element fixing tool is fixed on
It docks on trolley, and is connect with heater element, for heater element to be fixed on to the designated position around tested products.
Further, equipped with flange on vacuum tank, for the inside and outside electric signal transmission of container；Subordinate in vacuum tank
Side is equipped with guide rail, for the carrying and movement of tested products.
Wherein, product fixed tooling is arranged on by being spirally connected on turntable table top.
Wherein, temperature control system is mainly by heater element, temperature transducer, measurement cable, crossing cabin plug group, control signal wire
Cable, temperature controller, heating power supply, heating cable composition；Heater element is fixed on tested products week by heater element fixing tool
It encloses, temperature transducer is arranged on product surface by bonding way, to measure product temperature, temperature transducer and vacuum tank
Interior measurement cable connection, and the crossing cabin plug group of vacuum tank flange is corresponding with container external pelivimetry cable to be connected by being arranged on
It connects, container external pelivimetry cable access temperature controller, so as to which the measuring signal of temperature transducer is passed to temperature controller.
Further, temperature controller generates control signal according to the measuring signal of temperature transducer, and through control signal wire cable
Incoming heating power supply makes heating power supply generate certain DC current and voltage output, and successively by container external heat cable,
Heating cable reaches heater element in crossing cabin plug group and container, and heater element is made to be powered, so as to the low temperature in vacuum tank
To product surface output radiation hot-fluid under environment, change product surface temperature, so as to change the measuring signal of temperature transducer；Control
The control signal of Wen Yi adjusts in real time with the measuring signal of temperature transducer, so as to fulfill loop cooling control.
Further, heat sink inner surface spraying is pitch-dark, and Surface absorption rate is better than 0.9, the shape on the basis of low temperature environment
Into cold darkness environment.
Preferably, dry pump or mechanical pump can be used in low vacuum system；
Preferably, cryogenic pump or molecular pump can be used in high vacuum system；
Preferably, vacuum tank is made of stainless steel, is Horizontal cylinder body；
Preferably, it is heat sink to be made of brass material；
Preferably, liquid nitrogen pipeline external application sets thermal insulation material, is scattered and disappeared with reducing heat when liquid nitrogen flows in pipeline；
Preferably, heater element can be the combination of infrared cage, infrared lamp or both；Infrared cage is preferably cylindric, cylinder
Top surface heating zone and side heat area can realize to be controlled respectively, and carries stainless steel plate to improve Uniformity of Temperature Field；
Preferably, temperature transducer can be T-shaped thermoelectricity occasionally platinum resistance；
Preferably, docking trolley is made of stainless steel, the wheel rim with protrusion on the inside of car wheel, convenient for holding in vacuum
Guide rail upper limit in device；
Preferably, product mounting tooling is made of aluminum alloy materials.
The present invention has following advantageous effect：
(1) it is simple in structure：A kind of spatial rotational mechanism floor synthetic verification test based on the moment of reaction of the present invention
System is without being excessively transformed existing vacuum environment analog machine, and the testing equipment in vacuum tank is installed in pair
It connects on trolley, is moved easily, installs, debugs and fixes.
(2) it is easily manipulated：A kind of spatial rotational mechanism floor synthetic verification test based on the moment of reaction of the present invention
In system, vacuum system, cryogenic system, temperature control system and turret systems are separately controlled, and are facilitated and are carried out different tests magnitude
The combination loading of the environmental stress such as lower vacuum+high temperature/low temperature/temperature change+moment of reaction, is easy to carry out setting for test matrix
Meter and implementation.
(3) vacuum+high temperature/low temperature/temperature change+moment of reaction combined stress experimental enviroment can be provided：It is different from biography
The vacuum thermal test system of system, a kind of floor synthetic verification test system of spatial rotational mechanism based on the moment of reaction of the invention
System is a kind of test simulation that can be carried out vacuum, high temperature/low temperature/temperature change, moment of reaction combinational environment and couple loading
Device, available for space flight electronic product of the examination containing spatial rotational mechanism to the tolerance of above-mentioned integrated environment.
Description of the drawings
Fig. 1 is the present invention for the outer of the spatial rotational mechanism floor synthetic verification test system based on the moment of reaction
Profile view.
Fig. 2 is the spatial rotational mechanism floor synthetic verification test system vacuum container based on the moment of reaction of the present invention
Interior composition view.
Wherein：1 liquid nitrogen storage tank；2 liquid nitrogen blowdown pipings；3 high thresholds；4 flanges；5 crossing cabin plug groups；6 single axle tables are controlled out of my cabin
Cable processed；7 temperature sensor signals transmission cable out of my cabin；8 heater elements power cable out of my cabin；9 vacuum tanks；10 temperature controllers；
11 power supplys；12 single axle table switch boards；13 liquid nitrogen inlet pipes；14 liquid nitrogen liquid feed valves；15 liquid nitrogen pressure charging valves；16 liquid nitrogen gasifications
Device；17 liquid nitrogen pressure pipings；18 roughing pumps；19 roughing lines；20 roughing valve doors；21 high-vacuum pumps (cryogenic pump)；22 experiments
Part tooling；23 testpieces；24 temperature transducers；25 heater elements (infrared cage)；Transmission cable in 26 temperature sensor signal cabins；
Power cable in 27 heater element cabins；Controlling cable in 28 single axle table cabins；29 guide rails；30 docking trolleies；31 single axle tables；32
Heater element tooling；33 is heat sink.
Specific embodiment
Below in conjunction with attached drawing to the floor synthetic verification test system of spatial rotational mechanism based on the moment of reaction of the present invention
System is described in detail, the merely illustrative purpose of specific embodiment, it is no intended to limit the scope of the invention.
With reference to Fig. 1-2, Fig. 1-2 respectively illustrates the spatial rotational mechanism floor synthetic based on the moment of reaction of the present invention
Composition view in the outline view and vacuum tank of verification test system.Display could be aware that with reference to the accompanying drawings, of the invention
Spatial rotational mechanism floor synthetic verification test system based on the moment of reaction includes liquid nitrogen storage tank 1；Liquid nitrogen blowdown piping 2；
High threshold 3；Flange 4；Crossing cabin plug group 5；Single axle table controlling cable 6 out of my cabin；Temperature sensor signal transmission cable 7 out of my cabin；Add
Thermal device power cable 8 out of my cabin；Vacuum tank 9；Temperature controller 10；Power supply 11；Single axle table switch board 12；Liquid nitrogen inlet pipe
13；Liquid nitrogen liquid feed valve 14；Liquid nitrogen pressure charging valve 15；Liquid nitrogen converter 16；Liquid nitrogen pressure piping 17；Roughing pump 18；Roughing line
19；Roughing valve door 20；High-vacuum pump (cryogenic pump) 21；Testpieces tooling 22；Testpieces 23；Temperature transducer 24；Heater element
(infrared cage) 25；Transmission cable 26 in temperature sensor signal cabin；Power cable 27 in heater element cabin；The internal control of single axle table cabin
Cable 28 processed；Guide rail 29；Dock trolley 30；Single axle table 31；Heater element tooling 32；Heat sink 33.
In one embodiment, the spatial rotational mechanism floor synthetic verification test system of the invention based on the moment of reaction
The liquid nitrogen storage tank 1 of system is mounted on by pre-buried ground on the ground in Special test place, and vacuum tank 9 is installed by foundation bolt
On the ground in Special test place.Liquid nitrogen blowdown piping 2 is screwed onto by flange on heat sink 33 liquid outlet, high threshold 3 and method
Orchid 4 is mounted on by being spirally connected on vacuum tank 9, and crossing cabin plug group 5 is fixed on by being spirally connected on flange 4.Single axle table is controlled out of my cabin
6 one end of cable processed is welded on the plug out of my cabin of crossing cabin plug group 5, and the other end passes through connector and single axle table switch board 12
Connection；7 one end of transmission cable is welded on the plug out of my cabin of crossing cabin plug group 5 temperature sensor signal out of my cabin, and the other end passes through
Screw crimping form is connect with temperature controller 10；8 one end of power cable is welded on inserting out of my cabin for crossing cabin plug group 5 to heater element out of my cabin
On head, the other end crimps form by screw and is connect with power supply 11；Temperature controller 10 and power supply 11, which are bolted, to be fixed on specially
With on cabinet, which is placed in using castor on the ground on 9 side of vacuum tank；Single axle table switch board 12 is placed using castor
On the ground on 9 side of vacuum tank；13 one end of liquid nitrogen inlet pipe is screwed onto by flange on the liquid outlet of liquid nitrogen storage tank 1, separately
One end is screwed onto by flange on heat sink 33 inlet；Liquid nitrogen liquid feed valve 14 is screwed onto in liquid nitrogen inlet pipe 13；Liquid nitrogen increases
Pressure valve 15 is screwed onto on liquid nitrogen pressure piping 17；Liquid nitrogen converter 16 is connected to the ground on 1 side of liquid nitrogen storage tank by foundation bolt
On face, and pass through to be spirally connected and be connected with liquid nitrogen pressure piping 17；It is two sections that liquid nitrogen pressure piping 17, which is divided to, and one end of first segment passes through method
Orchid is screwed onto on the pressurized outlet of liquid nitrogen storage tank 1, and the other end is by being spirally connected on the entrance for being connected to liquid nitrogen converter 16, second segment
One end by being spirally connected in the outlet for being connected to liquid nitrogen converter 16, the other end is screwed onto the supercharging of liquid nitrogen storage tank 1 by flange
On entrance；Roughing pump 18 is placed in using pedestal on the ground on 9 side of vacuum tank, and it is two sections that roughing line 19, which is divided to, first segment
One end be screwed onto by flange on the air entry of roughing pump 18, before the other end is screwed onto roughing valve door 20 by flange
End, one end of second segment are screwed onto the rear end of roughing valve door 20 by flange, and the other end is screwed onto vacuum tank 9 by flange
Just take out on mouth；High-vacuum pump (cryogenic pump) 21 is mounted on by being spirally connected in high threshold 3；Testpieces tooling 22 is fixed on list by being spirally connected
On the table top of shaft rotation platform 31；Testpieces 23 is fixed on particular pose in testpieces tooling 22 by being spirally connected；Temperature transducer 24
Pass through the designated position being adhesively fixed on testpieces 23；Heater element (infrared cage) 25 is fixed on heater element work by being spirally connected
It fills on 32；26 one end of transmission cable is welded on the cabin female connector of crossing cabin plug group 5 in temperature sensor signal cabin, and the other end leads to
It crosses to be spirally connected and be connect with temperature transducer 24；27 one end of power cable is welded on the cabin interpolation of crossing cabin plug group 5 in heater element cabin
On head, the other end is welded in the input line of heater element (infrared cage) 25；28 one end of controlling cable passes through in single axle table cabin
Connector is connect with single axle table 31, and the other end is welded on the cabin female connector of crossing cabin plug group 5；Guide rail 29 is a pair two
Root is fixed on by being spirally connected on vacuum tank 9；Docking trolley 30 is placed in using wheel on guide rail 29, with convex on the inside of wheel
The wheel rim risen is stuck on the inside of guide rail, prevents trolley from derailing or turning on one's side in moving process；Single axle table 31 and heater element tooling
32, which are utilized respectively bolt, is fixed on docking trolley 30；Heat sink 33 are fixed on using bolt and docking auricle in vacuum tank 9.
The use process of the spatial rotational mechanism floor synthetic verification test system based on the moment of reaction of the present invention is such as
Under：
In the case of forming enclosure space in the closing of 9 gate of vacuum tank, container, initial suction valve door 20 and low vacuum are opened
Pump 18 forms underbalance effect using turbo blade high-speed rotating in roughing pump, the air in vacuum tank 9 is taken out outward
Go out, pressure in vacuum tank is made to reach the level better than 3Pa.At this point, closing initial suction valve door 20 and roughing pump 18, Gao Zhen is opened
Sky pump (cryogenic pump) 21 and high threshold 3, using cold head component of the temperature in cryogenic pump less than 10K to remaining gas in vacuum tank 9
Body molecule carries out absorption capture, and the pressure in vacuum tank 9 is made to reach 10-2Pa is horizontal.On this basis, liquid nitrogen pressure charging valve is opened
15, liquid nitrogen in liquid nitrogen storage tank 1 is made to flow into liquid nitrogen converter 16 through liquid nitrogen pressure piping 17, in liquid nitrogen converter 16 by with
The abundant exchanging air of outside air turns to nitrogen, and pressure itself increases, and the top of liquid nitrogen storage tank 1 is flowed back to through liquid nitrogen pressure piping 17
Portion is reached for the purpose being pressurized in liquid nitrogen storage tank 1.At this point, open liquid nitrogen liquid feed valve 14, the liquid nitrogen after supercharging in liquid nitrogen storage tank 1
Heat sink 33 are flowed into through liquid nitrogen inlet pipe 13 under pressure, through liquid nitrogen blow-down pipe after fully being flowed in heat sink 33 pipeline
The gasification discharge of road 2 so as to be reached for heat sink 33 cooling, establishes the purpose of low temperature cold background in vacuum tank 9；Meanwhile temperature
The heat sink gas molecule in vacuum tank 9 less than 100K also has certain suction-operated, can make in vacuum tank
Pressure reaches better than 1.33 × 10-3The level of Pa；On the other hand, the heat sink inner surface in face of product sprays pitch-dark, and surface is inhaled
Yield is better than 0.9, so as to set up complete vacuum environment and cold black background environment in vacuum tank 9.
In vacuum and cold black background environment, the temperature of 23 specific location of testpieces is measured using temperature transducer 24
Value, measuring signal transmission cable 26, crossing cabin plug group 5 and temperature sensor signal in temperature sensor signal cabin transmit out of my cabin
The signal path that cable 7 forms is passed to temperature controller 10, and temperature controller compares the measured value of temperature and given desired value, passes through
Generation control signal is passed to power supply 11 after crossing calculating, power supply 11 is made to generate certain DC current and voltage output, and successively logical
Cross the heater element complete signal access that power cable 27 is formed in power cable 8, crossing cabin plug group 5 and heater element cabin out of my cabin
Heater element (infrared cage) 25 is reached, heater element (infrared cage) 25 is made to be powered, so as to the cold black background ring in vacuum tank
Specific radiant heat flux is exported to 23 surface of testpieces under border, changes 23 surface temperature of testpieces, so as to change temperature transducer
24 measuring signal；The control signal of temperature controller 10 adjusts in real time with the measuring signal of temperature transducer 24, so as to fulfill closed loop
Temperature control makes the temperature of testpieces 23 realize that heating, cooling or temperature are kept according to given temperature value and Cooling rate, so as to for
Testpieces 23 provides high temperature, low temperature or temperature change environmental load.
In vacuum and cold black background environment, single axle table switch board 12 is according to given rotating speed and rotational angle instruction production
Raw control signal, controlling cable 28 is formed in single axle table out of my cabin controlling cable 6, crossing cabin plug group 5 and single axle table cabin
Complete signal access is passed to single axle table 31, makes single axle table according to given angular speed and angular turn, and pass through on table top
The testpieces tooling 22 of connection drives testpieces 23 to rotate, motor-driven so as to the posture adjustment of analog satellite platform.Due to testpieces 23 certainly
Body has certain angular-momentum vector, when single axle table 31 is rotated with certain angular speed, can change the angular motion of testpieces 23
Direction vector is measured, so as to apply the moment of reaction load of given size on testpieces 23.
The control of above-mentioned vacuum environment load, temperature loading and moment of reaction load is mutual indepedent, and can apply simultaneously,
Can be that testpieces 23 provides vacuum+high temperature/low temperature/temperature change+moment of reaction combined stress experimental enviroment, available for examining
Space flight electronic product containing spatial rotational mechanism is to the tolerance of above-mentioned integrated environment.
The test capability of the spatial rotational mechanism floor synthetic verification test system based on the moment of reaction of the present invention：Ring
Border pressure (vacuum degree)：Better than 1.33 × 10-3Pa, cold-scarce scape heat sink temperature：Better than 100K, heat sink background surface absorptivity：It is excellent
In 0.9, testpieces maximum heating ability：Better than 120 DEG C, testpieces maximum cooling capacity：Better than -120 DEG C, testpieces is maximum anti-
Opplied moment load：Better than 200Nm.
Although the specific embodiment of the present invention is described in detail and is illustrated above, it should be noted that
We can make various changes and modifications the above embodiment, but these spirit without departure from the present invention and appended power
The recorded range of profit requirement.
Claims (13)
1. the spatial rotational mechanism floor synthetic verification test system based on the moment of reaction, for vacuum+high temperature+reaction force
The compbined test environment of square, low temperature+temperature change+moment of reaction, including：Vacuum system, temperature control system, turns cryogenic system
Platform system and fixture system；
Wherein, vacuum system mainly includes vacuum tank, low vacuum system, high vacuum system, and vacuum tank is used to form closed
Space, low vacuum system are used to the air pressure in vacuum tank being down to 3Pa levels；High vacuum system is used for will be in vacuum tank
Air pressure is down to by 3Pa levels better than 1.33 × 10-3Pa is horizontal；
Cryogenic system mainly includes Dewar container for liquefied nitrogen, heat sink, associated ping and valve, and Dewar container for liquefied nitrogen is mainly used for the storage of liquid nitrogen,
Associated ping by Dewar container for liquefied nitrogen and it is heat sink connect, by the open and close of valve control piper, liquid nitrogen is introduced from Dewar container for liquefied nitrogen
To heat sink；Heat sink close vacuum tank inner surface arrangement forms " liner " of approximate closing, is pipeline+web structure, when having
Liquid nitrogen provides simulation space low temperature environment in heat sink interior flowing, for tested products；
Turret systems are single axle table system or three axis table system；
Wherein, fixture system is made of docking trolley, heater element fixing tool, product fixed tooling；Docking trolley is arranged on
On guide rail in vacuum tank, the immobilizing foundation as remaining equipment in vacuum tank, convenient in the inside and outside shifting of vacuum tank
It is dynamic；Turret systems are bolted on docking trolley, and product fixed tooling is arranged on the turntable table top of turret systems, and
It is connect with tested products, ensures that tested products are fixed on specific posture on turntable；Heater element fixing tool is fixed on pair
It connects on trolley, and is connect with heater element, for heater element to be fixed on to the designated position around tested products.
2. the spatial rotational mechanism floor synthetic verification test system based on the moment of reaction as described in claim 1, wherein,
Equipped with flange on vacuum tank, for the inside and outside electric signal transmission of container；Vacuum tank inner lower be equipped with guide rail, for by
The carrying and movement of trial product.
3. the spatial rotational mechanism floor synthetic verification test system based on the moment of reaction as described in claim 1, wherein,
Product fixed tooling is arranged on by being spirally connected on turntable table top.
4. the spatial rotational mechanism floor synthetic verification test system based on the moment of reaction as described in claim 1, wherein,
Temperature control system mainly by heater element, temperature transducer, measure cable, crossing cabin plug group, control signal wire cable, temperature controller, plus
Thermoelectric generator, heating cable composition；Heater element is fixed on by heater element fixing tool around tested products, temperature transducer
Product surface is arranged on by bonding way, to measure product temperature, temperature transducer connects with measuring cable in vacuum tank
It connects, and the crossing cabin plug group by being arranged on vacuum tank flange is correspondingly connected with container external pelivimetry cable, container external pelivimetry
Cable accesses temperature controller, so as to which the measuring signal of temperature transducer is passed to temperature controller.
5. the spatial rotational mechanism floor synthetic verification test system based on the moment of reaction as claimed in claim 4, wherein,
Temperature controller generates control signal according to the measuring signal of temperature transducer, and is passed to heating power supply through control signal wire cable, makes to add
Thermoelectric generator generates certain DC current and voltage output, and successively passes through container external heat cable, crossing cabin plug group and container
Interior heating cable reaches heater element, and heater element is made to be powered, thus to product surface under the low temperature environment in vacuum tank
Output radiation hot-fluid changes product surface temperature, so as to change the measuring signal of temperature transducer；The control signal of temperature controller with
The measuring signal of temperature transducer adjusts in real time, so as to fulfill loop cooling control.
6. such as spatial rotational mechanism floor synthetic verification test system of the claim 1-5 any one of them based on the moment of reaction
System, wherein, heat sink inner surface spraying is pitch-dark, and Surface absorption rate is better than 0.9, and cold black ring is formed on the basis of low temperature environment
Border.
7. such as spatial rotational mechanism floor synthetic verification test system of the claim 1-5 any one of them based on the moment of reaction
System, wherein, low vacuum system uses dry pump or mechanical pump；Cryogenic pump or molecular pump can be used in high vacuum system.
8. such as spatial rotational mechanism floor synthetic verification test system of the claim 1-5 any one of them based on the moment of reaction
System, wherein, vacuum tank is made of stainless steel, is Horizontal cylinder body.
9. such as spatial rotational mechanism floor synthetic verification test system of the claim 1-5 any one of them based on the moment of reaction
System, wherein, it is heat sink to be made of brass material.
10. such as spatial rotational mechanism floor synthetic verification test of the claim 1-5 any one of them based on the moment of reaction
System, wherein, the external application of liquid nitrogen pipeline sets thermal insulation material, is scattered and disappeared with reducing heat when liquid nitrogen flows in pipeline.
11. such as spatial rotational mechanism floor synthetic verification test of the claim 1-5 any one of them based on the moment of reaction
System, wherein, heater element is the combination of infrared cage, infrared lamp or both.
12. the spatial rotational mechanism floor synthetic verification test system based on the moment of reaction as claimed in claim 11,
In, infrared cage is cylindric, and cylinder top surface heating zone and side heat area realize and control respectively, and carries stainless steel plate to carry
High-temperature field uniformity.
13. such as spatial rotational mechanism floor synthetic verification test of the claim 1-5 any one of them based on the moment of reaction
System, wherein, docking trolley is made of stainless steel, the wheel rim with protrusion on the inside of car wheel, convenient in vacuum tank
Guide rail upper limit.
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| CN109269528A (en) * | 2018-09-17 | 2019-01-25 | 北京卫星环境工程研究所 | Spatial rotational mechanism floor synthetic verification experimental verification method based on the moment of reaction |
| CN109799421A (en) * | 2019-03-12 | 2019-05-24 | 北京卫星环境工程研究所 | The combined environment test of aerospace optical connector studies system |
| CN110646315A (en) * | 2019-10-08 | 2020-01-03 | 北京卫星环境工程研究所 | Wide-temperature-zone rapid temperature impact test system for product based on liquid nitrogen immersion deep space detection |
| CN112284783A (en) * | 2020-10-20 | 2021-01-29 | 北京卫星环境工程研究所 | Temperature gradient simulation test device and method for aerospace optical fiber cabin penetrating assembly |
| CN113532855A (en) * | 2021-07-23 | 2021-10-22 | 北京卫星环境工程研究所 | Ground comprehensive test system for verifying joint life of aerospace mechanical arm |
| CN113776824A (en) * | 2021-09-15 | 2021-12-10 | 北京卫星环境工程研究所 | High-precision dynamic micro friction torque testing system applied to space environment test |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102890006A (en) * | 2012-10-24 | 2013-01-23 | 上海交通大学 | High/low temperature space environment simulating container with high temperature change rate |
| CN103318427A (en) * | 2013-06-25 | 2013-09-25 | 上海宇航***工程研究所 | Space environment simulation testing system |
| CN103343884A (en) * | 2013-06-19 | 2013-10-09 | 北京航空航天大学 | Liquid helium conveying system used for large-size multi-section liquid helium heat sinks and class converting method for large-size multi-section liquid helium heat sinks |
| CN103600851A (en) * | 2013-11-22 | 2014-02-26 | 北京卫星环境工程研究所 | High heat flow simulator for spacecraft vacuum heat tests |
| CN103675084A (en) * | 2013-11-27 | 2014-03-26 | 北京航空航天大学 | System and method for measuring plume multi-component space distribution in vacuum low-temperature environment |
| CN204107552U (en) * | 2014-09-19 | 2015-01-21 | 常熟市虞华真空设备科技有限公司 | Vacuum test case complete set of equipments |
| CN205426491U (en) * | 2015-12-04 | 2016-08-03 | 深圳市特种设备安全检验研究院 | Relief valve cold test system |
| CN107215488A (en) * | 2017-05-24 | 2017-09-29 | 北京空间技术研制试验中心 | A kind of manned spacecraft repairs ground total factor simulation system out of my cabin |
-
2017
- 2017-12-15 CN CN201711344669.2A patent/CN108168878A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102890006A (en) * | 2012-10-24 | 2013-01-23 | 上海交通大学 | High/low temperature space environment simulating container with high temperature change rate |
| CN103343884A (en) * | 2013-06-19 | 2013-10-09 | 北京航空航天大学 | Liquid helium conveying system used for large-size multi-section liquid helium heat sinks and class converting method for large-size multi-section liquid helium heat sinks |
| CN103318427A (en) * | 2013-06-25 | 2013-09-25 | 上海宇航***工程研究所 | Space environment simulation testing system |
| CN103600851A (en) * | 2013-11-22 | 2014-02-26 | 北京卫星环境工程研究所 | High heat flow simulator for spacecraft vacuum heat tests |
| CN103675084A (en) * | 2013-11-27 | 2014-03-26 | 北京航空航天大学 | System and method for measuring plume multi-component space distribution in vacuum low-temperature environment |
| CN204107552U (en) * | 2014-09-19 | 2015-01-21 | 常熟市虞华真空设备科技有限公司 | Vacuum test case complete set of equipments |
| CN205426491U (en) * | 2015-12-04 | 2016-08-03 | 深圳市特种设备安全检验研究院 | Relief valve cold test system |
| CN107215488A (en) * | 2017-05-24 | 2017-09-29 | 北京空间技术研制试验中心 | A kind of manned spacecraft repairs ground total factor simulation system out of my cabin |
Non-Patent Citations (7)
| Title |
|---|
| 刘立杰 等: "ZM3000 光学遥感器空间环境模拟试验设备研制", 《低温与超导》 * |
| 周原 等: "航天产品在真空热试验环境下的振动采集技术研究", 《中国力学大会-2017 暨庆祝中国力学学会成立 60 周年大会论文集(A)》 * |
| 姚非: "航天器姿态控制***仿真平台的研究", 《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》 * |
| 彭皓: "卫星运动模拟器的结构设计与分析", 《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》 * |
| 林来兴: "卫星研制过程中运用工程仿真提高产品质量", 《航天控制》 * |
| 邓庆东: "飞行仿真三轴转台的静动力学分析", 《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》 * |
| 陈凯 等: "半实物仿真中三轴转台姿态运动相似性研究", 《机械科学与技术》 * |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109269528A (en) * | 2018-09-17 | 2019-01-25 | 北京卫星环境工程研究所 | Spatial rotational mechanism floor synthetic verification experimental verification method based on the moment of reaction |
| CN109799421A (en) * | 2019-03-12 | 2019-05-24 | 北京卫星环境工程研究所 | The combined environment test of aerospace optical connector studies system |
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| CN112284783A (en) * | 2020-10-20 | 2021-01-29 | 北京卫星环境工程研究所 | Temperature gradient simulation test device and method for aerospace optical fiber cabin penetrating assembly |
| CN112284783B (en) * | 2020-10-20 | 2023-03-14 | 北京卫星环境工程研究所 | Temperature gradient simulation test device and method for aerospace optical fiber cabin penetrating assembly |
| CN113532855A (en) * | 2021-07-23 | 2021-10-22 | 北京卫星环境工程研究所 | Ground comprehensive test system for verifying joint life of aerospace mechanical arm |
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