CN106275523B - The rotatable infrared heating cage of venetian blind type - Google Patents
The rotatable infrared heating cage of venetian blind type Download PDFInfo
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- CN106275523B CN106275523B CN201510318950.3A CN201510318950A CN106275523B CN 106275523 B CN106275523 B CN 106275523B CN 201510318950 A CN201510318950 A CN 201510318950A CN 106275523 B CN106275523 B CN 106275523B
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- infrared
- cage
- infrared heating
- heating unit
- connecting rod
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Abstract
The invention discloses a kind of infrared cage of shutter rotary window for spacecraft thermal vacuum test process, mainly include infrared cage main frame, reducing motor, shaft coupling, connecting rod and bearing pin, heating component, bearing and bearing block and angular transducer, the motor mount of reducing motor is set on the side of main frame, the output shaft of reducing motor on motor mount is coaxially connected by yielding coupling and one of infrared heating unit, some infrared heating units are connected by connecting rod in parallel and fixed respectively by bearing pin, after connecting rod in parallel and bearing pin and some heating units are combined, all heating units just form parallel institution, in the presence of connecting rod in parallel, synchronous axial system.When simulating low temperature environment, heating unit is rotated by driver element, heating tape is turned over 90 ° of angles, make the vertical spacecraft surface of heating zone face, reduce heating tape to block spacecraft, improve area of the spacecraft relative to heat sink radiation, improve the rate of temperature fall of spacecraft.
Description
Technical field
The invention belongs to spacecraft ground heat test technical field, and in particular to spacecraft heat under a kind of vacuum low-temperature environment
The turnable infrared heat flow simulation system of experiment.
Background technology
Spacecraft in face of spacecraft on ground before transmission, it is necessary to carry out space environment simulated test, to verify spacecraft
Reliability in orbit, wherein vacuum thermal test are the important rings in spacecraft environment experiment.In thermal vacuum environment experiment,
Infrared cage is a kind of effective Orbital heat flux simulation meanses, and infrared cage is typically located at 100mm-200mm on the outside of spacecraft, its shape
Typically change with the external envelope of spacecraft.
Infrared cage is typically made up of tape and skeleton, and skeleton arranges that tape presses certain spacing by the external envelope of spacecraft
Uniformly it is arranged on infrared cage skeleton, infrared cage tape organizes the formation of heating circuit by certain, by outside cable and container
Power supply connection, during experiment by give infrared cage power up, the Orbital heat flux that Simulated Spacecraft undergoes during in orbit.
The problem of existing during existing infrared cage use：
The infrared cage used at present during spacecraft thermal vacuum test be all it is fixed, i.e.,：The skeleton of infrared cage is all
It is welded with bar section of stainless steel, tape is fixed on skeleton by polytetrafluoro sheet material, and the state of tape and skeleton is once installed
Complete, just can not change again.In vacuum thermal test, infrared cage is arranged on spacecraft surface, forms the outside bag of a closing
Network, because tape has certain width, with certain coverage rate（0.1~0.5）Spacecraft surface is enclosed in, this part tape
Presence blocked spacecraft and it is heat sink between radiation heat transfer, especially under worst cold case, had a strong impact on the drop of spacecraft
Warm speed, extend the spacecraft testing time.
The content of the invention
Use, can make red during spacecraft thermal vacuum test the technical problem to be solved in the present invention is to provide a kind of
Outer cage tape（Tape group）The infrared cage rotated as blade of louver window, the infrared cage in closed condition, play with it is existing
Infrared cage identical function, but in the case of opening, infrared cage can be reduced spacecraft surface is blocked, increase spacecraft
With heat sink heat exchange area, accelerate the cooling of spacecraft, shorten the test period.
The purpose of the present invention is achieved by the following technical solution：
For the infrared cage of shutter rotary window of spacecraft thermal vacuum test process, mainly including infrared cage main frame,
Reducing motor, shaft coupling, connecting rod and bearing pin, heating component, bearing and bearing block and angular transducer, the side of above-mentioned main frame
The upper motor mount for setting reducing motor, heating component are made up of some infrared heating units, and some infrared heating units are equal
It is even to be arranged in above-mentioned main frame, the axis of each infrared heating unit and the axis keeping parallelism of other infrared heating units and
Coplanar, each infrared heating unit is fixed on the rolling bearing in infrared cage main frame, rolling bearing support by both ends short axle
On bearing block, the output shaft of the reducing motor on motor mount passes through yielding coupling and one of infrared heating unit
Coaxially connected, some infrared heating units are connected by connecting rod in parallel and fixed respectively by bearing pin, when connecting rod in parallel and bearing pin
After being combined with some infrared heating units, all infrared heating units just form parallel institution, in connecting rod in parallel
Under effect, synchronous axial system.
Wherein, the shoulder of some infrared heating units is threaded hole, and bearing pin is threadedly secured to infrared heating unit
Shoulder, be provided with connecting rod in parallel with some equidistant pin-and-holes of infrared heating unit, pin-and-hole is with bearing pin using gap cooperation.
Wherein, above-mentioned main frame is the square bearer being welded by four angle steel, is set on the left and right angle steel of square bearer
Symmetrical infrared heating unit mounting hole at equal intervals, mounting hole is interior to set rolling bearing.
Wherein, any infrared heating unit not being connected with reducing motor, its side short axle and angle are connected using shaft coupling
The input shaft spent on sensor, angular transducer are arranged on infrared cage main frame.
Wherein, temperature measure and control system carries out closed-loop control to the temperature of reducing motor, reducing motor is in work
Make in temperature range.
Wherein, reducing motor is made up of stepper motor and turbine and worm decelerator.
Wherein, the infrared cage of venetian blind type controls infrared heating unit corner, infrared heating list by the way of closed-loop control
The corner of member is gathered in real time by angular transducer, and the corner value collected feeds back to the control outside environmental simulation container
System, control system judge whether the actual rotational angle of infrared heating unit reaches setting value.
Wherein, all control signals, heating plate power supply and motor power by penetrating cable outside environmental simulation container
Introduce, penetrating cable is made up of tank outer cable and tank inner cable, and both are connected by the sealing plug positioned at tank skin.
Wherein, motor mount sets heat insulating mattress with above-mentioned main frame side.
In order to adapt to the environment of vacuum and low temperature in container, using the temperature control mode of thermocouple+heating plate：In motor and worm screw
Thermocouple and heating plate are pasted on the shell of decelerator, and is incubated in the multilayer module of 10 units of external sheath.Pass through
Thermocouple is acquired to the actual temperature of motor and worm reducer, and motor and worm reducer are led by heating plate
Dynamic temperature control, makes their temperature remain near room temperature.
When simulating low temperature environment, reducing motor is driven by driver element, makes 90 ° of infrared heating finite element rotation, makes heating
The vertical spacecraft surface of zone face, because heating tape thickness only has 0.1mm, therefore heating tape can be largely reduced to heat sink
Block, strengthen spacecraft test specimen and it is heat sink between radiation heat transfer, accelerate the temperature-fall period of spacecraft, on the one hand can reduce
Test period, save experimentation cost；On the other hand spacecraft can be made to reach lower temperature section, play original infrared cage not
It can achieve the effect that, for the model of survey of deep space, can more accurately simulate the depth of survey of deep space model
Cold environment, the examination to spacecraft are more abundant.
Brief description of the drawings
Fig. 1 is the front view of the infrared cage of venetian blind type of the present invention.
Wherein, 1:Reducing motor；3:Infrared heating unit 5:Infrared cage main frame；
Fig. 2 is the side view of the infrared cage of venetian blind type of the present invention.
Wherein, 1:Reducing motor 3:Infrared heating unit 4:Connecting rod 5:Infrared cage main frame 6:Bearing block；
Fig. 3 is the A-A views of the infrared cage of venetian blind type in Fig. 1.
Wherein, 1:Reducing motor；2:Shaft coupling；3:Infrared heating unit；5:Infrared cage main frame；6:Bearing block；7:Axle
Hold；8:Bearing (ball) cover； 9:Motor mount；10:Heat insulating mattress.
Fig. 4 is the B-B views of the infrared cage of venetian blind type in Fig. 2.
Wherein, 4:Connecting rod 11:Bearing pin.
Fig. 5 is the infrared cage C-C views of venetian blind type in Fig. 1.
Wherein, 12:Angular transducer.
Embodiment
Introduced below is the embodiment as content of the present invention, below by embodiment to this
The content of invention is made further to illustrate.Certainly, it is only the not Tongfang of the example present invention to describe following detailed description
The content in face, and should not be construed as limiting the scope of the invention.
Referring to Fig. 1, Fig. 1-2 is respectively the front view and side view of the infrared cage of venetian blind type of the present invention.The use of the present invention
In the infrared cage of shutter rotary window of spacecraft thermal vacuum test process, mainly including infrared cage main frame 5, reducing motor 1,
Shaft coupling 2, connecting rod 4 and bearing pin 11, heating component, bearing 7 and bearing block 6 and angular transducer 12, the side of infrared cage main frame 5
The motor mount 9 of reducing motor 1 is set on face, and motor mount sets heat insulating mattress with main frame side.Heating component by
Some infrared heating units 3 are formed, and some infrared heating units 3 are evenly arranged in infrared cage main frame 5, each infrared heating
The axis keeping parallelism of the axis of unit 3 and other infrared heating units 3 and coplanar, each infrared heating unit 3 passes through both ends
Short axle is fixed on the rolling bearing 7 in infrared cage main frame 5, and rolling bearing 7 is supported on bearing block 6 and entered by bearing (ball) cover 8
Row compresses, and the output shaft of the reducing motor 1 on motor mount 9 passes through yielding coupling 2 and one of infrared heating unit 3
Coaxially connected, some infrared heating units 3 are connected by connecting rod 4 in parallel and fixed respectively by bearing pin 11, when connecting rod 4 in parallel with
After bearing pin and some infrared heating units 3 are combined, all infrared heating units just form parallel institution, in parallel connection even
In the presence of bar 4, synchronous axial system.
In one embodiment, the shoulder of some infrared heating units 3 is threaded hole, and bearing pin is threadedly secured to red
The shoulder of additional hot cell, it is provided with connecting rod in parallel and is adopted with some equidistant pin-and-holes of infrared heating unit, pin-and-hole with bearing pin
Coordinated with gap.Infrared cage main frame 5 is the square bearer being welded by four angle steel, is set on the left and right angle steel of square bearer
Symmetrical infrared heating unit mounting hole at equal intervals, mounting hole is interior to set rolling bearing.
Referring to Fig. 3, Fig. 3 is the A-A views of the infrared cage of venetian blind type in Fig. 1.Wherein, reducing motor 1 by stepper motor and
Turbine and worm decelerator is formed, and reducing motor 1 is arranged on electric machine stand 9, is connected using shaft coupling 2 with infrared heating unit 3,
Reducing motor driving infrared heating unit 3, infrared heating unit 3 be used as driving link, drives remaining infrared to add by connecting rod 4 in parallel
Hot cell is synchronized with the movement, and ensures the uniformity of all infrared heating unit motions；
Referring to Fig. 4, Fig. 4 is the B-B views of the infrared cage of venetian blind type in Fig. 2.Wherein, parallel institution is by the He of connecting rod 4 in parallel
Bearing pin 11 forms, and the shoulder design screwed hole of infrared heating unit 3, bearing pin 11 is threadedly secured in infrared heating list by front portion
The shoulder of member 3, be designed with connecting rod 4 in parallel with the equidistant pin-and-hole of infrared heating unit, pin-and-hole and bearing pin using gap cooperation,
After connecting rod 4 in parallel and bearing pin 11 and all infrared heating units 3 are combined, all heating units and connecting rod are with regard to shape
Into a parallel institution, all infrared heating units in this mechanism are synchronized with the movement in the presence of connecting rod 4.
Wherein, all control signals, heating plate power supply and motor power by penetrating cable outside environmental simulation container
Introduce, penetrating cable is made up of tank outer cable and tank inner cable, and both are connected by the sealing plug positioned at tank skin.
Extreme pressure grease is taken to substitute the common lubricant fat in reducing motor, both having played prevents common grease volatilization to vacuum
Container pollutes, and and can ensures the lubrication to motor.
Temperature control is carried out to reducing motor 1 by the way of heating plate+thermocouple combines, thermocouple and heating plate are attached to deceleration
On the shell of motor 1, maintained a certain distance between thermocouple and heating plate, then using the multilayer insulation component of 10 units
Reducing motor is coated, blocks motor and heat sink radiation heat transfer.In use, using special temperature measure and control system
Unite and closed-loop control is carried out to the temperature of reducing motor, ensure that reducing motor is in operating temperature range.
The infrared cage of venetian blind type controls the corner of infrared heating unit 3 by the way of closed-loop control, infrared heating unit 3
Corner is gathered in real time by angular transducer 12, and the corner value collected feeds back to the control meter outside environmental simulation container
Whether calculation machine, the actual rotational angle for judging infrared heating unit 3 by control computer reach setting value.The installation of angular transducer 12
Mode is identical with reducing motor 1（Referring to Fig. 5）.
Although giving detailed description and explanation to the embodiment of the present invention above, it should be noted that
Those skilled in the art can carry out various equivalent changes and modification, its institute to above-mentioned embodiment according to the spirit of the present invention
Caused function, all should be within the scope of the present invention in the spirit covered without departing from specification and accompanying drawing.
Claims (8)
1. for spacecraft thermal vacuum test process the infrared cage of shutter rotary window, mainly including infrared cage main frame, subtract
Speed motor, shaft coupling, connecting rod and bearing pin, heating component, bearing and bearing block and angular transducer, on the side of the main frame
The motor mount of reducing motor is set, and heating component is made up of some infrared heating units, and some infrared heating units are uniform
It is arranged in the main frame, the axis of each infrared heating unit and the axis keeping parallelism of other heating units and coplanar,
Each infrared heating unit is fixed on the rolling bearing in infrared cage main frame by both ends short axle, and rolling bearing is supported on axle
In bearing, the output shaft of the reducing motor on motor mount is coaxial by yielding coupling and one of infrared heating unit
Connection, some infrared heating units are connected by connecting rod in parallel and are fixed respectively by bearing pin, if when connecting rod in parallel and bearing pin and
After dry heating unit is combined, all heating units just form parallel institution, synchronous to turn in the presence of connecting rod in parallel
It is dynamic.
2. the infrared cage of shutter rotary window as claimed in claim 1, wherein, the shoulder of some infrared heating units sets spiral shell
Pit, bearing pin are threadedly secured to the shoulder of infrared heating unit, be provided with connecting rod in parallel between some heating units etc.
Away from pin-and-hole, pin-and-hole and bearing pin are using gap cooperation.
3. the infrared cage of shutter rotary window as claimed in claim 1, wherein, the main frame be by four angle steel welding and
Into square bearer, symmetrical infrared heating unit mounting hole at equal intervals is set on the left and right angle steel of square bearer, in mounting hole
Rolling bearing is set.
4. the infrared cage of shutter rotary window as described in claim any one of 1-3, wherein, what is be not connected with reducing motor appoints
One infrared heating unit, its side short axle and the input shaft on angular transducer are connected using shaft coupling, angular transducer is set
On infrared cage main frame.
5. the infrared cage of shutter rotary window as described in claim any one of 1-3, wherein, temperature measure and control system pair
The temperature of reducing motor carries out closed-loop control, reducing motor is in operating temperature range.
6. the infrared cage of shutter rotary window as described in claim any one of 1-3, wherein, reducing motor by stepper motor and
Turbine and worm decelerator forms.
7. the infrared cage of shutter rotary window as described in claim any one of 1-3, wherein, the infrared cage of venetian blind type, which uses, to be closed
The mode of ring control controls infrared heating unit corner, and the corner of infrared heating unit is gathered in real time by angular transducer,
The corner value collected feeds back to the control system outside environmental simulation container, and control system judges the reality of infrared heating unit
Whether border corner reaches setting value.
8. the infrared cage of shutter rotary window as described in claim any one of 1-3, wherein, motor mount and the main frame
Frame side sets heat insulating mattress.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510318950.3A CN106275523B (en) | 2015-06-11 | 2015-06-11 | The rotatable infrared heating cage of venetian blind type |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510318950.3A CN106275523B (en) | 2015-06-11 | 2015-06-11 | The rotatable infrared heating cage of venetian blind type |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106275523A CN106275523A (en) | 2017-01-04 |
| CN106275523B true CN106275523B (en) | 2018-03-27 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510318950.3A Expired - Fee Related CN106275523B (en) | 2015-06-11 | 2015-06-11 | The rotatable infrared heating cage of venetian blind type |
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| CN (1) | CN106275523B (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107310756A (en) * | 2017-05-26 | 2017-11-03 | 航天东方红卫星有限公司 | A kind of infrared cage of skin Nano satellite hot-fluid |
| CN109018456B (en) * | 2018-06-28 | 2020-07-14 | 上海卫星工程研究所 | Thermal vacuum test external heat flow simulation method of high-orbit remote sensing satellite platform |
| CN109398768B (en) * | 2018-10-23 | 2020-02-18 | 北京卫星环境工程研究所 | Super-large infrared heat flow simulation device suitable for space station cabin level spacecraft |
| CN109803461A (en) * | 2019-03-08 | 2019-05-24 | 天津赛金节能科技股份有限公司 | A kind of multi-faceted far-infrared heater |
| CN111483624B (en) * | 2020-03-09 | 2022-04-19 | 航天科工空间工程发展有限公司 | Heating cage for satellite thermal test |
| CN111942622B (en) * | 2020-07-02 | 2021-12-14 | 航天科工空间工程发展有限公司 | Infrared heating cage |
| CN112357133A (en) * | 2020-11-18 | 2021-02-12 | 北京卫星环境工程研究所 | Testing system for large-scale space structure thermal dynamic response characteristics |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000211599A (en) * | 1999-01-22 | 2000-08-02 | Mitsubishi Electric Corp | Thermal louver |
| CN201173440Y (en) * | 2007-12-04 | 2008-12-31 | 北京卫星环境工程研究所 | Single lamp for spacecraft vacuum heat test and infrared lamp array constituted by same |
| CN201293721Y (en) * | 2008-11-17 | 2009-08-19 | 北京卫星环境工程研究所 | Infrared heating cage for spacecraft vacuum heat test |
| CN102435099B (en) * | 2011-09-30 | 2013-07-17 | 北京航空航天大学 | High-temperature radiation temperature enhancement device of quartz lamp used for guided missile thermal test |
| CN102963545B (en) * | 2012-11-06 | 2015-11-18 | 上海卫星装备研究所 | Infrared lamp arrays heating system |
| CN103163173B (en) * | 2013-03-15 | 2015-07-15 | 北京航空航天大学 | Inner-wall non-sectional type high-temperature thermal test device of large high-speed aircraft round-shell structure |
| CN103600851B (en) * | 2013-11-22 | 2016-07-06 | 北京卫星环境工程研究所 | Spacecraft thermal vacuum test high heat flux simulation device |
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- 2015-06-11 CN CN201510318950.3A patent/CN106275523B/en not_active Expired - Fee Related
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Granted publication date: 20180327 Termination date: 20210611 |