CN102778154B - Small-temperature-difference efficient heat exchange device for movable assembly of space optical remote sensor - Google Patents
Small-temperature-difference efficient heat exchange device for movable assembly of space optical remote sensor Download PDFInfo
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- CN102778154B CN102778154B CN2012102514551A CN201210251455A CN102778154B CN 102778154 B CN102778154 B CN 102778154B CN 2012102514551 A CN2012102514551 A CN 2012102514551A CN 201210251455 A CN201210251455 A CN 201210251455A CN 102778154 B CN102778154 B CN 102778154B
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Abstract
The invention discloses a small-temperature-difference efficient heat exchange device for a movable assembly of a space optical remote sensor, belongs to the field of aviation and aerospace, and relates to an efficient heat exchange device for a movable focal plane assembly of a movable assembly of a space optical remote sensor. The small-temperature-difference efficient heat exchange device solves problems of low heat exchange speed and heat exchange efficiency, high temperature difference and the like when heat exchange is carried out between a movable assembly and the outside of the movable assembly in a radiation mode or by the aid of a heat conduction rope, and the like. The small-temperature-difference efficient heat exchange device for the movable assembly of the space optical remote sensor comprises a substrate, a heat sink, a movable focal plane assembly, an oscillating shaft, a flexible heat tube and a power gear train. Heat exchange capacity of movable components inside the space optical remote sensor is improved by two efficient heat transfer modes including a heat conduction mode and a heat transfer mode by the aid of the heat tube, the temperature difference between a cold end and a hot end is reduced, temperature control capacity is improved, and efficient heat exchange of the movable focal plane assembly and the heat sink or other mechanisms in external environments is realized.
Description
Technical field
The invention belongs to aerospace field, relate to the movable focal plane subassembly high-efficiency heat exchanger of space optical remote sensor movable component.
Background technology
Movable component is indispensable assembly in a lot of space optical remote sensors, the important part of the movable focal plane subassembly of such as focus adjusting mechanism, hot topic etc., especially space optical remote sensor.Due to movable component space vacuum environment of living in, electronics device self on movable focal plane subassembly has again larger heating, make structural member on movable component or the temperature of electronic device not meet the demands, therefore require movable component and near fixing structural member or heat sinkly carry out efficient heat exchange.And because the residing special vacuum environment of space optical remote sensor and ground installation have a great difference, most situations can't be used the heat convection mode to carry out heat exchange as ground installation.And the activity characteristic of movable part can't simply be used the metal highly heat-conductive material, make the movable component of space optical remote sensor inside and the heat exchange of external environment become a difficult problem, the high-power electronic device on especially movable focal plane subassembly.At present, domestic heat exchange to the movable focal plane subassembly in space optical remote sensor adopts the modes such as direct radiation heat transfer or employing heat conduction rope to carry out the heat exchange between movable part and fixture mostly.These two kinds of methods are because its specific heat transfer boundary condition requires to make exchange capability of heat poor (being generally a watt level), and the temperature difference is shortcomings such as (generally wanting tens degrees centigrade of even tens degrees centigrade of temperature difference) greatly.Radiation heat transfer for example, its heat exchange amount is directly proportional to the biquadratic of temperature is poor, is directly proportional to area of dissipation.And for the movable part of space optical remote sensor, especially with the movable focal plane subassembly of focusing and bias mechanism, often complex structure, can't install the radiating surface that provides enough.Therefore when demand heat exchange amount was large and pass through radiation heat transfer, the temperature difference was larger.Adopt heat conduction rope thermal resistance larger, cause the cold junction of heat exchange and warm end temperature difference large, thermal diffusion is slow.Simultaneously, the kinetic characteristic of movable focal plane subassembly, metal material and the general heat pipe that can't use common height to lead.Therefore, efficient little temperature difference heat exchange is extremely important for the heat radiation of the movable focal plane subassembly in space optical remote sensor, especially even more important to the large power consumption electronic device of the exigent movable focal plane subassembly of temperature conditions.
Summary of the invention
In order to overcome, existingly by modes such as radiation or heat conduction ropes, to carry out the problems such as the mode heat transfer rate of movable component and heat exchange with outside is slow, the temperature difference is large and make the heat endurance of part movable component in space optical remote sensor or the electronics device operating temperature range on movable component be difficult to guarantee, and then may cause hydraulic performance decline or the function limitation of space optical remote sensor.The objective of the invention is to solve the technical problem of movable component and external environment high efficient heat exchanging, make electronics device and external environment on movable component or movable component keep high efficient heat exchanging, thereby make the controlled member temperature within the temperature range of design, make the thermal characteristics on movable component more stable, especially on the impact on performance of the thermal change of the optical detector on the focal plane subassembly that takes in sail, also can make and high-power optical detection device is installed becomes possibility on the movable focal plane subassembly of space optical remote sensor.
The technical problem to be solved in the present invention is: the little temperature difference high-efficiency heat exchanger that a kind of space optical remote sensor movable component is provided.The technical scheme of technical solution problem comprises substrate, it is characterized in that, this heat-exchanger rig also comprises flexible heat pipe, power gear group, heat sink, movable focal plane subassembly and swinging axle; One end of flexible heat pipe is that flexible heat pipe stiff end, the other end are that flexible heat pipe movable end, middle part are the flexible heat pipe bellows segment; Flexible heat pipe stiff end and heat sink being connected; Flexible heat pipe movable end and movable focal plane subassembly are connected; Movable focal plane subassembly is arranged on swinging axle, can relatively rotate with swinging axle; Movable focal plane subassembly is by fan-shaped gear ring and the engagement of power gear group; Heat sink and swinging axle is arranged on substrate respectively.
Operation principle of the present invention is: movable focal plane subassembly according to mission requirements under the drive of power gear group, requirement according to appointment is done oscillating motion around swinging axle, by the flexible heat pipe bellows segment, bears the relative motion of flexible heat pipe stiff end and flexible heat pipe movable end; Simultaneously, the heat that high power device on movable focal plane subassembly produces conducts by movable focal plane subassembly and passes to the flexible heat pipe movable end or directly by high power device itself, directly pass to the flexible heat pipe movable end by heat, and heat passes to the flexible heat pipe stiff end via the flexible heat pipe bellows segment; By the flexible heat pipe stiff end, contact heat passes in the mechanism of heat sink or other external environment with the mechanism of heat sink or other external environment again.
The invention has the beneficial effects as follows: owing on whole bang path, only having heat conduction and heat pipe heat to transmit two kinds of efficient thermaltransmission modes, make more than exchange capability of heat reaches 20W, the temperature difference between the mechanism of movable focal plane subassembly and heat sink or other external environment is less than 6 ℃; Therefore, the present invention has stronger exchange capability of heat to the movable part of space optical remote sensor inside, the less cool and heat ends temperature difference, and temperature control capacity, realized the High Efficiency Thermal exchange of the mechanism of movable focal plane subassembly and heat sink or other external environment faster.
The accompanying drawing explanation
Fig. 1 is the little temperature difference high-efficiency heat exchanger schematic diagram of a kind of space optical remote sensor movable component of the present invention;
Fig. 2 is the left view of Fig. 1;
The specific embodiment
The present invention presses Fig. 1, structure shown in Figure 2 is implemented, and the little temperature difference high-efficiency heat exchanger of a kind of space optical remote sensor movable component of the present invention comprises movable focal plane subassembly 4, power gear group 5, flexible heat pipe, heat sink 6, swinging axle 7, substrate 8; One end of flexible heat pipe is that flexible heat pipe stiff end 1, the other end are that flexible heat pipe movable end 3, middle part are flexible heat pipe bellows segment 2; Flexible heat pipe stiff end 1 is connected with heat sink 6; Flexible heat pipe movable end 3 is connected with movable focal plane subassembly 4; Movable focal plane subassembly 4 is arranged on swinging axle 7, can relatively rotate with swinging axle 7; Movable focal plane subassembly 4 is by fan-shaped gear ring and 5 engagements of power gear group; Heat sink 6 and swinging axle 7 be arranged on respectively on substrate 8.
Wherein flexible heat pipe stiff end 1 adopt that screw is fixed, stickup or alternate manner closely be fixed on heat sink 6 or the structural member of external environment on, require the contact interface contact good, the full-filling thermal grease conduction; Flexible heat pipe movable end 3 adopts that screws are fixed, stickup or alternate manner closely are fixed on the heat sink or high-power electronic device on movable focal plane subassembly 4, requires the contact interface contact good, the full-filling thermal grease conduction; Movable focal plane subassembly 4 is by fan-shaped gear ring and 5 engagements of power gear group, power gear group 5 can be that gear or tooth bar or worm screw etc. can provide the mechanism that swings power to movable focal plane subassembly 4, power gear group 5 is rotated under motor drives, drive activity focal plane subassembly 4 swings around swinging axle 7, and hunting range is depending on factors such as the length of scope of activities demand, flexible heat pipe bellows segment 2, service lifes.General pendulum angle is less than ± and 30 °.
Flexible heat pipe can customize to heat pipe manufacturer according to the requirement of version.Flexible heat pipe stiff end 1 and flexible heat pipe movable end 3 can be according to the version of mounting interface and the customizations of heat exchange amount, and as the interface size of installation interface, material etc., for example the heat-transfer surface installation dimension of certain flexible heat pipe is 60mm * 40mm, and material is aluminium.The general stainless steel material that adopts of flexible heat pipe bellows segment 2 is to adapt to the requirement of oscillating motion, the length of flexible heat pipe bellows segment 2 and diameter are according to the customization of the factors such as the interface size of structure, amplitude of fluctuation, number of oscillations, service life, as movable focal plane subassembly 4 amplitudes of fluctuation, it is ± 5 °, number of oscillations is about 5000 times, 1 year life-span, the about 100mm of flexible heat pipe compliant section length of customization, diameter is about Φ 13mm.After the relevant parameter of flexible heat pipe is determined, can be to the customization of heat pipe production unit, as Beijing City Space Vehicle Ensemble Designing Departmen.
The design of movable focal plane subassembly 4, can determine according to the size of the electronic device such as detector and structural member, generally can select the material of aluminium alloy as movable focal plane subassembly 4.Movable focal plane subassembly will provide for detector the hot interface of structure mounting interface and heat dissipation channel, so that the heat of detector is transmitted to flexible heat pipe movable end 3 by movable focal plane subassembly 4.
The motor of power gear group 5 is chosen.Movable focal plane subassembly 4 drives by power gear group 5, because the material of flexible heat pipe bellows segment 2 is generally stainless steel, make flexible heat pipe, in swinging crooked process, certain swing resistance be arranged, therefore, choosing of motor in power gear group 5 will be considered this factor, makes power of motor stay certain surplus.
Determining of swinging axle 7 positions.The position of swinging axle 7 will with flexible heat pipe point-blank, otherwise that flexible heat pipe is rolled to each side is asymmetric due to oscillating motion, and then may produce the uncertain factors such as stuck.The position of swinging axle 7 will be on the flexible heat pipe bellows segment, apart from stiff end, certain distance is arranged, the main factors such as diameter amplitude of fluctuation of considering flexible heat pipe, as the position of the swinging axle 7 of above-mentioned flexible heat pipe in the bellows segment of flexible heat pipe apart from stiff end 20mm left and right (calculating from the bellows segment starting position).
By structural member installation and debugging such as movable focal plane subassembly 4, power gear group 5 and swinging axles 7, make the flexible heat pipe movable end 3 heat pipe installed surfaces on the flexible heat pipe stiff end 1 heat pipe installed surface and heat sink 6 on movable focal plane subassembly 4 coplanar, to guarantee that demonstrate,proving flexible heat pipe is in the state of not stressing after installation.
Start power gear group 5 motors, drive activity focal plane subassembly 4 swings back and forth around swinging axle 7 according to the mode of operation of appointment.Movable focal plane subassembly is swingable ± and 5 °, number of oscillations is more than 5000 times.Thermal source on unlatching activity focal plane subassembly 4 (or opening high-power electronic device), the temperature on measurement activity focal plane subassembly 4 (or temperature of high-power electronic device).Under normal operating conditions, when movable focal plane subassembly 4 exported to heat sink 6 power consumption lower than 20W, focal plane subassembly 4 was less than 6 ℃ with heat sink 6 the temperature difference.
Claims (3)
1. the little temperature difference high-efficiency heat exchanger of a space optical remote sensor movable component, comprise substrate (8) and heat sink (6), it is characterized in that, this heat-exchanger rig also comprises flexible heat pipe, power gear group (5), movable focal plane subassembly (4) and swinging axle (7); One end of flexible heat pipe is that flexible heat pipe stiff end (1), the other end are that flexible heat pipe movable end (3), middle part are flexible heat pipe bellows segment (2); Flexible heat pipe stiff end (1) is connected with heat sink (6); Flexible heat pipe movable end (3) is connected with movable focal plane subassembly (4); It is upper that movable focal plane subassembly (4) is arranged on swinging axle (7), can relatively rotate with swinging axle (7); Movable focal plane subassembly (4) is by fan-shaped gear ring and power gear group (5) engagement; Heat sink (6) and swinging axle (7) are arranged on respectively on substrate (8).
2. the little temperature difference high-efficiency heat exchanger of a kind of space optical remote sensor movable component according to claim 1, is characterized in that, the heat pipe installed surface of the heat pipe installed surface of described flexible heat pipe stiff end (1) and flexible heat pipe movable end (3) is coplanar.
3. the little temperature difference high-efficiency heat exchanger of a kind of space optical remote sensor movable component according to claim 1, is characterized in that, described power gear group (5) can be gear, tooth bar or worm screw.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012102514551A CN102778154B (en) | 2012-07-19 | 2012-07-19 | Small-temperature-difference efficient heat exchange device for movable assembly of space optical remote sensor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012102514551A CN102778154B (en) | 2012-07-19 | 2012-07-19 | Small-temperature-difference efficient heat exchange device for movable assembly of space optical remote sensor |
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| Publication Number | Publication Date |
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| CN102778154A CN102778154A (en) | 2012-11-14 |
| CN102778154B true CN102778154B (en) | 2013-11-27 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2012102514551A Expired - Fee Related CN102778154B (en) | 2012-07-19 | 2012-07-19 | Small-temperature-difference efficient heat exchange device for movable assembly of space optical remote sensor |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103471634B (en) * | 2013-09-04 | 2015-11-25 | 北京空间机电研究所 | A kind of space optical remote sensor heat abstractor |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS57169598A (en) * | 1981-04-14 | 1982-10-19 | Fujikura Ltd | Heat pipe |
| JPS6136692A (en) * | 1984-07-27 | 1986-02-21 | Japan Goatetsukusu Kk | Heat pipe |
| CN100524166C (en) * | 2006-05-31 | 2009-08-05 | 中国科学院理化技术研究所 | Dynamic computer chip radiator |
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