CN110143294A - The full posture aircraft thermal design structure of Star Simulator - Google Patents
The full posture aircraft thermal design structure of Star Simulator Download PDFInfo
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- CN110143294A CN110143294A CN201910290411.1A CN201910290411A CN110143294A CN 110143294 A CN110143294 A CN 110143294A CN 201910290411 A CN201910290411 A CN 201910290411A CN 110143294 A CN110143294 A CN 110143294A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
- B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
- B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
- B64G1/503—Radiator panels
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
- B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
- B64G1/506—Heat pipes
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- Cooling Or The Like Of Electrical Apparatus (AREA)
- Thermal Insulation (AREA)
Abstract
The present invention provides a kind of full posture aircraft thermal design structures of Star Simulator, the structure includes OSR, multilayer insulation component, pitch-dark, fluid circuit, heat sink, radiator, heat pipe, OSR is pasted in aircraft+X side plate ,+Y side plate, top plate ,+X+Y oblique side plate ,-Y side plate lower semisection outside, multilayer insulation component is coated on the outside of remaining side plate, the spraying of single machine surface is pitch-dark in all side wall inner surfaces, dashboard and cabin, fluid circuit is in the layout of in cabin, the installation of part single machine bottom is heat sink, and radiator is located at+Y side plate lower semisection and-Y side plate lower semisection.The present invention is convenient for general assembly and test, has efficient heat collection and dissipation ability, adaptable, can be applied to wild trajectory and any attitude aircraft.
Description
Technical field
The invention belongs to spacecraft thermal control design fields, for the aircraft under wild trajectory and any attitude, especially
It is related to the aircraft thermal design technology for having big power consumption single machine, and in particular, to the full posture aircraft thermal design structure of Star Simulator.
Background technique
With the development of science and technology and the demand of Space Industry, electronic instrument is stepped to small-sized, lightweight, modularization direction
Into function is more powerful, but heat consumption is increasing, how to solve the heat dissipation problem of such single machine into a great problem.By
In the particularity of space environment, external environment is severe, and the more evil become with the difference of track and posture, external thermal environments
It is bad, thermal design difficulty has been significantly greatly increased.
Currently, being directed to Star Simulator, full posture aircraft, big power consumption in cabin is solved by hot pipe network and fluid circuit technology
The Thermal design of single machine heat dissipation problem, still belongs to the first time at home.Usual aircraft uses based on passively, supplemented by active
Thermal design, mainly solution Orbital heat flux situation is relatively stable, has the aircraft of fixed radiating surface, to track and Gesture
Higher, adaptability is poor, and on solving big power consumption single machine heat dissipation problem, be limited it is more, especially to the layout of single machine and
There is more harsh requirement in its working time, significantly limits the use of such single machine on board the aircraft.And conventional heat
With the thermal control technology compared with strong adaptability, such as LHP, shutter or be heat collection and dissipation scarce capacity, it is unable to satisfy
Demand or it is that reliability is too low, or the resource expended is too big, beyond overall power limit.Therefore it must propose more efficient
Thermal design, with optimal resource distribution, higher reliability, solve thermal design problem.
Summary of the invention
For the defects in the prior art, the present invention provides the full posture aircraft thermal design structure of Star Simulator, it is convenient for
General assembly and test have efficient heat collection and dissipation ability, adaptable, can be applied to the flight of wild trajectory any attitude
Device.
The full posture aircraft thermal design structure of the Star Simulator provided according to the present invention, comprising:
OSR is pasted onto aircraft+X side plate ,+Y side plate, top plate ,+X+Y oblique side plate ,-Y side plate lower semisection outside, for flying
The whole device heat dissipation of row device；
Insulating assembly is pasted onto for anti-leak-stopping heat except aircraft+X side plate ,+Y side plate, top plate ,+X+Y oblique side plate ,-Y
On the outside of aircraft other than side plate lower semisection side plate；
It is pitch-dark, it is radiated for strengthening in cabin, realizes isothermal, be sprayed in all side wall inner surfaces, dashboard and cabin single
Machine surface；
Fluid circuit is in the layout of in cabin, including heat sink 5, radiator 6, for solving big power consumption single machine heat dissipation in cabin；
It is heat sink, it is mounted on part single machine bottom, is used for heat collection；
Radiator is formed, radiator 6 by heat pipe 7 pre-buried in aircraft+Y side plate lower semisection and-Y side plate lower semisection
The back side couples pre-buried heat pipe 7 integrally by heat sink 5, and the waste heat for collecting heat sink 5 passes through dissipation to the outer space；
Heat pipe is installed in single machine region by the dashboard and+Y side plate that are embedded in aircraft, forms hot pipe network.
Preferably, OSR is the silver-plated second surface mirror thermal control coating of conductivity type cerium glass；The silver-plated secondary instrument of conductivity type cerium glass
Face mirror thermal control coating is that, by vacuum plating silver, have low α using cerium glass as groundS/εhThe thermal control coating of ratio, design value: αS
=0.12 ± 0.02, εh=0.82 ± 0.02.
Preferably, insulating assembly is multilayer, is made of T20-A terylene silk net and 6 μm of two-sided aluminized mylars, outermost layer
It aluminizes second surface mirror for 25 μm of conductivity type polyimides, design value: αS=0.36 ± 0.02, εh=0.69 ± 0.02.
Preferably, pitch-dark, it is that SR107-E51 pitch-dark, black anodizing or E51 are one of pitch-dark；Wherein, thermal control
SR107-E51 coating is used in the high emissivity of stellar interior, coating type thermal control coating, design value: εh=0.88 ± 0.02；
Black anodizing coating is the thermal control coating that instrument uses in star, design value: εh≥0.88；The pitch-dark thermal control coating of E51 is to make
High emissivity, coating type thermal control coating used in stellar interior, design value: εh=0.88 ± 0.02.
Preferably, fluid circuit is by pump, thermostat valve, check valve, liquid storage device, filter, heat sink, radiator and controller group
At.
Preferably, heat sink that short rib corrugated plate interstitital texture is arranged using rectangle difference, rectangle is filled between heat sink body and cover board
Difference arranges short rib corrugated fin, and heat sink body and cover board are welded as a whole by vacuum brazing mode.
Preferably, radiator, by the aluminum alloy honeycomb plate of aircraft+Y side plate lower semisection and-Y side plate lower semisection
It is formed in pre-buried heat pipe.
Preferably, heat pipe is I-shaped diplopore aluminium ammonia heat pipe.
Compared with prior art, the present invention have it is following the utility model has the advantages that
1, radiating surface pastes OSR, guarantees when aircraft makes Orbital heat flux change because of track or pose adjustment, whole device
Still there is certain heat-sinking capability, improve aircraft temperature environment adaptability；
2, insulating assembly can be strengthened in cabin and radiate, and realize isothermalization design；
3, pitch-dark setting solves big power consumption single machine heat dissipation problem in cabin；
4, using fluid circuit technology, pre-buried heat pipe in dashboard forms hot pipe network, realizes isothermalization design in cabin；
5, heat sink in fluid circuit, solve big power consumption single machine heat dissipation problem；
6, heat pipe-type radiator facilitates heat dissipation, is conducive to isothermal in cabin；
7, the two-way master backup installation of radiator, guarantee have a radiator available under any circumstance；
8, heat pipe is that I-shaped diplopore aluminium ammonia heat pipe configuration is simple, is convenient for general assembly, high reliablity, the requirement drop to pumping function
It is low, reduce cost；
9, the technology is convenient for general assembly and test, has efficient heat collection and dissipation ability, adaptable, can be applied to
All kinds of full posture aircraft of Star Simulator.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is aircraft thermal control conceptual design schematic diagram in the present invention.
Fig. 2 is Instrumental plate thermal design schematic diagram of the present invention.
Fig. 3 is+Y side plate thermal design schematic diagram in the present invention.
Fig. 4 is-Y side plate thermal design schematic diagram in the present invention.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection scope.
In one embodiment, comprehensive function of the invention is as follows:
OSR1, for the whole device heat dissipation of aircraft；
Insulating assembly 2, for anti-leak-stopping heat；
Pitch-dark 3, it is radiated for strengthening in cabin, realizes isothermal；
Fluid circuit 4, for solving big power consumption single machine heat dissipation in cabin；
Heat sink 5, it is used for heat collection；
Radiator 6, waste heat for collecting heat sink 5 is by dissipation to the outer space, and the back side is with heat sink 5 by pre-buried heat
Pipe 7 couples integrally, so that heat pipe 7 pre-buried in dashboard and+Y side plate installation single machine region forms hot pipe network；
+ X side plate 8, the main radiating surface of aircraft are used for whole device heat dissipation；
+ Y side plate 9, the main radiating surface of aircraft, 6 mounting surface of radiator are used for whole device heat dissipation；
Top plate 10, the main radiating surface of aircraft are used for whole device heat dissipation；
+ X+Y oblique side plate 11, aircraft auxiliary heat dissipation face assist whole device heat dissipation when necessary；
- Y side plate 12,6 mounting surface of radiator assist whole device heat dissipation when necessary；
Dashboard 13, aircraft instrument install carrier, structural slab.
Next the present invention is described in detail.
As shown in attached Fig. 1 to Fig. 4, the invention discloses the full posture aircraft thermal design structure of Star Simulator, convenient for general assembly and
Test has efficient heat collection and dissipation ability, adaptable, can be applied to wild trajectory and any attitude aircraft.
Thermal design structure includes OSR1, insulating assembly 2, pitch-dark 3, fluid circuit 4, heat sink 5, radiator 6, heat pipe 7.
OSR1 is pasted onto aircraft+X side plate 8 ,+Y side plate 9, top plate 10 ,+X+Y oblique side plate 11,12 lower semisection of-Y side plate outside, is used for
The whole device heat dissipation of aircraft；Insulating assembly 2 is pasted onto for anti-leak-stopping heat except aircraft+X side plate 8 ,+Y side plate 9, top plate 10 ,+X
On the outside of aircraft other than+Y oblique side plate 11,12 lower semisection side plate of-Y side plate；Pitch-dark 3, it is radiated for strengthening in cabin, realizes isothermal
Change, is sprayed on all side wall inner surfaces, in dashboard and cabin single machine surface；Fluid circuit 4, is in the layout of in cabin, including heat sink 5,
Radiator 6, for solving big power consumption single machine heat dissipation in cabin；Heat sink 5, it is mounted on part single machine bottom, is used for heat collection；Radiation
Device 6 is formed by heat pipe 7 pre-buried in 9 lower semisection of aircraft+Y side plate and 12 lower semisection of-Y side plate, and 6 back side of radiator passes through
Heat sink 5 couple pre-buried heat pipe 7 integrally, and the waste heat for collecting heat sink 5 passes through dissipation to the outer space；Heat pipe 7 leads to
It crosses the dashboard 13 for being embedded in aircraft and+Y side plate 9 is installed in single machine region, form hot pipe network.
The present invention is first in aircraft+X side plate 8 ,+Y side plate 9, top plate 10 ,+X+Y oblique side plate 11,12 lower semisection of-Y side plate
OSR1 is pasted in outside, and OSR1 is the silver-plated second surface mirror thermal control coating of conductivity type cerium glass；The silver-plated secondary instrument of conductivity type cerium glass
Face mirror thermal control coating is that, by vacuum plating silver, have low α using cerium glass as groundS/εhThe thermal control coating of ratio, design value: αS
=0.12 ± 0.02, εh=0.82 ± 0.02.OSR1 guarantees in aircraft as whole device radiating surface because of track or pose adjustment
And when Orbital heat flux being made to change, whole device still has certain heat-sinking capability, improves aircraft temperature environment adaptability.
Leakage heat in order to prevent, insulating assembly 2 are multilayer；It is radiated to strengthen in cabin, realizes isothermalization design, insulating assembly
2, it is made of T20-A terylene silk net and 6 μm of two-sided aluminized mylars, outermost layer is aluminized secondary for 25 μm of conductivity type polyimides
Surface mirror, design value: αS=0.36 ± 0.02, εh=0.69 ± 0.02.
In order to solve big power consumption single machine heat dissipation problem in cabin, pitch-dark 3 be SR107-E51 pitch-dark, black anodizing or E51
It is one of pitch-dark；Wherein, thermal control SR107-E51 coating is used in the high emissivity of stellar interior, coating type thermal control coating,
Design value: εh=0.88 ± 0.02；Black anodizing coating is the thermal control coating that instrument uses in star, design value: εh≥
0.88；The pitch-dark thermal control coating of E51 is used in the high emissivity of stellar interior, coating type thermal control coating, design value: εh=0.88
±0.02。
To realize isothermalization design in cabin, fluid circuit technology is used, specifically, fluid circuit 4 is mainly by pump, temperature control
The compositions such as valve, check valve, liquid storage device, filter, heat sink 5, radiator 6 and controller.
Heat sink 5 be fluid circuit important component, and selected section single machine bottom installation heat sink 5, is received for heat in cabin
Collection, solves big power consumption single machine heat dissipation problem.For the ease of heat collection, short rib corrugated plate interstitital texture is arranged using rectangle difference,
The short rib corrugated fin of rectangle difference row is filled between heat sink 5 ontology and cover board, heat sink 5 ontology and cover board pass through vacuum brazing mode and weld
It is connected in one.
Radiator 6 is fluid circuit important component, for the ease of heat dissipation, by under aircraft+Y side plate 9
Half section forms in the aluminum alloy honeycomb plate of 12 lower semisection of-Y side plate in pre-buried heat pipe 7.Heat pipe-type radiator 6, configuration is simple, just
In general assembly, high reliablity, the requirement to pumping function is reduced, and realizes isothermalization design in cabin.+ Y side plate 9 and-Y side plate 12 are each simultaneously
One piece of radiator is installed, two-way master backup setting, guarantee has a radiator available under any circumstance, improve reliability with
Adaptability.Heat pipe 7 is I-shaped diplopore aluminium ammonia heat pipe, and pre-buried heat pipe in dashboard forms hot pipe network, the requirement to pumping function
It reduces, reduces cost.
In conclusion the radiating surface in structure of the invention pastes OSR, guarantee to make in aircraft because of track or pose adjustment
When Orbital heat flux changes, whole device still has certain heat-sinking capability, improves aircraft temperature environment adaptability；Insulating assembly
It can strengthen in cabin and radiate, realize isothermalization design；Pitch-dark setting solves big power consumption single machine heat dissipation problem in cabin；Using stream
Body circuit technology, pre-buried heat pipe in dashboard form hot pipe network, realize isothermalization design in cabin；It is heat sink in fluid circuit,
Solves big power consumption single machine heat dissipation problem；Heat pipe-type radiator facilitates heat dissipation, is conducive to isothermal in cabin；Radiator is double
It is installed to master backup, guarantee has a radiator available under any circumstance；Heat pipe is I-shaped diplopore aluminium ammonia heat pipe configuration
Simply, it is convenient for general assembly, high reliablity, the requirement to pumping function reduces, and reduces cost；Technology of the invention is convenient for general assembly and survey
Examination has efficient heat collection and dissipation ability, adaptable, can be applied to the full posture aircraft of all kinds of Star Simulators.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring substantive content of the invention.
Claims (8)
1. a kind of full posture aircraft thermal design structure of Star Simulator characterized by comprising
OSR is pasted onto aircraft+X side plate ,+Y side plate, top plate ,+X+Y oblique side plate ,-Y side plate lower semisection outside, is used for aircraft
Whole device heat dissipation；
Insulating assembly is pasted onto for anti-leak-stopping heat except aircraft+X side plate ,+Y side plate, top plate ,+X+Y oblique side plate ,-Y side plate
On the outside of aircraft other than lower semisection side plate；
It is pitch-dark, it is radiated for strengthening in cabin, realizes isothermal, be sprayed on all side wall inner surfaces, single machine table in dashboard and cabin
Face；
Fluid circuit is in the layout of in cabin, including heat sink, radiator, for solving big power consumption single machine heat dissipation in cabin；
It is heat sink, it is mounted on part single machine bottom, is used for heat collection；
Radiator, by aircraft+Y side plate lower semisection and-Y side plate lower semisection pre-buried heat pipe formed, the radiator back side is logical
Cross it is heat sink pre-buried heat pipe is coupled it is integral, for the waste heat of heat sink collection to be passed through dissipation to the outer space；
Heat pipe is installed in single machine region by the dashboard and+Y side plate that are embedded in aircraft, forms hot pipe network.
2. the full posture aircraft thermal design structure of Star Simulator as described in claim 1, which is characterized in that the OSR1 is conduction
The silver-plated second surface mirror thermal control coating of type cerium glass；The silver-plated second surface mirror thermal control coating of conductivity type cerium glass is with cerium glass
Glass is ground, by vacuum plating silver, has low αS/εhThe thermal control coating of ratio, design value: αS=0.12 ± 0.02, εh=0.82
±0.02。
3. the full posture aircraft thermal design structure of Star Simulator as described in claim 1, which is characterized in that the insulating assembly is
Multilayer is made of T20-A terylene silk net and 6 μm of two-sided aluminized mylars, and outermost layer is that 25 μm of conductivity type polyimides are aluminized
Second surface mirror, design value: αS=0.36 ± 0.02, εh=0.69 ± 0.02.
4. the full posture aircraft thermal design structure of Star Simulator as described in claim 1, which is characterized in that it is described pitch-dark, be
SR107-E51 is pitch-dark, black anodizing or E51 are one of pitch-dark；Wherein, thermal control SR107-E51 coating is used in star
The high emissivity in internal portion, coating type thermal control coating, design value: εh=0.88 ± 0.02；Black anodizing coating is in star
The thermal control coating that instrument uses, design value: εh≥0.88；The pitch-dark thermal control coating of E51 be used in stellar interior high emissivity,
Coating type thermal control coating, design value: εh=0.88 ± 0.02.
5. the full posture aircraft thermal design structure of Star Simulator as described in claim 1, which is characterized in that the fluid circuit by
Pump, thermostat valve, check valve, liquid storage device, filter, heat sink, radiator and controller composition.
6. the full posture aircraft thermal design structure of Star Simulator as described in claim 1, which is characterized in that described heat sink using square
Shape difference arranges short rib corrugated plate interstitital texture, and rectangle difference is filled between the heat sink body and cover board and arranges short rib corrugated fin, described
Heat sink body and cover board are welded as a whole by vacuum brazing mode.
7. the full posture aircraft thermal design structure of Star Simulator as described in claim 1, which is characterized in that the radiator leads to
It crosses and is formed in the aluminum alloy honeycomb plate of aircraft+Y side plate lower semisection and-Y side plate lower semisection in pre-buried heat pipe.
8. the full posture aircraft thermal design structure of Star Simulator as described in claim 1, which is characterized in that the heat pipe is I-shaped
Shape diplopore aluminium ammonia heat pipe.
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