CN106467176A - The temp. control method in satellite booster cabin - Google Patents
The temp. control method in satellite booster cabin Download PDFInfo
- Publication number
- CN106467176A CN106467176A CN201610810994.2A CN201610810994A CN106467176A CN 106467176 A CN106467176 A CN 106467176A CN 201610810994 A CN201610810994 A CN 201610810994A CN 106467176 A CN106467176 A CN 106467176A
- Authority
- CN
- China
- Prior art keywords
- cabin
- propelling module
- satellite
- temp
- control method
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000000034 method Methods 0.000 title claims abstract description 25
- 238000009413 insulation Methods 0.000 claims abstract description 13
- 238000002955 isolation Methods 0.000 claims description 4
- 239000003380 propellant Substances 0.000 abstract description 6
- 238000005253 cladding Methods 0.000 abstract 1
- 239000011248 coating agent Substances 0.000 abstract 1
- 238000000576 coating method Methods 0.000 abstract 1
- 238000005516 engineering process Methods 0.000 description 6
- 230000008901 benefit Effects 0.000 description 3
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 239000008280 blood Substances 0.000 description 1
- 210000004369 blood Anatomy 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
Classifications
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
-
- 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
- B64G1/40—Arrangements or adaptations of propulsion systems
-
- 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
Abstract
The invention provides a kind of temp. control method in satellite booster cabin, it is arranged on a single propelling module based on propulsion system, and the method for designing of employing is whole Surface coating multilayer insulation assembly out of my cabin；Part thruster needs out of my cabin to coat multilayer insulation assembly；Design compensation heater ensures the temperature levels of electromagnetic valve；Pipeline and support cladding multilayer insulation assembly out of my cabin；Do not make any thermal control in propelling module to process.Adopt foregoing invention on the basis of new type low temperature propellant, the temperature requirements in satellite booster cabin can be solved.
Description
Technical field
The present invention relates in spacecraft Evolution of Thermal Control Technique field, in particular it relates to the temp. control method in satellite booster cabin.
Background technology
Recently as the progress of electronic integration technology and payload miniaturization technology, moonlet relies on its higher skill
The features such as art is integrated, low cost, lead time are short, achieves and develops rapidly.Development high-performance payload is little with low cost
Satellite, will play technology traction and the effect supporting to the progress of space technology.
Propulsion system controls the actuator of subsystem as satellite attitude orbit, and main task is according to attitude track control
System needs, rate damping, preliminary orbit capture are provided, the power of required by task such as track keeps, orbit maneuver and attitude keep or
Moment, to guarantee completing of satellite task.Propelling module is by latching valve, tank, plus valve, pressure transducer, thruster, and mistake
Filter, pipeline, support etc. form directly under part, and in order to ensure the in-orbit normal work of propelling module, each assembly need meet certain
Temperature index.
In conventional satellite design at present, the main thermal control design of propulsion system is：Tank is installed after compensating heater and coat
Multilayer insulation assembly, other assemblies coat multilayer insulation assembly after will being wound around heating tape, and the unit then carrying out whole star again is installed
Work.This design has higher requirement for power consumption, quality, develops flow process for whole star and there is larger shadow the lead time
Ring, be unfavorable for the development need of Modern Satellite.In order to solve the above problems, a kind of design of needs development is simple, the lead time is fast
The temp. control method in the satellite booster cabin of speed.
At present, in conventional satellite design, propulsion system thermal design is usually present following problem：
1st, under the conditions of conventional propellant, propulsion system requires higher for thermal temperature.Under the conditions of this heat control system in order to
Meet design requirement resource consumption big, be unfavorable for the utilization of resources.
2nd, under the conditions of conventional propellant, the design of propulsion system thermal control method is complicated, installs loaded down with trivial details.Major defect is weight
Weight, installation are complicated, and for the control of propulsion system temperature, cost is larger.
Content of the invention
Adapt to the thermal design problem of propulsion system under the conditions of new propellant in order to solve prior art, the present invention proposes
A kind of temp. control method in satellite booster cabin, the propulsion system thermal design under the conditions of especially suitable new type low temperature propellant.
A kind of temp. control method in the satellite booster cabin being provided according to the present invention, including：
Isolation propelling module cabin in and out of my cabin between radiant heat exchange, inside cabin, plate surface all coats multilayer insulation group
Part, makes propelling module inner assembly uniformity of temperature profile；
Using compensating electric heater, to propelling module, outer electromagnetic valve carries out heat compensation；
The outer surface of propelling module outer panel and support pipeline all coats multilayer insulation assembly.
Preferably, described compensation electric heater is pasted on out of my cabin on electromagnetism valve surface.
Preferably, carry out in thermal design step in the propelling module to satellite, except propelling module inner assembly, not in propelling module
Make any thermal control to process.
Preferably, satellite propulsion system is arranged in a single propelling module.
Compared with prior art, the present invention has the advantages that：
(1) adopt the present invention provide satellite booster cabin temp. control method, can avoid cabin inner part heater and multilamellar every
The design of hot assembly, its power consumption and quality have minimizing by a relatively large margin, have reached the shortening lead time and have reduced research fund
Purpose；
(2) temp. control method in the satellite booster cabin of present invention offer is provided, advances under the conditions of new type low temperature propellant
Optimized System Design provides thermal design basis.
(3) present invention accomplishes designing simple, lead time quick design requirement, good reliability, flexible design.
Brief description
The detailed description with reference to the following drawings, non-limiting example made by reading, the further feature of the present invention,
Objects and advantages will become more apparent upon：
Fig. 1 is the propelling module configuration schematic diagram of the temp. control method using satellite booster cabin；
In figure：1 is propelling module inner assembly, and 2 is the outer electromagnetic valve of propelling module, and 3 is propelling module outer panel and support pipeline.
Specific embodiment
With reference to specific embodiment, the present invention is described in detail.Following examples will be helpful to the technology of this area
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill to this area
For personnel, without departing from the inventive concept of the premise, some changes and improvements can also be made.These broadly fall into the present invention
Protection domain.
Present embodiments provide a kind of temp. control method in satellite booster cabin, comprise the steps：
Thermal design is carried out to the propelling module of satellite：With radiant heat exchange out of my cabin in isolation cabin, inside cabin, plate surface all coats
Multilayer insulation assembly, makes propelling module inner assembly 1 uniformity of temperature profile, and in cabin, other parts do not make any thermal control process；Using benefit
Outer electromagnetic valve 2 carries out heat compensation to propelling module to repay electric heater；Propelling module outer panel and support pipeline 3 outer surface all coat many
Layer insulating assembly.
With radiant heat exchange out of my cabin in isolation cabin, inside cabin, plate surface all coats multilayer insulation assembly, makes group in propelling module
Part 1 uniformity of temperature profile：Inside propelling module, plate surface all coats multilayer insulation assembly, and in cabin, other parts are not made at any thermal control
Reason.Compensate electric heater to be pasted on outer electromagnetic valve 2 surface of propelling module.
Further, thermal design is carried out to propelling module outer panel and support pipeline 3：To propelling module outer panel and support pipeline
3 outer surface coats multilayer insulation assembly entirely.
Compared with the temp. control method in traditional satellite booster cabin, the temp. control method in the satellite booster cabin that the present invention provides, tool
Effective good, adaptability is good, thermal control measure is convenient to carry out feature.
Above the specific embodiment of the present invention is described.It is to be appreciated that the invention is not limited in above-mentioned
Particular implementation, those skilled in the art can make a variety of changes within the scope of the claims or change, this not shadow
Ring the flesh and blood of the present invention.In the case of not conflicting, feature in embodiments herein and embodiment can any phase
Mutually combine.
Claims (4)
1. a kind of temp. control method in satellite booster cabin is it is characterised in that include：
Isolation propelling module cabin in and out of my cabin between radiant heat exchange, inside cabin, plate surface all coats multilayer insulation assembly, makes
Propelling module inner assembly uniformity of temperature profile；
Using compensating electric heater, to propelling module, outer electromagnetic valve carries out heat compensation；
The outer surface of propelling module outer panel and support pipeline all coats multilayer insulation assembly.
2. the temp. control method in satellite booster cabin according to claim 1 is it is characterised in that described compensation electric heater is pasted
On electromagnetism valve surface out of my cabin.
3. the temp. control method in satellite booster cabin according to claim 1 is it is characterised in that carry out in the propelling module to satellite
In thermal design step, do not process to making any thermal control in propelling module.
4. the temp. control method in satellite booster cabin according to claim 1 is it is characterised in that be arranged on satellite propulsion system
In one single propelling module.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610810994.2A CN106467176A (en) | 2016-09-08 | 2016-09-08 | The temp. control method in satellite booster cabin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610810994.2A CN106467176A (en) | 2016-09-08 | 2016-09-08 | The temp. control method in satellite booster cabin |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106467176A true CN106467176A (en) | 2017-03-01 |
Family
ID=58230378
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610810994.2A Pending CN106467176A (en) | 2016-09-08 | 2016-09-08 | The temp. control method in satellite booster cabin |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106467176A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107323694A (en) * | 2017-05-18 | 2017-11-07 | 上海卫星工程研究所 | Modular satellite booster cabin |
| CN107719704A (en) * | 2017-09-22 | 2018-02-23 | 北京空间飞行器总体设计部 | A kind of spacecraft propulsion agent pipeline entirety thermal controls apparatus |
| CN107856886A (en) * | 2017-11-16 | 2018-03-30 | 北京千乘探索科技有限公司 | A kind of thermal controls apparatus of the outer cold air propulsion die of satellite capsule |
| CN114476139A (en) * | 2022-01-13 | 2022-05-13 | 上海卫星工程研究所 | Thermal control design system and method for Mars circulator traveling wave tube assembly |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10252559A (en) * | 1997-03-13 | 1998-09-22 | Mitsubishi Electric Corp | Propulsion module |
| JP2004197592A (en) * | 2002-12-17 | 2004-07-15 | Kawasaki Heavy Ind Ltd | Method and device for generating thrust |
| CN102303710A (en) * | 2011-06-08 | 2012-01-04 | 航天东方红卫星有限公司 | General propelling module for small satellites |
| CN103921956A (en) * | 2014-04-16 | 2014-07-16 | 南京理工大学 | Solid cool air micro-propelling system |
| CN104828262A (en) * | 2015-04-30 | 2015-08-12 | 北京控制工程研究所 | Low-pressure liquefied gas thrust generating method for spacecraft |
| CN105035365A (en) * | 2015-07-31 | 2015-11-11 | 上海卫星工程研究所 | Satellite temperature control method allowing rapid responding and multi-orbit adaption |
| CN105109708A (en) * | 2015-08-31 | 2015-12-02 | 北京航天长征飞行器研究所 | Thermal control method of spatial aircraft |
-
2016
- 2016-09-08 CN CN201610810994.2A patent/CN106467176A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10252559A (en) * | 1997-03-13 | 1998-09-22 | Mitsubishi Electric Corp | Propulsion module |
| JP2004197592A (en) * | 2002-12-17 | 2004-07-15 | Kawasaki Heavy Ind Ltd | Method and device for generating thrust |
| CN102303710A (en) * | 2011-06-08 | 2012-01-04 | 航天东方红卫星有限公司 | General propelling module for small satellites |
| CN103921956A (en) * | 2014-04-16 | 2014-07-16 | 南京理工大学 | Solid cool air micro-propelling system |
| CN104828262A (en) * | 2015-04-30 | 2015-08-12 | 北京控制工程研究所 | Low-pressure liquefied gas thrust generating method for spacecraft |
| CN105035365A (en) * | 2015-07-31 | 2015-11-11 | 上海卫星工程研究所 | Satellite temperature control method allowing rapid responding and multi-orbit adaption |
| CN105109708A (en) * | 2015-08-31 | 2015-12-02 | 北京航天长征飞行器研究所 | Thermal control method of spatial aircraft |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107323694A (en) * | 2017-05-18 | 2017-11-07 | 上海卫星工程研究所 | Modular satellite booster cabin |
| CN107719704A (en) * | 2017-09-22 | 2018-02-23 | 北京空间飞行器总体设计部 | A kind of spacecraft propulsion agent pipeline entirety thermal controls apparatus |
| CN107719704B (en) * | 2017-09-22 | 2019-11-29 | 北京空间飞行器总体设计部 | A kind of spacecraft propulsion agent pipeline entirety thermal controls apparatus |
| CN107856886A (en) * | 2017-11-16 | 2018-03-30 | 北京千乘探索科技有限公司 | A kind of thermal controls apparatus of the outer cold air propulsion die of satellite capsule |
| CN107856886B (en) * | 2017-11-16 | 2024-04-26 | 北京千乘探索科技有限公司 | Thermal control device of cold air propulsion module outside satellite cabin |
| CN114476139A (en) * | 2022-01-13 | 2022-05-13 | 上海卫星工程研究所 | Thermal control design system and method for Mars circulator traveling wave tube assembly |
| CN114476139B (en) * | 2022-01-13 | 2024-01-30 | 上海卫星工程研究所 | Mars circulator traveling wave tube assembly thermal control design system and method |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170301 |
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| RJ01 | Rejection of invention patent application after publication |