CN107529359B - A kind of fuel tank thermal controls apparatus - Google Patents
A kind of fuel tank thermal controls apparatusInfo
- Publication number
- CN107529359B CN107529359B CN201318008057.2A CN201318008057A CN107529359B CN 107529359 B CN107529359 B CN 107529359B CN 201318008057 A CN201318008057 A CN 201318008057A CN 107529359 B CN107529359 B CN 107529359B
- Authority
- CN
- China
- Prior art keywords
- fuel tank
- tank
- controls apparatus
- thermal controls
- heater
- 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.)
- Expired - Fee Related
Links
- 239000002828 fuel tank Substances 0.000 title claims abstract description 30
- 238000010276 construction Methods 0.000 claims abstract description 11
- 229920000134 Metallised film Polymers 0.000 claims abstract description 9
- 239000004952 Polyamide Substances 0.000 claims abstract description 9
- 239000000835 fiber Substances 0.000 claims abstract description 9
- 238000009413 insulation Methods 0.000 claims abstract description 9
- 229920002647 polyamide Polymers 0.000 claims abstract description 9
- 238000009434 installation Methods 0.000 claims abstract description 7
- 239000011152 fibreglass Substances 0.000 claims description 5
- 229910001006 Constantan Inorganic materials 0.000 claims description 4
- 239000004642 Polyimide Substances 0.000 claims description 4
- 238000005485 electric heating Methods 0.000 claims description 4
- 229920001721 polyimide Polymers 0.000 claims description 4
- 239000003380 propellant Substances 0.000 abstract description 14
- 238000012546 transfer Methods 0.000 abstract description 4
- 238000005253 cladding Methods 0.000 abstract description 2
- 238000013461 design Methods 0.000 abstract description 2
- 238000012360 testing method Methods 0.000 abstract description 2
- 230000003044 adaptive effect Effects 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 230000002277 temperature effect Effects 0.000 description 2
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005422 blasting Methods 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 239000007800 oxidant agent Substances 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 230000000704 physical effect Effects 0.000 description 1
Abstract
The present invention provides a kind of engine fuel tank thermal controls apparatus, including：Sandwich construction, heat insulating mattress, heater and thermistor.Hemisphere face and shell of column, tank installing plate upper and lower sides, the surface corresponding to tank support bar of the fuel tank are wrapped in including the sandwich construction.The sandwich construction is respectively the multilayer insulation component of Unit 10, Unit 5, Unit 5, and the insulating unit of each multilayer is separately made up of two-sided aluminized mylar and polyamide fibre hairnet.The present invention is according to conventional dynamic loading star heat balance test result, the in-orbit interim consumption feature of bonding propellant, in addition to heat-insulated installation and all cladding multilayer, emphasis carries out thermal compensation control to ball section under tank and installation region, to meet the thermal control demand of bipropellant tank.Satellite fuel tank high precision temperature control requirement is met, while has adapted to transfer orbit section and normal in-orbit section temperature requirements, good reliability, flexible design.
Description
Technical field
The technical field of space flight and aviation of the present invention, more particularly to a kind of fuel tank thermal controls apparatus.
Background technology
Bipropellant propulsion system is launched first since the mid-1970s, to the extensive use eighties.Should
Double elements Liquid apogee engine of the engine block of system by a 490N, 16~18 10N thrusts
Device forms, and they use same pressure and Propellant Control system, and the pipeline flow dividing of engine valve in front of the door is into far
Point and attitude control engine, be characterized in than leaping high, payload it is big.Pass through the multiple of Liquid apogee engine
Ignition performance, greatly improve orbit injection accuracy.
Further, the propellant receptacle storing module of the Propellant Control system mainly includes 4 propellant receptacles
Case, 8 latching valves, 2 normally opened electric blasting valves, 4 plus valve, 4 pressure sensors and some pipelines etc.
Component.Wherein, 4 propellant tank tiled arrangements, oxidant and incendiary agent are stored in 2 tanks respectively.
The tank is half management surface tension propellant tank, and profile is spherocylinder, using auricle connected mode.490N is sent out
The double elements tank volume of motivation is big, big by ambient temperature effect in star, and bipropellant is controlled the temperature difference
It is required that it is high, and the propellant tank temperature difference of the same race, within 3 DEG C, the xenogenesis propellant tank temperature difference is within 5 DEG C.
It is and inconsistent, it is necessary to adaptive temperature requirement simultaneously in transfer orbit section and normally in-orbit section, tank temperature requirement.
Requirements at the higher level are thus proposed to propellant tank thermal control, to ensure propulsion subsystem normal work.
The content of the invention
The invention aims to solve the problems, such as the thermal control demand of bipropellant tank, a kind of combustion is proposed
Expect tank thermal controls apparatus, especially adapt to 490N engine.
To solve the above problems, the present invention provides a kind of engine fuel tank thermal controls apparatus, including：Multilayer knot
Structure, heat insulating mattress, heater and thermistor.
Further, including the sandwich construction is wrapped in the hemisphere face and shell of column, tank peace of the fuel tank
Surface corresponding to loading board upper and lower sides, tank support bar.
Further, the sandwich construction is respectively the multilayer insulation component of Unit 10, Unit 5, Unit 5,
The insulating unit of each multilayer is separately made up of two-sided aluminized mylar and polyamide fibre hairnet.
Further, the insulating unit of each multilayer is by one layer of two-sided aluminized mylar and one layer of polyamide fibre hairnet phase
Interval composition.
Further, the heat insulating mattress is fiberglass, between the auricle and tank installing plate of fuel tank.
Further, the heater includes：Public heater all the way, and installation and the 3 of each tank respectively
Road separate heater.
Further, the heater is polyimides constantan paper tinsel electric heating sheets.
Further, in addition to program control control unit and remote control unit, stroke is entered to tackling the heater
Control control and remote control.
Further, the thermistor corresponds to tank installing plate measuring point, and the thermistor type is MF501
Type.
Further, in addition to temperature control threshold cell, the temperature control threshold value is modified by noting number mode.
Present invention accomplishes the requirement of satellite fuel tank high precision temperature control, at the same adapted to transfer orbit section with it is normal
In-orbit section of temperature requirements, good reliability, flexible design.
Further, the multilayer is wrapped in tank hemisphere face and shell of column, tank installing plate upper and lower sides, tank branch
On strut, multilayer is respectively Unit 10, Unit 5, Unit 5, and each multilayer insulation unit is double by one layer 6 μm
Face aluminized mylar and one layer of 20d polyamide fibre hairnet separately form.
Further, the heat insulating mattress is fiberglass, is padded between auricle and tank installing plate, thickness 4
mm
Further, the electric heater is polyimides constantan paper tinsel electric heating sheets, and both program-controlled control, again might be used
Remote control, temperature control threshold value can be modified by noting number mode.
Further, the thermistor is MF501 types.
The present invention is special according to conventional dynamic loading star heat balance test result, the in-orbit interim consumption of bonding propellant
Point, in addition to heat-insulated installation and all cladding multilayer, emphasis carries out thermal compensation to ball section under tank and installation region
Control, to meet the thermal control demand of bipropellant tank.
Compared with prior art, the present invention has following beneficial effects：
(1) meet tank in twilight orbit section and the different temperatures demand of in-orbit period；
(2) it can ensure that same fuel tank mean temperature difference is no more than 3 DEG C, different fuel tank mean temperature difference
No more than 5 DEG C；
(3) material source is abundant, and technique is simple, it is easy to accomplish, cost is relatively low.
Brief description of the drawings
Fig. 1 is the structural representation of the fuel tank thermal controls apparatus of one embodiment of the invention；
Fig. 2 is the twilight orbit section tank lower semisphere temperature of the fuel tank thermal controls apparatus of one embodiment of the invention
Write music line；
Fig. 3 is the normal in-orbit tank lower semisphere temperature of the fuel tank thermal controls apparatus of one embodiment of the invention
Curve.
Embodiment
Double elements tank volume is big in the prior art.The double elements tank volume of especially 490N engines is big,
It is big by ambient temperature effect in star, and bipropellant controls the temperature difference and requires high, and propellant receptacle of the same race
Box temperature difference is within 3 DEG C, and the xenogenesis propellant tank temperature difference is within 5 DEG C.In transfer orbit section and normal in-orbit
Section, tank temperature requirement are inconsistent, it is necessary to adaptive temperature requirement simultaneously.Thus propellant tank thermal control is proposed
Requirements at the higher level, to ensure propulsion subsystem normal work.
To solve the above problems, the present invention provides a kind of engine fuel tank thermal controls apparatus, including：Multilayer knot
Structure, heat insulating mattress, heater and thermistor.
Further, including the sandwich construction is wrapped in the hemisphere face and shell of column, tank peace of the fuel tank
Surface corresponding to loading board upper and lower sides, tank support bar.The sandwich construction is respectively Unit 10, Unit 5,5
The multilayer insulation component of unit, the insulating unit of each multilayer are alternate by two-sided aluminized mylar and polyamide fibre hairnet
Every composition.
Further, the insulating unit of each multilayer is by one layer of 6 μm of two-sided aluminized mylar and one layer of 20d
Polyamide fibre hairnet separately forms.Further, the heat insulating mattress is fiberglass, positioned at the auricle of fuel tank
Between tank installing plate.
Further, the heater includes：Public heater all the way, and installation and the 3 of each tank respectively
Road separate heater.As one embodiment, the heater implements active temperature control to tank, wherein public all the way
With heater, each tank difference additionally mounted 3 tunnel separate heater (2 masters 1 are standby), supply voltage is
42V, install the ball section under tank concentratedly.
Further, the heater is polyimides constantan paper tinsel electric heating sheets.Also include program control control unit and
Remote control unit, to program control control and remote control should be carried out to the heater.Also include temperature control threshold value list
Member, and the temperature control threshold value is modified by noting number mode.
The thermistor corresponds to tank installing plate measuring point, and the thermistor type is MF501 types.
It is understandable to enable the above objects, features and advantages of the present invention to become apparent, below in conjunction with the accompanying drawings to this
The specific embodiment of invention is described in detail.
Fig. 1 is the structural representation of the tank thermal controls apparatus of one embodiment of the invention.Wherein, it is corresponding, 1
For sandwich construction；2 be heat insulating mattress；3 be heater；4 be thermistor；5 be tank.The multilayer
Structure 1 is wrapped in the hemisphere face and shell of column, the installing plate upper and lower sides of tank 5, the support bar of tank 5 of tank 5
On, respectively Unit 10, Unit 5,5 unit multi-layer insulating assemblies.Each multilayer insulation unit is by one layer 6 μm
Two-sided aluminized mylar and one layer of 20d polyamide fibre hairnet separately form；The heat insulating mattress 2 is fiberglass,
Pad is between auricle and tank installing plate, thickness 4mm.
The heater 3 implements active temperature control to tank 5, wherein public heater all the way, each tank 5
Wherein, 3 tunnel separate heater is 21 standby, supply voltages of master to additionally mounted 3 tunnel separate heater respectively
It is 42V, installs the ball section under tank concentratedly.
Further, the installing plate measuring point of the corresponding tank 5 of the thermistor 4, type is MF501 types.
Based on above thermal controls apparatus, tank body and tank during to certain satellite twilight orbit section and in-orbit beginning of lifetime
Between temperature carried out analysis and calculated, model has carried out necessary simplification and it is assumed that satellite basic parameter, such as rail
Road, posture etc. are configured according to general technical requirement.The thermal physical property parameter of satellite thermal control coating and material is chosen
Provide to set by by general technical requirement.
Fig. 2 and Fig. 3 is the temperature curve in each tank lower semisphere section same location unit, the emulation point more than
Analysis result can be seen that tank can maintain the temperature at 20~22 DEG C in twilight orbit section, and in-orbit period can keep
Lower semisphere temperature is at 15~17 DEG C.And it can guarantee that same fuel tank mean temperature difference is no more than 3 DEG C, difference combustion
Expect that tank mean temperature difference is no more than 5 DEG C.Temperature levels meet index request.
Although present disclosure is as above, the present invention is not limited to this.Any those skilled in the art, not
Depart from the spirit and scope of the present invention, can make various changes or modifications, therefore protection scope of the present invention should
It is defined when by claim limited range.
Claims (9)
- A kind of 1. fuel tank thermal controls apparatus, it is characterised in that including：Sandwich construction, heat insulating mattress, heater and Thermistor；The sandwich construction is wrapped in the hemisphere face and shell of column, tank installing plate of the fuel tank Surface corresponding to upper and lower sides, tank support bar.
- 2. fuel tank thermal controls apparatus as claimed in claim 1, it is characterised in that the sandwich construction includes 10 Individual multilayer insulation assembly unit, 5 multilayer insulation assembly units and 5 multilayer insulation assembly units, often Individual multilayer insulation assembly unit is separately made up of two-sided aluminized mylar and polyamide fibre hairnet.
- 3. fuel tank thermal controls apparatus as claimed in claim 2, it is characterised in that the insulating assembly list of each multilayer Member is separately made up of one layer of two-sided aluminized mylar and one layer of polyamide fibre hairnet.
- 4. fuel tank thermal controls apparatus as claimed in claim 1, it is characterised in that the heat insulating mattress is fiberglass, Between the auricle and tank installing plate of fuel tank.
- 5. fuel tank thermal controls apparatus as claimed in claim 1, it is characterised in that the heater includes：One The public heater in road, and installation and 3 tunnel separate heaters of each tank respectively.
- 6. fuel tank thermal controls apparatus as claimed in claim 1, it is characterised in that the heater is polyimides Constantan paper tinsel electric heating sheets.
- 7. fuel tank thermal controls apparatus as claimed in claim 1, it is characterised in that also including program control control unit and Remote control unit, to program control control and remote control should be carried out to the heater.
- 8. fuel tank thermal controls apparatus as claimed in claim 1, it is characterised in that the thermistor corresponds to tank Installing plate measuring point, the thermistor type are MF501 types.
- 9. fuel tank thermal controls apparatus as claimed in claim 1, it is characterised in that also including temperature control threshold cell, The temperature control threshold value is modified by noting number mode.
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107529359B true CN107529359B (en) | 2016-09-07 |
Family
ID=
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN108019620A (en) * | 2017-12-05 | 2018-05-11 | 上海空间推进研究所 | A kind of temperature control liquid alkali metal surface tension propellant tank |
| CN111400837A (en) * | 2020-03-24 | 2020-07-10 | 北京卫星环境工程研究所 | Method, device, equipment and medium for determining installation parameters of propellant tank |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN108019620A (en) * | 2017-12-05 | 2018-05-11 | 上海空间推进研究所 | A kind of temperature control liquid alkali metal surface tension propellant tank |
| CN111400837A (en) * | 2020-03-24 | 2020-07-10 | 北京卫星环境工程研究所 | Method, device, equipment and medium for determining installation parameters of propellant tank |
| CN111400837B (en) * | 2020-03-24 | 2023-07-11 | 北京卫星环境工程研究所 | Method, device, apparatus and medium for determining installation parameters of propellant tank |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR03 | Grant of secret patent right | ||
| DC01 | Secret patent status has been lifted | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160907 |