CN113562199A - Heating structure suitable for spacecraft low-thrust engine - Google Patents
Heating structure suitable for spacecraft low-thrust engine Download PDFInfo
- Publication number
- CN113562199A CN113562199A CN202110769309.7A CN202110769309A CN113562199A CN 113562199 A CN113562199 A CN 113562199A CN 202110769309 A CN202110769309 A CN 202110769309A CN 113562199 A CN113562199 A CN 113562199A
- Authority
- CN
- China
- Prior art keywords
- heating
- engine
- temperature sensor
- loop
- injector
- 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.)
- Granted
Links
- 238000010438 heat treatment Methods 0.000 title claims abstract description 87
- 238000005485 electric heating Methods 0.000 claims abstract description 39
- 238000009413 insulation Methods 0.000 claims abstract description 32
- 229920002379 silicone rubber Polymers 0.000 claims description 9
- 229920000728 polyester Polymers 0.000 claims description 7
- 229920006267 polyester film Polymers 0.000 claims description 7
- 229920001721 polyimide Polymers 0.000 claims description 7
- 239000004744 fabric Substances 0.000 claims description 4
- 239000005340 laminated glass Substances 0.000 claims description 4
- 238000010030 laminating Methods 0.000 claims description 4
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 3
- 239000011888 foil Substances 0.000 claims description 3
- 125000006850 spacer group Chemical group 0.000 claims description 3
- 238000003466 welding Methods 0.000 claims description 3
- 239000000853 adhesive Substances 0.000 claims description 2
- ISWSIDIOOBJBQZ-UHFFFAOYSA-N phenol group Chemical group C1(=CC=CC=C1)O ISWSIDIOOBJBQZ-UHFFFAOYSA-N 0.000 claims description 2
- 239000004945 silicone rubber Substances 0.000 claims 2
- 239000011810 insulating material Substances 0.000 claims 1
- 238000000034 method Methods 0.000 description 3
- 229910052782 aluminium Inorganic materials 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000011217 control strategy Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000003292 glue Substances 0.000 description 2
- 239000012774 insulation material Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 229910052755 nonmetal Inorganic materials 0.000 description 2
- -1 phenolic aldehyde Chemical class 0.000 description 2
- 239000003380 propellant Substances 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 210000002469 basement membrane Anatomy 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000002386 leaching Methods 0.000 description 1
- WABPQHHGFIMREM-UHFFFAOYSA-N lead(0) Chemical compound [Pb] WABPQHHGFIMREM-UHFFFAOYSA-N 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
Images
Classifications
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
The invention provides a heating structure suitable for a spacecraft low-thrust engine, which comprises an electric heating sheet, a temperature sensor, a multilayer heat insulation assembly and a heat insulation gasket, wherein the temperature sensor is arranged on an engine injector which is connected with an electromagnetic valve, one surface of the electric heating sheet is arranged on the electromagnetic valve, and the multilayer heat insulation assembly is arranged on the other surface of the electric heating sheet; the engine injector is arranged on the rack, and the heat insulation gasket is arranged between the engine injector and the rack.
Description
Technical Field
The invention relates to the field of engines for spacecraft propulsion systems, in particular to a heating structure suitable for a spacecraft low-thrust engine, and particularly suitable for a spacecraft two-component engine with low thrust.
Background
A plurality of groups of propellant flow channels are arranged in an injector of a spacecraft engine, and heating measures are needed in a low-temperature environment of a space to ensure that the temperature of propellant in the injector is higher than the freezing point. In the ignition process of the engine, the injector of the engine can reach the high temperature of more than 150 ℃ due to the heat back leaching effect and is often higher than the use temperature of a heater. Accordingly, engine injectors are typically heated using sheathed heaters.
In the prior art, for example, patent document CN106134394B discloses a method for heating an injector of a spacecraft engine, wherein a sheathed heater is installed on the injector of the engine for heating the injector, and the injector of the engine needs to provide a sheathed heater installation groove and fixing structures such as screw holes. For a low-thrust two-component engine, the size of the engine is small, the total heat capacity of a valve is larger than the heat capacity of an injector, and if an armored heater is still used for heating, the whole weight of the engine is increased, and the injector of the engine is designed more complexly.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a heating structure suitable for a spacecraft low-thrust engine.
The heating structure suitable for the spacecraft low-thrust engine comprises an electric heating sheet, a temperature sensor, a multi-layer heat insulation assembly and a heat insulation gasket;
the temperature sensor is arranged on an engine injector, the engine injector is connected with an electromagnetic valve, one surface of the electric heating sheet is arranged on the electromagnetic valve, and the multilayer heat insulation assembly is arranged on the other surface of the electric heating sheet;
the engine injector is mounted on the frame, and the heat insulating gasket is arranged between the engine injector and the frame.
Preferably, the electric heating sheet is a polyimide film type electric heating sheet;
the inside of electric heating piece is provided with main heating circuit and reserve heating circuit, and wherein, the lead wire that main heating circuit, reserve heating circuit have all draws forth in electric heating piece's one end.
Preferably, the electric heating sheet is adhered to the solenoid valve by silicon rubber.
Preferably, the temperature sensor is a surface-adhered temperature sensor, and is fixed by a spot welding layer of titanium alloy foil after being adhered to an engine injector through silicon rubber adhesive.
Preferably, the multi-layer heat insulation assembly is of a structure formed by alternately laminating double-sided aluminum-plated polyester films and polyester nets.
Preferably, the multi-layer heat insulation assembly adopts a structure that 11 layers of double-sided aluminum-plated polyester films and 10 layers of polyester nets are alternately stacked.
Preferably, the heat insulation gasket is made of non-metal heat insulation materials.
Preferably, the heat insulation gasket is made of phenolic aldehyde laminated glass cloth plates.
Preferably, automatic temperature control is adopted, and the automatic temperature control method comprises an engine working mode and an engine storage mode;
when the temperature control threshold value is A in the engine working mode1，A2The temperature sensor of the injector at the head of the engine is lower than A2When the temperature sensor is lower than A, the main heating loop is electrified for heating1When the heating device is used, the main heating loop and the standby heating loop are electrified for heating; temperature sensor higher than A2When the heater is in use, the heaters of the main heating loop and the standby heating loop are powered off;
when the temperature control threshold value is B in the engine storage mode1，B2Engine injector temperature sensor lower than B2When the temperature sensor is lower than B, the main heating loop is electrified for heating1While, the main heating loop is standbyHeating by electrifying the heating loops; temperature sensor higher than B2When the heater is in use, the heaters of the main heating loop and the standby heating loop are both powered off.
Preferably, A1At 10 ℃ A2At 15 ℃ B1At-10 ℃ and B2Is-5 ℃.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention indirectly ensures the temperature of the engine injector by adopting the electromagnetic valve heating measure, cancels the armored heater of the engine injector, can reduce the whole weight of the engine by more than 20 percent, simplifies the design of the engine injector, improves the reliability of the engine heater and solves the temperature requirement of the engine for reliable work.
2. The multilayer heat insulation assembly is compact in structure formed by alternately laminating the double-sided aluminum plated polyester film and the polyester net, can prevent the temperature of the electric heating sheet from losing, and improves the heat insulation effect.
3. The invention can realize automatic temperature control in two modes of an engine working mode and an engine storage mode, can realize a more matched temperature control strategy by switching the work of the two heaters of the main heating loop and the standby heating loop, and is beneficial to fast and accurate temperature regulation and control in a universe environment.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic partial cross-sectional view of the present invention;
fig. 2 is a schematic view of the two-way polyimide film type electric heating sheet.
The figures show that:
1-electric heating plate 5-engine spray pipe
2-temperature sensor 6-Engine injector
3-multilayer heat insulation assembly 7-electromagnetic valve
4-Heat insulating spacer
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
Example 1:
aiming at the defects in the prior art, the invention provides a heating structure suitable for a small thrust engine of a spacecraft in order to reduce the weight of the engine and simplify the design of the engine, and the small thrust engine in the invention particularly refers to an aircraft engine with the thrust smaller than 10N. As shown in fig. 1, the engine thermal insulation structure comprises an electric heating sheet 1, a temperature sensor 2, a multilayer thermal insulation assembly 3 and a thermal insulation gasket 4, wherein the temperature sensor 2 is installed on an engine injector 6, the engine injector 6 is connected with an electromagnetic valve 7, one surface of the electric heating sheet 1 is installed on the electromagnetic valve 7 and used for heating the electromagnetic valve 7, the multilayer thermal insulation assembly 3 is installed on the electric heating sheet 1 and used for preserving heat of the electric heating sheet 1 and preventing heat dissipation of the electric heating sheet 1, and the multilayer thermal insulation assembly 3 preferably adopts a structure formed by alternately overlapping a double-sided aluminum plated polyester film and a polyester net.
The engine injector 6 is mounted on the frame, the heat insulation gasket 4 is arranged between the engine injector 6 and the frame, and the heat insulation gasket 4 is made of non-metal heat insulation materials, so that heat conduction from the head of the engine to the frame can be reduced. The heat insulating gasket 4 is preferably made of a phenolic laminated glass cloth plate.
Specifically, electric heating plate 1 adopts polyimide film type electric heating plate, electric heating plate 1's inside is provided with main heating circuit and reserve heating circuit, and wherein, 4 leads that main heating circuit, reserve heating circuit have all draw forth in electric heating plate 1's one end, make the structure compacter.
The temperature control of the invention adopts automatic temperature control, comprises two modes of an engine working mode and an engine storage mode, and the engine working mode is adoptedThe lower temperature control threshold is A1，A2The temperature sensor of the injector at the head of the engine is lower than A2When the temperature sensor is lower than A, the main heating loop is electrified for heating1When the heating device is used, the main heating loop and the standby heating loop are electrified for heating; temperature sensor higher than A2When the temperature control threshold value is B in the storage mode of the engine1，B2Engine injector temperature sensor lower than B2When the temperature sensor is lower than B, the main heating loop is electrified for heating1When the heating device is used, the main heating loop and the standby heating loop are electrified for heating; temperature sensor higher than B2When the heater is in use, the heaters of the main heating loop and the standby heating loop are both powered off.
Specifically, the electric heating plate 1 is adhered to the electromagnetic valve 7 through silicon rubber, the temperature sensor 2 is a surface-adhered temperature sensor, and is fixed by spot welding 1 layer of titanium alloy foil after being adhered to the engine injector 6 through the silicon rubber.
Example 2:
this embodiment is a preferred embodiment of embodiment 1.
The embodiment provides a heating structure suitable for little thrust engine of spacecraft, electric heating plate 1 adopts double-circuit polyimide film type electric heating plate, and the appearance is the rectangle, and the top layer is the polyimide film, and main heating circuit, 4 leads of heating circuit are drawn forth in heater one end for being equipped with, and electric heating plate 1 installs the cylinder at engine solenoid valve 7, pastes 1 layer of insulating basement membrane at the engine cylinder at first, then coats 1 layer of silicon rubber on electric heating plate 1, pastes electric heating plate 1 at solenoid valve 7's cylinder.
The multilayer heat insulation assembly 3 is arranged on the outer layer of the double-path polyimide film type electric heating sheet 1 and fixed through an aluminized film with glue, and the multilayer heat insulation assembly 3 adopts a structure that 11 layers of double-sided aluminized polyester films and 10 layers of polyester nets are alternately overlapped.
The temperature sensors 2 are symmetrically arranged on the inclined planes on the two sides of the engine injector 6, firstly, a sensing head of the temperature sensor 2 is fixed by 502 glue, then 1 layer of silicon rubber is covered, after the silicon rubber is solidified, 1 layer of titanium foil is integrally spot-welded, and the heat insulation gasket 4 is arranged between a flange of the engine injector 6 and a frame.
The temperature control strategy is automatic temperature control, and two modes are set: engine operating mode and engine storage mode, B1At-10 ℃ and B2At-5 ℃ A1At 10 ℃ A2The temperature of the injector 6 of the engine is indirectly ensured by heating the electromagnetic valve 7 at 15 ℃, the temperature control thresholds of the working mode of the engine are respectively 10 ℃ and 15 ℃, the temperature control thresholds of the storage mode of the engine are-10 ℃ and-5 ℃, and the temperature of the injector 6 of the engine is indirectly ensured by heating the electromagnetic valve 7.
In the embodiment, the heat insulation gasket 4 is made of a phenolic aldehyde laminated glass cloth plate, the shape is rectangular, a through hole is formed in the middle of the heat insulation gasket, and the thickness of the gasket is 5-10 mm.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A heating structure suitable for a spacecraft low-thrust engine is characterized by comprising an electric heating sheet (1), a temperature sensor (2), a multi-layer heat insulation assembly (3) and a heat insulation gasket (4);
the temperature sensor (2) is installed on an engine injector (6), the engine injector (6) is connected with an electromagnetic valve (7), the electric heating sheet (1) is installed on the electromagnetic valve (7), and the multilayer heat insulation assembly (3) is installed on the electric heating sheet (1);
the engine injector (6) is mounted on the frame, and the heat insulation gasket (4) is arranged between the engine injector (6) and the frame.
2. The heating structure suitable for spacecraft low thrust engines, according to claim 1, characterized in that said electric heating sheet (1) is a polyimide film type electric heating sheet;
the electric heating plate is characterized in that a main heating loop and a standby heating loop are arranged inside the electric heating plate (1), wherein leads of the main heating loop and the standby heating loop are led out from one end of the electric heating plate (1).
3. The heating structure for a spacecraft low-thrust engine according to claim 1, characterized in that said electric heating sheet (1) is bonded to said solenoid valve (7) by silicone rubber.
4. The heating structure suitable for the spacecraft low-thrust engine as claimed in claim 1, wherein the temperature sensor (2) is a surface-adhesive temperature sensor, and is fixed by spot welding 1 layer of titanium alloy foil after being adhered to an engine injector (6) through silicone rubber.
5. The heating structure suitable for a spacecraft low thrust engine according to claim 1, characterized in that the multilayer thermal insulation assembly (3) adopts a structure formed by alternately laminating double-sided aluminized polyester films and polyester nets.
6. The heating structure suitable for a spacecraft low thrust engine according to claim 1, characterized in that said multilayer thermal insulation assembly (3) adopts a structure of alternately laminating 11 layers of double-sided aluminized polyester film and 10 layers of polyester mesh.
7. The heating structure for a spacecraft low thrust engine according to claim 1, wherein said insulating spacer (4) is a non-metallic insulating material.
8. The heating structure for a spacecraft low thrust engine according to claim 1, characterized in that said insulating spacer (4) is made of a phenolic laminated glass cloth sheet.
9. The heating structure suitable for the spacecraft low-thrust engine according to claim 2, wherein automatic temperature control is adopted, and the heating structure comprises an engine working mode and an engine storage mode;
when the temperature control threshold value is (A) in the engine working mode1，A2) The temperature sensor of the injector at the head of the engine is lower than A2When the temperature sensor is lower than A, the main heating loop is electrified for heating1When the heating device is used, the main heating loop and the standby heating loop are electrified for heating; temperature sensor higher than A2When the heater is in use, the heaters of the main heating loop and the standby heating loop are powered off;
when the temperature control threshold value is (B) in the engine storage mode1，B2) Engine injector temperature sensor lower than B2When the temperature sensor is lower than B, the main heating loop is electrified for heating1When the heating device is used, the main heating loop and the standby heating loop are electrified for heating; temperature sensor higher than B2When the heater is in use, the heaters of the main heating loop and the standby heating loop are both powered off.
10. Heating structure suitable for a spacecraft low thrust engine, according to claim 9, characterized in that a1At 10 ℃ A2At 15 ℃ B1At-10 ℃ and B2Is-5 ℃.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110769309.7A CN113562199B (en) | 2021-07-07 | 2021-07-07 | Heating structure suitable for spacecraft low thrust engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110769309.7A CN113562199B (en) | 2021-07-07 | 2021-07-07 | Heating structure suitable for spacecraft low thrust engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113562199A true CN113562199A (en) | 2021-10-29 |
| CN113562199B CN113562199B (en) | 2023-08-18 |
Family
ID=78163988
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110769309.7A Active CN113562199B (en) | 2021-07-07 | 2021-07-07 | Heating structure suitable for spacecraft low thrust engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113562199B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001207913A (en) * | 2000-01-25 | 2001-08-03 | Ishikawajima Harima Heavy Ind Co Ltd | Heating system of injector for rocket engine |
| JP2002308200A (en) * | 2001-04-09 | 2002-10-23 | Mitsubishi Electric Corp | Thruster heat insulating bracket |
| CN106134394B (en) * | 2012-06-18 | 2014-10-22 | 上海空间推进研究所 | A kind of heating implementation method of spacecraft engine ejector filler |
| CN109595097A (en) * | 2018-10-29 | 2019-04-09 | 上海空间推进研究所 | Using the liquid oxygen and methane engine and control method of inserted valve |
| CN110933785A (en) * | 2019-11-28 | 2020-03-27 | 中国空间技术研究院 | Intelligent temperature control heater |
-
2021
- 2021-07-07 CN CN202110769309.7A patent/CN113562199B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001207913A (en) * | 2000-01-25 | 2001-08-03 | Ishikawajima Harima Heavy Ind Co Ltd | Heating system of injector for rocket engine |
| JP2002308200A (en) * | 2001-04-09 | 2002-10-23 | Mitsubishi Electric Corp | Thruster heat insulating bracket |
| CN106134394B (en) * | 2012-06-18 | 2014-10-22 | 上海空间推进研究所 | A kind of heating implementation method of spacecraft engine ejector filler |
| CN109595097A (en) * | 2018-10-29 | 2019-04-09 | 上海空间推进研究所 | Using the liquid oxygen and methane engine and control method of inserted valve |
| CN110933785A (en) * | 2019-11-28 | 2020-03-27 | 中国空间技术研究院 | Intelligent temperature control heater |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113562199B (en) | 2023-08-18 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| RU2737048C2 (en) | Heating device and method of its production | |
| US11130559B2 (en) | Heated panels with ballistic structures | |
| US20200015325A1 (en) | Fusion welded positive temperature coefficient heater assemblies | |
| CN103332302B (en) | A kind of separation device thermal controls apparatus and thermal control method thereof | |
| JP2000356358A (en) | Plate structural member of floor surface plate particularly for aircraft | |
| WO2012170198A1 (en) | System and method for insulating frame member | |
| US20030169558A1 (en) | Multi-function carbon composite capacitor electrode | |
| US10101099B2 (en) | Radiator, as well as space vehicle structure comprising such radiator | |
| CN106428642B (en) | A kind of spacecraft thruster open type rotary table heat-proof device | |
| US20170254246A1 (en) | Heating device for a motor vehicle operating fluid tank with a ptc plastic element | |
| CN113562199A (en) | Heating structure suitable for spacecraft low-thrust engine | |
| CN205168943U (en) | Orbit transfer vehicle star sensor temperature on low side is heat accuse device independently | |
| CN106568354B (en) | A kind of heat-preservation cylinder with temperature control function | |
| EP2907757B1 (en) | Radiator, as well as space vehicle structure comprising such a radiator | |
| US20190016482A1 (en) | Radiator, as well as space vehicle structure comprising such radiator | |
| CN203788631U (en) | Low-reflectivity stray-light-eliminating multilayer heat-insulating/heat-conducting assembly | |
| JP7377607B2 (en) | Heat and sound insulation blanket for aircraft | |
| CN213620304U (en) | Thermal control device of flat-plate satellite thruster storage tank | |
| JP2012071514A (en) | Honeycomb sandwich structure composite material, and method for manufacturing honeycomb sandwich structure composite material | |
| US11805573B2 (en) | Flexible resistor | |
| US20220264702A1 (en) | Heater device | |
| CN108820259B (en) | Integral thermal protection device suitable for multidimensional movement of extraterrestrial rotating mechanism | |
| US10800554B2 (en) | Space system | |
| BR102016000131B1 (en) | ENVIRONMENTAL ASPECTS CONTROL SET, AND, SYSTEM TO CONTROL ONE OR MORE ENVIRONMENTAL ASPECTS | |
| CN115642410B (en) | Multilayer heat insulation assembly grounding device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |