CN113562199B - Heating structure suitable for spacecraft low thrust engine - Google Patents
Heating structure suitable for spacecraft low thrust engine Download PDFInfo
- Publication number
- CN113562199B CN113562199B CN202110769309.7A CN202110769309A CN113562199B CN 113562199 B CN113562199 B CN 113562199B CN 202110769309 A CN202110769309 A CN 202110769309A CN 113562199 B CN113562199 B CN 113562199B
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- engine
- heating
- temperature sensor
- heat insulation
- loop
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- 238000010438 heat treatment Methods 0.000 title claims abstract description 78
- 238000005485 electric heating Methods 0.000 claims abstract description 41
- 238000009413 insulation Methods 0.000 claims abstract description 34
- 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
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 3
- 239000011888 foil Substances 0.000 claims description 3
- ISWSIDIOOBJBQZ-UHFFFAOYSA-N phenol group Chemical group C1(=CC=CC=C1)O ISWSIDIOOBJBQZ-UHFFFAOYSA-N 0.000 claims description 3
- 238000003466 welding Methods 0.000 claims description 3
- 239000000853 adhesive Substances 0.000 claims 1
- 239000011810 insulating material Substances 0.000 claims 1
- 239000010410 layer Substances 0.000 description 20
- 239000004945 silicone rubber Substances 0.000 description 3
- 238000011217 control strategy Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 230000000694 effects Effects 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
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- JJWKPURADFRFRB-UHFFFAOYSA-N carbonyl sulfide Chemical compound O=C=S JJWKPURADFRFRB-UHFFFAOYSA-N 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- -1 phenolic aldehyde Chemical class 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 238000002791 soaking Methods 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 239000002344 surface layer Substances 0.000 description 1
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 application provides a heating structure suitable for a spacecraft low-thrust engine, which comprises an electric heating plate, a temperature sensor, a multilayer heat insulation assembly and a heat insulation gasket, wherein the temperature sensor is arranged on an engine injector, the engine injector is connected with an electromagnetic valve, one surface of the electric heating plate is arranged on the electromagnetic valve, and the multilayer heat insulation assembly is arranged on the other surface of the electric heating plate; the engine injector is arranged on the frame, and the heat insulation gasket is arranged between the engine injector and the frame.
Description
Technical Field
The application relates to the field of engines for spacecraft propulsion systems, in particular to a heating structure suitable for a low-thrust engine of a spacecraft, and particularly relates to a heating structure suitable for a low-thrust dual-component engine of a spacecraft.
Background
In the space low-temperature environment, heating measures are needed to ensure that the temperature of the propellant in the injector is higher than the freezing point. During engine ignition, the engine injector can reach a high temperature of more than 150 ℃ due to the hot return soaking effect, and is often higher than the service temperature of the heater. Therefore, engine injectors are typically heated using sheathed heaters.
In the prior art, as in patent document CN106134394B, a method for realizing heating of an engine injector of a spacecraft is disclosed, an armored heater is installed on the engine injector for heating the injector, and the engine injector is required to be provided with an armored heater installation groove, screw holes and other fixing structures. For a low-thrust dual-component engine, the engine is smaller in size, the total heat capacity of the valve is larger than that of the injector, and if the armored heater is still adopted for heating, the overall weight of the engine is increased, and the design of the injector of the engine is complex.
Disclosure of Invention
Aiming at the defects in the prior art, the application aims to provide a heating structure suitable for a low-thrust engine of a spacecraft.
The application provides a heating structure suitable for a spacecraft low-thrust engine, which comprises an electric heating plate, a temperature sensor, a multi-layer heat insulation assembly and a heat insulation gasket, wherein the electric heating plate is arranged on the electric heating plate;
the temperature sensor is arranged on the engine injector, the engine injector is connected with the 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 insulation gasket is arranged between the engine injector and the frame.
Preferably, the electric heating sheet adopts a polyimide film type electric heating sheet;
the electric heating plate is internally provided with a main heating loop and a standby heating loop, wherein leads of the main heating loop and the standby heating loop are led out at one end of the electric heating plate.
Preferably, the electric heating plate is adhered to the electromagnetic valve through silicone rubber.
Preferably, the temperature sensor is a surface-mounted temperature sensor, and the titanium alloy foil of the spot welding layer is fixed after being stuck to the engine injector through silicon rubber.
Preferably, the multi-layer heat insulation assembly adopts a structure formed by alternately overlapping double-sided aluminized polyester films and polyester nets.
Preferably, the multi-layer heat insulation assembly adopts a structure that 11 layers of double-sided aluminized polyester films and 10 layers of polyester nets are alternately overlapped.
Preferably, the heat insulation gasket is made of non-metal heat insulation materials.
Preferably, the insulation blanket is made from phenolic laminated glass cloth sheets.
Preferably, automatic temperature control is adopted, including an engine operating mode and an engine storage mode;
when the temperature control threshold value is A in the engine working mode 1 ，A 2 The engine head injector temperature sensor is lower than A 2 When the main heating loop is electrified to heat, the temperature sensor is lower than A 1 When the heating device is used, the main heating loop and the standby heating loop are electrified to heat; the temperature sensor is higher than A 2 When the heating device is in use, the two paths of 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 mode 1 ，B 2 The temperature sensor of the engine injector is lower than B 2 When the main heating loop is electrified to heat, the temperature sensor is lower than B 1 When the heating device is used, the main heating loop and the standby heating loop are electrified to heat; the temperature sensor is higher than B 2 And when the heating device is in a power-off state, the two heaters of the main heating loop and the standby heating loop are powered off.
Preferably, A 1 At 10 ℃, A 2 At 15 ℃, B 1 at-10deg.C, B 2 Is-5 ℃.
Compared with the prior art, the application has the following beneficial effects:
1. the application indirectly guarantees the temperature of the engine injector by adopting the electromagnetic valve heating measure, cancels the armored heater of the engine injector, can lighten 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 reliable operation of the engine.
2. The multi-layer heat insulation assembly is compact in structure formed by alternately overlapping the double-sided aluminized polyester films and the polyester nets, can prevent the temperature of the electric heating plate from being lost, and improves the heat insulation effect.
3. According to the application, automatic temperature control can be realized in two modes of an engine working mode and an engine storage mode, and a more matched temperature control strategy can be realized through working switching of two paths of heaters of a main heating loop and a standby heating loop, so that the rapid and accurate temperature regulation and control in a cosmic environment are facilitated.
Drawings
Other features, objects and advantages of the present application will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a schematic view in partial cross-section of the present application;
FIG. 2 is a schematic diagram of the two-way polyimide film type electric heater strip.
The figure shows:
1-electric heating sheet 5-engine spray pipe
2-temperature sensor 6-engine injector
3-multilayer heat insulation assembly 7-electromagnetic valve
4-heat insulation gasket
Detailed Description
The present application will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the present application, but are not intended to limit the application in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present application.
Example 1:
aiming at the defects in the prior art, the application provides a heating structure suitable for a spacecraft low-thrust engine in order to lighten the weight of the engine and simplify the design of the engine, and the low-thrust engine in the application particularly refers to an aeroengine with thrust less than 10N. As shown in fig. 1, the electric heating plate comprises an electric heating plate 1, a temperature sensor 2, a multi-layer heat insulation component 3 and a heat insulation gasket 4, wherein the temperature sensor 2 is arranged on an engine injector 6, the engine injector 6 is connected with an electromagnetic valve 7, one surface of the electric heating plate 1 is arranged on the electromagnetic valve 7 and used for heating the electromagnetic valve 7, the multi-layer heat insulation component 3 is arranged on the electric heating plate 1 and used for preserving heat of the electric heating plate 1 and preventing heat dissipation of the electric heating plate 1, and the multi-layer heat insulation component 3 preferably adopts a structure formed by alternately overlapping a double-sided aluminized polyester film and a polyester net.
The engine injector 6 is arranged 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 a nonmetal heat insulation material, so that heat conduction from the engine head to the frame can be reduced. The insulating spacer 4 is preferably made of phenolic laminated glass cloth plates.
Specifically, the electric heating plate 1 adopts a polyimide film type electric heating plate, and a main heating loop and a standby heating loop are arranged in the electric heating plate 1, wherein 4 leads of the main heating loop and the standby heating loop are led out at one end of the electric heating plate 1, so that the structure is more compact.
The temperature control of the application adopts automatic temperature control, which comprises two modes of an engine working mode and an engine storage mode, when the temperature control threshold value is A in the engine working mode 1 ，A 2 The engine head injector temperature sensor is lower than A 2 When the main heating loop is electrified to heat, the temperature sensor is lower than A 1 When the heating device is used, the main heating loop and the standby heating loop are electrified to heat; the temperature sensor is higher than A 2 When the engine is in the storage mode, the temperature control threshold is B 1 ，B 2 The temperature sensor of the engine injector is lower than B 2 When the main heating loop is electrified to heat, the temperature sensor is lower than B 1 When the heating device is used, the main heating loop and the standby heating loop are electrified to heat; the temperature sensor is higher than B 2 And when the heating device is in a power-off state, the two heaters of the main heating loop and the standby heating loop are powered off.
Specifically, the electric heating plate 1 is adhered to the electromagnetic valve 7 through silicone rubber, the temperature sensor 2 is a surface adhesion type temperature sensor, and after being adhered to the engine injector 6 through silicone rubber, the 1-layer titanium alloy foil is fixed through spot welding.
Example 2:
this embodiment is a preferable example of embodiment 1.
The heating structure suitable for the spacecraft low-thrust engine is characterized in that the electric heating plate 1 is a double-path polyimide film type electric heating plate, the shape of the electric heating plate is rectangular, the surface layer of the electric heating plate is a polyimide film, 4 leads of a main heating loop and a standby heating loop are led out at one end of a heater, the electric heating plate 1 is arranged on the cylindrical surface of an electromagnetic valve 7 of the engine, firstly, 1 layer of insulating base film is adhered to the cylindrical surface of the engine, then 1 layer of silicon rubber is coated on the electric heating plate 1, and the electric heating plate 1 is adhered to the cylindrical surface of the electromagnetic valve 7.
The multi-layer heat insulation component 3 is arranged on the outer layer of the double-path polyimide film type electric heating sheet 1 and is fixed through the glued aluminized films, and the multi-layer heat insulation component 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 inclined planes on two sides of the engine injector 6, firstly, the sensitive heads of the temperature sensors 2 are 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 and a frame of the engine injector 6.
The temperature control strategy is automatic temperature control, and two modes are set: engine operating mode and engine storage mode, B 1 at-10deg.C, B 2 At-5 ℃, A 1 At 10 ℃, A 2 The temperature of the engine injector 6 is indirectly ensured by heating the electromagnetic valve 7 at 15 ℃, the temperature control threshold of the engine working mode is 10 ℃ and 15 ℃ respectively, and the temperature control threshold of the engine storage mode is-10 ℃ and-5 ℃, and the temperature of the engine injector 6 is indirectly ensured by heating the electromagnetic valve 7.
The heat insulation gasket 4 is made of phenolic aldehyde laminated glass cloth plates, the appearance is rectangular, a through hole is formed in the middle of the heat insulation gasket, and the thickness of the heat insulation gasket is 5-10 mm.
In the description of the present application, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present application.
The foregoing describes specific embodiments of the present application. It is to be understood that the application is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the application. The embodiments of the application and the features of the embodiments may be combined with each other arbitrarily without conflict.
Claims (6)
1. The heating structure suitable for the low-thrust engine of the spacecraft is characterized by comprising an electric heating plate (1), a temperature sensor (2), a multi-layer heat insulation assembly (3) and a heat insulation gasket (4), wherein the low-thrust engine refers to an aeroengine with thrust less than 10N;
the temperature sensor (2) is arranged on the engine injector (6), the engine injector (6) is connected with the electromagnetic valve (7), the electric heating sheet (1) is adhered to the electromagnetic valve (7) through silicon rubber, the multi-layer heat insulation assembly (3) is arranged on the electric heating sheet (1), the electric heating sheet (1) adopts a polyimide film type electric heating sheet, and a main heating loop and a standby heating loop are arranged inside the electric heating sheet (1);
the engine injector (6) is arranged on the frame, and the heat insulation gasket (4) is arranged between the engine injector (6) and the frame;
the multi-layer heat insulation assembly (3) adopts a structure formed by alternately overlapping a double-sided aluminized polyester film and a polyester net, the temperature sensor (2) is a surface-adhesive temperature sensor, and after being adhered to an engine injector (6) through silicon rubber, 1 layer of titanium alloy foil is fixed by spot welding;
the automatic temperature control is adopted, and the automatic temperature control comprises an engine working mode and an engine storage mode;
when the temperature is controlled in the engine working modeIs (A) 1 ，A 2 ) The engine head injector temperature sensor is lower than A 2 When the main heating loop is electrified to heat, the temperature sensor is lower than A 1 When the heating device is used, the main heating loop and the standby heating loop are electrified to heat; the temperature sensor is higher than A 2 When the heating device is in use, the two paths of heaters of the main heating loop and the standby heating loop are powered off;
when the temperature control threshold value in the engine storage mode is (B 1 ，B 2 ) The temperature sensor of the engine injector is lower than B 2 When the main heating loop is electrified to heat, the temperature sensor is lower than B 1 When the heating device is used, the main heating loop and the standby heating loop are electrified to heat; the temperature sensor is higher than B 2 And when the heating device is in a power-off state, the two heaters of the main heating loop and the standby heating loop are powered off.
2. The heating structure for a low thrust engine of a spacecraft according to claim 1, wherein the main heating circuit and the standby heating circuit have leads led out at one end of the electric heating plate (1).
3. The heating structure suitable for a low thrust engine of a spacecraft according to claim 1, wherein the multi-layer 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.
4. The heating structure for a low thrust engine of a spacecraft according to claim 1, wherein said insulating pad (4) is made of a non-metallic insulating material.
5. The heating structure for a low thrust engine of a spacecraft according to claim 1, characterized in that said insulating gasket (4) is made of phenolic laminated glass cloth.
6. The heating structure for a low thrust engine of a spacecraft of claim 1, wherein a 1 At 10 ℃, A 2 Is 15℃，B 1 at-10deg.C, B 2 Is-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 CN113562199A (en) | 2021-10-29 |
| CN113562199B true CN113562199B (en) | 2023-08-18 |
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| 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 |
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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 |
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| Publication number | Publication date |
|---|---|
| CN113562199A (en) | 2021-10-29 |
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