CN113942663A - High-performance cold air attitude control engine system based on turbine exhaust pipe heat exchanger - Google Patents
High-performance cold air attitude control engine system based on turbine exhaust pipe heat exchanger Download PDFInfo
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- CN113942663A CN113942663A CN202111278096.4A CN202111278096A CN113942663A CN 113942663 A CN113942663 A CN 113942663A CN 202111278096 A CN202111278096 A CN 202111278096A CN 113942663 A CN113942663 A CN 113942663A
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- cold air
- attitude control
- exhaust pipe
- heat exchanger
- turbine exhaust
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- 238000010438 heat treatment Methods 0.000 claims abstract description 13
- 239000007921 spray Substances 0.000 claims abstract description 12
- 238000007599 discharging Methods 0.000 claims description 3
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 239000002737 fuel gas Substances 0.000 abstract description 2
- 238000012423 maintenance Methods 0.000 abstract description 2
- 238000000034 method Methods 0.000 abstract description 2
- 231100000956 nontoxicity Toxicity 0.000 abstract description 2
- 239000007789 gas Substances 0.000 description 11
- 230000000149 penetrating effect Effects 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- WYTGDNHDOZPMIW-RCBQFDQVSA-N alstonine Natural products C1=CC2=C3C=CC=CC3=NC2=C2N1C[C@H]1[C@H](C)OC=C(C(=O)OC)[C@H]1C2 WYTGDNHDOZPMIW-RCBQFDQVSA-N 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 231100000252 nontoxic Toxicity 0.000 description 1
- 230000003000 nontoxic effect Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
Images
Classifications
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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
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/244—Spacecraft control systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
Abstract
The invention relates to a high-performance cold air attitude control engine system based on a turbine exhaust pipe heat exchanger. The turbine exhaust pipe heat exchanger heats cold air in the cold air pipeline of the cold air attitude control engine and is discharged from the spray pipe to generate thrust. The beneficial effects are as follows: the system meets the requirements of non-toxicity, easy maintenance and storage and repeated use of the reusable carrier rocket; the high-pressure cold air is heated, so that the specific impulse of the spray pipe can be improved, the attitude control engine has higher specific impulse performance, and the attitude control method can be suitable for attitude control with large impulse and large thrust; the working medium generated in the fuel gas generator is used for heating the high-pressure cold air, no additional heating equipment is needed, the space is saved, and the total mass of the system is reduced.
Description
Technical Field
The invention relates to the technical field of cold air attitude control engines in the technical field of aerospace propulsion, in particular to a high-performance cold air attitude control engine system based on a turbine exhaust pipe heat exchanger.
Background
The attitude control engine is an auxiliary power device of a space carrier rocket, has the characteristics of repeated starting, long-pulse steady-state work, short-pulse transient work and the like, and is generally required to be installed to provide rolling direction control torque. The traditional disposable rocket is high in cost and gradually cannot meet the requirements of large-scale and low-cost launching of commercial aerospace, the reusable rocket becomes the key direction of the development of the current carrier rocket, the reusable attitude control engine is required to be non-toxic, safe, reliable, easy to maintain and long-term to store, and only a cold air engine meets the requirements at present. Therefore, for the reusable rocket and the load orbit entering, the attitude control engine needs to adopt a cold air scheme and has higher performance, for example, the specific impulse performance of the cold air engine needs to be improved urgently.
The turbine exhaust pipe heat exchanger is used for pressurizing and heating gas passing through the turbine exhaust pipe heat exchanger by using a turbine, and the heated gas enters a heat exchange cavity to exchange heat with a structure needing heat exchange. If the structure needing heat exchange is a cold air pipeline of the cold air engine, the temperature of a propellant of the cold air engine can be increased undoubtedly, and further the specific impulse of the cold air engine is increased.
Disclosure of Invention
The invention aims at solving the problem that the existing rocket can be repeatedly used and loaded into orbit and needs an attitude control engine to adopt a cold air scheme, and the specific impact performance of the cold air engine is to be improved urgently.
In order to achieve the purpose, the invention provides a high-performance cold air attitude control engine system based on a turbine exhaust pipe heat exchanger, which comprises a cold air attitude control engine provided with a cold air pipeline and the turbine exhaust pipe heat exchanger, wherein the turbine exhaust pipe heat exchanger heats cold air in the cold air pipeline of the cold air attitude control engine and discharges the cold air from a spray pipe to generate thrust.
Furthermore, the turbine exhaust pipe heat exchanger sequentially comprises a turbine air inlet pipeline, a supercharging heating turbine (a turbine shaft and a turbine disc), a heat exchange cavity and a turbine exhaust pipe (a Laval nozzle, and a nozzle outlet of the Laval nozzle is a hot air outlet) along the air flow to sequentially form an integral structure, the cold air pipeline penetrates through the heat exchange cavity, and the cold air is heated through the cold air pipeline penetrating through the heat exchange cavity.
The cold air attitude control engine further comprises an air charging and discharging hand valve arranged on the cold air pipeline along the air flow direction, a cold air cylinder group formed by connecting a plurality of cold air cylinders in parallel, a main path electromagnetic valve, a pressure reducing valve, a plurality of branch path electromagnetic valves and a plurality of corresponding spray pipes.
Specifically, the number of the branch electromagnetic valves is two, and the corresponding branch electromagnetic valves are two.
Preferably, the cold air cylinder group comprises four cylinders connected in parallel.
Preferably, a filter is further arranged on the cold air pipeline between the cold air cylinder group and the main path electromagnetic valve.
Preferably, the warmed cold air duct is a cold air duct on a branch line.
The high-performance cold air attitude control engine system based on the turbine exhaust pipe heat exchanger has the following beneficial effects:
(1) the system meets the requirements of non-toxicity, easy maintenance and storage and repeated use of the reusable carrier rocket;
(2) the high-pressure cold air is heated, so that the specific impulse of the spray pipe can be improved, the attitude control engine has higher specific impulse performance, and the attitude control method can be suitable for attitude control with large impulse and large thrust;
(3) the working medium generated in the fuel gas generator is used for heating the high-pressure cold air, no additional heating equipment is needed, the space is saved, and the total mass of the system is reduced.
Drawings
FIG. 1 is a schematic diagram of a high-performance cold air attitude control engine system based on a turbine exhaust pipe heat exchanger according to the present invention.
Wherein: 1-turbine exhaust pipe heat exchanger, 11-turbine inlet pipeline, 12-supercharging heating turbine, 121-turbine shaft, 122-turbine disc, 13-heat exchange cavity, 14-turbine exhaust pipe, 2-cold air attitude control engine, 21-cold air pipeline, 211-serpentine pipeline, 22-inflation and deflation hand valve, 23-cold air cylinder, 24-main path electromagnetic valve, 25-pressure reducing valve, 26-branch path electromagnetic valve, 27-cold air spray pipe and 28-filter.
Detailed Description
The invention is further described with reference to specific embodiments.
It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
It should be noted that in the description of the present invention, the terms "lateral", "longitudinal", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
The invention provides a high-performance cold air attitude control engine system based on a turbine exhaust pipe heat exchanger, which comprises a cold air attitude control engine provided with a cold air pipeline and the turbine exhaust pipe heat exchanger, wherein the turbine exhaust pipe heat exchanger heats cold air in the cold air pipeline of the cold air attitude control engine and discharges the cold air from a spray pipe to generate thrust.
The turbine exhaust pipe heat exchanger sequentially comprises a turbine air inlet pipeline, a supercharging heating turbine (comprising a turbine shaft and a turbine disc), a heat exchange cavity and a turbine exhaust pipe (a Laval nozzle, and a nozzle outlet of the Laval nozzle is a hot air outlet) along air flow, and sequentially forms an integral structure, the cold air pipeline penetrates through the heat exchange cavity, the cold air is heated through the cold air in the cold air pipeline penetrating through the heat exchange cavity, the heat exchange cavity is a hollow circular tubular cavity, and the heated cold air pipeline is a cold air pipeline on a branch road. The turbine shaft and the turbine disc are arranged in the closed turbine air inlet shell, and the turbine air inlet pipeline, the supercharging heating turbine arranged in the closed turbine air inlet shell, the heat exchange cavity and the turbine exhaust pipe form a communicated air flow space.
Wherein the turbine inlet pipeline enters the gas generated by the reaction of the gas generator on the rocket.
The heat exchange cavity is a hollow circular tubular cavity, the gas in the heat exchange cavity carries out heat exchange with a cold air pipeline needing heat exchange, and cold air in the cold air pipeline is heated. The cold air passes through the exhaust pipe heat exchanger, the energy of the air is increased, and the specific impulse of the cold air attitude control engine is improved.
The turbine exhaust pipe is a Laval nozzle, and the outlet of the Laval nozzle is the hot gas outlet.
The cold air attitude control engine further comprises an air charging and discharging hand valve arranged on the cold air pipeline along the air flow direction, a cold air cylinder group formed by connecting a plurality of cold air cylinders in parallel, a main path electromagnetic valve, a pressure reducing valve, a plurality of branch path electromagnetic valves and a plurality of corresponding spray pipes. The pressure reducing valve is arranged to ensure the pressure in front of the spray pipe to be stable. The two spray pipes are controlled by one electromagnetic valve to generate attitude control torque in the rolling direction (the number of the electromagnetic valves is reduced, and the starting synchronism of the engine is ensured).
The number of the branch electromagnetic valves is two, and the number of the corresponding branch electromagnetic valves is two.
The cold air cylinder group comprises four parallel air cylinders. The parallel gas cylinder group is convenient to install and low in cost compared with one gas cylinder.
And a filter is also arranged on the cold air pipeline between the cold air cylinder group and the main path electromagnetic valve. The filter is arranged at the outlet of the gas cylinder, so that the normal work of the pressure reducing valve and the electromagnetic valve is ensured, and otherwise, the impurities can cause the valve to be blocked.
The warmed cold air duct is a cold air duct on a branch line, such as a serpentine duct shown in fig. 1.
The turbine exhaust pipe heat exchanger and the cold air attitude control engine are integrally or separately designed, processed and formed.
The split design processing molding is to divide the system into three parts: the device comprises a supercharging and heating gas end (comprising a turbine air inlet pipeline, a supercharging and heating turbine, a turbine air inlet shell and other parts), a heat exchanger (comprising a heat exchange cavity, a heat exchange pipeline, namely a cold air pipeline, a turbine exhaust pipe and the like) and a cold air engine, wherein the supercharging and heating gas end, the heat exchanger and the cold air engine are respectively processed and then connected through flanges.
Claims (7)
1. The high-performance cold air attitude control engine system based on the turbine exhaust pipe heat exchanger is characterized by comprising a cold air attitude control engine with a cold air pipeline and the turbine exhaust pipe heat exchanger, wherein the turbine exhaust pipe heat exchanger heats cold air in the cold air pipeline of the cold air attitude control engine and discharges the cold air from a spray pipe to generate thrust.
2. The high performance cold air attitude control engine system based on the turbine exhaust pipe heat exchanger as claimed in claim 1, wherein the turbine exhaust pipe heat exchanger comprises a turbine air inlet pipeline, a pressure boosting heating turbine, a heat exchange cavity and a turbine exhaust pipe in sequence along the air flow to form an integral structure, the cold air pipeline passes through the heat exchange cavity, and the cold air is warmed through the cold air pipeline passing through the heat exchange cavity.
3. The high-performance cold air attitude control engine system based on the turbine exhaust pipe heat exchanger is characterized by further comprising an air charging and discharging hand valve arranged on a cold air pipeline along the air flow direction, a cold air cylinder group formed by connecting a plurality of cold air cylinders in parallel, a main path electromagnetic valve, a pressure reducing valve, a plurality of branch path electromagnetic valves and a plurality of corresponding groups of spray pipes.
4. The high-performance cold air attitude control engine system based on the turbine exhaust pipe heat exchanger is characterized in that the number of the electromagnetic valves of the plurality of branches is two, and the number of the corresponding branches is two.
5. The high performance cold gas attitude control engine system based on the turbine exhaust pipe heat exchanger as claimed in claim 1, wherein the cold gas cylinder group includes four cylinders connected in parallel.
6. The high-performance cold air attitude control engine system based on the turbine exhaust pipe heat exchanger is characterized in that a filter is further arranged on a cold air pipeline between the cold air cylinder group and the main path electromagnetic valve.
7. The turbine exhaust pipe heat exchanger based high performance cold air attitude control engine system according to claim 2, characterized in that the warmed cold air duct is a cold air duct on a branch line.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111278096.4A CN113942663A (en) | 2021-10-30 | 2021-10-30 | High-performance cold air attitude control engine system based on turbine exhaust pipe heat exchanger |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111278096.4A CN113942663A (en) | 2021-10-30 | 2021-10-30 | High-performance cold air attitude control engine system based on turbine exhaust pipe heat exchanger |
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| Publication Number | Publication Date |
|---|---|
| CN113942663A true CN113942663A (en) | 2022-01-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111278096.4A Pending CN113942663A (en) | 2021-10-30 | 2021-10-30 | High-performance cold air attitude control engine system based on turbine exhaust pipe heat exchanger |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114162361A (en) * | 2022-02-14 | 2022-03-11 | 中国人民解放军战略支援部队航天工程大学 | Aerodynamic vector propulsion system of satellite ground simulation device |
-
2021
- 2021-10-30 CN CN202111278096.4A patent/CN113942663A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114162361A (en) * | 2022-02-14 | 2022-03-11 | 中国人民解放军战略支援部队航天工程大学 | Aerodynamic vector propulsion system of satellite ground simulation device |
| CN114162361B (en) * | 2022-02-14 | 2022-05-06 | 中国人民解放军战略支援部队航天工程大学 | Aerodynamic vector propulsion system of satellite ground simulation device |
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