CN113294242A - Layout of built-in control circuit board of microminiature aviation turbine engine - Google Patents
Layout of built-in control circuit board of microminiature aviation turbine engine Download PDFInfo
- Publication number
- CN113294242A CN113294242A CN202110530808.0A CN202110530808A CN113294242A CN 113294242 A CN113294242 A CN 113294242A CN 202110530808 A CN202110530808 A CN 202110530808A CN 113294242 A CN113294242 A CN 113294242A
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- Prior art keywords
- circuit board
- control circuit
- turbine engine
- engine
- layout
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K5/00—Casings, cabinets or drawers for electric apparatus
- H05K5/02—Details
- H05K5/0217—Mechanical details of casings
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K5/00—Casings, cabinets or drawers for electric apparatus
- H05K5/02—Details
- H05K5/03—Covers
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/14—Mounting supporting structure in casing or on frame or rack
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/20845—Modifications to facilitate cooling, ventilating, or heating for automotive electronic casings
- H05K7/20863—Forced ventilation, e.g. on heat dissipaters coupled to components
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Toys (AREA)
Abstract
The invention relates to a layout of a built-in control circuit board of a microminiature aircraft turbine engine, which comprises the control circuit board, wherein the control circuit board is fixed on a compressor impeller casing of the engine, and a fairing of the engine covers the control circuit board. According to the invention, the control chip module and the driving module of the microminiature aircraft turbine engine are integrated together, and finally the control circuit board is integrated in the engine fairing, so that the number of external equipment and accessories of the engine is reduced, the system weight of the microminiature aircraft turbine engine is effectively reduced, and the thrust-weight ratio is improved; the system device can accelerate the heat dissipation of the circuit board through gas flow, and effectively reduce the temperature of the circuit board; the system device has better stability and reliability.
Description
Technical Field
The invention relates to the technical field of microminiature aviation turbine engines, in particular to a layout of a built-in control circuit board of a microminiature aviation turbine engine.
Background
The microminiature aviation turbine engine can be divided into a microminiature turbojet engine, a microminiature turboprop engine, a microminiature turboshaft engine and the like; the microminiature turbojet engine is characterized in that high-temperature and high-pressure gas generated by combustion work of air which works through a centrifugal compressor and a diffuser in a combustion chamber drives a turbine to rotate at a high speed, and finally the gas is ejected at a high speed from a tail nozzle to generate thrust through ejected high-speed airflow; the core parts of the micro turboprop engine and the micro turboshaft engine are similar to those of the micro turbojet engine, and are different from the micro turboprop engine in that the core parts of the micro turboprop engine and the micro turboshaft engine provide power for a high-speed aircraft through output shaft power. The microminiature turbine engine has the advantages of precise structure, small volume, large thrust-weight ratio, high combustion efficiency and the like, is mainly used for providing required power for unmanned aerial vehicles, flying missiles, target planes, light airplanes or personal aircrafts and the like, and can also provide power and the like for ground devices.
Compared with the heart of an aircraft, the built-in control circuit system of the microminiature aircraft turbine engine can be compared with a neural network system, and particularly plays an important role in ensuring the stable work of the aircraft in the states of realizing starting, climbing, emergency maneuvering and the like. The existing engine control equipment of the same type is arranged outside an engine, the number of system accessories is large, the improper installation and fixing modes of the system accessories bring risk and hidden troubles to the stable work of the engine, meanwhile, a certain amount of cable harnesses and connecting connectors are needed when the system accessories are connected with an engine body, the arrangement brings more extra weight to the engine, and the thrust-weight ratio performance of the engine is reduced. Therefore, a set of small built-in control circuit system is designed in the micro aerial turbine engine, so that the weight of the micro aerial turbine engine can be effectively reduced, the internal structure is simplified, and the thrust-weight ratio is improved; thereby ensuring to provide reliable guarantee for the long-time stable work of the aircraft engine.
Disclosure of Invention
Aiming at the defects of the prior art, the invention aims to provide the layout of the built-in control circuit board of the microminiature aviation turbine engine, and the device realizes the stable control of the microminiature aviation turbine engine (turbojet, turboprop and turboshaft engine) in the flight envelope of the airplane; the system also obviously reduces the number of external equipment and system accessories of the microminiature aircraft turbine engine, greatly integrates the control system on an internal circuit board of the engine, simultaneously positively integrates the control module and the driving module of the microminiature aircraft turbine engine, designs the space geometry of a compressor impeller casing and a fairing of the microminiature aircraft turbine engine into a fan-shaped circuit board shape, and arranges a gap between the front edge of the compressor impeller casing and the fairing of the microminiature aircraft turbine engine based on the layout, when the engine works, the air in the cavities of the fairing and the compressor impeller casing can be sucked into the air compressor to participate in combustion through the gap by the air compressor of the engine, and simultaneously, cold air is sucked in through an air inlet of the fairing, and the heat generated by the work of the circuit board and the heat conducted by the engine casing are taken away by the air flow in the cavities of the fairing and the compressor impeller casing, effectively reduce the circuit board temperature, provide stability and reliability, economic performance is good, simple structure.
The invention is realized by the following technical scheme.
A layout of a built-in control circuit board of a microminiature aircraft turbine engine comprises the control circuit board, wherein the control circuit board is fixed on a compressor impeller casing of the engine, and a fairing of the engine covers the control circuit board.
Preferably, an air inlet gap is provided between the leading edge of the compressor wheel casing and the fairing.
Preferably, the control circuit board is a fan-shaped circuit board with a fan-shaped geometric shape.
Preferably, the control circuit board is provided with a fixed seat, and the compressor impeller casing is provided with a mounting hole corresponding to the fixed seat.
Preferably, the number of the fixing seats is at least three, two of the fixing seats are located at two ends of the control circuit board, and the rest of the fixing seats are located at any position between the two ends of the control circuit board.
Preferably, the fixing seats are uniformly distributed.
Specifically, the control circuit board is provided with a rotating speed measuring module, an exhaust temperature measuring module, an engine control module and an oil valve control module.
Specifically, the rotating speed measuring module comprises a rotating speed measuring detector and a rotating speed measuring joint.
Specifically, the exhaust temperature measurement module comprises an exhaust temperature measurer and an exhaust temperature measurer joint.
Specifically, the engine control module comprises a control chip module, a driving module and a control module joint.
Specifically, the fuel valve control module comprises a main fuel valve control module, an ignition fuel valve control module and a fuel valve power supply connector.
Specifically, the control circuit board comprises a starting motor connector and an engine communication and power supply socket, the engine communication and power supply socket is arranged on the side face of the control circuit board, and a socket hole corresponding to the engine communication and power supply socket is formed in the fairing.
Compared with the prior art, the invention has the advantages that:
1. according to the invention, the control circuit board of the microminiature aircraft turbine engine is integrated in the inner part of the fairing of the microminiature aircraft turbine engine, so that the number of external equipment and system accessories of the microminiature aircraft turbine engine is reduced, the overall weight of the microminiature aircraft turbine engine is effectively reduced, the overall structure of the microminiature aircraft turbine engine is simplified, and the thrust-weight ratio of the microminiature aircraft turbine engine is greatly improved;
2. according to the invention, a control module and a driving module of the microminiature aircraft turbine engine are integrated together, and are designed into a fan-shaped circuit board according to the space geometry of the compressor impeller casing and the fairing, so that the internal space between the fairing and the compressor impeller casing is fully utilized;
3. based on the layout, a gap is arranged between the front edge of the compressor impeller casing and the fairing, when the micro-miniature aero-turbine engine works, the engine compressor can suck air in cavities of the fairing and the compressor impeller casing into the compressor through the gap to participate in combustion, meanwhile, cold air enters through an air inlet of the fairing, and air flow in the cavities of the fairing and the compressor impeller casing takes away heat generated by self work on a circuit board and heat conducted by the engine casing, so that the temperature of the circuit board is effectively reduced, and stability and reliability are provided.
Drawings
FIG. 1 is a schematic diagram of a built-in control circuit board layout and an efficient heat dissipation device according to the present invention;
FIG. 2 is a detailed view of the layout of the built-in control circuit board and the efficient heat dissipation device of the present invention;
FIG. 3 is a schematic top view of the built-in circuit board of the present invention;
FIG. 4 is a schematic view of the outer cowl of the present invention;
FIG. 5 is an enlarged view of H in FIG. 4 of the present invention;
FIG. 6 is a schematic view of a compressor wheel case of the present invention;
FIG. 7 is a schematic view of the present invention installed on a microminiature aircraft turbine engine;
the parts in the drawings are numbered as follows:
1: control circuit board, 11: fixing base, 12: fixing seats a, 13: fixing seats b, 14: fixing seats c and 15: starting a motor connector, 16: engine communication and power supply socket, 17: an air intake gap;
2: rotation speed measurement module, 21: rotation speed measurement detector, 22: a rotational speed measuring joint;
3: exhaust temperature measurement module, 31: exhaust gas temperature measuring device, 32: an exhaust temperature measurer fitting;
4: engine control module, 41: control chip module, 42: drive module, 43: a control module joint;
5: oil valve control module, 51: main fuel valve control module, 52: ignition oil valve control module, 53: an oil valve power supply connector;
6: compressor impeller casing, 61: mounting hole, 62: a compressor impeller casing leading edge;
7: cowl, 71: and a socket hole.
Detailed Description
The invention is further described with reference to the following drawings and specific examples, which are not intended to be limiting.
Referring to fig. 1 to 7, a layout of a built-in control circuit board of a micro-miniature aircraft turbine engine is characterized by comprising a control circuit board 1, wherein the control circuit board 1 is fixed on a compressor impeller casing 6 of the engine, and a fairing 7 of the engine covers the control circuit board 1, so that the control circuit board 1 is arranged in the fairing 7.
In a preferred embodiment, an air inlet gap 17 is provided between the compressor wheel case leading edge 62 and the fairing 7. An air inlet gap 17 is arranged between the front edge 62 of the impeller casing of the compressor and the fairing 7, when the micro-miniature aero-turbine engine works, the air in cavities of the fairing 7 and the impeller casing of the centrifugal compressor can be sucked into the centrifugal compressor through the air inlet gap 17 to participate in combustion, meanwhile, cold air is sucked in through an air inlet of the fairing 7, and the air flow in the cavities of the fairing 7 and the impeller casing of the centrifugal compressor takes away heat generated by the self-work of the control circuit board 1 and heat conducted by the engine casing, so that the temperature of the control circuit board 1 can be effectively reduced, and the stability and the reliability of the control circuit board 1 are ensured.
As a preferred embodiment, the control circuit board 1 is a fan-shaped circuit board with a fan-shaped geometry.
As a preferred embodiment, a fixing seat 11 is arranged on the control circuit board 1, and a mounting hole 61 corresponding to the fixing seat 11 is arranged on the compressor impeller casing 6.
As a preferred embodiment, there are at least three fixing seats 11, two fixing seats 11 are located at two ends of the control circuit board 1, and the rest fixing seats 11 are located at any position between two ends of the control circuit board 1; preferably, the fixed seats 11 are uniformly distributed; the embodiment is specifically provided with three fixing seats 11, wherein two fixing seats 11 are located at two ends of the control circuit board 1, the other fixing seat 11 is located in the middle of the control circuit board 1, the three fixing seats 11 are specifically a fixing seat a12, a fixing seat b13 and a fixing seat c14, and the fixing seat a12, the fixing seat b13 and the fixing seat c14 can stably fix the control circuit board 1 inside the fairing 7 of the micro aerial turbine engine, so that looseness cannot occur.
As a specific embodiment, the control circuit board 1 is provided with a rotation speed measuring module 2, an exhaust temperature measuring module 3, an engine control module 4 and an oil valve control module 5.
As a specific embodiment, the rotation speed measuring module 2 comprises a rotation speed measuring detector 21 and a rotation speed measuring joint 22; the rotating speed measuring detector 21 is a programmed highly integrated micro-miniature component and is arranged on the control circuit board 1, the rotating speed measuring detector is used for measuring the rotating speed of the rotor core part of the micro-miniature aviation turbine engine, usually, the centrifugal compressor is coaxially connected with the turbine, and therefore, the rotating speed measuring detector has the same rotating speed, the rotating speed measuring connector 22 can be used for independently measuring the rotating speed of the centrifugal compressor, and the rotating speed measuring connector is communicated through an external lead to form a closed loop, so that the normal electrifying work of the whole speed monitoring is ensured.
As a specific embodiment, the exhaust temperature measurement module 3 includes an exhaust temperature measurer 31 and an exhaust temperature measurer joint 32; the exhaust temperature measuring device 31 is a programmed, highly integrated, miniature monitor component, and is disposed on the control circuit board 1, the temperature inside the microminiature aircraft turbine engine is detected by a temperature sensor arranged inside the microminiature aircraft turbine engine, and comprises the temperature at the outlet of a centrifugal compressor, the temperature at the outlet of a combustion chamber, the temperature after a turbine and the temperature at the outlet of a tail nozzle, the monitoring of the actual working condition of the microminiature aviation turbine engine and the optimization of the control strategy can be better realized by monitoring the temperature, the high-temperature components of the microminiature aircraft turbine engine are ensured not to be burnt out due to over-temperature by controlling the fuel oil supply law in different flight envelope lines, the exhaust temperature measurer joint 32, and the device is communicated through an external lead to form a closed loop, so that the normal power-on work in the whole temperature detection process is ensured.
As a specific embodiment, the engine control module 4 includes a control chip module 41, a driving module 42 and a control module connector 43; the control chip module 41 is a highly integrated microminiature working component which has been programmed and has a certain function, the control chip module 41 is arranged on the control circuit board 1, the control chip module 41 controls various functions of the microminiature aircraft turbine engine by receiving information instructions input from the outside, the driving module 42 is also arranged on the control circuit board 1, and the control chip module 41 is mainly used for assisting the control chip module 41 to have better reliability and functionality for all maneuverability of the whole microminiature aircraft turbine engine, the control module joint 43 is communicated through an external lead to form a closed loop, and the whole control chip module 41 and the driving module 42 are ensured to work on the microminiature aircraft turbine engine normally.
As a specific embodiment, the fuel valve control module 5 includes a main fuel valve control module 51, an ignition fuel valve control module 52, and a fuel valve power connector 53; the main fuel valve control module 51 is arranged on the control circuit board 1, the main fuel valve control module 51 is a main fuel switch for controlling the microminiature aviation turbine engine, and an external input signal is input to the engine control module 4 to adjust the supply of fuel flow in a combustion chamber, so that the normal supply work of the whole fuel system is ensured; the ignition oil valve control module 52 is mainly used for controlling the fuel flow of the microminiature aviation turbine engine in the starting and ignition stage, so that the microminiature aviation turbine engine can be reliably ignited and started to work in the airplane flight envelope; the oil valve socket 53 integrates the main fuel valve control module 51 and the ignition oil valve control module 52 into a socket, simplifies the whole structure of the control circuit board 1, reduces the whole weight of the microminiature aviation turbine engine, is communicated through an external lead to form a closed loop, and ensures the whole structure of the main fuel valve control module 51 and the ignition oil valve control module 52 to work in normal electrification of the control of the fuel flow of the fuel system of the microminiature aviation turbine engine and the normal ignition starting.
As a specific embodiment, the control circuit board 1 comprises a starting motor connector 15 and an engine communication and power supply socket 16, the engine communication and power supply socket 16 is arranged on the side surface of the control circuit board 1, and the fairing 7 is provided with a socket hole 71 corresponding to the engine communication and power supply socket 16; the starting motor connector 15 ensures that the starting motor is normally electrified in the starting stage of the centrifugal compressor of the microminiature aircraft turbine engine, and the engine communication and power supply socket 16 ensures that the whole control circuit board 1 is normally electrified to work.
For the sake of clarity of the present invention, the cowling 7 of fig. 1 and 2 is in an uninstalled state, the cowling 7 not covering the control circuit board 1, and fig. 7 is a schematic view of the installation of the present invention on a microminiature aircraft turbine engine.
While the invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes in form and detail may be made therein without departing from the spirit and scope of the invention.
Claims (10)
1. The layout of the built-in control circuit board of the microminiature aircraft turbine engine is characterized by comprising a control circuit board (1), wherein the control circuit board (1) is fixed on a compressor impeller casing (6) of the engine, and a fairing (7) of the engine covers the control circuit board (1), so that the control circuit board (1) is built in the fairing (7).
2. The layout of the internal control circuit board of the microminiature aircraft turbine engine as recited in claim 1, characterized in that an air intake gap (17) is provided between the leading edge (62) of the compressor impeller casing and the cowling (7).
3. The layout of the built-in control circuit board of the microminiature aircraft turbine engine as claimed in claim 1, wherein said control circuit board (1) is a fan-shaped circuit board with a fan-shaped geometry.
4. The layout of the built-in control circuit board of the microminiature aircraft turbine engine according to claim 1, wherein the control circuit board (1) is provided with a fixed seat (11), and the compressor impeller casing (6) is provided with a mounting hole (61) corresponding to the fixed seat (11).
5. The layout of the built-in control circuit board of the microminiature aircraft turbine engine according to claim 1, characterized in that the control circuit board (1) is provided with a rotation speed measuring module (2), an exhaust temperature measuring module (3), an engine control module (4) and an oil valve control module (5).
6. The layout of the internal control circuit board of the microminiature aircraft turbine engine according to claim 5, characterized in that the rotation speed measurement module (2) comprises a rotation speed measurement detector (21) and a rotation speed measurement connector (22).
7. The layout of the internal control circuit board of the microminiature aircraft turbine engine as recited in claim 5, characterized in that said exhaust temperature measurement module (3) comprises an exhaust temperature measurer (31) and an exhaust temperature measurer joint (32).
8. The layout of the internal control circuit board of the microminiature aircraft turbine engine according to claim 5, characterized in that the engine control module (4) comprises a control chip module (41), a drive module (42) and a control module connector (43).
9. The layout of the internal control circuit board of the microminiature aircraft turbine engine according to claim 5, characterized in that the oil valve control module (5) comprises a main fuel valve control module (51), an ignition oil valve control module (52) and an oil valve power connector (53).
10. The layout of the built-in control circuit board of the microminiature aircraft turbine engine as claimed in claim 1, wherein the control circuit board (1) comprises a starting motor connector (15) and an engine communication and power supply socket (16), the engine communication and power supply socket (16) is arranged on the side surface of the control circuit board (1), and the fairing (7) is provided with a socket hole (71) corresponding to the engine communication and power supply socket (16).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110530808.0A CN113294242B (en) | 2021-05-15 | 2021-05-15 | Built-in control circuit board layout of microminiature aviation turbine engine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110530808.0A CN113294242B (en) | 2021-05-15 | 2021-05-15 | Built-in control circuit board layout of microminiature aviation turbine engine |
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| CN113294242A true CN113294242A (en) | 2021-08-24 |
| CN113294242B CN113294242B (en) | 2024-08-16 |
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Citations (8)
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|---|---|---|---|---|
| US5012639A (en) * | 1989-01-23 | 1991-05-07 | United Technologies Corporation | Buffer region for the nacelle of a gas turbine engine |
| WO2010009945A2 (en) * | 2008-07-25 | 2010-01-28 | Continental Automotive Gmbh | Cooled turbocharger housing comprising one or more electronic devices |
| US20100071638A1 (en) * | 2008-09-25 | 2010-03-25 | Airbus Operations Sas | System for managing the heat fluxes of an aircraft |
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| CN212829064U (en) * | 2020-07-08 | 2021-03-30 | 杭州启飞智能科技有限公司 | Unmanned aerial vehicle integrated avionics module and unmanned aerial vehicle thereof |
| US20210336513A1 (en) * | 2018-10-26 | 2021-10-28 | Borgwarner Inc. | Rotating machine and method of using the same |
| CN215213694U (en) * | 2021-05-15 | 2021-12-17 | 上海睿瑞航空设备科技有限公司 | Built-in control circuit board system of microminiature aviation turbine engine |
-
2021
- 2021-05-15 CN CN202110530808.0A patent/CN113294242B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5012639A (en) * | 1989-01-23 | 1991-05-07 | United Technologies Corporation | Buffer region for the nacelle of a gas turbine engine |
| WO2010009945A2 (en) * | 2008-07-25 | 2010-01-28 | Continental Automotive Gmbh | Cooled turbocharger housing comprising one or more electronic devices |
| US20100071638A1 (en) * | 2008-09-25 | 2010-03-25 | Airbus Operations Sas | System for managing the heat fluxes of an aircraft |
| CN202628278U (en) * | 2012-06-15 | 2012-12-26 | 北京中陆航星机械动力科技有限公司 | Miniature turbojet engine starting system |
| CN107893701A (en) * | 2016-10-03 | 2018-04-10 | 通用电气公司 | Method and apparatus for shunting cooling under radome fairing |
| US20210336513A1 (en) * | 2018-10-26 | 2021-10-28 | Borgwarner Inc. | Rotating machine and method of using the same |
| CN212829064U (en) * | 2020-07-08 | 2021-03-30 | 杭州启飞智能科技有限公司 | Unmanned aerial vehicle integrated avionics module and unmanned aerial vehicle thereof |
| CN215213694U (en) * | 2021-05-15 | 2021-12-17 | 上海睿瑞航空设备科技有限公司 | Built-in control circuit board system of microminiature aviation turbine engine |
Non-Patent Citations (1)
| Title |
|---|
| 刘葆华;黄金泉;: "航空发动机电子控制系统的小型化SIP技术", 航空动力学报, no. 09, 26 September 2013 (2013-09-26), pages 2140 - 2144 * |
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| CN113294242B (en) | 2024-08-16 |
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