CN113464262B - Temperature control device and control method of aviation piston engine for unmanned aerial vehicle - Google Patents
Temperature control device and control method of aviation piston engine for unmanned aerial vehicle Download PDFInfo
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- CN113464262B CN113464262B CN202110741944.4A CN202110741944A CN113464262B CN 113464262 B CN113464262 B CN 113464262B CN 202110741944 A CN202110741944 A CN 202110741944A CN 113464262 B CN113464262 B CN 113464262B
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- 238000000034 method Methods 0.000 title claims abstract description 17
- 238000001816 cooling Methods 0.000 claims abstract description 22
- 230000007246 mechanism Effects 0.000 claims abstract description 10
- 230000005540 biological transmission Effects 0.000 claims abstract description 5
- 238000009423 ventilation Methods 0.000 claims description 21
- 238000013016 damping Methods 0.000 claims description 5
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 2
- 230000000903 blocking effect Effects 0.000 claims description 2
- 238000013461 design Methods 0.000 abstract description 4
- 230000008569 process Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 6
- 230000009286 beneficial effect Effects 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 230000017525 heat dissipation Effects 0.000 description 3
- 230000036760 body temperature Effects 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000011217 control strategy Methods 0.000 description 1
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- 230000008021 deposition Effects 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
- F01P7/00—Controlling of coolant flow
- F01P7/02—Controlling of coolant flow the coolant being cooling-air
- F01P7/026—Thermostatic control
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
- F01P11/00—Component parts, details, or accessories not provided for in, or of interest apart from, groups F01P1/00 - F01P9/00
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
- F01P11/00—Component parts, details, or accessories not provided for in, or of interest apart from, groups F01P1/00 - F01P9/00
- F01P11/14—Indicating devices; Other safety devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
- F01P7/00—Controlling of coolant flow
- F01P7/02—Controlling of coolant flow the coolant being cooling-air
- F01P7/04—Controlling of coolant flow the coolant being cooling-air by varying pump speed, e.g. by changing pump-drive gear ratio
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Abstract
The invention provides a temperature control device and a temperature control method of an aviation piston engine for an unmanned aerial vehicle, which relate to the technical field of aircraft design, can control the temperature of the engine by controlling the cooling air volume, promote the engine to always work in a proper temperature range, and improve the service life and the working efficiency of the engine; the device comprises a plurality of groups of temperature control structures which are respectively arranged around the engine and used for cooling the engine; the temperature control structure comprises an air guide cover, a control steering engine and an adjustable air guide plate; a flow channel through which cooling airflow flows is arranged in the air guide cover; the adjustable air deflector is rotatably arranged in the flow channel of the air guide cover; the control steering engine is connected with the adjustable air guide plate through a transmission mechanism and controls the opening and closing of the adjustable air guide plate. The technical scheme provided by the invention is suitable for the temperature control process of the engine of the unmanned aerial vehicle.
Description
Technical Field
The invention relates to the technical field of aircraft design, in particular to a temperature control device and a temperature control method of an aviation piston engine for an unmanned aerial vehicle.
Background
The temperature of the cylinder during the operation of the piston engine affects the efficiency and the service life of the engine. The temperature of the cylinder body is high, the thermal fatigue life of the engine is reduced, and the engine is easy to damage; the cylinder body is low in temperature, insufficient in combustion and low in efficiency, carbon deposition in the engine cylinder is caused, and when the temperature is too low, the engine can even be flamed out. Therefore, controlling the temperature of the cylinder of the piston engine to be maintained in a proper range is an important factor for ensuring the reliable work of the piston engine and improving the work efficiency of the piston engine.
The piston engine for the unmanned aerial vehicle is generally cooled in a natural air cooling mode, however, the natural air cooling mode is difficult to adapt to great changes of altitude and speed, and the cooling conditions of low-altitude ground tests and high-altitude flight tasks are greatly different, so that great difficulty is brought to the control of the temperature of a cylinder body of the piston engine.
Accordingly, there is a need to develop a temperature control device and a temperature control method for an aviation piston engine for an unmanned aerial vehicle, which address the deficiencies of the prior art and solve or alleviate one or more of the problems.
Disclosure of Invention
In view of the above, the invention provides a temperature control device and a temperature control method for an aviation piston engine for an unmanned aerial vehicle, which can control the temperature of the engine by controlling the cooling air volume, so that the engine is always operated in a proper temperature range, and the service life and the working efficiency of the engine are improved.
On one hand, the invention provides a temperature control device of an aviation piston engine for an unmanned aerial vehicle, which comprises a plurality of groups of temperature control structures, wherein the temperature control structures are respectively arranged around the engine to cool the engine;
the temperature control structure comprises an air guide cover, a control steering engine and an adjustable air guide plate; a flow channel through which cooling airflow flows is arranged in the air guide cover;
the adjustable air deflector is rotatably arranged in the flow channel of the air guide cover;
the control steering engine is connected with the adjustable air guide plate through a transmission mechanism and controls the opening and closing of the adjustable air guide plate.
The above aspects and any possible implementations further provide an implementation in which the wind scooper is fixedly attached around the engine by a bracket.
The above aspect and any possible implementation further provide an implementation in which the bracket is fixedly connected to a vibration damping device of the engine.
The above aspects and any possible implementations further provide an implementation in which the transmission mechanism includes a link structure and an adjustable air deflector shaft;
one end of the connecting rod structure is connected with the control steering engine, and the other end of the connecting rod structure is connected with one end of the adjustable air deflector shaft;
the adjustable air deflector shaft is rotatably arranged in the flow channel of the air guide cover, and the adjustable air deflector is fixedly connected with the adjustable air deflector shaft.
The above aspect and any possible implementation further provide an implementation in which the bracket is provided with a wind deflector with a matching shape for blocking the flow of gas through the bracket.
The above aspect and any possible implementation further provide an implementation in which the link structure includes a first link, a second link, and a third link;
one end of the first connecting rod is fixedly connected with the control steering engine, and the other end of the first connecting rod is movably connected with one end of the second connecting rod; the other end of the second connecting rod is movably connected with one end of the third connecting rod, and the other end of the third connecting rod is fixedly connected with the adjustable air deflector shaft.
The above-mentioned aspects and any possible implementation manner further provide an implementation manner that the front end opening of the wind scooper is a flared type, a contracted type or a straight type.
The above aspects and any possible implementation manners further provide an implementation manner, wherein the control steering engine is connected with the engine temperature sensor and the flight control device at the same time, and is used for acquiring the temperature of the engine, the height of the unmanned aerial vehicle and the flight speed of the unmanned aerial vehicle in real time.
In another aspect, the present invention provides a method for controlling the temperature of an aviation piston engine for an unmanned aerial vehicle, the method being adapted to any one of the control devices described above.
According to the aspect and any possible implementation manner, an implementation manner is further provided, the steering engine is controlled to control the opening and closing degree of the adjustable air guide plate according to the temperature of the engine, the height and the speed of the unmanned aerial vehicle, and then the cooling air quantity passing through the air guide cover flow channel is controlled, so that the engine is always in a proper working temperature range.
The above aspects and any possible implementation further provide an implementation in which the temperature control device is operated before the engine is started and maintains the maximum ventilation operation; after the engine is started and reaches a stable working state, the temperature control device enters closed-loop control; after the unmanned aerial vehicle finishes the task, under the condition that the temperature control device keeps the maximum ventilation quantity, the engine stops; the method comprises the following specific steps:
s1, setting the temperature control device as the maximum ventilation quantity;
s2, judging whether the current altitude of the unmanned aerial vehicle reaches a specified range, if so, entering the next step, and if not, continuing to keep the maximum ventilation;
s3, judging whether the current airspeed of the unmanned aerial vehicle reaches a specified range, if so, entering the next step, and if not, continuously keeping the maximum ventilation volume;
s4, judging the relation between the cylinder temperature of the engine and the optimal interval, if the relation is lower than the optimal interval, reducing the ventilation quantity of the temperature control device, and entering closed-loop control; if the temperature control device is in the optimal interval, the temperature control device continues to keep the maximum ventilation volume, and returns to the step S2 to continue judging;
s5, setting the temperature control device as the maximum ventilation volume after the closed-loop control is finished; and then judging whether the aircraft task is finished, if so, stopping the engine, and otherwise, returning to the step S2.
When the aircraft is in a normal flying state, the temperature of the engine reaching a specified height and at a specified speed is lower, the situation higher than the optimal interval cannot occur, if the temperature of the engine cylinder is higher than the optimal interval in a special situation, the cooling mode of the maximum ventilation volume is continuously kept, and other emergency measures are carried out, such as starting other cooling modes, entering a return mode or emergency forced landing.
The above-described aspect and any possible implementation further provide an implementation in which the closed-loop control of the temperature control device includes the steps of:
s41, judging whether the current airspeed of the unmanned aerial vehicle reaches a specified range, if so, entering the next step, and if not, ending the closed-loop control;
s42, judging whether the current altitude of the unmanned aerial vehicle reaches a specified range, if so, entering the next step, and if not, ending the closed-loop control;
s43, judging the relation between the cylinder temperature of the engine and the optimum section, if the relation is lower than the optimum section, reducing the ventilation quantity of the temperature control device and returning to the step S41; if the optimum interval is reached, returning to step S41; if the temperature is higher than the optimum interval, the temperature control device is adjusted to the maximum ventilation amount, and the process returns to step S41.
Compared with the prior art, one of the technical schemes has the following advantages or beneficial effects: the temperature control structure is arranged around the engine, and the temperature of the engine is controlled by controlling the cooling air volume flowing through the temperature control structure, so that the engine is enabled to work in a proper temperature range all the time, and the service life and the working efficiency of the engine are improved;
another technical scheme in the above technical scheme has the following advantages or beneficial effects: according to the invention, the cooling air volume is controlled according to the real-time temperature of the engine, the height of the unmanned aerial vehicle and the flying speed, and the engine is accurately controlled by temperature;
another technical scheme in the above technical scheme has the following advantages or beneficial effects: the temperature control structure is not directly connected with the engine but indirectly connected with the engine through the vibration damping structure, so that the temperature control structure can be prevented from colliding with the engine in a vibration environment, and the transportability of the temperature control structure is improved.
Of course, it is not necessary for any one product in which the invention is practiced to achieve all of the above-described technical effects simultaneously.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic diagram of a temperature control device according to an embodiment of the present invention installed in an engine;
FIG. 2 is a first schematic structural diagram of a temperature control device according to an embodiment of the present invention;
FIG. 3 is a schematic structural diagram of a temperature control device according to an embodiment of the present invention;
FIG. 4 is a schematic structural diagram III of a temperature control device according to an embodiment of the present invention;
FIG. 5 is a schematic diagram illustrating an optimized configuration of an air guiding cover of an engine temperature control device according to an embodiment of the present invention;
FIG. 6 is a flow chart of operation of a temperature control device in cooperation with an engine according to one embodiment of the present invention;
fig. 7 is a logic diagram of a closed-loop control of a temperature control device according to an embodiment of the present invention.
Wherein, in the figure:
1. a rear wind scooper; 2. a front air guide cover; 3. a support; 4. a wind deflector; 5. controlling a steering engine; 6. a first link; 7. a second link; 8. a third link; 9. an adjustable air deflector shaft; 10. an adjustable air deflector.
Detailed Description
For better understanding of the technical solutions of the present invention, the following detailed descriptions of the embodiments of the present invention are provided with reference to the accompanying drawings.
It should be understood that the described embodiments are only some embodiments of the invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The terminology used in the embodiments of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used in the examples of the present invention and the appended claims, the singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise.
The invention provides a temperature control device and a temperature control method of an aviation piston engine for an unmanned aerial vehicle, aiming at the requirement of controlling the cylinder temperature of the aviation piston engine when the existing unmanned aerial vehicle works at different altitudes and speeds.
The mounting position of the temperature control device of the invention on an aviation piston engine is shown in figure 1. The structure of the temperature control device is shown in fig. 2-4. The temperature control device comprises two groups of temperature control structures which are respectively arranged on two sides of the engine to cool the engine so as to realize temperature control. Each group of temperature control structures comprises a rear air guide cover 1, a front air guide cover 2, a support 3, a wind shield 4, a control steering engine 5, an adjustable wind guide plate shaft 9 and an adjustable wind guide plate 10. The entire temperature control device is fixed to the engine side of the engine damping device by a bracket 3. The rear wind scooper 1, the front wind scooper 2, the wind shield 4, the control steering engine 5 and the adjustable wind guide plate shaft 9 are fixedly connected to the support 3 through bolts. When the temperature control device and the engine are installed on the airplane, the front windshield 2 faces the front of the airplane, namely the windward direction; the rear wind scooper 1 faces the rear of the fuselage. The steering engine 5 is controlled to provide torque, and the adjustable air deflector shaft 9 is controlled to rotate through a first connecting rod 6, a second connecting rod 7 and a third connecting rod 8 which are connected in sequence; the adjustable air deflector 10 is fixedly connected to the adjustable air deflector shaft 9, so that the angle of the adjustable air deflector 10 is controlled by the steering engine 5, and the cooling air quantity of an engine cylinder is further controlled. The temperature control device is isolated from the airplane body through the vibration damper, so that the collision between the temperature control device and the airplane body when the engine vibrates can be avoided. Simultaneously, fix the connected mode on the engine, also provide probably for temperature control device transplants the unmanned aerial vehicle to different models.
The front wind guide cover and the rear wind guide cover are combined to form a space with three side walls with openings at the front end and the rear end for cooling airflow to pass through. The front end of the front air guide cover can adopt a flaring structure, as shown in fig. 2, which is beneficial to more cooling air entering. The adjustable air deflector 10 is arranged at the joint of the front wind scooper 2 and the rear wind scooper 1, and the size and the shape of the adjustable air deflector are matched with the space shape at the joint of the two wind scoopers, so that the air flow channel is opened and closed. The rear end face of the rear wind scooper 1 is provided with an opening for cooling airflow to flow out after cooling. The preferred vertical setting of adjustable aviation baffle axle 9, adjustable aviation baffle 10 is vertical to link firmly with adjustable aviation baffle axle 9, rotates thereupon when adjustable aviation baffle axle 9 rotates, realizes opening and closing of air current passageway.
The working principle of the temperature control device is as follows: temperature control device provides moment by control steering wheel 5 when needing the radiating operational aspect of engine normal such as unmanned aerial vehicle ground test run state, unmanned aerial vehicle low-altitude flight state, controls the angle of adjustable aviation baffle axle 9 and adjustable aviation baffle 10 through first connecting rod 6, second connecting rod 7 and third connecting rod 8, makes to be in the open mode, provides the cooling amount of wind of the normal heat dissipation demand of engine. When the temperature control device needs to reduce the heat dissipation capacity of engines in the high-altitude flight state of the unmanned aerial vehicle and other working conditions, the steering engine 5 is controlled to control the angle of the adjustable air deflector 10, so that the temperature control device is in a closed state, the heat dissipation air quantity of an engine cylinder body is reduced, and the temperature of the engines is further controlled.
In the temperature control device, only one actuating mechanism is used for controlling the steering engine 5, and the control logic is simple. The temperature control device controls the three connecting rods by controlling an electronic controller (namely ECU) in the steering engine, controls the steering engine and a cylinder body temperature sensor sharing temperature sensor when the engine works normally, determines an action range of the steering engine 5 and an opening angle range required by the adjustable air deflector 10 according to the real-time temperature of the engine and the current height and speed of the unmanned aerial vehicle, and regulates and controls the temperature. Simultaneously through the feedback data that temperature sensor provided (gather the temperature of engine promptly in real time), according to this feedback data and unmanned aerial vehicle height, speed, the control action of real-time correction control steering wheel 5 realizes through changing the engine cylinder body cooling air volume that the engine cylinder body temperature remains throughout in suitable working interval.
The temperature control device can also optimize the appearance of the wind scooper according to the engine to which the temperature control device is applied, reduce resistance and realize the function of controlling the temperature of the engine. An example of the optimization is shown in fig. 5. The front end of the front air guide cover 2 adopts a necking streamline design, so that the resistance is reduced. The design is suitable for unmanned aerial vehicles with high requirements on resistance and relatively low requirements on air volume. The front end of the front windshield 2 may be a straight shape, i.e., consistent front and back, depending on the situation.
The working flow of the temperature control device matched with the engine is shown in figure 6. The temperature control device starts to operate before the engine is started and maintains the maximum ventilation amount to operate. After the engine is started and reaches a stable working state, the temperature control device enters closed-loop control. After the unmanned aerial vehicle finishes the task, the engine stops under the condition that the temperature control device keeps the maximum ventilation quantity.
The flow of the closed-loop control of the temperature control device is shown in fig. 7. The temperature control device changes the ventilation quantity of the engine cylinder body by controlling the action of the steering engine 5. The temperature control device uses an engine electronic controller (namely ECU) to control the working angle of the steering engine, and shares a temperature sensor with a cylinder temperature sensor when the engine works normally. The control logic during closed loop control of the temperature control device is shown in fig. 7. Before the current altitude and the flight speed of the unmanned aerial vehicle reach the specified range, the temperature control device is in the maximum ventilation state. The temperature control device is in the maximum ventilation state so as to ensure that fault conditions such as engine overtemperature and the like do not occur. And after the specified range is reached, judging the relation between the current engine cylinder temperature and the optimum working interval of the cylinder, reducing the ventilation quantity of the temperature control device when the current temperature is lower, and increasing the ventilation quantity of the temperature control device when the current temperature is higher. Typically, the engine temperature is too low for a given range of drone altitude speeds. The temperature control device realizes the function of maintaining the temperature of the engine cylinder body in a proper working range by controlling the ventilation quantity.
The invention has the following advantages:
(1) the invention provides a temperature control mechanism which is fixed at an engine end and is far away from an airplane body, so that the vibration problem of an engine is avoided, the structure is simple, and the universality is high;
(2) the temperature of the engine cylinder body can be controlled under different flight conditions of the unmanned aerial vehicle, the combustion environment in the engine cylinder is improved, the working efficiency of the engine is improved, and the engine is suitable for different working conditions such as the ground, high altitude and flight;
(3) the engine ECU is used as a control unit, the temperature control mechanism only has an actuating mechanism, and the temperature control mechanism and the engine ECU share a temperature sensor, so that a control strategy is simple and reliable.
The temperature control device and the temperature control method for the aviation piston engine for the unmanned aerial vehicle according to the embodiments of the present application are described in detail above. The above description of the embodiments is only for the purpose of helping to understand the method of the present application and its core ideas; meanwhile, for a person skilled in the art, according to the idea of the present application, the specific implementation manner and the application scope may be changed, and in summary, the content of the present specification should not be construed as a limitation to the present application.
As used in the specification and claims, certain terms are used to refer to particular components. As one skilled in the art will appreciate, manufacturers may refer to a component by different names. This specification and claims do not intend to distinguish between components that differ in name but not function. In the following description and in the claims, the terms "include" and "comprise" are used in an open-ended fashion, and thus should be interpreted to mean "include, but not limited to. "substantially" means within an acceptable error range, and a person skilled in the art can solve the technical problem within a certain error range to substantially achieve the technical effect. The following description is of the preferred embodiment for carrying out the present application, but is made for the purpose of illustrating the general principles of the application and is not to be taken in a limiting sense. The protection scope of the present application shall be subject to the definitions of the appended claims.
It should also be noted that the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a good or system that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such good or system. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other like elements in a commodity or system that includes the element.
It should be understood that the term "and/or" as used herein is merely one type of association that describes an associated object, meaning that three relationships may exist, e.g., a and/or B may mean: a exists alone, A and B exist simultaneously, and B exists alone. In addition, the character "/" herein generally indicates that the former and latter related objects are in an "or" relationship.
The foregoing description shows and describes several preferred embodiments of the present application, but as aforementioned, it is to be understood that the application is not limited to the forms disclosed herein, but is not to be construed as excluding other embodiments and is capable of use in various other combinations, modifications, and environments and is capable of changes within the scope of the application as described herein, commensurate with the above teachings, or the skill or knowledge of the relevant art. And that modifications and variations may be effected by those skilled in the art without departing from the spirit and scope of the application, which is to be protected by the claims appended hereto.
Claims (7)
1. The temperature control device of the aviation piston engine for the unmanned aerial vehicle is characterized by comprising a plurality of groups of temperature control structures which are respectively arranged around the engine to cool the engine;
the temperature control structure comprises a wind scooper, a control steering engine and an adjustable wind deflector; the air guide cover comprises a front air guide cover and a rear air guide cover, the front air guide cover faces the front of the airplane, and the rear air guide cover faces the rear of the airplane body; the front air guide cover and the rear air guide cover are combined to form a flow channel with three side walls with openings at the front end and the rear end for cooling air to flow through;
the adjustable air deflector is rotatably arranged in the flow channel of the air guide cover;
the control steering engine is connected with the adjustable air deflector through a transmission mechanism and controls the opening and closing of the adjustable air deflector;
the wind scooper is fixedly connected to the periphery of the engine through a support;
the bracket is fixedly connected with a vibration damping device of the engine; the temperature control device is isolated from the airplane body through the vibration damping device, so that collision between the temperature control device and the airplane body when the engine vibrates is avoided;
the transmission mechanism comprises a connecting rod structure and an adjustable air deflector shaft;
one end of the connecting rod structure is connected with the control steering engine, and the other end of the connecting rod structure is connected with one end of the adjustable air deflector shaft;
the adjustable air deflector is fixedly connected with the adjustable air deflector shaft.
2. The temperature control device for the aviation piston engine for the unmanned aerial vehicle as claimed in claim 1, wherein the bracket is provided with a wind shield with a matched shape for blocking the gas from flowing through the bracket.
3. The temperature control apparatus for an aviation piston engine for an unmanned aerial vehicle as claimed in claim 1, wherein the connecting rod structure includes a first connecting rod, a second connecting rod and a third connecting rod;
one end of the first connecting rod is fixedly connected with the control steering engine, and the other end of the first connecting rod is movably connected with one end of the second connecting rod; the other end of the second connecting rod is movably connected with one end of the third connecting rod, and the other end of the third connecting rod is fixedly connected with the adjustable air deflector shaft.
4. The temperature control device for an aviation piston engine for an unmanned aerial vehicle according to claim 1, wherein the front end opening of the air guide cover is a flared shape, a contracted shape, or a straight shape.
5. The temperature control device of the aviation piston engine for the unmanned aerial vehicle as claimed in claim 1, wherein the control steering engine is connected with an engine temperature sensor and a flight control device at the same time.
6. A method for controlling the temperature of an aviation piston engine for an unmanned aerial vehicle, wherein the method is applied to the temperature control apparatus according to any one of claims 1 to 5;
the opening and closing degree of the adjustable air guide plate is controlled by the control steering engine according to the temperature of the engine and the height and speed of the unmanned aerial vehicle, so that the cooling air quantity passing through the air guide cover flow channel is controlled, and the engine is enabled to be always in a proper working temperature range.
7. The method of controlling the temperature of an aviation piston engine for an unmanned aerial vehicle according to claim 6, wherein the temperature control means is operated before the engine is started and maintains the maximum ventilation amount; after the engine is started and reaches a stable working state, the temperature control device enters closed-loop control; after the unmanned aerial vehicle finishes the task, the engine stops under the condition that the temperature control device keeps the maximum ventilation quantity.
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| CN202110741944.4A CN113464262B (en) | 2021-06-30 | 2021-06-30 | Temperature control device and control method of aviation piston engine for unmanned aerial vehicle |
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| CN202110741944.4A CN113464262B (en) | 2021-06-30 | 2021-06-30 | Temperature control device and control method of aviation piston engine for unmanned aerial vehicle |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB543219A (en) * | 1940-05-08 | 1942-02-16 | Constant Speed Airscrews Ltd | Improvements in the direct cooling of aircraft engines |
| CN203515764U (en) * | 2013-09-05 | 2014-04-02 | 中船重工（海南）飞船发展有限公司 | Wind deflector system of aviation piston engine |
| CN203879605U (en) * | 2014-06-12 | 2014-10-15 | 国家电网公司 | Air-cooling heat sink for engine |
| CN210971556U (en) * | 2019-08-13 | 2020-07-10 | 珠海天晴航空航天科技有限公司 | Engine temperature regulating device and unmanned aerial vehicle with same |
| CN110901930A (en) * | 2019-12-06 | 2020-03-24 | 西安爱生技术集团公司 | Rear-mounted ventilation cooling device of piston engine |
| CN213384746U (en) * | 2020-11-03 | 2021-06-08 | 海丰通航科技有限公司 | Cylinder temperature stabilizing system of aero-engine |
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| CN113464262A (en) | 2021-10-01 |
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Effective date of registration: 20240626 Address after: No. 58 Xindong Road, Huaqiao Town, Kunshan City, Suzhou City, Jiangsu Province, 215332 Patentee after: Feihong (Kunshan) Energy Power Technology Co.,Ltd. Country or region after: China Address before: Room 149, building 2, East Ring Road, Yanqing Park, Zhongguancun, Yanqing District, Beijing 102100 Patentee before: AEROSPACE TIMES FEIHONG TECHNOLOGY Co.,Ltd. Country or region before: China |