CN113482827B - Engine for unmanned aerial vehicle and control method thereof - Google Patents
Engine for unmanned aerial vehicle and control method thereof Download PDFInfo
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- CN113482827B CN113482827B CN202110868622.6A CN202110868622A CN113482827B CN 113482827 B CN113482827 B CN 113482827B CN 202110868622 A CN202110868622 A CN 202110868622A CN 113482827 B CN113482827 B CN 113482827B
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- 238000000034 method Methods 0.000 title claims abstract description 19
- 238000010438 heat treatment Methods 0.000 claims abstract description 38
- 238000001514 detection method Methods 0.000 claims abstract description 4
- 239000000295 fuel oil Substances 0.000 abstract description 17
- 239000000446 fuel Substances 0.000 abstract description 9
- 238000002485 combustion reaction Methods 0.000 abstract description 4
- 230000017525 heat dissipation Effects 0.000 description 9
- 238000005485 electric heating Methods 0.000 description 8
- 238000007664 blowing Methods 0.000 description 6
- 238000011897 real-time detection Methods 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000008021 deposition Effects 0.000 description 1
- 239000010711 gasoline engine oil Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 230000001568 sexual effect Effects 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02N—STARTING OF COMBUSTION ENGINES; STARTING AIDS FOR SUCH ENGINES, NOT OTHERWISE PROVIDED FOR
- F02N19/00—Starting aids for combustion engines, not otherwise provided for
- F02N19/02—Aiding engine start by thermal means, e.g. using lighted wicks
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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
- F02B77/00—Component parts, details or accessories, not otherwise provided for
- F02B77/08—Safety, indicating, or supervising devices
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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
- F02B77/00—Component parts, details or accessories, not otherwise provided for
- F02B77/08—Safety, indicating, or supervising devices
- F02B77/089—Safety, indicating, or supervising devices relating to engine temperature
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
- Forklifts And Lifting Vehicles (AREA)
Abstract
The invention discloses an engine for an unmanned aerial vehicle, which belongs to the field of unmanned aerial vehicles and can reduce the failure rate of the engine in the starting stage, and comprises: a cylinder body; the heating device is arranged on the cylinder body and used for heating the cylinder body; the temperature sensor is arranged on the cylinder body and used for detecting the working temperature of the engine; an engine control unit capable of receiving detection data of the temperature sensor and controlling the heating device; by applying the engine for the unmanned aerial vehicle, the problems of engine starting failure and the like caused by insufficient combustion of heavy oil fuel in the starting stage can be effectively avoided, and the failure rate of the engine in the starting stage is reduced; the invention further provides an engine control method for the unmanned aerial vehicle.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicles, in particular to an engine for an unmanned aerial vehicle and a control method thereof.
Background
In the middle of present civilian unmanned aerial vehicle, heavy oil engine is adopted more and more, compares with gasoline engine, and heavy oil engine has that the durability is good, load capacity is stronger, sexual valence relative altitude, security height, high altitude performance advantage etc. each item advantage.
However, the working temperature of the heavy oil engine needs to be controlled within a specific range, and if the working temperature of the engine is lower than the specified temperature range of the engine, the heavy oil is insufficiently combusted, and the working efficiency of the engine is reduced; if the working temperature of the engine is higher than the designated temperature range, the engine piston and the cylinder are excessively tightly matched, and the inner wall of the cylinder is strained; therefore, when the engine operating temperature is low in the starting stage, the situation that the heavy oil is insufficiently combusted easily occurs, and the normal operation of the engine in the starting stage is affected.
Disclosure of Invention
The present invention is directed to solving at least one of the problems of the prior art. Therefore, the invention provides an engine for an unmanned aerial vehicle, which can reduce the failure rate of the engine in the starting stage.
The invention relates to an engine for an unmanned aerial vehicle, which comprises: a cylinder body; the heating device is arranged on the cylinder body and used for heating the cylinder body; the temperature sensor is arranged on the cylinder body and used for detecting the working temperature of the engine; and an engine control unit capable of receiving the detection data of the temperature sensor and controlling the heating device.
According to some embodiments of the invention, the engine for the drone further comprises: the radiating fin is connected with the top end of the cylinder body; the flow deflector is rotationally connected to the radiating fin and can change the flow direction of airflow flowing through the flow deflector and blowing to the cylinder body; the adjusting device can adjust the rotation angle theta of the guide vane relative to the radiating fin.
According to some embodiments of the invention, the engine has two cylinders, each of which is provided with a heating device.
According to some embodiments of the invention, the cooling fins are connected to both cylinders, and the guide vanes are located at the rear sides of both cylinders.
The invention also provides an engine control method for the unmanned aerial vehicle, which is characterized by comprising the following steps of: the engine working temperature T is detected, and when T is lower than a preset value, the heating device is started.
According to some embodiments of the present invention, when T ≦ T0, the heating device is activated until T ≧ T0 at which T0 is the cranking temperature and then the engine is started.
According to some embodiments of the invention, when T ≦ T0, θ is adjusted such that θ reaches a minimum value.
According to some embodiments of the present invention, when T0 ≦ T1, the relationship between T and θ satisfies T3 ≦ T4, where T0 ≦ T1 ≦ T4 is satisfied between T4, T0, and T1.
According to some embodiments of the invention, T1 ≦ T2, the relationship between T and θ satisfies T1 ≦ T3525, wherein T1 ≦ T4 ≦ T2 between T4, T1, and T2.
According to some embodiments of the present invention, when T2 ≦ T3, the relationship between T and θ satisfies T2 ≦ T3, where T4 ≦ T2 ≦ T3 is satisfied between T4, T2, and T3.
The engine for the unmanned aerial vehicle can control the heating device to heat the engine in the starting stage, so that the temperature of the cylinder body can be raised to a proper temperature under the condition that the engine is not required to ignite and burn fuel, and then ignition is carried out, for a heavy oil engine, the problems of engine starting failure and the like caused by insufficient combustion of the heavy oil fuel in the starting stage can be effectively avoided, and the failure rate of the engine in the starting stage is reduced; wherein, engine control unit can be through the operating temperature of temperature sensor real-time detection engine, can close heating device after heating device heats the cylinder body to predetermined temperature, prevents that power consumption is too big to lead to storage battery insufficient voltage, the unable accident of starting of engine.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
FIG. 1 is an isometric view of a portion of an aircraft engine according to an embodiment of the present invention;
FIG. 2 is an enlarged view taken at A in FIG. 1;
FIG. 3 is an enlarged view at B in FIG. 1;
FIG. 4 is an enlarged view at C of FIG. 1;
FIG. 5 is a schematic view of a heating apparatus according to an embodiment of the present invention;
the above figures contain the following reference numerals.
| Reference numerals | Name (R) |
| 100 | |
| 200 | |
| 210 | |
| 220 | |
| 230 | |
| 240 | Connecting |
| 250 | Rocker |
| 260 | |
| 300 | |
| 400 | |
| 410 | |
| 420 | Electrode for |
| 430 | Electric heating rod |
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative only for the purpose of explaining the present invention and are not to be construed as limiting the present invention.
In the description of the present invention, it should be understood that the orientation or positional relationship referred to in the description of the orientation, such as upper, lower, front, rear, left, right, etc., is based on the orientation or positional relationship shown in the drawings only for the convenience of description of the present invention and simplification of the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
In the description of the present invention, the meaning of a plurality of means is one or more, the meaning of a plurality of means is two or more, and more than, less than, more than, etc. are understood as excluding the present number, and more than, less than, etc. are understood as including the present number. If the first and second are described for the purpose of distinguishing technical features, they are not to be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated or implicitly indicating the precedence of the technical features indicated.
In the description of the present invention, unless otherwise explicitly limited, terms such as arrangement, installation, connection and the like should be understood in a broad sense, and those skilled in the art can reasonably determine the specific meanings of the above terms in the present invention in combination with the specific contents of the technical solutions.
Referring to fig. 1, the engine for a drone of the first aspect of the present embodiment includes: a cylinder block 100; and a heating device 400 provided on the cylinder 100, the heating device 400 being used to heat the cylinder 100.
Use above-mentioned an engine for unmanned aerial vehicle, at the start-up stage, can control heating device 400 and heat the engine for under the condition that need not engine ignition burning fuel, the cylinder body 100 temperature can rise to suitable temperature, then the ignition, to the heavy oil engine, can effectively avoid the insufficient engine start trouble scheduling problem that leads to of start-up stage heavy oil fuel burning, reduce the fault rate of engine start-up stage.
When the heavy oil is used as the engine raw material, the engine is more sensitive to the working temperature, and when the working temperature of the engine is too low, the problems of unsmooth combustion, carbon deposition and the like are more likely to occur when the heavy oil is used, so that the heating device 400 plays a more important role in the heavy oil engine.
It is understood that the heating device 400 can heat the cylinder 100 in various ways, such as heating with the electric heating device 400, heating the cylinder 100 with a heat pump system, and the like.
As shown in fig. 4 and 5, the heating apparatus 400 includes: a mounting seat 410; the electric heating rod 430 is provided on the mount 410, and the electric heating rod 430 abuts against the cylinder block 100.
Specifically, the electric heating rod 430 is provided in plurality, and an electrode 420 is provided at one end of the electric heating rod 430, and the electrode 420 is used to supply power to the electric heating rod 430.
As shown in fig. 4, in order to facilitate maintenance of the engine, a cylinder cover is connected to the cylinder block 100, the cylinder cover is detachably engaged with the cylinder block 100, and a heating device 400 is disposed on the cylinder cover; when the engine is maintained, the inner wall of the cylinder body 100 can be maintained only by disassembling the cylinder cover and the electric heating device 400, and the whole engine does not need to be disassembled.
As shown in fig. 1, the engine further includes: a heat sink 200 connected to the top end of the cylinder 100; and a guide vane 220 rotatably coupled to the heat sink 200, the guide vane 220 being capable of changing a flow direction of the air flowing through the guide vane 220 and blowing to the cylinder 100.
By applying the engine heat dissipation device, when the temperature of the engine is too high, the adjusting device can drive the flow deflector 220 to deflect, so that the airflow flowing through the flow deflector 220 and blowing to the cylinder body 100 is increased, the heat dissipation of the engine is enhanced, and the working temperature of the engine is reduced to a specified temperature range; when the temperature of the engine is too low, the adjusting device can drive the flow deflector 220 to deflect, so that the airflow flowing through the flow deflector 220 and blowing to the cylinder body 100 is reduced, the heat dissipation of the engine is weakened, and the temperature of the engine is increased to a specified temperature range; the purpose of controlling the working temperature of the engine can be achieved by controlling the direction of the air flow, and the engine control device is simple in structure and convenient to control.
The engine further comprises an adjusting device, the adjusting device can adjust the rotation angle of the guide vane 220 relative to the radiating fin 200, in the engine starting stage, the heating device 400 can help the engine to reach normal working temperature as soon as possible under the condition that heavy oil fuel is not combusted, in the flying process, the adjusting device can operate the guide vane to adjust the working temperature of the engine, the over-high or over-low temperature of the engine is avoided, and in the whole process of starting and working of the engine, the heating device 400 and the guide vane 220 are matched to ensure the stable operation of the engine.
As shown in fig. 3, the adjusting device can adjust the rotation angle of the guide vane 220 relative to the heat sink 200; in the flying process, the adjusting device can adjust the deflection angle of the guide vane 220 in real time according to the running condition of the engine; certainly, on the premise that the adjustment in time is not needed in the flight process, the adjusting device is not needed, and the deflecting position of the guide vane 220 is manually adjusted and then fixed; it can be understood that the adjusting device may adjust the position of the guide vane 220 in various ways, for example, the guide vane 220 is driven to rotate by a motor or an air cylinder coaxially disposed with the rotation shaft of the guide vane 220, and one end of the guide vane 220 may also be pulled by a telescopic air cylinder or a linear motor, so that the guide vane 220 rotates.
As shown in fig. 2, the adjusting apparatus includes: the pull rod 230 is rotatably connected with the guide vane 220, and the pull rod 230 can drive the guide vane 220 to deflect upwards or downwards; a driving device capable of moving the drawbar 230 up and down; at this time, the driving device only needs to push and pull the pull rod 230, so as to adjust the rotation angle of the deflector 220.
As shown in fig. 3, the driving device includes a deflection steering gear 260, and a rocker arm 250 of the deflection steering gear 260 is rotatably connected with the pull rod 230; at this time, the deflection steering engine 260 can control the rocker arm 250 to rotate, so that the rocker arm 250 can drive the pull rod 230 to move up and down to drive the guide vanes 220 to rotate; on unmanned aerial vehicle, the steering wheel is comparatively the power spare commonly used, has advantages such as easily control, torque are big, uses the steering wheel control deflection angle to simplify the power form on the aircraft, the control of being convenient for.
Specifically, as shown in fig. 2 and 3, the adjusting device further includes a connecting rod 240, two ends of the connecting rod 240 are respectively and rotatably connected with the rocker arm 250 and the pull rod 230, and the connecting rod 240 is telescopically arranged.
Specifically, the link 240 includes: a rod body; the two connectors are respectively connected with the pull rod 230 and the rocker arm 250 in a rotating way; the two connectors are in threaded connection with the two ends of the rod body; when the length of the connecting rod 240 needs to be adjusted, the connecting rod 240 only needs to be twisted, the thread matching distance between the connecting rod 240 and the connectors at the two ends is changed, and due to the reverse self-locking performance of the threads, the adjusted length of the screw rod can be well kept; of course, other forms of telescoping connecting rod 240 may be used, such as connecting rod 240 that fits through multiple pin and pin holes, etc.
As shown in fig. 4, there are two cylinder blocks 100, and a heating device 400 is provided on each of the two cylinder blocks 100.
It can be understood that the engine further comprises an engine control unit, and the engine control unit can receive the detection data of the temperature sensor 210, and accordingly, the normal operation of the engine can be effectively guaranteed according to the operation of the heating device 400 and the state of the adjusting device.
By applying the engine for the unmanned aerial vehicle, the heating device 400 can be controlled to heat the engine in the starting stage, so that the temperature of the cylinder body 100 can be raised to a proper temperature under the condition that the engine is not required to ignite and burn fuel, and then ignition is carried out, for a heavy oil engine, the problems of engine starting failure and the like caused by insufficient combustion of the heavy oil fuel in the starting stage can be effectively avoided, and the failure rate of the engine in the starting stage is reduced; wherein, engine control unit can be through the operating temperature of temperature sensor 210 real-time detection engine, can close heating device 400 after heating device 400 heats cylinder body 100 to the predetermined temperature, prevents that power consumption is too big to lead to the storage battery insufficient voltage, the unable accident of starting of engine.
In a second aspect of the present embodiment, a method for controlling an engine of an unmanned aerial vehicle is disclosed, for controlling the engine of the unmanned aerial vehicle, the method includes the following steps: the engine operating temperature T is detected and when T is lower than a predetermined value, the heating device 400 is activated.
Specifically, when T is less than or equal to T0, the heating device 400 is started until T is more than or equal to T0, and then the engine is started, wherein T0 is the starting temperature; before the engine is heated to the starting temperature, the heating device 400 can be controlled to heat the engine under the condition of no ignition, so that the engine is heated as soon as possible, and heavy oil fuel is prevented from being combusted in a low-temperature environment; wherein T0 is preferably 120 ℃.
When the engine temperature reaches T0 and the engine is ignited, the adjusting device may be controlled to adjust the angle of the baffle 220 by detecting the operating temperature T of the engine and adjusting the deflection angle θ of the baffle 220 relative to the heat sink 200 such that T approaches the first preset temperature T4.
In the flying process, when the temperature of the engine is too high, the adjusting device can drive the guide vane 220 to deflect, so that the airflow flowing through the guide vane 220 and blowing to the cylinder body 100 is increased, the heat dissipation of the engine is enhanced, and the working temperature of the engine is reduced to a specified temperature range; when the temperature of the engine is too low, the adjusting device can drive the flow deflector 220 to deflect, so that the airflow flowing through the flow deflector 220 and blowing to the cylinder body 100 is reduced, the heat dissipation of the engine is weakened, and the temperature of the engine is increased to a specified temperature range; the aim of controlling the working temperature of the engine can be achieved by controlling the direction of the airflow, and the engine has a simple structure and is convenient to control; particularly, the adjusting device can adjust the angle of the guide vane 220 in time during the flight process to control the working temperature of the engine.
When T1 is less than or equal to T2, the relation between T and theta satisfies T1 is K1, wherein T1 is less than or equal to T4 is less than or equal to T2 among T4, T1 and T2; when θ is 0, the guide vane 220 is in a state of being parallel to the heat sink 200; in the interval from T1 to T2, the engine is in a normal temperature working state, T1 is preferably 130 ℃, T2 is preferably 150 ℃ under the actual working condition, and T4 is actually the optimal working temperature of the engine, preferably 140 ℃; of course, the values of T1, T2, and T4 may vary depending on the engine.
Specifically, when the working temperature of the engine is higher, the deflection angle of the flow deflector 220 is increased, the heat dissipation of the engine is enhanced, and the temperature gradually falls back to the vicinity of T4; when the temperature is at T4, θ is 0.
Further, when T2 ≦ T3, the relationship between T and θ satisfies T2 ═ K2 ×, where T4 ≦ T2 ≦ T3 between T4, T2, and T3; when T is not less than T2 and not more than T3, the engine is in a warning temperature range with higher temperature, and rapid heat dissipation is needed, so that the guide vanes 220 deflect upwards by a larger angle under the working condition, the heat dissipation of the engine is further enhanced, and the engine is helped to be cooled as soon as possible; specifically, in the present embodiment, T3 is preferably 159 degrees celsius.
On the other hand, when T0 ≦ T1, the relationship between T and θ satisfies T — K3 × θ, where T0 ≦ T1 ≦ T4 is satisfied between T4, T0, and T1; when T is more than or equal to T0 and less than or equal to T1, the engine is in a boundary temperature range where the working temperature intersects, the temperature needs to be raised as soon as possible to enable the engine to return to a normal temperature range, and at the moment, the guide vanes 220 deflect downwards by a large angle, so that the heat dissipation of the engine is reduced, and the temperature of the engine is raised as soon as possible.
In the method, θ is a positive value when the guide vane 220 deflects upward, and θ is a negative value when the guide vane 220 deflects downward.
As shown in fig. 5, in the present embodiment, the engine mounted on the drone is preferably a longitudinally-arranged two-cylinder engine, two cylinders 100 of the engine are placed along the front-back direction of the drone, the propeller and the rotating hub 300 are located at the front side of the engine, and the flow deflector 220 is located at the rear side of the two cylinders 100; compared with the traditional horizontally-arranged engine, the windward resistance can be effectively reduced.
In the present embodiment, the engine operating temperatures T and θ are variables, and other values such as T0, T1, T2, T3, T4, K1, K2, and K3 are constants.
The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the above embodiments, and various changes can be made within the knowledge of those skilled in the art without departing from the gist of the present invention.
Claims (4)
1. A method of controlling an engine for a drone, for controlling the engine for the drone, the method comprising the steps of:
detecting the working temperature T of the engine, when the T is less than or equal to T0, starting the heating device (400), adjusting theta to enable the theta to reach the minimum value until the T is more than or equal to T0, and then starting the engine, wherein T0 is the starting temperature;
the engine for the drone includes:
a cylinder block (100);
a heating device (400) disposed on the cylinder (100), the heating device (400) being for heating the cylinder (100);
a temperature sensor (210) provided on the cylinder block (100) for detecting an operating temperature of the engine;
an engine control unit capable of receiving detection data of the temperature sensor (210) and controlling the heating device (400);
a heat sink (200) connected to the top end of the cylinder (100);
the guide vane (220) is rotatably connected to the radiating fin (200), and the guide vane (220) can change the flow direction of the airflow which flows through the guide vane (220) and is blown to the cylinder body (100);
an adjustment device capable of adjusting a rotation angle θ of the deflector (220) with respect to the heat sink (200).
2. The engine control method for the unmanned aerial vehicle of claim 1, wherein the relationship between T and θ satisfies T = K3 θ when T0 ≦ T1, wherein T0 ≦ T1 ≦ T4 is satisfied between T4, T0, and T1.
3. The engine control method for the unmanned aerial vehicle of claim 2, wherein the relationship between T and θ satisfies T = K1 × θ when T1 ≦ T2, wherein T1 ≦ T4 ≦ T2 is satisfied between T4, T1, and T2.
4. The engine control method for the unmanned aerial vehicle of claim 3, wherein the relationship between T and θ satisfies T = K2 θ when T2 ≦ T3, wherein T4 ≦ T2 ≦ T3 is satisfied between T4, T2, and T3.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110575433 | 2021-05-26 | ||
| CN202110575433X | 2021-05-26 |
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| CN113482827A CN113482827A (en) | 2021-10-08 |
| CN113482827B true CN113482827B (en) | 2022-07-12 |
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