CN113479334A - Rapid starting method for power system of ejection type unmanned aerial vehicle - Google Patents
Rapid starting method for power system of ejection type unmanned aerial vehicle Download PDFInfo
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- CN113479334A CN113479334A CN202111048114.XA CN202111048114A CN113479334A CN 113479334 A CN113479334 A CN 113479334A CN 202111048114 A CN202111048114 A CN 202111048114A CN 113479334 A CN113479334 A CN 113479334A
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- 238000000034 method Methods 0.000 title claims abstract description 49
- 230000008569 process Effects 0.000 claims abstract description 14
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 12
- 229910052744 lithium Inorganic materials 0.000 claims description 12
- 238000010521 absorption reaction Methods 0.000 claims description 4
- 238000013016 damping Methods 0.000 claims description 3
- 238000004804 winding Methods 0.000 claims description 3
- 238000010792 warming Methods 0.000 abstract description 5
- 230000005540 biological transmission Effects 0.000 description 7
- 230000004044 response Effects 0.000 description 5
- 230000001276 controlling effect Effects 0.000 description 3
- 238000004891 communication Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 230000000087 stabilizing effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
- B64D31/02—Initiating means
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/11—Propulsion using internal combustion piston engines
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/70—Launching or landing using catapults, tracks or rails
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- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Control Of Vehicle Engines Or Engines For Specific Uses (AREA)
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Abstract
The invention provides a quick starting method of a power system of an ejection type unmanned aerial vehicle, which solves the problem that the power requirement of a box body emission cluster unmanned aerial vehicle in a take-off stage cannot be met due to the fact that the existing unmanned aerial vehicle is low in low-temperature starting reliability and needs to undergo pre-starting and warming processes. The method comprises the following steps: firstly, completely ejecting an unmanned aerial vehicle out of a box; step two, the direct current brushless motor and the piston engine are started simultaneously, the high-voltage electronic speed regulator controls the direct current brushless motor to output full load within T1 time, meanwhile, the control module sets an accelerator of the piston engine to be medium and small load, the piston engine is started rapidly under the dragging of the direct current brushless motor, and a warming-up program is entered; and step three, immediately outputting maximum power to the outside under full load after the piston engine warm-up procedure is completed, driving the propeller to provide power for the unmanned aerial vehicle and completing the subsequent takeoff process, and simultaneously controlling the zero-load output of the direct-current brushless motor by the high-voltage electronic speed regulator.
Description
Technical Field
The invention belongs to the field of unmanned aerial vehicles, and particularly relates to a quick starting method for a power system of an ejection type unmanned aerial vehicle.
Background
With the development of unmanned aerial vehicle autonomy and network communication technology, the application mode of the unmanned aerial vehicle is continuously developed, a single unmanned aerial vehicle is limited by factors such as detection capability and load, and is difficult to complete a complex flight task, and a cluster unmanned aerial vehicle can break up all functions of a single complete unmanned aerial vehicle platform into parts such as reconnaissance monitoring and communication relay, has the core advantages of large individual number, capability of executing complex tasks, high system survival rate, wide coverage range and the like, and has wide application prospect in the civil field.
Based on transportation convenience and rapid deployment consideration, a large number of clustered unmanned aerial vehicles are usually placed in a launching box of a launching vehicle in high-density arrangement, and the takeoff mode of the clustered unmanned aerial vehicles is generally catapulting in the box (including rocket launching and catapulting frame catapulting takeoff). The inner space of the launching box is extremely narrow, and when the unmanned aerial vehicle is not ejected out of the box, a power system cannot be started in advance; after the unmanned aerial vehicle is ejected out of the box, the power system is urgently needed to immediately output the maximum power, so that the airspeed of the unmanned aerial vehicle is kept above the safe airspeed and quickly climbs to the safe height, the flight safety in the takeoff stage is guaranteed, and the extremely high requirement is provided for the instantaneous response speed of the power system.
At present, the control method of the power system applied to the takeoff phase of the unmanned aerial vehicle mainly comprises the following steps:
a) a power system control method based on an aviation piston engine. Before taking off, the control module sends out a starting instruction, an engine is started in advance (the engine can be started successfully for 2-3 times in a low-temperature environment), a propeller is driven to keep idling, and the engine enters a warming-up program; after a heating process of more than tens of seconds, finishing heating after the temperature of the engine cylinder meets the use requirement, and enabling the power system to enter a flying waiting state; after the control module sends a starting instruction, the control module adjusts the load of the engine, outputs the maximum power and meets the takeoff requirement. When the mode is used for starting, the starting time of the engine is long, and the starting reliability in a low-temperature environment is low; secondly, the piston engine needs to go through a heat engine process for more than tens of seconds after being started, and cannot work at full load immediately;
b) a control method based on a pure electric drive power system is provided. After the control module receives the takeoff instruction, the motor drives the propeller and outputs the power required by the takeoff stage through the electronic speed regulator. The control method is simple, but the energy density of the battery is limited, so that the requirement of long endurance is difficult to meet;
c) a control method based on a gasoline-electric hybrid power system. The main expression form of current unmanned aerial vehicle oil-electricity hybrid power system is comparatively various, and its control method is also diverse, mainly has:
(1) the piston engine drives the generator, and after rectification output, the generator drives the propeller to work. The control method of the takeoff stage is similar to that of a propeller propulsion power system based on an aviation piston engine, and comprises a pre-starting stage and a warming-up stage, so that the maximum power output in a short time can not be realized to meet the takeoff requirement;
(2) the engine and the motor work independently of each other. The control method of the takeoff stage mainly comprises the following steps: pre-starting an engine before taking off and finishing a warm-up program; after the takeoff instruction is sent out, the engine and the motor are output at full load, so that sufficient power is provided for the takeoff stage, however, the mode needs a pre-starting and warming process, the starting time is long, and the catapult takeoff requirement of the cluster unmanned aerial vehicle is not met;
(3) the engine and the motor realize power coupling output through gear transmission (or chain transmission, belt transmission and other types), and the control method of the takeoff stage mainly comprises the following steps: before taking off, the motor drives the engine to realize pre-starting through gear transmission, and a warming-up program is completed; after the takeoff instruction is sent out, the engine and the motor work in full load and are coupled and output through gear transmission to drive the propeller to provide power in the takeoff stage, but the starting time is long due to the pre-starting and warming processes, and the requirement of catapult takeoff of the cluster unmanned aerial vehicle is not met; in addition, the power system is complex and heavy in structure, large in overall size and large in occupied space, and cannot meet the requirement of catapult takeoff in the cluster unmanned chassis;
(4) and (5) inspiring an integrated oil-electricity hybrid power system. The system directly connects a small-sized starting motor with an engine, and the control method of the system in the takeoff stage comprises the following steps: before taking off, the starting integrated motor drives the engine to realize pre-starting and complete a warming-up program; after the takeoff instruction is sent out, in order to meet the power requirement in the takeoff stage, the engine drives the propeller to output full load, and simultaneously, the motor is started to run in no-load mode, and electric energy is not output externally.
In summary, the existing control method of the unmanned aerial vehicle power system in the takeoff phase cannot meet the power requirement of the box body launching cluster unmanned aerial vehicle in the takeoff phase due to low-temperature starting reliability, the need of a pre-starting and warming process, complex structure, large overall size or non-conformity with the long endurance requirement.
Disclosure of Invention
The invention aims to solve the problem that the existing unmanned aerial vehicle power system cannot meet the power requirement of a take-off stage of a box body launching cluster unmanned aerial vehicle due to low-temperature starting reliability and the need of a pre-starting and warming process, and provides a quick starting method of a catapulting type unmanned aerial vehicle power system. The method aims at the catapult takeoff stage of the small-sized long-endurance catapult type unmanned aerial vehicle, is a control method capable of realizing instant starting and full-load power output of the power system, and can realize rapid full-load response of the power system.
In order to achieve the purpose, the invention adopts the following technical scheme:
the ejection type unmanned aerial vehicle power system provided by the invention comprises a piston type engine, a direct current brushless motor, a high-voltage electronic speed regulator, a starting lithium battery pack, a voltage stabilizing power supply module, a control module and an airborne battery pack; the output end of the piston type engine is connected with the propeller and used for driving the propeller to rotate so as to provide power for the unmanned aerial vehicle to fly; the direct current brushless motor is arranged at the front end of the piston type engine, and a rotor of the direct current brushless motor is rigidly connected with a crankshaft of the piston type engine; the full load output power of the direct current brushless motor is not less than the full load output power of the piston type engine, and the full load output power of the piston type engine is not less than the absorption power of the propeller at the take-off rotating speed; the high-voltage electronic speed regulator is arranged in the unmanned aerial vehicle body, the input end of the high-voltage electronic speed regulator is respectively connected with the starting lithium battery pack and the control module, and the output end of the high-voltage electronic speed regulator is connected with a winding of the direct-current brushless motor; the starting lithium battery pack supplies electric energy to the direct current brushless motor through the high-voltage electronic speed regulator; and the onboard battery pack supplies power to the control module and the high-voltage electronic speed regulator through the voltage-stabilized power supply module respectively.
Furthermore, the rotor of the brushless direct current motor is rigidly connected with the crankshaft of the piston engine through conical surface interference fit, and the connection mode is simple and compact in structure and free of transmission mechanical loss.
Further, driving system passes through damping device and sets up the fuselage afterbody at the unmanned aerial vehicle body for unmanned aerial vehicle reduces the influence to driving system when launching.
Further, the piston engine is a small aviation piston engine.
Meanwhile, the invention also provides a quick starting method of the power system of the ejection type unmanned aerial vehicle, which is realized based on the power system arranged at the tail part of the unmanned aerial vehicle body and specifically comprises the following steps:
step one, a control module sends a take-off instruction, an unmanned aerial vehicle ejection program is started, and the unmanned aerial vehicle is ejected out of a box completely;
after the unmanned aerial vehicle is ejected out of the tank completely, the control module sends a starting instruction, the direct-current brushless motor and the piston engine are started simultaneously, the high-voltage electronic speed regulator controls the direct-current brushless motor to output full load within T1 time, meanwhile, the control module sets an accelerator of the piston engine to be medium and small load, the piston engine is started quickly under the dragging of the direct-current brushless motor, and a warming program is entered;
and step three, immediately outputting maximum power to the outside under full load after the piston engine warming program is finished, driving a propeller to provide power for the unmanned aerial vehicle and finishing the subsequent takeoff process, and simultaneously controlling the zero-load output of the direct-current brushless motor by the high-voltage electronic speed regulator, wherein the direct-current brushless motor does not output power to the outside any more.
Further, in the second step, the throttle of the piston engine is set to be 15% -35% load, and T1=1.5 s.
Compared with the prior art, the invention has the following beneficial effects:
1. the method and the system adopt a starting mode that the piston engine is matched with the brushless direct current motor, and the starting is not required to be started in advance, so that the starting time is short, and the requirement of the rapid full-load response of the power system in the launching and taking-off stage of the cluster unmanned aerial vehicle box body is met.
2. The power system has high starting rotating speed, good low-temperature starting performance and reliable starting, and ensures the flight safety in the take-off stage.
3. In the cruising stage of the unmanned aerial vehicle, the on-board battery pack can be charged by controlling the on-board operation of the direct-current brushless motor, so that the cruising time of the unmanned aerial vehicle is prolonged.
Drawings
Fig. 1 is a schematic axial view of a catapult-type unmanned aerial vehicle carrying a power system of the present invention;
fig. 2 is a schematic view of the catapult-type unmanned aerial vehicle power system of the invention;
fig. 3 is a schematic view of the connection between the rotor of the dc brushless motor and the crankshaft of the piston engine according to the present invention.
Reference numerals: the method comprises the following steps of 1-an unmanned aerial vehicle body, 2-a power system, 3-a control module, 4-a starting lithium battery pack, 5-a high-voltage electronic speed regulator, 6-an airborne battery pack, 7-a voltage-stabilized power supply module, 8-a direct-current brushless motor, 9-a crankshaft, 10-a piston engine, 11-a propeller and 12-a rotor of the direct-current brushless motor.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood by those skilled in the art that these embodiments are only for explaining the technical principle of the present invention and are not intended to limit the scope of the present invention.
The invention provides a quick starting method and a power system of a catapult type unmanned aerial vehicle power system.
The power system 2 is arranged at the tail part of the unmanned aerial vehicle body 1 through the damping device, has a compact structure and occupies a small space, and is suitable for being launched in a box. As shown in fig. 1 and 2, the power system 2 specifically includes a piston engine 10, a brushless dc motor 8, a high-voltage electronic governor 5, a starting lithium battery pack 4, a control module 3, a regulated power supply module 7, and an onboard battery pack 6. Piston engine 10 specifically can be small-size aviation piston engine, sets up on unmanned aerial vehicle body 1, and its output is connected with unmanned aerial vehicle's screw 11 for screw 11 provides power, screw 11 installs in piston engine 10's rear end.
The invention is characterized in that a direct current brushless motor 8 is arranged at the front end of a piston engine 10, a rotor 12 of the direct current brushless motor is rigidly connected with a crankshaft 9 of the piston engine 10, a stator of the direct current brushless motor 8 is fixed on a crankcase of the piston engine 10 through a screw, a high-voltage electronic speed regulator 5, a starting lithium battery pack 4 and a control module 3 are arranged inside a body of an unmanned aerial vehicle, a winding of the direct current brushless motor 8 is connected with the output end of the high-voltage electronic speed regulator 5, the control module 3 and the starting lithium battery pack 4 are connected with the input end of the high-voltage electronic speed regulator 5, the high-voltage electronic speed regulator 5 and the control module 3 are powered by a voltage stabilizing power module 7 through an onboard battery pack 6, and the starting lithium battery pack 4 supplies electric energy to the direct current brushless motor 8 through the high-voltage electronic speed regulator 5.
The designed output power of the direct current brushless motor 8 is highly matched with the sum of the mechanical loss power of the engine and the absorption power of the propeller, namely, when the model selection is determined, the full-load output power of the direct current brushless motor 8 is not less than the full-load output power of the piston type engine 10, and the full-load output power of the piston type engine 10 is not less than the absorption power of the propeller 11 at the takeoff rotating speed.
As shown in fig. 3, in the embodiment of the present invention, the rotor 12 of the dc brushless motor and the crankshaft 9 of the piston engine 10 are rigidly connected by a conical interference fit, and this connection is simple and compact in structure and has no transmission mechanical loss.
Based on the system, the quick starting process of the ejection type unmanned aerial vehicle power system is as follows:
the control module 3 sends a takeoff instruction of the unmanned aerial vehicle, starts an unmanned aerial vehicle ejection program, and completely ejects the unmanned aerial vehicle out of the box after 0.5 s; after the unmanned aerial vehicle is completely ejected out of the box, the control module 3 sends a starting instruction, the direct-current brushless motor 8 and the piston engine 10 are started simultaneously, the high-voltage electronic speed regulator 5 controls the direct-current brushless motor 8 to output full load within 2s after the takeoff instruction is sent, meanwhile, the control module 3 sets an accelerator of the piston engine 10 to be medium and small load (15% -35% load), the piston engine 10 is quickly and reliably started under the dragging of the direct-current brushless motor 8 and enters a warming-up program, in the process, the piston engine 10 drives the propeller 11 to take-off rotating speed and maintains the speed for not less than 30s, the airspeed of the unmanned aerial vehicle at the initial stage of the takeoff stage is kept, and the unmanned aerial vehicle normally climbs to a safe height;
after a takeoff instruction is sent out for 30.5s, an engine warm-up program is completed, the piston engine 10 immediately outputs maximum power to the outside in full load, the propeller 11 is driven to provide power for the unmanned aerial vehicle and complete the subsequent takeoff process, meanwhile, the high-voltage electronic speed regulator 5 controls the zero-load output of the direct-current brushless motor 8, and the direct-current brushless motor 8 does not output power to the outside any more.
The unmanned aerial vehicle adopts a starting mode that the piston engine 10 and the direct-current brushless motor 8 are matched, so that the requirement of the box body launching cluster unmanned aerial vehicle on quick response of a starting system in a take-off stage is met. Meanwhile, the starting system is high in starting speed, good in low-temperature starting performance and reliable in starting, and flight safety in the takeoff phase is guaranteed. In addition, in the cruising stage of the unmanned aerial vehicle, the onboard battery pack 6 can be charged by controlling the on-load operation of the direct current brushless motor 8, so that the cruising time of the unmanned aerial vehicle is prolonged.
The method adopts a starting mode that the piston engine 10 and the direct current brushless motor 8 are matched, so that the rapid starting and the full-load operation can be realized within 1.5s after the starting instruction is sent out, and the rapid full-load response requirement of the cluster unmanned aerial vehicle box body on the starting system 2 in the launching and taking-off stage is met.
In the embodiment of the invention, the power system 2 mainly comprises a piston engine 10, a propeller 11, a direct current brushless motor 8, a high-voltage electronic speed regulator 5, a starting lithium battery pack 4, a control module 3, a voltage-stabilized power supply module 7 and an airborne battery pack 6. In order to realize the application effect of the method, when the type selection is determined, the full load output power of the direct current brushless motor 8 is not less than the full load output power of the engine, and the full load output power of the engine is not less than the power required by takeoff. Specifically, the output power of the brushless direct current motor 8 is 12kw at the rotation speed 6200rpm, the output power of the engine is 10.5kw at the rotation speed 6200rpm, and the required power in the takeoff stage is about 9.5 kw.
Before taking off, the control module 3 is powered by an onboard battery pack 6 through a regulated power supply module 7. During taking off, the control module 3 sends out a taking-off instruction, starts a small-sized foldable fixed wing unmanned aerial vehicle ejection program during long voyage, and ejects the unmanned aerial vehicle out of the box after 0.5 s; after a takeoff instruction is sent for 0.5s, a control module 3 sends a starting instruction, a direct-current brushless motor 8 and a piston engine 10 are started simultaneously, a high-voltage electronic speed regulator 5 controls the direct-current brushless motor 8 to output full load within 1.5s, meanwhile, an accelerator of the piston engine is set to be 35% of load, the piston engine 10 is started quickly and reliably under the dragging of the direct-current brushless motor 8 and enters a warming-up program, in the process, the piston engine 10 drives a propeller 11 to be not lower than the takeoff rotating speed of 6200rpm and maintains not less than 30s, the airspeed of the unmanned aerial vehicle in the takeoff stage is kept, and the unmanned aerial vehicle normally climbs to a safe height; after a takeoff instruction is sent out for 30.5s, an engine warm-up program is finished, the engine warm-up program immediately outputs maximum power to the outside under full load, the propeller 11 is driven to rotate at a speed not lower than 6200rpm, power is provided for the unmanned aerial vehicle, a follow-up takeoff process is completed, meanwhile, the high-voltage electronic speed regulator 5 controls the zero-load output of the direct-current brushless motor 8, the direct-current brushless motor 8 quits working, and the power is not output to the outside.
The power system has high starting rotating speed, particularly 6200rpm, and long duration which can reach 30s at most, so that the power system has good low-temperature starting performance and reliable starting, and can ensure the flight safety in the takeoff stage.
Claims (5)
1. A quick starting method of a power system of an ejection type unmanned aerial vehicle is characterized by comprising the following steps: the method is realized on the basis of a power system (2) arranged at the tail part of an unmanned aerial vehicle body (1), wherein the power system (2) comprises a piston engine (10), a direct-current brushless motor (8), a high-voltage electronic speed regulator (5), a starting lithium battery pack (4), a voltage-stabilized power supply module (7), a control module (3) and an airborne battery pack (6);
the output end of the piston engine (10) is connected with a propeller (11); the direct current brushless motor (8) is arranged at the front end of the piston type engine (10), and a rotor (12) of the direct current brushless motor is rigidly connected with a crankshaft (9) of the piston type engine (10); the full-load output power of the direct current brushless motor (8) is not less than that of the piston engine (10), and the full-load output power of the piston engine (10) is not less than the absorption power of the propeller (11) at the take-off rotating speed;
the high-voltage electronic speed regulator (5) is arranged inside the unmanned aerial vehicle body (1), the input end of the high-voltage electronic speed regulator is respectively connected with the starting lithium battery pack (4) and the control module (3), and the output end of the high-voltage electronic speed regulator is connected with a winding of the direct-current brushless motor (8); the starting lithium battery pack (4) provides electric energy for the direct current brushless motor (8) through the high-voltage electronic speed regulator (5); the onboard battery pack (6) supplies power to the control module (3) and the high-voltage electronic speed regulator (5) through a voltage-stabilized power supply module (7) respectively;
the method comprises the following steps:
step one, a control module (3) sends a take-off instruction, an unmanned aerial vehicle ejection program is started, and the unmanned aerial vehicle is ejected out of a box completely;
after the unmanned aerial vehicle is ejected out of the tank completely, the control module (3) sends a starting instruction, the direct-current brushless motor (8) and the piston engine (10) are started simultaneously, the high-voltage electronic speed regulator (5) controls the direct-current brushless motor (8) to output full load within T1 time, meanwhile, the control module (3) sets an accelerator of the piston engine (10) to be medium-low load, the piston engine (10) is started quickly under the dragging of the direct-current brushless motor (8), and a warming-up program is started;
and step three, immediately outputting maximum power to the outside under full load after a warm-up procedure of the piston engine (10) is completed, driving a propeller (11) to provide power for the unmanned aerial vehicle and completing a subsequent take-off process, and simultaneously controlling zero-load output of the direct current brushless motor (8) by the high-voltage electronic speed regulator (5), wherein the direct current brushless motor (8) does not output power to the outside any more.
2. The method for rapidly starting the catapult-type unmanned aerial vehicle power system according to claim 1, characterized in that: the rotor (12) of the direct current brushless motor is rigidly connected with the crankshaft (9) of the piston engine (10) through conical surface interference fit.
3. The method for rapidly starting the catapult-type unmanned aerial vehicle power system according to claim 1, characterized in that: starting system (2) pass through damping device and set up the fuselage afterbody at unmanned aerial vehicle body (1).
4. The method for rapidly starting the catapult type unmanned aerial vehicle power system according to claim 1, 2 or 3, characterized in that in the second step, the throttle of the piston engine (10) is set to be a medium-small load, specifically: throttle setting 15% -35% load, T1=1.5 s.
5. The method for rapidly starting the catapult-type unmanned aerial vehicle power system according to claim 4, wherein the method comprises the following steps: the piston engine (10) is a small-sized aviation piston engine.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115839283A (en) * | 2023-02-22 | 2023-03-24 | 四川腾盾科技有限公司 | Starting method and system for piston engine of unmanned aerial vehicle |
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