1. The transmission and control system of the oil-driven multi-rotor aircraft is characterized by comprising a transmission unit and a control unit, wherein the transmission unit is used for taking electric energy as an energy transmission medium, transmitting mechanical energy to a propeller and driving the propeller to rotate to provide energy required by flight; the control unit is used for outputting instructions and executing the instructions to change the pitch of the propeller to change the lift force and the counter-torque force of the propeller, controlling the attitude of the aircraft to realize hovering and flying in all directions by utilizing the lift force and the counter-torque force of each rotor wing, sending control signals to the transmission unit to stabilize the rotating speed of the power mechanism and adjust the total energy of the aircraft, monitoring the rotating speed of the engine and the rotating speed of the pitch-variable propeller, and judging whether the transmission system works normally or not through the comparison of the rotating speeds of the engine and the pitch-variable propeller.

2. The transmission and control system for an oil-driven multi-rotor aircraft according to claim 1, wherein the transmission unit includes an engine, a generator, an ac synchronous motor, and a variable pitch propeller, the generator is disposed on the engine, an electrical power output terminal of the generator is connected to an electrical power input terminal of the ac synchronous motor, and the variable pitch propeller is disposed on the ac synchronous motor.

3. The transmission and control system of an oil-driven multi-rotor aircraft according to claim 2, wherein the transmission unit further comprises an oil tank, the oil tank is disposed on the engine, and the fuel in the oil tank provides energy power for the engine to operate to drive the generator to generate electric energy.

4. The transmission and control system for an oil-driven multi-rotor aircraft according to claim 3, wherein there are a plurality of ac synchronous motors powered by the generator, each ac synchronous motor having a variable pitch propeller.

5. The transmission and control system of the oil-driven multi-rotor aircraft according to claim 4, wherein the control unit comprises a flight control unit and a servo steering engine, the output end of the flight control unit is connected with the control end of the servo steering engine and the control end of the engine respectively, the servo steering engine is arranged on the variable pitch propeller, and the electric energy output end of the generator is connected with the electric energy input end of the flight control unit.

6. The transmission and control system of an oil-driven multi-rotor aircraft according to claim 5, wherein the number of servo steering engines is multiple, the control end of each servo steering engine is connected to the output end of the flight control, and each servo steering engine controls the lift force and the counter torque force of a variable pitch propeller.

7. An oil-driven multi-rotor aircraft, comprising the transmission and control system according to any one of claims 1 to 6 and a frame on which the transmission and control system is provided.

8. The oil-driven multi-rotor aircraft according to claim 7, wherein the frame includes a bracket, a fixed plate, and a plurality of connecting rods, the fixed plate being disposed on the bracket, the plurality of connecting rods being disposed on the fixed plate, respectively.

9. The oil-driven multi-rotor aircraft according to claim 8, wherein the plurality of connecting rods and the fixed plate are located on the same plane, and the included angles formed by two adjacent connecting rods are equal.

Background

Most of the existing oil-driven multi-rotor aircrafts adopt a range extending scheme, namely, an engine drives a generator to generate electricity, a rectifier rectifies alternating current generated by the generator into direct current, and the direct current is matched with a battery to jointly supply power to an electronic speed regulator (the direct current output by the rectifier can also be charged by the battery and is distributed by a power management system). The electronic speed regulator receives the command sent by the flight control to drive the alternating current synchronous motor to rotate, and adjusts the rotating speed of the alternating current synchronous motor according to the command, so that the attitude and the flight direction of the aircraft are controlled.

The existing oil-driven multi-rotor technical scheme is only provided with one set of power generation system in the pure electric multi-rotor technology, and the endurance time of the aircraft is prolonged. However, the following disadvantages still exist in the technology: the energy utilization efficiency is low. The technology has more energy conversion times, and the energy conversion process sequentially comprises the following steps: chemical energy → mechanical energy → alternating current → direct current → alternating current → mechanical energy. When the generator charges the battery and then uses the battery to drive the electronic speed regulator, the energy conversion efficiency is as follows in sequence: chemical energy → mechanical energy → alternating current → direct current → chemical energy → direct current → alternating current → mechanical energy. Each energy conversion causes energy loss, resulting in a reduction in overall energy utilization.

The scheme is low in reliability when applied to a large unmanned aerial vehicle, the technology relates to an engine, a generator, a rectifier, a battery, a power management system, flight control, an electronic speed regulator and a motor, and flight safety can be influenced by any one set of system faults. Especially, the prior high-power management system and the electronic speed regulator are not mature enough in technology and low in stability.

The flight control technology has defects when the scheme is applied to a large unmanned aerial vehicle, the posture of the aircraft is adjusted by a method for adjusting the rotating speed of the rotor wing, and the rotating speed of the rotor wing needs to be frequently adjusted in the flight process. The rotary wing of the large aircraft has large rotary inertia, and the rotating speed adjustment response speed is slow, so that the attitude control response of the aircraft is slow, and the aircraft is difficult to control.

Disclosure of Invention

The invention aims to provide a transmission and control system of an oil-driven multi-rotor aircraft, and aims to solve the technical problems of low fuel efficiency, slow control response and low reliability of the existing oil-driven multi-rotor aircraft.

The transmission and control system of the oil-driven multi-rotor aircraft comprises a transmission unit and a control unit, wherein the transmission unit is used for transmitting mechanical energy to a propeller by taking electric energy as an energy transmission medium to drive the propeller to rotate so as to provide energy required by flight; the control unit is used for outputting instructions and executing the instructions to change the pitch of the propeller to change the lift force and the counter-torque force of the propeller, controlling the attitude of the aircraft to realize hovering and flying in all directions by utilizing the lift force and the counter-torque force of each rotor wing, sending control signals to the transmission unit to stabilize the rotating speed of the power mechanism and adjust the total energy of the aircraft, monitoring the rotating speed of the engine and the rotating speed of the pitch-variable propeller, and judging whether the transmission system works normally or not through the comparison of the rotating speeds of the engine and the pitch-variable propeller.

The further technical scheme of the invention is as follows: the transmission unit comprises an engine, a generator, an alternating current synchronous motor and a variable pitch propeller, wherein the generator is arranged on the engine, the electric energy output end of the generator is connected with the electric energy input end of the alternating current synchronous motor, and the variable pitch propeller is arranged on the alternating current synchronous motor.

The further technical scheme of the invention is as follows: the transmission unit further comprises an oil tank, the oil tank is arranged on the engine, and the fuel oil in the oil tank provides energy power for the engine to drive the generator to generate electric energy.

The further technical scheme of the invention is as follows: the alternating current synchronous motor is multiple, multiple alternating current synchronous motors supply energy through the generators, and each alternating current synchronous motor is provided with a variable pitch propeller.

The further technical scheme of the invention is as follows: the control unit comprises a flight control unit and a servo steering engine, the output end of the flight control unit is respectively connected with the control end of the servo steering engine and the control end of the engine, the servo steering engine is arranged on the variable pitch propeller, and the electric energy output end of the generator is connected with the electric energy input end of the flight control unit.

The further technical scheme of the invention is as follows: the servo steering engine is multiple, the control end of each servo steering engine is connected with the output end of the flight control, and each servo steering engine controls the lifting force and the counter-torque force of a variable pitch propeller.

Another object of the present invention is to provide an oil-driven multi-rotor aircraft, which includes a transmission and control system and a frame, wherein the transmission and control system is disposed on the frame.

The further technical scheme of the invention is as follows: the rack comprises a support, a fixing plate and a plurality of connecting rods, wherein the fixing plate is arranged on the support, and the connecting rods are arranged on the fixing plate respectively.

The further technical scheme of the invention is as follows: a plurality of the connecting rods with the fixed plate is located the coplanar, and the contained angle that two adjacent connecting rods constitute equals.

The invention has the beneficial effects that: the transmission system of the alternating current synchronous motor driven by the alternating current generated by the generator is adopted to transmit the energy of the oil-driven engine to the propeller, so that the energy conversion process is reduced compared with the traditional extended-range oil-driven multi-rotor aircraft, and the energy utilization rate is improved; two important technical short boards, namely a power management system and an electronic speed regulator, in the original technical scheme are avoided, and the overall stability is still higher than that of the original system although a set of servo steering engine system is added; the attitude control adopts a variable pitch method to replace a variable rotating speed method in the original technical scheme, and the attitude control response is faster when the method is applied to a large aircraft.

Drawings

Fig. 1 is a block diagram of a transmission and control system of a conventional aircraft.

Fig. 2 is a block diagram of a transmission and control system of an oil-driven multi-rotor aircraft according to an embodiment of the present invention.

Fig. 3 is a schematic structural diagram of an oil-driven multi-rotor aircraft provided by an embodiment of the invention.

Fig. 4 is an exploded schematic view of an oil-driven multi-rotor aircraft according to an embodiment of the present invention.

Fig. 5 is a schematic structural diagram of a variable pitch propeller, a servo steering engine, an ac synchronous motor and a rotation speed sensor according to an embodiment of the present invention.

Detailed Description

Reference numerals: 10-frame 20-flight control 30-servo steering engine 40-variable pitch propeller 50-alternating current synchronous motor 60-engine 70-generator 80-oil tank 90-101-fixed plate 102-support 103-connecting rod

As shown in fig. 1, the transmission and control system of the oil-driven multi-rotor aircraft provided by the invention comprises a transmission unit and a control unit, wherein the output end of the control unit is connected with the input end of the transmission unit, the electric energy output end of the transmission unit is connected with the input end of the control unit, and the transmission unit takes electric energy as an energy transmission medium, transmits the mechanical energy of an engine to a propeller and drives the propeller to rotate. Flight control in the control system sends out the instruction, and servo steering wheel execution instruction changes the pitch of screw thereby changes the lift and the counter-torque force of screw. The flight control controls the attitude of the aircraft by controlling the lift force and the counter-torque force of each rotor wing, and achieves the purposes of hovering and flying in all directions.

The transmission unit comprises an engine 60, a generator 70, an alternating current synchronous motor 50 and a variable pitch propeller 40, wherein the generator 70 is arranged on the engine 60, the electric energy output end of the generator 70 is connected with the electric energy input end of the alternating current synchronous motor 50, and the variable pitch propeller 40 is arranged on the alternating current synchronous motor 50. The main characteristics include that the generator only transmits energy between the AC synchronous motors through AC; secondly, the system only provides energy required by flight and does not participate in flight attitude control. And thirdly, the control signal of the flight control to the engine is used for stabilizing the rotating speed of the engine and adjusting the total energy of the aircraft.

The transmission unit further comprises an oil tank 80, wherein the oil tank 80 is arranged on the engine 60, and the fuel oil in the oil tank 80 provides energy power for the engine to run so as to drive the generator 70 to generate electric energy.

The alternating current synchronous motors 50 are multiple, the alternating current synchronous motors 50 are powered by the power generator 70, and each alternating current synchronous motor 50 is provided with a variable pitch propeller 40.

The control unit comprises a flight control 20 and a servo steering engine 30, the output end of the flight control 20 is respectively connected with the control end of the servo steering engine 30 and the control end of an engine, the servo steering engine 30 is arranged on the variable pitch propeller 40, and the electric energy output end of the generator 70 is connected with the electric energy input end of the flight control 20.

The servo steering engines 30 are multiple, the control end of each servo steering engine 30 is connected with the output end of the flight control, and each servo steering engine 30 controls the lifting force and the counter-torque force of a variable pitch propeller 40.

Another object of the present invention is to provide an oil-driven multi-rotor aircraft, which includes a transmission and control system and a frame 10, wherein the transmission and control system is disposed on the frame 10.

The rack comprises a bracket 102, a fixing plate 101 and a plurality of connecting rods 103, wherein the fixing plate 101 is arranged on the bracket 102, and the connecting rods 103 are respectively arranged on the fixing plate 101.

The connecting rods 103 and the fixing plate 101 are located on the same plane, and the included angles formed by the two adjacent connecting rods 103 are equal.

The following is an embodiment of the present invention: this embodiment is a four rotor oil moves pitch control aircraft.

The aircraft mainly comprises a frame 10, an engine 60, a flight control 20, a generator 70, an alternating current synchronous motor 50, a servo steering engine 30, a variable pitch propeller 40, an oil tank 80 and the like.

The engine 60 drives the generator 70 to rotate, alternating current generated by the generator 70 is transmitted to the alternating current synchronous motor 50 through a cable, and the alternating current synchronous motor 50 drives the variable pitch propeller 40 to rotate, so that the aircraft obtains energy required by flight.

And a rotating speed sensor 90 is arranged on the alternating current synchronous motor 50 and is connected with the flight control two-way communication.

The flight control 20 sends out an instruction, and the servo steering engine 30 deflects according to the instruction of the flight control 20 to drive the propeller pitch of the propeller to change, so that the lift force of the propeller is changed. The flight control 20 achieves the purpose of controlling the attitude of the aircraft by controlling the lift force and the counter-torque force of each propeller through the method.

The flight control unit 20 gives a command to the engine 60 to control the rotation speed of the engine 60. Since a change in pitch during flight results in a change in the rotational resistance of the propeller and then a change in the rotational speed of the engine 60. The flight control 20 must monitor the engine speed in real time and make adjustments. When the rotating speed of the engine 60 is too low or the current energy of the aircraft is lower than the energy required by flight, the flight control unit 20 sends out an instruction to increase the accelerator to increase the rotating speed of the engine; conversely, when the engine 60 speed is too high, the flight control 20 commands a decrease in the throttle to reduce the engine 60 speed.

The flight control 20 detects the rotating speed signal of the propeller and the rotating speed of the engine 60, and judges whether the transmission system works normally or not by comparing the rotating speeds of the propeller and the engine. And if the transmission is abnormal, the flight control takes corresponding measures to prevent the airplane from being out of control.

The transmission system that the generator 70 sends out alternating current and drives the alternating current synchronous motor 50 is adopted, the energy of the oil-driven engine 60 is transmitted to the propeller, and compared with the traditional extended-range oil-driven multi-rotor aircraft, the energy conversion process is reduced, and the energy utilization rate is improved.

Two important technical short boards of a power management system and an electronic speed regulator in the original technical scheme are avoided, and the overall stability is still higher than that of the original system although a set of servo steering engine 30 system is added.

The attitude control adopts a variable pitch method to replace a variable rotating speed method in the original technical scheme, and the attitude control response is faster when the method is applied to a large aircraft.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.