An electromagnetic interference-proof oil-powered vertical take-off and landing fixed-wing UAV

Abstract

The present invention is applicable to the field of unmanned aerial vehicles (UAVs) and discloses an electromagnetic interference-resistant oil-powered vertical take-off and landing fixed-wing UAV. The UAV comprises a fuselage, a rotor assembly, a steering gear assembly, an oil-powered engine, an igniter, a flight controller, an electronic speed controller assembly, a power supply assembly, and an optical transmission system. The optical transmission system comprises a control sending assembly, an input speed measurement sending module, a control receiving assembly, and an input speed measurement receiving module. The steering gear assembly, the control sending assembly, and the input speed measurement receiving module are respectively connected to the flight controller. The control sending assembly and the rotor assembly are respectively connected to the electronic speed controller assembly. The input speed measurement sending module and the oil-powered engine are respectively connected to the igniter. The power supply assembly supplies power to the electronic speed controller assembly and the flight controller through a first power module and a second power module. The steering gear assembly, the optical transmission system, and the igniter are divided into zones and supplied with power in common. This can reduce electromagnetic interference and improve the flight safety of the UAV.

Description

Technical Field

[0001] The present invention relates to the field of unmanned aerial vehicles (UAVs), and in particular to an electromagnetic interference-resistant oil-powered vertical take-off and landing fixed-wing UAV. Background Art

[0002] A gasoline-powered vertical takeoff and landing (VTOL) fixed-wing drone achieves vertical takeoff and landing capabilities through front, rear, and left / right jet thrusters, with forward thrust provided by a gasoline engine. As the gasoline engine rotates, a Hall effect element, located adjacent but fixed to the magnetic bead on the rotating shaft, generates pulses that trigger a high-voltage spark in the igniter, periodically igniting the gasoline in the fuel injection device, thereby driving the gasoline engine to rotate continuously. However, the high-voltage pulses output by the igniter, as well as the high-frequency pulses modulated by the electronic control system and the large current surges, can cause electromagnetic interference to the weak current control lines, potentially causing the drone to lose control and affect its normal operation. Summary of the Invention

[0003] The purpose of the present invention is to provide an electromagnetic interference-proof oil-powered vertical take-off and landing fixed-wing UAV, which aims to solve the technical problem that the high-voltage pulses output by the high-voltage package of the oil-powered vertical take-off and landing fixed-wing UAV, as well as the high-frequency pulses modulated by the electronic control and large current mutations, may cause electromagnetic interference to the weak-current control line, which may easily cause the UAV to lose control and affect the normal operation of the UAV.

[0004] To achieve the above-mentioned purpose, the solution provided by the present invention is: an electromagnetic interference-proof oil-powered vertical take-off and landing fixed-wing UAV, comprising an optical transmission system, a fuselage and a rotor assembly arranged on the fuselage, a servo assembly, an oil-powered engine, an igniter, a flight controller, an electronic speed controller assembly and a power supply assembly, wherein the optical transmission system comprises a control sending assembly, an input speed measurement sending module, a control receiving assembly that transmits optical signals to the control sending assembly, and an input speed measurement receiving module that transmits optical signals to the input speed measurement sending module, the servo assembly, the control sending assembly and the input speed measurement receiving module are respectively connected to the flight controller, the control sending assembly and the rotor assembly are respectively connected to the electronic speed controller assembly, the input speed measurement sending module and the oil-powered engine are respectively connected to the igniter, and the power supply assembly comprises a first power supply module block, a second power supply module and a DC power converter, the first power supply module is used to generate a first power supply to power the electronic speed controller component, and the electronic speed controller component powers the control receiving component and the rotor component. The first power supply module is connected to the DC power converter and generates a second power supply and a third power supply with input and output ground isolation through the DC power converter. The second power supply is used to power the flight controller, and the third power supply is used to power the servo component, the input speed measurement receiving module and the control sending component. The flight controller, the servo component, the input speed measurement receiving module and the control sending component share a common ground. The second power supply module is used to power the input speed measurement sending module and the igniter. The input speed measurement sending module and the igniter share a common ground, and the igniter powers the oil-driven engine.

[0005] Preferably, the voltage value of the first power supply module is 45.6V, the voltage value of the first power supply is 45.6V, the voltage value of the second power supply is 12V, and the voltage value of the third power supply is 5V.

[0006] Preferably, the voltage value of the second power supply module is 7.2V.

[0007] Preferably, the rotor assembly includes a left front rotor, a left rear rotor, a right front rotor and a right rear rotor, the control sending assembly includes a first sending module, a second sending module, a third sending module and a fourth sending module, the first sending module, the second sending module, the third sending module and the fourth sending module are electrically connected to the flight controller respectively, the control receiving assembly includes a first receiving module connected to the first sending module via an optical fiber, a second receiving module connected to the second sending module via an optical fiber, a third receiving module connected to the third sending module via an optical fiber, and a fourth receiving module connected to the fourth sending module via an optical fiber, the electronic speed controller assembly includes a left front electric regulator, a left rear electric regulator, a right front electric regulator and a right rear electric regulator, the first receiving module and the left front rotor are electrically connected to the left front electric regulator respectively, the second receiving module and the left rear rotor are electrically connected to the left rear electric regulator respectively, the The third receiving module and the right front rotor are electrically connected to the right front electric regulator respectively, and the fourth receiving module and the right rear rotor are electrically connected to the right rear electric regulator respectively; the first power supply supplies power to the left front electric regulator, the left rear electric regulator, the right front electric regulator and the right rear electric regulator, and the left front electric regulator, the left rear electric regulator, the right front electric regulator and the right rear electric regulator share a common ground; the left front electric regulator supplies power to the left front rotor, the left rear electric regulator supplies power to the left rear rotor, the right front electric regulator supplies power to the right front rotor, and the right rear electric regulator supplies power to the right rear rotor; the third power supply is used to supply power to the servo assembly, the input speed measurement receiving module, the first sending module, the second sending module, the third sending module and the fourth sending module, and the flight controller, the servo assembly, the input speed measurement receiving module, the first sending module, the second sending module, the third sending module and the fourth sending module share a common ground.

[0008] Preferably, the servo assembly includes a throttle servo, a left tail servo, a right tail servo, a left aileron servo and a right aileron servo; the throttle servo, the left tail servo, the right tail servo, the left aileron servo and the right aileron servo are electrically connected to the flight controller respectively; the third power supply is used to power the throttle servo, the left tail servo, the right tail servo, the left aileron servo, the right aileron servo, the input speed measurement receiving module, the first sending module, the second sending module, the third sending module and the fourth sending module; the flight controller, the throttle servo, the left tail servo, the right tail servo, the left aileron servo, the right aileron servo, the input speed measurement receiving module, the first sending module, the second sending module, the third sending module and the fourth sending module are grounded in common.

[0009] Preferably, the first sending module, the second sending module, the third sending module, the fourth sending module and the input speed measurement sending module have the same structure. The first sending module includes a transistor Q1, a first optocoupler chip OC1, a first resistor R1, a second resistor R2, a third resistor R3, a first capacitor C1 and a second capacitor C2. The output end of the flight controller is respectively connected to the base of the transistor Q1 and the grounded first capacitor C1 through the first resistor R1, the collector of the transistor Q1 is connected to the grounded second resistor R2, the emitter of the transistor Q1 is connected to the TX- pin of the first optocoupler chip OC1 and one end of the third resistor R3, the TX+ pin of the first optocoupler chip OC1, the other end of the third resistor R3 and the positive electrode of the second capacitor C2 are respectively connected to the third power supply, and the negative electrode of the second capacitor C2 is grounded.

[0010] Preferably, the first receiving module, the second receiving module, the third receiving module, the fourth receiving module and the input speed measurement receiving module have the same structure. The first receiving module includes a second optocoupler chip OC2, a fourth resistor R4, an inductor L1, a third capacitor C3 and a fourth capacitor C4. The input end of the left front electronic regulator is respectively connected to the Data pin of the second optocoupler chip OC2 and one end of the fourth resistor R4, the GND pin of the second optocoupler chip OC2 is grounded, and the VCC pin of the second optocoupler chip OC2 is respectively connected to one end of the inductor L1, one end of the third capacitor C3 and one end of the fourth capacitor C4. The other end of the fourth resistor R4 and the other end of the inductor L1 are respectively connected to the left front electronic regulator, and one end of the fourth capacitor C4 is also connected to one end of the fourth resistor R4; the other end of the third capacitor C3 and the other end of the fourth capacitor C4 are respectively grounded.

[0011] The present invention provides a method for generating a first power supply for powering an electronic speed controller component through a first power supply module, and generating a second power supply and a third power supply with isolated input and output grounds through a DC power converter. The second power supply is used to power a flight controller, and the third power supply is used to power a steering gear component, an input speed measurement receiving module, and a control sending component. In addition, the second power supply module is used to power the input speed measurement sending module and an igniter, thereby realizing partitioned common ground power supply. This method can solve the interference problem between the modulated high-frequency signal of the electronic speed controller component and the sudden change signal ground of the power current, the steering gear and flight control ground, and the high-voltage ignition pulse ground of the oil-driven engine, and realize an anti-interference circuit that completely isolates the flight controller and steering gear component circuits, the igniter circuit, and the electronic speed controller component circuit. In addition, this embodiment is provided with a control sending component, an input speed measurement sending module, a control receiving component and an input speed measurement receiving module, and the control sending component and the input speed measurement receiving module are connected to the flight controller, the control receiving component is connected to the electronic speed controller component, and the input speed measurement sending module is connected to the igniter. The control sending component and the input speed measurement sending module can convert electrical signals into optical signals, and then transmit them to the control receiving component and the input speed measurement receiving module. The optical signal transmission will not be affected by electromagnetic interference, which greatly improves the security of signal transmission and can further improve flight safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying any creative work.

[0013] Figure 1 This is a structural block diagram of an electromagnetic interference-proof oil-powered vertical take-off and landing fixed-wing UAV provided by an embodiment of the present invention;

[0014] Figure 2 yes Figure 1 A magnified view of middle A;

[0015] Figure 3 yes Figure 1 Enlarged view of middle B;

[0016] Figure 4 is a circuit diagram of a first sending module provided in an embodiment of the present invention;

[0017] Figure 5 This is a circuit diagram of a first receiving module provided by an embodiment of the present invention.

[0018] Description of Figure Numbers:

[0019] 10. Power supply assembly; 11. First power module; 12. Second power module; 20. Rotor assembly; 21. Left front rotor; 22. Left rear rotor; 23. Right front rotor; 24. Right rear rotor; 30. Servo assembly; 31. Throttle servo; 32. Left tail servo; 33. Right tail servo; 34. Left aileron servo; 35. Right aileron servo; 40. Oil engine; 50. Ignition; 60. Flight controller; 70. Electronic speed controller assembly; 71 , left front ESC; 72, left rear ESC; 73, right front ESC; 74, right rear ESC; 80, control sending component; 81, first sending module; 82, second sending module; 83, third sending module; 84, fourth sending module; 90, input speed measurement sending module; 100, control receiving component; 101, first receiving module; 102, second receiving module; 103, third receiving module; 104, fourth receiving module; 110, input speed measurement receiving module. DETAILED DESCRIPTION

[0020] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0021] It should be noted that all directional indications in the embodiments of the present invention (such as up, down, left, right, front, back, etc.) are only used to explain the relative position relationship, movement status, etc. between the various components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0022] It should also be noted that when an element is referred to as being "fixed on" or "disposed on" another element, it may be directly on the other element or there may be an intermediate element. When an element is referred to as being "connected to" another element, it may be directly connected to the other element or there may be an intermediate element.

[0023] In addition, the descriptions of "first", "second", etc. in the present invention are for descriptive purposes only and should not be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" or "second" may explicitly or implicitly include at least one of such features. In addition, the technical solutions between the various embodiments can be combined with each other, but this must be based on the fact that they can be implemented by ordinary technicians in this field. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0024] like Figures 1 to 5 As shown, it is an electromagnetic interference-proof oil-powered vertical take-off and landing fixed-wing UAV according to an embodiment of the present invention.

[0025] See also Figure 1-Figure 3 As shown, the electromagnetic interference-proof oil-powered vertical take-off and landing fixed-wing UAV of the embodiment of the present invention includes a fuselage (not shown), a rotor assembly 20, a steering gear assembly 30, a oil-powered engine 40, an igniter 50, a flight controller 60, an electronic speed controller assembly 70, a power supply assembly 10 and an optical transmission system. The rotor assembly 20, the steering gear assembly 30, the oil-powered engine 40, the igniter 50, the flight controller 60, the electronic speed controller assembly 70 and the power supply assembly 10 are all arranged on the fuselage. The optical transmission system includes a control sending assembly 80, an input speed measurement sending module 90, a control receiving assembly 100 that transmits optical signals with the control sending assembly 80, and an input speed measurement receiving module 110 that transmits optical signals with the input speed measurement sending module 90. The steering gear assembly 30, the control sending assembly 80 and the input speed measurement receiving module 110 are respectively connected to the flight controller 60, the control sending assembly 80 and the rotor assembly 20 are respectively connected to the electronic speed controller assembly 70, and the input speed measurement sending module 90 and the oil-driven engine 40 are respectively connected to the igniter 50. The power supply assembly 10 includes a first power supply module 11, a second power supply module 12 and a DC power converter (not shown). The first power supply module 11 is used to generate a first power supply to power the electronic speed controller assembly 70. The electronic speed controller assembly 70 powers the control receiving assembly 100 and the rotor assembly 20. The first power supply module 11 is connected to the DC power converter and generates a second power supply and a third power supply with isolated input and output grounds through the DC power converter. The second power supply is used to power the flight controller 60. The third power supply is used to power the steering gear assembly 30, the input speed measurement receiving module 110 and the control sending assembly 80. The flight controller 60, the steering gear assembly 30, the input speed measurement receiving module 110 and the control sending assembly 80 share a common ground. The second power supply module 12 is used to power the input speed measurement sending module 90 and the igniter 50. The input speed measurement sending module 90 and the igniter 50 share a common ground. The igniter 50 powers the oil-driven engine 40.

[0026] In this embodiment, the voltage value of the first power module 11 is 45.6V, the voltage value of the first power supply is 45.6V, the voltage value of the second power supply is 12V, and the voltage value of the third power supply is 5V.

[0027] In this embodiment, the voltage value of the second power module 12 is 7.2V.

[0028] In this embodiment, a first power supply is generated by the first power supply module 11 to supply power to the electronic speed controller assembly 70, and a second power supply and a third power supply with isolated input and output grounds are generated by a DC power converter. The second power supply is used to supply power to the flight controller 60, and the third power supply is used to supply power to the servo assembly 30, the input speed measurement receiving module 110 and the control sending assembly 80. In addition, the second power supply module 12 is used to supply power to the input speed measurement sending module 90 and the igniter 50, thereby realizing partitioned common ground power supply, solving the interference problem between the modulated high-frequency signal of the electronic speed controller assembly 70 and the sudden change signal ground of the power current, the servo and flight control grounds, and the high-voltage ignition pulse ground of the oil-powered engine 40, and realizing an anti-interference circuit with complete isolation between the flight controller 60 and the servo assembly 30 circuits, the igniter 50 circuit, and the electronic speed controller assembly 70 circuits. In addition, this embodiment is provided with a control sending component 80, an input speed measurement sending module 90, a control receiving component 100 and an input speed measurement receiving module 110, and the control sending component 80 and the input speed measurement receiving module 110 are connected to the flight controller 60, the control receiving component 100 is connected to the electronic speed controller component 70, and the input speed measurement sending module 90 is connected to the igniter 50. The control sending component 80 and the input speed measurement sending module 90 can convert electrical signals into optical signals, and then transmit them to the control receiving component 100 and the input speed measurement receiving module 110. The optical signal transmission will not be affected by electromagnetic interference, which greatly improves the safety of signal transmission and can further improve flight safety.

[0029] See also Figure 3As shown, in some embodiments, for example, the rotor assembly 20 includes a left front rotor 21, a left rear rotor 22, a right front rotor 23 and a right rear rotor 24, the control sending component 80 includes a first sending module 81, a second sending module 82, a third sending module 83 and a fourth sending module 84, the first sending module 81, the second sending module 82, the third sending module 83 and the fourth sending module 84 are electrically connected to the flight controller 60 respectively, and the control receiving component 100 includes a first receiving module connected to the first sending module 81 through an optical fiber. The first receiving module 101, the second receiving module 102 connected to the second sending module 82 via an optical fiber, the third receiving module 103 connected to the third sending module 83 via an optical fiber, and the fourth receiving module 104 connected to the fourth sending module 84 via an optical fiber. The electronic speed controller assembly 70 includes a left front electric adjustment 71, a left rear electric adjustment 72, a right front electric adjustment 73 and a right rear electric adjustment 74. The first receiving module 101 and the left front rotor 21 are electrically connected to the left front electric adjustment 71 respectively, and the second receiving module 102 and the left rear rotor 22 are electrically connected to the left rear electric adjustment 71 respectively. The left front electric regulator 71 supplies power to the left front rotor 21, the left rear electric regulator 72 supplies power to the left rear rotor 22, and the right front electric regulator 73 supplies power to the right rear rotor 23. The right rear ESC 74 supplies power to the right rear rotor 24; the third power supply is used to supply power to the servo assembly 30, the input speed measurement receiving module 110, the first sending module 81, the second sending module 82, the third sending module 83 and the fourth sending module 84. The flight controller 60, the servo assembly 30, the input speed measurement receiving module 110, the first sending module 81, the second sending module 82, the third sending module 83 and the fourth sending module 84 are grounded. This design can improve the ability of the oil-powered vertical take-off and landing fixed-wing UAV to prevent electromagnetic interference.

[0030] See also Figure 2 and Figure 3As shown, in some embodiments, for example, the servo assembly 30 includes a throttle servo 31, a left tail servo 32, a right tail servo 33, a left aileron servo 34 and a right aileron servo 35, and the throttle servo 31, the left tail servo 32, the right tail servo 33, the left aileron servo 34 and the right aileron servo 35 are electrically connected to the flight controller 60 respectively, and the third power supply is used to supply power to the throttle servo 31, the left tail servo 32, the right tail servo 33, the left aileron servo 34, the right aileron servo 35, and the input speed receiving module. Block 110, the first sending module 81, the second sending module 82, the third sending module 83 and the fourth sending module 84 are powered, and the flight controller 60, the throttle servo 31, the left tail servo 32, the right tail servo 33, the left aileron servo 34, the right aileron servo 35, the input speed measurement receiving module 110, the first sending module 81, the second sending module 82, the third sending module 83 and the fourth sending module 84 are grounded. This design can improve the ability of the oil-powered vertical take-off and landing fixed-wing UAV to prevent electromagnetic interference.

[0031] See also Figure 4 As shown, in certain embodiments, illustratively, the structures of the first transmitting module 81, the second transmitting module 82, the third transmitting module 83, and the fourth transmitting module 84 are the same as those of the input speed measurement transmitting module 90. The first transmitting module 81 is used as an example for description below. The first transmitting module 81 includes a transistor Q1, a first optical coupler chip OC1, a first resistor R1, a second resistor R2, a third resistor R3, a first capacitor C1, and a second capacitor C2. The transmitting end is connected to the base of the transistor Q1 and the grounded first capacitor C1 through the first resistor R1, the collector of the transistor Q1 is connected to the grounded second resistor R2, the emitter of the transistor Q1 is connected to the TX- pin of the first optical coupler chip OC1 and one end of the third resistor R3, the TX+ pin of the first optical coupler chip OC1, the other end of the third resistor R3, and the positive electrode of the second capacitor C2 are respectively connected to the third power supply, and the negative electrode of the second capacitor C2 is grounded.

[0032] It can be understood that the transmitting end connected to the first transmitting module 81 , the second transmitting module 82 , the third transmitting module 83 and the fourth transmitting module 84 refers to the flight controller 60 , and the transmitting end connected to the input speed measurement transmitting module 90 refers to the igniter 50 .

[0033] It can be understood that the TX+ pin of the first optocoupler chip OC1, the other end of the third resistor R3, and the positive electrode of the second capacitor C2 of the first transmitting module 81, the second transmitting module 82, the third transmitting module 83, and the fourth transmitting module 84 are respectively connected to a third power supply, that is, a 5V power supply. The TX+ pin of the first optocoupler chip OC1, the other end of the third resistor R3, and the positive electrode of the second capacitor C2 of the input speed measurement transmitting module 90 are respectively connected to the second power supply module 12, that is, a 7.2V power supply.

[0034] The operating principle is as follows: The flight control system outputs a PWM square wave, controlling the electronic speed controller assembly 70 by adjusting the duty cycle, and receives pulses from the igniter 50 to measure the speed of the oil-powered engine 40. The flight control system outputs a control signal to the first transmitting module 81, which converts the control signal into an optical signal and transmits it via optical fiber to the first receiving module 101. The first receiving module 101 then converts the optical signal into an electrical signal and transmits it to the left front ESC 71, which controls the movement of the left front rotor 21 according to the command.

[0035] Specifically, the square wave electrical signal output by the flight control enters the transmitting end. When the input is high level, the transistor Q1 is not turned on, the first optocoupler chip OC1 is not turned on, and no optical signal is output; when the input is low level, the transistor Q1 is turned on, the first optocoupler chip OC1 is turned on, and an optical signal is output.

[0036] See also Figure 5 As shown, in certain embodiments, illustratively, the first receiving module 101, the second receiving module 102, the third receiving module 103, and the fourth receiving module 104 have the same structure as the input speed measurement receiving module 110. The first receiving module 101 is used as an example for description below. The first receiving module 101 includes: a second optocoupler chip OC2, a fourth resistor R4, an inductor L1, a third capacitor C3, and a fourth capacitor C4. The receiving end is connected to the Data pin of the second optocoupler chip OC2 and one end of the fourth resistor R4, respectively. The GND pin of the second optocoupler chip OC2 is grounded. The VCC pin of the second optocoupler chip OC2 is connected to one end of the inductor L1, one end of the third capacitor C3, and one end of the fourth capacitor C4, respectively. The other end of the fourth resistor R4 and the other end of the inductor L1 are respectively connected to the left front electronic controller 71. One end of the fourth capacitor C4 is also connected to one end of the fourth resistor R4. The other end of the third capacitor C3 and the other end of the fourth capacitor C4 are grounded.

[0037] As can be understood, the other end of the fourth resistor R4 of the first receiving module 101 and the other end of the inductor L1 are respectively connected to the left front electric regulator 71, and the power output of the left front electric regulator 71 is 5V. Similarly, the other end of the fourth resistor R4 of the second receiving module 102 and the other end of the inductor L1 are respectively connected to the left rear electric regulator 72, the other end of the fourth resistor R4 of the third receiving module 103 and the other end of the inductor L1 are respectively connected to the right front electric regulator 73, and the other end of the fourth resistor R4 of the fourth receiving module 104 and the other end of the inductor L1 are respectively connected to the right rear electric regulator 74.

[0038] It can be understood that the receiving end connected to the first receiving module 101 is the left front electric regulator 71, the receiving end connected to the second receiving module 102 is the left rear electric regulator 72, the receiving end connected to the third receiving module 103 is the right front electric regulator 73, the receiving end connected to the fourth receiving module 104 is the right rear electric regulator 74, and the receiving end connected to the input speed measurement receiving module 110 is the flight controller 60.

[0039] The transmitting end connected to the first transmitting module 81 , the second transmitting module 82 , the third transmitting module 83 and the fourth transmitting module 84 is the flight controller 60 , and the transmitting end connected to the input speed measurement transmitting module 90 is the igniter 50 .

[0040] The working principle is as follows: when the second optocoupler chip OC2 does not receive an optical signal, the second optocoupler chip OC2 is off and the receiving end outputs a high level. When the second optocoupler chip OC2 receives an optical signal, the second optocoupler chip OC2 is on and the receiving end outputs a low level.

[0041] The above description is only a preferred embodiment of the present invention and does not limit the patent scope of the present invention. All equivalent structural transformations made by using the contents of the present invention description and drawings under the inventive concept of the present invention, or direct / indirect application in other related technical fields are included in the patent protection scope of the present invention.

Claims

1. An electromagnetic interference-proof oil-powered vertical take-off and landing fixed-wing UAV, characterized in that: The invention comprises an optical transmission system, a fuselage, and a rotor assembly, a steering gear assembly, an oil-driven engine, an igniter, a flight controller, an electronic speed controller assembly, and a power supply assembly. The optical transmission system comprises a control sending assembly, an input speed measurement sending module, a control receiving assembly that transmits optical signals to the control sending assembly, and an input speed measurement receiving module that transmits optical signals to the input speed measurement sending module. The steering gear assembly, the control sending assembly, and the input speed measurement receiving module are respectively connected to the flight controller. The control sending assembly and the rotor assembly are respectively connected to the electronic speed controller assembly. The input speed measurement sending module and the oil-driven engine are respectively connected to the igniter. The power supply assembly comprises a first power supply module, a second power supply module, and a DC power converter. The first power supply module is used to generate a first power supply to power the electronic speed controller component, and the electronic speed controller component powers the control receiving component and the rotor component. The first power supply module is connected to the DC power converter and generates a second power supply and a third power supply with input and output ground isolation through the DC power converter. The second power supply is used to power the flight controller, and the third power supply is used to power the servo component, the input speed measurement receiving module and the control sending component. The flight controller, the servo component, the input speed measurement receiving module and the control sending component share a common ground. The second power supply module is used to power the input speed measurement sending module and the igniter. The input speed measurement sending module and the igniter share a common ground, and the igniter powers the oil-powered engine.

2. The electromagnetic interference-proof oil-powered vertical take-off and landing fixed-wing UAV according to claim 1, characterized in that: The voltage value of the first power supply module is 45.6V, the voltage value of the first power supply is 45.6V, the voltage value of the second power supply is 12V, and the voltage value of the third power supply is 5V.

3. The electromagnetic interference-proof oil-powered vertical take-off and landing fixed-wing UAV according to claim 1, characterized in that: The voltage value of the second power supply module is 7.2V.

4. The electromagnetic interference-proof oil-powered vertical take-off and landing fixed-wing UAV according to claim 1, characterized in that: The rotor assembly includes a left front rotor, a left rear rotor, a right front rotor and a right rear rotor, the control sending assembly includes a first sending module, a second sending module, a third sending module and a fourth sending module, the first sending module, the second sending module, the third sending module and the fourth sending module are electrically connected to the flight controller respectively, the control receiving assembly includes a first receiving module connected to the first sending module via an optical fiber, a second receiving module connected to the second sending module via an optical fiber, a third receiving module connected to the third sending module via an optical fiber, and a fourth receiving module connected to the fourth sending module via an optical fiber, the electronic speed controller assembly includes a left front electric regulator, a left rear electric regulator, a right front electric regulator and a right rear electric regulator, the first receiving module and the left front rotor are electrically connected to the left front electric regulator respectively, the second receiving module and the left rear rotor are electrically connected to the left rear electric regulator respectively, the third receiving module and the fourth receiving module are electrically connected to the fourth sending module via an optical fiber The receiving module and the right front rotor are electrically connected to the right front electric regulator respectively, and the fourth receiving module and the right rear rotor are electrically connected to the right rear electric regulator respectively; the first power supply supplies power to the left front electric regulator, the left rear electric regulator, the right front electric regulator and the right rear electric regulator, and the left front electric regulator, the left rear electric regulator, the right front electric regulator and the right rear electric regulator share a common ground; the left front electric regulator supplies power to the left front rotor, the left rear electric regulator supplies power to the left rear rotor, the right front electric regulator supplies power to the right front rotor, and the right rear electric regulator supplies power to the right rear rotor; the third power supply is used to supply power to the servo assembly, the input speed measurement receiving module, the first sending module, the second sending module, the third sending module and the fourth sending module, and the flight controller, the servo assembly, the input speed measurement receiving module, the first sending module, the second sending module, the third sending module and the fourth sending module share a common ground.

5. The electromagnetic interference-proof oil-powered vertical take-off and landing fixed-wing UAV according to claim 4, characterized in that: The servo assembly includes a throttle servo, a left tail servo, a right tail servo, a left aileron servo and a right aileron servo. The throttle servo, the left tail servo, the right tail servo, the left aileron servo and the right aileron servo are electrically connected to the flight controller respectively. The third power supply is used to power the throttle servo, the left tail servo, the right tail servo, the left aileron servo, the right aileron servo, the input speed measurement receiving module, the first sending module, the second sending module, the third sending module and the fourth sending module. The flight controller, the throttle servo, the left tail servo, the right tail servo, the left aileron servo, the right aileron servo, the input speed measurement receiving module, the first sending module, the second sending module, the third sending module and the fourth sending module are grounded.

6. The electromagnetic interference-proof oil-powered vertical take-off and landing fixed-wing UAV according to claim 4, characterized in that: The structures of the first sending module, the second sending module, the third sending module, and the fourth sending module are the same as those of the input speed measurement sending module. The first sending module includes a transistor Q1, a first optocoupler chip OC1, a first resistor R1, a second resistor R2, a third resistor R3, a first capacitor C1, and a second capacitor C2. The output end of the flight controller is respectively connected to the base of the transistor Q1 and the grounded first capacitor C1 through the first resistor R1, the collector of the transistor Q1 is connected to the grounded second resistor R2, the emitter of the transistor Q1 is connected to the TX- pin of the first optocoupler chip OC1 and one end of the third resistor R3, the TX+ pin of the first optocoupler chip OC1, the other end of the third resistor R3, and the positive electrode of the second capacitor C2 are respectively connected to the third power supply, and the negative electrode of the second capacitor C2 is grounded.

7. The electromagnetic interference-proof oil-powered vertical take-off and landing fixed-wing UAV according to claim 4, characterized in that: The structures of the first receiving module, the second receiving module, the third receiving module, the fourth receiving module and the input speed measurement receiving module are the same. The first receiving module includes a second optocoupler chip OC2, a fourth resistor R4, an inductor L1, a third capacitor C3 and a fourth capacitor C4. The input end of the left front electronic regulator is respectively connected to the Data pin of the second optocoupler chip OC2 and one end of the fourth resistor R4, the GND pin of the second optocoupler chip OC2 is grounded, the VCC pin of the second optocoupler chip OC2 is respectively connected to one end of the inductor L1, one end of the third capacitor C3 and one end of the fourth capacitor C4, the other end of the fourth resistor R4 and the other end of the inductor L1 are respectively connected to the left front electronic regulator, and one end of the fourth capacitor C4 is also connected to one end of the fourth resistor R4; the other end of the third capacitor C3 and the other end of the fourth capacitor C4 are respectively grounded.

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