Unmanned aircraft cruise hybrid power system and control method thereof

Abstract

The invention discloses an unmanned aircraft cruise hybrid power system and a control method thereof.The unmanned aircraft cruise hybrid power system comprises an engine, a motor and a propeller, the motor is arranged between the engine and the propeller, and an output shaft of the engine is in transmission connection with a rotating shaft of the propeller through a first one-way bearing; the outer circle face of the output shaft is in gapless contact connection with an inner side roller pin of the first one-way bearing, and the outer side face of a steel ring of the first one-way bearing is in interference fit connection with the inner circle face of the rotating shaft. A rotor of the motor is in transmission connection with the rotating shaft through a second one-way bearing, the inner circle face of the rotor is in interference fit connection with the outer side face of a steel ring of the second one-way bearing, and an inner side roller pin of the second one-way bearing is in gapless contact connection with the outer circle face of the rotating shaft. By arranging a double-clutch structure composed of the one-way bearing and the propeller shaft, two powers are output to one propeller, the limited weight distribution share of the aircraft can be utilized to the maximum degree, and the excellent performance of high energy-weight ratio and high power-weight ratio is achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicle power systems, and in particular to an unmanned aerial vehicle cruise hybrid power system and a control method thereof. Background Art

[0002] The existing UAV cruise power systems are divided into two types: fuel engines and brushless motors. Fuel engines come in a variety of types and models, and work in turbojet and piston modes. Most of the fuel is non-renewable petroleum products. The engine converts the thermal energy of the fuel into useful mechanical energy to propel the aircraft to fly. It is now widely used; and brushless motors, as a new type of power system, have a tendency to replace engine power. The motor technology and electronic speed regulator technology of brushless motors are already very mature. In addition to being used in aircraft power systems, they are also widely used in many electromechanical application fields.

[0003] However, the cruise power systems currently used in drone systems around the world are equipped with two types: fuel engines and brushless motors. Both are used separately and have their own advantages and disadvantages. The engines have sufficient endurance, but maintenance is cumbersome and inconvenient to use. Large-displacement engines have high power and high fuel consumption, while small-displacement engines have relatively low fuel consumption but are seriously lacking in power. Although electric motors have inherent power advantages, their endurance is limited due to the capacity limitations of energy storage batteries. Summary of the invention

[0004] The purpose of the present invention is to provide a hybrid power system for cruise of unmanned aerial vehicle and a control method thereof, so as to solve the above-mentioned problems existing in the prior art.

[0005] In order to solve the above technical problems, the present invention adopts the following technical solutions:

[0006] A hybrid cruise system for an unmanned aerial vehicle of the present invention comprises an engine, an electric motor and a propeller, wherein the electric motor is arranged between the engine and the propeller, the output shaft of the engine is connected to the rotating shaft of the propeller through a first one-way bearing, the outer cylindrical surface of the output shaft is connected to the inner needle roller of the first one-way bearing in gapless contact, the outer side surface of the steel ring of the first one-way bearing is connected to the inner cylindrical surface of the rotating shaft by interference fit, and the rotational motion of the output shaft is transmitted to the rotating shaft through the inherent one-way transmission effect of the first one-way bearing to drive the propeller to rotate; the rotor of the electric motor is connected to the rotating shaft through a second one-way bearing, the inner cylindrical surface of the rotor is connected to the outer side surface of the steel ring of the second one-way bearing by interference fit, the inner needle roller of the second one-way bearing is connected to the outer cylindrical surface of the rotating shaft in gapless contact, and the rotational motion of the rotor is transmitted to the rotating shaft through the inherent one-way transmission effect of the second one-way bearing to drive the propeller to rotate.

[0007] Preferably, when the engine stops running or the rotation speed of the output shaft is lower than the rotation speed of the propeller during running, the output shaft is disengaged from the transmission to the rotating shaft through the inherent one-way disengagement transmission action of the first one-way bearing, and the propeller is free to rotate in one direction without being constrained by the engine.

[0008] Preferably, when the motor stops running or the rotation speed of the rotor is lower than the rotation speed of the propeller during running, the rotor is disengaged from the transmission to the rotating shaft through the inherent one-way disengagement transmission action of the second one-way bearing, and the propeller is free to rotate in one direction without being constrained by the motor.

[0009] Preferably, when both the engine and the motor stop running, through the inherent one-way disengagement transmission effect of the first one-way bearing and the second one-way bearing, the propeller is not constrained by the engine and the motor and can rotate freely in one direction, so that the drone has the effect of the propeller rotating to reduce the gliding flight resistance.

[0010] The present invention also provides a control method for an unmanned aircraft cruise hybrid power system, which is applied to the unmanned aircraft cruise hybrid power system. The control method comprises:

[0011] The hybrid system runs the engine alone, so that when the drone is flying normally, the engine runs alone to drive the propeller to rotate, allowing the drone to fly without causing kinetic energy loss due to the additional resistance caused by the motor stopping running;

[0012] The hybrid system operates the electric motor alone, so that when the drone is flying normally, the electric motor alone drives the propeller to rotate, allowing the drone to fly without causing kinetic energy loss due to the additional resistance caused by the engine stopping.

[0013] The hybrid power system works in dual-engine mode, so when the drone is flying at high power, the engine and electric motor run simultaneously to drive the propeller to rotate, allowing the drone to fly.

[0014] Compared with the prior art, the beneficial technical effects of the present invention are:

[0015] 1. The hybrid cruise system of the unmanned aerial vehicle of the present invention cleverly creates a structure in which two powers are output to one propeller by setting a dual clutch structure consisting of a one-way bearing and a propeller shaft, thus solving the problem of power connection;

[0016] 2. The hybrid power system for unmanned aircraft cruise of the present invention designs a hybrid power system of a combination of an electric motor and an engine, utilizing the respective advantages of the engine and the electric motor, complementing each other's deficiencies, creating a new power system, maximizing the use of the limited weight distribution share of the aircraft, having excellent performance of high energy-to-weight ratio and high power-to-weight ratio, and can be widely used in aircraft power systems;

[0017] 3. Compared with the existing fuel engine power system and energy storage battery motor power system, the unmanned aircraft cruise hybrid power system of the present invention has the following advantages:

[0018] (1) For power systems of the same weight, hybrid power systems have higher power output than fuel engine power systems;

[0019] (2) For power systems of the same weight, the hybrid power system has a longer continuous power output time than the energy storage battery electric motor power system;

[0020] (3) The hybrid system has two power systems that can work independently or simultaneously, and has double the safety performance compared to the existing fuel engine power system and energy storage battery electric motor power system;

[0021] (4) For power systems of the same weight, the hybrid power system has an electric motor, which allows the engine to work in the best state in real time. When the power is at maximum power output, the fuel consumption is more economical than that of the fuel engine power system;

[0022] (5) Because the hybrid system transfers the excess cruising kinetic energy consumption to the battery to store electrical energy, the hybrid system saves more battery volume and weight than the battery-motor power system. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. 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 these drawings without paying creative work.

[0024] Figure 1 This is a schematic diagram of the overall structure of the unmanned aerial vehicle cruise hybrid power system according to Embodiment 1 of the present invention;

[0025] Figure 2 It is a cross-sectional structural schematic diagram of an unmanned aerial vehicle cruise hybrid power system according to embodiment 1 of the present invention;

[0026] Figure 3 This is a schematic diagram of the power transmission structure in the unmanned aerial vehicle cruise hybrid power system according to embodiment 1 of the present invention.

[0027] Explanation of the accompanying drawings: 1. Engine; 2. Electric motor; 3. Propeller; 4. Output shaft; 5. Rotor; 6. Rotating shaft; 7. First one-way bearing; 8. Second one-way bearing. DETAILED DESCRIPTION

[0028] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be understood as limiting the present invention.

[0029] In the description of the present invention, it should be understood that the terms "length", "width", "inside", "outside" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, the meaning of "multiple" is two or more, unless otherwise clearly and specifically defined.

[0030] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0031] The technical solutions provided by various embodiments of the present invention are described in detail below in conjunction with the accompanying drawings.

[0032] Example 1

[0033] like Figures 1 to 3 As shown, the unmanned aerial vehicle cruise hybrid system of this embodiment 1 includes an engine 1, an electric motor 2 and a propeller 3, the electric motor 2 is arranged between the engine 1 and the propeller 3, the output shaft 4 of the engine 1 and the rotating shaft 6 of the propeller 3 are connected by a first one-way bearing 7, and the rotor 5 of the electric motor 2 and the rotating shaft 6 of the propeller 3 are connected by a second one-way bearing 8.

[0034] Specifically, the outer cylindrical surface of the output shaft 4 of the engine 1 is connected with the inner needle roller of the first one-way bearing 7 in gapless contact, and the outer side surface of the steel ring of the first one-way bearing 7 is connected with the inner cylindrical surface of the rotating shaft 6 of the propeller 3 by interference fit. Through the inherent one-way transmission action of the first one-way bearing 7, the rotational motion of the output shaft 4 of the engine 1 is transmitted to the rotating shaft 6, driving the propeller 3 to rotate.

[0035] In addition, the inner circumferential surface of the rotor 5 of the motor 2 is interference fit connected with the outer surface of the steel ring of the second one-way bearing 8, and the inner needle roller of the second one-way bearing 8 is contacted with the outer circumferential surface of the rotating shaft 6 without gap. Through the inherent one-way transmission action of the second one-way bearing 8, the rotational motion of the rotor 5 of the motor 2 is transmitted to the rotating shaft 6, driving the propeller 3 to rotate.

[0036] In this embodiment 1, when the engine 1 stops running or the rotation speed of the output shaft 4 is lower than the rotation speed of the propeller 3, the output shaft 4 of the engine 1 is disengaged from the transmission to the rotating shaft 6 through the inherent one-way disengagement transmission action of the first one-way bearing 7, and the propeller 3 is free to rotate in one direction without being constrained by the engine 1.

[0037] In which, when the motor 2 stops running or the rotation speed of the rotor 5 is lower than the rotation speed of the propeller 3, the rotor 5 of the motor 2 is disengaged from the transmission to the rotating shaft 6 through the inherent one-way disengagement transmission effect of the second one-way bearing 8, and the propeller 3 is not constrained by the motor 2 and can rotate freely in one direction.

[0038] In addition, when both the engine 1 and the motor 2 stop running, the propeller 3 is free to rotate in one direction without being constrained by the engine 1 and the motor 2 through the inherent one-way disengagement transmission effect of the first one-way bearing 7 and the second one-way bearing 8, so that the UAV has the effect of the propeller 3 rotating in a feathering manner to reduce the gliding flight resistance.

[0039] In this embodiment 1, the hybrid power system operates the engine 1 alone to allow the drone to navigate normally, including: the engine 1 operates alone to drive the propeller 3 to rotate, allowing the drone to fly without causing kinetic energy loss due to the additional resistance caused by the motor 2 stopping running.

[0040] In this embodiment 1, the hybrid power system operates the motor 2 alone to allow the drone to navigate normally, including: the motor 2 operates alone to drive the propeller 3 to rotate, allowing the drone to fly without causing kinetic energy loss due to the additional resistance caused by the engine 1 stopping running.

[0041] In the present embodiment 1, the hybrid power system operates with two engines, so that the UAV can navigate with high power, including: the engine 1 and the motor 2 operate simultaneously to drive the propeller 3 to rotate, so that the UAV can fly.

[0042] Example 2

[0043] The control method of the unmanned aircraft cruise hybrid power system of this embodiment 2 is applied to the unmanned aircraft cruise hybrid power system, and the control method includes:

[0044] The hybrid power system operates the engine 1 alone, so that when the UAV is flying normally, the engine 1 operates alone to drive the propeller 3 to rotate, so that the UAV flies without causing kinetic energy loss due to the additional resistance caused by the stop of the motor 2;

[0045] The hybrid power system operates the motor 2 alone, so that when the UAV is flying normally, the motor 2 operates alone to drive the propeller 3 to rotate, so that the UAV flies without causing kinetic energy loss due to the additional resistance caused by the stoppage of the engine 1;

[0046] The hybrid power system operates in dual-engine mode, so that when the UAV is flying at high power, the engine 1 and the motor 2 operate simultaneously to drive the propeller 3 to rotate, allowing the UAV to fly.

[0047] The unmanned aerial vehicle cruise hybrid power system and control method of the present invention cleverly creates a structure in which two power outputs are output to one propeller by setting a dual-clutch structure composed of a one-way bearing and a propeller shaft, thereby solving the problem of power connection; at the same time, by designing a hybrid power system combining an electric motor and an engine, the respective advantages of the engine and the electric motor are utilized to complement each other's deficiencies, thereby creating a new power system that maximizes the utilization of the limited weight distribution share of the aircraft, has excellent performance of high energy-to-weight ratio and high power-to-weight ratio, and can be widely used in aircraft power systems.

[0048] The embodiments described above are only descriptions of the preferred modes of the present invention, and are not intended to limit the scope of the present invention. Without departing from the design spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by ordinary technicians in this field should all fall within the protection scope determined by the claims of the present invention.

Claims

1. A hybrid power system for unmanned aerial vehicle cruising, characterized in that: The invention comprises an engine (1), an electric motor (2) and a propeller (3), wherein the electric motor (2) is arranged between the engine (1) and the propeller (3), and the output shaft (4) of the engine (1) and the rotating shaft (6) of the propeller (3) are connected in transmission via a first one-way bearing (7), the outer cylindrical surface of the output shaft (4) is connected in contact with the inner needle roller of the first one-way bearing (7) without clearance, the outer side surface of the steel ring of the first one-way bearing (7) is connected in interference fit with the inner cylindrical surface of the rotating shaft (6), and the output shaft (4) is connected in contact with the inner needle roller of the first one-way bearing (7) through the inherent one-way transmission effect of the first one-way bearing (7). The rotational motion of the rotating shaft (4) is transmitted to the rotating shaft (6) to drive the propeller (3) to rotate; the rotor (5) of the motor (2) and the rotating shaft (6) are connected by a second one-way bearing (8); the inner circumferential surface of the rotor (5) is connected by interference fit with the outer circumferential surface of the steel ring of the second one-way bearing (8); the inner needle roller of the second one-way bearing (8) is connected by gapless contact with the outer circumferential surface of the rotating shaft (6); through the inherent one-way transmission effect of the second one-way bearing (8), the rotational motion of the rotor (5) is transmitted to the rotating shaft (6) to drive the propeller (3) to rotate.

2. The unmanned aerial vehicle cruise hybrid power system according to claim 1, characterized in that: When the engine (1) stops running or the rotation speed of the output shaft (4) is lower than the rotation speed of the propeller (3) during running, the output shaft (4) is disengaged from the transmission to the rotating shaft (6) through the inherent one-way disengagement transmission function of the first one-way bearing (7), and the propeller (3) is free to rotate in one direction without being constrained by the engine (1).

3. The unmanned aerial vehicle cruise hybrid power system according to claim 1, characterized in that: When the motor (2) stops running or the rotation speed of the rotor (5) is lower than the rotation speed of the propeller (3) during running, the rotor (5) is disengaged from the transmission to the rotating shaft (6) through the inherent one-way disengagement transmission function of the second one-way bearing (8), and the propeller (3) is free to rotate in one direction without being constrained by the motor (2).

4. The unmanned aircraft cruise hybrid power system according to claim 1, characterized in that: When the engine (1) and the electric motor (2) both stop running, the propeller (3) is free to rotate in one direction without being constrained by the engine (1) and the electric motor (2) due to the inherent one-way disengagement transmission effect of the first one-way bearing (7) and the second one-way bearing (8), so that the drone has the effect of the propeller (3) rotating in a feathering manner to reduce the gliding flight resistance.

5. A control method for a cruise hybrid power system of an unmanned aircraft, characterized in that: Applied to the unmanned aircraft cruise hybrid power system according to any one of claims 1 to 4, the control method comprises: The hybrid power system operates the engine (1) alone, so that when the UAV is flying normally, the engine (1) operates alone to drive the propeller (3) to rotate, so that the UAV flies without causing kinetic energy loss due to the additional resistance caused by the stoppage of the motor (2); The hybrid power system operates the electric motor (2) alone, so that when the UAV is flying normally, the electric motor (2) operates alone to drive the propeller (3) to rotate, so that the UAV flies without causing kinetic energy loss due to the additional resistance caused by the engine (1) stopping running; The hybrid power system operates in dual-engine mode, so that when the UAV is flying at high power, the engine (1) and the electric motor (2) operate simultaneously to drive the propeller (3) to rotate, so that the UAV can fly.

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