阅读说明：本技术 一种小型飞行器的变距螺旋桨和变距螺旋桨系统 (Variable pitch propeller and variable pitch propeller system of small aircraft ) 是由 王春利 赵政衡 周俊伟 卢杰 戴佳 万志明 任志文 赵胜海 张鹏 杨佳壁 陈尊敬 于 2019-12-05 设计创作，主要内容包括：本发明实施例公开了一种小型飞行器的变距螺旋桨和变距螺旋桨系统,包括：变距螺旋桨、伺服电机、固定杆,以及数量相同的变距杆和连接杆；述变距螺旋桨和伺服电机安装于飞行器发动机轴上,固定杆固定设置于所述伺服电机上,变距杆固定设置于变距螺旋桨的叶片根部,连接杆的一端连接在固定杆的端头上,另一端连接在变距杆的端头上；伺服电机,被配置为沿发动机轴的轴向进行移动时,带动固定杆、连接杆和变距杆移动,使得变距螺旋桨的叶片在所述变距杆的带动下进行转动。本发明实施例解决了当前配装小型高空长航时无人飞行器活塞发动机的定距螺旋桨飞行包线较窄和飞行效率较低的问题,同时改善了目前没有适用于小型飞行器的变距螺旋桨的现状。(The embodiment of the invention discloses a variable pitch propeller and a variable pitch propeller system of a small aircraft, which comprise: the variable pitch propeller comprises a variable pitch propeller, a servo motor, a fixed rod, and variable pitch rods and connecting rods which are the same in number; the variable pitch propeller and the servo motor are arranged on an engine shaft of the aircraft, the fixed rod is fixedly arranged on the servo motor, the variable pitch rod is fixedly arranged at the root part of a blade of the variable pitch propeller, one end of the connecting rod is connected to the end head of the fixed rod, and the other end of the connecting rod is connected to the end head of the variable pitch rod; and the servo motor is configured to drive the fixing rod, the connecting rod and the variable pitch rod to move when moving along the axial direction of the engine shaft, so that the blades of the variable pitch propeller rotate under the driving of the variable pitch rod. The embodiment of the invention solves the problems of narrow flight envelope and low flight efficiency of the fixed-pitch propeller which is provided with the piston engine of the small-sized high-altitude long-endurance unmanned aerial vehicle at present, and simultaneously improves the current situation that no variable-pitch propeller suitable for the small-sized aerial vehicle exists at present.)

1. A pitch propeller for a small aircraft, comprising: the variable pitch propeller comprises a variable pitch propeller, a servo motor, a fixed rod, and variable pitch rods and connecting rods which are the same in number;

the variable pitch propeller and the servo motor are arranged on an engine shaft of the aircraft, the fixed rod is fixedly arranged on the servo motor, the variable pitch rod is fixedly arranged at the root part of a blade of the variable pitch propeller, one end of the connecting rod is connected to the end head of the fixed rod, and the other end of the connecting rod is connected to the end head of the variable pitch rod;

the servo motor is configured to drive the fixing rod, the connecting rod and the variable pitch rod to move when moving along the axial direction of the engine shaft, so that the blades of the variable pitch propeller rotate under the driving of the variable pitch rod.

2. The variable pitch propeller of a small aircraft as claimed in claim 1, wherein the pitch rods, the connecting rods, and the fixing rods have the same number of tips as the blades of the variable pitch propeller and are arranged in one-to-one correspondence with the blades of the variable pitch propeller, respectively.

3. The variable pitch propeller of a small aircraft as claimed in claim 2, wherein the variable pitch propeller is a two-blade propeller, the number of the ends of the fixing rods, the number of the variable pitch rods and the number of the connecting rods are two, and the variable pitch rods are correspondingly arranged on blades of the two-blade propeller.

4. The variable pitch propeller of a small aircraft as claimed in claim 3, wherein the fixing rod comprises two fixing rods disposed on the servo motor, and the end of each fixing rod is connected with its corresponding connecting rod; alternatively, the first and second electrodes may be,

the fixed rod penetrates through the servo motor and the engine shaft, and two ends of the fixed rod are respectively connected with the corresponding connecting rods.

5. The variable pitch propeller of a small aircraft as claimed in claim 4, wherein the end of the fixing rod is a ball joint, and the end of the connecting rod connected with the fixing rod is a joint matched with the ball joint.

6. The variable pitch propeller of a small aircraft as claimed in claim 4, wherein the end of the variable pitch rod is a ball joint, and the end of the connecting rod connected with the variable pitch rod is a joint matched with the ball joint.

7. A pitch propeller system for a small aircraft, comprising: a pitch propeller for a small aircraft according to any one of claims 1 to 6, and a control subsystem and an electrical subsystem;

the control subsystem is configured to calculate the installation angle and the pitch of the propeller blades suitable for the current flight condition according to the flight height, the flight speed and the engine rotating speed of the aircraft;

the electric subsystem is respectively connected with the control subsystem and the servo motors of the variable pitch propellers and is configured to drive the servo motors to move to corresponding positions according to the installation angle and the pitch calculated by the control subsystem.

8. The pitch propeller system of a small aircraft as recited in claim 7, wherein a displacement sensor is disposed in the servo motor, the displacement sensor being coupled to the control subsystem and configured to transmit the position of the servo motor to the control subsystem.

Technical Field

The present application relates to, but is not limited to, the field of aircraft accessory technology, and more particularly to a pitch propeller and pitch propeller system for small aircraft.

Background

The aviation piston engine is widely applied to small-sized high-altitude long-endurance unmanned aerial vehicles due to the fuel economy, and the propeller is a propeller which is required to be equipped for each piston engine.

However, the simplest and most commonly used fixed pitch propeller has the problem of narrow flight envelope, and the propeller efficiency cannot be guaranteed to be in a high-efficiency area even in the available flight envelope, thereby causing great limitation to the overall performance index of the aircraft, including flight altitude, flight speed, flight time and the like. On the other hand, the pitch-variable propeller applied to the manned aircraft or the medium-large unmanned aircraft is complex in structure, electricity and control, and is not suitable for being applied to the small unmanned aircraft.

Disclosure of Invention

In order to solve the above technical problems, embodiments of the present invention provide a variable pitch propeller and a variable pitch propeller system of a small aircraft, so as to solve the problems of a narrow flight envelope range and low flight efficiency of a fixed pitch propeller on an existing small aircraft, and the current situation that no variable pitch propeller suitable for a small aircraft exists at present.

The embodiment of the invention provides a variable pitch propeller of a small aircraft, which comprises:

the variable pitch propeller comprises a variable pitch propeller, a servo motor, a fixed rod, and variable pitch rods and connecting rods which are the same in number;

the variable pitch propeller and the servo motor are arranged on an engine shaft of the aircraft, the fixed rod is fixedly arranged on the servo motor, the variable pitch rod is fixedly arranged at the root part of a blade of the variable pitch propeller, one end of the connecting rod is connected to the end head of the fixed rod, and the other end of the connecting rod is connected to the end head of the variable pitch rod;

the servo motor is configured to drive the fixing rod, the connecting rod and the variable pitch rod to move when moving along the axial direction of the engine shaft, so that the blades of the variable pitch propeller rotate under the driving of the variable pitch rod.

Optionally, in the pitch propeller of the small aircraft, the pitch rods, the connecting rods, and the fixing rods have the same number of tips as the number of the blades of the pitch propeller, and are respectively arranged in a one-to-one correspondence manner with the blades of the pitch propeller.

Optionally, in the variable pitch propeller of the small aircraft, the variable pitch propeller is a two-blade propeller, the number of the ends of the fixing rods, the number of the variable pitch rods and the number of the connecting rods are two, and the variable pitch rods are arranged on blades of the two-blade propeller in a one-to-one correspondence manner.

Optionally, in the pitch-variable propeller of the small aircraft, the fixing rod includes two fixing rods disposed on the servo motor, and an end of each fixing rod is connected to its corresponding connecting rod; alternatively, the first and second electrodes may be,

the fixed rod penetrates through the servo motor and the engine shaft, and two ends of the fixed rod are respectively connected with the corresponding connecting rods.

Optionally, in the variable pitch propeller of a small aircraft, an end of the fixing rod is a ball joint, and an end of the connecting rod connected to the fixing rod is a joint used in cooperation with the ball joint.

Optionally, in the variable pitch propeller of the small aircraft, an end of the variable pitch rod is a ball joint, and an end of the connecting rod connected to the variable pitch rod is a joint used in cooperation with the ball joint.

The embodiment of the invention also provides a variable pitch propeller system of a small aircraft, which comprises: a pitch propeller of a small aircraft as claimed in any one of the preceding claims, and a control subsystem and an electrical subsystem;

the control subsystem is configured to calculate the installation angle and the pitch of the propeller blades suitable for the current flight condition according to the flight height, the flight speed and the engine rotating speed of the aircraft;

the electric subsystem is respectively connected with the control subsystem and the servo motors of the variable pitch propellers and is configured to drive the servo motors to move to corresponding positions according to the installation angle and the pitch calculated by the control subsystem.

Optionally, in the pitch propeller system of a small aircraft as described above, a displacement sensor is disposed in the servo motor, and the displacement sensor is connected to the control subsystem and configured to transmit a moving position of the servo motor to the control subsystem.

The embodiment of the invention provides a variable pitch propeller and a variable pitch propeller system of a small aircraft, which comprise: the variable pitch propeller comprises a variable pitch propeller, a servo motor, a fixed rod, and variable pitch rods and connecting rods which are the same in number; the variable pitch propeller and the servo motor are arranged on an engine shaft of the aircraft, the fixed rod is fixedly arranged on the servo motor, the variable pitch rod is fixedly arranged at the root part of a blade of the variable pitch propeller, one end of the connecting rod is connected to the end head of the fixed rod, and the other end of the connecting rod is connected to the end head of the variable pitch rod; and the servo motor is configured to drive the fixing rod, the connecting rod and the variable pitch rod to move when moving along the axial direction of the engine shaft, so that the blades of the variable pitch propeller rotate under the driving of the variable pitch rod. The embodiment of the invention provides a novel variable pitch propeller, which solves the problems of narrow flight envelope and low flight efficiency of a fixed pitch propeller which is provided with a piston engine of a small-sized high-altitude long-endurance unmanned aerial vehicle at present, and simultaneously improves the current situation that no variable pitch propeller suitable for a small-sized aerial vehicle exists at present.

Drawings

The accompanying drawings are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the example serve to explain the principles of the invention and not to limit the invention.

FIG. 1 is a schematic structural diagram of a pitch-variable propeller of a small aircraft according to an embodiment of the present invention;

fig. 2 is a schematic structural diagram of a pitch-variable propeller of another small aircraft provided by the embodiment of the invention.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that the embodiments and features of the embodiments in the present application may be arbitrarily combined with each other without conflict.

The technical solution provided by the present invention is explained in detail by several specific examples below. The following specific embodiments of the present invention may be combined, and the same or similar concepts or processes may not be described in detail in some embodiments.

Fig. 1 is a schematic structural diagram of a pitch-variable propeller of a small aircraft according to an embodiment of the present invention. The variable pitch propeller of the small aircraft provided by the embodiment can comprise: the variable pitch propeller 6, the servo motor 2, the fixed rod 3, the variable pitch rods 5 and the connecting rods 4 are the same in number;

the variable pitch propeller 6 and the servo motor 2 are installed on an aircraft engine shaft 1, the fixed rod 3 is fixedly arranged on the servo motor 2, the variable pitch rod 5 is fixedly arranged at the root part of a blade of the variable pitch propeller 6, one end of the connecting rod 4 is connected to the end head of the fixed rod 3, and the other end of the connecting rod is connected to the end head of the variable pitch rod 5;

and the servo motor 2 is configured to drive the fixing rod 3, the connecting rod 4 and the pitch-variable rod 5 to move when moving along the axial direction of the engine shaft 1, so that the blades of the pitch-variable propeller 6 are driven by the pitch-variable rod 5 to rotate.

The pitch-variable rods 5, the connecting rods 4 and the ends of the fixing rods 3 in the embodiment of the invention can be the same as the pitch-variable propeller blades in number, and are respectively arranged in a one-to-one correspondence manner with the pitch-variable propeller blades.

Optionally, fig. 2 is a schematic structural diagram of a pitch-variable propeller of another small aircraft provided in the embodiment of the present invention. As shown in fig. 2, the variable pitch propeller may be a two-blade propeller, the number of the ends of the fixing rods 3, the number of the variable pitch rods 5 and the number of the connecting rods 4 are two, and the variable pitch rods 5 are correspondingly arranged on the blades of the two-blade propeller.

In one implementation manner of the embodiment of the present invention, the fixing rod 3 includes two fixing rods disposed on the servo motor 2, and an end of each fixing rod is connected to its corresponding connecting rod 4.

In another implementation manner of the embodiment of the present invention, the fixing rod 3 passes through the servo motor 2 and the engine shaft 1, and two ends of the fixing rod 3 are respectively connected with the corresponding connecting rods 4.

For the connection mode between the fixing rod 3 and the connecting rod 4, it can be: the end of the fixed rod 3 is a ball head connecting joint, and the end part of the connecting rod 4 connected with the fixed rod 3 is a connecting joint matched with the ball head connecting joint;

the connection between the pitch lever 5 and the connecting rod 4 may be: the end of the variable pitch rod 5 is a ball head connecting joint, and the end part of the connecting rod 4 connected with the variable pitch rod 5 is a connecting joint matched with the ball head connecting joint for use.

The variable pitch propeller of the small aircraft provided by the embodiment of the invention is a novel variable pitch propeller, the servo motor 2 arranged on the rotating shaft 1 of the piston engine is used for acting on the propeller 6, and the installation angle of blades of the propeller 6 is changed through the axial movement of the variable pitch rod 5, so that the pitch of the propeller 6 is changed.

Wherein, install dead lever 3 on servo motor 2, install displacement pole 5 on screw 6, dead lever 3 and displacement pole 5 pass through connecting rod 4 to be connected, and the connected mode between connecting rod 4 and dead lever 3 and the displacement pole 5 is the bulb link.

During the flying process of the aircraft, along with the change of the flying height, the flying speed and the engine rotating speed, the on-board control system calculates the pitch of the proper propeller 6 under the current flying condition according to a preset program, and then the electric system drives the servo motor 2 to move on the engine shaft to execute the propeller pitch changing task.

The variable pitch propeller of the small aircraft provided by the embodiment of the invention is a novel variable pitch propeller which utilizes a servo motor to drive the propeller to change the pitch, so that the propeller can calculate different pitches according to a preset program under the conditions of different flight heights, flight speeds and engine rotating speeds, and the pitch can enable the propeller to exert the optimal efficiency under the current flight condition. The embodiment of the invention can provide reliable guarantee for the small-sized high-altitude long-endurance unmanned aerial vehicle to work in a wide flight envelope and for the long-lasting flight endurance, solves the problems of narrow envelope and low use efficiency of the propeller of the piston engine of the small-sized high-altitude long-endurance unmanned aerial vehicle, and has obvious engineering application value.

The pitch-variable propeller of the small aircraft provided by the embodiment of the invention is described in detail through the specific implementation mode. Referring to fig. 1 and 2, the embodiment of the invention provides a novel variable pitch propeller applied to a small high-altitude long-endurance unmanned aerial vehicle.

As shown in fig. 1 and 2, the variable pitch propeller is mounted on an engine shaft 1, a servo motor 2 is also mounted on the engine shaft 1 and can move back and forth on the engine shaft along an axial direction, a fixing rod 3 is mounted on the servo motor 2, the end of the fixing rod 3 is a ball joint, a variable pitch rod 5 is mounted on a propeller 6, the end of the variable pitch rod 5 is also a ball joint, one end of a connecting rod 4 is connected with the fixing rod 3 through the ball joint, and the other end of the connecting rod 4 is connected with the variable pitch rod 5 through the ball joint.

Based on the pitch-variable propeller of the small aircraft provided by the above embodiment of the present invention, an embodiment of the present invention further provides a pitch-variable propeller system of a small aircraft, which may include: a variable pitch propeller of a small aircraft as in any of the embodiments above, and a control subsystem and an electrical subsystem;

a control subsystem configured to calculate the pitch and the angle of incidence of the propeller blades adapted to the current flight conditions from the altitude, the speed of flight and the engine speed of the aircraft; where refers to the angle from root to tip, 3/4.

The electric subsystem is respectively connected with the control subsystem and the servo motors of the variable pitch propellers and is configured to drive the servo motors to move to corresponding positions according to the installation angle and the pitch calculated by the control subsystem, so that the installation angle and the pitch of the blades are adjusted to be calculated values.

In the pitch-variable propeller system of the small aircraft provided by the embodiment of the invention, the servo motor is provided with the displacement sensor, and the displacement sensor is connected with the control subsystem and is configured to send the moving position of the servo motor to the control subsystem.

Referring to fig. 1 and 2 again, when the propeller 6 operates with the operation of the piston engine, according to the change of flight parameters such as flight height, flight speed and engine speed, the control system on the aircraft calculates the correct propeller blade installation angle and pitch according to a preset program, then the electromechanical system drives the servo motor 2 to move to a preset position, and in the moving process of the servo motor 2, the fixed rod 3, the connecting rod 4 and the variable pitch rod 5 act on the propeller 6, so that the blade installation angle of the propeller is changed to a proper value, namely the pitch of the propeller is changed to a proper value, and the propeller is kept to operate under a high-efficiency condition.

Although the embodiments of the present invention have been described above, the above description is only for the convenience of understanding the present invention, and is not intended to limit the present invention. It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.