Aircraft linear driving device

Abstract

The invention discloses an aircraft linear driving device which comprises a shell, a motor and a lead screw are arranged in the shell, the output end of the motor is connected with the lead screw through a connecting piece, a lead screw nut is installed on the outer side of the lead screw, a sleeve is installed on the lead screw nut, a top head is detachably installed at one end of the sleeve, and the top head is detachably installed on the other end of the sleeve. A plug matched with the sleeve is installed at one end of the shell. With the structural characteristic of vertical extension and retraction of the push rod, the device has the characteristics of attractive appearance, small size, low transmission resistance, low noise, convenience in installation and the like; the aircraft has the precise control capability, high-precision power output can be provided, precise control over all parts of the aircraft, including a control surface, a flap, an undercarriage and the like, is achieved, and therefore the maneuverability and the flight performance of the aircraft are improved.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft driving, in particular to an aircraft linear driving device. Background Art

[0002] Aircraft linear actuators are usually used to control the angle and position of aircraft rotors. This device plays a vital role in aircraft flight. It controls the aircraft's movements such as lifting, moving forward, backward, and sideways by changing the angle and position of the rotors, thereby achieving the stability and maneuverability of the aircraft.

[0003] As an important part of the aircraft control system, the aircraft linear drive device has some shortcomings in the existing technology. First, in terms of weight and volume, traditional aircraft linear drives are usually bulky and occupy a large space, which increases the overall weight of the aircraft, thus affecting its flight performance and payload. Secondly, in terms of energy efficiency and energy consumption, some linear drives have problems with low energy efficiency and high energy consumption, which will limit the aircraft's endurance and flight efficiency. In terms of maintenance and reliability, since the components of the linear drive device are prone to wear and failure under high-frequency use, frequent maintenance and overhaul are required, which increases operating costs and maintenance difficulties. In addition, the manufacturing cost of some linear drives is high and the manufacturing process is complex, which has a certain impact on the overall cost and manufacturing cycle of the aircraft.

[0004] In summary, the aircraft linear drive device in the existing technology has many shortcomings in terms of weight, energy efficiency, reliability, accuracy, anti-interference ability, cost, vibration and noise, and further improvement and optimization are needed in these aspects. Summary of the invention

[0005] The object of the present invention is to provide an aircraft linear drive device to solve the problems in the prior art.

[0006] To achieve the above-mentioned purpose, the present invention provides the following technical solution: a linear drive device for an aircraft, comprising a shell, a motor and a screw rod are arranged in the shell, the output end of the motor is connected to the screw rod through a connecting piece, a screw nut is installed on the outer side of the screw rod, a sleeve is installed on the screw nut, a top head is detachably installed on one end of the sleeve, and a plug matching the sleeve is installed on one end of the shell.

[0007] Preferably, it includes a shell, characterized in that: a motor and a screw are arranged in the shell, the output end of the motor is connected to the screw through a connecting piece, a screw nut is installed on the outer side of the screw, a sleeve is installed on the screw nut, a top head is detachably installed on one end of the sleeve, and a plug matching the sleeve is installed on one end of the shell.

[0008] Preferably, an end cover is installed at one end of the shell away from the plug, and the end cover and the top head are both provided with through holes.

[0009] Preferably, the end cover is connected to the outer shell by a thread, the plug is connected to the outer shell by a thread, and the top head is connected to the plug by a thread.

[0010] Preferably, the plug is provided with a spacer at one end of the screw nut.

[0011] Preferably, the sleeve and the screw nut are threadedly connected.

[0012] Compared with the prior art, the present invention has the following beneficial effects:

[0013] 1. The vertical extension and retraction of the push rod is its structural feature, which has the characteristics of beautiful appearance, small size, small transmission resistance, low noise and easy installation.

[0014] 2. It has precise control capabilities and can provide high-precision power output to achieve precise control of various aircraft components, including rudders, flaps, landing gear, etc., thereby improving the aircraft's maneuverability and flight performance.

[0015] 3. The aircraft linear drive device adopts an advanced electric system with high energy efficiency, which can achieve fast and accurate motion response, improve the operating efficiency of the aircraft, and reduce energy consumption.

[0016] 4. Use lightweight materials (aluminum alloy) and structural design to achieve lightweight and compactness, reduce the overall weight of the aircraft, and help improve flight performance and payload. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The accompanying drawings are used to provide a further understanding of the present invention and constitute a part of the specification. Together with the embodiments of the present invention, they are used to explain the present invention and do not constitute a limitation of the present invention. In the accompanying drawings:

[0018] Figure 1 It is a schematic diagram of the structure of the present invention;

[0019] Figure 2 is a cross-sectional view of the present invention;

[0020] Figure 3 is an exploded view of the present invention;

[0021] Figure 4 It is a schematic diagram of the structure of the present invention when the housing and the end cover are removed;

[0022] Figure 5 The present invention Figure 4 Schematic diagram of the structure when the sleeve is removed.

[0023] In the figure: 1. outer shell; 2. end cover; 3. top head; 4. motor; 5. top cover; 6. connecting piece; 7. screw nut; 8. screw; 9. sleeve; 10. spacer; 11. plug. DETAILED DESCRIPTION

[0024] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention. Therefore, the following detailed description of the embodiments of the present invention provided in the drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention.

[0025] See also Figure 1-5 In the embodiment of the present invention, a linear drive device for an aircraft comprises a housing 1 and a top cover 5, wherein the top cover 5 is located outside a connecting member 6, a motor 4 and a screw 8 are arranged in the housing 1, the output end of the motor 4 is connected to the screw 8 through the connecting member 6, a screw nut 7 is installed on the outside of the screw 8, a sleeve 9 is installed on the screw nut 7, a top head 3 is detachably installed at one end of the sleeve 9, and a plug 11 matching the sleeve 9 is installed at one end of the housing 1; the vertical extension of the push rod is the structural feature, and the device has the characteristics of beautiful appearance, small size, small transmission resistance, low noise, and convenient installation. First, it has the ability of precise control, can provide high-precision power output, and realize precise control of various components of the aircraft, including rudders, flaps, landing gear, etc., so as to improve the maneuverability and flight performance of the aircraft. Secondly, the linear drive device for the aircraft adopts an advanced electric system, has high energy efficiency, can achieve fast and precise action response, improve the operating efficiency of the aircraft, and reduce energy consumption at the same time. In addition, it uses lightweight materials (aluminum alloy) and structural design to achieve lightweight and compactness, reducing the overall weight of the aircraft, helping to improve flight performance and payload. The aircraft linear drive device has been rigorously designed and tested and has high reliability and stability.

[0026] like Figure 1-5 An end cover 2 is installed at the end of the shell 1 away from the plug 11, and the end cover 2 and the top head 3 are both provided with through holes; the end cover 2 and the shell 1 are connected by threads, the plug 11 and the shell 1 are connected by threads, and the top head 3 and the plug 11 are connected by threads; a spacer 10 is installed at one end of the plug 11 at the screw nut 7; the sleeve 9 and the screw nut 7 are connected by threads.

[0027] The working principle of the present invention is: the motor 4 drives the screw 8 to rotate, thereby driving the screw nut 7, the sleeve 9 and the top head 3 to move.

[0028] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or replace some of the technical features therein by equivalents. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. An aircraft linear drive device, comprising a housing (1), characterized in that: A motor (4) and a screw (8) are arranged in the housing (1); the output end of the motor (4) is connected to the screw (8) via a connecting piece (6); a screw nut (7) is installed on the outer side of the screw (8); a sleeve (9) is installed on the screw nut (7); a top head (3) is detachably installed on one end of the sleeve (9); and a plug (11) matching the sleeve (9) is installed on one end of the housing (1).

2. The aircraft linear drive device according to claim 1, characterized in that: It also comprises a top cover (5), wherein the top cover (5) is located outside the connecting member (6).

3. The aircraft linear drive device according to claim 1, characterized in that: An end cover (2) is installed at one end of the housing (1) away from the plug (11), and both the end cover (2) and the top head (3) are provided with through holes.

4. The aircraft linear drive device according to claim 3, characterized in that: The end cover (2) is connected to the outer shell (1) via a threaded connection, the plug (11) is connected to the outer shell (1) via a threaded connection, and the top head (3) is connected to the plug (11) via a threaded connection.

5. The aircraft linear drive device according to claim 1, characterized in that: The plug (11) is located at one end of the screw nut (7) and is provided with a cushion block (10).

6. The aircraft linear drive device according to claim 1, characterized in that: The sleeve (9) and the screw nut (7) are connected by threads.

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