Coaxial contra-rotating double-propeller aircraft control device
By using a coaxial counter-rotating twin-propeller aircraft control device, which utilizes a support frame and servo system to control the counter-rotating propellers, the yaw and roll problems caused by a single propeller are solved, thereby improving the system's stability and maneuverability.
Patent Information
- Application Number
- CN202423139474.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-19
- Publication Date
- 2025-10-21
- Estimated Expiration
- 2034-12-19
AI Technical Summary
Traditional single-propeller propulsion systems are prone to yaw and roll in aircraft or ships, requiring additional trim devices that increase system complexity and energy consumption.
It adopts a coaxial counter-rotating twin-propeller structure, which is connected by a support frame, an X-axis bogie and a Y-axis bogie. The reverse rotation of the propeller is controlled by a servo motor and a linkage system to counteract the rotational torque and improve stability and maneuverability.
It effectively counteracts the torque generated by the rotating propeller, improving the system stability and maneuverability of aircraft or ships, simplifying the structure and reducing energy consumption.
Smart Images
Figure CN223457112U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to an aircraft technical field, concretely is a kind of coaxial counter-rotating double propeller aircraft control device. BACKGROUND
[0002] In many fields such as aerospace, unmanned aerial vehicle and ship, the performance and efficiency of power recommendation system are crucial, and the coaxial counter-rotating double propeller structure has been applied due to its unique advantages. The traditional single propeller propulsion method has limitations in certain working conditions. For example, the torque generated by the single propeller will cause the aircraft or ship to deviate or tilt, and an additional trimming device is needed to correct it, which will increase the system complexity and energy loss. The coaxial counter-rotating double propeller structure can effectively offset the torque generated during propeller rotation, improving system stability and maneuverability. SUMMARY
[0003] The utility model aims at providing a kind of coaxial counter-rotating double propeller aircraft control device to solve the problem of the torque generated by the single propeller causing the aircraft or ship to deviate or tilt in the above background technology.
[0004] To achieve the above-mentioned purpose, the utility model provides the following technical scheme:
[0005] A coaxial counter-rotating double propeller aircraft control device includes a support frame, the top of the support frame is hinged to an X-axis bogie through a connecting arm, the inside of the X-axis bogie is hinged to a Y-axis bogie, a coaxial counter-rotating motor is fixedly installed on the Y-axis bogie, and two groups of counter-rotating propellers are respectively installed on the coaxial counter-rotating motor.
[0006] As a further scheme of the utility model: wherein, the X-axis bogie is connected with the connecting arm through a bearing.
[0007] As a further scheme of the utility model: wherein, the Y-axis bogie is connected with the X-axis bogie through a bearing
[0008] As a further scheme of the utility model: wherein, two groups of symmetrical control mechanisms are fixedly installed on the support frame, the control mechanisms are divided into left control mechanism and right control mechanism, the upper end of the left control mechanism is connected with the Y-axis bogie, and the upper end of the right control mechanism is connected with the X-axis bogie.
[0009] As a further scheme of the utility model: wherein, the control mechanism includes a steering gear, the steering gear is connected with a pull rod through a rocker arm, the pull rod and the rocker arm are connected through a ball head, and the other end of the pull rod is connected with the X-axis bogie and the Y-axis bogie through a ball head respectively.
[0010] As a further scheme of the utility model: two said steering engine cooperation movement, form angle control to coaxial counter rotating motor rotation in semicircle range.
[0011] Compared with the prior art, the utility model has the beneficial effects that:
[0012] The steering engine controller arranged at the bottom of the support frame controls the movement of the steering engine and the coaxial counter rotating motor, when the left steering engine rotates counterclockwise, the rocker arm also rotates counterclockwise downward, thereby dragging the pull rod to move downward, and the action of the upper ball head can control the Y-axis bogie to deflect counterclockwise around the Y-axis; at this time, the right steering engine rotates clockwise, the rocker arm rotates clockwise upward, thereby driving the pull rod to move upward, and the action of the ball head can control the X-axis bogie to deflect clockwise around the X-axis. Therefore, the coaxial counter rotating motor also deflects to the left, so that the torque generated when the propeller rotates is offset during the correction of the direction of the aircraft, and the stability and controllability of the system are improved. BRIEF DESCRIPTION OF DRAWINGS
[0013] Figure 1 It is the overall structure schematic view in the utility model;
[0014] Figure 2 It is the Y-axis bogie structure schematic view in the utility model;
[0015] Figure 3 It is the support frame structure schematic view in the utility model;
[0016] Figure 4 It is the control mechanism structure schematic view with the X-axis bogie and the Y-axis bogie in the utility model respectively;
[0017] The corresponding relationship between the annotations of various drawings and the component names in the drawings is as follows:
[0018] 10, support frame; 11, X-axis bogie; 12, Y-axis bogie; 13, coaxial counter rotating motor; 14, propeller; 20, steering engine; 21, rocker arm; 22, pull rod; 23, ball head. DETAILED DESCRIPTION
[0019] In the following, only certain exemplary embodiments are simply described. As those skilled in the art can recognize, the described embodiments can be modified in various different ways without departing from the spirit or scope of the utility model. Therefore, the drawings and the description are considered to be exemplary in nature rather than limiting.
[0020] Please refer to Figure 1 and Figure 2It is a whole structure schematic diagram of a coaxial counter-rotating double propeller aircraft control device, which comprises a support frame 10, the top of the support frame 10 is hinged with an X-axis bogie 11 through a connecting arm, the inside of the X-axis bogie 11 is hinged with a Y-axis bogie 12, a coaxial counter-rotating motor 13 is fixedly installed on the Y-axis bogie 12, two groups of counter-rotating propellers 14 are respectively installed on the coaxial counter-rotating motor 13, in this embodiment, by installing a battery and a rudder controller on the bottom of the support frame 10, the coaxial counter-rotating motor 13 is powered by the battery, the coaxial counter-rotating motor 13 rotates under power to drive the two groups of counter-rotating propellers installed thereon (i.e. simultaneously rotating in different directions), the coaxial counter-rotating double propeller structure can effectively offset the torque generated when the propellers rotate, and improve the system stability and maneuverability.
[0021] Further, the Y-axis bogie 12 is connected with the X-axis bogie 11 through a bearing, and the X-axis bogie 11 is also connected with the connecting arm through a bearing.
[0022] As shown in Figure 3 and Figure 4 , two groups of symmetrical control mechanisms are fixedly installed on the support frame 10, the control mechanisms are divided into left control mechanisms and right control mechanisms, the upper end of the left control mechanism is connected with the Y-axis bogie 12, the upper end of the right control mechanism is connected with the X-axis bogie 11, the control mechanism comprises a rudder 20, the rudder 20 is connected with a pull rod 22 through a rocker arm 21, the pull rod 22 and the rocker arm 21 are connected through a ball head 23, the other end of the pull rod 22 is connected with the X-axis bogie 11 and the Y-axis bogie 12 through a ball head 23. In this embodiment, the rudder 20 is controlled to work by a rudder controller on the support frame 10, the X-axis bogie 11 and the Y-axis bogie 12 are controlled to deflect by the rudder 20 through the rocker arm 21 and the pull rod 22, i.e. when the left control mechanism moves, the Y-axis bogie 12 is deflected around the Y-axis by the rudder 20 cooperating with the rocker arm and the pull rod 22; when the right control mechanism moves, the X-axis bogie 11 is deflected around the X-axis by the rudder 20 cooperating with the rocker arm 21 and the pull rod 22.
[0023] It should be noted that in this process, the two rudders 20 cooperate to control the angle of rotation of the coaxial counter-rotating motor 13 within a semicircle.
[0024] Working principle: in use, first through the support frame 10 bottom setting rudder controller control rudder 20 and coaxial counter-rotating motor 13 movement, when the left rudder 20 counterclockwise rotation, rocker arm 21 also counterclockwise downward rotation, in turn drag pull rod 22 downward movement, cooperate with the effect of upper ball head 23 can control Y axis bogie 12 about Y axis counterclockwise deflection, right side rudder 20 clockwise rotation, rocker arm 21 clockwise upward rotation, drive pull rod 22 upward movement, cooperate with the effect of ball head 23 can control X axis bogie 11 about X axis clockwise deflection. Therefore coaxial counter-rotating motor 13 also in the effect of left deflection, reached in the process of correcting the direction of aircraft, offset the torque generated when the propeller rotation, improve the stability and controllability of the system.
[0025] The above-described, only for the preferred specific embodiments of the present application, but the scope of the present application is not limited to this, any skilled in the art of the technical range disclosed in the present application, according to the technical scheme of the present application and the utility model concept of equivalent replacement or change, should be covered within the scope of the present application.
Claims
1. A coaxial contra-rotating twin propeller aircraft control device comprising a support frame (10), characterized in that, The top of the support frame (10) is hinged with an X-axis bogie (11) through a connecting arm, the inside of the X-axis bogie (11) is hinged with a Y-axis bogie (12), the Y-axis bogie (12) is fixedly installed with coaxial counter-rotating motors (13), and the coaxial counter-rotating motors (13) are respectively installed with two groups of mutually counter-rotating propellers (14).
2. The coaxial contra-rotating twin propeller aircraft control apparatus according to claim 1, wherein The X-axis bogie (11) is connected with the connecting arm through a bearing.
3. The coaxial contra-rotating twin propeller aircraft control apparatus according to claim 1, wherein The Y-axis bogie (12) is connected with the X-axis bogie (11) through a bearing.
4. The coaxial contra-rotating twin propeller aircraft control apparatus according to claim 1, wherein The support frame (10) is fixedly installed with two groups of symmetrically distributed control mechanisms, the control mechanisms are divided into left control mechanisms and right control mechanisms, the upper end of the left control mechanism is connected with the Y-axis bogie (12), and the upper end of the right control mechanism is connected with the X-axis bogie (11).
5. The coaxial contra-rotating twin propeller aircraft control apparatus according to claim 4, wherein The control mechanism comprises a steering engine (20), the steering engine (20) is connected with a pull rod (22) through a rocker arm (21), the pull rod (22) and the rocker arm (21) are connected through a ball head (23), and the other end of the pull rod (22) is connected with the X-axis bogie (11) and the Y-axis bogie (12) through ball heads (23) respectively.
6. The coaxial contra-rotating twin propeller aircraft control apparatus according to claim 5, wherein The two steering engines (20) cooperate to control the angle of rotation of the coaxial counter-rotating motors (13) within a semicircle.