Manual-automatic integrated electric undercarriage switch control device
By designing a manual-automatic electric landing gear switch control device, the automatic movement of the handle parts is achieved using the drive motor and reducer, the problem that the landing gear switch control device in the prior art only has manual mode, and the landing gear synchronous operation in the automatic mode is realized, reducing the workload and improving the reliability of operation.
Patent Information
- Application Number
- CN202311724788.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2023-12-14
- Publication Date
- 2025-06-17
AI Technical Summary
In the prior art, the landing gear switch control device has only manual mode, resulting in the need of secondary operation by ground crew or pilot after the aircraft lands or takes off to ensure that the handle components of the two landing gear switch control devices are in the same position, increasing the workload and the failure to relocate the operation may be forgotten.
A manual-automatic electric landing gear switch control device is designed, including handle parts, switch parts and actuators. The automatic action of the handle parts is realized through the driving motor and reducer, and the angular displacement sensor and electromagnetic brake are used to ensure the accurate position synchronization of the handle parts.
The landing gear switch control device has two modes: manual and automatic. When the handle part of one landing gear switch control device is turned into place, the handle part of the other landing gear switch control device is automatically in place, reducing the workload of ground crew members or pilots, and avoiding the risk of forgetting to return to the position.
Smart Images
Figure CN120156686A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to a landing gear switch control device, and in particular, to a manual and electric integrated landing gear switch control device. Background Art
[0002] In the aviation field, in order to adapt to the flight habits of pilots, the working mode of the landing gear switch control device is the manual mode. There are two landing gear switch control devices in a two-seat aircraft. The two landing gear switch control devices are independent of each other. When the handle part of one landing gear switch control device is pulled, the handle part of the other landing gear switch control device remains in place and does not follow automatically. It is necessary for the ground crew or the pilot to perform a secondary operation after the aircraft lands or takes off, and manually pull the handle part of the other landing gear switch control device to make the handle parts of the two landing gear switch control devices in the same position. The disadvantages are as follows: it increases the workload of the ground crew or the pilot, and sometimes it is easy to forget to perform the homing operation. Summary of the Invention
[0003] The object of the present invention is to solve the technical problem that the working mode of the landing gear switch control device in the prior art has only the manual mode, and to provide a new type of manual and electric integrated landing gear switch control device.
[0004] In order to achieve the above object, the technical solution provided by the present invention is: a manual and electric integrated landing gear switch control device, including: a handle part, a switch part and an actuator; the handle part has a handle rod part; the actuator has a drive motor and a reducer, and the drive motor drives the handle rod part to act through the reducer according to an external follow-up instruction. Wherein, the follow-up instruction is provided by another manual and electric integrated landing gear switch control device in the two-seat aircraft.
[0005] As a preferred solution of the manual and electric integrated landing gear switch control device, the upper end of the handle rod part has a handle holding part, and a handle indicator light is arranged inside the handle holding part.
[0006] As a preferred solution of the manual and automatic integrated electric landing gear switch control device, the switch component has a left control switch, a right control switch, a left spring piece, a right spring piece and a structural member including a left cam and a right cam. The left control switch is paired and installed with the left spring piece and fixed on the left side of the structural member; the right control switch is paired and installed with the right spring piece and fixed on the right side of the structural member; the structural member is fixed at the lower end of the handle rod part; when the handle rod part is pulled to the right, the left cam of the structural member touches the left spring piece, thereby triggering the left control switch and sending a first signal for the landing gear to act to the aircraft upper computer; when the handle rod part is pulled to the left, the right cam of the structural member touches the right spring piece, thereby triggering the right control switch and sending a second signal for the landing gear to act to the aircraft upper computer.
[0007] As a preferred solution of the manual and automatic integrated electric landing gear switch control device, it further includes: an angular displacement sensor, and the angular displacement sensor is used to sample the angular position of the handle rod part.
[0008] As a preferred solution of the manual and automatic integrated electric landing gear switch control device, it further includes: an electromagnetic brake, and the electromagnetic brake is used to selectively brake the reducer. The movement position of the handle rod part is locked by the electromagnetic brake.
[0009] As a preferred solution of the manual and automatic integrated electric landing gear switch control device, it further includes: a force-sensing damping device, and the force-sensing damping device is used to provide force-sensing damping to the handle rod part.
[0010] Compared with the prior art, the beneficial effects of the present invention are at least as follows: The landing gear switch control device has both manual and automatic modes. When there is a two-seat aircraft with two landing gear switch control devices, after the handle part of one landing gear switch control device is pulled in place, the handle part of the other landing gear switch control device automatically reaches the position. Thus, after the aircraft lands or takes off, there is no need for ground crew or pilots to perform secondary operations, greatly reducing the workload of ground crew or pilots. Description of the Drawings
[0011] Figure 1 It is a schematic assembly structure diagram of an embodiment of the present invention.
[0012] Figure 2 It is a schematic structural diagram of the landing gear switch operating handle part and the landing gear switch part of an embodiment of the present invention (combined state, the support housing is omitted).
[0013] Figure 3 It is a schematic structural diagram of the drive motor, the reducer, the electromagnetic brake and the angular displacement sensor of an embodiment of the present invention (combined state, the support housing is omitted).
[0014] Figure 4 This is a schematic structural view of the large gear in the final-stage spur gear pair in an embodiment of the present invention.
[0015] Figure 5 This is a schematic structural view of the angular displacement sensor in an embodiment of the present invention.
[0016] Figure 6 This is a schematic structural view of the force-sensing damping device in an embodiment of the present invention. Detailed implementation manners
[0017] The present invention will be further described in detail below in conjunction with the accompanying drawings through specific implementation manners. It should be noted here that the description of these implementation manners is used to help understand the present invention, but does not constitute a limitation to the present invention. In addition, the technical features involved in the various implementation manners of the present invention described below can be combined with each other as long as they do not conflict with each other.
[0018] Please refer to Figures 1 to 6 , which shows a manual and automatic electric landing gear switch control device.
[0019] The landing gear switch control device is used to control the landing gear of the aircraft to selectively perform retraction or lowering actions. Compared with the existing landing gear switch control device, the working mode of the landing gear switch control device in this embodiment not only has a manual mode, but also has an automatic mode.
[0020] The landing gear switch control device includes: a mounting box body 3, a handle component 1, a switch component 4, an actuator 5, an electromagnetic brake 8, an angular displacement sensor 9, a logic control circuit 7, etc.
[0021] Please refer to Figure 2 , which shows the handle component 1 and the switch component 4.
[0022] The handle component 1 has a handle grip portion 101, a manual mode switch 102, a handle rod portion 103, a protective cover 104, etc.
[0023] The handle grip portion 101 is fixed to the upper end of the handle rod portion 103 by screws. Preferably, there is a handle indicator light (not shown in the figure) inside the handle grip portion 101. The handle indicator light is used to indicate the working position of the handle grip portion 101. For example, when the handle indicator light is in the on state, it means that the handle grip portion 101 is pulled to the retraction position, and when the handle indicator light is in the off state, it means that the handle component 1 is pulled to the lowering position.
[0024] The manual mode switch 102 is fixed to the handle rod portion 103 by screws.
[0025] The protective cover 104 is fixed to the handle rod portion 103.
[0026] The switch component 4 includes a left control switch 401, a right control switch 402, a left spring piece 403, a right spring piece 404, and a structural member 405 including a left cam 406 and a right cam 407. The left control switch 401 is paired and installed with the left spring piece 403 and fixed to the left side of the structural member 405 by screws. The right control switch 402 is paired and installed with the right spring piece 404 and fixed to the right side of the structural member 405 by screws. The structural member 405 is fixed to the lower end of the handle rod portion 103 by screws. The structural member 405 moves synchronously with the handle rod portion 103 and has the same rotation axis. When the handle rod portion 103 is turned to the right, the left cam 406 of the structural member 405 touches the left spring piece 403, thereby triggering the left control switch 401 and sending a first landing gear action signal, such as a retraction signal, to the aircraft upper computer. When the handle rod portion 103 is turned to the left, the right cam 407 of the structural member 405 touches the right spring piece 404, thereby triggering the right control switch 402 and sending a second landing gear action signal, such as a lowering signal, to the aircraft upper computer.
[0027] Please refer to Figure 3 , the actuator 5 is shown in the figure. The actuator 5 has a drive motor 501 and a speed reducer. The drive motor 1 can be an adjustable-speed brushless DC motor and can rotate forward and backward. The drive motor 501 is fixed to the internal bracket by screws and serves as the power source of the speed reducer. The speed reducer includes: a front-end two-stage spur gear pair, a three-stage planetary gear train, and a final-stage spur gear pair.
[0028] The front two-stage spur gear pair comprises a first gear 502, a second gear 503, a third gear 504, a fourth gear 506, a first bearing pair 505 and a second bearing pair 507. The first gear 502 is meshed with the second gear 503 for transmission. The third gear 504 is meshed with the fourth gear 506 for transmission. The second gear 503 and the third gear 504 are double gears and have the same rotation axis. The first gear 502 is fixed to the output shaft of the drive motor 501 by screws. One of the shaft ends of the first gear 502 rotates synchronously with the output shaft of the drive motor 501 and has the same rotation axis. The second gear 503 and the third gear 504 are supported by the first bearing pair 505, and the first bearing pair 505 is installed in the housing bracket. The fourth gear 506 is supported by the second bearing pair 507, and there is a primary sun gear after the fourth gear 506 passes through the left bearing of the second bearing pair 507. The fourth gear 506 rotates synchronously with the primary sun gear and has the same rotation axis.
[0029] The three-stage planetary reduction gear train 508 is a planetary reduction gear, and the first-stage sun gear on the left side of the fourth gear 506 is the input sun gear of the three-stage planetary reduction gear train 508 .
[0030] See also Figure 4 , the final spur gear pair has a fifth gear 510 and a sixth gear 511. The fifth gear 510 in the final spur gear pair is mounted and fixed on the output planet carrier of the three-stage planetary reduction gear train 508, and the fifth gear 510 rotates synchronously with the output planet carrier of the three-stage planetary reduction gear train 508 and has the same rotation axis; the sixth gear 511 is supported by two bearings 509, and the fifth gear 510 in the final spur gear pair is meshed with the sixth gear 511 for transmission; a flat structure 514 is provided at the middle position on the right side of the shaft of the sixth gear 511 in the final spur gear pair, and a "I"-shaped groove structure 515 is provided at the right end. The sixth gear 511 and the handle rod 103 have a common rotating shaft. Preferably, each gear is selected with a small module.
[0031] See also Figure 5 , the angular displacement sensor 9 is fixed on the internal bracket by screws. The output shaft of the angular displacement sensor 9 has a flat "I"-shaped structure 902. The "I"-shaped structure 902 of the output shaft of the angular displacement sensor 9 is inserted into the "I"-shaped groove structure 515 of the sixth gear 511 in the final spur gear pair of the reducer. The output shaft of the angular displacement sensor 9 rotates synchronously with the sixth gear 511 of the final spur gear pair of the reducer and has the same rotation axis. The angular displacement sensor 9 is used to sample the rotation angle of the sixth gear 511, that is, to determine the angular position of the handle rod 103.
[0032] The logic control circuit 7 serves as the control center of the electric landing gear switch control device. Automatic mode of the landing gear switch control device: The manual mode switch 102 is shielded, and at this time, the manual mode switch 102 is ineffective when pressed. The drive motor 501 is powered on, and according to an external control signal (provided by the angular displacement sensor of another electric landing gear switch control device), the handle member 1 is controlled to rotate through the speed reducer. Manual mode of the landing gear switch control device: The manual mode switch 102 is pressed, the drive motor 501 is not powered on, and the handle member 1 operates under the control of the pilot.
[0033] In one embodiment, the electric landing gear switch control device further includes: an electromagnetic brake 8. The electromagnetic brake 8 is used to selectively brake the other shaft end of the first gear 502. The electromagnetic brake 8 is fixedly installed on the housing bracket through screws 801. The other shaft end of the first gear 502 is connected to the rotating part inside the electromagnetic brake 8, rotates synchronously with the rotating part inside the electromagnetic brake 8, and has the same rotation axis. In the locked mode of the electric landing gear switch control device, the electromagnetic brake 8 is powered off, and the first gear 502, the drive motor 501, and the speed reducer are all in a braking state. In the manual mode and automatic mode of the electric landing gear switch control device, the electromagnetic brake 8 is powered on, and the first gear 502, the output shaft of the drive motor 501, and the speed reducer are all in a non-braking state.
[0034] In one embodiment, please refer to Figure 6, the electric landing gear switch control device further includes: a force-sensing damping device 11. The force-sensing damping device 11 is located inside the device mounting box 3. The force-sensing damping device 11 has a dial 1101, a spring fixing block 1102, a spring 1103, and a steel ball 1104. The spring fixing block 1102 surrounds the outside of the dial 1101. The spring fixing block 1102 has a radial hole 1107. Inside the radial hole 1107 are the steel ball 1104 and the spring 1103. The steel ball 1104 is inside and the spring 1103 is outside. The outer end of the spring 1103 is fixed. The steel ball 1104 is always in contact with the groove surface 1106 of the dial 1101 under the elastic force of the spring 1103. The dial 1101 is provided with a flat inner hole 1108, which cooperates with the flat structure 514 at the middle position on the right side of the shaft of the sixth gear 511 in the final spur gear pair and rotates synchronously. The spring fixing block 1102 is provided with two protruding structures 1105 and is fixedly connected to the housing of the landing gear switch control device. The dial 1101 and the sixth gear 511 in the final spur gear pair have the same axis. The hole 1107 for installing the spring in the spring fixing block 1102 has the same indexing angle as the groove for placing the steel ball 1104 on the dial 1101. When the dial 1101 rotates relative to the spring fixing block 1102, the steel ball 1104 moves axially along the axis of the radial hole 1107 in the spring fixing block 1102 to enter and exit the dial groove 1106.
[0035] In one embodiment, the electric landing gear switch control device further includes: a light guide plate component 12. The light guide plate component 12 serves as the top cover of the device mounting box 3. On the light guide plate component 12, there are installed a one-key action switch 2, a "lower" position indication character 1201 for the control handle, and a "retract" position indication character 1202. The one-key action switch 2 is electrically connected to the logic control circuit 7 through a wire. After the one-key action switch 2 is pressed, the automatic action of the control handle can be realized, and the "retract" and "lower" position indication characters of the control handle can be lit.
[0036] The above only expresses the embodiments of the present invention, and its description is relatively specific and detailed, but it cannot be understood as a limitation to the scope of the invention patent. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present invention, several deformations and improvements can still be made, and these all belong to the protection scope of the present invention. Therefore, the protection scope of the present invention patent should be subject to the appended claims.
Claims
1. A manual and automatic integrated electric landing gear switch control device, characterized in that, Comprising: A handle component, a switch component and an actuator; the handle component has a handle rod portion; the actuator has a drive motor and a speed reducer, and the drive motor drives the handle rod portion to act through the speed reducer according to an external follow-up instruction.
2. The manual and automatic integrated electric landing gear switch control device according to claim 1, characterized in that, The upper end of the handle rod portion has a handle gripping portion, and a handle indicator light is arranged inside the handle gripping portion.
3. The manual and automatic integrated electric landing gear switch control device according to claim 1, characterized in that, The switch component has a left control switch, a right control switch, a left spring piece, a right spring piece and a structural member including a left cam and a right cam. The left control switch is paired and installed with the left spring piece and fixed on the left side of the structural member; the right control switch is paired and installed with the right spring piece and fixed on the right side of the structural member; the structural member is fixed at the lower end of the handle rod portion; when the handle rod portion is pulled to the right, the left cam of the structural member touches the left spring piece, thereby triggering the left control switch and sending a first signal for the landing gear to act to the aircraft upper computer; when the handle rod portion is pulled to the left, the right cam of the structural member touches the right spring piece, thereby triggering the right control switch and sending a second signal for the landing gear to act to the aircraft upper computer.
4. The manual and automatic integrated electric landing gear switch control device according to claim 1, characterized in that, Further comprising: An angular displacement sensor for sampling the angular position of the handle rod portion.
5. The manual and automatic integrated electric landing gear switch control device according to claim 1, characterized in that, Further comprising: An electromagnetic brake for selectively braking the speed reducer.
6. The manual and automatic integrated electric landing gear switch control device according to claim 1, characterized in that, Further comprising: A force-sensing damping device for providing force-sensing damping to the handle rod portion.