Aircraft control handle lifting and rotating mechanism with damping hand feeling
By designing damping components in the aircraft manipulating handle, the problem of airplane manipulating handle in the existing technology does not have the problem of damping the feel, and achieves higher operating accuracy and lower training costs.
Patent Information
- Application Number
- CN202310911253.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2023-07-24
- Publication Date
- 2025-01-24
AI Technical Summary
The existing aircraft joystick does not have a damping feel, which leads to misoperation or improper operation by the pilot, which increases the difficulty and requirements of aircraft driving, and increases the time and capital cost of pilot training.
Design a aircraft manipulating handle rotating mechanism with a damping feel, including the spindle components, rod components and damping parts. The damping part is composed of regulating nuts, compressed reeds, damping friction pieces, and damping fixing tablets, which generates rotation force by relative friction.
By increasing the damping parts, the aircraft controllery handle has a damping feel, reducing the possibility of misunderstanding, increasing the pilot's ability to control the rotation angle, and reducing the difficulty and training cost of aircraft driving.
Smart Images
Figure CN119348812A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to an aircraft control handle, in particular to an aircraft control handle lifting and rotating mechanism with a damping feel. Background Art
[0002] At present, the existing aircraft control handles do not have a damping feel, which can easily lead to pilots' misoperation or improper operation. In addition, it is difficult for pilots to control the rotation angle of the aircraft control handles, which increases the difficulty and requirements of aircraft driving and greatly increases the time and financial costs of pilot training. Summary of the invention
[0003] The purpose of the present invention is to solve the problem that the aircraft control handle in the prior art does not have a damping feel, and to provide a novel aircraft control handle lifting and rotating mechanism with a damping feel.
[0004] In order to achieve the above-mentioned purpose, the present invention provides a technical solution: a lifting and rotating mechanism of an aircraft control handle with a damping feel, comprising: a main shaft component, a rod component, and a damping component; the main shaft component has a transverse main shaft, and the transverse main shaft is driven to rotate by the rod component; the damping component has an adjusting nut, a compression spring, a damping friction plate, and a damping fixed plate, and the transverse main shaft passes through the adjusting nut, the compression spring, the damping friction plate, and the damping fixed plate in sequence, the damping fixed plate is fixed and the damping fixed plate does not interfere with the rotation of the transverse main shaft, and the adjusting nut, the compression spring, and the damping friction plate rotate synchronously with the transverse main shaft, and the adjusting nut applies a force to the damping friction plate in the direction of the damping fixed plate through the compression spring, so that the damping friction plate is against the damping fixed plate; when the transverse main shaft rotates, the damping friction plate rotates synchronously and the damping fixed plate is fixed, that is, the damping friction plate and the damping fixed plate generate relative friction to form a rotational damping force on the transverse main shaft.
[0005] As a preferred solution for an aircraft control handle lifting and rotating mechanism with a damping feel, the adjusting nut and the transverse main shaft form a thread pair; the adjusting nut is displaced to gradually change the size of the rotation damping force.
[0006] As a preferred solution for a lifting and rotating mechanism of an aircraft control handle with a damping feel, the damping friction plate has a through hole, and the transverse main shaft and the through hole of the damping friction plate are axially matched; the damping fixing plate has a through hole, and the transverse main shaft and the through hole of the damping fixing plate are idlingly matched.
[0007] As a preferred solution for an aircraft control handle lifting and rotating mechanism with a damping feel, the through hole of the damping friction plate is a waist-shaped structure; the through hole of the damping fixing plate is a circular structure.
[0008] As a preferred solution for an aircraft control handle lifting and rotating mechanism with a damping feel, an anti-loosening gasket is provided between the adjusting nut and the compression spring.
[0009] As a preferred solution of a lifting and rotating mechanism of an aircraft control handle with a damping feel, the rod component comprises a vertical rotating rod, a vertical control rod, a spring fixing frame, a limit movable block, and a compression spring; the vertical rotating rod is perpendicular to the transverse main axis of the main axis component, and the lower end of the vertical rotating rod is fixedly connected to the transverse main axis; one of the axial side surfaces of the vertical rotating rod has a U-shaped surrounding wall, and the axial side surface and the U-shaped surrounding wall together form a receiving slide groove with an upward opening and an axial opening; the lower end of the vertical control rod is inside the receiving slide groove and the two constitute a sliding pair; the spring fixing frame is on the axial side surface of the vertical rotating rod, and the spring fixing frame has a fixing frame vertical portion, a fixing frame The cam is an angular channel block which is configured to connect the bottom of the U-shaped frame to the top of the frame, and the bottom of the U-shaped frame is a vertical channel block which is configured to connect the bottom of the U-shaped frame to the top of the frame.
[0010] As a preferred solution for a lifting and rotating mechanism of an aircraft control handle with a damped feel, the lower end of the vertical rotating rod is provided with a through hole, and the transverse main shaft cooperates with the axial hole of the through hole of the vertical rotating rod to achieve a fixed connection between the lower end of the vertical rotating rod and the transverse main shaft; preferably, the through hole of the vertical rotating rod is a waist-shaped structure.
[0011] As a preferred solution for an aircraft control handle lifting and rotating mechanism with a damped feel, a spring guide column is provided inside the compression spring, and the spring guide column is fixedly connected to the transverse portion of the fixing frame.
[0012] As a preferred solution for an aircraft control handle lifting and rotating mechanism with a damped feel, the aircraft control handle lifting and rotating mechanism further includes: a gear switching plate and a gear switching wheel; the gear switching plate is fixed, the gear switching plate has a gear switching groove, the gear switching wheel is inside the gear switching groove, and the gear switching wheel is fixedly connected to the vertical control lever.
[0013] Compared with the prior art, the beneficial effects of the present invention are at least: 1. The damping component is added, and the damping friction plate and the damping fixed plate generate relative friction to form a rotational damping force on the lateral main axis, so that the aircraft control handle has a damping feel; 2. The adjusting nut is shifted, and the size of the rotational damping force is continuously adjustable within a certain range; 3. The rod component is modified to make the lifting action of the rod component smoother and more reliable. BRIEF DESCRIPTION OF THE DRAWINGS
[0014] Figure 1 It is a structural schematic diagram of the present invention.
[0015] Figure 2 It is a structural schematic diagram of the rod component in the present invention.
[0016] Figure 3 It is a structural schematic diagram of the damping component in the present invention.
[0017] Figure 4 It is a structural schematic diagram of the mid-gear switching plate of the present invention. Implementation
[0018] The present invention is further described in detail below by means of specific embodiments in combination with the accompanying drawings. It should be noted that the description of these embodiments is used to help understand the present invention, but does not constitute a limitation of the present invention. In addition, the technical features involved in each embodiment of the present invention described below can be combined with each other as long as they do not conflict with each other.
[0019] See also Figure 1 , the figure shows an aircraft control handle lifting and rotating mechanism with a damping feel.
[0020] The aircraft control handle lifting and rotating mechanism comprises: a mechanism housing 1, a main shaft component 2, a rod component 3, a damping component 4, etc. The control actions of the aircraft control handle lifting and rotating mechanism include: a lifting action and a rotating action.
[0021] The spindle component 2 includes a transverse spindle 21 , a spindle bearing 22 , etc. The transverse spindle 21 and the spindle bearing 22 are axially matched. The spindle bearing 22 is fixed. The transverse spindle 21 can rotate inside the spindle bearing 22 .
[0022] Preferably, the mechanism housing 1 has a bearing accommodating groove. The main shaft bearing 22 is located inside the bearing accommodating groove and is sealed and limited by the bearing retaining ring 23.
[0023] See also Figure 2 The rod component 3 includes a vertical rotating rod 31, a vertical operating rod 32, a rod holding portion 33, a spring fixing frame 34, a limiting movable block 35, a compression spring 36, etc.
[0024] The vertical rotating rod 31 is perpendicular to the transverse main shaft 21 of the main shaft component 2. The lower end of the vertical rotating rod 31 is fixedly connected to the transverse main shaft 21. The vertical rotating rod 31 rotates synchronously with the transverse main shaft 21.
[0025] In one embodiment, the lower end of the vertical rotating rod 31 has a through hole, and the transverse main shaft 21 is axially matched with the through hole of the vertical rotating rod 31 to achieve a fixed connection between the lower end of the vertical rotating rod 31 and the transverse main shaft 21. Preferably, the through hole of the vertical rotating rod 31 is a waist-shaped structure.
[0026] A U-shaped surrounding wall 37 is provided on one axial side surface of the vertical rotating rod 31. The axial side surface and the U-shaped surrounding wall 37 together form a receiving sliding groove with an upward opening and an axial opening.
[0027] The lower end of the vertical operating rod 32 is inside the accommodating chute. The lower end of the vertical operating rod 32 and the accommodating chute form a sliding pair. The lower end of the vertical operating rod 32 can move up and down along the accommodating chute. The upper end of the vertical operating rod 32 has the rod gripping portion 33.
[0028] The spring fixing frame 34 is on the axial side of the vertical rotating rod 31. The spring fixing frame 34 has a fixing frame vertical portion 341 and a fixing frame transverse portion 342. The fixing frame vertical portion 341 and the fixing frame transverse portion 342 form an H-shaped structure or a door-shaped structure. The fixing frame vertical portion 341 covers the side portion of the U-shaped surrounding wall 37, and the two can be fixedly connected by screws. The fixing frame transverse portion 342 covers the lower end portion of the vertical operating rod 32 to limit the lower end portion of the vertical operating rod 32 in the accommodating slot to prevent it from slipping out of the axial opening.
[0029] The limiting movable block 35 is located on the axial side of the vertical rotating rod 31 and below the fixing frame transverse portion 342. The limiting movable block 35 can be fixedly connected to the lower end of the vertical operating rod 32 by screws.
[0030] The compression spring 36 is disposed between the horizontal portion 342 of the fixing frame and the position limiting movable block 35. The compression spring 36 is in a compressed state. The downward force of the compression spring 36 acts on the position limiting movable block 35, so that the position limiting movable block 35 drives the lower end of the vertical operating rod 32 to abut against the bottom edge of the U-shaped surrounding wall 37. An upward force is applied to the vertical operating rod 32, and the vertical operating rod 32 shifts upward along the accommodating slide groove. During the shifting process, the vertical operating rod 32 further compresses the compression spring 36 through the position limiting movable block 35.
[0031] Preferably, a spring guide column 360 is provided inside the compression spring 36. The spring guide column 360 is fixedly connected to the fixed frame transverse portion 342. That is, the upper end of the spring guide column 360 is fixed to the fixed transverse portion 342, and the lower end of the spring guide column 360 is suspended. The spring guide column 360 is used to hold the compression spring 36 to prevent it from twisting.
[0032] See also Figure 3 , the damping component 4 is used to provide a rotational damping force to the transverse main shaft 21. The damping component 4 comprises an adjusting nut 41, a compression spring 42, a damping friction plate 43, a damping fixed plate 44, etc. The transverse main shaft 21 passes through the adjusting nut 41, the compression spring 42, the damping friction plate 43, and the damping fixed plate 44 in sequence. Among them, the damping fixed plate 44 is fixed and does not interfere with the rotation of the transverse main shaft 21, while the adjusting nut 41, the compression spring 42, the damping friction plate 43 rotate synchronously with the transverse main shaft 21. The adjusting nut 41 applies a force to the damping friction plate 43 in the direction of the damping fixed plate 44 through the compression spring 42, so that the damping friction plate 43 is against the damping fixed plate 44. The transverse main shaft 21 rotates, the damping friction plate 43 rotates synchronously, and the damping fixed plate 44 is fixed, that is, the damping friction plate 43 and the damping fixed plate 44 generate relative friction to form the rotation damping force.
[0033] The adjusting nut 41 and the transverse main shaft 21 form a thread pair. The adjusting nut 41 is displaced to gradually change the magnitude of the rotation damping force, that is, the magnitude of the rotation damping force is continuously adjustable within a certain range.
[0034] Preferably, the damping friction plate 43 has a through hole. The transverse main shaft 21 is matched with the through hole of the damping friction plate 43. The through hole of the damping friction plate 43 is preferably a waist-shaped structure.
[0035] Preferably, the damping fixing plate 44 has a through hole, and the transverse main shaft 21 and the through hole of the damping fixing plate 44 are idlingly matched to prevent interference between the two.
[0036] Preferably, there is an anti-loosening washer 45 between the adjusting nut 41 and the compression spring 42. The anti-loosening washer 45 is used to prevent the adjusting nut 41 from loosening.
[0037] See also Figure 4 , the aircraft control handle lifting and rotating mechanism may further include: a gear switching plate 5, a gear switching wheel 6, etc. The gear switching plate 5 is fixed. The gear switching plate 5 has a gear switching groove 50. The gear switching wheel 6 is inside the gear switching groove 50. The gear switching wheel 6 is fixedly connected to the vertical joystick 32. The method of using the vertical joystick 32 is as follows: pull the lever holding part 33 upward, and the vertical joystick 32 drives the gear switching wheel 6 to leave the initial slot. At this time, further push and pull the lever holding part 33, and when the gear switching wheel 6 reaches the target slot, release the lever holding part 33, the compression spring 36 resets the vertical joystick 32, and the gear switching wheel 6 automatically enters the target slot.
[0038] Preferably, the gear switching plate 5 can be fixed to the mechanism housing 1 by screws.
[0039] The above only expresses the implementation mode of the present invention, and its description is relatively specific and detailed, but it cannot be understood as limiting the scope of the invention patent. It should be pointed out that for ordinary technicians in this field, several modifications and improvements can be made without departing from the concept of the present invention, which all belong to the protection scope of the present invention. Therefore, the protection scope of the patent of the present invention shall be based on the attached claims.
Claims
1. An aircraft control handle lifting and rotating mechanism with a damping feel, characterized in that: include: A main shaft component, a rod component, and a damping component; the main shaft component has a transverse main shaft, and the transverse main shaft is driven to rotate by the rod component; the damping component has an adjusting nut, a compression spring, a damping friction plate, and a damping fixed plate, and the transverse main shaft passes through the adjusting nut, the compression spring, the damping friction plate, and the damping fixed plate in sequence, the damping fixed plate is fixed and the damping fixed plate does not interfere with the rotation of the transverse main shaft, and the adjusting nut, the compression spring, the damping friction plate and the transverse main shaft rotate synchronously, and the adjusting nut applies a force to the damping friction plate in the direction of the damping fixed plate through the compression spring, so that the damping friction plate is against the damping fixed plate; when the transverse main shaft rotates, the damping friction plate rotates synchronously and the damping fixed plate is fixed, that is, the damping friction plate and the damping fixed plate generate relative friction to form a rotational damping force on the transverse main shaft.
2. The aircraft control handle lifting and rotating mechanism with damping feel according to claim 1, characterized in that: The adjusting nut and the transverse main shaft form a thread pair; the adjusting nut is displaced to gradually change the magnitude of the rotation damping force.
3. The aircraft control handle lifting and rotating mechanism with damping feel according to claim 1, characterized in that: The damping friction plate has a through hole, and the transverse main shaft is axially matched with the through hole of the damping friction plate; the damping fixing plate has a through hole, and the transverse main shaft is idlingly matched with the through hole of the damping fixing plate.
4. The aircraft control handle lifting and rotating mechanism with damping feel according to claim 3, characterized in that: The through hole of the damping friction plate is a waist-shaped structure; the through hole of the damping fixing plate is a circular structure.
5. The aircraft control handle lifting and rotating mechanism with damping feel according to claim 1, characterized in that: An anti-loosening gasket is arranged between the adjusting nut and the compression spring.
6. The aircraft control handle lifting and rotating mechanism with damping feel according to any one of claims 1 to 5, characterized in that: The rod component comprises a vertical rotating rod, a vertical operating rod, a spring fixing frame, a limiting movable block, and a compression spring; the vertical rotating rod is perpendicular to the transverse main axis of the main axis component, and the lower end of the vertical rotating rod is fixedly connected to the transverse main axis; one of the axial side surfaces of the vertical rotating rod has a U-shaped surrounding wall, and the axial side surface and the U-shaped surrounding wall together form a accommodating slide groove with an upward opening and an axial opening; the lower end of the vertical operating rod is inside the accommodating slide groove and the two constitute a sliding pair; the spring fixing frame is on the axial side surface of the vertical rotating rod, and the spring fixing frame has a fixing frame vertical portion and a fixing frame transverse portion, and the fixing frame vertical portion covers The cam is secured on the side of the U-shaped enclosure wall and the two are fixedly connected, the transverse portion of the fixing frame covers the lower end portion of the vertical operating rod to limit the lower end portion of the vertical operating rod to the accommodating slot; the limiting movable block is on the axial side surface of the vertical rotating rod and is located below the transverse portion of the fixing frame, and the limiting movable block is fixedly connected to the lower end portion of the vertical operating rod; the compression spring is provided between the transverse portion of the fixing frame and the limiting movable block, and the compression spring is in a compressed state, and the downward force of the compression spring acts on the limiting movable block, so that the limiting movable block drives the lower end portion of the vertical operating rod to press against the bottom edge of the U-shaped enclosure wall.
7. The aircraft control handle lifting and rotating mechanism with damping feel according to claim 6, characterized in that: The lower end of the vertical rotating rod is provided with a through hole, and the transverse main shaft cooperates with the through hole of the vertical rotating rod to achieve a fixed connection between the lower end of the vertical rotating rod and the transverse main shaft; preferably, the through hole of the vertical rotating rod is a waist-shaped structure.
8. The aircraft control handle lifting and rotating mechanism with damping feel according to claim 6, characterized in that: A spring guide column is arranged inside the compression spring, and the spring guide column is fixedly connected to the transverse portion of the fixing frame.
9. The aircraft control handle lifting and rotating mechanism with damping feel according to any one of claims 6 to 8, characterized in that: The aircraft control handle lifting and rotating mechanism further includes: a gear switching plate and a gear switching wheel; the gear switching plate is fixed, the gear switching plate has a gear switching groove, the gear switching groove has the gear switching wheel inside, and the gear switching wheel is fixedly connected to the vertical control lever.