Cantilever type electromagnetic clutch friction pair structure and flight control system control line system

Abstract

This invention relates to a cantilevered electromagnetic clutch friction pair structure and a flight control system control wiring system, falling within the technical field of aircraft control system structural design. The cantilevered electromagnetic clutch friction pair structure includes: a release rocker arm, a release shaft, an intermediate component, and a limiting component. The intermediate component is mounted on the outer circumference of the release shaft; the limiting component is mounted on the outer circumference of the release shaft; the intermediate component restricts axial movement via the limiting component. When the electromagnetic clutch is engaged, the intermediate component is located within a hook-shaped hole at the end of the release rocker arm, engaging with the hook-shaped hole of the release rocker arm. When the release rocker arm rotates around the center of the hook-shaped hole, wear on the hook-shaped hole and the release shaft is avoided, thus preventing uncontrolled disengagement of the aileron clutch and facilitating reliable engagement of the electromagnetic clutch.

Description

Technical Field

[0001] This invention belongs to the field of aircraft control system structural design technology, and particularly relates to a cantilever electromagnetic clutch friction pair structure and flight control system control lines. Background Technology

[0002] Aircraft control systems are typically connected by two sets of wiring harnesses. If there is no aileron clutch between the left and right control wiring harnesses, the other wiring harness will also be uncontrollable when one side of the wiring harness is jammed, affecting aircraft safety. Therefore, a clutch needs to be installed between the two wiring harnesses. When one side of the control wiring harness is jammed, the clutch can be actively disengaged, allowing the other wiring harness, which is not jammed, to be controlled so that the aircraft can return safely.

[0003] Among the related technologies, there is an electromagnetic clutch that can disengage the left and right control lines in case of a single-sided control line failure. However, when the electromagnetic clutch is engaged, the release shaft and the engagement hole will slide and rub against each other, which can easily cause wear on the release shaft and the engagement hole, resulting in the uncontrolled disengagement of the aileron clutch. Summary of the Invention

[0004] To address the technical problem in related technologies where sliding friction occurs between the release shaft and the engagement hole when the electromagnetic clutch is engaged, easily causing wear on both and leading to uncontrolled disengagement of the aileron clutch, this invention provides a cantilevered electromagnetic clutch friction pair structure and a flight control system control wiring system. The technical solution is as follows:

[0005] In a first aspect, a cantilevered electromagnetic clutch friction pair structure is provided, comprising: a release rocker arm, a release shaft, an intermediate component, and a limiting component.

[0006] The intermediate component is installed on the outer circle of the release shaft; the limiting component is installed on the outer circle surface of the release shaft; the intermediate component restricts axial movement through the limiting component; when the electromagnetic clutch is engaged, the intermediate component is located in the hook-shaped hole at the end of the release rocker arm and is located between the release rocker arm and the release shaft.

[0007] Optionally, the limiting element is a retaining ring, and the outer surface of the release shaft is provided with an annular groove.

[0008] The retaining ring is installed on the annular groove on the outer circumference of the release shaft.

[0009] Optionally, the inside of the hook-shaped hole is coated with a self-lubricating coating.

[0010] Optionally, the intermediate component is a bearing.

[0011] Optionally, the intermediate component is a self-lubricating bushing.

[0012] Alternatively, the bearing may be a deep groove ball bearing, a roller bearing, or a needle roller bearing.

[0013] Alternatively, the clasp may be made of metal.

[0014] In a second aspect, a flight control system control line system is provided, characterized in that it includes the cantilevered electromagnetic clutch friction pair structure described in any one of the first aspects.

[0015] The beneficial effects of this invention are at least as follows:

[0016] The intermediate component of this structure is mounted on the outer circle of the release shaft; the limiting component is mounted on the outer circle surface of the release shaft; the intermediate component restricts axial movement through the limiting component; when the electromagnetic clutch is engaged, the intermediate component is located in the hook-shaped hole at the end of the release rocker arm, and the intermediate component engages with the hook-shaped hole of the release rocker arm; when the electromagnetic clutch is engaged, and the release rocker arm rotates around the center of the hook-shaped hole, wear on the hook-shaped hole of the release rocker arm and the release shaft is avoided, thus preventing the aileron clutch from disengaging uncontrollably and facilitating the reliable engagement of the electromagnetic clutch. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the engagement state of a cantilever electromagnetic clutch friction pair structure provided in an embodiment of the present invention;

[0018] Figure 2 for Figure 1 The AA section view shown. Detailed Implementation

[0019] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

[0020] Please see Figure 1 and Figure 2 This invention provides a cantilevered electromagnetic clutch friction pair structure, comprising: a release rocker arm 5, a release shaft 7, an intermediate component 101, and a limiting component 102.

[0021] Intermediate component 101 is mounted on the outer circumference of release shaft 7; limiting component 102 is mounted on the outer circumference of release shaft 7; intermediate component 101 restricts axial movement through limiting component 102; when the electromagnetic clutch is engaged, intermediate component 101 is located in the hook-shaped hole at the end of release rocker arm 5, and intermediate component 101 engages with the hook-shaped hole of release rocker arm 5. When release rocker arm 5 rotates around the center of the hook-shaped hole, wear on the hook-shaped hole of release rocker arm 5 and release shaft is avoided, thus preventing uncontrolled disengagement of the aileron clutch and facilitating reliable engagement of the electromagnetic clutch.

[0022] In one embodiment, the limiting member can be a retaining ring, and the outer circular surface of the release shaft 7 is provided with an annular groove, and the retaining ring is installed on the annular groove on the outer circular surface of the release shaft 7.

[0023] For example, the retainer ring is made of a metal material, such as stainless steel or titanium alloy.

[0024] In another embodiment, the limiting element can be a nut, which is threadedly connected to the release shaft 7.

[0025] Furthermore, to reduce wear, a self-lubricating coating is applied to the inside of the hook-shaped hole. This self-lubricating coating can be made of composite materials.

[0026] For example, the intermediate component can be a bearing. When the release rocker arm 5 rotates around the center of the hook-shaped hole, there is no relative movement between the outer circle of the bearing and the mating surface of the hook-shaped hole of the release rocker arm 5, which avoids wear on the hook-shaped hole of the release rocker arm and the release shaft. Therefore, it can prevent the aileron clutch from disengaging uncontrollably, which is conducive to the reliable engagement of the electromagnetic clutch.

[0027] In addition, the intermediate part can also be a self-lubricating bushing. When the release rocker arm 5 rotates around the center of the hook hole, the self-lubricating bushing does not move, thus avoiding wear on the release rocker arm hook hole and the release shaft.

[0028] Preferably, considering that there is also relative sliding between the self-lubricating bushing and the rocker arm hook hole, but it is more wear-resistant and has less frictional resistance than the traditional solution, while there is no relative sliding between the bearing and the rocker arm hook hole, the bearing is preferred as the intermediate component.

[0029] For example, the bearing may be a deep groove ball bearing, roller bearing, or needle roller bearing. In practical applications, the type of bearing can be selected based on the load capacity.

[0030] Taking a bearing as an example, the working process of the cantilever electromagnetic clutch friction pair structure provided by this invention is as follows:

[0031] When the electromagnetic clutch is engaged, the large cylindrical surface of the release shaft 7 and the intermediate part 101 are located inside the hook-shaped hole at the end of the release rocker arm 5, and the intermediate part 101 engages with the hook-shaped hole of the release rocker arm 5. When the release rocker arm 5 rotates around the center of the hook-shaped hole, there is no relative movement between the intermediate part 101 and the engagement surface of the hook-shaped hole of the release rocker arm 5, which avoids wear on the hook-shaped hole of the release rocker arm 5 and the release shaft. Therefore, it can prevent the aileron clutch from disengaging uncontrollably, which is conducive to the reliable engagement of the electromagnetic clutch.

[0032] When the electromagnetic clutch is in the clutch state, the release shaft 7 drives the intermediate part 101 to move horizontally to the left until the intermediate part 101 disengages from the hook-shaped hole at the end of the release rocker arm 5. At this time, the small cylindrical surface of the release shaft 7 disengages from the hook-shaped hole at the end of the release rocker arm 5, and the release rocker arm 5 and the release shaft 7 disengage, at which point the clutch is in the disengaged state.

[0033] The present invention also provides a flight control system control line system, including the above-described cantilever electromagnetic clutch friction pair structure.

[0034] The flight control system can be either an aileron or an elevator.

[0035] The above description merely illustrates the embodiments of this application, and while the description is relatively specific and detailed, it should not be construed as limiting the scope of the invention patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Furthermore, any parts of this invention not described in detail are conventional techniques.

Claims

1. A cantilever electromagnetic clutch friction pair structure, characterized in that, include: Release rocker arm, release shaft, intermediate component, and limit component. The intermediate component is mounted on the outer circumference of the release shaft; The limiting component is installed on the outer cylindrical surface of the release shaft; the intermediate component restricts axial movement through the limiting component; when the electromagnetic clutch is engaged, the large cylindrical surface of the release shaft and the intermediate component are located in the hook-shaped hole at the end of the release rocker arm, and the intermediate component is engaged with the hook-shaped hole of the release rocker arm; when the release rocker arm rotates around the center of the hook-shaped hole, there is no relative movement between the intermediate component and the hook-shaped hole engagement surface of the release rocker arm; when the electromagnetic clutch is disengaged, the release shaft drives the intermediate component to move horizontally to the left at the same time until the intermediate component disengages from the hook-shaped hole at the end of the release rocker arm, the small cylindrical surface of the release shaft disengages from the hook-shaped hole at the end of the release rocker arm, the release rocker arm and the release shaft disengage, and the clutch is in the disengaged state; The limiting component is a retaining ring, and the outer surface of the release shaft has an annular groove. The retaining ring is installed on the annular groove on the outer surface of the release shaft; The inside of the hook-shaped hole is coated with a self-lubricating coating. The intermediate component is a bearing; when the release rocker arm rotates around the center of the hook-shaped hole, there is no relative movement between the outer circle of the bearing and the mating surface of the hook-shaped hole of the release rocker arm; Alternatively, the intermediate component is a self-lubricating bushing that remains stationary when the rocker arm is released and rotates around the center of the hook-shaped hole.

2. The cantilevered electromagnetic clutch friction pair structure according to claim 1, characterized in that, The bearings are deep groove ball bearings, roller bearings, or needle roller bearings.

3. The cantilevered electromagnetic clutch friction pair structure according to claim 1, characterized in that, The retaining ring is made of metal.

4. A flight control system control wiring system, characterized in that, It includes the cantilevered electromagnetic clutch friction pair structure as described in any one of claims 1 to 3.

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