Linear displacement releasing mechanism for manual resetting of aircraft control

Abstract

The invention provides a linear displacement releasing mechanism for manual resetting of aircraft control, and belongs to the technical field of aircraft control systems. The mechanism comprises an outer side transmission rod assembly used for being connected with a main driving side rod system and an inner side transmission rod assembly used for being connected with a co-driving side rod system. The spring assembly is used for connecting the outer side transmission rod assembly and the inner side transmission rod assembly and has a release and recovery function; and the detection assembly is used for detecting the state of the spring assembly and outputting the detected state. The mechanism is used for connecting a pilot and copilot stick system, the releasing mechanism can be released for infinite times and can be easily reset after being released, and the problems that a traditional releasing mechanism needs to be returned to a factory to be replaced after being released, and the maintenance cost is high are solved. Meanwhile, the releasing force of the releasing mechanism can be adjusted within a certain range, and the problem that the releasing force of a traditional releasing mechanism cannot be adjusted is solved.

Description

Technical Field

[0001] This invention belongs to the field of aircraft control system technology, and specifically relates to a linear displacement release mechanism for manual reset of aircraft controls. Background Technology

[0002] Existing aircraft control line displacement release mechanisms generally use the method of destroying the connecting parts for release, such as the shear pin structure. This structure requires destroying the connecting parts during release, cannot be reused or repaired in the field, and must be returned to the factory for replacement. It has poor maintainability, long maintenance cycle, and high cost. Furthermore, after release, the end face of the destroying part will generate additional load, increasing the control friction. Summary of the Invention

[0003] The purpose of this invention is to provide a release mechanism that can be released an unlimited number of times and can be reset after each release.

[0004] To achieve the above objectives, the present invention provides the following technical solution: a linear displacement release mechanism for manual reset of aircraft controls, the mechanism comprising: an outer transmission rod assembly for connection to the pilot's side stick system, an inner transmission rod assembly for connection to the co-pilot's side stick system, a spring assembly for connecting the outer transmission rod assembly and the inner transmission rod assembly and having a release and recovery function, and a detection assembly for detecting the state of the spring assembly and outputting the detected state.

[0005] The linear displacement release mechanism for manual reset of aircraft controls provided by this invention also has the following technical feature: the outer transmission rod assembly includes a bearing housing connected to the driver's side linkage and an outer rod threadedly connected to the bearing housing. The inner drive rod assembly includes a bearing rod end connected to the passenger-side drivetrain and an inner rod threadedly connected to the bearing rod end. The outer rod is hollow, and the inner rod is inserted into the hollow outer rod. The inner rod assembly is also provided with a stop washer for limiting the circumferential rotation of the inner rod.

[0006] The linear displacement release mechanism for manual reset of aircraft control provided by the present invention also has the following technical features: the outer rod is provided with a through hole, the inner rod is provided with an inner rod annular groove, and the spring assembly passes through the through hole and is engaged in the inner rod annular groove.

[0007] The linear displacement release mechanism for manual reset of aircraft controls provided by this invention also has the following technical features: the spring assembly includes a housing fixed to the outer rod, two connecting structures disposed within the housing, multiple reset springs for reset, and a reset structure for providing thrust to the reset springs. The reset structure is also used to limit the connection structure when it is disengaged.

[0008] The linear displacement release mechanism for manual reset of aircraft controls provided by this invention also has the following technical features: the housing is provided with positioning holes for connection and positioning with an outer rod, positioning bosses for connection and positioning with a reset structure, and a housing extension plate for fixing the detection component. The positioning boss is provided with multiple housing slots for placing the reset spring.

[0009] The linear displacement release mechanism for manual reset of aircraft control provided by the present invention also has the following technical features: the connecting structure includes a bushing fixed to the housing, a steel column, a compression spring disposed in the steel column, a cover plate for applying force to the compression spring, and an adjusting shim disposed between the cover plate and the compression spring for adjusting the compression amount of the compression spring.

[0010] The linear displacement release mechanism for manual reset of aircraft control provided by the present invention also has the following technical features: the steel column includes a steel column ball that passes through the through hole and is engaged in the annular groove of the inner rod, a first steel column that contacts the reset structure, and a hollow steel column second column for accommodating the compression spring, wherein the steel column ball is provided with an end face.

[0011] The linear displacement release mechanism for manual reset of aircraft controls provided by this invention also has the following technical feature: the reset structure includes a reset plate for applying force and a ring. The ring is provided with a reset plate inner hole for the outer rod to pass through and a reset plate through hole for the steel column ball to pass through. The reset plate is provided with a reset plate boss, which contacts the housing to form a sealed space, and the reset spring is placed in the sealed space.

[0012] The linear displacement release mechanism for manual reset of aircraft controls provided by the present invention also has the following technical features: the detection component includes a bracket fixed on the spring assembly, two sensors fixed on the bracket by a double nut structure, a socket box fixed on the spring assembly, and a socket connected to the socket box.

[0013] The linear displacement release mechanism for manual reset of aircraft control provided by the present invention also has the following technical feature: the inner rod assembly further includes a locking nut for locking the stop washer, and the locking nut is provided with a safety hole for preventing loosening.

[0014] Beneficial effects: The linear displacement release mechanism for manual reset of aircraft controls provided by this invention is used to connect the pilot and co-pilot stick systems. This release mechanism can release an unlimited number of times and can be easily reset after release, solving the problem that traditional release mechanisms require factory replacement after release, resulting in high maintenance costs. At the same time, the release force of this release mechanism can be adjusted within a certain range, solving the problem that the release force of traditional release mechanisms is not adjustable. Attached Figure Description

[0015] To more clearly illustrate the technical solutions of the embodiments of this disclosure, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this disclosure. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 This is a schematic diagram of the linear displacement release mechanism for manual reset of aircraft controls provided in an embodiment of the present invention; Figure 2 A cross-sectional view of the linear displacement release mechanism for manual reset of aircraft controls provided in an embodiment of the present invention; Figure 3 This is a schematic diagram of the steel column structure provided in an embodiment of the present invention; Figure 4 This is a schematic diagram of the inner rod provided in an embodiment of the present invention; Figure 5 This is a schematic diagram of the structure of the reset plate provided in an embodiment of the present invention; Figure 6 This is a schematic diagram of the structure of the housing provided in an embodiment of the present invention. Wherein, 1: bearing housing; 1a: bearing housing internal thread; 2: outer rod; 2a: outer rod external thread; 3: steel column; 3a: steel column ball; 3b: end face; 3c: first cylinder; 3d: second cylinder; 4: inner rod; 4a: inner rod annular groove; 4b: inner rod internal thread; 5: bearing rod end; 5a: bearing rod end external thread; 6: compression spring; 7: return spring; 8: return plate; 8a: return plate inner hole; 8b: return plate through hole; 9: sensor; 10: adjusting shim; 1 1: Cover plate; 12: Housing; 12a: Housing groove; 12b: Housing extension plate; 13: First connecting screw; 14: First spring washer; 15: First flat washer; 16: Double nut structure; 17: Bracket; 18: Second connecting screw; 19: Second spring washer; 20: Second flat washer; 21: Bushing; 22: Set screw; 23: Locking washer; 24: Lock nut; 24a: Safety hole; 25: Third connecting screw; 26: Third spring washer; 27: Third flat washer. Detailed Implementation

[0017] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments. However, it should be noted that these embodiments are not intended to limit the present invention. Equivalent changes or substitutions in function, method, or structure made by those skilled in the art based on these embodiments are all within the protection scope of the present invention.

[0018] In the description of the embodiments of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the invention.

[0019] Furthermore, the terms "first," "second," "third," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined with "first," "second," etc., may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0020] The terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to the internal connection between two components. Those skilled in the art will understand the specific meaning of these terms in this invention based on the specific circumstances.

[0021] like Figure 1-6 As shown, this embodiment of the invention provides a linear displacement release mechanism for manual reset of aircraft controls. The mechanism includes: an outer transmission rod assembly for connection to the driver's side stick system, an inner transmission rod assembly for connection to the co-pilot's side stick system, a spring assembly for connecting the outer and inner transmission rod assemblies and having a release and recovery function, and a detection component for detecting the state of the spring assembly and outputting the detected state.

[0022] In some embodiments, the outer drive rod assembly includes a bearing housing 1 connected to the driver's side drivetrain and an outer rod 2 threadedly connected to the bearing housing 1. The outer rod 2 has an external thread 2a, which mates with the internal thread 1a of the bearing housing 1. The inner transmission rod assembly includes a bearing rod end 5 connected to the passenger-side linkage and an inner rod 4 threadedly connected to the bearing rod end 5. The inner rod has an internal thread 4b that connects to the bearing rod end external thread 5a. The outer rod 2 is hollow, and the inner rod 4 is inserted into the hollow outer rod 2. The inner rod assembly is also provided with a stop washer 23 for limiting the circumferential rotation of the inner rod 2.

[0023] In some embodiments, the outer rod 2 is provided with a through hole, the inner rod 4 is provided with an inner rod annular groove 4a, and the spring assembly passes through the through hole and is engaged in the inner rod annular groove 4a.

[0024] In some embodiments, the spring assembly includes a housing 12 fixed to the outer rod 2, two connecting structures disposed within the housing 12, a plurality of reset springs 7 for resetting, and a reset structure for providing thrust to the reset springs 7. The reset structure is also used to limit the connection structure when it is disengaged.

[0025] In some embodiments, the housing 12 is provided with a positioning hole for connecting and positioning with the outer rod 2, a positioning boss for connecting and positioning with the reset structure, and a housing extension plate 12b for fixing the detection component. The positioning boss is provided with a plurality of housing grooves 12a for placing the reset spring.

[0026] In some embodiments, the housing 12 is fixed to the outer rod 2 by a third connecting screw 25, and a third flat washer 27 for increasing the contact area and a third spring washer 26 for preventing loosening are provided in cooperation with the third screw 25.

[0027] In some embodiments, the connection structure includes a bushing 21 fixed to the housing 12, a steel column 3, a compression spring 6 disposed within the steel column 3, a cover plate 11 for applying force to the compression spring 6, and an adjusting shim 10 disposed between the cover plate 11 and the compression spring for adjusting the compression amount of the compression spring 6. The bushing 21 is fixed by a set screw 22.

[0028] In some embodiments, the housing 12 and the cover plate 11 are fixed together by a first connecting screw 13, and a first flat washer 15 for increasing the contact area and a first spring washer 14 for preventing loosening are provided in cooperation with the first connecting screw 13.

[0029] In some embodiments, the steel column 3 includes a steel column ball 3a that passes through the through hole and is engaged in the annular groove 4a of the inner rod, a first steel column cylinder 3c that contacts the reset structure, and a hollow steel column cylinder 3d for accommodating the compression spring. The steel column ball 3a has an end face 3b. Cutting an end face 3b on the steel column ball 3a reduces the disengagement distance.

[0030] In some embodiments, the reset structure includes a reset plate 8 for applying force and a ring. The ring has an inner hole 8a for the outer rod 2 to pass through and a through hole 8b for the steel ball 3a to pass through. The reset plate 8 has a reset plate boss, which contacts the housing 12 to form a sealed space. The reset spring 7 is placed in the sealed space. During processing, two planes can be cut on the ring to facilitate machining the through hole 8b.

[0031] In some embodiments, the detection assembly includes a bracket 17 fixed to a spring assembly, two sensors 9 fixed to the bracket 17 by a double nut structure 16, a socket box fixed to the spring assembly, and a socket connected to the socket box.

[0032] In some embodiments, the housing 12, the bracket 17 and the socket box are fixed together by a second connecting screw 18, and a second flat washer 20 for increasing the contact area and a second spring washer 19 for preventing loosening are provided in cooperation with the second connecting screw 18.

[0033] In some embodiments, the inner rod assembly further includes a locking nut 24 for locking the stop washer 23, the locking nut 24 having a safety hole 24a for preventing loosening.

[0034] In some embodiments, the linear displacement release mechanism for manual reset of the aircraft control has a release force of 1600N, a reset force of 92.7N, a release stroke of 2mm, a stroke of ±50mm relative to the outer cylinder after release, a reset stroke of 2mm, a release force adjustment range of (1287~1456) (N), and a distance of 240mm between the mounting holes at both ends.

[0035] The working principle of the device provided in any of the above embodiments is as follows: Under normal operating conditions, the pilot transmits the load to bearing housing 1, which then transmits it to outer rod 2. Outer rod 2 transmits the load to inner rod 4 via steel column 3. Inner rod 4 transmits the load to the co-pilot via bearing rod end 5. Under normal operating conditions, the vertical component of the transmitted load is less than the pressure of compression spring 6. The spherical surface 3a of steel column is located within the annular groove 4a of inner rod, thereby enabling the release mechanism to realize the movement and load transmission between inner rod 4 and outer rod 2. When one side of the channel is blocked, the vertical component of the load transmitted between the inner rod 4 and the outer rod 2 is greater than the pressure of the compression spring 6, thus causing the steel column 3 to disengage from the annular groove 4a of the inner rod. At the moment the steel column 3 slides out, due to the action of the return spring 7, the return plate 8 moves to the right, and the steel column 3 completely disengages from the annular groove 4a of the inner rod, achieving separation of the inner and outer rods. After the steel column 3 slides out, the return plate 8 moves to the right. The return plate 8 is made of metal, and after entering the magnetic field region at the bottom of the sensor 9, the output signal of the sensor 9 changes from high level to low level. When the jamming is released and resetting is required, the reset plate 8 can be manually pressed along the axis of the inner rod 4 to overcome the pressure of the reset spring 7 and reset the release mechanism. During resetting, the reset plate 8 moves out of the magnetic field area at the bottom of the sensor 9, and the output signal of the sensor 9 changes from low level to high level. The release mechanism uses an adjusting shim 10 and a cover plate 11 to adjust the release force. The cover plate 11 and the housing 12 are connected to prevent loosening by four first connecting screws 13, four first spring washers 14, and four first flat washers 15.

[0036] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention. The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of the present invention, and these improvements and modifications should also be considered within the protection scope of the present invention.

Claims

1. A linear displacement release mechanism for manual reset of aircraft controls, characterized in that, The mechanism includes: an outer drive rod assembly for connection to the driver's side drive system, an inner drive rod assembly for connection to the passenger side drive system, a spring assembly for connecting the outer and inner drive rod assemblies and having a release and recovery function, and a detection assembly for detecting the state of the spring assembly and outputting the detected state.

2. The linear displacement release mechanism for manual reset of aircraft controls according to claim 1, characterized in that, The outer drive rod assembly includes a bearing housing connected to the driver's side drivetrain and an outer rod threadedly connected to the bearing housing. The inner drive rod assembly includes a bearing rod end connected to the passenger-side drivetrain and an inner rod threadedly connected to the bearing rod end. The outer rod is hollow, and the inner rod is inserted into the hollow outer rod. The inner rod assembly is also provided with a stop washer for limiting the circumferential rotation of the inner rod.

3. The linear displacement release mechanism for manual reset of aircraft controls according to claim 2, characterized in that, The outer rod has a through hole, and the inner rod has an inner rod annular groove. The spring assembly passes through the through hole and is engaged in the inner rod annular groove.

4. The linear displacement release mechanism for manual reset of aircraft controls according to claim 3, characterized in that, The spring assembly includes a housing fixed to the outer rod, two connecting structures disposed within the housing, multiple return springs for resetting, and a reset structure for providing thrust to the return springs. The reset structure is also used to limit the connection structure when it is disengaged.

5. The linear displacement release mechanism for manual reset of aircraft controls according to claim 4, characterized in that, The housing is provided with positioning holes for connection and positioning with the outer rod, positioning bosses for connection and positioning with the reset structure, and a housing extension plate for fixing the detection components. The positioning boss is provided with multiple housing slots for placing the reset spring.

6. The linear displacement release mechanism for manual reset of aircraft controls according to claim 4, characterized in that, The connection structure includes a bushing fixed to the housing, a steel column, a compression spring disposed within the steel column, a cover plate for applying force to the compression spring, and an adjusting shim disposed between the cover plate and the compression spring for adjusting the compression amount of the compression spring.

7. The linear displacement release mechanism for manual reset of aircraft controls according to claim 6, characterized in that, The steel column includes a steel column ball that passes through the through hole and is engaged in the annular groove of the inner rod, a first steel column that contacts the reset structure, and a hollow steel column second column for accommodating the compression spring. The steel column ball has an end face.

8. The linear displacement release mechanism for manual reset of aircraft controls according to claim 4, characterized in that, The reset structure includes a reset plate for applying force and a ring. The ring is provided with a reset plate inner hole for the outer rod to pass through and a reset plate through hole for the steel column ball to pass through. The reset plate is provided with a reset plate boss, which contacts the housing to form a sealed space, and the reset spring is placed in the sealed space.

9. The linear displacement release mechanism for manual reset of aircraft controls according to claim 1, characterized in that, The detection assembly includes a bracket fixed to a spring assembly, two sensors fixed to the bracket by a double nut structure, a socket box fixed to the spring assembly, and a socket connected to the socket box.

10. The linear displacement release mechanism for manual reset of aircraft controls according to claim 2, characterized in that, The inner rod assembly also includes a locking nut for locking the stop washer, the locking nut having a safety hole for preventing loosening.

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