Aircraft tie rod base with controllable self-locking function and operation method thereof

Abstract

The present invention discloses an aircraft tie rod base with a controllable self-locking function and an operation method thereof, which belongs to the field of aircraft environmental control technology. The base includes a tie rod motion module for realizing the multi-degree-of-freedom rotation and displacement function of the tie rod, a limit module for limiting the degree of freedom of the tie rod motion module, a self-locking module for helping the limit ball shell to perform linear reciprocating motion, and a control module for real-time monitoring of the tie rod stress state and controlling the start and stop of each electrical component in the device; according to the monitored tie rod stress condition, under the end operation of the control module, the tie rod freedom degree can be adjusted and self-locked through the cooperation of the limit module and the self-locking module, so that the aircraft tie rod can cope with various pipeline working conditions within the full flight envelope, avoid excessive deformation and excessive vibration of the pipeline under special working conditions to have adverse effects on the aircraft structure, and ensure the safe operation of the aircraft environmental control system.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft environmental control, and in particular relates to an aircraft tie rod base with a controllable self-locking function and an operating method thereof. Background Art

[0002] The tie rod is a conventional component used to transmit control actions in the aircraft control system, and is mainly used to transmit movement in a single direction. The traditional tie rod uses a pair of pull ears and a ring buckle at the end of the rod body to rotatably connect, so the tie rod only has a high degree of freedom in the same direction as the pull ear. Once the aircraft encounters a specific working condition within the full flight envelope, the pipeline will be over-deformed, and the tie rod will be forced to twist to a certain extent in the direction of low freedom, which can easily lead to the tie rod breaking. Therefore, the traditional aircraft tie rod structure often faces the risk of fracture failure during operation, which will pose a serious threat to the normal operation of important equipment such as the engine.

[0003] Taking into account the complex operating conditions of aircraft air duct systems, it is a technical problem that urgently needs to be solved in this field to make targeted improvements to the traditional tie rod structure to increase the degree of freedom so that the tie rod can bear tensile and compressive external force loads at different angles and degrees.

[0004] Chinese patent CN 203793643 U discloses a multi-degree-of-freedom operating rod, in which an earring joint I and a rotation mechanism are respectively provided at both ends of the connecting rod, and the rotation mechanism is composed of an earring joint II, a bearing sleeve and a bearing, and the bearing is located between the earring joint II and the bearing sleeve, and a spherical bearing as an external interface is installed in the earring joint I and the earring joint II. In this scheme, after the rotation mechanism is designed at the end of the connecting rod, the rod can be rotated 360° in the axial direction of the rod without increasing the volume of the rod, and the degree of freedom of the rod is significantly improved. However, after careful analysis, it was found that the tie rod structure was proposed more to adapt to some more demanding installation environments or to adjust the initial angles of the tie rod ears at both ends. This is because if the pipeline twists around the tie rod during the flight of the aircraft, the spatial freedom of the tie rod mechanism will be significantly limited, and even present a degree of freedom equivalent to that of a traditional tie rod. Therefore, the tie rod mechanism cannot solve the problem of easy breakage of the tie rod ears under extreme working conditions, and cannot solve the problem of the tie rod tearing when the pipeline moves close to / away from the tie rod. In addition, the tie rod needs to be locked with a cotter pin after installation, so corresponding adjustments cannot be made during the flight of the aircraft, and the operational flexibility is relatively low.

[0005] To sum up, developing and designing a pull rod mechanism that can adapt to various flight conditions during actual flight, and can more flexibly adjust the degree of freedom of the pull rod, control the flexibility of the pipeline, limit its deformation, and ensure the safe operation of the aircraft environmental control system is still a problem that needs to be solved urgently. Solving this problem will also be a major breakthrough in the field of aircraft environmental control. Summary of the invention

[0006] The purpose of the present invention is to solve the problem that the aircraft pipeline tie rod is easy to tear and be damaged due to the difference in deformation freedom when the temperature and pressure of the air in the pipe increase, and to provide an aircraft tie rod base with a controllable self-locking function which has a simple structure, is easy to install, and is flexible and controllable. By controlling the freedom of the tie rod, the flexible adjustment of the aircraft air pipeline system can be achieved, thereby providing technical support for further ensuring its safety.

[0007] The present invention is implemented as follows: an aircraft tie rod base with a controllable self-locking function comprises a tie rod movement module, a limit module, a self-locking module and a control module; the tie rod movement module comprises a tie rod body, a tie rod ball pair and a limit ball shell, the tie rod ball pair is movably placed in the limit ball shell, and the bottom of the tie rod body passes through a second movable hole on the limit ball shell and is fixedly connected to the tie rod ball pair; the limit module comprises a limit rod, a limit block and an annular clamp, two limit rods are arranged on both sides of the tie rod movement module, the top and bottom of the limit rod are respectively fixed with an annular clamp and a limit block, and the limit block is rotatably connected to a fixed shaft; the self-locking module comprises a control rod, a gear rail and a transmission gear, the control rod is fixed at the bottom of the limit ball shell, the gear rail is longitudinally arranged on the side of the control rod, the transmission gear is driven to rotate by a power mechanism, the transmission gear is meshed with the gear rail, and the rotation of the transmission gear drives the gear rail to move longitudinally; the control module comprises a stress sensor and a control terminal, the stress sensor is arranged on the tie rod body, and the stress sensor, the power mechanism and the control terminal are electrically connected.

[0008] Furthermore, the pull rod movement module, the limit module and the self-locking module are packaged in a base box, the base box is fixedly connected to the aircraft cabin wall, a first movable hole is opened on the top of the base box, and the first movable hole and the second movable hole are coaxially arranged.

[0009] Furthermore, the limiting block is bucket-shaped, the pointed parts of the two limiting blocks are arranged inwardly and facing each other, and the arc-shaped opening parts of the two annular clamps are arranged inwardly and facing each other.

[0010] Furthermore, an electromagnetic device is embedded on the inner side of the limiting rod. The electromagnetic device can be magnetically connected to the limiting spherical shell after being energized and magnetized. The electromagnetic device is electrically connected to the control terminal, and a magnetic block is set on the limiting spherical shell at the position in contact with the electromagnetic device.

[0011] Furthermore, a displacement sensor electrically connected to the control terminal is provided on the control rod for monitoring the moving position of the control rod.

[0012] Furthermore, the limiting rod is integrally formed with the limiting block at its bottom and the annular clamp at its top.

[0013] Furthermore, the outer end of the fixed shaft is fixed on the box wall of the base box, and the fixed shaft and the limiting rod space are vertically arranged.

[0014] Furthermore, an annular sleeve is arranged on the outer periphery of the control rod, the inner diameter of the annular sleeve is adapted to the outer diameter of the control rod, a longitudinally penetrating bayonet is arranged on the annular sleeve, the opening size of the bayonet is adapted to the size of the gear rail, a group of connecting shafts are arranged opposite to each other on the annular sleeve, and the other end of the connecting shaft is fixed to the inner wall of the base box.

[0015] The operation method of the above-mentioned aircraft tie rod base with controllable self-locking function is as follows:

[0016] 1) When the stress sensor detects that the stress of the pull rod body reaches or exceeds 0.8 times of the allowable stress σ, the signal is fed back to the control terminal, and the control terminal controls the electromagnetic device to cut off the power, and no magnetic attraction occurs between the limit rod and the limit ball shell. Then the power mechanism drives the transmission gear to rotate, thereby driving the gear rail and the control rod to rise. The limit ball shell pushes the limit rod open during the rising process, and the limit rod rotates outward around the fixed axis. The two annular clamps open back to back. During the rising process of the control rod, the displacement sensor monitors the rising distance and feeds back to the control terminal. When the control rod rises to the specified position, the self-locking module stops working, and the pull rod body obtains a large degree of rotational freedom;

[0017] 2) When the stress sensor detects that the stress of the pull rod body is reduced to less than 0.8 times of the allowable stress σ, the signal is fed back to the control terminal, and the control terminal controls the power mechanism to drive the transmission gear to rotate in the opposite direction, thereby driving the gear rail and the control rod to descend together. During the descent of the limit ball shell, the tip of the limit block is gradually pressed down, driving the limit rod to rotate around the fixed axis, and the two annular clamps close towards each other. The displacement sensor monitors the moving distance and feeds back to the control terminal. When the control rod descends to the specified position, the control terminal controls the electromagnetic device to energize and generate magnetism, and the limit rod and the limit ball shell are magnetically attracted and tightly bound. The position of the limit rod is fixed again, and the pull rod body loses its large rotational freedom, that is, the self-locking of the pull rod is achieved.

[0018] Furthermore, in step 1), when the control rod rises to the upper limit position and the pull rod body obtains a large rotational freedom, the electromagnetic device is controlled to be energized and magnetized again, so that the limit rod can be stably adsorbed on the limit housing to limit the movement of the limit rod;

[0019] Therefore, in step 2), before the signal is fed back to the control terminal and the control terminal controls the power mechanism to drive the transmission gear to rotate in the opposite direction, the control terminal needs to first control the electromagnetic device to cut off the power so that the limit rod can be released from the bound state before subsequent work can be carried out.

[0020] Beneficial effects:

[0021] 1. The present application replaces the traditional tie rod with a ball-jointed tie rod. When the aircraft air pipeline is over-deformed under special working conditions and the tie rod stress reaches or exceeds 0.8 times the allowable stress, the lock of the tie rod can be cancelled through the cooperation of the self-locking module and the limit module, giving the tie rod a larger rotational freedom, thereby controlling the pipeline flexibility, limiting its deformation, and ensuring the safe operation of the aircraft environmental control system; when the pipeline stress drops and the tie rod stress is reduced to less than 0.8 times the allowable stress, the tie rod can be self-locked through the cooperation of the self-locking module and the limit module. The overall control method of the base is flexible and controllable, with a high degree of automation. Through the control of the control module, it is helpful to achieve high-precision adjustment of the flexibility of the aircraft air duct system;

[0022] 2. The present application controls the connection state between the limit rod and the limit ball shell through an electromagnetic device, making the movement of the limit rod more controllable while retaining the relative sliding function. Compared with other mechanical connection methods, the manipulability is stronger. In the entire operation process, the firmness of the self-locking state and the controllability of the activity of the limit rod in the unlocking state are further guaranteed by controlling the magnetization process, which helps to improve the overall stability of the device and avoid damage to the device structure due to unnecessary collisions during operation.

[0023] 3. This application can flexibly combine a large number of tie rods in the aircraft air pipeline system with different degrees of freedom by independently controlling each tie rod, so as to adapt to all working conditions faced by the pipeline within the aircraft's full flight envelope;

[0024] 4. The aircraft tie rod base disclosed in the present application has a simple system structure, clear partitions, can realize multi-level control functions, and has strong adaptability to different states of the tie rod. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a schematic diagram of the overall structure of an aircraft tie rod base with a controllable self-locking function;

[0026] Figure 2 It is a main schematic diagram of the self-locking module;

[0027] Figure 3 is a bottom-up schematic diagram of the self-locking module;

[0028] Figure 4 is an axonometric view of the limit rod;

[0029] Figure 5 It is a schematic diagram of the internal structure of the electromagnetic device;

[0030] Figure 6 It is a schematic diagram of the main view of the aircraft when the pull rod has a large degree of freedom;

[0031] Figure 7It is a schematic diagram of the front view of the aircraft lever in the self-locking state;

[0032] Figure 8 This is a schematic diagram of the installation of an aircraft tie rod base with a controllable self-locking function in a pipeline;

[0033] in:

[0034] 11-tie rod body, 12-tie rod ball pair, 13-limiting ball shell;

[0035] 131- second movable hole;

[0036] 21-limiting rod, 22-limiting block, 23-annular clamp, 24-electromagnetic device, 25-fixed shaft;

[0037] 241-copper wire coil, 242-iron core;

[0038] 31-control rod, 32-gear rail, 33-transmission gear, 34-power motor, 35-annular sleeve;

[0039] 351- bayonet, 352- connecting shaft;

[0040] 41-stress sensor, 42-control terminal;

[0041] 5- base;

[0042] 51-first movable hole. DETAILED DESCRIPTION

[0043] The preferred embodiments of the present invention are described in detail below so that the advantages and features of the present invention can be more easily understood by those skilled in the art, thereby making a clearer and more definite definition of the protection scope of the present invention.

[0044] Embodiment 1: Aircraft tie rod base with controllable self-locking function

[0045] In order to better improve the degree of freedom of the pull rod so that it can meet the usage requirements under various flight conditions and thus ensure the safe operation of the aircraft environmental control system, the present embodiment discloses an aircraft pull rod base with a controllable self-locking function, including a pull rod motion module, a limit module, a self-locking module and a control module; the pull rod motion module, the limit module and the self-locking module are encapsulated in a base box 5, the base box 5 is fixedly connected to the aircraft cabin wall, and a first movable hole 51 is opened on the top of the base box 5 to provide sufficient movable space for the pull rod, and the control module is arranged outside the base box for electrically connecting with each signal transceiver.

[0046] The tie rod motion module is used to realize the multi-degree-of-freedom rotation and displacement function of the tie rod, including a tie rod body 11, a tie rod ball pair 12 and a limiting ball shell 13. The tie rod ball pair 12 is movably placed in the limiting ball shell 12. The diameter of the tie rod ball pair 12 is slightly smaller than the diameter of the limiting ball shell 13, so that the tie rod ball pair 12 can rotate in the limiting ball shell 12 without any obvious position deviation in the horizontal direction. A second movable hole 131 is provided on the top of the limiting ball shell 13, and the first movable hole 51 is coaxially arranged with the second movable hole 131. The bottom of the tie rod body 11 passes through the second movable hole 131 and is fixedly connected to the surface of the tie rod ball pair 12. Based on the motion characteristics of the tie rod ball pair 12 that can rotate at multiple angles, the tie rod body 11 can be given a high degree of freedom of movement under specified conditions.

[0047] The limit module is arranged on the side of the pull rod motion module, and is used to limit the freedom of the pull rod motion module, including a limit rod 21, a limit block 22, an annular clamp 23 and an electromagnetic device 24. The two limit rods 21 are arranged opposite to each other on both sides of the pull rod motion module, and the limit block 22 is fixed to the bottom of the limit rod 21. The limit block 22 is bucket-shaped, and the pointed parts of the two limit blocks are arranged inwardly. The limit block 22 is rotatably connected to a fixed shaft 25. The fixed shaft 25 and the limit rod 21 are arranged vertically in space, and the outer end of the fixed shaft 25 is fixedly connected to the inside of the base box 5, so that the entire limit rod 21 is in a state of being able to rotate around the fixed shaft 25 in a free state. An annular clamp 23 is fixed on the top of each limit rod 22, and the arc-shaped openings of the two annular clamps 23 are arranged inwardly. An electromagnetic device 24 is embedded on the inner side of the limit rod 21, and the electromagnetic device 24 is used to magnetically connect with the limit ball shell 13 to achieve the position limitation of the limit rod 22. In order to achieve the effect of magnetic connection, the limit ball shell 13 can be made of magnetic material as a whole or only a magnetic block can be fixed on the limit ball shell 13 at the position in contact with the electromagnetic device 24.

[0048] The shell of the electromagnetic device 24 is a rectangular structure. The side that contacts the limiting ball shell 13 is made of high-carbon steel sheet with magnetic conductivity, and the other five sides are covered with aluminum foil magnetic isolation layer. The copper wire coil 241 is wrapped around the iron core 242 and placed in the electromagnetic device 24. The iron core 242 is electrically connected to achieve the effect of generating magnetism when electricity is turned on.

[0049] In order to improve the integrity of the movement and the stability of the structure, the limiting rod 21, the limiting block 22 at its bottom and the annular clamp 23 at its top are integrally formed during manufacturing.

[0050] The self-locking module is arranged below the pull rod motion module, and is used to help the limiting spherical shell structure to realize intelligent linear reciprocating motion. The self-locking module includes a control rod 31, a gear rail 32, a transmission gear 33 and a power motor 34; the cylindrical control rod 31 is fixed at the bottom of the limiting spherical shell 13, and the gear rail 32 is longitudinally arranged on the side of the control rod 31. The transmission gear 33 is connected to the motor shaft of the power motor 34 through a coupling to complete the rotation operation. The transmission gear 33 is meshed with the gear rail 32. After the transmission gear 33 rotates, it will drive the gear rail 32 meshed with it to move longitudinally, thereby driving the control rod 31 and the limiting shell 13 to move longitudinally synchronously.

[0051] In order to improve the stability of the longitudinal movement of the control rod 31, an annular sleeve 35 is provided on the outer ring of the control rod 31. The inner diameter of the annular sleeve 35 is adapted to the outer diameter of the control rod 31, so that the outer peripheral surface of the control rod 31 can fit the inner arc surface of the annular sleeve 35 to complete the longitudinal penetration action. In order to ensure that there is no position interference between the annular sleeve 35 and the gear rail 32 during the movement, a longitudinal through-hole 351 is provided on the annular sleeve 35. The opening size of the bayonet 351 is adapted to the size of the gear rail 32. A group of connecting shafts 352 are relatively provided on the annular sleeve 35. The other end of the connecting shaft 352 is fixed on the inner wall of the base box 5, thereby realizing the position limitation of the annular sleeve 35. The design of the annular sleeve 35 can also avoid the problem of gear derailment when the pull rod body 11 rotates around the axis.

[0052] The control module is used to monitor the stress state of the rod in real time and control the start and stop of the device, including a stress sensor 41 and a control terminal 42. The stress sensor 41 is provided on the rod body 11 for real-time monitoring of the stress of the rod, and the stress sensor 41 is electrically connected to the control terminal 42. In order to better control the movement process of the control rod 31, the power motor 34 is electrically connected to the control terminal 42, and a displacement sensor electrically connected to the control terminal 42 is provided on the control rod 31 to limit the moving position of the control rod 31. In order to perform end control on the magnetization process of the electromagnetic device 24, the iron core 242 is also electrically connected to the control terminal 42 in this embodiment.

[0053] The operation method of the above-mentioned aircraft tie rod base is as follows:

[0054] When the deformation of the aircraft air pipeline is too large under special working conditions, the stress sensor 41 detects that the stress of the pull rod body 11 reaches or exceeds 0.8 times the allowable stress σ (σ can be regarded as the stress limit value, 0.8σ means the stress limit value is multiplied by the safety factor 0.8, mainly used to ensure operational safety), the signal is fed back to the control terminal 42, and the control terminal 42 controls the electromagnetic device 24 to cut off the power, so that the limit rod 21 and the limit ball shell 13 are separated from the magnetic attraction and binding state, and then the control terminal 42 controls the power motor 34 to start , driving the transmission gear 33 to rotate, thereby driving the gear rail 32 meshing with it and the control rod 31 to rise. The limiting ball shell 13 will push open the limiting rod 21 during the rising process, and the limiting rod 21 will rotate outward around the fixed axis 25, thereby causing the annular clamp 23 on the top of the limiting rod 21 to open backward. During the rising process of the control rod 31, the displacement sensor monitors the rising distance and feeds back to the control terminal 42. When the control rod 31 rises to the specified position, the self-locking module stops working, and the pull rod body 11 obtains a large rotational freedom. Figure 6 As shown;

[0055] In the above state, the pull rod body 11 obtains a large degree of freedom, but the limit rod 21 at this time is out of the magnetic state, so it may cause unnecessary rotation in the base box 5. Combined with the special working conditions, this unnecessary rotation may affect the stability of the structure and thus affect the normal operation of the aircraft. Therefore, after the pull rod body 11 obtains a large degree of rotational freedom, the electromagnetic device 24 can be controlled again to energize and generate magnetism, so that the limit rod 21 can be stably adsorbed on the limit shell 13.

[0056] When the pull rod body obtains the rotational freedom and the pipeline stress drops, the stress sensor 41 detects that the stress of the pull rod body 11 is reduced to less than 0.8 times of the allowable stress σ, and after the signal is fed back to the control terminal 42, the control terminal 42 first controls the electromagnetic device 24 to cut off the power, so that the limit rod 21 is released from the bound state, and then the control terminal 42 controls the power motor 34 to start, driving the transmission gear 33 to rotate in the opposite direction, thereby driving the gear rail 32 meshing with it to descend together with the control rod 31. During the descent process, the limit ball shell 13 will first contact the limit block 22 and gradually press down the tip of the limit block 22 as the descent process continues, thereby driving the limit ball shell 13 to move downward. The limit rod 21 rotates around the fixed axis 25, so that the annular clamp 23 on the top of the limit rod 21 closes towards each other, and the displacement sensor monitors the moving distance and feeds back to the control terminal 42. When the control rod 31 drops to the specified position, the control terminal 42 controls the electromagnetic device 24 to energize and generate magnetism. The limit rod 21 and the limit ball shell 13 are stably connected due to the magnetic attraction, and the position of the limit rod 21 is fixed again. At this time, the pull rod body 11 is confined in a small space enclosed by the two annular clamps 23. The pull rod body 11 loses a large degree of rotational freedom and can only rotate in the space enclosed by the clamps, thereby realizing the self-locking of the pull rod body 11. Figure 7 shown.

[0057] The above descriptions are merely embodiments of the present invention and are not intended to limit the patent scope of the present invention. Any equivalent structure or equivalent process transformation made using the contents of the present invention specification and drawings, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present invention.

Claims

1. An aircraft tie rod base with a controllable self-locking function, characterized in that: It includes a pull rod motion module, a limit module, a self-locking module and a control module; The tie rod motion module comprises a tie rod body, a tie rod ball pair and a limiting ball shell. The tie rod ball pair is movably arranged in the limiting ball shell. The bottom of the tie rod body passes through the second movable hole on the limiting ball shell and is fixedly connected with the tie rod ball pair. The limit module includes a limit rod, a limit block and an annular clamp. Two limit rods are arranged opposite to each other on both sides of the pull rod motion module. The top and bottom of the limit rod are respectively fixed with an annular clamp and a limit block. The limit block is rotatably connected to the fixed shaft. The self-locking module includes a control rod, a gear rail and a transmission gear. The control rod is fixed at the bottom of the limiting ball shell. The gear rail is longitudinally arranged on the side of the control rod. The transmission gear is driven to rotate by the power mechanism. The transmission gear is meshed with the gear rail. The rotation of the transmission gear drives the gear rail to move longitudinally. The control module includes a stress sensor and a control terminal, the stress sensor is arranged on the pull rod body, and the stress sensor, the power mechanism and the control terminal are electrically connected; The limit block is in the shape of a bucket, the pointed parts of the two limit blocks are arranged inwardly and facing each other, and the arc-shaped opening parts of the two annular clamps are arranged inwardly and facing each other; An electromagnetic device is embedded and connected on the inner side of the limit rod. The electromagnetic device can be magnetically connected to the limit ball shell after being energized and magnetized. The electromagnetic device is electrically connected to the control terminal. A magnetic block is arranged on the limit ball shell at a position in contact with the electromagnetic device. The control rod is provided with a displacement sensor electrically connected to the control terminal for monitoring the moving position of the control rod.

2. The aircraft tie rod base with controllable self-locking function as claimed in claim 1, characterized in that: The pull rod movement module, the limit module and the self-locking module are packaged in a base box, the base box is fixedly connected to the aircraft cabin wall, a first movable hole is opened on the top of the base box, and the first movable hole and the second movable hole are coaxially arranged.

3. The aircraft tie rod base with controllable self-locking function as claimed in claim 1, characterized in that: The limiting rod is integrally formed with the limiting block at the bottom and the annular clamp at the top.

4. The aircraft tie rod base with controllable self-locking function as claimed in claim 2, characterized in that: The outer end of the fixed shaft is fixed on the box wall of the base box, and the fixed shaft and the limiting rod space are vertically arranged.

5. The aircraft tie rod base with controllable self-locking function as claimed in claim 2, characterized in that: An annular sleeve is arranged on the outer periphery of the control rod, the inner diameter of the annular sleeve is adapted to the outer diameter of the control rod, a longitudinally penetrating bayonet is arranged on the annular sleeve, the opening size of the bayonet is adapted to the size of the gear rail, a group of connecting shafts are arranged opposite to each other on the annular sleeve, and the other end of the connecting shaft is fixed on the inner wall of the base box.

6. The method for operating an aircraft tie rod base with a controllable self-locking function according to any one of claims 1 to 5, characterized in that: The operation process is as follows: 1) When the stress sensor detects that the stress of the pull rod body reaches or exceeds 0.8 times the allowable stress σ, the signal is fed back to the control terminal, and the control terminal controls the electromagnetic device to cut off the power, and there is no magnetic attraction between the limit rod and the limit ball shell. Then the power mechanism drives the transmission gear to rotate, thereby driving the gear rail and the control rod to rise. The limit ball shell pushes the limit rod during the rising process, and the limit rod rotates outward around the fixed axis. The two annular clamps open back to back. During the rising process of the control rod, the displacement sensor monitors the rising distance and feeds back to the control terminal. When the control rod rises to the specified position, the self-locking module stops working, and the pull rod body obtains a large degree of rotational freedom; 2) When the stress sensor detects that the stress of the pull rod body is reduced to less than 0.8 times the allowable stress σ, the signal is fed back to the control terminal. The control terminal controls the power mechanism to drive the transmission gear to rotate in the opposite direction, thereby driving the gear rail and the control rod to descend together. During the descent of the limit ball shell, the tip of the limit block is gradually pressed down, driving the limit rod to rotate around the fixed axis, and the two annular clamps close towards each other. The displacement sensor monitors the moving distance and feeds back to the control terminal. When the control rod descends to the specified position, the control terminal controls the electromagnetic device to energize and generate magnetism. The limit rod and the limit ball shell are magnetically attracted and tightly bound, and the position of the limit rod is fixed again. The pull rod body loses its large rotational freedom, thus realizing the self-locking of the pull rod.

7. The method for operating the aircraft tie rod base with controllable self-locking function as claimed in claim 6, characterized in that: In step 1), when the control rod rises to the upper limit position and the pull rod body obtains a large rotational freedom, the electromagnetic device is controlled to be energized and magnetized again, so that the limit rod can be stably adsorbed on the limit ball shell to limit the movement of the limit rod; Therefore, in step 2), before the signal is fed back to the control terminal and the control terminal controls the power mechanism to drive the transmission gear to rotate in the opposite direction, the control terminal needs to first control the electromagnetic device to cut off the power so that the limit rod can be released from the bound state before subsequent work can be carried out.

Images