Horizontal tail actuator support testing device

Abstract

A horizontal tail actuator support testing device is used for supporting an airplane horizontal tail and triggering a safety rod locking mechanism of a horizontal tail actuator to lock and reset, and comprises an execution element which is connected with the horizontal tail and drives the horizontal tail to move and a control system which drives and controls the execution element. The control system comprises a protection device, and under the condition that the acting force of the execution element on the horizontal tail is higher than a specified value, the protection device acts to enable the acting force to be reduced below the specified value.

Description

Technical Field

[0001] The utility model relates to a horizontal tail actuator support test device. Background Technique

[0002] The horizontal tail actuator is a mechanical device for connecting the horizontal tail and the vertical tail structures of an aircraft. By adjusting the horizontal tail actuator, the angle of the horizontal tail can be adjusted to maintain the static stability of the aircraft. As an important component for maintaining the stable flight of the aircraft, the horizontal tail actuator is provided with a main force transmission path structure and a backup force transmission path structure. The backup force transmission path structure is usually a safety rod locking mechanism, which is used to maintain the horizontal tail posture through two-way (axial and circumferential) locking when the main force transmission path fails due to a fault. To ensure the reliability of the safety rod locking mechanism, its functional test and inspection need to be carried out regularly.

[0003] Currently, in the test and inspection of the above-mentioned safety rod locking mechanism, a fixed / locating strut device needs to be installed to support the horizontal tail and adjust the position of the horizontal tail during the test. The existing fixed / locating strut devices are mainly horizontal tail fixing / locating jigs of a length-adjustable mechanical mechanism. For example, as Figure 2 shown, the horizontal tail fixing / locating jig of the prior art includes a positive and negative nut, a vertical tail connecting screw, a horizontal tail connecting screw, and a connecting member for connecting the horizontal tail, the vertical tail and the screw.

[0004] In the above-mentioned horizontal tail fixing / locating jig of the prior art, the length of the jig is adjusted by rotating the positive and negative nut, so that the jig supports the movement of the horizontal tail. When the jig is in the maximum extended state, the horizontal tail is in the maximum upward position, and when the jig is in the shortest extended state, the horizontal tail is in the neutral position. By moving the horizontal tail up and down, the safety rod in the safety rod locking mechanism of the horizontal tail actuator is pulled to move, so as to trigger the locking or resetting of the safety rod locking mechanism. In addition, the jig can be self-locked at any length within its length adjustment range, so that the horizontal tail can be fixed and supported when disassembling and assembling the horizontal tail actuator.

[0005] However, in the above-mentioned horizontal tail fixing / locating jig, during the process of triggering the safety rod locking mechanism of the horizontal tail actuator by rotating the positive and negative nut, since a wrench is used to rotate the positive and negative nut, it is difficult to appropriately control the magnitude of the force during the rotation of the nut, and there is a situation of over-tightening. When over-tightening occurs, the structure at the connection between the jig and the aircraft structure or other parts may be deformed and damaged due to the large acting force. In addition, due to the limited space near the horizontal tail of the aircraft and the observation point for judging the triggering of the safety rod locking mechanism is usually located at a position far from the position where the jig is configured, the tester usually cannot observe the triggering condition of the safety rod locking mechanism while operating the jig, so usually two people need to cooperate to test the safety rod locking mechanism. Content of the Utility Model

[0006] The present utility model is completed in view of the above problems, and aims to provide a horizontal tail actuator support test device, which can effectively avoid structural deformation damage caused by improper operation while being used for the functional test of the safety rod locking device of the horizontal tail actuator and supporting the horizontal tail.

[0007] To achieve the above object, the present utility model provides a horizontal tail actuator support test device, which is used to support the horizontal tail of an aircraft and trigger the locking and resetting of the safety rod locking mechanism of the horizontal tail actuator, and includes: an actuating element, which is connected to the horizontal tail and drives the horizontal tail to move; and a control system, which drives and controls the movement of the actuating element to trigger the locking or resetting of the safety rod locking mechanism. Wherein, the control system includes a protection device, and when the acting force of the actuating element on the horizontal tail is higher than a specified value, the protection device acts to reduce the acting force to below the specified value.

[0008] According to the horizontal tail actuator support test device of the present utility model, when the acting force on the aircraft structure including the horizontal tail is greater than the specified value, the above-mentioned acting force can be reduced by the provided protection device, thereby preventing damage to the aircraft structure caused by excessive acting force due to improper operation. In addition, due to the adoption of a structure including an actuating element and a control system, the actuating element can be controlled by the control system at a position where it is convenient to observe the triggering condition of the safety rod locking mechanism of the horizontal tail actuator, so that a single person can test the safety rod locking structure.

[0009] In addition, in the horizontal tail actuator support test device of the present utility model, preferably, the specified value is greater than the larger one of the acting forces when triggering the locking or resetting of the safety rod locking mechanism.

[0010] According to this structure, before the safety rod locking mechanism triggers locking or resetting, the protection device will not act, thus ensuring that the support test device can normally test the function of the safety rod locking mechanism.

[0011] In addition, in the horizontal tail actuator support test device of the present utility model, preferably, the control system is a hydraulic control system, the hydraulic control system and the actuating element form a hydraulic circuit, and the protection device is a pressure relief valve.

[0012] According to this structure, the control system drives and controls the actuating element through hydraulic pressure, and relieves pressure through the provided pressure relief valve to reduce the acting force applied to the aircraft structure, thereby protecting the aircraft structure.

[0013] In addition, in the horizontal tail actuator support test device of the present utility model, preferably, a plurality of pressure relief valves are provided in parallel.

[0014] According to this structure, by arranging a plurality of pressure relief valves in parallel, in the case where one of the pressure relief valves fails and cannot be normally opened for pressure relief, pressure relief can still be carried out through other pressure relief valves connected in parallel therewith, thereby improving the reliability of the support test device.

[0015] In addition, in the horizontal tail actuator support test device of the present utility model, preferably, the actuating element includes a cylinder barrel and a piston, and the horizontal tail is connected to any one of the cylinder barrel and the piston.

[0016] In addition, in the horizontal tail actuator support test device of the present utility model, preferably, the control system further includes a switching element, and the switching element switches the movement direction of the piston relative to the cylinder barrel.

[0017] According to this structure, the control system can switch the movement direction of the piston in the actuating element through the switching element, thereby switching the movement direction of the horizontal tail connected to the actuating element, and triggering the locking or resetting of the safety rod locking mechanism.

[0018] In addition, in the horizontal tail actuator support test device of the present utility model, preferably, the control system further includes a check valve, and the check valve enables the liquid in the hydraulic circuit to flow unidirectionally.

[0019] According to this structure, the liquid in the hydraulic circuit only flows unidirectionally, thereby preventing backflow from occurring when the movement direction of the piston is switched by the switching element and affecting the normal operation of the support test device.

[0020] (Effect of the utility model)

[0021] According to the present utility model, a horizontal tail actuator support test device composed of a control system and an actuating element is adopted. Compared with the conventional method of moving the aircraft horizontal tail by manually turning a nut and telescoping a support rod, in the case where the force applied to the aircraft structure is greater than a preset specified value due to improper human operation or the like, the protection device provided can timely reduce the above-mentioned force and prevent deformation and damage of the aircraft structure. In addition, by driving and controlling the actuating element through the control system to drive the aircraft horizontal tail to move to test the function of the safety rod locking mechanism, stable control can be achieved, and it is convenient to control the actuating element while observing the triggering state of the safety rod locking mechanism, reducing the labor cost. Moreover, the support test device can not only be used to test the function of the safety rod locking mechanism, but also support the horizontal tail and maintain its posture for the disassembly and assembly maintenance of the horizontal tail actuator. Description of the Drawings

[0022] Figure 1It is a schematic diagram showing the connection state between the support test device of the embodiment and the peripheral structure of the horizontal tail actuator.

[0023] Figure 2 It is a schematic structural diagram of a fixture in the prior art.

[0024] Figure 3 It is a schematic diagram of the principle of the support test device of the embodiment.

[0025] Figure 4 It is a schematic structural diagram of the actuation connection device of the embodiment.

[0026] Figure 5 It is a schematic diagram showing the connection between the actuation connection device of the embodiment and the horizontal tail and vertical tail.

[0027] Figure 6 It is a force analysis diagram of the support test device of the embodiment.

[0028] (Symbol Explanation)

[0029] 1 Horizontal tail;

[0030] 2 Horizontal tail actuator;

[0031] 3 Vertical tail;

[0032] 10 Actuation connection device;

[0033] 11 Actuating cylinder;

[0034] 11a Cylinder part;

[0035] 11b Connection part;

[0036] 12 Piston rod;

[0037] 13, 15 Bolts;

[0038] 14, 16 Nuts;

[0039] 17 Vertical tail joint;

[0040] 18 Horizontal tail joint;

[0041] 20 Directional control valve;

[0042] 21 Inlet port;

[0043] 22 Return port;

[0044] 23, 24 Outlet ports;

[0045] 30 First pressure relief valve;

[0046] 40 Second pressure relief valve;

[0047] 50, 60 Check valves;

[0048] 70 fuel tank;

[0049] 80 hydraulic pump;

[0050] 111, 121 double fork ears;

[0051] 112, 122 through holes. Detailed implementation mode

[0052] The implementation mode of the present utility model will be described below with reference to the accompanying drawings.

[0053] As Figure 3 shown, the horizontal tail actuator support test device (hereinafter, sometimes simply referred to as "support test device") of this implementation mode mainly includes an actuation connection device 10 as an actuating element and a control system for controlling the operation of the actuation connection device 10.

[0054] (Actuation connection device)

[0055] As Figure 4 shown, the main body of the actuation connection device 10 is a pressure cylinder, which includes an actuating cylinder 11 and a piston rod 12. In addition, the actuation connection device 10 also includes a connecting component. Hereinafter, for the convenience of description, the length direction of the actuation connection device 10 is set as the left - right direction, and the direction in which the piston rod 12 is pushed out of the actuating cylinder 11 is set as the right direction.

[0056] The actuating cylinder 11 is, for example, a hydraulic actuating cylinder formed of a high - strength material such as cast iron or cast steel, and it includes a cylinder part 11a and a connecting part 11b.

[0057] The cylinder part 11a is formed in a cylindrical shape, with its left end closed and its right end open. A ring - shaped part protruding radially inward is formed around the entire circumference of the right end of the cylinder part 11a, and an opening for the rod body of the piston rod 12 to pass through is formed radially inward of the ring - shaped part. The interior of the cylinder part 11a is divided into two chambers, left and right, by the rod tail of the piston rod 12 described later.

[0058] The connecting part 11b is integrally formed with the cylinder part 11a. As Figure 4 shown, the main body part of the connecting part 11b is formed in a plate - like shape extending in the left - right direction from the left end of the cylinder part 11a. A double fork ear 111 is formed at the left end of the connecting part 11b, and two through holes 112 penetrating the double fork ear 111 in the thickness direction of the connecting part 11b are formed on the double fork ear 111. The through holes 112 are for bolts 13 to pass through. The actuating cylinder 11 is connected to the vertical tail joint 17 described later through the double fork ear 111.

[0059] In addition, the above - mentioned double fork ear 111 is integrally formed with the actuating cylinder 11, but it is not limited thereto. For example, it can also be fixed to the actuating cylinder 11 as an independent component in a manner that can rotate relative to the actuating cylinder 11.

[0060] The piston rod 12 is also formed of a high-strength material and includes a rod head, a rod body, and a rod tail.

[0061] The rod tail of the piston rod 12 of the present embodiment is formed in a cylindrical shape extending in the left-right direction. The rod tail is disposed in the cylinder portion 11a of the actuating cylinder 11 so as to be movable in the left-right direction relative to the actuating cylinder 11, and the outer peripheral edge of the rod tail contacts the inner wall of the cylinder portion 11a in a liquid-tight manner, thereby partitioning the interior of the cylinder portion 11a into two left and right chambers. When hydraulic oil enters the actuating cylinder 11, the hydraulic oil drives the rod tail, thereby driving the entire piston rod 12 to move. And when the piston rod 12 moves to the rightmost position, the rod tail can be engaged with the annular portion at the right end of the actuating cylinder 11, thereby achieving the effect of restricting the piston rod 12 from detaching from the actuating cylinder 11.

[0062] The rod head is formed at the right end of the piston rod 12, and its main body portion is formed in a cylindrical shape extending in the left-right direction from the right end of the rod body. Similarly, a double fork ear 121 and two through holes 122 on the double fork ear 121 are formed at the right end portion of the rod head and the connecting portion 11b of the actuating cylinder 11 described above, and the through holes 122 are for bolts 15 to pass through. The piston rod 12 is connected to a horizontal tail joint 18 described later through the double fork ear 121.

[0063] The rod body is formed in a cylindrical shape extending in the left-right direction, and constitutes the main body portion of the piston rod 12. It is connected to the rod tail at the left end and to the rod head at the right end. The rod body can pass through the opening formed at the right end of the actuating cylinder 11 and move in the left-right direction relative to the actuating cylinder 11. The diameter of the rod body is smaller than the diameter of the rod tail. In addition, the length of the rod body can be specifically selected according to the actual application situation.

[0064] In addition, the double fork ear 121 is integrally formed with the piston rod 12, but is not limited thereto. For example, it can also be a separate component and be fixed to the piston rod 12 in a manner that can rotate relative to the piston rod 12.

[0065] The connecting members include bolts 13, 15 and nuts 14, 16. The bolts 13, 14 are composed of heads and screws, and their screws can pass through the through holes 112, 122 described above and the through holes formed in the vertical tail joint 17 and the horizontal tail joint 18 described later. The nuts 15, 16 can be respectively threadedly engaged with the screws of the bolts 13, 14.

[0066] In addition, as described above, in the actuating connection device 10 of the embodiment, the actuating cylinder 11 is connected to the vertical tail joint 17, and the piston rod 12 is connected to the horizontal tail joint 18, but is not limited thereto. It can also be that the actuating cylinder 11 is connected to the horizontal tail joint 17, and the piston rod 12 is connected to the vertical tail joint 18. At this time, the direction in which the piston rod 12 is pushed out relative to the actuating cylinder 11 is leftward.

[0067] (Control system)

[0068] As Figure 3 shown, the control system of this embodiment is a hydraulic control system. In addition, the liquid used in the hydraulic control system of this embodiment is hydraulic oil.

[0069] The hydraulic control system includes a directional control valve 20, a first pressure relief valve 30, a second pressure relief valve 40, check valves 50, 60, an oil tank 70, and a hydraulic pump 80. The hydraulic oil stored in the oil tank 70 sequentially passes through the hydraulic pump 80, the check valve 50, the directional control valve 20, the actuator 11 (chamber), the directional control valve 20, and the check valve 60 and returns to the oil tank 70, thereby forming a hydraulic oil circuit.

[0070] The directional control valve 20 constituting the switching element of this embodiment is a three-position four-way manual directional control valve, which has three working positions (left position, middle position, right position), and four passages are provided inside it.

[0071] The directional control valve 20 has four ports 21 to 24. Among them, the port 21 is an oil inlet connected to the hydraulic pump 80 through a hydraulic oil circuit, the port 22 is an oil return port connected to the oil tank 70 through a hydraulic oil circuit, and the ports 23 and 24 are oil outlets, which are respectively connected to the left chamber and the right chamber inside the actuator 11 through a hydraulic oil circuit.

[0072] By manually switching the working position of the directional control valve 20 to select the passage, the states of the left and right chambers of the actuator 11 are switched.

[0073] Specifically, when the directional control valve 20 is set to the left position, the port 21 communicates with the right chamber of the actuator 11 via the port 24, and the port 22 communicates with the left chamber via the port 23. The high-pressure hydraulic oil pressurized by the hydraulic pump 80 enters the right chamber to make it a high-pressure chamber. When the directional control valve 20 is set to the right position, the port 21 communicates with the left chamber of the actuator 11 via the port 23, and the port 22 communicates with the right chamber via the port 24. The high-pressure hydraulic oil enters the left chamber to make it a high-pressure chamber. When the directional control valve 20 is set to the middle position, the ports 21 and 22 are not connected to any of the ports 23 and 24, so the left and right chambers cannot be connected through the hydraulic oil circuit and are in a cut-off and isolated state.

[0074] The one-way valves 50 and 60 are hydraulic components that allow the hydraulic oil to flow from the inlet to the outlet and prevent backflow. The one-way valve 50 is arranged on the hydraulic oil path connecting the port 21 of the directional control valve 20 and the hydraulic pump 80, allowing the hydraulic oil to flow from the hydraulic pump 80 into the directional control valve 20 and preventing backflow. The one-way valve 60 is arranged on the hydraulic oil path connecting the port 22 of the directional control valve 20 and the oil tank 70, allowing the hydraulic oil to flow back from the directional control valve 20 to the oil tank 70 and preventing backflow. Through the one-way valves 50 and 60, when the working position of the directional control valve 20 is switched to switch the hydraulic oil path, backflow of the hydraulic oil will not occur in the hydraulic oil path, thereby maintaining the state of applying pressure to the piston rod 12.

[0075] The hydraulic pump 80 is, for example, a manual piston-type hydraulic pump that sucks hydraulic oil from the oil tank 70, pressurizes it into high-pressure oil, and then transports the high-pressure oil into the hydraulic oil path. The high-pressure hydraulic oil transmitted to the actuator 11 drives the piston rod to move. In addition, the hydraulic pump 80 is not limited to a piston pump, and it can also be a vane pump, a screw pump, etc., and the hydraulic pump 80 can also be an electric or pneumatic hydraulic pump.

[0076] The first pressure relief valve 30 and the second pressure relief valve 40 constitute the protection device of this embodiment. The pressure relief valves 30 and 40 are, for example, spring-type pressure relief valves. Their inlet ends are connected between the one-way valve 50 and the port 21 of the directional control valve 20, and their outlet ends are connected between the port 22 of the directional control valve 20 and the one-way valve 60, and the first pressure relief valve 30 and the second pressure relief valve 40 are connected in parallel with each other. Each pressure relief valve can be automatically opened and closed according to the pressure in the system. When the pressure in the system exceeds a preset pressure threshold (pressure setting value), each pressure relief valve opens, allowing the hydraulic oil to flow directly back to the oil tank 70, thereby preventing the pressure applied by the actuating connection device 10 to each structure connected thereto from being too large due to excessive pressure in the system, and further preventing structural deformation damage caused by the operation of the actuating connection device. In addition, since two pressure relief valves 30 and 40 are arranged in parallel, when one of the pressure relief valves fails to open normally due to a fault or the like, the other pressure relief valve can still be used for pressure relief, thereby improving the reliability of the protection function.

[0077] In addition, the number of pressure relief valves constituting the protection device can also be one, or more than three.

[0078] Hereinafter, a method for determining the pressure relief valve pressure of the first pressure relief valve 30 and the second pressure relief valve 40 will be described.

[0079] Figure 6 It is the force analysis diagram of the support test device of the embodiment. Figure 6 In it, the line segment AB represents the horizontal tail actuator, the line segment CD represents the support test device, the point E represents the pivot axis of the horizontal tail, the point G represents the center of gravity of the horizontal tail, the point H represents the safety rod locking mechanism of the horizontal tail actuator, L HRepresents the lever arm from the safety bar locking mechanism to the horizontal tail pivot shaft, L G Represents the lever arm from the center of gravity of the horizontal tail to the horizontal tail pivot shaft, L GSE Represents the lever arm from the horizontal tail pivot shaft to the support test device. When the horizontal tail is in the horizontal equilibrium position, i.e., the zero position, the safety bar locking mechanism is subjected to a tensile force. Let the gravity of the horizontal tail at this time be F G The tensile force received at the safety bar locking mechanism is set as F H Then the torque relationship on both sides of the pivot shaft at this time is shown in the following formula (1).

[0080] F H ×L H =F G ×L G (1)

[0081] Let the force (trigger force) that triggers the safety bar locking mechanism be F T And let the pressure received by the support test device when the safety bar locking mechanism is triggered be F GSE ’, then the torque relationship at this time is shown in the following formula (2).

[0082] (F T -F H )×L H =F GSE ’×L GSE (2)

[0083] Thus, F GSE ’ can be expressed by the following formula (3).

[0084] F GSE ’=(F T -F G ×L G / L H )×L H / L GSE (3)

[0085] Let the restoring force of the safety bar locking mechanism be F T ’, and let the tensile force received by the support test device when the safety bar locking mechanism is restored be F GSE ”, then the torque relationship at this time is shown in the following formula (4).

[0086] (F T ’+F H )×L H =F GSE ”×L GSE (4)

[0087] Thus, F GSE ” can be expressed by the following formula (5).

[0088] FGSE ” = (F T ’ + F G × L G / L H ) × L H / L GSE (5)

[0089] Here, the larger value of F GSE ’ and F GSE ” calculated by the above formulas (3) and (5) is taken as the minimum required triggering force F GSE of the support test device. When this minimum required triggering force, that is, the acting force of the actuating connection device 10 on the horizontal tail is F GSE , the hydraulic pressure in the hydraulic control system, that is, the triggering hydraulic pressure of the safety rod locking mechanism, is set to P, and P is obtained by the following formula (6),

[0090] P = F GSE / A (6)

[0091] where A is the piston area.

[0092] Therefore, in order to ensure the triggering of the safety rod locking mechanism while preventing excessive pressure in the hydraulic control system from damaging the structure, the opening pressure of the first pressure relief valve 30 is set to a suitable value greater than the triggering hydraulic pressure of the safety rod locking mechanism, for example, set to P + 50 Psi. At the same time, the opening pressure of the second pressure relief valve 40 as the second-stage pressure relief unit is set to a suitable value greater than the opening pressure of the first pressure relief valve 30, for example, set to P + 100 Psi. In addition, the set values of the opening pressures of the first pressure relief valve 30 and the second pressure relief valve 40 are not limited to the above values, and they can be appropriately set according to the compressive strength of the actuating connection device 10 and each structure connected to the actuating connection device 10. Also, the opening pressures of the first pressure relief valve 30 and the second pressure relief valve 40 can be set to the same value.

[0093] When using the support test device of the embodiment, first, the actuating connection device 10 is connected to the vertical tail and the horizontal tail of the aircraft. Specifically, as Figure 1 shown, a horizontal tail joint 18 is fixedly connected to the horizontal tail 1, and a vertical tail joint 17 is fixedly connected to the vertical tail 3. The joints 17 and 18 respectively have ears that can be inserted into the double fork ears 111 and 121, and through holes (not shown) are formed in the ears along the thickness direction of the ears. When the horizontal tail actuator 2 is operated to make the horizontal tail 1 in the neutral position, first, the double fork ear 111 of the actuating cylinder 11 is fitted to the ear of the vertical tail joint 17, so that the ear of the vertical tail joint 17 is inserted between the two fork ears of the double fork ear 111 and the through hole formed in the ear coincides with the two through holes 112 in the through direction of the through hole. Then, as Figure 5As shown, the vertical tail joint 17 and the actuating cylinder 11 are fastened by bolts 13 and nuts 14 to connect them. The actuating connecting device 10 can rotate relative to the vertical tail joint 17 through the actuating cylinder 11.

[0094] Afterwards, when the horizontal tail 1 is in the neutral position, the length of the piston rod 12 in the actuating connection device 10 extending from the actuating cylinder 11 is adjusted by the oil pressure control system, and the actuating connection device 10 is rotated to a suitable angle relative to the vertical tail joint 17 so that the double fork ears 121 on the piston rod 12 are matched to the ears on the horizontal tail joint 18 in the same manner as the double fork ears 111, and the bolts 15 and nuts 16 are used for fastening and connection. Thus, the connection between the actuating connection device 10 and the horizontal tail 1 and the vertical tail 3 is completed.

[0095] When the function of the safety rod locking mechanism of the horizontal tail actuator is tested by using the support test device of the embodiment, the safety rod locking mechanism is triggered to lock or reset by adjusting the length of the actuation connection device 10 .

[0096] Specifically, the safety rod locking mechanism mainly includes a safety rod that can move up and down, a torque spring connected to the safety rod, a housing that limits the upward movement of the safety rod, and a reset rod for judging the moving position of the safety rod. When the safety rod moves upward for a certain distance, the flange formed on the safety rod base is locked to the top of the housing, thereby limiting its further upward movement. At this time, it can be judged whether the safety rod moves upward and triggers the lock by the degree of exposure of the mark marked on the top of the reset rod. When testing the locking function of the safety rod locking mechanism, first, for example, the main force transmission path of the horizontal tail actuator 2 is disconnected by removing the connection structure between the main force transmission path of the horizontal tail actuator 2 and the horizontal tail 1. Then, the tester manually operates the hydraulic pump 80 to suck in and pressurize the hydraulic oil in the oil tank 70 into high-pressure hydraulic oil, and at this time, the three-position four-way reversing valve 20 is set in the right position, and the high-pressure hydraulic oil flows into the left chamber of the actuator cylinder 11 through the one-way valve 50 and the reversing valve 20, driving the piston rod 12 to move rightward relative to the actuator cylinder 11, thereby pulling the horizontal tail 1 connected thereto to move upward. At this time, the safety rod (not shown) in the safety rod locking mechanism in the horizontal tail connector 2 connected to the horizontal tail 1 moves upward along with the movement of the horizontal tail 1. When the horizontal tail 1 moves upward a certain distance, the safety rod locking mechanism is triggered to lock.

[0097] Afterwards, when testing the reset function of the safety rod locking mechanism, the reversing valve 20 is set to the left position, and the high-pressure hydraulic oil flows into the right chamber of the actuator cylinder 11, driving the piston rod 12 to move left relative to the actuator cylinder 11, thereby pulling the horizontal tail and subsequently pulling the safety rod downward, triggering the reset of the safety rod locking mechanism.

[0098] A first pressure relief valve 30 and a second pressure relief valve 40 with an opening pressure greater than that of the first pressure relief valve 30 are provided in the hydraulic control system. The opening pressure of each pressure relief valve is greater than the triggering hydraulic pressure of the above-mentioned safety rod locking mechanism and much less than the pressure that can damage the aircraft structure. During the above-mentioned test using the support test device of the implementation method, the tester continuously operates the hydraulic pump 80 manually to move the piston rod 12 of the actuating connection device 10 to the left or right. During this process, when the pressure in the hydraulic control system is higher than the triggering hydraulic pressure of the safety rod locking mechanism and exceeds the set value of the opening pressure of the first pressure relief valve 30 due to improper operation of the tester, the first pressure relief valve 30 opens, causing the high-pressure hydraulic oil to flow back to the fuel tank 70, thereby reducing the pressure in the system and preventing excessive pressure from deforming and damaging the structure.

[0099] In the case where the first pressure relief valve 30 fails to operate normally, the second pressure relief valve 40 provided can cause the high-pressure hydraulic oil to flow back to the fuel tank 70 when the pressure in the system exceeds the opening pressure of the second pressure relief valve 40, thereby reducing the pressure in the system and preventing excessive pressure from deforming and damaging the structure. Therefore, by providing the second pressure relief valve 40, the reliability of the function of preventing structural damage of the support test device can be improved.

[0100] Thus, even if an operation error occurs during the operation of the horizontal tail actuator support test device of this implementation method, resulting in excessive pressure, the two pressure relief valves provided can automatically relieve the pressure and reduce the pressure, avoiding deformation damage caused by excessive pressure.

[0101] In addition, through the support test device composed of the hydraulic control system and the actuating connection device 10, the tester can place the hydraulic control system near a position where it is convenient to observe and judge whether the safety rod locking mechanism is triggered (for example, the top of the horizontal tail actuator 2), so that the up and down movement of the horizontal tail 1 can be controlled while observing the triggering condition of the safety rod locking mechanism. Thus, the number of people participating in the test operation can be reduced, saving labor costs.

[0102] In addition, the horizontal tail 1 can be adjusted to an appropriate position by setting the reversing valve 20 to the left or right position, and then the reversing valve 20 is set to the middle position, so that the left and right chambers of the actuating cylinder 11 are isolated from each other, so that the actuating connection device 10 is used for the support of the horizontal tail 1. Thus, the support test device of the implementation method can be used to position and support the horizontal tail 1 for disassembly, maintenance, etc. of the horizontal tail actuator 2.

[0103] (Main effects of this implementation method)

[0104] According to the horizontal tail actuator support test device of the present embodiment, a support test device composed of an actuating connection device and a hydraulic control system for driving and controlling the actuating connection device is adopted. A pressure relief valve is provided in the hydraulic control system. When the hydraulic pressure in the system is too high due to improper human operation or the like, and the acting force applied to the aircraft structure is greater than the preset specified value, the pressure relief valve is used to relieve the pressure in time to reduce the above-mentioned acting force and prevent the deformation and damage of the aircraft structure. In addition, by driving and controlling the movement of the aircraft horizontal tail through the hydraulic control system to test the function of the safety rod locking mechanism, stable control can be achieved, and it is convenient to control the movement of the horizontal tail while observing the triggering state of the safety rod locking mechanism, reducing the labor cost. Moreover, the support test device can support the horizontal tail and maintain its posture for the disassembly, assembly and maintenance of the horizontal tail actuator.

[0105] The present invention has been described exemplarily above in conjunction with the accompanying drawings. Obviously, the specific implementation of the present invention is not limited by the above embodiments.

[0106] For example, in the above embodiment, a horizontal tail support test device for an aircraft with an actuating connection device configured as a hydraulic cylinder as an actuator and a hydraulic drive control system as a control system is taken as an example for description. However, the support test device can also be composed of an electric cylinder as an actuator and a servo control system for driving and controlling the electric cylinder.

[0107] The electric cylinder includes a lead screw and a cylinder body. The cylinder body is connected to the vertical tail, and the lead screw is connected to the horizontal tail. The lead screw moves linearly relative to the cylinder body to drive the horizontal tail to move.

[0108] The servo control system includes, for example, a controller, a power source (power supply), a servo motor, etc. The electric cylinder has a lead screw as a moving part. The servo motor is connected to the electric cylinder to drive the lead screw of the electric cylinder to move, and for example, the controller changes the current direction in the circuit to control the movement direction of the lead screw.

[0109] In addition, a pressure sensor for detecting the acting force borne on the lead screw is provided in the servo control system. The pressure sensor sends the detected pressure information to the controller of the servo control system in a wired or wireless manner. The judgment module in the controller judges whether the detected pressure value exceeds the preset specified value. When it is judged that the detected pressure value is higher than the specified value, the controller immediately switches the current direction in the circuit to the direction opposite to the current direction until the detected pressure value is less than the specified value. Thus, a protection device is constituted by the pressure sensor and the controller.

[0110] It should be understood that within its scope, the present invention can freely combine the various parts in the embodiments, or appropriately deform or omit the various parts in the embodiments.

Claims

1. A horizontal tail actuator support test device, used to support the horizontal tail of an aircraft and trigger the safety rod locking mechanism of the horizontal tail actuator to lock and reset, characterized in that: include: An actuator, the actuator is connected to the horizontal tail and drives the horizontal tail to move; as well as A control system, wherein the control system drives and controls the movement of the actuator to trigger the locking or resetting of the safety rod locking mechanism, The control system includes a protection device, When the force exerted by the actuator on the horizontal tail is higher than a specified value, the protection device is activated to reduce the force to below the specified value.

2. The horizontal tail actuator support test device according to claim 1, characterized in that: The predetermined value is greater than the larger one of the forces when the safety lever locking mechanism is triggered to lock or reset.

3. The horizontal tail actuator support test device according to claim 2, characterized in that: The control system is a hydraulic control system, and the hydraulic control system and the actuator form a hydraulic circuit. The protection device is a pressure relief valve.

4. The horizontal tail actuator support test device according to claim 3, characterized in that: A plurality of the pressure relief valves are arranged in parallel.

5. The horizontal tail actuator support test device according to claim 3 or 4, characterized in that: The actuator comprises a cylinder and a piston. The horizontal tail is connected to any one of the cylinder and the piston.

6. The horizontal tail actuator support test device according to claim 5, characterized in that: The control system further comprises a switching element, The switching element switches a movement direction of the piston relative to the cylinder.

7. The horizontal tail actuator support test device according to claim 6, characterized in that: The control system further includes a one-way valve, which enables the fluid in the hydraulic circuit to flow in one direction.

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