CN117184444B - Prediction test method for obstacle surmounting impact load of aviation aircraft tire - Google Patents
Prediction test method for obstacle surmounting impact load of aviation aircraft tire Download PDFInfo
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Abstract
The invention discloses a prediction test method for an obstacle surmounting impact load of an aircraft tire, which belongs to the technical field of aircraft tests and comprises the following steps of S1, constructing a tire low-speed obstacle surmounting test system; s2, performing a tire low-speed obstacle crossing test; s3, predicting the high-speed obstacle surmounting load, and acquiring the equivalent displacement of the wheel axle center of the tire surmounting an obstacle through the method for predicting the obstacle surmounting impact load of the aircraft tire, so that the accuracy of the obstacle surmounting load of the aircraft tire can be effectively improved, the clamping devices on two sides of the obstacle test system can enable the flat plate to enter the fixing frame to be in a horizontal state, the test error is reduced, and the accuracy of predicting the obstacle surmounting load of the aircraft is further improved.
Description
Technical Field
The invention relates to the technical field of aircraft load prediction and test verification, in particular to an aircraft tire obstacle crossing impact load prediction test method.
Background
Aircraft tires are commonly known as aircraft tires. Aircraft tires are important components in aircraft where safety and reliability requirements are high. Both the safe take-off and landing of an aircraft must rely on various unique functions of the aircraft tires.
The obstacle crossing test of the aviation tire refers to the performance of the tire when passing through obstacles, and mainly comprises the aspects of the grip force, the lateral stability, the durability and the like of the tire.
The obstacle crossing test of the aircraft tire is generally carried out by adopting a method for simulating actual conditions, such as adding obstacles in the test process, simulating different road surface conditions and the like. Professional test equipment and tools, such as sensors, data collectors, computers, etc., are required for testing in order to analyze and evaluate the test results.
The obstacle crossing test of the aircraft tire is one of important links for ensuring the safe operation of the aircraft, and the test result directly influences the take-off and landing performance and the flight safety of the aircraft. Accordingly, aircraft tire manufacturers must strictly follow relevant standards and requirements and carefully analyze and evaluate the test results to ensure quality and reliability of the aircraft tires.
The aircraft can cross the obstacle in the running process, a transient impact force can be generated to act on the aircraft body and the landing gear, and particularly, the running speed of the carrier-based aircraft is higher, the carrier-based environment is more complex, and the strength assessment of the aircraft body and the landing gear is more strict. In the design of the carrier-based aircraft, because the impact load caused by crossing a deck obstacle is difficult to predict accurately, and the impact load can be superimposed to the high impact load, which is the key load input for the design of the aircraft, the previous method of directly acting the shape of the obstacle on the center of the wheel shaft of the landing gear cannot consider the influence of the deformation and the energy absorption of the aircraft tire, so that the prediction error of the obstacle crossing load is larger, and therefore, the accurate prediction and simulation of the obstacle crossing dynamics process and the impact load of the carrier-based aircraft are required by an aircraft obstacle crossing impact load prediction and test method.
Disclosure of Invention
In order to solve the technical problems, the invention provides a prediction test method for obstacle surmounting impact load of an aircraft tire.
The technical scheme of the invention is as follows: a prediction test method for obstacle surmounting impact load of an aircraft tire comprises the following steps:
s1, constructing a low-speed obstacle surmounting test system of an aircraft tire:
the aircraft tire is arranged in an obstacle test system, the motor drives the flat plate to horizontally move, the aircraft tire above the flat plate is driven to roll under the action of friction force after the flat plate moves, the flat plate moves at a uniform speed in the test process, and the movement of the flat plate can be stopped after the aircraft tire completely passes over an obstacle on the flat plate;
s2, performing a low-speed obstacle surmounting test of the aircraft tire:
the obstacle is fixed on the flat plate, the uniform motion state of the flat plate is detected by the infrared displacement sensor so as to ensure that the flat plate is in the uniform motion state, and the impact load applied to the aircraft tire when the aircraft tire passes over the obstacle in a quasi-static state under the rated load is detected by the force sensorF(s) And calculate the equivalent displacement of the wheel axle center of the aircraft tire across the obstacle through the formula (1),
Equivalent displacement of the wheel axle center of the aircraft tire over an obstacleThe calculation formula of (2) is as follows:
(1)
wherein,for aircraft tires to cross obstacles as a function of rolling distance, +.>For the curve of the equivalent displacement of the center of the wheel axle along with the rolling distance when the aircraft tire passes over the obstacle, +.>Is the vertical rigidity of the aircraft tire;
s3, predicting the high-speed obstacle surmounting load:
equivalent displacement of the center of the wheel axle calculated in the step S2Inputting the high-speed obstacle surmounting impact load prediction model into an airplane multi-body dynamics analysis model to predict the high-speed obstacle surmounting impact load of an airplane tire;
the formula of the aircraft multi-body dynamics analysis model is as follows:
+m/>(2)
wherein,for the landing gear before obstacle crossing initial load +.>Predicting load for high speed obstacle surmounting impact of aircraft tires, < > for>For vertical damping of aircraft tires, m is the mass of the aircraft tire, < >>For the vertical equivalent speed of the shaft center when the aircraft tire passes over the obstacle wheel, +.>For the vertical equivalent acceleration of the wheel axle centre when the aircraft tire passes over an obstacle, < >>Is byOne derivation is performed to obtain ∈>By->And (3) conducting twice derivation.
Further, the rated load range of the aircraft tire is 10-500kN, and the moving speed v of the flat plate is in the range of 0m/min < v < 10m/min.
Description: the moving speed of the flat plate is usually smaller, and the flat plate is used for obstacle crossing test under a quasi-static state, so that the load born by the aircraft tire is detected, the equivalent displacement of the wheel axle center is calculated through the load born by the aircraft tire, and then the load born by the aircraft tire is predicted when the aircraft is obstacle crossing under a high speed through the equivalent displacement of the wheel axle center.
Further, the obstacle test system comprises a base, a fixing frame is fixedly connected to the base, a tire mounting system is arranged above the fixing frame, an obstacle mounting system is arranged below the fixing frame, and a force sensor is arranged between the fixing frame and the tire mounting system.
Description: the obstacle test system can be used for effectively predicting the load born by the aircraft tire during obstacle crossing at high speed.
Further, the tire mounting system comprises a hydraulic actuator, the fixed end of the hydraulic actuator is rigidly connected with the top of the fixing frame, a sleeve is fixedly connected below the telescopic end of the hydraulic actuator, a rotating shaft is rotationally connected with the sleeve, and two ends of the rotating shaft are respectively fixedly connected with an aircraft tire.
Description: the aircraft tire is adjusted to contact the flat plate by a hydraulic actuator of the tire mounting system.
Further, the aircraft tire comprises a hub, a tread is wrapped on the outer side of the hub, and the hub is detachably connected with the rotating shaft.
Description: the rotating shaft is fixedly connected with the rotating shaft through the hub, and the rotating shaft rotates in the sleeve.
Further, the barrier mounting system comprises a plurality of gear shafts, the plurality of gear shafts are connected to the fixing frame in a parallel rotating mode, a motor is arranged at the front end of one gear shaft, an output shaft of the motor is connected with the gear shafts in a transmission mode, a flat plate is arranged above the plurality of gear shafts, the gear shafts are connected with the bottom of the flat plate in a meshed transmission mode, and barriers are fixedly connected to the upper surface of the flat plate.
Description: the flat plate is fixed through the obstacle mounting system, the gear shaft is meshed with the bottom of the flat plate for transmission, movement of the flat plate can be controlled better, and movement precision of the flat plate is improved.
Further, each of the left side and the right side of the base is provided with a clamping device, each clamping device comprises a clamping frame, an upper shock absorber is arranged above the clamping frame, a lower shock absorber is arranged below the clamping frame, each of the two sides above the clamping frame is provided with an upper sliding groove, each of the two sides below the clamping frame is provided with a lower sliding groove, the upper end of each upper shock absorber is fixedly connected with the upper end of the clamping frame and is in sliding connection with the upper sliding groove, and the lower end of each lower shock absorber is fixedly connected with the upper surface of the base and is in sliding connection with the lower sliding groove.
Description: the two sides of the flat plate are clamped through the clamping device, so that the flat plate is ensured to enter the fixing frame to be in a horizontal state, an optimal test state is further achieved, the two sides of the flat plate are prevented from being bent due to no stress, and adverse effects are caused on test results.
Further, the upper shock absorber and the lower shock absorber comprise pneumatic rods, the fixed end of the pneumatic rod of the upper shock absorber is fixedly connected with the top of the clamping frame, the fixed end of the pneumatic rod of the lower shock absorber is fixedly connected with the upper surface of the base, the two telescopic ends of the pneumatic rods are fixedly connected with fixed shafts, two ends of the fixed shaft connected with the pneumatic rod of the upper shock absorber are slidably connected in the upper sliding groove, two ends of the fixed shaft connected with the pneumatic rod of the lower shock absorber are slidably connected in the lower sliding groove, and a roller is rotatably connected to the front side and the rear side of the fixed shaft.
Description: the upper shock absorber and the lower shock absorber clamp the flat plate between the upper shock absorber and the lower shock absorber, so that the flat plate enters the fixing frame to be in a horizontal state.
Further, the force sensor is installed between the fixing frame and the hydraulic actuator.
Description: the load applied by the aircraft tire obstacle crossing process is detected by the force sensor.
Further, the left side of the base is fixedly connected with a displacement detection frame, and an infrared displacement sensor for detecting the displacement of the flat plate is fixedly connected to the displacement detection frame.
Description: and detecting whether the flat plate is in a uniform motion state or not through the infrared displacement sensor so as to timely adjust the moving speed of the flat plate.
The beneficial effects of the invention are as follows:
the method comprises the steps of dividing high-speed obstacle crossing analysis of an aircraft into two stages, wherein the first stage obtains equivalent displacement of the wheel axle center of the low-speed obstacle crossing of an aircraft tire through a test, and the second stage inputs the equivalent displacement into an aircraft multi-body dynamics obstacle crossing analysis model to predict impact load born by the high-speed obstacle crossing of the aircraft tire;
the previous method for directly acting the shape of the obstacle on the center of the wheel shaft of the landing gear cannot consider the influence of deformation and energy absorption of the aircraft tire, so that the prediction error of the obstacle surmounting load is larger, the equivalent displacement of the wheel shaft center of the aircraft tire surmounting the obstacle is obtained by the prediction test method for the obstacle surmounting impact load of the aircraft tire, the accuracy of the obstacle surmounting load of the aircraft tire can be effectively improved, the clamping devices on two sides of the obstacle test system can enable the flat plate to enter the fixed frame to be in a horizontal state, the test error is reduced, and the prediction accuracy of the obstacle surmounting load of the aircraft is further improved.
Drawings
FIG. 1 is a schematic view of the overall structure of an obstacle testing system of the present invention;
FIG. 2 is a schematic view of the structure of the fixing frame and the clamping device of the present invention;
FIG. 3 is a right side view block diagram of the aircraft tire of the present invention;
FIG. 4 is a left side view of the clamping device;
FIG. 5 is a predicted test method of the present invention for the impact load of an aircraft tire surmounting an obstacle.
The device comprises a 1-base, a 2-fixing frame, a 3-tire mounting system, a 4-barrier mounting system, a 31-hydraulic actuator, a 32-sleeve, a 33-rotating shaft, a 34-aircraft tire, a 341-hub, a 342-tread, a 41-gear shaft, a 42-motor, a 43-flat plate, a 44-barrier, a 5-clamping device, a 51-clamping frame, a 52-upper shock absorber, a 53-lower shock absorber, a 54-upper sliding groove, a 55-lower sliding groove, a 56-pneumatic rod, a 57-fixed shaft, a 58-roller, a 6-force sensor, a 7-displacement detection frame and a 71-infrared displacement sensor.
Detailed Description
Example 1: as shown in fig. 1, the obstacle test system comprises a base 1, a fixing frame 2 is fixedly connected to the base 1, a tire mounting system 3 is arranged above the fixing frame 2, an obstacle mounting system 4 is arranged below the fixing frame 2, and a force sensor 6 is arranged between the fixing frame 2 and the tire mounting system 3.
As shown in fig. 2 and 3, the tire mounting system 3 includes a hydraulic actuator 31, a fixed end of the hydraulic actuator 31 is rigidly connected to the top of the fixing frame 2, a sleeve 32 is fixedly connected below a telescopic end of the hydraulic actuator 31, a rotating shaft 33 is rotatably connected to the sleeve 32, and two ends of the rotating shaft 33 are respectively and fixedly connected to an aircraft tire 34.
The aircraft tire 34 includes a hub 341, a tread 342 is wrapped around the hub 341, and the hub 341 is detachably connected to the rotating shaft 33.
The obstacle mounting system 4 comprises a plurality of gear shafts 41, the plurality of gear shafts 41 are connected to the fixing frame 2 in a parallel rotating mode, a motor 42 is arranged at the front end of one gear shaft 41, an output shaft of the motor 42 is in transmission connection with the gear shafts 41, a flat plate 43 is arranged above the plurality of gear shafts 41, the gear shafts 41 are in meshed transmission connection with the bottom of the flat plate 43, and an obstacle 44 is fixedly connected to the upper surface of the flat plate 43.
The force sensor 6 is mounted between the mount 2 and the hydraulic actuator 31.
The left side of the base 1 is fixedly connected with a displacement detection frame 7, and an infrared displacement sensor 71 for detecting the displacement of the flat plate 43 is fixedly connected to the displacement detection frame 7.
Example 2: in this embodiment, on the basis of embodiment 1, a clamping device 5 is added, as shown in fig. 4, two clamping devices 5 are respectively disposed on the left and right sides of the base 1, the clamping device 5 includes a clamping frame 51, an upper damper 52 is disposed above the clamping frame 51, a lower damper 53 is disposed below the clamping frame 51, two upper sliding grooves 54 are disposed on two sides above the clamping frame 51, two lower sliding grooves 55 are disposed on two sides below the clamping frame 51, the upper ends of the upper dampers 52 are fixedly connected with the upper ends of the clamping frame 51 and are slidably connected with the upper sliding grooves 54, and the lower ends of the lower dampers 53 are fixedly connected with the upper surface of the base 1 and are slidably connected with the lower sliding grooves 55.
The upper shock absorber 52 and the lower shock absorber 53 comprise pneumatic rods 56, the fixed end of the pneumatic rod 56 of the upper shock absorber 52 is fixedly connected with the top of the clamping frame 51, the fixed end of the pneumatic rod 56 of the lower shock absorber 53 is fixedly connected with the upper surface of the base 1, the telescopic ends of the two pneumatic rods 56 are fixedly connected with fixed shafts 57, two ends of the fixed shafts 57 connected with the pneumatic rod 56 of the upper shock absorber 52 are slidably connected in the upper sliding grooves 54, two ends of the fixed shafts 57 connected with the pneumatic rod 56 of the lower shock absorber 53 are slidably connected in the lower sliding grooves 55, and the front side and the rear side of the fixed shafts 57 are rotatably connected with rollers 58 respectively.
In this embodiment, the clamping device 5 clamps two sides of the flat plate 43, so as to ensure that the flat plate 43 enters the fixing frame 2 to be in a horizontal state, thereby achieving an optimal test state, and avoiding the two sides of the flat plate 43 from being bent due to no stress, thereby causing adverse effects on test results.
Example 3: as shown in fig. 5, this embodiment is based on the obstacle test system of embodiment 2, and describes a prediction test method for obstacle surmounting impact load of an aircraft tire, comprising the following steps:
s1, constructing a low-speed obstacle surmounting test system of the aircraft tire 34:
the aircraft tire 34 is arranged in an obstacle test system, the motor 42 drives the flat plate 43 to horizontally move, the flat plate 43 moves and then drives the aircraft tire 34 positioned above the flat plate 43 to roll under the action of friction force, the flat plate 43 moves at a uniform speed in the test process, and the movement of the flat plate 43 can be stopped after the aircraft tire 34 completely passes over an obstacle 44 on the flat plate 43;
s2, performing a low-speed obstacle surmounting test of the aircraft tire 34:
an obstacle 44 is fixed on the flat plate 43, the uniform motion state of the flat plate 43 is detected by an infrared displacement sensor 71 to ensure that the flat plate 43 is in the uniform motion state, and the impact load applied to the aircraft tire 34 when the aircraft tire passes over the obstacle 44 in a quasi-static state under the rated load is detected by a force sensor 6F(s) And calculate the equivalent displacement of the wheel axle center of the aircraft tire 34 over the obstacle 44 by equation (1),
Equivalent displacement of the wheel axle center of the aircraft tire 34 over the obstacle 44The calculation formula of (2) is as follows:
(1)
wherein,for the aircraft tire 34 to cross the obstacle 44 as a function of the rolling distance, +.>For the curve of the equivalent displacement of the wheel axis center as a function of the rolling distance when the aircraft tire 34 passes over the obstacle 44>Is the vertical stiffness of the aircraft tire 34;
s3, predicting the high-speed obstacle surmounting load:
equivalent displacement of the center of the wheel axle calculated in the step S2Inputting the high-speed obstacle-surmounting impact load prediction of the aircraft tire 34 into an aircraft multi-body dynamics analysis model;
the formula of the aircraft multi-body dynamics analysis model is as follows:
+m/>(2)
wherein,for the landing gear before obstacle crossing initial load +.>Predicting load for high speed obstacle surmounting impact of aircraft tire 34,>for vertical damping of the aircraft tire 34, m is the mass of the aircraft tire 34, +.>For the vertical equivalent speed of the axle center of the aircraft tire 34 over the obstacle 44, +.>For a vertical equivalent acceleration of the center of the wheel axis when the aircraft tire 34 passes over the obstacle 44,by->One derivation is performed to obtain ∈>By->And (3) conducting twice derivation.
The rated load range of the aircraft tire 34 is 10kN, and the moving speed v of the flat plate 43 is 1m/min.
Example 4: example 4 differs from example 3 in that the rated load range of the aircraft tire 34 in example 4 is 100kN, and the moving speed v of the flat plate 43 is 5m/min.
Example 5: example 5 differs from example 3 in that the rated load range of the aircraft tire 34 in example 4 is 500kN, and the moving speed v of the flat plate 43 is 9m/min.
The motor 42, the infrared displacement sensor 71, the force sensor 6, and the hydraulic actuator 31 used in the above embodiments are commercially available products, so long as the functions of the present invention can be implemented, and those skilled in the art can select and use them according to conventional knowledge, and are not particularly limited herein.
Claims (10)
1. The prediction test method for the obstacle surmounting impact load of the aircraft tire is characterized by comprising the following steps of:
s1, constructing a low-speed obstacle crossing test system of an aircraft tire (34):
the aircraft tire (34) is arranged in an obstacle test system, the motor (42) drives the flat plate (43) to horizontally move, the flat plate (43) is driven to roll under the action of friction force after moving, the flat plate (43) moves at a uniform speed in the test process, and the movement of the flat plate (43) can be stopped after the aircraft tire (34) completely passes over an obstacle (44) on the flat plate (43);
s2, performing a low-speed obstacle crossing test of the aircraft tire (34):
an obstacle (44) is fixed on the flat plate (43), the uniform motion state of the flat plate (43) is detected by an infrared displacement sensor (71) to ensure that the flat plate (43) is in the uniform motion state, and the impact load applied to the aircraft tire (34) when the aircraft tire passes over the obstacle (44) in a quasi-static state under the rated load is detected by a force sensor (6)F(s) And calculate the equivalent displacement of the wheel axle center of the aircraft tire (34) over the obstacle (44) by the formula (1),
Equivalent displacement of the wheel axle center of the aircraft tire (34) over an obstacle (44)The calculation formula of (2) is as follows:
(1)
wherein,for the aircraft tire (34) to cross an obstacle (44) as a function of the rolling distance +.>For the curve of the equivalent displacement of the wheel axis center as a function of the rolling distance when the aircraft tire (34) passes over an obstacle (44), +.>Is the vertical stiffness of the aircraft tire (34);
s3, predicting the high-speed obstacle surmounting load:
equivalent displacement of the center of the wheel axle calculated in the step S2Inputting the high-speed obstacle surmounting impact load prediction of the aircraft tire (34) into an aircraft multi-body dynamics analysis model;
the formula of the aircraft multi-body dynamics analysis model is as follows:
+m/>(2)
wherein,for the landing gear before obstacle crossing initial load +.>Predicting load for high-speed obstacle surmounting impact of aircraft tire (34), and (B)>For the vertical damping of an aircraft tire (34), m is the mass of the aircraft tire (34), -A>For the vertical equivalent speed of the axle centre when the aircraft tyre (34) passes over the obstacle (44), +.>For the vertical equivalent acceleration of the axle centre when the aircraft tyre (34) passes over an obstacle (44), +.>By->One derivation is performed to obtain ∈>By->And (3) conducting twice derivation.
2. An aircraft tire obstacle surmounting impact load prediction test method as claimed in claim 1, wherein the aircraft tire (34) has a rated load range of 10-500kN and the flat plate (43) has a moving speed v in the range of 0m/min < v < 10m/min.
3. The method for predicting the obstacle surmounting impact load of the aircraft tire according to claim 1, wherein the obstacle test system comprises a base (1), a fixing frame (2) is fixedly connected to the base (1), a tire mounting system (3) is arranged above the fixing frame (2), an obstacle mounting system (4) is arranged below the fixing frame (2), and a force sensor (6) is arranged between the fixing frame (2) and the tire mounting system (3).
4. A method of prediction testing for obstacle surmounting impact loads of aircraft tires according to claim 3, characterized in that the tire mounting system (3) comprises a hydraulic actuator (31), the fixed end of the hydraulic actuator (31) is rigidly connected with the top of the fixed frame (2), a sleeve (32) is fixedly connected below the telescopic end of the hydraulic actuator (31), a rotating shaft (33) is rotatably connected with the sleeve (32), and two ends of the rotating shaft (33) are respectively fixedly connected with an aircraft tire (34).
5. The method for predicting the obstacle surmounting impact load of an aircraft tire according to claim 4, wherein said aircraft tire (34) comprises a hub (341), said hub (341) being externally wrapped with a tread (342), said hub (341) being removably connected to said rotating shaft (33).
6. A method for predicting an obstacle surmounting impact load of an aircraft tire according to claim 3, wherein the obstacle mounting system (4) comprises a plurality of gear shafts (41), the plurality of gear shafts (41) are connected to the fixing frame (2) in a side-by-side rotating manner, a motor (42) is arranged at the front end of one gear shaft (41), an output shaft of the motor (42) is in transmission connection with the gear shaft (41), a flat plate (43) is arranged above the plurality of gear shafts (41), the gear shafts (41) are in meshed transmission connection with the bottom of the flat plate (43), and an obstacle (44) is fixedly connected to the upper surface of the flat plate (43).
7. A method for predicting an obstacle surmounting impact load of an aircraft tire according to claim 3, wherein a clamping device (5) is respectively arranged on the left side and the right side of the base (1), the clamping device (5) comprises a clamping frame (51), an upper shock absorber (52) is arranged above the clamping frame (51), a lower shock absorber (53) is arranged below the clamping frame (51), an upper sliding groove (54) is respectively arranged on the two sides above the clamping frame (51), a lower sliding groove (55) is respectively arranged on the two sides below the clamping frame (51), the upper end of the upper shock absorber (52) is fixedly connected with the upper end of the clamping frame (51) and is in sliding connection with the upper sliding groove (54), and the lower end of the lower shock absorber (53) is fixedly connected with the upper surface of the base (1) and is in sliding connection with the lower sliding groove (55).
8. The method for predicting the obstacle surmounting impact load of the aircraft tire according to claim 7, wherein the upper damper (52) and the lower damper (53) each comprise a pneumatic rod (56), the fixed ends of the pneumatic rods (56) of the upper damper (52) are fixedly connected with the top of the clamping frame (51), the fixed ends of the pneumatic rods (56) of the lower damper (53) are fixedly connected with the upper surface of the base (1), the telescopic ends of the two pneumatic rods (56) are fixedly connected with fixed shafts (57), two ends of the fixed shafts (57) connected with the pneumatic rods (56) of the upper damper (52) are slidably connected in the upper sliding groove (54), two ends of the fixed shafts (57) connected with the pneumatic rods (56) of the lower damper (53) are slidably connected in the lower sliding groove (55), and two front and rear sides of the fixed shafts (57) are rotatably connected with one roller (58).
9. A method of prediction testing for obstacle surmounting impact loads of aircraft tires according to claim 3, characterized in that the force sensor (6) is mounted between the mounting bracket (2) and the hydraulic actuator (31).
10. The prediction test method for the obstacle surmounting impact load of the aircraft tire according to claim 6, wherein a displacement detection frame (7) is fixedly connected to the left side of the base (1), and an infrared displacement sensor (71) for detecting the displacement of the flat plate (43) is fixedly connected to the displacement detection frame (7).
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