CN117073957A - Ship-borne aircraft load measurement and ship surface characteristic simulation device and method - Google Patents
Ship-borne aircraft load measurement and ship surface characteristic simulation device and method Download PDFInfo
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- CN117073957A CN117073957A CN202311323405.4A CN202311323405A CN117073957A CN 117073957 A CN117073957 A CN 117073957A CN 202311323405 A CN202311323405 A CN 202311323405A CN 117073957 A CN117073957 A CN 117073957A
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- 238000005259 measurement Methods 0.000 title claims abstract description 33
- 238000004088 simulation Methods 0.000 title claims abstract description 32
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/08—Shock-testing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The invention discloses a carrier-based aircraft load measurement and carrier surface characteristic simulation device and method. The simulation method comprises the following steps: s1, preparing a test; s2, drop test: including leveling or tilting or obstacle landing; s3, leveling the ship surface for secondary earthquake falling. The simulation device can directly simulate the direction angle and the motion characteristic of the aircraft carrier deck when the carrier-based aircraft is on the ship, simulate the boundary condition more truly, and have higher test and measurement precision.
Description
Technical Field
The invention relates to the technical field of aircraft tests, in particular to a device and a method for measuring the load of a carrier-based aircraft and simulating the characteristics of the carrier surface.
Background
When the carrier-based aircraft carries on the carrier surface, the carrier surface impact load is critical to the structural design evaluation, the weight reduction optimization scheme design and the like. The ship surface impact load is usually measured by a ground load test platform through ground tests performed by a laboratory in the development stage.
The ground test is only aimed at the ground load test condition of the landing gear of the normal landing ship. However, for special scenes such as yaw landing, blocking hooking landing and striking, the course speed cannot be simulated by adopting a wheel steering mode, the traditional landing gear landing test method cannot meet the requirement of course speed simulation, and the simulation is needed by a method of installing a rotary flywheel below a test piece.
At present, no ship-borne aircraft load measurement and ship surface characteristic simulation device of the type exists in China.
Disclosure of Invention
Aiming at the problems, the invention provides a device and a method for measuring the load of a carrier-based aircraft and simulating the characteristics of the carrier surface.
The technical scheme of the invention is as follows:
the device comprises a first rotary flywheel, a second rotary flywheel and a balancing weight, wherein the first rotary flywheel and the second rotary flywheel are synchronously driven to rotate by a driving motor, a sliding block is fixedly connected below the driving motor, the bottom of the sliding block is connected with a sliding groove in a sliding manner, and the front end of the sliding block is provided with a push rod motor for driving the sliding block to slide along the sliding groove;
the side wall of the first rotary flywheel is sequentially fixed with a first force measuring part, a second force measuring part and a third force measuring part, a plurality of first force measuring sensors which are closely arranged are arranged on the inner wall of the first force measuring part, and the first force measuring sensors are attached to the side wall of the first rotary flywheel;
the inner wall of the second force measuring part is provided with a plurality of second force measuring sensors which are closely arranged, and the second force measuring sensors are attached to the side wall of the first rotary flywheel;
the inner wall of the third force measuring part is provided with a plurality of third force measuring sensors which are closely arranged, and the third force measuring sensors are attached to the side wall of the first rotary flywheel;
a circle of fourth force measuring parts are fixedly sleeved on the side wall of the second rotary flywheel, a plurality of fourth force measuring sensors which are closely arranged are arranged on the inner wall of each fourth force measuring part, and the fourth force measuring sensors are attached to the side wall of the second rotary flywheel;
the top of the balancing weight is connected with the top of the laboratory through an electrohydraulic push rod, a blocking hook test piece is hinged to the bottom of the rear side of the balancing weight, and the tail end hook head of the blocking hook test piece is located right above the initial position of the first rotary flywheel.
Further, the output shaft of the driving motor is fixedly connected with the center of the rear side surface of the first rotary flywheel, a connecting rod is arranged at the center of the front side surface of the first rotary flywheel and fixedly connected with the center of the rear side surface of the second rotary flywheel, a rotating rod is arranged at the center of the front side surface of the second rotary flywheel, a fixed block is arranged at the front side of the top surface of the sliding block, the rotating rod is rotationally connected with the rear side wall of the fixed block, and the rear side of the top surface of the sliding block is fixedly connected with the bottom of the driving motor through the fixed rod.
Description: the first rotary flywheel and the second rotary flywheel can synchronously rotate through the arrangement of the connecting rod and the rotating rod, so that the aim of rapid adjustment is fulfilled, and the second rotary flywheel can reach a set speed immediately after moving.
Further, the first force measuring part is a hollow -type ring with the radian of pi/4-pi/3, the outer ring radius of the first force measuring part is 1.1-1.2 times of the radius of the first rotary flywheel, the second force measuring part is a hollow -type ring with the radian of pi/2-2 pi/3, the outer ring radius of the second force measuring part is 0.5-0.8 times of the radius of the first rotary flywheel, the third force measuring part is a hollow -type ring with the radian of 2 pi/3~3 pi/4, the outer ring radius of the third force measuring part is 2-2.5 times of the radius of the first rotary flywheel, the fourth force measuring part is a hollow -type ring, the outer ring radius of the fourth force measuring part is 1.1-1.2 times of the radius of the second rotary flywheel, and the outer ring radius of the first force measuring part is the same as the outer ring radius of the fourth force measuring part.
Description: since the situation that the flat warship surface is collided is most common, the contact stress situation of the flat warship surface can be simulated by setting the outer ring radiuses of the first force measuring part and the fourth force measuring part, and the situation can be more similar to the real situation.
Further, a plurality of grooves are formed in the outer wall of the third force measuring part.
Description: the situation that the blocking hook impacts the ship surface obstacle can be simulated through the arrangement of the grooves.
Further, a plurality of threaded holes are arranged at equal intervals on the edges of the front side and the rear side of the first rotary flywheel and the second rotary flywheel, the equal interval of both sides inward flange is equipped with a plurality of threaded rod around first dynamometry portion, second dynamometry portion, third dynamometry portion, fourth dynamometry portion, the threaded rod runs through the screw hole and with screw hole threaded connection, threaded rod both ends all are equipped with the nut.
Description: the connection between each force measuring part and the rotary flywheel can be ensured by the threaded rod connection mode, so that the stability of each force measuring sensor is enhanced.
Further, the outer side surface of the first rotary flywheel is provided with an encoder corresponding to the positions of the first force measuring part, the second force measuring part and the third force measuring part, and the outer wall surfaces of the first force measuring part, the second force measuring part, the third force measuring part and the fourth force measuring part are coated with aircraft carrier deck coating materials.
Description: the position of the falling point of the blocking hook can be accurately controlled through the arrangement of the encoder, and the force measuring part is closer to the actual situation through coating the aircraft carrier deck coating material.
The invention also provides a carrier-based aircraft load measurement and carrier-based characteristic simulation method, which is based on the carrier-based aircraft load measurement and carrier-based characteristic simulation device and comprises the following steps:
s1, test preparation: resetting the sliding block to the forefront end of the sliding groove through the push rod motor, enabling the arresting hook test piece to be positioned right above the first rotary flywheel, and lifting the balancing weight to a specified height through the electro-hydraulic push rod;
s2, drop test: including leveling or tilting or obstacle landing;
wherein, level warship surface shakes off: starting a driving motor to drive a first rotary flywheel and a second rotary flywheel to synchronously rotate, sweeping the outer side surface of the first rotary flywheel through an external controller, determining the time when a first force measuring part passes over the first rotary flywheel, and then calculating the falling time of a blocking hook test piece through the initial height of the tail end hook head of the blocking hook test piece from the position right above the first rotary flywheel and the instant speed when the blocking hook test piece falls over the first rotary flywheel, so that the blocking hook test piece can be ensured to accurately collide onto the first force measuring part after falling, the collision load is measured through the first force measuring sensor, and the stress load when the blocking hook of a carrier-based aircraft is contacted and collided with a flat ship surface at first after falling is simulated;
inclined ship surface landing earthquake: starting a driving motor to drive a first rotary flywheel and a second rotary flywheel to synchronously rotate, sweeping the outer side surface of the first rotary flywheel through an external controller, determining the time when a second force measuring part passes through the position right above the first rotary flywheel, and then calculating the falling time of the arresting hook test piece through the initial height of the tail end hook head of the arresting hook test piece from the position right above the first rotary flywheel and the instant speed when the arresting hook test piece falls to the position right above the first rotary flywheel, so as to ensure that the arresting hook test piece accurately collides against the second force measuring part after falling, measuring the collision load through a second force measuring sensor, and simulating the stress load when the arresting hook of the carrier aircraft contacts and collides with an inclined surface at first after falling;
obstacle warship surface landing earthquake: starting a driving motor to drive a first rotary flywheel and a second rotary flywheel to synchronously rotate, sweeping the outer side surface of the first rotary flywheel through an external controller, determining the time when a third force measuring part passes through the position right above the first rotary flywheel, and then calculating the falling time of the arresting hook test piece through the initial height of the tail end hook head of the arresting hook test piece from the position right above the first rotary flywheel and the instant speed when the arresting hook test piece falls to the position right above the first rotary flywheel, so as to ensure that the arresting hook test piece accurately collides against the third force measuring part after falling, measuring the collision load through a third force measuring sensor, and simulating the stress load when the arresting hook of the carrier aircraft contacts and collides with an obstacle after falling;
s3, leveling the ship surface for secondary earthquake falling: when the arresting hook test piece collides with the first force measuring part, the second force measuring part or the third force measuring part and then bounces, the arresting hook test piece moves upwards around the hinging point of the arresting hook test piece and the balancing weight and then falls down, at the moment, the push rod motor is started to drive the sliding block to slide along the sliding groove, the second rotating flywheel still in rotation moves to the position right below the arresting hook test piece, the arresting hook test piece falls down and collides with the fourth force measuring part, the impact load is measured through the fourth force measuring sensor, and the stress load when the arresting hook of the carrier-based aircraft contacts and collides with the plane carrier surface after the arresting hook of the carrier-based aircraft falls down for the second time is simulated.
Further, in the step S2, the driving motor is started to drive the first rotary flywheel and the second rotary flywheel to synchronously rotate at a linear speed of 260-300 km/h, and the instantaneous speed of the blocking hook test piece when falling to the position right above the first rotary flywheel is 6-8 m/S.
Description: the collision speed of the blocking hook during landing of the real carrier-based aircraft can be simulated by adjusting the linear speed of the synchronous rotation of the first rotary flywheel and the second rotary flywheel, and the instantaneous speed of the blocking hook test piece falling to the position right above the first rotary flywheel is adjusted in a matched mode, so that force balance and speed balance are realized.
Further, in the step S3, the push rod motor is turned on to drive the slide block to slide along the chute, and the rotation speed of the driving motor is adjusted to drive the first rotary flywheel and the second rotary flywheel to synchronously rotate at a linear speed of 240-260 km/h.
Description: the linear speed of the second rotary flywheel is adjusted so as to truly simulate the speed of secondary collision after the blocking hook bounces when the carrier-borne aircraft lands on the ship.
The beneficial effects of the invention are as follows:
(1) The carrier-based aircraft load measurement and carrier surface characteristic simulation device can directly simulate the direction angle and the movement characteristic of the aircraft carrier deck when the carrier-based aircraft is on a carrier, the simulation boundary condition is more true, the collision simulation is mainly carried out by installing the force measuring part on the rotating flywheel rotating at high speed and matching with the free falling of the blocking hook test piece, the condition that the collision load of the conventional high-speed rotating body needs to be measured and deduced through the strain gauge is overcome, the device can be used for directly testing, theoretical deduction is not needed through other formulas, and the device has higher test and measurement precision;
(2) According to the carrier-based aircraft load measurement and carrier-based characteristic simulation device, the situation of secondary collision after the blocking hook bounces off when the carrier-based aircraft lands on the ship can be simulated by arranging the two rotary flywheels and matching with the corresponding force measuring parts, and the aim of quick adjustment can be achieved through the sliding blocks and the push rod, so that the second rotary flywheels can reach the set speed immediately after moving;
(3) According to the carrier-based aircraft load measurement and carrier surface characteristic simulation device, different carrier landing conditions can be simulated through different force measuring parts, as the collision condition of a flat carrier surface is most common, the contact force bearing condition of the flat carrier surface can be simulated through setting the outer ring radiuses of the first force measuring part and the fourth force measuring part, the real condition can be more similar, the second force measuring part is set to be a small-radius large-radian ring and used for simulating the vibration falling condition of an inclined carrier surface, the blocking hook is simulated through the groove arranged on the third force measuring part, the tight and firm connection between each force measuring part and the rotary flywheel can be ensured through the screw connection mode, and the stability of each force measuring sensor is enhanced;
(4) According to the carrier-based aircraft load measurement and carrier surface characteristic simulation method, the linear speed of synchronous rotation of the first rotary flywheel and the second rotary flywheel is adjusted, so that the collision speed of the blocking hook during landing of a real carrier-based aircraft can be simulated, and the instantaneous speed of the blocking hook test piece falling to the position right above the first rotary flywheel is adjusted in a matching manner, so that force balance and speed balance are realized; the linear speed of the second rotary flywheel is adjusted so as to truly simulate the speed of secondary collision after the blocking hook bounces when the carrier-borne aircraft lands on the ship.
Drawings
FIG. 1 is a schematic diagram of the overall structure of a carrier-based aircraft load measurement and carrier-based characteristic simulation device;
FIG. 2 is a schematic diagram of the structure of each force measuring part on the first rotary flywheel of the carrier-based aircraft load measurement and carrier-based characteristic simulation device;
FIG. 3 is a front view of a test piece of a blocking hook in the device for measuring the load of a carrier-based aircraft and simulating the characteristics of the carrier surface, which is positioned at an initial position;
FIG. 4 is a schematic diagram of a first force measuring part of the carrier-based aircraft load measurement and carrier-based characteristic simulation device of the invention;
FIG. 5 is a schematic diagram of a second force measuring section of the carrier-based aircraft load measurement and carrier-based characteristic simulation device of the present invention;
FIG. 6 is a schematic diagram of a third force measuring section of the carrier-based aircraft load measurement and carrier-based characteristic simulation device of the present invention;
FIG. 7 is a cross-sectional view of the junction of the top of the second rotating flywheel and the fourth force measuring section of the carrier-based aircraft load measurement and carrier-based performance simulator of the present invention;
FIG. 8 is a top view of the carrier-based aircraft load measurement and carrier-surface characteristic simulation apparatus of the present invention after movement of a second rotating flywheel;
FIG. 9 is a flow chart of a method for measuring the load of a carrier-based aircraft and simulating the characteristics of the carrier surface according to the invention;
FIG. 10 is a graph of the load of two impacts versus time measured in the experimental example of the present invention.
The device comprises a first rotary flywheel, a 11-connecting rod, a 12-threaded hole, a 2-second rotary flywheel, a 21-rotating rod, a 3-balancing weight, a 31-electrohydraulic push rod, a 32-blocking hook test piece, a 4-driving motor, a 5-sliding block, a 51-sliding groove, a 52-push rod motor, a 53-fixed block, a 54-fixed rod, a 6-first force measuring part, a 61-first force measuring sensor, a 62-threaded rod, a 63-nut, a 7-second force measuring part, a 71-second force measuring sensor, a 8-third force measuring part, a 81-third force measuring sensor, a 82-groove, a 9-fourth force measuring part and a 91-fourth force measuring sensor.
Detailed Description
Example 1: as shown in fig. 1 and 3, the carrier-based aircraft load measurement and carrier surface characteristic simulation device comprises a first rotary flywheel 1, a second rotary flywheel 2 and a balancing weight 3, wherein the first rotary flywheel 1 and the second rotary flywheel 2 are synchronously driven to rotate by a driving motor 4, a sliding block 5 is fixedly connected below the driving motor 4, the bottom of the sliding block 5 is slidingly connected with a sliding groove 51, the front end of the sliding block 5 is provided with a push rod motor 52 for driving the sliding block 5 to slide along the sliding groove 51, the push rod motor 52 is a commercially available push rod motor, the driving motor 4 is a commercially available gear reduction motor, an output shaft of the driving motor 4 is fixedly connected with the center of the rear side surface of the first rotary flywheel 1, a connecting rod 11 is arranged at the center of the front side surface of the first rotary flywheel 1 and fixedly connected with the center of the rear side surface of the second rotary flywheel 2, a rotating rod 21 is arranged at the center of the front side surface of the second rotary flywheel 2, a fixed block 53 is arranged at the front side of the top surface of the sliding block 5, the rotating rod 21 is rotationally connected with the rear side wall of the fixed block 53, and the rear side of the top surface of the sliding block 5 is fixedly connected with the bottom of the driving motor 4 by the fixed rod 54;
as shown in fig. 1, 2 and 4, a first force measuring part 6, a second force measuring part 7 and a third force measuring part 8 are sequentially fixed on the side wall of the first rotary flywheel 1, a plurality of first force measuring sensors 61 are arranged on the inner wall of the first force measuring part 6, the first force measuring sensors 61 are attached to the side wall of the first rotary flywheel 1, the first force measuring part 6 is a hollow -type circular ring with the radian of pi/4, and the radius of the outer ring of the first force measuring part 6 is 1.1 times that of the first rotary flywheel 1;
as shown in fig. 1, 2 and 5, the inner wall of the second force measuring part 7 is provided with a plurality of second force measuring sensors 71 which are closely arranged, the second force measuring sensors 71 are attached to the side wall of the first rotary flywheel 1, the second force measuring part 7 is a hollow circular ring with the radian of pi/2, and the outer ring radius of the second force measuring part 7 is 0.6 times of the radius of the first rotary flywheel 1;
as shown in fig. 1, 2 and 6, the inner wall of the third force measuring part 8 is provided with a plurality of third force measuring sensors 81 which are closely arranged, the third force measuring sensors 81 are attached to the side wall of the first rotary flywheel 1, the third force measuring part 8 is a hollow type circular ring with the radian of 2 pi/3, the outer ring radius of the third force measuring part 8 is 2.2 times that of the first rotary flywheel 1, and the outer wall of the third force measuring part 8 is provided with a plurality of grooves 82;
as shown in fig. 1, 2 and 7, a circle of fourth force measuring part 9 is fixedly sleeved on the side wall of the second rotary flywheel 2, a plurality of fourth force measuring sensors 91 which are closely arranged are arranged on the inner wall of the fourth force measuring part 9, the fourth force measuring sensors 91 are attached to the side wall of the second rotary flywheel 2, the fourth force measuring part 9 is a hollow circular ring, the outer ring radius of the fourth force measuring part 9 is 1.1 times of the radius of the second rotary flywheel 2, and the outer ring radius of the first force measuring part 6 is the same as the outer ring radius of the fourth force measuring part 9;
as shown in fig. 2 and 7, a plurality of threaded holes 12 are formed in the front and rear side edges of the first rotary flywheel 1 and the second rotary flywheel 2 at equal intervals, a plurality of threaded rods 62 are formed in the front and rear side inner edges of the first force measuring part 6, the second force measuring part 7, the third force measuring part 8 and the fourth force measuring part 9 at equal intervals, the threaded rods 62 penetrate through the threaded holes 12 and are in threaded connection with the threaded holes 12, and nuts 63 are arranged at two ends of the threaded rods 62;
as shown in fig. 3, the top of the balancing weight 3 is connected with the top of a laboratory through an electrohydraulic push rod 31, a blocking hook test piece 32 is hinged to the bottom of the rear side of the balancing weight 3, the tail end hook head of the blocking hook test piece 32 is located right above the initial position of the first rotary flywheel 1, encoders are arranged on the outer side face of the first rotary flywheel 1 and correspond to the positions of the first force measuring part 6, the second force measuring part 7 and the third force measuring part 8, the encoders are multi-circle absolute value encoders, LINDE IHA-608 type encoders are selected, the power supply voltage is 24V, the absolute precision is 25, an interface SSI, a shaft diameter D12 and the outer wall surfaces of the first force measuring part 6, the second force measuring part 7, the third force measuring part 8 and the fourth force measuring part 9 are all coated with aircraft carrier deck coating materials which are commonly used in the prior art.
Example 2: this embodiment differs from embodiment 1 in that:
the outer ring radius of the second force measuring part 7 is 0.5 times of the radius of the first rotary flywheel 1; the outer ring radius of the third force measuring part 8 is 2 times the radius of the first rotary flywheel 1.
Example 3: this embodiment differs from embodiment 1 in that:
the first force measuring part 6 is a hollow circular ring with the radian of pi/3, and the radius of the outer ring of the first force measuring part 6 is 1.2 times of the radius of the first rotary flywheel 1; the second force measuring part 7 is a hollow circular ring with the radian of 2 pi/3, and the outer ring radius of the second force measuring part 7 is 0.8 times of the radius of the first rotary flywheel 1; the third force measuring part 8 is a hollow circular ring with the radian of 3 pi/4, and the outer ring radius of the third force measuring part 8 is 2.5 times of the radius of the first rotary flywheel 1; the outer ring radius of the fourth force measuring part 9 is 1.2 times the radius of the second rotary flywheel 2.
Example 4: the embodiment describes a method for measuring the load of a carrier-based aircraft and simulating the characteristics of the carrier-based aircraft, which is based on the device for measuring the load of the carrier-based aircraft and simulating the characteristics of the carrier-based aircraft in the embodiment 1, as shown in fig. 9, and comprises the following steps:
s1, test preparation: the sliding block 5 is reset to the forefront end of the sliding groove 51 through the push rod motor 52, the arresting hook test piece 32 is positioned right above the first rotary flywheel 1, and the balancing weight 3 is lifted to a specified height through the electrohydraulic push rod 31;
s2, drop test:
leveling landing of the ship surface: starting a driving motor 4 to drive a first rotary flywheel 1 and a second rotary flywheel 2 to synchronously rotate, sweeping the outer side surface of the first rotary flywheel 1 through an external controller, determining the time when a first force measuring part 6 passes through the position right above the first rotary flywheel 1, calculating the falling time of a blocking hook test piece 32 through the initial height of the tail end hook head of the blocking hook test piece 32 from the position right above the first rotary flywheel 1 and the instant speed when the blocking hook test piece 32 falls to the position right above the first rotary flywheel 1, further ensuring that the blocking hook test piece 32 accurately collides with the first force measuring part 6 after falling, measuring the collision load through a first force measuring sensor 61, and simulating the stress load when the blocking hook of a carrier aircraft contacts with a flat carrier surface at first after falling; starting a driving motor 4 to drive a first rotary flywheel 1 and a second rotary flywheel 2 to synchronously rotate at a linear speed of 280km/h, wherein the instantaneous speed of the blocking hook test piece 32 falling to the position right above the first rotary flywheel 1 is 7m/s;
s3, leveling the ship surface for secondary earthquake falling:
when the arresting hook test piece 32 collides with the first force measuring part 6 and then bounces, the arresting hook test piece 32 moves upwards around the hinge point of the arresting hook test piece and the balancing weight 3 and falls down, at the moment, the push rod motor 52 is started to drive the sliding block 5 to slide along the sliding groove 51, the second rotating flywheel 2 still in rotation is moved to the position right below the arresting hook test piece 32, the arresting hook test piece 32 collides with the fourth force measuring part 9 after falling down, the fourth force measuring sensor 91 is used for measuring the collision load, the force load when the arresting hook of the carrier aircraft contacts with the flat carrier after falling down for the second time is simulated, the push rod motor 52 is started to drive the sliding block 5 to slide along the sliding groove 51, and meanwhile, the rotating speed of the driving motor 4 is adjusted to drive the first rotating flywheel 1 and the second rotating flywheel 2 to synchronously rotate at the linear speed of 250km/h.
Example 5: this embodiment differs from embodiment 4 in that:
the drop test in the step S2 is that the inclined ship surface drops: starting a driving motor 4 to drive a first rotary flywheel 1 and a second rotary flywheel 2 to synchronously rotate, sweeping the outer side surface of the first rotary flywheel 1 through an external controller, determining the time when a second force measuring part 7 passes through the position right above the first rotary flywheel 1, then starting the driving motor 4 to drive the first rotary flywheel 1 and the second rotary flywheel 2 to synchronously rotate through the initial height of the tail end hook head of the blocking hook test piece 32 from the position right above the first rotary flywheel 1 and the instantaneous speed when the blocking hook test piece 32 falls to the position right above the first rotary flywheel 1 so as to calculate the falling time of the blocking hook test piece 32, further ensuring that the blocking hook test piece 32 accurately collides against the second force measuring part 7 after falling, measuring the collision load through a second force measuring sensor 71, simulating the stress load when the blocking hook of a ship aircraft contacts and collides with an inclined ship surface at first after falling, and starting the driving motor 4 to drive the linear speed when the blocking hook test piece 32 falls to the position right above the first rotary flywheel 1 to synchronously rotate to be 260 km/s, wherein the instantaneous speed when the blocking hook test piece 32 falls to the position right above the first rotary flywheel 1 is 6m/s;
in step S3, when the arresting hook test piece 32 collides with the second force measuring portion 7 and then bounces, the push rod motor 52 is started to drive the slide block 5 to slide along the slide groove 51, and meanwhile, the rotation speed of the driving motor 4 is adjusted to drive the first rotary flywheel 1 and the second rotary flywheel 2 to synchronously rotate at a linear speed of 240km/h.
Example 6: this embodiment differs from embodiment 4 in that:
the drop test in the step S2 is that the ship surface of the obstacle drops to the earthquake: starting a driving motor 4 to drive a first rotary flywheel 1 and a second rotary flywheel 2 to synchronously rotate, sweeping the outer side surface of the first rotary flywheel 1 through an external controller, determining the time when a third force measuring part 8 passes through the position right above the first rotary flywheel 1, then calculating the falling time of the blocking hook test piece 32 through the initial height of the tail end hook head of the blocking hook test piece 32 from the position right above the first rotary flywheel 1 and the instantaneous speed when the blocking hook test piece 32 falls to the position right above the first rotary flywheel 1, further ensuring that the blocking hook test piece 32 accurately collides against the third force measuring part 8 after falling, measuring the collision load through a third force measuring sensor 81, simulating the forced load when the blocking hook of the carrier aircraft contacts and collides with a carrier obstacle at first after falling, and starting the driving motor 4 to drive the linear speed of the first rotary flywheel 1 and the second rotary flywheel 2 to synchronously rotate to be 300km/h, wherein the instantaneous speed when the blocking hook test piece 32 falls to the position right above the first rotary flywheel 1 is 8m/s;
in step S3, when the arresting hook test piece 32 collides with the third force measuring portion 8 and then bounces, the push rod motor 52 is started to drive the slide block 5 to slide along the slide groove 51, and meanwhile, the rotation speed of the driving motor 4 is adjusted to drive the first rotary flywheel 1 and the second rotary flywheel 2 to synchronously rotate at a linear speed of 260km/h.
Working principle: the working principle of the simulation device of the present invention will be further described below in connection with the simulation method of the present invention.
When in use, when step S2 is carried out, the balancing weight 3 drives the arresting hook test piece 32 to do free falling motion, after the hook head of the arresting hook test piece 32 touches any force measuring part on the first rotary flywheel 1, the balancing weight 3 is immediately braked under the action of the electrohydraulic push rod 31, so that the balancing weight 3 stops falling, meanwhile, the arresting hook test piece 32 is sprung upwards, rotates around the hinging point of the arresting hook test piece 32 and the balancing weight 3 and falls, at the moment, the push rod motor 52 is started to drive the sliding block 5 to slide along the sliding groove 51, the second rotary flywheel 2 still in rotation is moved to be right below the arresting hook test piece 32, the arresting hook test piece 32 falls and collides with the fourth force measuring part 9, and the impact load is measured through the fourth force measuring sensor 91, as shown in fig. 8;
if the vibration of the flat carrier surface is carried out, the blocking hook firstly impacts the flat carrier deck surface and then impacts the flat carrier deck surface again;
if the inclined carrier surface is subjected to the earthquake, the blocking hook firstly impacts the inclined carrier deck surface, then impacts the flat carrier deck surface again, and when the impacted second force measuring part 7 is positioned lower, the corresponding simulated carrier deck surface inclination angle is larger;
if the obstacle warship surface is shocked, the blocking hook firstly impacts an obstacle on the aircraft carrier deck warship surface, such as a lampshade and the like, and then impacts the flat aircraft carrier deck warship surface again; the three conditions are the most frequently occurring conditions, and the true stress condition of the arresting hook can be restored to the greatest extent.
Experimental example: in the following analysis of experimental results after the experimental results of the simulation devices and the simulation methods according to embodiments 1 and 5 of the present invention, the simulated aircraft carrier deck surface inclination angle is 5 to 15 °, as shown in fig. 10, the unit of the vertical impact load is MPa, and the unit of the horizontal time is ms, it can be seen that when the blocking hook test piece 32 impacts the second force measuring portion 7 for the first time, the second force measuring sensor 71 collects a stress signal, which is a first peak, and then oscillates during the continuous rotation of the first rotary flywheel 1, and oscillates during the continuous rotation of the second force measuring portion 7, so that a second peak is shown in fig. 10, the arc three-way force sensor can have a stress less than the strength limit of the material under the combined force of fz=300 KN, fx=fy=150 KN, and has a sufficient safety factor 1400/454=3.08, and can be used under the full range (fz=300 KN, fx=fy=150 KN); when the arresting hook test piece 32 falls and impacts the fourth force measuring part 9, another stress signal is collected through the fourth force measuring sensor 91, and then the two groups of stress signals are compared.
Claims (9)
1. The device for measuring the load and simulating the ship surface characteristics of the carrier-based aircraft is characterized by comprising a first rotary flywheel (1), a second rotary flywheel (2) and a balancing weight (3), wherein the first rotary flywheel (1) and the second rotary flywheel (2) are synchronously driven to rotate through a driving motor (4), a sliding block (5) is fixedly connected below the driving motor (4), a sliding groove (51) is slidably connected at the bottom of the sliding block (5), and a push rod motor (52) for driving the sliding block (5) to slide along the sliding groove (51) is arranged at the front end of the sliding block;
the side wall of the first rotary flywheel (1) is sequentially fixed with a first force measuring part (6), a second force measuring part (7) and a third force measuring part (8), a plurality of first force measuring sensors (61) which are closely arranged are arranged on the inner wall of the first force measuring part (6), and the first force measuring sensors (61) are attached to the side wall of the first rotary flywheel (1);
the inner wall of the second force measuring part (7) is provided with a plurality of second force measuring sensors (71) which are closely arranged, and the second force measuring sensors (71) are attached to the side wall of the first rotary flywheel (1);
the inner wall of the third force measuring part (8) is provided with a plurality of third force measuring sensors (81) which are closely arranged, and the third force measuring sensors (81) are attached to the side wall of the first rotary flywheel (1);
a circle of fourth force measuring parts (9) are fixedly sleeved on the side wall of the second rotary flywheel (2), a plurality of fourth force measuring sensors (91) which are closely arranged are arranged on the inner wall of each fourth force measuring part (9), and the fourth force measuring sensors (91) are attached to the side wall of the second rotary flywheel (2);
the top of the balancing weight (3) is connected with the top of the laboratory through an electrohydraulic push rod (31), a blocking hook test piece (32) is hinged to the bottom of the rear side of the balancing weight (3), and the tail end hook head of the blocking hook test piece (32) is located right above the initial position of the first rotary flywheel (1).
2. The ship-borne aircraft load measurement and ship surface characteristic simulation device according to claim 1, wherein an output shaft of the driving motor (4) is fixedly connected with the center of the rear side surface of the first rotary flywheel (1), a connecting rod (11) is arranged at the center of the front side surface of the first rotary flywheel (1), the connecting rod (11) is fixedly connected with the center of the rear side surface of the second rotary flywheel (2), a rotating rod (21) is arranged at the center of the front side surface of the second rotary flywheel (2), a fixed block (53) is arranged at the front side of the top surface of the sliding block (5), the rotating rod (21) is rotatably connected with the rear side wall of the fixed block (53), and the rear side of the top surface of the sliding block (5) is fixedly connected with the bottom of the driving motor (4) through a fixed rod (54).
3. The ship-borne aircraft load measurement and ship surface characteristic simulation device according to claim 1, wherein the first force measurement portion (6) is a hollow -type ring with a radian of pi/4-pi/3, the outer ring radius of the first force measurement portion (6) is 1.1-1.2 times of the radius of the first rotary flywheel (1), the second force measurement portion (7) is a hollow -type ring with a radian of pi/2-2 pi/3, the outer ring radius of the second force measurement portion (7) is 0.5-0.8 times of the radius of the first rotary flywheel (1), the third force measurement portion (8) is a hollow -type ring with a radian of 2 pi/3~3 pi/4, the outer ring radius of the third force measurement portion (8) is 2-2.5 times of the radius of the first rotary flywheel (1), the fourth force measurement portion (9) is a hollow -type ring, and the outer ring radius of the fourth force measurement portion (9) is the same as the outer ring radius of the first rotary flywheel (1.2-2).
4. The ship-borne aircraft load measurement and ship surface characteristic simulation device according to claim 1, wherein a plurality of grooves (82) are formed in the outer wall of the third force measuring part (8).
5. The ship-borne aircraft load measurement and ship surface characteristic simulation device according to claim 1, wherein a plurality of threaded holes (12) are formed in the edges of the front side and the rear side of the first rotary flywheel (1) and the edges of the second rotary flywheel (2) at equal intervals, a plurality of threaded rods (62) are formed in the inner edges of the front side and the rear side of the first force measuring part (6), the inner edges of the second force measuring part (7), the inner edges of the third force measuring part (8) and the inner edges of the fourth force measuring part (9) at equal intervals, and the threaded rods (62) penetrate through the threaded holes (12) and are in threaded connection with the threaded holes (12), and nuts (63) are arranged at two ends of the threaded rods (62).
6. The ship-borne aircraft load measurement and ship surface characteristic simulation device according to claim 1, wherein encoders are arranged on the outer side surfaces of the first rotary flywheel (1) corresponding to the positions of the first force measuring part (6), the second force measuring part (7) and the third force measuring part (8), and the outer wall surfaces of the first force measuring part (6), the second force measuring part (7), the third force measuring part (8) and the fourth force measuring part (9) are coated with aircraft carrier deck coating materials.
7. A method for measuring the load of a carrier-based aircraft and simulating the characteristics of the carrier-based aircraft, based on the device for measuring the load of the carrier-based aircraft and simulating the characteristics of the carrier-based aircraft according to any one of claims 1 to 6, comprising the following steps:
s1, test preparation: the sliding block (5) is reset to the forefront end of the sliding groove (51) through the push rod motor (52), the blocking hook test piece (32) is positioned right above the first rotary flywheel (1), and the balancing weight (3) is lifted to a specified height through the electro-hydraulic push rod (31);
s2, drop test: including leveling or tilting or obstacle landing;
wherein, level warship surface shakes off: starting a driving motor (4) to drive a first rotary flywheel (1) and a second rotary flywheel (2) to synchronously rotate, sweeping the outer side surface of the first rotary flywheel (1) through an external controller, determining the time when a first force measuring part (6) passes through the position right above the first rotary flywheel (1), and then calculating the falling time of the blocking hook test piece (32) through the initial height of the tail end hook head of the blocking hook test piece (32) from the position right above the first rotary flywheel (1) and the instant speed when the blocking hook test piece (32) falls to the position right above the first rotary flywheel (1), so as to ensure that the blocking hook test piece (32) accurately collides against the first force measuring part (6), measuring the collision load through a first force measuring sensor (61), and simulating the stress load when the blocking hook of the carrier aircraft collides with a flat ship surface at first after falling;
inclined ship surface landing earthquake: starting a driving motor (4) to drive a first rotary flywheel (1) and a second rotary flywheel (2) to synchronously rotate, sweeping the outer side surface of the first rotary flywheel (1) through an external controller, determining the time when a second force measuring part (7) passes through the position right above the first rotary flywheel (1), and then calculating the falling time of the blocking hook test piece (32) through the initial height of the tail end hook head of the blocking hook test piece (32) from the position right above the first rotary flywheel (1) and the instant speed when the blocking hook test piece (32) falls to the position right above the first rotary flywheel (1), so as to ensure that the blocking hook test piece (32) accurately collides against a second force measuring part (7) after falling, measuring the collision load through a second force measuring sensor (71), and simulating the stress load when the blocking hook of the carrier aircraft collides with an inclined ship surface at first after falling;
obstacle warship surface landing earthquake: starting a driving motor (4) to drive a first rotary flywheel (1) and a second rotary flywheel (2) to synchronously rotate, sweeping the outer side surface of the first rotary flywheel (1) through an external controller, determining the time when a third force measuring part (8) passes through the position right above the first rotary flywheel (1), and then calculating the falling time of the blocking hook test piece (32) through the initial height of the tail end hook head of the blocking hook test piece (32) from the position right above the first rotary flywheel (1) and the instant speed when the blocking hook test piece (32) falls to the position right above the first rotary flywheel (1), so as to ensure that the blocking hook test piece (32) accurately collides against a third force measuring part (8), measuring the collision load through a third force measuring sensor (81), and simulating the stress load when the blocking hook of the carrier aircraft collides with a carrier surface obstacle at first after falling;
s3, leveling the ship surface for secondary earthquake falling:
when the arresting hook test piece (32) collides with the first force measuring part (6), the second force measuring part (7) or the third force measuring part (8), the arresting hook test piece (32) is sprung up and falls down after moving upwards around the hinge point of the arresting hook test piece and the balancing weight (3), the push rod motor (52) is started at the moment to drive the sliding block (5) to slide along the sliding groove (51), the second rotating flywheel (2) still in rotation is moved to the position right below the arresting hook test piece (32), the arresting hook test piece (32) collides with the fourth force measuring part (9) after falling down, the impact load is measured through the fourth force measuring sensor (91), and the stress load when the arresting hook of the carrier aircraft contacts with the flat ship surface after falling down for the second time is simulated.
8. The method for measuring the load and simulating the ship surface characteristics of the ship-borne aircraft according to claim 7, wherein in the step S2, the driving motor (4) is started to drive the first rotary flywheel (1) and the second rotary flywheel (2) to synchronously rotate at a linear speed of 260-300 km/h, and the instantaneous speed of the blocking hook test piece (32) when falling right above the first rotary flywheel (1) is 6-8 m/S.
9. The method for measuring the load and simulating the ship surface characteristics of the ship-borne aircraft according to claim 7, wherein in the step S3, a push rod motor (52) is started to drive a sliding block (5) to slide along a sliding groove (51), and meanwhile, the rotating speed of a driving motor (4) is adjusted to drive a first rotary flywheel (1) and a second rotary flywheel (2) to synchronously rotate at a linear speed of 240-260 km/h.
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