CN117141745A - Device and method for simulating blocking hook impact speed during carrier aircraft carrier landing - Google Patents
Device and method for simulating blocking hook impact speed during carrier aircraft carrier landing Download PDFInfo
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- CN117141745A CN117141745A CN202311436056.7A CN202311436056A CN117141745A CN 117141745 A CN117141745 A CN 117141745A CN 202311436056 A CN202311436056 A CN 202311436056A CN 117141745 A CN117141745 A CN 117141745A
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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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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
- G01B5/24—Measuring arrangements characterised by the use of mechanical techniques for measuring angles or tapers; for testing the alignment of axes
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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
- G01M13/00—Testing of machine parts
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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
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Abstract
The invention discloses a simulation device and a method for simulating the impact speed of a blocking hook during carrier landing of a carrier-based aircraft, wherein the device comprises a blocking hook motion state simulation system, a driving system and a measurement and control system; the output end of the driving system is connected with a blocking hook motion state simulation system, and the measurement and control system comprises a landing height for landing gearh 1 Rotation angle alpha of arresting hook and landing time of landing geartA camera for performing measurement and an auxiliary detection device; the method comprises the following steps: s1, parameter setting of a measurement and control system, S2, simulating landing of a carrier-based aircraft, S3, measuring the performances of a blocking hook and a flywheel; the invention can study the situation of no need by adjusting the height and the angle of the arresting hookThe landing speed and performance of the arresting hooks under the same sinking speed and different angles.
Description
Technical Field
The invention relates to the technical field of aviation aircraft tests, in particular to a simulation device and a simulation method for simulating the impact speed of a blocking hook during carrier landing of a carrier-based aircraft.
Background
As is well known, carrier-based aircraft is critical to the ability to play a fight on aircraft carriers. For the carrier-borne aircraft, the carrier landing technology is both key and difficult. Therefore, when the carrier-based aircraft blocking design is carried out, firstly, the problem of the carrier landing speed after the blocking hook touches the carrier is considered, and how to control the speed of the blocking hook so as to control the impact load when the carrier-based aircraft lands is directly related to whether the carrier-based aircraft can smoothly block the carrier.
Along with the development of aircraft carrier and carrier-based aircraft technologies, research on the problem of the blocking hook carrier-contacting course speed is gradually developed, the current carrier-based aircraft blocking hook carrier-contacting impact course speed verification test is still blank, and the current stage is usually verified by adopting a carrier-based adaptive test flight test, but the risk is high. The risk and the cost of carrying out the impact speed test of the arresting hook carrier in a laboratory are low, and the impact heading speed of the arresting hook can be obtained rapidly so as to guide the structural design of the arresting hook. The method provides a basis for the performance design of the blocking hook of the carrier-based aircraft and the evaluation of the influence of the blocking hook impact on the machine body structure and the service life of the blocking hook. Laboratory research and verification of the arresting hook system in the process of aircraft arresting a ship are extremely important.
Disclosure of Invention
In order to solve the technical problems, the invention provides a simulation device and a simulation method for simulating the impact speed of a blocking hook when a carrier-based aircraft is on a carrier.
The technical scheme of the invention is as follows: a simulator for simulating the collision speed of a blocking hook during carrier landing of a carrier-based aircraft comprises a blocking hook motion state simulation system, a driving system and a measurement and control system; the output end of the driving system is connected with the arresting hook motion state simulation system;
the arresting hook motion state simulation system comprises a mounting table, a falling body device and a flywheel, wherein the falling body device and the flywheel are mounted on the mounting table;
the falling body device is arranged on the mounting table through the upright post and is positioned above the flywheel, the flywheel is rotatably arranged on the mounting table, and the top of the flywheel can be in contact with the falling body device;
the falling body device comprises a hanging basket, a landing gear, a arresting hook angle adjusting mechanism and an arresting hook, wherein the hanging basket is connected with the upright post in an up-down sliding manner, the landing gear is arranged at the bottom of the hanging basket, the arresting hook angle adjusting mechanism is arranged at the bottom of the hanging basket and is positioned right above the flywheel, and the arresting hook is rotatably arranged on the arresting hook angle adjusting mechanism;
the driving system is connected with the flywheel through a diaphragm coupler and is used for providing rotating power for the flywheel, and a second motor for adjusting the height of the falling body device; the first motor is arranged on the mounting table, and the second motor is arranged on the hanging basket;
the measurement and control system comprises a control system for controlling the landing height of the landing gearh 1 Rotation angle alpha of arresting hook and landing time of landing geartThe auxiliary detection device comprises a speed sensor and a three-way force sensor which are sequentially and detachably arranged on the flywheel along the circumferential direction;
description: the simulation device can effectively simulate the height and angle of the carrier-based aircraft, simulate the carrier landing height of the carrier-based aircraft by utilizing the height of the falling body device, simulate the carrier landing angle of the carrier-based aircraft by utilizing the angle of the blocking hook, simulate the flywheel speed at the designated height and angle by the falling body motion of the blocking hook, and then simulate and calculate the course speed of the blocking hook according to the auxiliary detection device, thereby obtaining the impact speed of the blocking hook; the three-dimensional force sensor is used for measuring impact load (namely vertical force) of the carrier-based aircraft to the flywheel at the moment of landing, braking load (namely heading force) of the flywheel and lateral force at the moment of landing by the arresting hook, so that whether the carrier-based aircraft falls at the current height or angle and has shimmy or damage to the flywheel can be judged according to the lateral force and the vertical force, and the arresting performance of the arresting hook is tested through the heading force, so that whether the carrier-based aircraft falls at the current height or angle meets the arresting requirement is judged.
Further, the arresting hook angle adjusting mechanism comprises a mounting mechanism and an adjusting mechanism;
the mounting mechanism comprises a mounting plate which is arranged along the vertical direction and fixedly connected with the bottom surface of the hanging basket, a mounting cavity which is arranged on one side surface of the mounting plate along the horizontal direction, and an arc-shaped groove which is arranged on the mounting plate; a rotating shaft is arranged on the mounting plate positioned at the center of the arc-shaped groove, one end of the blocking hook is rotationally connected with the rotating shaft,
a first air column is arranged in the arc-shaped groove, one end of the first air column is fixedly arranged at the bottom of the arc-shaped groove, the other end of the first air column is fixedly connected with a first magnetic block, and the first magnetic block is arranged in the arc-shaped groove in a sliding manner; an elastic air bag is arranged on the other side surface of the mounting plate, and an air inlet of the elastic air bag is communicated with an air outlet of the first air column through a pipeline with a one-way valve;
the other end of the arresting hook is connected with the first magnetic block through an electromagnetic column,
the adjusting mechanism comprises a sliding rod arranged in the mounting cavity along the horizontal direction, a second air column sleeved on the sliding rod and one end of which is connected with the mounting cavity, a sliding block sleeved on the sliding rod and connected with the other end of the second air column, a second magnetic block arranged on the sliding block and connected with the sliding block in a sliding way,
the inner top surface of the sliding rod is provided with a plurality of grooves for being clamped with the second magnetic blocks, electromagnetic sheets are arranged in the grooves, the bottom of the sliding block is hinged with an adjusting rod, and the adjusting rod penetrates through a strip-shaped groove in the bottom surface of the mounting cavity and is hinged with the middle part of the blocking hook; an air inlet valve and an air release valve which are communicated with the second air column are also arranged on the side surface of the other side of the mounting plate;
the air outlet of the elastic air bag is connected with the air inlet valve through a pipeline with a one-way valve;
a first electromagnetic valve for controlling the on/off of the electromagnetic column and a second electromagnetic valve for controlling the on/off of the electromagnetic sheet are arranged on the side surface of the other side of the mounting plate, the first electromagnetic valve is electrically connected with the electromagnetic column, and the second electromagnetic valve is electrically connected with the electromagnetic sheet;
the falling height h of the arresting hook on the arresting hook angle adjusting mechanism 2 =R（1-cosα），α=[0，90]The method comprises the steps of carrying out a first treatment on the surface of the The angle alpha is the rotation angle of the arresting hook, the unit is an angle, the size of the angle alpha is determined through the clamping position of the slot and the sliding block, and R is the length of the arresting hook; simulated height h of landing gear 3 =h 1 +h 2 Wherein the saidh 1 Is the landing height of the landing gear;
description: the elastic air bag is used for inflating and deflating the second air column to enable the sliding block to move to the slotting position at the corresponding position, then the electromagnetic sheet is electrified to start, so that the magnetic attraction effect between the slotting position at the corresponding position and the second magnetic block is realized, the blocking hook is positioned, and then the current position of the sliding block is judged by the camera to determine the angle of the blocking hook; the regulation of blocking the arbitrary angle of hook is placed through the unidirectional gas circulation between first gas column, elasticity gasbag, the second gas column, utilize disconnection of first, second solenoid valve to realize blocking the falling body motion of hook, also can be through setting up the angle value scale on the installation cavity, can direct artificial reading angle value, avoided blocking the operation that the angle value need be read at any time in the hook adjustment process, and the admission valve, the bleed valve with the second gas column intercommunication can be in time adjusted according to analog angle, thereby make the falling body analog motion of carrier-borne aircraft more accurate and easy operation.
Further, an air pump communicated with the elastic air bag is arranged on one side of the elastic air bag;
description: can in time aerify the inside of elasticity gasbag when the gas volume is too little in first gas column through the air pump so as to ensure the quick inflation of second gas column thereby promote the adjustment efficiency of arresting hook angle, further promote analogue means's simulation efficiency.
Further, a load unit is arranged at the bottom of the front side of the landing gear, and a negative weight is arranged in the load unit;
description: the weight can be adjusted through the inside removable loading piece of loading unit to simulate the fuselage equivalent weight of different models, and the commonality is strong, and the simulation is effectual.
Further, the outer edge of the flywheel is made of deck steel, and anti-slip paint is coated on the deck steel;
description: the anti-slip coating can be EPOXO300C epoxy polyamide; the method can simulate the collision boundary condition of the blocking hook of the carrier-based aircraft more truly, and has better simulation effect.
The invention also provides a simulation method for simulating the blocking hook impact speed when the carrier aircraft is on the ship, which is based on the simulation device for simulating the blocking hook impact speed when the carrier aircraft is on the ship, and comprises the following steps:
s1, parameter setting of measurement and control system
Determining a simulated height of the landing gear based on test requirementsh 3 Rotation angle of blocking hookαThe method comprises the steps of carrying out a first treatment on the surface of the Landing time of landing gear by using measurement and control systemtDetermining, namely positioning the arresting hook through the arresting hook angle adjusting mechanism and determining the falling height of the arresting hook on the arresting hook angle adjusting mechanismh 2 Then according toh 1 =h 3 -h 2 Calculating landing gear landing heighth 1 Positioning the landing gear through a second motor;
s2, simulating landing of carrier-based aircraft
Using a first motor to give the flywheel an initial speedv 1 Then releasing the arresting hook through the arresting hook angle adjusting mechanism, and enabling the arresting hook to descend to strike the flywheel, and utilizing a speed sensor on the flywheel; measuring the speed of the flywheel after the blocking hook collides with the flywheelv 2 ；
According to the describedv 1 、v 2 Andtcalculate the impact speed of the blocking hookv；
S3, measuring performances of arresting hooks and flywheel
Utilize three-dimensional force sensor to survey vertical force that carrier-borne aircraft produced at carrier landing momentF 1 Heading forceF 2 And lateral forceF 3 Based on the lateral forceF 3 Comparing with the shimmy safety value of the carrier-based aircraft, and judging the simulation height of the landing gearh 3 Blocking railAnalog angle of the blocking hookαWhether the lower carrier-based aircraft can generate shimmy or not and utilize heading forceF 2 The rate of change of (2) determining the arresting performance of the arresting hook, and further determining the simulated heighth 3 Analog angleαWhether the landing of the carrier-based aircraft meets the blocking requirement or not;
impact velocity through the arresting hookvCalculated at the simulated heighth 3 Analog angleαImpact load deformation of lower flywheelL、Maximum impact load F of blocking hook on flywheel d By comparing the damage safety value of the flywheel with the maximum impact load F of the blocking hook on the flywheel d Determining the simulated heighth 3 Analog angleαWhether the landing of the carrier-based aircraft damages the flywheel or not;
the shimmy safety value and the damage safety value of the flywheel of the carrier-based aircraft are all known parameters for testing the carrier-based aircraft.
Further, the striking speed of the arresting hookvThe calculation formula of (2) is as follows:
v=（1）
in the method, in the process of the invention,v 1 for the speed measured by the speed sensor at the initial rotation of the flywheel,v 2 the rotation speed of the flywheel measured by the speed sensor after the blocking hook collides with the flywheel is measured, g is the gravity acceleration, the value is 9.8m/s, and the landing time of the landing gear is t, specifically the time when the falling body device starts to fall to the blocking hook and collide with the flywheel;
description: the formula can calculate the impact speed of the arresting hook, so that the simulation result is more visual and accurate.
Further, the flywheel impact load deformationLThe calculation formula of (2) is as follows:
L=（2）
in the method, in the process of the invention,mis the weight of the carrier-based aircraft,Lis the impact load deformation amount of the flywheel,vis a blocking hookIs used for the impact velocity of the vehicle,kthe elastic coefficient of the flywheel is 75GPa;
description: the load deformation condition of the flywheel can be quantized by the formula, so that the performance of the flywheel can be determined more intuitively.
Furthermore, the judging method for whether the landing of the carrier-based aircraft damages the flywheel comprises the following steps:
firstly, according to the impact load deformation of flywheelLCalculating the maximum impact load F of the blocking hook on the flywheel d The method comprises the steps of carrying out a first treatment on the surface of the The maximum impact load F of the blocking hook to the flywheel d The calculation formula of (2) is as follows:
F d =kL（3）
in the method, in the process of the invention,kthe elastic coefficient of the flywheel is 75GPa,Lthe impact load deformation of the flywheel;
the maximum impact load F of the arresting hook is then applied d Compared with the damage safety value of flywheel, whenF d The failure safety value of the flywheel is greater than the simulated height of the landing gearh 3 Analog angle of blocking hookαThe lower carrier aircraft can damage the flywheel when falling down; when (when)F d < the flywheel failure safety value, then the simulated height at landing gearh 3 Analog angle of blocking hookαThe lower carrier-based aircraft can not damage the flywheel when falling down;
description: the formula can provide technical support for the impact performance of the arresting hook, and reduces the technical risk of test flight verification of the landing adaptation of the real aircraft.
Furthermore, the method for judging whether shimmy occurs in the landing of the carrier-based aircraft comprises the following steps:
by lateral forceF 3 Compared with the shimmy safety value of the carrier-based aircraft, whenF 3 The shimmy safety value of the carrier-based aircraft is more than the simulation height of the landing gearh 3 Analog angle of blocking hookαThe lower carrier aircraft falls to generate shimmy; when (when)F 3 If the shimmy safety value of the carrier-based aircraft is less than the shimmy safety value, the simulation height of the landing gear is representedh 3 Analog angle of blocking hookαThe landing of the lower carrier-based aircraft cannot generate shimmy;
description: the formula can provide technical support for the impact performance of the arresting hook, and reduces the technical risk of test flight verification of the landing adaptation of the real aircraft.
The beneficial effects of the invention are as follows:
(1) According to the invention, through adjusting the height of the landing gear and the angle of the arresting hook, the landing speed of the arresting hook under different sinking speeds and different angles can be studied; the landing gear and the arresting hook test piece are replaced by adjusting the counterweight mass to simulate the equivalent mass of the machine body of different machine types, so that the design tests of different arresting hook landing course speeds can be carried out, and the landing gear has good universality for different landing gears;
(2) According to the angle adjusting mechanism of the arresting hook, the arresting hook is adjusted and placed at any angle through unidirectional air circulation among the first air column, the elastic air bag and the second air column, falling motion of the arresting hook is realized through disconnection of the first electromagnetic valve and the second electromagnetic valve, the angle value can be directly read manually through setting an angle value scale on the mounting cavity, and an air inlet valve and an air outlet valve which are communicated with the second air column can be adjusted in time according to the simulation angle, so that falling simulation motion of a carrier aircraft is more accurate and easy to operate;
(3) According to the sensor detachably mounted on the surface of the flywheel, the sensor can be detached and replaced according to the items to be detected, the simulation efficiency is improved, the corresponding performance parameters can be calculated through the parameters of the sensor, so that the performance of the arresting hook is judged more effectively, the arresting hook is optimized and improved correspondingly, the sensor is adopted, the simulation test result is more visual, the simulation precision is more accurate, and the simulation effect is further improved.
Drawings
FIG. 1 is a flow chart of a simulation method of embodiment 1 of the present invention;
FIG. 2 is a schematic diagram showing the overall structure of a simulation apparatus according to embodiment 1 of the present invention;
FIG. 3 is a schematic view of the falling body device according to embodiment 1 of the present invention;
fig. 4 is a schematic structural view of an adjusting unit according to embodiment 1 of the present invention;
FIG. 5 is an enlarged view of a portion of the invention at A in FIG. 4;
FIG. 6 is a front view of the adjustment mechanism of embodiment 1 of the present invention;
FIG. 7 is a schematic view of a mounting plate structure in embodiment 3 of the present invention;
the device comprises a 1-arresting hook motion state simulation system, an 11-mounting table, a 12-falling body device, a 121-upright post, a 122-hanging basket, a 123-landing gear, a 1231-loading unit, a 124-arresting hook angle adjusting mechanism, 1240-mounting plates, 1241-mounting cavities, 1242-arc grooves, 1243-first air columns, 1244-first magnetic blocks, 1245-elastic air bags, 1246-air pumps, 125-arresting hooks, 126-adjusting mechanisms, 1261-sliding rods, 1262-second air columns, 1263-sliding blocks, 1264-second magnetic blocks, 1265-slotting, 1266-adjusting rods, 13-flywheels, a 2-driving system, a 3-measurement and control system, a 31-auxiliary detecting device, a 32-speed sensor and 33-three-way force sensors.
Detailed Description
The invention will be described in further detail with reference to the following embodiments to better embody the advantages of the invention.
Example 1: the simulation device for simulating the impact speed of the arresting hook during carrier landing of the carrier aircraft as shown in fig. 2 to 6 comprises an arresting hook motion state simulation system 1, a driving system 2 and a measurement and control system 3; the output end of the driving system 2 is connected with the arresting hook motion state simulation system 1;
the arresting hook motion state simulation system 1 comprises a mounting table 11, a falling body device 12 and a flywheel 13, wherein the falling body device 12 and the flywheel 13 are mounted on the mounting table 11; the outer edge of the flywheel 13 is made of deck steel, and the deck steel is coated with anti-slip paint; wherein, the anti-slip coating adopts commercial EPOXO300C epoxy polyamide;
the falling body device 12 is arranged on the mounting table 11 through the upright post 121 and is positioned above the flywheel 13, the flywheel 13 is rotatably arranged on the mounting table 11, and the top can be contacted with the falling body device 12;
the falling body device 12 comprises a hanging basket 122 which is connected with a column 121 in a sliding way up and down, a landing gear 123 which is arranged at the bottom of the hanging basket 122, a blocking hook angle adjusting mechanism 124 which is arranged at the bottom of the hanging basket 122 and is positioned right above the flywheel 13, and a blocking hook 125 which is rotatably arranged on the blocking hook angle adjusting mechanism 124; wherein, the hanging basket 122 is connected in the sliding groove on the upright post 121 in a sliding way through a sliding block;
the bottom of the front side of the landing gear 123 is provided with a load unit 1231, and a load block is arranged in the load unit 1231;
the arresting hook angle adjustment mechanism 124 includes a mounting mechanism and an adjustment mechanism 126;
the mounting mechanism comprises a mounting plate 1240 which is arranged along the vertical direction and fixedly connected with the bottom surface of the hanging basket 122, a mounting cavity 1241 which is arranged on one side surface of the mounting plate 1240 along the horizontal direction, an arc-shaped groove 1242 which is arranged on the mounting plate 1240, a rotating shaft which is arranged on the mounting plate 1240 and positioned at the center of the arc-shaped groove 1242, one end of a blocking hook 125 is rotatably connected with the rotating shaft,
the arc-shaped groove 1242 is internally provided with a first air column 1243, one end of the first air column 1243 is fixedly arranged at the bottom of the arc-shaped groove 1242, the other end of the first air column 124is fixedly connected with a first magnetic block 1244, and the first magnetic block 1244 is slidably arranged in the arc-shaped groove 1242; an elastic air bag 1245 is arranged on the side surface of the other side of the mounting plate 1240, and an air inlet of the elastic air bag 1245 is communicated with an air outlet of the first air column 1243 through a pipeline with a one-way valve;
the other end of the arresting hook 125 is connected with a first magnetic block 1244 through an electromagnetic pillar,
the adjusting mechanism 126 comprises a slide rod 1261 arranged in the mounting cavity 1241 along the horizontal direction, a second air column 1262 sleeved on the slide rod 1261 and one end of which is connected with the mounting cavity 1241, a slide block 1263 sleeved on the slide rod 1261 and connected with the other end of the second air column 1262, a second magnetic block 1264 slidingly connected with the slide block 1263,
the inner top surface of the slide rod 1261 is provided with a plurality of grooves 1265 for being clamped with the second magnetic blocks 1264, electromagnetic sheets are arranged in the grooves 1265, the bottom of the slide block 1263 is hinged with an adjusting rod 1266, and the adjusting rod 1266 passes through a strip-shaped groove on the bottom surface of the mounting cavity 1241 and is hinged with the middle part of the blocking hook 125; an air inlet valve and an air outlet valve which are communicated with the second air column 1262 are also arranged on the side surface of the other side of the mounting plate 1240;
the air outlet of the elastic air bag 1245 is connected with the air inlet valve through a pipeline with a one-way valve;
a first electromagnetic valve for controlling the on/off of the electromagnetic column is arranged on the side surface of the other side of the mounting plate 1240, and a second electromagnetic valve for controlling the on/off of the electromagnetic sheet is arranged on the side surface of the other side of the mounting plate 1240;
drop height of the arresting hooks 125 on the arresting hook angle adjusting mechanism 124h 2 =R（1-cosα），α=[0，90]The method comprises the steps of carrying out a first treatment on the surface of the Wherein, alpha is the rotation angle of the arresting hook 125, the unit is that the size of alpha is determined by the clamping position of the slot 1265 and the sliding block 1263, and R is the length of the arresting hook 125; simulated height of landing gear 123h 3 =h 1 +h 2 Wherein the saidh 1 Is the landing height of landing gear 123;
the driving system 2 comprises a first motor which is connected with the flywheel 13 through a diaphragm coupling and is used for providing rotation power for the flywheel 13, and a second motor which is used for adjusting the height of the falling body device 12; the first motor is arranged on the mounting table 11, and the second motor is arranged on the hanging basket 122;
the measurement and control system 3 includes a control system for controlling the landing height of the landing gear 123h 1 Rotation angle alpha of the arresting hook 125 and landing time of the landing gear 123tA camera for measuring and an auxiliary detection device 31, wherein the auxiliary detection device 31 comprises a speed sensor 32 and a three-way force sensor 33 which are sequentially and detachably arranged on the flywheel 13 in the circumferential direction;
it should be noted that: the embodiment further includes a PLC controller, a power supply, a driving system 2, a three-way force sensor 33, and a speed sensor 32, which are all commercial products, and the camera adopts a commercial intelligent panoramic camera, which is not described herein;
meanwhile, the camera is connected with the PLC, the PLC is connected with the second motor through the third electromagnetic valve, the landing gear 123 is driven to move through the second motor, meanwhile, a groove 1265 at one end of the second air column 1262 is used as a starting point, the current corresponding groove 1265 of the sliding block 1263 is detected through the camera to serve as an end point, and therefore the length from the starting point to the end point is calculated, and the rotation angle of the blocking hook 125 is calculated and judged.
Example 2: the embodiment describes a simulation method for simulating the impact speed of a blocking hook when a carrier aircraft is on a carrier, and the simulation device for simulating the impact speed of the blocking hook when the carrier aircraft is on the carrier based on the embodiment 1 is shown in fig. 1, and comprises the following steps:
s1, parameter setting of measurement and control system 3
Determination of the simulated height of landing gear 123 based on test requirementsh 3 Rotation angle of the arresting hook 125αThe method comprises the steps of carrying out a first treatment on the surface of the Landing time of landing gear 123 using measurement and control system 3tMeasuring, positioning the arresting hook 125 by the arresting hook angle adjusting mechanism 124, and determining the landing height of the arresting hook 125 on the arresting hook angle adjusting mechanism 124h 2 Then according toh 1 =h 3 -h 2 Calculated landing gear 123 landing heighth 1 And positioning the landing gear 123 by the second motor;
the blocking hook angle adjusting mechanism 124 is specifically located in the following manner:
firstly, calculating the angle between two adjacent slots 1265 according to the number of the slots 1265, then determining the position of the slots 1265 according to the rotation angle of the blocking hooks 125 which are simulated as required, opening an air inlet valve of the second air column 1262, simultaneously opening a first electromagnetic valve, enabling air in the elastic air bag 1245 to enter the second air column 1262 and drive the second air column 1262 to expand, driving a first magnetic block 1244 at the other end of the blocking hooks 125 to move along the arc-shaped slots 1242 in the right moving process of the sliding blocks 1263, observing the position of the sliding blocks 1263, opening the second electromagnetic valve when the sliding blocks 1263 move to the position of the slots 1265 of a target, fixing the second magnetic block 1264 with the slots 1265 under the action of magnetic force, opening an air release valve of the second air column 1262, enabling air in the second air column 1262 to be completely lost and contracted, then closing the second electromagnetic valve, enabling the other end of the blocking hooks 125 and the first magnetic block 1244 to move downwards under the action of gravity, and realizing extrusion of the first air column 1243, and adjusting the position of the blocking hooks 1245 when the air in the first air column 1243 flows into the elastic air column 1245 for the next time;
s2, simulating landing of carrier-based aircraft
An initial speed is given to the flywheel 13 by the first motorv 1 The arresting hook 125 is released by the arresting hook angle adjusting mechanism 124, the arresting hook 125 descends to strike the flywheel 13, and speed sensing on the flywheel 13 is utilizedThe device 32 measures the speed of the flywheel 13 after the blocking hook 125 collides with the flywheel 13v 2 ；
According to the describedv 1 、v 2 Andtcalculate the impact velocity of the blocking hook 125vThe method comprises the steps of carrying out a first treatment on the surface of the The impact speed of the arresting hooks 125vThe calculation formula of (2) is as follows:
v=（1）
in the method, in the process of the invention,v1 is the speed measured by the speed sensor 32 at the initial rotation of the flywheel 13,v2 is the rotational speed of the flywheel 13 measured by the speed sensor 32 after the catch hook 125 collides with the flywheel 13,gthe gravity acceleration is 9.8m/s,tthe landing time of the landing gear 123, specifically, the time when the falling body device 12 starts to fall to the time when the arresting hook 125 collides with the flywheel 13;
s3, measuring performances of the arresting hooks 125 and the flywheel 13
Determination of vertical force generated by carrier-based aircraft at carrier landing moment by using three-way force sensor 33F 1 Heading forceF 2 And lateral forceF 3 According to the lateral forceF 3 Comparing with the shimmy safety value of the carrier-based aircraft, and judging the simulation height of the landing gear 123h 3 Analog angle of the arresting hook 125αWhether shimmy occurs in landing of the carrier-based aircraft or not by using course forceF 2 The rate of change of (a) determines the blocking performance of the blocking hook 125, and further determines the simulated heighth 3 Analog angleαWhether the landing of the carrier-based aircraft meets the blocking requirement or not;
the impact velocity through the arresting hooks 125vCalculated at the simulated heighth 3 Analog angleαImpact load deformation amount of lower to flywheel 13L、Maximum impact load F of the blocking hook 125 on the flywheel 13 d By comparing the breaking safety value of the flywheel 13 with the maximum impact load F of the blocking hook 125 on the flywheel 13 d Determining the simulated heighth 3 Analog angleαWhether the landing of the carrier-based aircraft can damage the flywheel 13 or not;
deformation of flywheel 13 due to impact loadLThe calculation formula of (2) is as follows:
L=（2）
in the method, in the process of the invention,mis the weight of the carrier-based aircraft,Las the amount of impact load deformation of the flywheel 13,vto arrest the rate of impact of the hooks 125,kthe elastic coefficient of the flywheel 13 is 75GPa;
the judging method for whether the landing of the carrier-based aircraft damages the flywheel 13 is as follows:
first according to the impact load deformation of the flywheel 13LCalculating the maximum impact load of the arresting hook 125 on the flywheel 13F d The method comprises the steps of carrying out a first treatment on the surface of the Maximum impact load of the blocking hook 125 on the flywheel 13F d The calculation formula of (2) is as follows:
F d =kL（3）
in the method, in the process of the invention,kthe elastic coefficient of the flywheel 13 is 75GPa,Lthe impact load deformation amount of the flywheel 13;
the maximum impact load of the arresting hooks 125 is then appliedF d In contrast to the fail-safe value of the flywheel 13, whenF d The fail safe value of the flywheel 13 is then indicative of the simulated height at the landing gear 123h 3 Analog angle of the arresting hook 125αThe lower carrier aircraft can damage the flywheel 13; when (when)F d < the fail safe value of flywheel 13, then the simulated height at landing gear 123 is indicatedh 3 Analog angle of the arresting hook 125αThe lower carrier aircraft can not damage the flywheel 13 when falling;
the judging method for whether shimmy occurs in the landing of the carrier-based aircraft comprises the following steps:
by lateral forceF 3 Compared with the shimmy safety value of the carrier-based aircraft, whenF 3 The shimmy safety value of the carrier aircraft is greater than the simulated altitude at landing gear 123h 3 Analog angle of the arresting hook 125αThe lower carrier aircraft falls to generate shimmy; when (when)F 3 The shimmy safety value of the carrier-based aircraft is expressed in terms of landing and risingAnalog height of shelf 123h 3 Analog angle of the arresting hook 125αThe landing of the lower carrier-based aircraft cannot generate shimmy;
the shimmy safety value and the damage safety value of the flywheel 13 of the carrier-based aircraft are known parameters for testing the carrier-based aircraft.
Example 3: the difference from embodiment 1 is that, as shown in fig. 7, an air pump 1246 communicating with the elastic air bag 1245 is provided on one side of the elastic air bag 1245;
the working principle of this embodiment is basically the same as that of embodiment 1, except that: the air pump 1246 is used for inflating the interior of the elastic air bag 1245, so that the air quantity in the interior of the elastic air bag 1245 is not limited by the movement condition of the first magnetic block 1244, and the adjustment efficiency of the blocking hook angle adjusting mechanism 124 is further improved.
Claims (10)
1. The simulator for simulating the collision speed of the arresting hook during carrier landing of the carrier-based aircraft is characterized by comprising a arresting hook motion state simulation system (1), a driving system (2) and a measurement and control system (3); the output end of the driving system (2) is connected with the arresting hook motion state simulation system (1);
the arresting hook motion state simulation system (1) comprises a mounting table (11), a falling body device (12) and a flywheel (13) which are mounted on the mounting table (11);
the falling body device (12) is arranged on the mounting table (11) through a stand column (121) and is positioned above the flywheel (13), the flywheel (13) is rotatably arranged on the mounting table (11), and the top of the flywheel can be in contact with the falling body device (12);
the falling body device (12) comprises a hanging basket (122) which is connected with the upright post (121) in an up-down sliding way, a landing gear (123) which is arranged at the bottom of the hanging basket (122), a blocking hook angle adjusting mechanism (124) which is arranged at the bottom of the hanging basket (122) and is positioned right above the flywheel (13), and a blocking hook (125) which is rotatably arranged on the blocking hook angle adjusting mechanism (124);
the driving system (2) comprises a first motor which is connected with the flywheel (13) through a diaphragm type coupling and is used for providing rotating power for the flywheel (13), and a second motor which is used for adjusting the height of the falling body device (12); the first motor is arranged on the mounting table (11), and the second motor is arranged on the hanging basket (122);
the measurement and control system (3) comprises a control system for controlling the landing height of the landing gear (123)h 1 The rotation angle alpha of the arresting hook (125) and the landing time of the landing gear (123)tThe device comprises a camera for measuring and an auxiliary detection device (31), wherein the auxiliary detection device (31) comprises a speed sensor (32) and a three-way force sensor (33) which are sequentially and detachably arranged on the flywheel (13) along the circumferential direction.
2. The simulator for simulating the impact speed of a blocking hook when a carrier aircraft is landing on a ship according to claim 1, wherein the blocking hook angle adjusting mechanism (124) comprises a mounting mechanism and an adjusting mechanism (126);
the mounting mechanism comprises a mounting plate (1240) which is arranged along the vertical direction and fixedly connected with the bottom surface of the hanging basket (122), a mounting cavity (1241) which is arranged on one side surface of the mounting plate (1240) along the horizontal direction, and an arc-shaped groove (1242) which is arranged on the mounting plate (1240), a rotating shaft is arranged on the mounting plate (1240) which is positioned at the center of the arc-shaped groove (1242), one end of the blocking hook (125) is rotationally connected with the rotating shaft,
a first air column (1243) is arranged in the arc-shaped groove (1242), one end of the first air column (1243) is fixedly arranged at the bottom of the arc-shaped groove (1242) and the other end of the first air column is fixedly connected with a first magnetic block (1244), and the first magnetic block (1244) is slidably arranged in the arc-shaped groove (1242); an elastic air bag (1245) is arranged on the other side surface of the mounting plate (1240), and an air inlet of the elastic air bag (1245) is communicated with an air outlet of the first air column (1243) through a pipeline with a one-way valve;
the other end of the arresting hook (125) is connected with the first magnetic block (1244) through an electromagnetic column,
the adjusting mechanism (126) comprises a slide rod (1261) arranged in the mounting cavity (1241) along the horizontal direction, a second air column (1262) sleeved on the slide rod (1261) and one end of which is connected with the mounting cavity (1241), a slide block (1263) sleeved on the slide rod (1261) and connected with the other end of the second air column (1262), a second magnetic block (1264) connected with the slide block in a sliding way is arranged on the slide block (1263),
a plurality of grooves (1265) used for being clamped with the second magnetic blocks (1264) are formed in the inner top surface of the sliding rod (1261), electromagnetic sheets are arranged in the grooves (1265), an adjusting rod (1266) is hinged to the bottom of the sliding block (1263), and the adjusting rod (1266) penetrates through a strip-shaped groove in the bottom surface of the mounting cavity (1241) and is hinged to the middle part of the blocking hook (125); an air inlet valve and an air outlet valve which are communicated with the second air column (1262) are also arranged on the side surface of the other side of the mounting plate (1240);
an air outlet of the elastic air bag (1245) is connected with the air inlet valve through a pipeline with a one-way valve;
a first electromagnetic valve for controlling the on/off of the electromagnetic column and a second electromagnetic valve for controlling the on/off of the electromagnetic sheet are arranged on the side surface of the other side of the mounting plate (1240), the first electromagnetic valve is electrically connected with the electromagnetic column, and the second electromagnetic valve is electrically connected with the electromagnetic sheet;
the falling height of the arresting hook (125) on the arresting hook angle adjusting mechanism (124)h 2 =R（1-cosα），α=[0，90]The method comprises the steps of carrying out a first treatment on the surface of the The alpha is the rotation angle of the arresting hook (125), the unit is degrees, the size of the alpha is determined by the clamping position of the slot (1265) and the sliding block (1263), and the R is the length of the arresting hook (125); simulated height of landing gear (123)h 3 =h 1 +h 2 Wherein the saidh 1 Is the landing height of the landing gear (123).
3. The simulator for simulating the collision speed of the blocking hooks during carrier landing of the carrier aircraft according to claim 2, wherein an air pump (1246) communicated with the elastic air bag (1245) is arranged on one side of the elastic air bag (1245).
4. The simulator for simulating the collision speed of a blocking hook during carrier landing of a carrier-based aircraft according to claim 1, wherein a load unit (1231) is arranged at the bottom of the front side of the landing gear (123), and a load block is arranged in the load unit (1231).
5. The simulator for simulating the collision speed of a blocking hook during carrier landing of a carrier-based aircraft according to claim 1, wherein the outer edge of the flywheel (13) is made of deck steel, and the deck steel is coated with anti-slip paint.
6. A simulation method for simulating the impact speed of a blocking hook when a carrier aircraft is on a carrier, based on the simulation device for simulating the impact speed of a blocking hook when a carrier aircraft is on a carrier according to any one of claims 1 to 5, which is characterized by comprising the following steps:
s1, parameter setting of measurement and control system (3)
Determining a simulated height of the landing gear (123) based on test requirementsh 3 Rotation angle of the arresting hook (125)αThe method comprises the steps of carrying out a first treatment on the surface of the Landing time of landing gear (123) by means of measurement and control system (3)tMeasuring, positioning the arresting hook (125) through the arresting hook angle adjusting mechanism (124), and determining the falling height of the arresting hook (125) on the arresting hook angle adjusting mechanism (124)h 2 Then according toh 1 =h 3 -h 2 Calculating the landing gear (123) landing heighth 1 And positioning the landing gear (123) by means of a second motor;
s2, simulating landing of carrier-based aircraft
An initial speed of the flywheel (13) is given by the first motorv 1 The arresting hook (125) is released by the arresting hook angle adjusting mechanism (124), the arresting hook (125) descends to strike the flywheel (13), and the speed sensor (32) on the flywheel (13) is utilized to measure the flying of the arresting hook (125) after the collision with the flywheel (13)Speed of wheel (13)v 2 ；
According to the describedv 1 、v 2 Andtcalculating the impact speed of the blocking hook (125)v；
S3, measuring performances of the arresting hooks (125) and the flywheel (13)
Measuring vertical force generated by carrier-based aircraft at carrier landing moment by using three-way force sensor (33)F 1 Heading forceF 2 And lateral forceF 3 According to the lateral forceF 3 Comparing with the shimmy safety value of the carrier-based aircraft, judging the simulation height of the landing gear (123)h 3 Analog angle of arresting hook (125)αWhether shimmy occurs in landing of the carrier-based aircraft or not by using course forceF 2 The rate of change of (1) determines the blocking performance of the blocking hook (125), and further determines the simulated heighth 3 Analog angleαWhether the landing of the carrier-based aircraft meets the blocking requirement or not;
impact velocity through the arresting hook (125)vCalculated at the simulated heighth 3 Analog angleαImpact load deformation amount of lower pair flywheel (13)L、Maximum impact load of blocking hook (125) to flywheel (13)F d By comparing the damage safety value of the flywheel (13) with the maximum impact load of the blocking hook (125) on the flywheel (13)F d Determining the simulated heighth 3 Analog angleαWhether the landing of the carrier-based aircraft can damage the flywheel (13) or not;
the shimmy safety value and the damage safety value of the flywheel (13) of the carrier-based aircraft are known parameters for testing the carrier-based aircraft.
7. The method for simulating the collision velocity of a blocking hook during carrier landing of a carrier aircraft according to claim 6, wherein in step S2, the collision velocity of the blocking hook (125) is determinedvThe calculation formula of (2) is as follows:v=（1）
in the method, in the process of the invention,v 1 for the speed measured by the speed sensor (32) at the initial rotation of the flywheel (13),v 2 to stop the rotational speed of the flywheel (13) measured by a speed sensor (32) after the collision of the hook (125) with the flywheel (13),gthe gravity acceleration is 9.8m/s,tthe landing gear (123) is lowered for a time period, specifically, a time period when the falling body device (12) starts to fall to a time period when the blocking hook (125) collides with the flywheel (13).
8. The method for simulating the collision speed of a blocking hook during carrier landing of a carrier-based aircraft according to claim 6, wherein in step S3, the flywheel (13) is deformed by collision loadLThe calculation formula of (2) is as follows:L=（2）
in the method, in the process of the invention,mis the weight of the carrier-based aircraft,Lis the impact load deformation of the flywheel (13),vto arrest the impact velocity of the hooks (125),kthe elastic coefficient of the flywheel (13) is 75GPa.
9. The simulation method for simulating the collision speed of a blocking hook when a carrier aircraft lands on a ship according to claim 8, wherein the judgment method for judging whether the landing of the carrier aircraft damages the flywheel (13) is as follows:
firstly, according to the impact load deformation of the flywheel (13)LCalculating the maximum impact load of the blocking hook (125) on the flywheel (13)F d The method comprises the steps of carrying out a first treatment on the surface of the The maximum impact load of the blocking hook (125) on the flywheel (13)F d The calculation formula of (2) is as follows:
F d =kL（3）
in the method, in the process of the invention,kthe elastic coefficient of the flywheel (13) is 75GPa,Lis the impact load deformation of the flywheel (13);
then the arresting hook (125)Maximum impact loadF d Compared with the damage safety value of the flywheel (13), whenF d The failure safety value of the flywheel (13) is then indicative of the simulated height at the landing gear (123)h 3 Analog angle of arresting hook (125)αThe lower carrier aircraft can damage the flywheel (13); when (when)F d < flywheel (13) destroys the safety value, then indicates the simulated height at landing gear (123)h 3 Analog angle of arresting hook (125)αThe lower carrier-based aircraft can not damage the flywheel (13).
10. The method for simulating the collision speed of a blocking hook when a carrier aircraft lands on a ship according to claim 6, wherein the method for judging whether shimmy occurs in landing of the carrier aircraft is as follows:
by lateral forceF 3 Compared with the shimmy safety value of the carrier-based aircraft, whenF 3 The shimmy safety value of the carrier aircraft is represented by the simulated altitude at the landing gear (123)h 3 Analog angle of arresting hook (125)αThe lower carrier aircraft falls to generate shimmy; when (when)F 3 < shimmy safety value of carrier aircraft, then the simulated altitude at landing gear (123)h 3 Analog angle of arresting hook (125)αThe landing of the lower carrier-based aircraft can not generate shimmy.
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