CN114778056B - Test system and method for testing dynamic impact mechanical property of light airplane structure - Google Patents
Test system and method for testing dynamic impact mechanical property of light airplane structure Download PDFInfo
- Publication number
- CN114778056B CN114778056B CN202210659659.2A CN202210659659A CN114778056B CN 114778056 B CN114778056 B CN 114778056B CN 202210659659 A CN202210659659 A CN 202210659659A CN 114778056 B CN114778056 B CN 114778056B
- Authority
- CN
- China
- Prior art keywords
- test
- adjusting
- light aircraft
- connecting panel
- dynamic impact
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 147
- 238000000034 method Methods 0.000 title claims description 21
- 230000001133 acceleration Effects 0.000 claims abstract description 40
- 238000005259 measurement Methods 0.000 claims abstract description 29
- 238000009863 impact test Methods 0.000 claims abstract description 14
- 238000010998 test method Methods 0.000 claims abstract description 7
- 238000003780 insertion Methods 0.000 claims description 23
- 230000037431 insertion Effects 0.000 claims description 23
- 230000008569 process Effects 0.000 claims description 19
- 230000007246 mechanism Effects 0.000 claims description 15
- 230000005484 gravity Effects 0.000 claims description 8
- 230000009471 action Effects 0.000 claims description 4
- 230000004044 response Effects 0.000 claims description 4
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 3
- 239000003638 chemical reducing agent Substances 0.000 claims description 3
- 239000000741 silica gel Substances 0.000 claims description 3
- 229910002027 silica gel Inorganic materials 0.000 claims description 3
- 230000001960 triggered effect Effects 0.000 claims description 3
- 230000000149 penetrating effect Effects 0.000 claims description 2
- 238000005286 illumination Methods 0.000 abstract description 4
- 238000005516 engineering process Methods 0.000 abstract description 2
- 230000001360 synchronised effect Effects 0.000 abstract description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
Images
Classifications
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
-
- 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
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
- G01N3/04—Chucks
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
- G01N3/06—Special adaptations of indicating or recording means
- G01N3/068—Special adaptations of indicating or recording means with optical indicating or recording means
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/30—Investigating strength properties of solid materials by application of mechanical stress by applying a single impulsive force, e.g. by falling weight
- G01N3/307—Investigating strength properties of solid materials by application of mechanical stress by applying a single impulsive force, e.g. by falling weight generated by a compressed or tensile-stressed spring; generated by pneumatic or hydraulic means
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0014—Type of force applied
- G01N2203/0016—Tensile or compressive
- G01N2203/0019—Compressive
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/003—Generation of the force
- G01N2203/0042—Pneumatic or hydraulic means
- G01N2203/0044—Pneumatic means
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/06—Indicating or recording means; Sensing means
- G01N2203/0641—Indicating or recording means; Sensing means using optical, X-ray, ultraviolet, infrared or similar detectors
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/06—Indicating or recording means; Sensing means
- G01N2203/067—Parameter measured for estimating the property
- G01N2203/0676—Force, weight, load, energy, speed or acceleration
Landscapes
- General Physics & Mathematics (AREA)
- Physics & Mathematics (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Health & Medical Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention provides a test system and a test method for testing dynamic impact mechanical properties of a light airplane structure, and belongs to the technical field of airplane testing. The test system comprises a trolley, a test tool fixture, a measurement control assembly, an illumination assembly for providing illumination for the test system, a camera measurement assembly and a light aircraft test piece arranged on the test tool fixture, wherein an aviation dummy is placed in the light aircraft test piece; the test fixture disclosed by the invention has the advantages that the trolley is used as a test platform, the acceleration curve of a light aircraft test piece can be accurately controlled, the test fixture can meet the requirements of two test working conditions of 0-degree and 60-degree, the working condition requirements of other angles can be met, and the reliability is high; the test system integrates the advanced test technology of the measurement control assembly and the camera measurement assembly, completes synchronous triggering of various devices, can meet the requirements of horizontal impact tests of general light airplanes, and has the advantages of strong operability, low test risk and wide application prospect.
Description
Technical Field
The invention belongs to the technical field of airplane testing, and particularly relates to a test system and a test method for testing dynamic impact mechanical properties of a light airplane structure.
Background
At the takeoff and landing stages of the airplane, the impact load borne by the airplane body has the characteristics of long stroke and large magnitude, and at the moment, the part with weak structural strength of the airplane body often generates large impact stress, so that the structure of the airplane is damaged, and the safety of passengers is influenced. Safety is a primary factor of design consideration of the airplane, the safety comprises safety of passengers and safety of an airplane body structure, and in a survivable flight accident, the airplane body and the aviation seat play an important role in protecting the passengers.
In order to detect whether the aircraft structure meets the airworthiness standard of an acceleration load waveform and ensure the safety of the aircraft and personnel, a light aircraft horizontal impact test needs to be carried out, and in the horizontal impact test process, data needing to be collected comprise response information such as strain, structural deformation, acceleration, a dummy movement track and seat deformation.
The horizontal impact test in the current dynamic impact mechanical property test of the light aircraft structure is only for aviation seats or automobile seats and is limited by the size and the load of a horizontal impact test bed, the loading and the test of a test system can not meet the impact test requirements of the whole general light aircraft, the factors of an aircraft body are ignored, and no relevant content exists in the research of the horizontal impact test of the general light aircraft in China. Therefore, a test system and a test method for testing dynamic impact mechanical properties of a light aircraft structure are needed.
Disclosure of Invention
Aiming at the existing problems, the invention provides a test system and a test method for testing the dynamic impact mechanical property of a light airplane structure.
The technical scheme of the invention is as follows: the test system for testing the dynamic impact mechanical property of the light aircraft structure comprises a trolley, a test tool fixture, a measurement control assembly, a lighting assembly for providing lighting for the test system, a camera measurement assembly and a light aircraft test piece arranged on the test tool fixture, wherein an aviation dummy is placed in the light aircraft test piece;
the test tooling fixture comprises a lower connecting panel arranged at the upper end of the trolley, an upper connecting panel hinged with one end of the lower connecting panel, an angle adjusting support assembly arranged between the upper connecting panel and the lower connecting panel, and a machine body connecting mechanism arranged at the upper end of the upper connecting panel, wherein a light aircraft test piece is arranged at the upper end of the upper connecting panel through the machine body connecting mechanism;
the angle adjusting support assembly comprises two horizontal sliding strips, an adjusting sliding plate, a second adjusting sliding groove and an angle adjusting rod, wherein the two horizontal sliding strips are arranged on the lower connecting panel along the length direction, the upper ends of the two horizontal sliding strips are provided with first adjusting sliding grooves, the bottom ends of the two horizontal sliding strips are in sliding connection with the first adjusting sliding grooves through first adjusting sliding blocks, the second adjusting sliding grooves are arranged on the bottom surface of the upper connecting panel along the length direction, the left sides and the right sides of the inner wall of the upper connecting panel are provided with a plurality of first fixed inserting holes, the angle adjusting rod is arranged between the adjusting sliding plate and the upper connecting panel, one end of the angle adjusting rod is hinged with the adjusting sliding plate, the other end of the angle adjusting rod is in sliding connection with the second adjusting sliding grooves through second adjusting sliding blocks, the left sides and the right sides of the second adjusting sliding plate are connected with the first fixed inserting holes through bolts, and the adjusting sliding plate is driven to slide back and forth in the first adjusting sliding grooves through first electric telescopic rods;
the measurement control assembly comprises a controller for controlling each electrical element to normally operate, a first acceleration sensor connected with the controller and used for measuring the acceleration of the light aircraft test piece in the process of testing impact, a strain sensor used for measuring the stress of the light aircraft test piece in the process of testing impact, a second acceleration sensor used for measuring the acceleration and stress conditions inside the body of the aviation dummy in the process of testing impact, and a force sensor;
and shooting a dynamic impact test process of the light aircraft test piece through the camera shooting measurement component.
Furthermore, each first fixed jack is internally provided with a first electromagnetic coil, the left side and the right side of each second adjusting slider are respectively provided with a spring inserted bar, the tail end of each spring inserted bar is provided with a second electromagnetic coil with the same polarity as the first electromagnetic coil, and when the first electromagnetic coil and the second electromagnetic coil are electrified, each spring inserted bar is compressed to one side close to the second adjusting slider under the action of repulsive force, so that the spring inserted bars are moved out from the first fixed jacks at the corresponding positions, and then different working conditions are adjusted by moving the positions of the second adjusting sliders in the second adjusting chutes, so that the dynamic impact mechanical property test of the light aircraft structure under different working conditions is met.
Furthermore, the spring inserted bars are multiple and are symmetrically arranged on the left side and the right side of the second adjusting slide block respectively, so that each spring inserted bar can be inserted into the corresponding first fixing insertion hole, the supporting firmness of the whole angle adjusting support assembly is guaranteed through the spring inserted bars, and the reliability of the device is improved.
Further, fuselage coupling mechanism is including locating on the top connection panel and the upper end is equipped with the spout connecting plate that the spout was adjusted to the third along length direction, locate on the spout connecting plate and the bottom adjust two of spout connection through third adjusting block and third, locate on the spout connecting plate and be used for the drive to connect the second electric telescopic handle of grip block horizontal slip, the horizontal slip of grip block is connected through the drive of second electric telescopic handle, adjust two distances of connecting between the grip block, thereby satisfy not unidimensional light aircraft test piece's use, and wide applicability.
Further, two it all is equipped with a plurality of anti-skidding tight cushions of subsides to connect the grip block offside, just the tight cushion of antiskid subsides is the soft silica gel material, be equipped with the fixed jack of a plurality of seconds on the spout connecting plate, every connect on the grip block run through be equipped with the pole is twisted to the screw thread of the fixed jack threaded connection of second, after adjusting two distances of connecting between the grip block, twist the fixed connection between pole and the fixed jack of second through the screw thread, further fixed connecting the grip block, increase the mechanical strength of connecting the grip block, it is more firm to the centre gripping of light aircraft test piece to make two connection grip blocks.
Further, two it all is equipped with the installing port to connect the grip block offside, the lock joint has the centre gripping buckle in the installing port, can dismantle on the centre gripping buckle and be connected with the centre gripping kicking block, the centre gripping kicking block lateral wall is located to the tight cushion of antiskid subsides, and one side that two centre gripping kicking blocks are relative is arbitrary in arc, U-shaped or the V-arrangement, carries out the centre gripping to light-duty aircraft test piece through the centre gripping kicking block that can dismantle the different shapes of connection, satisfies and carries out the centre gripping to the light-duty aircraft test piece appearance of different shapes, is favorable to dynamic impact mechanical properties test's normal clear, and the practicality is high, is fit for using widely.
Furthermore, down on the connection panel and with last connection panel offside be equipped with controller electric connection's angle sensor, two connection grip block offside is equipped with gravity sensor, through the angle between angle sensor measurement lower connection panel and the last connection panel, makes things convenient for the experimental angle of accurate control, satisfies the demand of different experimental operating modes, detects through gravity sensor whether to connect grip block and light aircraft test spare contact, makes and connects grip block and light aircraft test spare centre gripping firm, guarantees the normal clear of dynamic impact mechanical properties test.
Further, the measurement control assembly further comprises a display operation screen.
The invention also discloses a test method of the test system for testing the dynamic impact mechanical property of the light airplane structure, which comprises the following steps:
s1, before a dynamic impact mechanical property test, a dummy piece with the same quality as a light airplane test piece is installed on the trolley for debugging, a required acceleration waveform curve is obtained by adjusting the air pressure value of external air pressure power equipment and a speed reducer of the trolley, and is transmitted to the controller;
s2, placing the light airplane test piece on the chute connecting plate, starting the two second electric telescopic rods to extend through the controller, enabling the two connecting clamping plates to move oppositely, detecting whether the corresponding connecting clamping plates are in contact with the light airplane test piece through the two gravity sensors, and controlling the two second electric telescopic rods to stop extending through the controller when the connecting clamping plates are in contact with the light airplane test piece;
s3, adjusting the angle between the lower connecting panel and the upper connecting panel according to the working condition requirement of the dynamic impact mechanical property test, taking the second adjusting slide block on the angle adjusting rod down from the second adjusting chute and horizontally placing the second adjusting slide block on the lower connecting panel when a 0-degree working condition is required, and then placing the upper connecting panel on the lower connecting panel along the horizontal direction;
s4, when a 60-degree working condition is needed, the second adjusting slide block on the angle adjusting rod is arranged in the second adjusting slide groove and is electrified to the first electromagnetic coil and the second electromagnetic coil, under the action of the repulsion force of like poles, each spring inserted bar is compressed to one side close to the second adjusting slide block, so that the spring inserted bar is moved out from the first fixed jack at the corresponding position to start the first electric telescopic rod, the first electric telescopic rod drives the adjusting sliding plate to slide on the first adjusting sliding groove, and meanwhile, the second adjusting sliding block synchronously slides in the second adjusting sliding groove, and the angle between the lower connecting panel and the upper connecting panel is detected in real time by an angle sensor, when the angle reaches 60 degrees, powering off the first electromagnetic coil and the second electromagnetic coil, restoring the elasticity of the spring inserted bar at the moment, inserting the spring inserted bar into the first fixed jack, and repeating the process when working conditions at other angles are required;
and S5, after the angle is adjusted, the external air pressure power equipment provides power for the trolley according to the acceleration waveform curve, the measurement control assembly, the lighting assembly and the camera measurement assembly are synchronously triggered through the emission button of the trolley, the acceleration of the light aircraft test piece is measured through the first acceleration sensor, the stress of the light aircraft test piece is measured through the strain sensor, the acceleration inside the body of the aviation dummy is measured through the second acceleration sensor, the stress condition inside the body of the aviation dummy is measured through the force sensor, the dynamic impact test process of the light aircraft test piece is shot through the camera measurement assembly, the acceleration waveform curve received by the controller is used as input, the detected data is used as response, and the test result is output according to the provisions of the pilot standard.
Compared with the prior art, the invention has the beneficial effects that:
(1) the test fixture disclosed by the invention has the advantages that the trolley is used as a test platform, the acceleration curve of a light aircraft test piece can be accurately controlled, the test fixture can meet the requirements of two test working conditions of 0-degree and 60-degree, the working condition requirements of other angles can be met, and the reliability is high; the test system integrates the advanced test technologies of the measurement control assembly and the camera measurement assembly, completes the synchronous triggering of various devices, can meet the requirements of the horizontal impact test of the general light aircraft, and has strong operability, low test risk and wide application prospect;
(2) when the machine body connecting mechanism is used, the second electric telescopic rod can drive the connecting clamping plates to slide left and right to adjust the distance between the two connecting clamping plates, so that the use of light aircraft test pieces with different sizes is met, and meanwhile, the friction force between the connecting clamping plates and the light aircraft test pieces is increased through the arrangement of the anti-skidding tight cushions on the opposite sides of the two connecting clamping plates, so that the two connecting clamping plates can clamp the light aircraft test pieces more firmly.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a schematic structural view of an angle bracket set according to embodiment 1 of the present invention;
FIG. 3 is a schematic structural view of an angle bracket set according to embodiment 4 of the present invention;
fig. 4 is a schematic structural view of the body attachment mechanism of embodiment 1 of the present invention;
fig. 5 is a schematic structural view of the body attachment mechanism of embodiment 2 of the present invention;
fig. 6 is a schematic structural view of a body attachment mechanism of embodiment 3 of the invention;
fig. 7 is a side view of the body attachment mechanism of embodiment 1 of the present invention.
Wherein, 1-trolley, 2-test tool fixture, 20-lower connecting panel, 21-upper connecting panel, 22-angle adjusting bracket assembly, 220-horizontal sliding bar, 2200-first adjusting sliding groove, 221-adjusting sliding plate, 2210-first adjusting sliding block, 222-second adjusting sliding groove, 2220-first fixing insertion hole, 2221-first electromagnetic coil, 223-angle adjusting rod, 2230-second adjusting sliding block, 2231-spring inserted rod, 2232-second electromagnetic coil, 224-first electric telescopic rod, 23-machine body connecting mechanism, 230-sliding groove connecting plate, 2300-third adjusting sliding groove, 2301-second fixing insertion hole, 2302-threaded rod, 231-connecting clamping plate, 2310-third adjusting sliding block, 2311-antiskid tight soft cushion tight fit, 2312-a gravity sensor, 232-a second electric telescopic rod, 233-an installation port, 234-a clamping buckle, 235-a clamping top block, 24-an angle sensor, 3-a measurement control component, 30-a controller, 31-a first acceleration sensor, 32-a strain sensor, 33-a second acceleration sensor, 34-a force sensor, 35-a display operation screen, 4-a lighting component, 5-a camera shooting measurement component and 6-a light airplane test piece.
Detailed Description
In order to further understand the contents of the present invention, the present invention is described in detail by examples below.
Example 1
As shown in fig. 1, the test system for testing dynamic impact mechanical properties of a light aircraft structure comprises a trolley 1, a test tool fixture 2, a measurement control assembly 3, an illumination assembly 4 for providing illumination for the test system, a camera measurement assembly 5 and a light aircraft test piece 6 arranged on the test tool fixture 2, wherein an aviation dummy is placed in the light aircraft test piece 6;
the test tooling fixture 2 comprises a lower connecting panel 20 arranged at the upper end of the trolley 1, an upper connecting panel 21 hinged with one end of the lower connecting panel 20, an angle adjusting support assembly 22 arranged between the upper connecting panel 21 and the lower connecting panel 20, and a machine body connecting mechanism 23 arranged at the upper end of the upper connecting panel 21, wherein the light aircraft test piece 6 is arranged at the upper end of the upper connecting panel 21 through the machine body connecting mechanism 23;
as shown in fig. 2, the angle adjusting bracket assembly 22 includes two horizontal sliding bars 220 provided on the lower connection panel 20 along the length direction and having a first adjusting sliding groove 2200 at the upper end thereof, an adjusting sliding plate 221 provided at the upper end of the two horizontal sliding bars 220 and having a bottom end slidably connected to the first adjusting sliding groove 2200 through a first adjusting slider 2210, a second adjusting sliding groove 222 provided at the bottom surface of the upper connection panel 21 along the length direction and having 10 first fixing insertion holes 2220 at both left and right sides of an inner wall thereof, an angle adjusting rod 223 provided between the adjusting sliding plate 221 and the upper connection panel 21, one end of the angle adjusting rod 223 being hinged to the adjusting sliding plate 221, the other end being slidably connected to the second adjusting sliding groove 222 through a second adjusting slider 2230, the left and right sides of the second adjusting slide block 2230 are connected with the first fixing insertion hole 2220 through the insertion pin, and the adjusting slide plate 221 is driven by the first electric telescopic rod 224 to slide back and forth in the first adjusting slide slot 2200;
the measurement control assembly 3 comprises a controller 30 for controlling normal operation of each electrical element, a first acceleration sensor 31 which is connected with the controller 30 and is used for measuring acceleration of the light aircraft test piece 6 in the test impact process, a strain sensor 32 for measuring stress of the light aircraft test piece 6 in the test impact process, a second acceleration sensor 33 and a force sensor 34 which are used for measuring acceleration and stress conditions inside the body of the aeronautical dummy in the test impact process, and a display operation screen 35;
shooting a dynamic impact test process of a light aircraft test piece 6 through the camera shooting measurement component 5;
as shown in fig. 4 and 7, the machine body connecting mechanism 23 includes a chute connecting plate 230 disposed on the upper connecting panel 21 and having a third adjusting chute 2300 at an upper end thereof along a length direction, two connecting clamping plates 231 disposed on the chute connecting plate 230 and having bottom ends connected to the third adjusting chute 2300 via a third adjusting slider 2310, and a second electric telescopic rod 232 disposed on the chute connecting plate 230 and configured to drive the connecting clamping plates 231 to slide left and right;
the opposite sides of the two connecting and clamping plates 231 are respectively provided with 5 anti-skidding and tightly-attached cushions 2311, the anti-skidding and tightly-attached cushions 2311 are made of soft silica gel, the chute connecting plate 230 is provided with 4 second fixing insertion holes 2301, and each connecting and clamping plate 231 is provided with a threaded screwing rod 2302 in threaded connection with the second fixing insertion holes 2301 in a penetrating manner;
the opposite sides of the two connecting clamping plates 231 are respectively provided with a mounting hole 233, a clamping buckle plate 234 is buckled in the mounting hole 233, a clamping ejector block 235 is detachably connected to the clamping buckle plate 234, an anti-skidding tight-sticking soft cushion 2311 is arranged on the side wall of the clamping ejector block 235, and the opposite sides of the two clamping ejector blocks 235 are both arc-shaped;
the lower connection panel 20 is provided with an angle sensor 24 electrically connected to the controller 30 at an opposite side to the upper connection panel 21, and the two connection clamping plates 231 are provided with a gravity sensor 2312 at an opposite side.
Example 2
The present embodiment is different from embodiment 1 in that:
as shown in fig. 5, the opposite sides of the two clamping top blocks 235 are V-shaped.
Example 3
The present embodiment is different from embodiment 1 in that:
as shown in fig. 6, the opposite sides of the two clamping top blocks 235 are U-shaped.
Example 4
The present embodiment is different from embodiment 1 in that:
as shown in fig. 3, a first solenoid 2221 is disposed in each first fixed insertion hole 2220, spring insertion rods 2231 are disposed on the left and right sides of each second adjusting slider 2230, and a second solenoid 2232 having the same polarity as that of the first solenoid 2221 is disposed at the end of each spring insertion rod 2231;
there are 6 spring rods 2231, and the 6 spring rods 2231 are symmetrically disposed on the left and right sides of the second adjusting block 2230, respectively.
Example 5
This embodiment is different from embodiment 4 in that:
there are 10 spring plungers 2231.
Example 6
This embodiment is different from embodiment 4 in that:
there are 12 spring plungers 2231.
Example 7
The embodiment discloses a test method of the test system for testing the dynamic impact mechanical property of the light aircraft structure in the embodiment 4, which comprises the following steps:
s1, before a dynamic impact mechanical property test, a dummy part with the same quality as the light aircraft test part 6 is installed on the trolley 1 for debugging, a required acceleration waveform curve is obtained by adjusting the air pressure value of external air pressure power equipment and a speed reducer of the trolley 1, and the acceleration waveform curve is transmitted to the controller 30;
s2, placing the light airplane test piece 6 on the chute connecting plate 230, starting the two second electric telescopic rods 232 to extend through the controller 30, enabling the two connecting clamping plates 231 to move oppositely, meanwhile, detecting whether the corresponding connecting clamping plates 231 are in contact with the light airplane test piece 6 through the two gravity sensors 2312, and when the two connecting clamping plates are in contact with the light airplane test piece 6, controlling the two second electric telescopic rods 232 to stop extending through the controller 30;
s3, adjusting the angle between the lower connection panel 20 and the upper connection panel 21 according to the working condition requirement of the dynamic impact mechanical property test, when a working condition of 0 degree is required, taking the second adjusting slide block 2230 on the angle adjusting rod 223 from the second adjusting slide groove 222, horizontally placing the second adjusting slide block on the lower connection panel 20, and then placing the upper connection panel 21 on the lower connection panel 20 along the horizontal direction;
s4, when a 60 ° working condition is required, the second adjusting slider 2230 on the angle adjusting rod 223 is placed in the second adjusting sliding slot 222, and the first electromagnetic coil 2221 and the second electromagnetic coil 2232 are energized, under the action of the repulsion force of like poles, each spring plunger 2231 is compressed towards the side close to the second adjusting slider 2230, so that the spring plunger 2231 is moved out from the first fixed insertion hole 2220 at the corresponding position, the first electric telescopic rod 224 is started, the adjusting sliding plate 221 is driven by the first electric telescopic rod 224 to slide on the first adjusting sliding slot 2200, at the same time, the second adjusting slider 2230 slides synchronously in the second adjusting sliding slot 222, and the angle between the lower connection panel 20 and the upper connection panel 21 is detected in real time by the angle sensor 24, when the working condition reaches 60 °, the first electromagnetic coil 2221 and the second electromagnetic coil 2232 are de-energized, at this time, the spring plunger 2231 restores the elastic insertion hole and is inserted into the first fixed insertion hole 2220, when the working conditions of other angles are needed, the process is repeated;
s5, after the angle is adjusted, the external air pressure power equipment provides power for the trolley 1 according to the acceleration waveform curve, the measurement control component 3, the lighting component 4 and the camera measurement component 5 are synchronously triggered through the emission button of the trolley 1, the acceleration of the light aircraft test piece 6 is measured through the first acceleration sensor 31, the stress of the light aircraft test piece 6 is measured through the strain sensor 32, the acceleration inside the body of the aviation dummy is measured through the second acceleration sensor 33, the stress inside the body of the aviation dummy is measured through the force sensor 34, the dynamic impact test process of the light aircraft test piece 6 is shot through the camera measurement component 5, the acceleration waveform curve received by the controller 30 serves as input, the detected data serves as response, and the test result is output according to the pilot standard.
Claims (9)
1. The test system for the dynamic impact mechanical property test of the light aircraft structure is characterized by comprising a trolley (1), a test tool fixture (2), a measurement control assembly (3), a lighting assembly (4) for providing lighting for the test system, a camera measurement assembly (5) and a light aircraft test piece (6) arranged on the test tool fixture (2), wherein an aviation dummy is placed in the light aircraft test piece (6);
the test tooling fixture (2) comprises a lower connecting panel (20) arranged at the upper end of the trolley (1), an upper connecting panel (21) hinged with one end of the lower connecting panel (20), an angle adjusting support assembly (22) arranged between the upper connecting panel (21) and the lower connecting panel (20), and a machine body connecting mechanism (23) arranged at the upper end of the upper connecting panel (21), wherein a light aircraft test piece (6) is arranged at the upper end of the upper connecting panel (21) through the machine body connecting mechanism (23);
the angle adjusting bracket assembly (22) comprises two horizontal sliding bars (220) which are arranged on the lower connecting panel (20) along the length direction and provided with first adjusting sliding chutes (2200) at the upper ends, adjusting sliding plates (221) which are arranged at the upper ends of the two horizontal sliding bars (220) and are in sliding connection with the first adjusting sliding chutes (2200) at the bottom ends through first adjusting sliding blocks (2210), second adjusting sliding chutes (222) which are arranged on the bottom surface of the upper connecting panel (21) along the length direction and are provided with a plurality of first fixed insertion holes (2220) at the left and right sides of the inner wall, and angle adjusting rods (223) which are arranged between the adjusting sliding plates (221) and the upper connecting panel (21), wherein one ends of the angle adjusting rods (223) are hinged with the adjusting sliding plates (221), the other ends of the angle adjusting sliding rods are in sliding connection with the second adjusting sliding chutes (222) through second adjusting sliding blocks (2230), and the left and right sides of the second adjusting sliding blocks (2230) are connected with the first fixed insertion holes (2220) through bolts, the adjusting sliding plate (221) is driven by a first electric telescopic rod (224) to slide back and forth in a first adjusting sliding groove (2200);
the measurement control assembly (3) comprises a controller (30) for controlling normal operation of each electrical element, a first acceleration sensor (31) which is connected with the controller (30) and is used for measuring acceleration of the light aircraft test piece (6) in a test impact process, a strain sensor (32) which is used for measuring stress of the light aircraft test piece (6) in the test impact process, a second acceleration sensor (33) which is used for measuring acceleration and stress conditions inside the body of the aeronautical dummy in the test impact process, and a force sensor (34);
and shooting the dynamic impact test process of the light aircraft test piece (6) through the camera shooting measurement component (5).
2. The test system for the dynamic impact mechanical property test of the light aircraft structure is characterized in that a first electromagnetic coil (2221) is arranged in each first fixed insertion hole (2220), spring insertion rods (2231) are respectively arranged on the left side and the right side of each second adjusting slide block (2230), and a second electromagnetic coil (2232) with the same polarity as that of the first electromagnetic coil (2221) is arranged at the tail end of each spring insertion rod (2231).
3. The test system for the dynamic impact mechanical property test of the light aircraft structure as recited in claim 2, wherein a plurality of spring rods (2231) are provided, and the plurality of spring rods (2231) are respectively symmetrically arranged on the left and right sides of the second adjusting slider (2230).
4. The test system for the dynamic impact mechanical property test of the light aircraft structure according to claim 1, wherein the aircraft body connecting mechanism (23) comprises a chute connecting plate (230) which is arranged on the upper connecting panel (21) and provided with a third adjusting chute (2300) at the upper end along the length direction, two connecting clamping plates (231) which are arranged on the chute connecting plate (230) and connected with the third adjusting chute (2300) at the bottom end through a third adjusting slider (2310), and a second electric telescopic rod (232) which is arranged on the chute connecting plate (230) and used for driving the connecting clamping plates (231) to slide left and right.
5. The test system for the dynamic impact mechanical property test of the light aircraft structure according to claim 4, wherein a plurality of anti-slip tight cushions (2311) are arranged on opposite sides of the two connecting clamping plates (231), the anti-slip tight cushions (2311) are made of soft silica gel, a plurality of second fixing insertion holes (2301) are arranged on the chute connecting plate (230), and a threaded screwing rod (2302) in threaded connection with the second fixing insertion holes (2301) is arranged on each connecting clamping plate (231) in a penetrating manner.
6. The test system for the dynamic impact mechanical property test of the light aircraft structure as recited in claim 5, wherein two opposite sides of the connecting clamping plate (231) are provided with mounting holes (233), a clamping buckle plate (234) is buckled in the mounting holes (233), a clamping top block (235) is detachably connected to the clamping buckle plate (234), the anti-slip tight cushion (2311) is arranged on a side wall of the clamping top block (235), and one opposite side of the two clamping top blocks (235) is any one of an arc shape, a U shape or a V shape.
7. The test system for the dynamic impact mechanical property test of the light aircraft structure is characterized in that an angle sensor (24) electrically connected with the controller (30) is arranged on the lower connecting panel (20) and on the opposite side of the upper connecting panel (21), and a gravity sensor (2312) is arranged on the opposite side of the two connecting and clamping plates (231).
8. The test system for the dynamic impact mechanical property test of the light aircraft structure is characterized in that the measurement control component (3) further comprises a display operation screen (35).
9. The test method of the test system for the dynamic impact mechanical property test of the light aircraft structure according to any one of claims 1 to 8, is characterized by comprising the following steps:
s1, before a dynamic impact mechanical property test, a dummy part with the same quality as the light aircraft test part (6) is installed on the trolley (1) for debugging, a required acceleration waveform curve is obtained by adjusting the air pressure value of external air pressure power equipment and a speed reducer of the trolley (1) and is transmitted to the controller (30);
s2, placing the light airplane test piece (6) on the sliding chute connecting plate (230), starting the two second electric telescopic rods (232) to extend through the controller (30), enabling the two connecting clamping plates (231) to move oppositely, simultaneously detecting whether the corresponding connecting clamping plates (231) and the light airplane test piece (6) are in contact or not through the two gravity sensors (2312), and when the two second electric telescopic rods (232) are in contact, controlling the two second electric telescopic rods (232) to stop extending through the controller (30);
s3, adjusting the angle between the lower connecting panel (20) and the upper connecting panel (21) according to the working condition requirement of the dynamic impact mechanical property test, taking down a second adjusting slide block (2230) on an angle adjusting rod (223) from a second adjusting slide groove (222) when a 0-degree working condition is required, horizontally placing the second adjusting slide block on the lower connecting panel (20), and then placing the upper connecting panel (21) on the lower connecting panel (20) along the horizontal direction;
s4, when a 60-degree working condition is needed, a second adjusting slide block (2230) on the angle adjusting rod (223) is placed in a second adjusting slide groove (222), a first electromagnetic coil (2221) and a second electromagnetic coil (2232) are electrified, under the action of repulsion force of like poles, each spring inserted rod (2231) is compressed to one side close to the second adjusting slide block (2230), the spring inserted rod (2231) is moved out of a first fixed insertion hole (2220) at a corresponding position, a first electric telescopic rod (224) is started, an adjusting slide plate (221) is driven to slide on the first adjusting slide groove (2200) through the first electric telescopic rod (224), meanwhile, the second adjusting slide block (2230) synchronously slides in the second adjusting slide groove (222), an angle between the lower connecting panel (20) and the upper connecting panel (21) is detected in real time through an angle sensor (24), and when the angle reaches 60 degrees, the first electromagnetic coil (2221) and the second electromagnetic coil (2232) are powered off, at the moment, the spring inserted rod (2231) restores elasticity and is inserted into the first fixed insertion hole (2220), and when the working conditions of other angles are needed, the process is repeated;
s5, after the angle is adjusted, external air pressure power equipment provides power for the trolley (1) according to an acceleration waveform curve, a measuring control assembly (3), a lighting assembly (4) and a camera measuring assembly (5) are synchronously triggered through a transmitting button of the trolley (1), the acceleration of a light aircraft test piece (6) is measured through a first acceleration sensor (31), the stress of the light aircraft test piece (6) is measured through a strain sensor (32), the acceleration inside the body of the aeronautical dummy is measured through a second acceleration sensor (33), the stress condition inside the body of the aeronautical dummy is measured through a force sensor (34), the dynamic impact testing process of the light aircraft test piece (6) is shot through the camera measuring assembly (5), the acceleration waveform curve received by a controller (30) serves as input, and the detected data serves as response, and outputting the test result according to the provisions of the pilot standard.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210659659.2A CN114778056B (en) | 2022-06-13 | 2022-06-13 | Test system and method for testing dynamic impact mechanical property of light airplane structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210659659.2A CN114778056B (en) | 2022-06-13 | 2022-06-13 | Test system and method for testing dynamic impact mechanical property of light airplane structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114778056A CN114778056A (en) | 2022-07-22 |
| CN114778056B true CN114778056B (en) | 2022-09-02 |
Family
ID=82422032
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210659659.2A Active CN114778056B (en) | 2022-06-13 | 2022-06-13 | Test system and method for testing dynamic impact mechanical property of light airplane structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114778056B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117029697B (en) * | 2023-10-08 | 2024-01-05 | 中国飞机强度研究所 | Device for measuring space displacement dynamic image of landing gear wheel shaft of carrier-based aircraft drop test |
| CN117705399B (en) * | 2024-02-05 | 2024-04-16 | 中国飞机强度研究所 | Dynamic impact test system and method for aircraft airborne system |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5872321A (en) * | 1997-12-08 | 1999-02-16 | The United States Of America As Represented By The Secretary Of The Navy | Side impact injury test apparatus |
| EP1251343A1 (en) * | 2001-04-20 | 2002-10-23 | Vladimir Makarov | Method and device for mechanical stresses measurement |
| CN102692306A (en) * | 2011-03-23 | 2012-09-26 | 武汉东江阀业制造有限公司 | Small online impact detection test stand |
| CA2778574A1 (en) * | 2011-06-14 | 2012-12-14 | The Boeing Company | Blunt impact test apparatus and method |
| WO2013105917A2 (en) * | 2011-12-02 | 2013-07-18 | Intel Corporation | Automatic accident analysis |
| CN103645026A (en) * | 2013-11-28 | 2014-03-19 | 江西洪都航空工业集团有限责任公司 | General-purpose plane longitudinal horizontal crash test device and test method |
| CN104359675A (en) * | 2014-10-29 | 2015-02-18 | 西安航空制动科技有限公司 | Method for testing load impact loading of aircraft wheel bearings |
| JP2016065856A (en) * | 2014-09-25 | 2016-04-28 | Imv株式会社 | Impact testing machine |
| CN210180841U (en) * | 2019-05-09 | 2020-03-24 | 清华大学苏州汽车研究院（相城） | Impact load testing device for aircraft engine supporting structural member |
| CN111409860A (en) * | 2020-04-30 | 2020-07-14 | 中国飞机强度研究所 | Impact resistance test platform and system suitable for aviation seat assembly |
| CN112683481A (en) * | 2021-01-08 | 2021-04-20 | 中国人民解放军63919部队 | Low-G-value gravitational field aircraft impact experiment system and method |
| CN113800005A (en) * | 2021-11-10 | 2021-12-17 | 中航飞机起落架有限责任公司 | Emergency breaking test bed and test method for main landing gear of airplane |
| CN114323529A (en) * | 2021-12-23 | 2022-04-12 | 中国飞机强度研究所 | Head damage testing device and method for unmanned aerial vehicle falling collision personnel |
| CN216309380U (en) * | 2021-04-22 | 2022-04-15 | 郑州飞机装备有限责任公司 | Mechanics loading mechanism capable of simulating pneumatic load |
-
2022
- 2022-06-13 CN CN202210659659.2A patent/CN114778056B/en active Active
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5872321A (en) * | 1997-12-08 | 1999-02-16 | The United States Of America As Represented By The Secretary Of The Navy | Side impact injury test apparatus |
| EP1251343A1 (en) * | 2001-04-20 | 2002-10-23 | Vladimir Makarov | Method and device for mechanical stresses measurement |
| CN102692306A (en) * | 2011-03-23 | 2012-09-26 | 武汉东江阀业制造有限公司 | Small online impact detection test stand |
| CA2778574A1 (en) * | 2011-06-14 | 2012-12-14 | The Boeing Company | Blunt impact test apparatus and method |
| WO2013105917A2 (en) * | 2011-12-02 | 2013-07-18 | Intel Corporation | Automatic accident analysis |
| CN103645026A (en) * | 2013-11-28 | 2014-03-19 | 江西洪都航空工业集团有限责任公司 | General-purpose plane longitudinal horizontal crash test device and test method |
| JP2016065856A (en) * | 2014-09-25 | 2016-04-28 | Imv株式会社 | Impact testing machine |
| CN104359675A (en) * | 2014-10-29 | 2015-02-18 | 西安航空制动科技有限公司 | Method for testing load impact loading of aircraft wheel bearings |
| CN210180841U (en) * | 2019-05-09 | 2020-03-24 | 清华大学苏州汽车研究院（相城） | Impact load testing device for aircraft engine supporting structural member |
| CN111409860A (en) * | 2020-04-30 | 2020-07-14 | 中国飞机强度研究所 | Impact resistance test platform and system suitable for aviation seat assembly |
| CN112683481A (en) * | 2021-01-08 | 2021-04-20 | 中国人民解放军63919部队 | Low-G-value gravitational field aircraft impact experiment system and method |
| CN216309380U (en) * | 2021-04-22 | 2022-04-15 | 郑州飞机装备有限责任公司 | Mechanics loading mechanism capable of simulating pneumatic load |
| CN113800005A (en) * | 2021-11-10 | 2021-12-17 | 中航飞机起落架有限责任公司 | Emergency breaking test bed and test method for main landing gear of airplane |
| CN114323529A (en) * | 2021-12-23 | 2022-04-12 | 中国飞机强度研究所 | Head damage testing device and method for unmanned aerial vehicle falling collision personnel |
Non-Patent Citations (3)
| Title |
|---|
| Experimental research on impact loading characteristics by full-scale airplane impacting on concrete target;Zhuo-ping Duan 等;《Nuclear Engineering and Design》;20180117;全文 * |
| 某轻型飞机驾驶员座椅装机动态水平冲击试验分析;郑亚明;《中国科技信息》;20150515(第10期);全文 * |
| 轻型飞机全机水平撞击试验装置设计研究;魏榕祥 等;《机械科学与技术》;20120215;第31卷(第2期);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114778056A (en) | 2022-07-22 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN114778056B (en) | Test system and method for testing dynamic impact mechanical property of light airplane structure | |
| GB2583418A (en) | Unmanned-aerial-vehicle hangar | |
| CN102359874B (en) | Mechanical property testing platform for automobile chair | |
| CN109406842B (en) | Motor test bench | |
| US20050056755A1 (en) | Latch device | |
| CN212083586U (en) | Partial discharge ultrasonic detection device | |
| CN111006890B (en) | Test and data acquisition device for mechanical separation of falling separation electric connector for aerospace | |
| CN104977160A (en) | Special fixture for aerospace electrical connector separation test | |
| CN110068471B (en) | Low-impact separation simulation experiment device | |
| CN209085910U (en) | A kind of charging interface plug and pull out detector | |
| CN109142040A (en) | A kind of spontaneous load experimental rig remotely controlled | |
| CN101358944B (en) | Detection device for inlay pieces | |
| CN112683504B (en) | Portable automatic parachute opening device detector | |
| CN110118650B (en) | Fatigue test equipment for parking release mechanism of double-diaphragm disc spring brake chamber | |
| CN210119341U (en) | Test device for locking and releasing mechanism unfolding under vacuum | |
| CN208367122U (en) | A kind of performance test mechanism of Seat lumbar motor driver | |
| CN210037448U (en) | Portable multifunctional elevator loading testing device | |
| CN209140249U (en) | A kind of air blower press-loading device | |
| CN109341924B (en) | Integrated missile launcher unlocking force testing device | |
| CN108693425B (en) | Keyboard detection device for radio-frequency electromagnetic field radiation immunity test of oiling machine | |
| CN202100084U (en) | Electronic lock used for wire harness test | |
| CN112129555A (en) | Windshield system testing method | |
| CN116533505B (en) | Biaxially oriented device for processing polypropylene film | |
| CN218283614U (en) | Quick positioning mechanism for spin riveting machine | |
| CN215932060U (en) | Detection apparatus applied to inflatable cabinet |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |