CN113740019A - Unmanned aerial vehicle horizontal impact test system - Google Patents
Unmanned aerial vehicle horizontal impact test system Download PDFInfo
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- CN113740019A CN113740019A CN202111170604.7A CN202111170604A CN113740019A CN 113740019 A CN113740019 A CN 113740019A CN 202111170604 A CN202111170604 A CN 202111170604A CN 113740019 A CN113740019 A CN 113740019A
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- 230000003584 silencer Effects 0.000 claims description 4
- 238000013519 translation Methods 0.000 claims description 4
- 230000000694 effects Effects 0.000 abstract description 2
- 230000001105 regulatory effect Effects 0.000 description 10
- 238000012544 monitoring process Methods 0.000 description 7
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- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 2
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- 229910052804 chromium Inorganic materials 0.000 description 2
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- 238000005259 measurement Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
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- 230000003746 surface roughness Effects 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 208000035473 Communicable disease Diseases 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
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- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000003116 impacting effect Effects 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/08—Shock-testing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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Abstract
The invention discloses a horizontal impact test system of an unmanned aerial vehicle, which comprises a test platform, a launching device, a sighting device and a dummy seat, wherein the launching device is arranged on the test platform; the launching device comprises a power mechanism, a damping mechanism and a bearing table which are sequentially arranged on the test platform, wherein the power mechanism comprises a launching rod which penetrates through the damping mechanism to be connected with the bearing table; the aiming device is arranged on the test platform and can rotate around the connecting shaft; the distance between the dummy seat and the test platform is adjustable. During the use, adjust well through sighting device calibration test platform and dummy seat earlier, adjust well back rotation sighting device and make unmanned aerial vehicle jet out, the back is adjusted well in the calibration, arranges unmanned aerial vehicle in on the plummer, provides power through emitter, makes unmanned aerial vehicle have great speed, then the damping mechanism effect makes the launching rod stop gradually, unmanned aerial vehicle jets out under inertia and collides with the dummy on the dummy seat. Therefore, the ground equivalent test that the ground high-value target is collided by the small-sized light unmanned aerial vehicle is realized.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicle collision safety tests, and particularly relates to an unmanned aerial vehicle horizontal impact test system.
Background
Unmanned aerial vehicles emerged at the earliest 20 s in the 20 th century. Drones tend to be more suitable for tasks that are too "fool, dirty, or dangerous" than are manned aircraft. Unmanned aerial vehicles can be classified into military and civil applications according to the application field. For military use, unmanned aerial vehicles divide into reconnaissance aircraft and target drone. In the civil aspect, the unmanned aerial vehicle is applied in the industry and is really just needed by the unmanned aerial vehicle; at present, the unmanned aerial vehicle is applied to the fields of aerial photography, agriculture, plant protection, miniature self-timer, express transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, romantic manufacturing and the like, the application of the unmanned aerial vehicle is greatly expanded, and developed countries actively expand industrial application and develop unmanned aerial vehicle technology.
And at present, the use, operation, protection, management and control and other specifications of the civil light and small unmanned aerial vehicle lack effective data and test support during the process of making.
Disclosure of Invention
The invention aims to provide a horizontal impact test system of an unmanned aerial vehicle aiming at the defects of the prior art.
The horizontal impact test system of the unmanned aerial vehicle comprises a test platform, a launching device, a sighting device and a dummy seat; the launching device comprises a power mechanism, a damping mechanism and a bearing table which are sequentially arranged on the test platform, wherein the power mechanism comprises a launching rod which penetrates through the damping mechanism to be connected with the bearing table; the aiming device is arranged on the test platform and can rotate around the connecting shaft; the distance between the dummy seat and the test platform is adjustable.
The test platform comprises supports, adjusting mechanisms and a bedplate, wherein the supports are uniformly arranged, and the bedplate is arranged on the supports through the adjusting mechanisms.
The adjusting mechanism comprises an adjusting seat, an adjusting block, an adjusting screw rod and an adjusting nut; the adjusting seat is an L-shaped seat body, a through hole is formed in the vertical surface of the adjusting seat, and the adjusting block is a frustum-shaped block; the adjusting seat is detachably connected with the support through a horizontal section of the adjusting seat, the adjusting nut is arranged at the through hole of the vertical section of the adjusting seat, the adjusting screw is in threaded connection with the adjusting nut, and a force applying rod is arranged outside one end of the adjusting screw, and the other end of the adjusting screw is connected with the large-diameter end of the adjusting block.
The test platform further comprises a slide rail, and the slide rail is arranged on the bedplate.
The power mechanism comprises an air source and a high-speed cylinder; the high-speed cylinder comprises a cylinder body and a piston rod, one end of the cylinder body is connected with an air source, the other end of the cylinder body is connected with the damping mechanism, the piston rod is coaxially arranged in the cylinder body, and the outer end of the piston rod penetrates through the damping mechanism to be connected with the bearing platform.
And a guide sliding seat is arranged outside the piston rod and connected to the sliding rail.
The damping mechanism comprises a damping cylinder, a buffering air source and a damping ring; radial holes are respectively formed in two ends of the wall of the damping cylinder, the silencer is connected to the outside of the radial hole at one end, the radial hole at the other end is communicated with a buffering air source, the inner diameter of the damping ring is matched with the outer diameter of the piston rod, and the damping ring is coaxially arranged in the damping cylinder.
Aiming device is including sliding axle, linking frame, lifter and laser emitter, and the axle that slides assembles on the slide rail, and the base of linking frame is connected and can be followed axial rotation in the epaxial of sliding, and the lifter sets up the linking frame topside, and laser emitter connects in the bottom of lifter.
The dummy seat comprises a base, a pitching plate, a seat main body and an adjusting device; the pitching plate is assembled on the base through the adjusting device, the pitching angle of the pitching plate is adjusted by the adjusting device, and the seat body is connected to the pitching plate and can slide and be locked along the length direction of the pitching plate.
The base comprises a guide rail, a sliding block and a slewing bearing, the guide rail is laid on the foundation, and the slewing bearing is arranged on the guide rail through the sliding block; the adjusting device comprises a bearing seat, a screw rod, a nut seat and a connecting rod, wherein a handle is arranged at the outer end of the screw rod so as to rotate; the pair of bearing seats are vertically arranged on the base, the screw rod is assembled with the two bearing seats, the nut seat is connected to the screw rod and converts rotation into translation, and the nut seat at one end of the connecting rod is connected and the other end of the connecting rod is hinged with the pitching plate.
When the unmanned aerial vehicle is put into use, the aiming device is used for checking whether the test platform is aligned with the dummy seat, the aiming device is rotated after the alignment so that the unmanned aerial vehicle can be ejected, the unmanned aerial vehicle is placed on the bearing table after the alignment is corrected, the power is provided by the ejecting device so that the unmanned aerial vehicle has higher speed, then the damping mechanism acts so that the ejecting rod is gradually stopped, and the unmanned aerial vehicle is ejected under inertia and collides with the dummy on the dummy seat. Thereby realize ground high value target and dummy and receive the ground equivalent test of light small unmanned aerial vehicle collision, can inspect personnel or the ground high value target receive the damage degree of collision, for the affirmation and the verification of collision dynamics numerical model provide data support, for the use of civilian light small unmanned aerial vehicle, operation, protection and management and control specification provide effectual data and experimental support.
Drawings
Fig. 1 is a schematic layout of a preferred embodiment of the present invention.
Fig. 2 is an enlarged schematic view of the adjusting mechanism in the preferred embodiment.
Fig. 3 is an enlarged schematic view of the power mechanism in the preferred embodiment.
Fig. 4 is an enlarged schematic view of the damping mechanism in the preferred embodiment.
Fig. 5 is a side enlarged schematic view of the aiming device in the preferred embodiment.
Fig. 6 is an enlarged schematic view of the dummy seat in the present preferred embodiment.
Fig. 7 is a schematic enlarged top view of the pitch plate of the dummy seat in the preferred embodiment.
Fig. 8 is a schematic diagram of the working principle of the control system according to the preferred embodiment.
Fig. 9 is a schematic view of the air inlet and outlet control in the preferred embodiment.
Fig. 10 is a schematic view of pressure acquisition of the preferred embodiment.
Sequence numbers of the drawings:
1-a test platform, wherein the test platform,
11-a support, wherein the support is provided with a plurality of support grooves,
12-an adjusting mechanism, 121-an adjusting seat, 122-an adjusting block, 123-an adjusting screw rod, 124-an adjusting nut, 125-a forcing rod,
13-a platen;
2-the part of the transmitting device,
21-power mechanism, 211-air source, 212-hose, 213-switch valve, 214-connecting flange, 215-cylinder body, 216-piston rod,
22-damping mechanism, 221-damping cylinder, 222-buffer air source, 223-damping ring,
23-a guide slide carriage which guides the slide carriage,
24-a bearing table, wherein the bearing table is provided with a bearing plate,
25-a silencer;
3-aiming device, 31-sliding shaft, 32-connecting frame, 33-lifting rod, 34-laser emitter;
4-a dummy seat, wherein the dummy seat is provided with a seat body,
41-base, 411-guide rail, 412-slide block, 413-slewing bearing,
42-a pitch plate, wherein the pitch plate is provided with a pitch plate,
43-the main body of the seat,
44-adjusting device, 441-bearing seat, 442-screw rod, 443-nut seat, 444-connecting rod, 445-handle,
45-a straight-line sliding table,
46-ear plate.
Detailed Description
As shown in fig. 1, the horizontal impact test system for the unmanned aerial vehicle disclosed in the present embodiment includes a test platform 1, a launching device 2, a sighting device 3, and a dummy seat 4. The launching device and the aiming device are arranged on the test platform, the dummy seat is arranged on the foundation, and the horizontal distance between the dummy seat and the support at the tail end of the test platform is adjustable.
The test platform 1 is composed of a support 11, an adjusting mechanism 12 and a bedplate 13. The support 11 is frame-type support, and a plurality of supports are one row and stand on the basis, and platen 13 sets up on each support through adjustment mechanism 12, establishes slide rail 14 on platen 13's the tip so that launch unmanned aerial vehicle 5. When the device is arranged, the distance between the adjacent brackets is controlled to be 2.5m, and the length of the cantilever section of the bedplate does not exceed 0.5 m.
As shown in fig. 2, the adjusting mechanism 12 includes an adjusting seat 121, an adjusting block 122, an adjusting screw 123, and an adjusting nut 124. The adjusting seat 121 is an L-shaped seat body, a through hole is formed in the center of a vertical surface of the adjusting seat, an adjusting nut is arranged at the through hole, a plurality of mounting holes are formed in the horizontal plane of the adjusting seat, and the adjusting seat is arranged on the support in the horizontal plane and is locked by bolts penetrating through the mounting holes. The regulating block 122 is a frustum-shaped block, and is connected with the regulating screw by facing the vertical surface of the regulating seat at the large-diameter end of the regulating block, and a bearing seat is arranged outside the regulating screw to ensure the stability of connection and rotation, the other end of the regulating screw penetrates through a through hole and a regulating nut, and a force applying rod 125 is arranged outside the end of the regulating screw so as to control the rotation of the regulating screw, adjust the included angle between the regulating block and the horizontal plane, and finely adjust the positions of the upper part, the lower part, the left part and the right part of the bedplate in all directions, so that the accurate positioning of the high-speed cylinder in the launching device 2 can be realized.
As shown in fig. 1, the launching device 2 is composed of a power mechanism 21, a damping mechanism 22, a guide slide 23 and a bearing table 24.
As shown in fig. 3, the power mechanism 21 includes an air source 211, a hose 212, a switch valve 213, a connecting flange 214, and a high-speed cylinder. The high-speed cylinder has two parts, namely a cylinder body 215 and a piston rod 216. The cylinder body is made of No. 45 steel pipe, the inner hole is plated with hard chromium, and the surface roughness is not more than 0.4. The inner diameter is 180mm, the wall thickness is 15mm, and the piston rod is processed by 7050 forged aluminum, so that the emission quality can be effectively reduced. The stroke of the high-speed cylinder is 2000mm, the cylinder piston sealing ring adopts a customized high-speed wear-resistant heat-resistant metal sealing element, one end of the cylinder body is communicated with the switch valve through a connecting flange, and the other end of the switch valve is communicated with an air source through a hose. The cylinder body and the connecting flange are connected and positioned through the seam allowance, the cylinder body and the connecting flange are sealed in pairs through O-shaped rings, and the other end of the cylinder body is connected with the damping mechanism 22.
As shown in fig. 4, the damper mechanism 22 is constituted by a damper cylinder 221, a cushion air source 222, and a damper ring 223. The damping cylinder 221 is a cylinder with two open ends, one end is connected with the cylinder body, two ends of the cylinder wall are provided with radial holes, the radial hole near one end of the power mechanism is externally connected with the silencer 25, and the radial hole at the other end is connected with the buffer air source 222. The damping ring is coaxially arranged in the damping cylinder and is positioned between the two radial holes. The outer end of the piston rod penetrates through the damping cylinder and extends to the slide rail of the bedplate, a guide slide seat 23 is arranged between the extending section of the piston rod and the slide rail, and the outermost end of the piston rod is connected with a bearing platform 24. The plummer is C type frame, and its confined vertical section links to each other with the piston rod, and its inner chamber is used for bearing unmanned aerial vehicle. And the aiming device 3 is arranged on the slide rail so as to calibrate the launching device and the dummy on the dummy seat to be positioned on the same straight line.
As shown in fig. 5, the aiming device 3 includes a sliding shaft 31, a connecting frame 32, a lifting rod 33 and a laser emitter 34, wherein the laser emitter 34 is a laser pen. The sliding shaft is assembled on the sliding rail, the bottom edge of the connecting frame is connected to the sliding shaft and can rotate around the axial direction, the lifting rod is provided with the top edge of the connecting frame, and the laser emitter is connected to the bottom end of the lifting rod. The aiming device is placed on the central axis of the cylinder before the test, the connecting frame is adjusted and rotates around the sliding shaft, so that the emitted light of the laser emitter is positioned at the designated position of the test piece of the unmanned aerial vehicle, the central axis is quickly placed on the central axis through the platform processing, the laser is aimed at the direction parallel to the emitting direction, and the direction of measurement can be adjusted and adjusted to aim at the test dummy/high-value object placed on the dummy seat 4. The clamp is made of an aluminum alloy material, and the effective distance of the laser emitter is 50 m.
As shown in fig. 6 and 7, the dummy seat 4 includes a base 41, a pitch plate 42, a seat main body 43, and an adjustment device 44. The base is arranged on the foundation, the pitching plate is obliquely arranged, the bottom end of the pitching plate is hinged to the base, and the high end of the pitching plate is hinged to the base through the adjusting device; the seat body is connected to the pitch plate, and can slide and lock along the longitudinal direction of the pitch plate. When the adjustable seat is used, the pitching angle of the pitching plate is adjusted through the adjusting device, and the horizontal position of the seat body of the base is adjusted.
The base 41 is composed of a guide 411, a slider 412 and a pivoting support 413, and the pivoting support is provided with an ear seat 414 for mounting the tilting plate 42. During assembly, the guide rail is laid on the foundation, and one end of the guide rail is connected with the support at the tail end of the test platform. The slewing bearing is arranged on the guide rail through the sliding block, and the slewing bearing can slide along the guide rail so as to adjust the horizontal position of each part on the slewing bearing.
As shown in fig. 7, the pitching plate 42 is provided with a slide groove in which a linear slide table 45 is provided, and the seat main body 43 is fitted to a slide portion of the linear slide table, and the relative position of the seat main body and the pitching plate is adjusted by the linear slide table so as to adjust the height of the seat main body 3. A pair of ear plates 46 are arranged below the pitching plate 42, the ear plate at the lower end is hinged with the ear seat, and the ear plate at the upper end is hinged with the adjusting device 44. An angle display disc is arranged outside the ear plate at the lower end of the pitching plate, the angle display disc can be a universal protractor, and the pitching angle of the pitching plate can be measured by concentric centers of the protractor and the hinge shaft.
The adjusting device 44 includes a bearing seat 441, a lead screw 442, a nut seat 443, and a connecting rod 444; the pair of bearing seats are erected on the base and are positioned on the same straight line with the lug seats; the screw rod is assembled through two bearing seats and is kept in a horizontal state; the nut seat is connected to the screw rod, the rotation is converted into translation, and a hinge seat is arranged outside the nut seat; the two ends of the connecting rod are respectively provided with a hinged plate, the connecting rod is arranged in an inclined mode, the hinged plate at the lower end is hinged to a hinged seat outside the nut seat, and the hinged plate at the high end is hinged to an ear plate at the high end of the pitching plate. And the outer end of the screw rod 442 is provided with a handle 445 convenient to control, the screw rod is driven to rotate by rotating the handle, and the nut seat converts the rotation of the screw rod into translation, so that the angle of a connecting rod connected to the nut seat is changed, and the pitching adjustment of the pitching plate is realized.
During the concrete implementation, make the every single move board can satisfy the user demand of different model dummy at 0 to 30 within range through the design of lead screw length, namely make unmanned aerial vehicle can strike dummy head to chest scope.
When this kind of dummy seat drops into the use, according to the requirement of operating mode and the different models of dummy, adjust the inclination of every single move board through adjusting device, the regulation of dummy position is realized in the slip of cooperation seat main part on the every single move board, and unmanned aerial vehicle can strike dummy head to chest scope when guaranteeing the simulation, can satisfy the operational requirement of all kinds of dummy models and different operating modes through same seat, and the commonality is good, does benefit to and improves test efficiency, guarantees experimental progress.
In specific implementation, the material of the high-speed cylinder body is a forty-five steel pipe material, the inner hole is plated with hard chromium, and the surface roughness is not more than 0.4. An inner diameter of
The wall thickness is 15mm, and the piston rod adopts 7050 forged aluminum processing, can effectively alleviate the transmission quality. The stroke of the high-speed cylinder is 2000mm, the cylinder piston sealing ring adopts a customized high-speed wear-resistant heat-resistant metal sealing element, the rodless cavity of the high-speed cylinder is connected and positioned with the switch valve through the spigot, and the high-speed cylinder is sealed by the O-shaped ring. When the high-speed air cylinder is used, the switch valve is normally closed by pressurizing the air source when a transmitting instruction is not obtained, and high-pressure air does not exist in the high-speed air cylinder; after the emission instruction is obtained, the switch valve is opened, and high-pressure gas enters the cylinder without a rodIn the cavity, the clasper is loosened to release the piston rod.
And pressurizing the gas tank of the buffer gas source to 0.8MPa, impacting the piston of the arresting device after the piston reaches a set speed, and emitting the test piece according to the inertia principle. The gas tank is pre-pressurized, when the buffer piston moves rightwards, the pressure in the rodless cavity is increased and throttled to the gas tank through the metal gas tank, the buffer effect is achieved, and when the pressure is increased to the set pressure of the overflow valve, the pressure can be relieved through the throttle hole, so that the piston rod of the high-speed cylinder can be stably buffered and stopped.
The embodiment is used in combination with a control system during testing.
The control system is used for controlling the high-speed cylinder when the unmanned aerial vehicle is launched. The main idea is to use a computer, system software and the like to realize automatic testing, and the use is simple, convenient and safe. Through automatic control, errors caused by human factors are reduced; through the safety protection design of the system, the potential safety hazards of personnel and articles in the test process are reduced.
The control system mainly comprises an operation table, an acquisition controller, a speed measurement sensor, safety protection equipment and the like.
An operation table: the test system is placed in an operation room, consists of a dual piano type operation table and a computer system, and is a control center of the whole test system.
An acquisition controller: and receiving a command sent by the operating platform, and finishing data acquisition and system control, wherein the internal part of the system comprises an analog quantity acquisition resource, a switching value resource and a power supply module.
Safety protection equipment: the system comprises a video monitoring system, entrance guard monitoring, sound-light alarming and the like, provides a laboratory visual environment for operators, and provides emergency alarming and the like for whether observers evacuate all.
The working principle of the system is shown in fig. 8, an operation console is connected with an acquisition controller and monitoring equipment through Ethernet, and a mechanical button is provided for emission unlocking and emergency stop control; and the acquisition controller is used for providing an acquisition control channel and a power supply for the whole system.
The gas gun launcher: the electromagnetic valve control comprises air inlet of an air tank, air outlet of the air tank and air inlet of a launching chamber, a 24V DC power supply is switched on/off through a switching value channel in the acquisition controller, and the control is matched with a mechanical button of a console; pressure signal acquisition, namely monitoring the pressure signal through a pressure sensor with a digital display function, wherein a power supply of the pressure sensor is provided by an acquisition controller and is acquired by an analog channel; safety protection equipment: the monitoring signal is transmitted into the operation desk through the Ethernet, and the acousto-optic alarm, the entrance guard monitoring and the like are controlled, collected and provided with power supply through the collection controller.
And an industrial personal computer with reliable performance is selected as the operating console, system software is carried, and the operating console is connected with the acquisition controller through the Ethernet to complete system control and data display. And providing a mechanical button to finish launching unlocking and scram control.
The acquisition controller is a test device with comprehensive functions, is connected with the operation platform through the Ethernet and executes control commands and data acquisition work.
The air inlet and outlet control principle is shown in fig. 9:
the air inlet and outlet of the air gun launching device are controlled by an electromagnetic valve, and the valve is opened when the straight-through electromagnetic valve is electrified and closed when the straight-through electromagnetic valve is powered off. And the system software switches on and off the electromagnetic valve through the switching value channel.
The air inlet control signal of the air tank is low in normal state and is high in effectiveness. Namely, the valve is closed when the power is off, and the valve is opened when the power is on to charge the gas tank;
the air tank deflation control signal is default to high and low. Namely, the valve is closed when the power is off, and the valve is opened when the power is on to deflate the gas tank;
the emission chamber air inlet control signal is default low and highly effective. Namely, the valve is closed when the power is off, and the valve is opened when the power is on to charge the gas for the launching chamber.
The principle of pressure acquisition is shown in fig. 10, and strain type digital display pressure sensors are used for pressure acquisition and are respectively installed at the rear ends of an air inlet of an air tank and an air inlet of a launching chamber. The pressure sensor signal converts the pressure signal into a voltage signal, the voltage signal is collected by an analog channel, and the voltage signal is converted into the pressure signal through system software.
When the unmanned aerial vehicle is put into use, the aiming device is used for checking whether the test platform is aligned with the dummy seat, the aiming device is rotated after the alignment so that the unmanned aerial vehicle can be ejected, the unmanned aerial vehicle is placed on the bearing table after the alignment is corrected, the power is provided by the ejecting device so that the unmanned aerial vehicle has higher speed, then the damping mechanism acts so that the ejecting rod is gradually stopped, and the unmanned aerial vehicle is ejected under inertia and collides with the dummy on the dummy seat. Thereby realize ground high value target and dummy and receive the ground equivalent test of light small unmanned aerial vehicle collision, can inspect personnel or the ground high value target receive the damage degree of collision, for the affirmation and the verification of collision dynamics numerical model provide data support, for the use of civilian light small unmanned aerial vehicle, operation, protection and management and control specification provide effectual data and experimental support.
Claims (10)
1. The utility model provides an unmanned aerial vehicle horizontal impact test system which characterized in that: the system comprises a test platform, a launching device, a sighting device and a dummy seat;
the launching device comprises a power mechanism, a damping mechanism and a bearing table which are sequentially arranged on the test platform, wherein the power mechanism comprises a launching rod which penetrates through the damping mechanism to be connected with the bearing table;
the aiming device is arranged on the test platform and can rotate around the connecting shaft;
the distance between the dummy seat and the test platform is adjustable.
2. The horizontal impact test system for unmanned aerial vehicles of claim 1, wherein: the test platform comprises supports, adjusting mechanisms and a bedplate, wherein the supports are uniformly arranged, and the bedplate is arranged on the supports through the adjusting mechanisms.
3. The horizontal impact test system for unmanned aerial vehicles of claim 1, wherein: the adjusting mechanism comprises an adjusting seat, an adjusting block, an adjusting screw rod and an adjusting nut; the adjusting seat is an L-shaped seat body, a through hole is formed in the vertical surface of the adjusting seat, and the adjusting block is a frustum-shaped block; the adjusting seat is detachably connected with the support through a horizontal section of the adjusting seat, the adjusting nut is arranged at the through hole of the vertical section of the adjusting seat, the adjusting screw is in threaded connection with the adjusting nut, and a force applying rod is arranged outside one end of the adjusting screw, and the other end of the adjusting screw is connected with the large-diameter end of the adjusting block.
4. The horizontal impact test system for unmanned aerial vehicles of claim 1, wherein: the test platform further comprises a slide rail, and the slide rail is arranged on the bedplate.
5. The horizontal impact test system for unmanned aerial vehicles of claim 4, wherein: the power mechanism comprises an air source and a high-speed cylinder; the high-speed cylinder comprises a cylinder body and a piston rod, one end of the cylinder body is connected with an air source, the other end of the cylinder body is connected with the damping mechanism, the piston rod is coaxially arranged in the cylinder body, and the outer end of the piston rod penetrates through the damping mechanism to be connected with the bearing platform.
6. The dummy seat for the horizontal impact test of the unmanned aerial vehicle according to claim 5, wherein: and a guide sliding seat is arranged outside the piston rod and connected to the sliding rail.
7. The horizontal impact test system for unmanned aerial vehicles of claim 5, wherein: the damping mechanism comprises a damping cylinder, a buffering air source and a damping ring; radial holes are respectively formed in two ends of the wall of the damping cylinder, the silencer is connected to the outside of the radial hole at one end, the radial hole at the other end is communicated with a buffering air source, the inner diameter of the damping ring is matched with the outer diameter of the piston rod, and the damping ring is coaxially arranged in the damping cylinder.
8. The horizontal impact test system for unmanned aerial vehicles of claim 4, wherein: aiming device is including sliding axle, linking frame, lifter and laser emitter, and the axle that slides assembles on the slide rail, and the base of linking frame is connected and can be followed axial rotation in the epaxial of sliding, and the lifter sets up the linking frame topside, and laser emitter connects in the bottom of lifter.
9. The horizontal impact test system for unmanned aerial vehicles of claim 1, wherein: the dummy seat comprises a base, a pitching plate, a seat main body and an adjusting device; the pitching plate is assembled on the base through the adjusting device, the pitching angle of the pitching plate is adjusted by the adjusting device, and the seat body is connected to the pitching plate and can slide and be locked along the length direction of the pitching plate.
10. The horizontal impact test system for unmanned aerial vehicles of claim 9, wherein: the base comprises a guide rail, a sliding block and a slewing bearing, the guide rail is laid on the foundation, and the slewing bearing is arranged on the guide rail through the sliding block; the adjusting device comprises a bearing seat, a screw rod, a nut seat and a connecting rod, wherein a handle is arranged at the outer end of the screw rod so as to rotate; the pair of bearing seats are vertically arranged on the base, the screw rod is assembled with the two bearing seats, the nut seat is connected to the screw rod and converts rotation into translation, and the nut seat at one end of the connecting rod is connected and the other end of the connecting rod is hinged with the pitching plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
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| CN115144146A (en) * | 2022-08-31 | 2022-10-04 | 中国民航管理干部学院 | Unmanned aerial vehicle ground impact test device |
| CN117699047A (en) * | 2024-02-06 | 2024-03-15 | 中国科学院力学研究所 | Aircraft arresting comprehensive simulation test system |
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| CN117699047A (en) * | 2024-02-06 | 2024-03-15 | 中国科学院力学研究所 | Aircraft arresting comprehensive simulation test system |
| CN117699047B (en) * | 2024-02-06 | 2024-05-03 | 中国科学院力学研究所 | Aircraft arresting comprehensive simulation test system |
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