CN114148545B - Detection device for industrial design aircraft and application method thereof - Google Patents
Detection device for industrial design aircraft and application method thereof Download PDFInfo
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- CN114148545B CN114148545B CN202111484089.XA CN202111484089A CN114148545B CN 114148545 B CN114148545 B CN 114148545B CN 202111484089 A CN202111484089 A CN 202111484089A CN 114148545 B CN114148545 B CN 114148545B
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- 238000001514 detection method Methods 0.000 title claims abstract description 28
- 238000000034 method Methods 0.000 title claims abstract description 16
- 238000003825 pressing Methods 0.000 claims description 11
- 230000006835 compression Effects 0.000 claims description 8
- 238000007906 compression Methods 0.000 claims description 8
- 238000004891 communication Methods 0.000 claims 1
- 230000000694 effects Effects 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000523 sample Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
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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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- Aviation & Aerospace Engineering (AREA)
- Force Measurement Appropriate To Specific Purposes (AREA)
Abstract
The invention belongs to the field of aircrafts, in particular to a detection device for an industrial design aircrafts and a use method thereof, aiming at the problems that when the existing aircrafts detect braking distances, the test flying process is complex, time and labor are wasted, the braking distances are not known accurately, the detection speed is slow, and the existing detection requirements cannot be met.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a detection device for an industrial design aircrafts and a use method thereof.
Background
An aircraft is an instrument that flies within the atmosphere or outside the atmosphere in space (space). Aircraft fall into 3 categories: aircraft, spacecraft, rockets, and missiles. Flying in the atmosphere is known as an aircraft, such as a balloon, airship, airplane, etc. They fly by aerodynamic lift generated by static buoyancy of air or relative motion of air. In space flight, the aircraft is called a spacecraft, such as an artificial earth satellite, a manned spacecraft, a space probe, a space plane and the like. They get the necessary speed into space under the propulsion of the carrier rocket and then rely on inertia to do orbital motion similar to celestial bodies.
The aircraft is required to be detected during production, the braking distance of the aircraft is one of detection, the aircraft in the prior art is required to be flown by test and braked when the braking distance is detected, the braking distance is known, the test flight process is complex, time and labor are wasted, the braking distance is not known accurately enough, the detection speed is slow, and the existing detection requirement cannot be met, so that a detection device for an industrial design aircraft and a use method thereof are provided for solving the problems.
Disclosure of Invention
The invention aims to solve the defects that in the prior art, when an aircraft detects a braking distance, the aircraft needs to be flown and braked, and the braking distance is known, so that the aircraft is complex in the process of flying test, time-consuming and labor-consuming, the braking distance is not known accurately, the detection speed is slow, and the existing detection requirement cannot be met.
In order to achieve the above purpose, the present invention adopts the following technical scheme:
the utility model provides a detection device that industrial design aircraft was used, includes the test box, the equal fixedly connected with landing leg in bottom four corners of test box, one side inner wall sliding connection of test box has the mounting panel, the one end fixedly connected with baffle of mounting panel, the bottom inner wall fixedly connected with of test box is inconsistent with the fixed block of baffle, the bottom inner wall of test box is provided with the scale mark, one side of mounting panel is provided with the pointer, one side fixedly connected with first rubber pad of mounting panel, the bottom inner wall sliding connection of test box has the second sliding plate, two pressure springs of fixedly connected with symmetry setting between one side of second sliding plate and the one side inner wall of test box, two through-holes of symmetry setting have been seted up to the inside of second sliding plate, the inside slip of through-hole runs through there is first sliding plate, the inside of first sliding plate is provided with and is used for carrying out spacing subassembly to the second sliding plate, the bottom inner wall fixedly connected with first spring of through-hole, the top of first spring is inconsistent with the bottom of first sliding plate.
Preferably, the limiting component comprises a mounting groove formed in the first sliding plate, a clamping block penetrates through the mounting groove in a sliding mode, the bottom of the clamping block is fixedly connected with the same third spring between the bottom of the mounting groove and the inner wall of the bottom of the mounting groove, one side of the clamping block is abutted to one side of the second sliding plate and used for limiting the second sliding plate, and the second sliding plate can be guaranteed to be located at the same position during detection every time.
Preferably, two fixedly connected with same connecting plate between the first sliding plate, fixedly connected with same second spring between the bottom of connecting plate and the bottom inner wall of test box, the top fixedly connected with depression bar of connecting plate, the top fixedly connected with spacing ball of depression bar for control the lift of first sliding plate, convenient operation.
Preferably, a limiting block is fixedly connected to one side of the top of the first sliding plate and used for preventing the second sliding plate from falling off.
Preferably, the second rubber pad is fixedly connected with one side inner wall of the test box and used for playing a buffering function when the first rubber pad and the mounting plate are driven to move by the aircraft with the overlong braking distance, and prolonging the service life of the device.
Preferably, the top fixedly connected with symmetry of second sliding plate sets up two risers of top fixedly connected with symmetry setting of connecting plate, the chute has been seted up to the bottom of diaphragm, riser and chute cooperation use for drive the second sliding plate and resume initial position.
Preferably, two sliding grooves which are symmetrically arranged are formed in the inner wall of the bottom of the test box, two sliding blocks which are symmetrically arranged are fixedly connected to the bottom of the second sliding plate, and the bottom of each sliding block extends to the inside of each sliding groove and is in sliding connection with each sliding groove so as to ensure the moving stability of the second sliding plate.
A method of using a detection device for an industrial design aircraft, comprising the steps of:
s1, when the aircraft is used, the aircraft is placed on one side of a second sliding plate, a limiting ball is vertically pressed downwards, the limiting ball drives a pressing rod to vertically move downwards, a pressing rod drives a connecting plate and a vertical plate to vertically move downwards, the vertical plate is no longer positioned in a chute, meanwhile, the connecting plate drives a first sliding plate to vertically move downwards and extrude a second spring, the first sliding plate drives a clamping block to vertically move downwards, and at the moment, the second sliding plate pushes the aircraft to transversely move under the action of the elastic force of a pressure spring;
s2, the aircraft is abutted against one side of the first rubber pad, the first rubber pad and the mounting plate can simulate resistance in the flight process, when the second sliding plate pushes the aircraft to move, the speed of the aircraft during flight can be simulated, at the moment, the aircraft can push the first rubber pad to move transversely, the aircraft starts to decelerate gradually, therefore, the distance of the aircraft when the obstacle is detected to be decelerated can be detected, the length of the deceleration distance of the aircraft can be clearly known through the scale mark and the pointer, and whether the aircraft is qualified or not is judged;
s3, after the aircraft pops out, the limiting ball is loosened, the connecting plate vertically moves upwards under the action of the elastic force of the second spring, the connecting plate drives the compression rod and the first sliding plate to vertically move upwards, at the moment, the connecting plate drives the vertical plate to vertically move upwards, the vertical plate transversely moves along the chute and drives the transverse plate to transversely move towards the direction close to the connecting plate and extrude the pressure spring, the second sliding plate pushes the clamping block, the clamping block extrudes the third spring and vertically moves downwards until the second sliding plate moves to one side of the clamping block, and the next use is facilitated.
Compared with the prior art, the invention has the beneficial effects that:
1. when the aircraft is used, the aircraft is placed on one side of the second sliding plate, the limiting ball is vertically pressed downwards, the limiting ball drives the pressing rod to vertically move downwards, the pressing rod drives the connecting plate and the vertical plate to vertically move downwards, the vertical plate is no longer positioned in the chute, meanwhile, the connecting plate drives the first sliding plate to vertically move downwards and squeeze the second spring, the first sliding plate drives the clamping block to vertically move downwards, and at the moment, the second sliding plate pushes the aircraft to transversely move under the action of the elastic force of the pressure spring;
2. the first rubber pad and the mounting plate can simulate resistance in the flight process, the second sliding plate can simulate the speed of the aircraft when pushing the aircraft to move, the aircraft can push the first rubber pad to move transversely at the moment and enable the aircraft to start to decelerate gradually, so that the distance of the aircraft when detecting that an obstacle needs to decelerate can be detected, the length of the deceleration distance of the aircraft can be clearly known through the scale mark and the pointer, and whether the aircraft is qualified or not is judged;
3. after the aircraft pops out, loosen spacing ball, the connecting plate is vertical upwards to be removed under the elasticity effect of second spring, the connecting plate drives depression bar and first sliding plate vertical upwards to be removed, the connecting plate drives the vertical upward movement of riser this moment, the riser is along chute lateral shifting to drive the diaphragm to be close to the direction lateral shifting of connecting plate and extrude the pressure spring, the second sliding plate promotes the fixture block, the fixture block extrudees the third spring and vertical downward movement, until the second sliding plate removes to one side of fixture block, the next use of being convenient for.
According to the invention, the function of pushing the aircraft can be completed by pressing the limiting ball, the power given by the second sliding plate is consistent every time, so that the detection structure is accurate, the second sliding plate can be restored to the initial position after the limiting ball is loosened, the device is convenient to use for a plurality of times, time and labor are saved, the detection speed is high, the effect is good, the braking distance is clear, and the use is convenient.
Drawings
FIG. 1 is a schematic three-dimensional view of a first view angle of a detection device for an industrial design aircraft according to the present invention;
FIG. 2 is a schematic three-dimensional view of a second view of a detection device for an industrial design aircraft according to the present invention;
FIG. 3 is a three-dimensional view of a first view of a second slide plate and a connecting plate of the present invention;
FIG. 4 is a three-dimensional view of a second slide plate and a second view of a connecting plate according to the present invention;
FIG. 5 is a three-dimensional view of a second slide plate according to the present invention;
FIG. 6 is a three-dimensional view of a web of the present invention;
FIG. 7 is a three-dimensional cross-sectional view of a first slide plate according to the present invention;
fig. 8 is a three-dimensional cross-sectional view of a cross-plate in accordance with the present invention.
In the figure: 1. a support leg; 2. scale marks; 3. a test box; 4. a pointer; 5. a baffle; 6. a fixed block; 7. a chute; 8. a first sliding plate; 9. a cross plate; 10. a limit ball; 11. a second sliding plate; 12. a first rubber pad; 13. a mounting plate; 14. a second rubber pad; 15. a compression bar; 16. a clamping block; 17. a first spring; 18. a limiting block; 19. a through hole; 20. a slide block; 21. a riser; 22. a connecting plate; 23. a pressure spring; 24. a second spring; 25. a chute; 26. a third spring; 27. and a mounting groove.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments.
Example 1
Referring to fig. 1-8, a detection device for industrial design aircraft, including test box 3, the equal fixedly connected with landing leg 1 in bottom four corners of test box 3, one side inner wall sliding connection of test box 3 has mounting panel 13, the one end fixedly connected with baffle 5 of mounting panel 13, the bottom inner wall fixedly connected with of test box 3 and the fixed block 6 that the baffle 5 is inconsistent, the bottom inner wall of test box 3 is provided with scale mark 2, one side of mounting panel 13 is provided with pointer 4, one side fixedly connected with first rubber pad 12 of mounting panel 13, the bottom inner wall sliding connection of test box 3 has second sliding plate 11, two pressure springs 23 of fixedly connected with symmetry setting between one side of second sliding plate 11 and the one side inner wall of test box 3, two through-holes 19 of symmetry setting have been seted up to the inside of second sliding plate 11, the inside slip of through-hole 19 is run through and is provided with first sliding plate 8, the inside of first sliding plate 8 is provided with the spacing subassembly that is used for carrying out spacing to second sliding plate 11, the bottom inner wall fixedly connected with first spring 17 of through-hole 19, the top of first spring 17 is inconsistent with the bottom of first sliding plate 8.
Example two
Referring to fig. 1-8, a detection device for an industrial design aircraft comprises a test box 3, wherein four corners of the bottom of the test box 3 are fixedly connected with supporting legs 1, one side inner wall of the test box 3 is slidably connected with a mounting plate 13, one end of the mounting plate 13 is fixedly connected with a baffle 5, the bottom inner wall of the test box 3 is fixedly connected with a fixed block 6 which is in contact with the baffle 5, the bottom inner wall of the test box 3 is provided with scale marks 2, one side of the mounting plate 13 is provided with a pointer 4, one side of the mounting plate 13 is fixedly connected with a first rubber pad 12, the bottom inner wall of the test box 3 is slidably connected with a second sliding plate 11, two compression springs 23 which are symmetrically arranged are fixedly connected between one side of the second sliding plate 11 and one side inner wall of the test box 3, two through holes 19 which are symmetrically arranged are formed in the second sliding plate 11, the inner part of the through holes 19 is slidably penetrated by the first sliding plate 8, the first sliding plate 8 is internally provided with a limiting component for limiting the second sliding plate 11, the limiting component comprises a mounting groove 27 arranged in the first sliding plate 8, a clamping block 16 is penetrated through the mounting groove 27 in a sliding manner, the bottom of the clamping block 16 and the inner wall of the bottom of the mounting groove 27 are fixedly connected with one third spring 26, one side of the clamping block 16 is abutted against one side of the second sliding plate 11 and used for limiting the second sliding plate 11, the second sliding plate 11 can be further ensured to be positioned at the same position during each detection, the inner wall of the bottom of the through hole 19 is fixedly connected with a first spring 17, the top of the first spring 17 is abutted against the bottom of the first sliding plate 8, the two first sliding plates 8 are fixedly connected with one connecting plate 22, the bottom of the connecting plate 22 and the inner wall of the bottom of the test box 3 are fixedly connected with one second spring 24, the top fixedly connected with depression bar 15 of connecting plate 22, the top fixedly connected with spacing ball 10 of depression bar 15, be used for controlling the lift of first sliding plate 8, convenient operation, top one side fixedly connected with stopper 18 of first sliding plate 8, be used for avoiding second sliding plate 11 to drop, one side inner wall fixedly connected with second rubber pad 14 of test box 3, be used for braking the aircraft of overlength when driving first rubber pad 12 and mounting panel 13 and remove, buffer function can be played in the time of the life of extension device, two diaphragm 9 of the top fixedly connected with symmetry setting of second sliding plate 11, two riser 21 of the top fixedly connected with symmetry setting of connecting plate 22, chute 25 has been seted up to the bottom of diaphragm 9, riser 21 and chute 25 cooperation use, be used for driving second sliding plate 11 and resume initial position, two spouts 7 of symmetry setting are seted up to the bottom inner wall of test box 3, the bottom fixedly connected with two sliders 20 of second sliding plate 11 symmetry setting, the bottom of slider 20 extends to the inside of spout 7 and with spout 7 sliding connection, be used for guaranteeing the stability of second sliding plate 11 removal.
A method of using a detection device for an industrial design aircraft, comprising the steps of:
s1, when the aircraft is used, the aircraft is placed on one side of the second sliding plate 11, the limiting ball 10 is vertically pressed downwards, the limiting ball 10 drives the compression rod 15 to vertically move downwards, the compression rod 15 drives the connecting plate 22 and the vertical plate 21 to vertically move downwards, the vertical plate 21 is not positioned in the chute 25 any more, meanwhile, the connecting plate 22 drives the first sliding plate 8 to vertically move downwards and extrude the second spring 24, the first sliding plate 8 drives the clamping block 16 to vertically move downwards, and at the moment, the second sliding plate 11 pushes the aircraft to transversely move under the action of the elastic force of the pressure spring 23;
s2, the aircraft is abutted against one side of the first rubber pad 12, the first rubber pad 12 and the mounting plate 13 can simulate resistance in the flight process, when the second sliding plate 11 pushes the aircraft to move, the speed of the aircraft during flight can be simulated, at the moment, the aircraft can push the first rubber pad 12 to move transversely, and the aircraft starts to decelerate gradually, so that the distance of the aircraft when the obstacle is detected to be decelerated can be detected, the length of the deceleration distance of the aircraft can be clearly known through the scale mark 2 and the pointer 4, and whether the aircraft is qualified or not is judged;
s3, after the aircraft pops out, the limiting ball 10 is loosened, the connecting plate 22 vertically moves upwards under the action of the elastic force of the second spring 24, the connecting plate 22 drives the compression rod 15 and the first sliding plate 8 to vertically move upwards, at the moment, the connecting plate 22 drives the vertical plate 21 to vertically move upwards, the vertical plate 21 transversely moves along the chute 25 and drives the transverse plate 9 to transversely move towards the direction close to the connecting plate 22 and press the pressure spring 23, the second sliding plate 11 pushes the clamping block 16, the clamping block 16 presses the third spring 26 and vertically moves downwards until the second sliding plate 11 moves to one side of the clamping block 16, and the next use is facilitated.
Working principle: when in use, the aircraft is placed on one side of the second sliding plate 11, the limiting ball 10 is vertically pressed downwards, the limiting ball 10 drives the pressing rod 15 to vertically move downwards, the pressing rod 15 drives the connecting plate 22 and the vertical plate 21 to vertically move downwards, the vertical plate 21 is not positioned in the chute 25 any more, meanwhile, the connecting plate 22 drives the first sliding plate 8 to vertically move downwards and press the second spring 24, the first sliding plate 8 drives the clamping block 16 to vertically move downwards, at the moment, the second sliding plate 11 pushes the aircraft to transversely move under the action of the elastic force of the pressure spring 23, the aircraft is in contact with one side of the first rubber pad 12, the first rubber pad 12 and the mounting plate 13 can simulate the resistance in the flight process, when the second sliding plate 11 pushes the aircraft to move, the speed of the aircraft can be simulated when the aircraft flies can be pushed, at the moment, the aircraft can push the first rubber pad 12 to transversely move, the aircraft begins to gradually decelerate, the distance used by the aircraft when the aircraft detects that the obstacle needs to decelerate can be detected, the length of the deceleration distance of the aircraft can be clearly known through the scale marks 2 and the pointer 4, whether the aircraft is qualified or not is judged, after the aircraft is ejected, the limiting ball 10 is loosened, the connecting plate 22 vertically moves upwards under the elastic force of the second spring 24, the connecting plate 22 drives the compression rod 15 and the first sliding plate 8 to vertically move upwards, at the moment, the connecting plate 22 drives the vertical plate 21 to vertically move upwards, the vertical plate 21 transversely moves along the chute 25 and drives the transverse plate 9 to transversely move towards a direction close to the connecting plate 22 and press the pressure spring 23, the second sliding plate 11 pushes the clamping block 16, the clamping block 16 presses the third spring 26 and vertically moves downwards until the second sliding plate 11 moves to one side of the clamping block 16, and the next use is facilitated.
The present invention is not limited to the above-mentioned embodiments, and any person skilled in the art, based on the technical solution of the present invention and the inventive concept thereof, can be replaced or changed within the scope of the present invention.
Claims (5)
1. The utility model provides a detection device for industrial design aircraft, includes test box (3), a serial communication port, the equal fixedly connected with landing leg (1) in bottom four corners of test box (3), one side inner wall sliding connection of test box (3) has mounting panel (13), one end fixedly connected with baffle (5) of mounting panel (13), the bottom inner wall fixedly connected with of test box (3) and fixed block (6) that baffle (5) are inconsistent, the bottom inner wall of test box (3) is provided with scale mark (2), one side of mounting panel (13) is provided with pointer (4), one side fixedly connected with first rubber pad (12) of one side of mounting panel (13), one side of bottom inner wall sliding connection of test box (3) has second sliding plate (11), two pressure springs (23) that fixedly connected with symmetry set up between one side inner wall of second sliding plate (11) and test box (3), two through-holes (19) that symmetry set up are seted up to the inside sliding plate (8) of through-hole (19), first sliding plate (8) are used for carrying out spacing subassembly (17) are located to inside sliding plate (8), the top of the first spring (17) is in contact with the bottom of the first sliding plate (8);
the limiting assembly comprises a mounting groove (27) formed in the first sliding plate (8), a clamping block (16) is penetrated in the mounting groove (27) in a sliding manner, the bottom of the clamping block (16) is fixedly connected with the same third spring (26) between the bottom of the mounting groove (27) and the inner wall of the bottom of the mounting groove, and one side of the clamping block (16) is abutted against one side of the second sliding plate (11);
the two first sliding plates (8) are fixedly connected with the same connecting plate (22), the bottom of the connecting plate (22) and the inner wall of the bottom of the test box (3) are fixedly connected with the same second spring (24), the top of the connecting plate (22) is fixedly connected with a pressing rod (15), and the top of the pressing rod (15) is fixedly connected with a limiting ball (10);
the top fixedly connected with symmetry of second sliding plate (11) sets up two diaphragm (9), the top fixedly connected with symmetry of connecting plate (22) sets up two riser (21), chute (25) have been seted up to the bottom of diaphragm (9), riser (21) and chute (25) cooperation use.
2. The detection device for an industrial design aircraft according to claim 1, wherein a limiting block (18) is fixedly connected to one side of the top of the first sliding plate (8).
3. The detection device for an industrial design aircraft according to claim 1, wherein a second rubber pad (14) is fixedly connected to an inner wall of one side of the test box (3).
4. The detection device for the industrial design aircraft according to claim 1, wherein two sliding grooves (7) symmetrically arranged are formed in the inner wall of the bottom of the test box (3), two sliding blocks (20) symmetrically arranged are fixedly connected to the bottom of the second sliding plate (11), and the bottoms of the sliding blocks (20) extend to the inside of the sliding grooves (7) and are in sliding connection with the sliding grooves (7).
5. The method of using a detection device for an industrial design aircraft according to any one of claims 1-4, comprising the steps of:
s1, when the aircraft is used, the aircraft is placed on one side of a second sliding plate (11), the limiting ball (10) is vertically pressed downwards, the limiting ball (10) drives the pressing rod (15) to vertically move downwards, the pressing rod (15) drives the connecting plate (22) and the vertical plate (21) to vertically move downwards, the vertical plate (21) is not positioned in the chute (25) any more, meanwhile, the connecting plate (22) drives the first sliding plate (8) to vertically move downwards and press the second spring (24), the first sliding plate (8) drives the clamping block (16) to vertically move downwards, and at the moment, the second sliding plate (11) pushes the aircraft to transversely move under the elastic force of the pressure spring (23);
s2, the aircraft is abutted against one side of the first rubber pad (12), the first rubber pad (12) and the mounting plate (13) can simulate resistance in the flight process, the second sliding plate (11) can simulate the speed of the aircraft when pushing the aircraft to move, the aircraft can push the first rubber pad (12) to move transversely at the moment, the aircraft starts to decelerate gradually, therefore, the distance of the aircraft when detecting that an obstacle needs to decelerate can be detected, the length of the deceleration distance of the aircraft can be clearly known through the scale mark (2) and the pointer (4), and whether the aircraft is qualified or not is judged;
s3, after the aircraft pops out, the limiting ball (10) is loosened, the connecting plate (22) vertically moves upwards under the action of the elastic force of the second spring (24), the connecting plate (22) drives the compression rod (15) and the first sliding plate (8) to vertically move upwards, at the moment, the connecting plate (22) drives the vertical plate (21) to vertically move upwards, the vertical plate (21) transversely moves along the chute (25) and drives the transverse plate (9) to transversely move towards the direction close to the connecting plate (22) and extrude the pressure spring (23), the second sliding plate (11) pushes the clamping block (16), and the clamping block (16) extrudes the third spring (26) and vertically moves downwards until the second sliding plate (11) moves to one side of the clamping block (16) so as to be convenient for next use.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202111484089.XA CN114148545B (en) | 2021-12-07 | 2021-12-07 | Detection device for industrial design aircraft and application method thereof |
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| CN202111484089.XA CN114148545B (en) | 2021-12-07 | 2021-12-07 | Detection device for industrial design aircraft and application method thereof |
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| CN114148545B true CN114148545B (en) | 2023-10-31 |
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| 薛志鹏.扁簧式起落架无人机着陆滑跑关键技术研究.《博士论文全文数据库 工程科技Ⅱ辑》.2015,第1-231页. * |
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