CN216734826U - Static test device for target drone - Google Patents
Static test device for target drone Download PDFInfo
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- CN216734826U CN216734826U CN202123175641.5U CN202123175641U CN216734826U CN 216734826 U CN216734826 U CN 216734826U CN 202123175641 U CN202123175641 U CN 202123175641U CN 216734826 U CN216734826 U CN 216734826U
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Abstract
The utility model provides a target drone static test device, which is used for the static test of a target drone and comprises a test platform, a first counter-force steel frame, a second counter-force steel frame, a launching load loading device, an parachute opening recovery load loading device and a landing load loading device; the first reaction steel frame and the second reaction steel frame are arranged on the test platform; the target drone aircraft body is arranged on the first counter-force steel frame, and one end of the target drone aircraft body is in threaded connection with the second counter-force steel frame; the first counter-force steel frame is provided with a launching load loading device and an umbrella opening recovery load loading device; and the first counterforce steel frame is provided with a landing load loading device. The utility model discloses target drone static test device, simple structure is practical, and the loading mode is stable, and loading power size, direction are adjustable, and easily operation can satisfy target drone static test technical requirement, can be used to target drone static test field.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicle static test, in particular to target drone static test device.
Background
The target drone is an important branch in the family of unmanned aerial vehicles, is mainly used for simulating various air moving targets and is matched with air defense army training, live ammunition shooting and various air defense weapon efficiency identifications. As a consumable device, low cost is one of the main evaluation indexes of the drone.
The target drone relates to various load working conditions from launching to recovering, including a launching load working condition, a flight load working condition, an parachute opening and recovering load working condition, a landing load working condition and the like. The launching load, the parachute opening recovery load and the landing load in the load working conditions mainly act on the body in the form of large concentrated force, and the three load working conditions are also the most serious load working conditions in the structural analysis of the target drone.
At present, most of devices aiming at the static test of the target drone can only meet the loading of a single working condition. Even can satisfy the multi-operating mode loading, the testing arrangement is also comparatively huge, and is with high costs, and the operation is complicated, and test site environment requires highly.
SUMMERY OF THE UTILITY MODEL
For solving the technical problem, the utility model provides a target drone static test device, simple structure can adapt to multiple model, and is with low costs, easy operation, and is not high to the test site environmental requirement.
The technical scheme of the utility model is that:
a static test device of a target drone, which is used for the static test of the target drone,
the device comprises a test platform, a first counterforce steel frame, a second counterforce steel frame, a launching load loading device, an umbrella opening and recovering load loading device and a landing load loading device;
the first reaction steel frame and the second reaction steel frame are arranged on the test platform;
the target drone aircraft body is arranged on the first counter-force steel frame, and one end of the target drone aircraft body is in threaded connection with the second counter-force steel frame;
the first counter-force steel frame is provided with a launching load loading device and an umbrella opening recovery load loading device;
and the first counterforce steel frame is provided with a landing load loading device.
The first counter-force steel frame is a rectangular frame steel frame, the target drone aircraft body is installed in the middle of the rectangular frame steel frame through a fixing piece, and the axis of the target drone aircraft body is parallel to the test platform.
The launching load loading device comprises a launching loading actuator cylinder, a launching loading actuator cylinder mounting seat, a launching actuator cylinder connecting rod and a pressure sensing device;
the launching loading actuator cylinder mounting base is fixedly mounted on the first reaction steel frame;
the bottom of the launching loading actuator cylinder is arranged on the launching loading actuator cylinder mounting seat;
the top of the launching and loading actuating cylinder is connected with the pressure sensing device;
a launching cone head is arranged on the target drone body;
and two ends of the connecting rod of the launching actuating cylinder are respectively connected with the launching conical head and the pressure sensing device.
The parachute opening recovery load loading device comprises a parachute opening loading actuator cylinder and a first steel wire rope;
the first reaction steel frame is provided with a beam, and the beam can be arranged at different positions of the first reaction steel frame;
the bottom of the parachute opening loading actuator cylinder is hinged to the cross beam;
a connecting point of a front umbrella rope of the target drone body is arranged on the drone body;
two ends of the first steel wire rope are respectively connected with a front umbrella rope connecting point of the machine body and the top of the umbrella opening loading actuating cylinder;
and a first tension sensing device is arranged on the first steel wire rope.
The landing load loading device comprises a landing loading actuator cylinder and a second steel wire rope;
an engine simulation dummy piece is arranged at the tail part of the target drone aircraft body;
the bottom of the landing loading actuator cylinder is hinged to the test platform, two ends of the second steel wire rope are respectively connected with the engine simulation dummy piece and the top of the landing loading actuator cylinder, the second steel wire rope is provided with a second tension sensing device, and the engine simulation dummy piece is connected with an engine frame.
The cross beam is provided with a first hinged joint, and the bottom of the umbrella opening loading actuating cylinder is hinged to the first hinged joint.
And the bottom of the landing loading actuator cylinder is hinged to the landing loading actuator cylinder connecting joint.
The fixing piece is a supporting clamping plate assembly, and the number of the supporting clamping plate assemblies is more than two groups.
The support clamping plate assembly comprises a support clamping plate and a root connection angle material, a groove matched with the cambered surface of the target drone aircraft body is formed in the support clamping plate, the connection angle material is arranged at each of two ends of the support clamping plate, and the connection angle material is installed on the first counter-force steel frame.
The second reaction steel frame is a triangular steel frame, and a vertical plate of the triangular steel frame is in threaded connection with the front end of the drone aircraft body.
Compared with the prior art, the utility model discloses target drone static test device, simple structure is practical, under the prerequisite of not changing experimental frock, can satisfy the loading of big concentrated loads such as target drone transmission load, parachute-opening recovery load, landing load. The loading mode is stable, the loading force is adjustable in size and direction, the operation is easy, the technical requirements of the target drone static test can be met, and the method can be used in the field of the target drone static test.
Drawings
FIG. 1 is a general schematic view of the static test device of the target drone of the utility model;
FIG. 2 is a side view of the static test device of the target drone of the present invention;
FIG. 3 is a schematic view of a support card assembly;
FIG. 4 is a schematic diagram of an engine simulation dummy;
in the figure, 1, test platform; 2. a first reaction steel frame; 3. a second reaction steel frame; 4. a target drone fuselage; 5. supporting the clamping plate assembly; 6. a supporting clamping plate; 7. connecting angle bars; 8. a launch load ram; 9. a launch loading actuator cylinder mounting base; 10. a firing ram connecting rod; 11. a launching cone head; 12. a pressure sensing device; 13. the parachute opening loads the actuator cylinder; 14. a first tension sensing device; 15. a first wire rope; 16. a first articulation joint; 17. a connecting point of the umbrella rope in front of the machine body; 18. a landing load actuator; 19 landing load ram connection joints; 20. a second wire rope; 21. simulating a dummy part by the engine; 22. a cross beam; 23. an engine frame; 24. a second tension sensor device.
Detailed Description
In order to make the technical field better understand the solution of the present invention, the following detailed description of the present invention is provided with reference to the accompanying drawings and the detailed description.
The utility model adopts a progressive description method.
With reference to fig. 1 to 4, a static test device for a target drone is used for static test of the target drone,
the device comprises a test platform 1, a first counterforce steel frame 2, a second counterforce steel frame 3, a launching load loading device, an umbrella opening and recovering load loading device and a landing load loading device;
the first reaction steel frame 2 and the second reaction steel frame 3 are arranged on the test platform;
the target drone aircraft body 4 is arranged on the first counter-force steel frame 2, and one end of the target drone aircraft body 4 is in threaded connection with the second counter-force steel frame 3;
the first counterforce steel frame 2 is provided with a launching load loading device and an umbrella opening recovery load loading device;
and a landing load loading device is arranged on the first counterforce steel frame 2.
Further, the first counter-force steel frame 2 is a rectangular frame steel frame, the target drone aircraft body 4 is installed in the middle of the rectangular frame steel frame through a fixing piece, and the axis of the target drone aircraft body 4 is parallel to the test platform.
Furthermore, the launching load loading device comprises a launching loading actuator cylinder 8, a launching loading actuator cylinder mounting seat 9, a launching actuator cylinder connecting rod 10 and a pressure sensing device 12;
the launching loading actuator cylinder mounting base 9 is fixedly mounted on the first reaction steel frame 2;
the bottom of the launching loading actuator cylinder 8 is arranged on the launching loading actuator cylinder mounting seat 9;
the top of the launching loading actuating cylinder 8 is connected with the pressure sensing device 12;
the target drone fuselage 4 is provided with a launching cone head 11;
two ends of the launching actuating cylinder connecting rod 10 are respectively connected with the launching conical head 11 and the pressure sensing device 12.
Further, the parachute opening recovery load loading device comprises a parachute opening loading actuator 13 and a first steel wire rope 15;
the first reaction steel frame 2 is provided with a beam 22, and the beam 22 can be arranged at different positions of the first reaction steel frame 2;
the bottom of the parachute opening loading actuating cylinder 13 is hinged to the cross beam 22;
a machine body front umbrella rope connecting point 17 is arranged on the target machine body 4;
two ends of the first steel wire rope 15 are respectively connected with a front umbrella rope connecting point 17 of the machine body and the top of the umbrella opening loading actuating cylinder 13;
the first steel wire rope 15 is provided with a first tension sensing device 14.
Further, the landing load loading device comprises a landing loading actuator 18 and a second steel wire rope 20;
the tail part of the target drone aircraft body 4 is provided with an engine simulation dummy part 21;
the bottom of the landing loading actuator cylinder 18 is hinged to the test platform 1, two ends of the second steel wire rope 20 are respectively connected with the engine simulation dummy part 21 and the top of the landing loading actuator cylinder 18, the second steel wire rope 20 is provided with a second tension sensing device 24, and the engine simulation dummy part is connected with an engine frame 23.
Furthermore, a first hinge joint 16 is arranged on the first reaction steel frame 2, and the bottom of the parachute opening loading actuator 13 is hinged to the first hinge joint 16.
Furthermore, a landing loading actuator connecting joint 19 is arranged on the first reaction force steel frame 2, and the bottom of the landing loading actuator 18 is hinged to the landing loading actuator connecting joint 19.
Further, the fixing piece is a support clamping plate assembly 5, and the number of the support clamping plate assemblies 5 is more than two.
Further, support cardboard subassembly 5 including support cardboard 6 and 2 connection angle bars 7, be equipped with on the support cardboard 6 with 4 cambered surface complex recesses of target drone fuselage, the both ends of supporting cardboard 6 are equipped with respectively connect the angle bar, connect angle bar 7 and install on first counter-force steelframe 2.
Further, the second reaction steel frame 3 is a triangular steel frame, and a vertical plate of the triangular steel frame is in threaded connection with the front end of the drone aircraft body 4.
Further, the first reaction steel frame and the second reaction steel frame 3 are fixed on the test platform 1 through bolts.
The working principle is as follows:
in the static test process of the target drone, the target drone body 4 is installed on the test platform, the launching load loading device, the parachute opening recovery load loading device and the landing load loading device respectively act on the target drone body 4, and corresponding data are tested.
The two ends of the launching actuating cylinder connecting rod 10 are respectively connected with the launching conical head 11 and the pressure sensing device 12, the launching loading actuating cylinder 8 applies force to the launching actuating cylinder connecting rod 10, and the top of the launching loading actuating cylinder 8 is connected with the pressure sensing device 12; in the case of analog transmission, the pressure sensor system 12 can detect the corresponding data.
The parachute opening loading actuating cylinder 13 acts on a first steel wire rope 15, the first steel wire rope 15 is connected with a front parachute rope connecting point 17 arranged on the target drone fuselage 4, and when parachute opening loading is simulated, the first tension sensing device 14 can measure corresponding data
The bottom of the landing loading actuator cylinder 18 is hinged to the test platform 1, two ends of the second steel wire rope 20 are respectively connected to the engine simulation dummy part 21 and the top of the landing loading actuator cylinder 18, the second steel wire rope 20 is provided with a second tension sensing device 24, and the second tension sensing device 24 can measure corresponding data when landing is simulated.
The adjustment of the parachute opening load loading direction can be achieved by moving the cross beam 22 forward and backward.
The target drone fuselage 4 can be installed and disassembled by adjusting the installation position of the supporting clamp plate assembly 5 on the first counterforce steel frame 2, and the target drone fuselage 4 can also adapt to different types of target drone fuselages 4.
The connection angle 7 on the support cardboard subassembly 5 that is close to the front end can be installed different positions on the first reaction steelframe 2 realize reciprocating, connect reciprocating of angle 7, can drive support cardboard 6 and can reciprocate to the realization is fixed to the front end of target drone fuselage 4.
The connection angle 7 on the support cardboard subassembly 5 that is close to the rear end can be installed different positions on the first counter-force steelframe 2 realize horizontal axial displacement, and the axial displacement of connecting angle 7 can drive and support cardboard 6 and can carry out axial displacement to the realization is fixed to the rear end of target drone fuselage 4.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. A target drone static test device for the static test of the target drone is characterized in that:
the device comprises a test platform (1), a first counterforce steel frame (2), a second counterforce steel frame (3), a launching load loading device, an umbrella opening and recovering load loading device and a landing load loading device;
the first reaction steel frame (2) and the second reaction steel frame (3) are arranged on the test platform;
a target drone fuselage (4) is mounted on the first reaction steel frame (2), and one end of the target drone fuselage (4) is in threaded connection with the second reaction steel frame (3);
a launching load loading device and an umbrella opening recovery load loading device are arranged on the first counter-force steel frame (2);
and a landing load loading device is arranged on the first reaction steel frame (2).
2. The static test apparatus of an end effector as claimed in claim 1, wherein:
the first counter-force steel frame (2) is a rectangular frame steel frame, the target drone aircraft body (4) is installed in the middle of the rectangular frame steel frame through a fixing piece, and the axis of the target drone aircraft body (4) is parallel to the test platform.
3. The target drone static test apparatus of claim 2 wherein:
the launching load loading device comprises a launching loading actuator cylinder (8), a launching loading actuator cylinder mounting seat (9), a launching actuator cylinder connecting rod (10) and a pressure sensing device (12);
the launching loading actuator cylinder mounting base (9) is fixedly mounted on the first reaction steel frame (2);
the bottom of the launching loading actuator cylinder (8) is arranged on the launching loading actuator cylinder mounting seat (9);
the top of the launching loading actuating cylinder (8) is connected with the pressure sensing device (12);
a launching conical head (11) is arranged on the target drone fuselage (4);
two ends of the launching actuating cylinder connecting rod (10) are respectively connected with the launching conical head (11) and the pressure sensing device (12).
4. The static test apparatus of an end effector as claimed in claim 3, wherein:
the parachute opening recovery load loading device comprises a parachute opening loading actuator cylinder (13) and a first steel wire rope (15);
a cross beam (22) is arranged on the first counterforce steel frame (2);
the bottom of the parachute opening loading actuating cylinder (13) is hinged to the cross beam (22);
a front umbrella rope connecting point (17) of the target drone fuselage (4) is arranged;
two ends of the first steel wire rope (15) are respectively connected with a front umbrella rope connecting point (17) of the machine body and the top of the umbrella opening loading actuating cylinder (13);
and a first tension sensing device (14) is arranged on the first steel wire rope (15).
5. The static test apparatus of an end effector as claimed in claim 4, wherein:
the landing load loading device comprises a landing loading actuator cylinder (18) and a second steel wire rope (20);
an engine simulation dummy piece (21) is arranged at the tail part of the target drone aircraft body (4);
the bottom of the landing loading actuator cylinder (18) is hinged to the test platform (1), two ends of a second steel wire rope (20) are respectively connected with the top of the engine simulation dummy piece (21) and the top of the landing loading actuator cylinder (18), a second tension sensing device (24) is arranged on the second steel wire rope (20), and the engine simulation dummy piece is connected with an engine frame (23).
6. The static test apparatus of an end effector as claimed in claim 5, wherein:
the cross beam (22) is provided with a first hinged joint (16), and the bottom of the parachute opening loading actuating cylinder (13) is hinged to the first hinged joint (16).
7. The static test apparatus of an end effector as claimed in claim 6, wherein:
and a landing loading actuator cylinder connecting joint (19) is arranged on the first reaction force steel frame (2), and the bottom of the landing loading actuator cylinder (18) is hinged to the landing loading actuator cylinder connecting joint (19).
8. The static test apparatus of an end effector as claimed in claim 2, wherein:
the fixing piece is a support clamping plate assembly (5), and the number of the support clamping plate assemblies (5) is more than two.
9. The static test apparatus of an end effector as claimed in claim 8, wherein:
the support clamping plate assembly (5) comprises a support clamping plate (6) and 2 connecting angle bars (7), grooves matched with the arc surface of the target drone aircraft body (4) are formed in the support clamping plate (6), the connecting angle bars are arranged at two ends of the support clamping plate (6) respectively, and the connecting angle bars (7) are installed on the first counter-force steel frame (2).
10. The target drone static test apparatus of any one of claims 1 to 9 wherein:
the second reaction steel frame (3) is a triangular steel frame, and a vertical plate of the triangular steel frame is in threaded connection with the front end of the drone aircraft body (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123175641.5U CN216734826U (en) | 2021-12-16 | 2021-12-16 | Static test device for target drone |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123175641.5U CN216734826U (en) | 2021-12-16 | 2021-12-16 | Static test device for target drone |
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| Publication Number | Publication Date |
|---|---|
| CN216734826U true CN216734826U (en) | 2022-06-14 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202123175641.5U Active CN216734826U (en) | 2021-12-16 | 2021-12-16 | Static test device for target drone |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117104526A (en) * | 2023-09-21 | 2023-11-24 | 捷中鲨鱼(沧州)飞机制造有限公司 | Static test supporting device for front fuselage of light aircraft |
-
2021
- 2021-12-16 CN CN202123175641.5U patent/CN216734826U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117104526A (en) * | 2023-09-21 | 2023-11-24 | 捷中鲨鱼(沧州)飞机制造有限公司 | Static test supporting device for front fuselage of light aircraft |
| CN117104526B (en) * | 2023-09-21 | 2024-05-28 | 捷中鲨鱼(沧州)飞机制造有限公司 | Static test supporting device for front fuselage of light aircraft |
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