CN218858709U - Power test bed for electric vertical take-off and landing aircraft with tilt rotor - Google Patents
Power test bed for electric vertical take-off and landing aircraft with tilt rotor Download PDFInfo
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- CN218858709U CN218858709U CN202223395669.4U CN202223395669U CN218858709U CN 218858709 U CN218858709 U CN 218858709U CN 202223395669 U CN202223395669 U CN 202223395669U CN 218858709 U CN218858709 U CN 218858709U
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Abstract
The utility model discloses a power test bed of a tilt rotor electric vertical take-off and landing aircraft, which comprises a bed base component, a power unit of the tilt rotor electric vertical take-off and landing aircraft, a simulation wing component and a tilt measurement unit; the tilting measurement unit comprises a tilting shaft assembly, a tension and torque measurement assembly and a tilting steering engine assembly, and the power unit is connected with the tension and torque measurement assembly; the tilting shaft assembly is connected with the simulation wing assembly, and a pull pressure sensor is arranged on the simulation wing assembly; and a tension-torsion composite sensor and an inclination angle sensor are arranged on the tension and torque measuring component. The utility model provides a test bench can develop the power pack's of the electronic VTOL aircraft of rotor that verts performance test, and the steady state performance, dynamic response, rotor and the wing of power pack influence each other and study, provides the means that the power performance is effectively verified for the development of new configuration aircraft.
Description
Technical Field
The utility model relates to an aircraft field, in particular to electronic VTOL aircraft power test bench of rotor verts.
Background
No matter the traditional navigation aircraft adopting a piston engine and a propeller as power or the electric aircraft adopting a motor and a propeller as power, in the process of aircraft development, in order to verify the functions, performance, reliability and the like of a power unit, a ground test of the power unit needs to be carried out. The power unit test bench is used for serving the developed aircraft, and different aircraft configurations have different power unit test requirements. For example, for a fixed-wing aircraft, a performance test of a power unit in the horizontal direction is mainly carried out; and for a rotor aircraft, a performance test of a power unit in the vertical direction is mainly carried out.
For the existing common aircraft power unit test bench, the following problems mainly exist: (1) Corresponding to the aircraft, the performance test of the power unit in one direction of horizontal or vertical can be carried out, and the performance test of the power unit at different angles cannot be carried out. (2) The dynamic performance test of the power unit in the tilting transition process cannot be completed.
Along with the rapid development of the electric vertical take-off and landing aircraft with the tilting rotors at home and abroad in recent years, new requirements are provided for a power unit test bed, tests in the horizontal direction and the vertical direction of the power unit are required to be carried out, tests in the dynamic performance of the tilting transition state of the power unit can be carried out, and tests in the mutual influence between the rotors and the wings are carried out. Based on this, the utility model discloses found a test bench that is used for electronic VTOL aircraft power unit of rotor that verts.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a electronic VTOL aircraft power test bench of rotor verts, including rack base subassembly 1, the power unit 2 of the electronic VTOL aircraft of rotor verts, emulation wing subassembly 3 and the measuring unit 4 that verts, the measuring unit 4 that verts includes motor installing support 41, the axle subassembly 42 that verts, pulling force and torque measurement subassembly 43 and the steering wheel subassembly 44 that verts, power unit 2 passes through rotation axis connection with pulling force and torque measurement subassembly 43, the axle subassembly 42 that verts is fixed in pulling force and torque measurement subassembly 43 top, the steering wheel subassembly 44 that verts is fixed in pulling force and torque measurement subassembly 43 below. A pull pressure sensor 33 is arranged on the simulation wing assembly 3 to measure the pressure of the downwash airflow of the rotor wing on the wing; a tension-torsion composite sensor 434 and an inclination angle sensor 438 are arranged on the tension and torque measuring assembly 43, and tension, torque and inclination angle tests are carried out; the rack base assembly 1 comprises a 0-degree limiting support, a 90-degree limiting support, a 15,0-degree limiting support and a 90-degree limiting support, and the tilting measurement unit 4 is subjected to limiting protection in a horizontal 0-degree and vertical 90-degree state, and the tilting steering engine assembly 44 is fixed on the tilting steering engine mounting support 15.
As above, the power test bed for the electric VTOL aircraft with the tilt rotor wings, wherein the bed base assembly 1 further comprises an underframe 11 and a mounting plate 12, the underframe 11 is formed by vertically welding a transverse frame and a vertical frame and is supported and fixed between the transverse frame and the vertical frame through an inclined frame, the mounting plate 12 is fixed at the top of the vertical frame, the mounting plate 12 is used for mounting the simulation wing assembly 3, and the vertical frame is laterally provided with a 0-degree limiting support 13, a 90-degree limiting support 14 and a tilt steering engine mounting support 15.
The power test bench for the tilt rotor electric vertical take-off and landing aircraft comprises an outer skin 31, a frame 32 and four pull pressure sensors 33, wherein the outer skin 31 is wrapped on the frame 32, the four pull pressure sensors 33 are mounted at the bottom of the frame 32, and the pressure of rotor downwash airflow on the simulated wings is measured through the four pull pressure sensors 33.
According to the power test bench for the tilt rotor electric VTOL aircraft, the tilt measurement unit 4 further comprises the motor mounting bracket 41 and the tilt shaft assembly 42, one end of the motor mounting bracket 41 is connected with the motor of the power unit 2, and the other end of the motor mounting bracket 41 is connected with the tension and torque measurement assembly 43.
The power test bed for the tilt rotor electric vertical take-off and landing aircraft comprises a tilt shaft assembly 42, wherein the tilt shaft assembly 42 comprises two bearing assemblies 421, a tilt shaft 422, stop nails 423, two stroke micro switches 424 and three fixing seats 425, each bearing assembly 421 comprises a bearing and a bearing base, the bearing is sleeved on the tilt shaft 422, each bearing assembly 421 rotates around the tilt shaft 422, each stop nail 423 rotates together with the corresponding bearing assembly 421, when each stop nail 423 contacts with each stroke micro switch 424, each stroke micro switch 424 sends a stop signal to a test bed control system, and the test bed control system can perform power-off protection on the test bed; the tilting shaft 422 is fixed on the mounting plate 12 through three fixing seats 425; tilt shaft assembly 42 is secured to the base plate of tension and torque measuring assembly 43 by two bearing assemblies 421.
The power test bed for the electric vertical take-off and landing aircraft with the tilt rotor wing comprises the power test bed, wherein the tension and torque measuring assembly 43 further comprises two connecting flanges 431, two linear sliding bearings 432, a connecting shaft 433, a rear seat 435, a bottom plate 436 and a protection limiting block 437; the two connecting flanges 431 respectively connect the connecting shaft 433 with the motor mounting bracket 41 and the tension-torsion composite sensor 434 to transmit tension and torque; the two linear sliding bearings 432 are sleeved on the connecting shaft 433 and used for supporting the connecting shaft 433.
The tilt rotor electric vertical take-off and landing aircraft power test bench is characterized in that the tilt steering engine assembly 44 comprises a mounting seat 441, a tilt steering engine 442, an adapter 443, a tilt rocker arm 444 and a plug bolt 445; the mounting seat 441 is fixed on the tilting steering engine mounting bracket 15 through a fastener, the output end of the tilting steering engine 442 is connected with the tilting rocker arm 444 through the adapter 443, the tilting rocker arm 444 is connected through the plug bolt 445, and the tilting rocker arm 444 is fixed on the bottom plate 436 through the fastener.
Compared with the prior art, the utility model discloses following beneficial effect has: the utility model provides a test bench can develop the power pack's of the electronic VTOL aircraft of rotor that verts performance test, and the steady state performance, dynamic response, rotor and the wing of power pack influence each other and study, provides the means that the power performance is effectively verified for the development of new configuration aircraft.
Drawings
FIGS. 1 to 5 are views showing the structure of a test bed;
FIG. 6 is a schematic view of a gantry base assembly;
FIGS. 7 and 8 are schematic views of simulated wing components;
FIGS. 9 to 11 are schematic views of a tilt measuring unit;
FIG. 12 is a schematic view of a tilt shaft assembly;
FIG. 13 is a schematic view of a tension and torque measuring assembly;
fig. 14 is a schematic view of a tilt steering engine assembly.
In the figure: 1. a gantry base assembly; 11. a chassis; 12. mounting a plate; 13. a 0 degree limit bracket; 14. a 90-degree limiting bracket; 15. a tilting steering engine mounting bracket; 2. a power unit; 3. simulating a wing assembly; 31. an outer skin; 32. a frame; 33. a pull pressure sensor; 4. a tilt measurement unit; 41. a motor mounting bracket; 42. a tilt shaft assembly; 43. a tension and torque measuring assembly; 44. a tilt steering engine assembly; 421. a bearing assembly; 422. a tilt shaft; 423. a stop pin; 424. a travel microswitch; 425. a fixed seat; 431. a connecting flange; 432. a linear sliding bearing; 433. a connecting shaft; 434. a tension-torsion composite sensor; 435. a rear seat; 436. a base plate; 437. a protection limiting block; 438. a tilt sensor; 441. a mounting seat; 442. a tilting steering engine; 443. an adapter; 444. a tilt rocker arm; 445. and (5) plugging bolts.
Detailed Description
In order to make the technical means, creation features, achievement purposes and functions of the present invention easy to understand, the present invention is further described below with reference to the following embodiments.
In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "front end", "rear end", "both ends", "one end", "the other end" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element to which the reference is made must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "disposed," "connected," and the like are to be construed broadly, and for example, "connected" may be either fixedly connected or detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood as a specific case by those skilled in the art.
Fig. 1-5 show an isometric view of a test stand, fig. 2 shows a side view of the test stand, fig. 3 shows a top view of the test stand, fig. 4 shows a tilt transition state of a power unit, and fig. 5 shows a 90 ° vertical state of the power unit.
The utility model provides an electronic VTOL aircraft power test bench of rotor verts, including rack base subassembly 1, the power unit 2 of the electronic VTOL aircraft of rotor verts, emulation wing subassembly 3 and the measuring unit 4 that verts, the measuring unit 4 that verts includes motor installing support 41, the axle subassembly 42 that verts, pulling force and torque measurement subassembly 43 and the steering wheel subassembly 44 that verts, power unit 2 passes through the rotation axis with pulling force and torque measurement subassembly 43 and is connected, the axle subassembly 42 that verts is fixed in pulling force and torque measurement subassembly 43 top, the steering wheel subassembly 44 that verts is fixed in pulling force and torque measurement subassembly 43 below. A pull pressure sensor 33 is arranged on the simulation wing assembly 3 to measure the pressure of the downwash airflow of the rotor wing on the wing; a tension-torsion composite sensor 434 and an inclination angle sensor 438 are arranged on the tension and torque measuring assembly 43, and tension, torque and inclination angle tests are carried out; the rack base assembly 1 comprises a 0-degree limiting support, a 90-degree limiting support, a tilting steering engine mounting support 15,0-degree limiting support and a 90-degree limiting support, the tilting measuring unit 4 is subjected to limiting protection in a horizontal 0-degree and vertical 90-degree state, and the tilting steering engine assembly 44 is fixed on the tilting steering engine mounting support 15.
Referring to fig. 6, the gantry base assembly 1 includes an underframe 11, a mounting plate 12, a 0 ° limit bracket 13, a 90 ° limit bracket 14, and a tilt steering engine mounting bracket 15. The underframe 11 is formed by perpendicularly welding a transverse frame and a vertical frame, the transverse frame and the vertical frame are supported and fixed through a slant frame, a mounting plate 12 is fixed at the top of the vertical frame, the mounting plate 12 is used for mounting a simulation wing assembly 3, a 0-degree limiting support 13 is laterally mounted on the vertical frame, a 90-degree limiting support 14 and a tilting steering engine mounting support 15 are laterally mounted on the vertical frame, the tilting steering engine mounting support 15 is used for mounting a tilting measurement unit 4, and the tilting measurement unit 4 is subjected to limiting protection in a horizontal 0-degree and vertical 90-degree state through the first limiting support 13 and the second limiting support 14.
Referring to fig. 7 and 8, the simulated wing assembly 3 is a wing of a simulated tilt rotor electric VTOL aircraft, and is used for measuring the mutual influence between the rotor and the wing when the power unit 2 is in a rotor mode vertical to 90 degrees. The artificial wing assembly 3 comprises an outer skin 31, a framework 32 and pull-pressure sensors 33, wherein the outer skin 31 is wrapped on the framework 32, the four pull-pressure sensors 33 are installed at the bottom of the framework 32, and the pressure of the downwash of the rotor wing on the artificial wing is measured through the four pull-pressure sensors 33.
Referring to fig. 9 to 11, fig. 9 is an isometric view of the tilt measuring unit, fig. 10 is a side view of the tilt measuring unit, and fig. 11 is a top view of the tilt measuring unit. The tilt measurement unit 4 includes a motor mounting bracket 41, a tilt shaft assembly 42, a tension and torque measurement assembly 43, and a tilt steering engine assembly 44. One end of the motor mounting bracket 41 is connected with the motor of the power unit 2, and the other end is connected with the tension and torque measuring assembly 43. The tilting shaft assembly 42 is fixedly connected with the base of the tension and torque measurement assembly 43 and is fixed above the base of the torque measurement assembly 43, and the tilting steering engine assembly 44 is fixedly connected with the base of the tension and torque measurement assembly 43 through a fastener and is fixed below the base of the torque measurement assembly 43.
As shown in fig. 12, the tilting shaft assembly 42 includes two bearing assemblies 421, a tilting shaft 422, a stop pin 423, two stroke microswitches 424 and three fixing seats 425, the bearing assemblies 421 include bearings and bearing bases, the bearings are sleeved on the tilting shaft 422, the bearing assemblies 421 rotate around the tilting shaft 422, the stop pin 423 rotates together with the middle bearing assemblies 421, the stroke microswitches 424 are fixed on the middle bearing assemblies 421, when the stop pin 423 contacts the stroke microswitches 424, the stroke microswitches 424 send stop signals to the test bed control system, and the test bed control system can perform power-down protection on the test bed; the tilting shaft 422 is fixed on the mounting plate 12 through three fixing seats 425; the tilt shaft assembly 42 is fixed to the base plate of the tension and torque measuring assembly 43 by two bearing assemblies 421.
The utility model discloses a test bench includes twice protection machanism: the first protection mechanism is a stop nail 423 and two stroke micro switches 424, when the motion angle of the power unit 2 exceeds-5 degrees to 95 degrees, the 423 stop nail can touch the 424 stroke micro switches to send a protection signal to a test bed control system, and the test bed can perform power-off protection to prevent the power unit from further rotating; the second protection mechanism is a first limit bracket 13 and a second limit bracket 14, and when the power unit 2 still continues to rotate, mechanical limit is performed through the first limit bracket 13 and the second limit bracket 14, so that the danger of contact with the ground or backward tilting of the rotor of the power unit 2 is avoided.
Referring to fig. 13, the tension and torque measuring assembly 43 includes two connecting flanges 431, two linear sliding bearings 432, a connecting shaft 433, a tension and torsion composite sensor 434, a rear seat 435, a bottom plate 436, a protective limiting block 437 and an inclination sensor 438. The two connecting flanges 431 respectively connect the connecting shaft 433 with the motor mounting bracket 41 and the tension-torsion composite sensor 434, and transmit tension and torque. Two straight line slide bearing 432 cup joint on connecting axle 433 for support connecting axle 433, because straight line slide bearing 432 has very low coefficient of friction, can reduce the frictional force of connecting axle 433 in the measurement process, improve pulling force and moment of torsion measurement accuracy. The tension-torsion composite sensor 434 is arranged at the rear end of the connecting shaft 433, the rear seat 435 is connected at the tail end of the connecting shaft 433, and the two linear sliding bearings 432 and the rear seat 435 are fixed on the bottom plate 436. The protection limiting block 437 is arranged on the tension-torsion composite sensor 434 and used for preventing the connecting shaft 433 from flying and falling off due to fracture failure of the tension-torsion composite sensor 434, and the inclination angle sensor is arranged on the base plate 436 and used for measuring the inclination angle of the aircraft.
Referring to fig. 14, tilt actuator assembly 44 includes a mounting block 441, a tilt actuator 442, an adapter 443, a tilt rocker 444, and a tuck bolt 445. The mount pad 441 is fixed on the steering wheel installing support 15 that verts through the fastener, and adapter 443 links to each other steering wheel 442 output and the rocking arm 444 that verts, beats bolt 445 through the stopper and connects, and the rocking arm 444 that verts passes through the fastener to be fixed on bottom plate 436.
When the output end of the tilting steering engine assembly 44 extends out or retracts, the driving pulling force and torque measuring assembly 43 and the motor mounting bracket 41 rotate around the tilting shaft 422 by driving the tilting rocker 444, and then the whole power unit 2 rotates around the tilting shaft 422. The tilt angle of the power unit 2 is measured by the tilt sensor 438.
The working principle is as follows: the utility model provides a test bench can accomplish power pulling force and moment of torsion test, the dynamic response test who verts the transition in-process under the different angles in 0 ~ 90 to and rotor and wing when perpendicular 90 influence each other is experimental. Fig. 1 shows the power unit 2 in a horizontal 0 ° state, and the test bench can perform tests such as tensile force and torque of the power unit. Fig. 4 shows the tilting transition state of the power unit, and fig. 5 shows the power unit in a vertical 90-degree state.
As shown in fig. 2, when entering the tilting transition state, the output end of the tilting steering engine 44 extends out, and by driving the tilting rocker 444, the pulling force and torque measuring assembly 43 and the motor mounting bracket 41 rotate around the tilting shaft 422, so that the whole power unit 2 rotates around the tilting shaft 422. The transition rate of movement that verts is realized through the rate of movement of control steering wheel 44, and specific numerical value sets up according to the demand. The tension, the torque, the tilting angle, the dynamic response and the like of the power unit 2 can be measured in the tilting transition process. After the power unit 2 leaves the horizontal position, the measured tension needs to be corrected according to the tilt angle, the mass of the power unit 2 and the tilt measuring unit 4.
As shown in fig. 3, when the test rig enters the vertical 90 ° state, the test rig can perform tests on the pull force, the torque, the tilt angle, the downward pressure of the rotor downwash on the wing, and the influence of the wing on the pull force of the rotor.
The foregoing shows and describes the basic principles and principal features of the invention, together with the advantages thereof. It will be understood by those skilled in the art that the present invention is not limited to the above embodiments, and that the foregoing embodiments and descriptions are provided only to illustrate the principles of the present invention without departing from the spirit and scope of the present invention. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (7)
1. A power test bench for a tilt rotor electric vertical take-off and landing aircraft is characterized by comprising a bench base assembly (1), a power unit (2) of the tilt rotor electric vertical take-off and landing aircraft, a simulation wing assembly (3) and a tilt measurement unit (4);
the tilting measurement unit (4) comprises a motor mounting bracket (41), a tilting shaft assembly (42), a tension and torque measurement assembly (43) and a tilting steering engine assembly (44), the power unit (2) is connected with the tension and torque measurement assembly (43) through a rotating shaft, the tilting shaft assembly (42) is fixed above the tension and torque measurement assembly (43), and the tilting steering engine assembly (44) is fixed below the tension and torque measurement assembly (43); a pull pressure sensor (33) is arranged on the simulation wing assembly (3) to measure the pressure of the downwash airflow of the rotor wing on the wing; a tension-torsion composite sensor (434) and an inclination angle sensor (438) are arranged on the tension and torque measuring assembly (43) to perform tension, torque and inclination angle tests;
the rack base assembly (1) comprises a 0-degree limiting support (13), a 90-degree limiting support (14) and a tilting steering engine mounting support (15), the 0-degree limiting support (13) and the 90-degree limiting support (14) carry out limiting protection on the tilting measurement unit (4) in a horizontal 0-degree and vertical 90-degree state, and the tilting steering engine assembly (44) is fixed on the tilting steering engine mounting support (15).
2. The tiltrotor electric VTOL aircraft power test bed according to claim 1, characterized in that, the bed base assembly (1) further comprises an underframe (11) and a mounting plate (12), the underframe (11) is composed of a horizontal frame and a vertical frame which are vertically welded and supported and fixed by an oblique frame, the mounting plate (12) is fixed at the top of the vertical frame, the mounting plate (12) is used for mounting the simulation wing assembly (3), and a 0-degree limit bracket (13), a 90-degree limit bracket (14) and a tilting steering engine mounting bracket (15) are laterally mounted on the vertical frame.
3. The tilt rotor electric VTOL aircraft power test bench according to claim 1, characterized in that the simulation wing assembly (3) further comprises an outer skin (31) and a frame (32), the outer skin (31) is wrapped on the frame (32), four pull pressure sensors (33) are installed at the bottom of the frame (32), and the pressure of the rotor downwash air flow to the simulation wing is measured through the four pull pressure sensors (33).
4. A tiltrotor electric vtol aircraft power test rig in accordance with claim 1, wherein the tilt measurement unit (4) further comprises a motor mounting bracket (41) and a tilt shaft assembly (42), one end of the motor mounting bracket (41) being connected to the motor of the power unit (2) and the other end being connected to the tension and torque measurement assembly (43).
5. A tiltrotor electric vtol aircraft power test rig according to claim 4, wherein the tilt shaft assembly (42) comprises two bearing assemblies (421), a tilt shaft (422), a detent pin (423), two travel microswitches (424), and three holders (425), the bearing assemblies (421) comprise bearings and bearing bases, the bearings are sleeved on the tilt shaft (422), the bearing assemblies (421) rotate around the tilt shaft (422), the detent pin (423) rotates with the bearing assemblies (421), the travel microswitches (424) are fixed on the bearing assemblies (421); the tilting shaft (422) is fixed on the mounting plate (12) through three fixing seats (425); the tilt shaft assembly (42) is fixed to the base plate of the tension and torque measuring assembly (43) by two bearing assemblies (421).
6. The tiltrotor electric vtol aircraft power test rig of claim 4, wherein the tension and torque measuring assembly (43) further comprises two attachment flanges (431), two linear sliding bearings (432), an attachment shaft (433), a rear seat (435), a base plate (436), and a protective stop block (437); the two connecting flanges (431) respectively connect the connecting shaft (433) with the motor mounting bracket (41) and the tension-torsion composite sensor (434) to transmit tension and torque; the two linear sliding bearings (432) are sleeved on the connecting shaft (433) and used for supporting the connecting shaft (433).
7. The tiltrotor electric vtol aircraft power test rig of claim 6, wherein the tilt steering engine assembly (44) comprises a mounting base (441), a tilt steering engine (442), an adapter (443), a tilt rocker arm (444), and a tuck bolt (445); the mounting seat (441) is fixed on the tilting steering engine mounting bracket (15) through a fastener, the output end of the tilting steering engine (442) is connected with the tilting rocker arm (444) through the adapter (443), the tilting rocker arm (444) is connected through a plug bolt (445), and the mounting seat is fixed on the bottom plate (436) through the fastener.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223395669.4U CN218858709U (en) | 2022-12-15 | 2022-12-15 | Power test bed for electric vertical take-off and landing aircraft with tilt rotor |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223395669.4U CN218858709U (en) | 2022-12-15 | 2022-12-15 | Power test bed for electric vertical take-off and landing aircraft with tilt rotor |
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| CN218858709U true CN218858709U (en) | 2023-04-14 |
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| CN202223395669.4U Active CN218858709U (en) | 2022-12-15 | 2022-12-15 | Power test bed for electric vertical take-off and landing aircraft with tilt rotor |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116654279A (en) * | 2023-05-26 | 2023-08-29 | 中国民航大学 | Rotor aerodynamic force integrated test platform |
| CN117842378A (en) * | 2024-01-15 | 2024-04-09 | 中国电信股份有限公司无人科技技术创新中心 | Performance test device for power component of rotor unmanned aerial vehicle |
-
2022
- 2022-12-15 CN CN202223395669.4U patent/CN218858709U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116654279A (en) * | 2023-05-26 | 2023-08-29 | 中国民航大学 | Rotor aerodynamic force integrated test platform |
| CN116654279B (en) * | 2023-05-26 | 2023-12-19 | 中国民航大学 | Rotor aerodynamic force integrated test platform |
| CN117842378A (en) * | 2024-01-15 | 2024-04-09 | 中国电信股份有限公司无人科技技术创新中心 | Performance test device for power component of rotor unmanned aerial vehicle |
| CN117842378B (en) * | 2024-01-15 | 2024-06-11 | 中国电信股份有限公司无人科技技术创新中心 | Performance test device for power component of rotor unmanned aerial vehicle |
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