A nacelle parameter testing device for a vertical takeoff and landing aircraft

Abstract

The present invention discloses a nacelle parameter testing device for a vertical takeoff and landing aircraft, which includes a mounting assembly, a mounting bench, a servo motor, a rocker arm and a tension and compression sensor; the mounting assembly is used for mounting an engine, and a propeller is mounted at the driving end of the engine; the servo motor is fixed to one side of the mounting bench, the driving end of the servo motor is fixedly connected to one end of the tension and compression sensor, the other end of the tension and compression sensor is fixedly connected to the middle of the rocker arm, and the servo motor can drive the rocker arm to rotate through the tension and compression sensor; the first end of the rocker arm is rotatably connected to the upper end of the mounting bench, and the second end of the rocker arm extends out of the mounting bench from one side of the servo motor and is fixedly connected to the mounting assembly. In the present invention, by adding a tension and compression sensor between the servo motor and the rocker arm, when the servo motor drives the rocker arm to tilt the engine and the propeller, the pressure or tension received at the output end of the servo motor can be detected in real time to verify the accuracy of the design parameters and ensure that the nacelle design meets the aircraft requirements.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft performance detection, and particularly relates to a nacelle parameter testing device for a vertical takeoff and landing aircraft. Background Art

[0002] The tilt nacelle is a main component of a tiltrotor aircraft. In the aircraft structural design, various parameters such as the pulling force generated by the engine in the nacelle and the downward pressure on the wing will directly affect the design. Therefore, in the design stage, clarifying the parameters of the nacelle is the most basic requirement for the aircraft development stage. Summary of the Invention

[0003] An object of the present invention is to provide a new technical solution for a nacelle parameter testing device for a vertical takeoff and landing aircraft to solve the above problems. Through a simple tooling, at least one parameter in the nacelle can be tested and verified to ensure that the design parameters meet the requirements.

[0004] According to a first aspect of the present invention, there is provided a nacelle parameter testing device for a vertical takeoff and landing aircraft, including a mounting assembly, a mounting bench, a servo motor, a rocker arm, and a tension and compression sensor; the mounting assembly is used for mounting an engine, and a driving end of the engine is used for mounting a propeller; the servo motor is fixed to one side of the mounting bench, a driving end of the servo motor is fixedly connected to one end of the tension and compression sensor, the other end of the tension and compression sensor is fixedly connected to the middle of the rocker arm, and the servo motor can drive the rocker arm to rotate through the tension and compression sensor; a first end of the rocker arm is rotatably connected to an upper end of the mounting bench, a second end of the rocker arm extends out of the mounting bench from one side of the servo motor and is fixedly connected to the mounting assembly.

[0005] In one embodiment, the mounting assembly includes a connecting piece, a sliding shaft, a tension and torsion integrated sensor, a connecting plate, a mounting plate, and a footrest; the engine, the sliding shaft, the tension and torsion integrated sensor, and the connecting plate are fixedly connected in sequence, and one end of the connecting piece away from the sliding shaft is used for being fixedly connected to the engine; an axial direction of the sliding shaft is perpendicular to a rotation direction of the propeller; a bottom end of the connecting plate is fixedly connected to the mounting plate; a bottom end of the footrest is fixedly connected to the mounting plate, and an upper end of the footrest is fixedly connected to the second end of the rocker arm.

[0006] In one embodiment, the mounting assembly further includes a sliding bearing, the sliding bearing is fixed on the mounting plate and sleeved on the sliding shaft, and the sliding shaft can slide axially relative to the sliding bearing.

[0007] In one embodiment, the mounting assembly further includes a first flange, and the connecting piece is fixedly connected to the sliding shaft through the first flange.

[0008] In one embodiment, the mounting assembly further includes a shock pad, and the shock pad is located between the connecting member and the first flange.

[0009] In one embodiment, the vertical takeoff and landing aircraft nacelle parameter testing device further includes a plurality of acceleration sensors, and the plurality of acceleration sensors are mounted on the connecting member and / or the first flange for detecting acceleration.

[0010] In one embodiment, the mounting assembly further includes a second flange, and the sliding shaft is fixedly connected to the tension-torsion integrated sensor through the second flange.

[0011] In one embodiment, the vertical takeoff and landing aircraft nacelle parameter testing device further includes a nacelle connecting rod and a rotary bearing. The first end of the nacelle connecting rod is fixedly connected to the first end of the rocker arm; at least a part of the middle of the nacelle connecting rod is fixedly connected to the inner ring of the rotary bearing, and the nacelle connecting rod is rotatable; the outer ring of the rotary bearing is fixedly connected to the upper end of the mounting bench.

[0012] In one embodiment, the vertical takeoff and landing aircraft nacelle parameter testing device further includes an inclination sensor, and the angle sensor is fixedly arranged at the second end of the nacelle connecting rod.

[0013] In one embodiment, the vertical takeoff and landing aircraft nacelle parameter testing device further includes a connecting seat. The lower end of the connecting seat is fixedly connected to the upper end of the mounting bench, and the rotary bearing is fixedly connected to the upper end of the connecting seat.

[0014] In one embodiment, the vertical takeoff and landing aircraft nacelle parameter testing device further includes a first limiting ring and a second limiting ring. The first limiting ring is provided with a first limiting platform, and the second limiting ring is provided with a second limiting platform; a first positioning platform is arranged on one side of the connecting seat close to the rocker arm, and a second positioning platform is arranged on the other side of the connecting seat far from the rocker arm; both the first limiting ring and the second limiting ring are fixedly sleeved on the nacelle connecting rod, and the first limiting platform and the first positioning platform are opposite to each other, and the second limiting platform and the second positioning platform are opposite to each other; the first limiting ring and the second limiting ring rotate along with the nacelle connecting rod, and can make the first positioning platform and the first limiting platform contact, and / or, the second limiting platform and the second positioning platform contact.

[0015] In one embodiment, the short nacelle parameter testing device for a vertical takeoff and landing aircraft further includes a simulated wing, a control surface, and a variable-angle connecting rod; the simulated wing is fixedly arranged at the upper end of the mounting bench, the simulated wing is sleeved on the rocker arm, and there is a gap between the simulated wing and the rocker arm, and an installation groove is formed on the simulated wing; the control surface is located in the installation groove and is rotatably connected to the groove wall of the installation groove; one end of the variable-angle connecting rod is hinged to the simulated wing, and the other end of the variable-angle connecting rod is hinged to the lower surface of the control surface; the connecting rod can drive the control surface to rotate.

[0016] In one embodiment, the short nacelle parameter testing device for a vertical takeoff and landing aircraft further includes a wind pressure sensor, the simulated wing is fixed on the mounting bench through the wind pressure sensor, and the wind pressure sensor can be used to detect the wind pressure below the simulated wing.

[0017] In one embodiment, the short nacelle parameter testing device for a vertical takeoff and landing aircraft further includes an adapter, and the driving end of the steering gear is fixedly connected to the tension and compression sensor through the adapter.

[0018] In one embodiment, the short nacelle parameter testing device for a vertical takeoff and landing aircraft further includes a spherical bearing, and the tension and compression sensor is fixedly connected to the rocker arm through the spherical bearing.

[0019] In one embodiment, the short nacelle parameter testing device for a vertical takeoff and landing aircraft further includes a rotational speed sensor, and the rotational speed sensor is fixedly arranged on the rocker arm and is used to detect the rotational speed of the propeller.

[0020] In one embodiment, the short nacelle parameter testing device for a vertical takeoff and landing aircraft further includes a noise sensor and a temperature, humidity and pressure sensor, and both the noise sensor and the temperature, humidity and pressure sensor are fixed on the mounting bench.

[0021] The short nacelle parameter testing device for a vertical takeoff and landing aircraft provided by the present invention includes a mounting assembly, a mounting bench, a steering gear, a rocker arm, and a tension and compression sensor; the mounting assembly is used to mount an engine, and the driving end of the engine is used to mount a propeller; the steering gear is fixed on one side of the mounting bench, the driving end of the steering gear is fixedly connected to one end of the tension and compression sensor, the other end of the tension and compression sensor is fixedly connected to the middle of the rocker arm, and the steering gear can drive the rocker arm to rotate through the tension and compression sensor; the first end of the rocker arm is rotatably connected to the upper end of the mounting bench, and the second end of the rocker arm extends out of the mounting bench from one side of the steering gear and is fixedly connected to the mounting assembly. In the present invention, by adding a tension and compression sensor between the steering gear and the rocker arm, when the engine and the propeller are tilted by driving the rocker arm by the steering gear, the pressure or tension received by the output end of the steering gear can be detected in real time, so as to verify the accuracy of the design parameters and ensure that the nacelle design meets the aircraft requirements.

[0022] Other features and advantages of the present invention will become apparent from the following detailed description of exemplary embodiments of the invention with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The drawings incorporated in and forming a part of this specification illustrate embodiments of the invention and, together with the description, serve to explain the principles of the invention.

[0024] Figure 1 General assembly schematic diagram of the nacelle parameter test device for a vertical takeoff and landing aircraft provided for an embodiment of the invention.

[0025] Figure 2 Schematic diagram of the nacelle parameter test device for a vertical takeoff and landing aircraft provided for an embodiment of the invention without a simulated wing structure.

[0026] Figure 3 Schematic diagram of the installation of the simulated wing in the nacelle parameter test device for a vertical takeoff and landing aircraft provided for an embodiment of the invention.

[0027] Figure 4 Schematic diagram of the bottom of the simulated wing in the nacelle parameter test device for a vertical takeoff and landing aircraft provided for an embodiment of the invention.

[0028] Figure 5 Schematic diagram of the mounting bench structure in the nacelle parameter test device for a vertical takeoff and landing aircraft provided for an embodiment of the invention.

[0029] The markings in the figures are as follows:

[0030] 1 - Propeller; 2 - Engine; 3 - Connecting piece; 4 - First flange; 5 - Sliding bearing; 6 - Base; 7 - Slide shaft; 8 - Second flange; 9 - Torsion integrated sensor; 10 - Connecting plate; 11 - Wind speed sensor; 12 - Servo; 13 - Footrest; 14 - Rotation speed sensor; 15 - Fixed bracket; 16 - Rocker arm; 17 - Ball eye bearing; 18 - Tensile and compressive sensor; 19 - Adapter; 20 - Nacelle connecting rod; 21 - First limiting ring; 22 - Connecting seat; 23 - Rotary bearing; 24 - Second limiting ring; 25 - Mounting plate; 26 - Inclination sensor; 27 - Mounting bench; 28 - Acceleration sensor; 29 - Shock pad; 30 - Wind pressure sensor; 31 - Wind pressure mounting seat; 32 - Temperature, humidity and pressure sensor; 33 - Noise sensor; 34 - Simulated wing; 35 - Rudder surface; 36 - First connecting rod; 37 - Variable angle connecting rod; 38 - Second connecting rod; 39 - Mounting plate; 40 - Rotating shaft; 100 - Mounting assembly. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0031] Various exemplary embodiments of the present invention will now be described in detail with reference to the accompanying drawings. It should be noted that: unless otherwise specifically stated, the relative arrangements of components and steps, numerical expressions, and numerical values set forth in these embodiments do not limit the scope of the present invention.

[0032] The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way a limitation on the present invention or its application or use.

[0033] Technologies, methods, and devices known to those of ordinary skill in the relevant art may not be discussed in detail, but where appropriate, such technologies, methods, and devices should be regarded as part of the specification.

[0034] In all examples shown and discussed herein, any specific values should be construed as merely exemplary and not as a limitation. Thus, other examples of exemplary embodiments may have different values.

[0035] As Figures 1 to 5 shown, the vertical takeoff and landing aircraft nacelle parameter testing device provided by the embodiment of the present invention includes a mounting assembly 100, a mounting bench 27, a servo 12, a rocker arm 16, and a tension and compression sensor 18; the mounting assembly 100 is used to mount an engine 2, and a propeller 1 is mounted at the driving end of the engine 2; the servo 12 is fixed to one side of the mounting bench 27, the driving end of the servo 12 is fixedly connected to one end of the tension and compression sensor 18, the other end of the tension and compression sensor 18 is fixedly connected to the middle of the rocker arm 16, and the servo 12 can drive the rocker arm 16 to rotate through the tension and compression sensor 18; the first end of the rocker arm 16 is rotatably connected to the upper end of the mounting bench 27, the second end of the rocker arm 16 extends out of the mounting bench 27 from one side of the servo 12 and is fixedly connected to the mounting assembly 100. In the embodiment of the present invention, by adding a tension and compression sensor 18 between the servo 12 and the rocker arm 16, the servo 12 drives the rocker arm 16 to rotate, and the rocker arm 16 is fixedly connected to the mounting assembly. Therefore, when the rocker arm 16 drives the engine 2 and the propeller 1 to tilt through the mounting assembly 100, at this time, the pressure or tension received at the output end of the servo 12 can be detected in real time to verify the accuracy of the design parameters and ensure that the nacelle design meets the aircraft requirements.

[0036] In one embodiment, the mounting assembly 100 includes a connecting member 3, a sliding shaft 7, a tension-torsion integrated sensor, a connecting plate 10, a mounting plate 39, and a footrest 13; the engine 2, the sliding shaft 7, the tension-torsion integrated sensor, and the connecting plate 10 are fixedly connected in sequence, and one end of the connecting member 3 away from the sliding shaft 7 is used to be fixedly connected to the engine 2; the axial direction of the sliding shaft 7 is perpendicular to the rotation direction of the propeller 1; the bottom end of the connecting plate 10 is fixedly connected to the mounting plate 39; the bottom end of the footrest 13 is fixedly connected to the mounting plate 39, and the upper end of the footrest 13 is fixedly connected to the second end of the rocker arm 16. Specifically, the upper end of the footrest 13 is fixedly connected to the second end of the rocker arm 16 by bolts. In this embodiment, the connecting member 3 is cylindrical, the engine 2 is installed in the cylinder, and the axis of rotation 40 of the propeller 1, the axis of the cylinder, and the axial direction of the sliding shaft 7 are all coaxially arranged. In this way, on the one hand, the stability of the installation can be ensured; on the other hand, the loss of force conduction can be reduced, making the measurement result closer to the true result. In this embodiment, the engine 2, the propeller 1, and the sliding shaft 7 are also fixed into one body through the mounting plate 39 and then connected to the rocker arm 16, making the structure simple and the installation convenient.

[0037] Those skilled in the art can understand that during the process of the engine 2 driving the propeller 1 to rotate, the propeller 1 generates an axial pulling force and a torsional force on the engine 2, and the engine 2 is fixedly connected to the sliding shaft 7 through the connecting member 3 and the first flange 4. Therefore, the pulling force and the torsional force will be transmitted to the sliding shaft 7. Therefore, by testing the pulling force and the torsional force received by the sliding shaft 7, the pulling force and the torsional force generated when the propeller 1 rotates can be known.

[0038] In one embodiment, the mounting assembly 100 further includes a sliding bearing 5. The sliding bearing 5 is fixed on the mounting plate 39 and sleeved on the sliding shaft 7, and the sliding shaft 7 can slide axially relative to the sliding bearing 5. By providing the sliding bearing 5, on the one hand, it can play a role in supporting the sliding shaft 7 to prevent the sliding shaft 7 from breaking. On the other hand, due to the low friction performance of the sliding bearing 5, the resistance of the sliding shaft 7 sliding in the sliding bearing 5 can be greatly reduced, thereby reducing the influence of external factors on the detection result. In this embodiment, a base 6 is also provided between the sliding bearing 5 and the mounting plate 39. The base 6 is fixed on the mounting plate 39, and the sliding bearing 5 is fixed above the base 6, so as to facilitate adjusting the installation height of the sliding bearing 5 seat and avoid generating radial force between the sliding bearing 5 and the sliding shaft 7. Those skilled in the art can understand that the number of sliding bearings 5 can be multiple, such as two, three, or four, etc., and can be specifically set according to the length of the sliding shaft 7. In this embodiment, two are preferably used.

[0039] In one embodiment, the mounting assembly 100 further includes a first flange 4, and the connecting member 3 is fixedly connected to the sliding shaft 7 through the first flange 4. The connecting member 3 is cylindrical. Therefore, it is relatively difficult to directly connect to the sliding shaft 7. However, through the transfer of the first flange 4, the connection between the sliding shaft 7 and the connecting member 3 can be conveniently realized.

[0040] In one embodiment, the mounting assembly 100 further includes a shock pad 29, and the shock pad 29 is located between the connecting member 3 and the first flange 4. When the engine 2 drives the propeller 1 to work, a large amount of vibration will be generated. Through the shock pad 29, the vibration transmitted to components such as the sliding shaft 7 and the connecting member 3 on the side of the first flange 4 away from the engine 2 can be reduced, thereby reducing the influence on the detection parameters during the operation of the engine 2 and improving the detection accuracy; on the other hand, it can also reduce noise.

[0041] In one embodiment, the vertical takeoff and landing aircraft nacelle parameter testing device further includes a plurality of acceleration sensors 28, and the plurality of acceleration sensors 28 are installed on the connecting member 3 and / or the first flange 4 for detecting acceleration. Specifically, in this embodiment, an acceleration sensor 28 is provided on both the connecting member 3 and the first flange 4.

[0042] In one embodiment, the mounting assembly 100 further includes a second flange 8, and the sliding shaft 7 is fixedly connected to the tension-torsion integrated sensor through the second flange 8. Those skilled in the art can know that by providing the second flange 8, the mounting surface between the torsion integrated sensor 9 and the sliding shaft 7 can be adjusted. Since the second flange 8 has a large surface, the force of the sliding shaft 7 can be more evenly transmitted to the torsion integrated sensor 9, making the parameters measured by the torsion integrated sensor 9 more accurate.

[0043] In one embodiment, the vertical takeoff and landing aircraft nacelle parameter testing device further includes a nacelle connecting rod 20 and a rotary bearing 23. The first end of the nacelle connecting rod 20 is fixedly connected to the first end of the rocker arm 16; at least a part of the middle of the nacelle connecting rod 20 is fixedly connected to the inner ring of the rotary bearing 23, and the nacelle connecting rod 20 is rotatable; the outer ring of the rotary bearing 23 is fixedly connected to the upper end of the mounting bench 27. As is well known, the bearing can greatly reduce the friction force. Therefore, in this embodiment, through the nacelle connecting rod 20, the rocker arm 16 can be extended, so as to facilitate the setting of the parameters of the rocker arm 16; and by providing the rotary bearing 23, the resistance of the nacelle connecting rod 20 to rotate can be greatly reduced, thus facilitating the testing.

[0044] In one embodiment, the short nacelle parameter testing device of the vertical takeoff and landing aircraft further includes an inclination sensor 26, which is fixedly arranged at the second end of the nacelle connecting rod 20. Specifically, an installation bracket 25 is further arranged between the inclination sensor 26 and the nacelle connecting rod 20. One end of the installation bracket 25 is fixedly connected to the second end of the nacelle connecting rod 20, and the other end is detachably connected to the inclination sensor 26. In this way, the installation and maintenance of the inclination sensor 26 can be facilitated. Through the inclination sensor 26, the real-time inclination angle of the rocker arm 16 in different states can be accurately measured, helping designers collect the parameters of the rocker arm 16. Those skilled in the art can understand that the rocker arm 16 is fixedly connected to parts such as the aircraft nacelle, that is, the engine 2 and the propeller 1. Therefore, by measuring the rotation angle of the rocker arm 16, the tilting angle of the aircraft nacelle can be obtained.

[0045] In one embodiment, the short nacelle parameter testing device of the vertical takeoff and landing aircraft further includes a connecting seat 22. The lower end of the connecting seat 22 is fixedly connected to the upper end of the installation bench 27, and the rotary bearing 23 is fixedly connected to the upper end of the connecting seat 22. Through the connecting seat 22, the installation convenience of the embodiment of the present invention can be improved, facilitating the use by operators.

[0046] In one embodiment, the short nacelle parameter testing device of the vertical takeoff and landing aircraft further includes a first limiting ring 21 and a second limiting ring 24. The first limiting ring 21 is provided with a first limiting platform, and the second limiting ring 24 is provided with a second limiting platform; a first positioning platform is arranged on one side of the connecting seat 22 close to the rocker arm 16, and a second positioning platform is arranged on the side of the connecting seat 22 far from the rocker arm 16; the first limiting ring 21 and the second limiting ring 24 are both fixedly sleeved on the nacelle connecting rod 20, and the first limiting platform and the first positioning platform are opposite to each other, and the second limiting platform and the second positioning platform are opposite to each other; the first limiting ring 21 and the second limiting ring 24 rotate with the nacelle connecting rod 20, and can make the first positioning platform and the first limiting platform contact, and / or, the second limiting platform and the second positioning platform contact. In the embodiment of the present invention, by setting the first limiting ring and the second limiting ring 24, the rotation angle of the rocker arm 16 can be limited, avoiding the overload of the steering gear 12 or the abnormal movement of the engine 2, resulting in too large a rotation amplitude of the rocker arm 16 and damaging the experimental components. At the same time, in the embodiment of the present invention, by setting the first limiting ring 21 and the second limiting ring 24, the rotation stability of the rocker arm 16 can be ensured, avoiding single-point stress, and at the same time, the axial load along the nacelle connecting rod can be avoided from being too large, damaging the overall structure and the equipment.

[0047] In one embodiment, the vertical takeoff and landing aircraft nacelle parameter testing device further includes a simulation wing 34, a control surface 35, and a variable-angle connecting rod 37. The simulation wing 34 is fixedly arranged at the upper end of the mounting bracket 27. The simulation wing 34 is sleeved on the rocker arm 16 and there is a gap between the simulation wing 34 and the rocker arm 16. Such a setting can avoid interference between the simulation wing 34 and the rocker arm 16, resulting in abnormal parameters of the rocker arm 16. An installation groove is formed in the simulation wing 34. The control surface 35 is located in the installation groove and is rotatably connected to the groove wall of the installation groove. Specifically, the installation groove includes two opposite side walls and a bottom wall connecting the two side walls. Installation holes are formed in the two side walls. Rotating shafts 40 are arranged on both sides of the control surface 35. The rotating shafts 40 on both sides of the control surface 35 are respectively inserted into the installation holes on both sides of the installation groove and can rotate in the installation holes, so as to simulate the tilting of the control surface 35. One end of the variable-angle connecting rod 37 is hinged to the simulation wing 34, and the other end of the variable-angle connecting rod 37 is hinged to the lower surface of the control surface 35. The connecting rod can drive the control surface 35 to rotate. Specifically, a first connecting rod 36 is fixed below the simulation wing 34, a second connecting rod 38 is fixed below the control surface 35, and the variable-angle connecting rod 37 is respectively hinged to the first connecting rod 36 and the second connecting rod 38. In the embodiment of the present invention, the variable-angle connecting rod 37 drives the control surface 35 to rotate, so as to simulate the tilting of the control surface 35 in different environments, and thus the parameters of the aircraft in more states can be obtained, providing more parameter bases for optimizing the aircraft design.

[0048] In one embodiment, the vertical takeoff and landing aircraft nacelle parameter testing device further includes a wind pressure sensor 30. The simulation wing is fixed on the mounting bracket 27 through the wind pressure sensor 30, and the wind pressure sensor 30 is used to detect the wind pressure below the simulation wing 34. Specifically, the lower end of the wind pressure sensor 30 is installed on the mounting bracket 27, and the upper end of the wind pressure sensor is fixedly connected to the lower part of the simulation wing 34. Those skilled in the art can understand that a wind pressure mounting seat 31 for installing the wind pressure sensor 30 is further arranged at the upper end of the mounting bracket 27, which is convenient for the installation of the wind pressure sensor 30. In this embodiment, through the wind pressure sensor 30, the wind pressure below the wing during the flight of the aircraft can be provided for the designer, so as to verify the fluid characteristics of the wing and provide an experimental basis for the designer to optimize the wing.

[0049] In one embodiment, the short nacelle parameter testing device for the vertical takeoff and landing aircraft further includes an adapter 19, and the driving end of the servo 12 is fixedly connected to the tension and compression sensor 18 through the adapter 19. Specifically, one end of the adapter 19 is fixedly connected to the driving end of the servo 12, and the other end of the adapter 19 is fixedly connected to the tension and compression sensor 18. In this embodiment, by providing the adapter 19, the installation position of the tension and compression sensor 18 can be appropriately adjusted, so that the tension and compression sensor 18 is located at a position convenient for disassembly. Those skilled in the art can know that, as a kind of sensor, the service life of the tension and compression sensor 18 is relatively short, and it needs to be calibrated regularly. At the same time, when measuring different models of aircraft, it is also possible to replace the tension and compression sensor 18. Therefore, by providing the adapter 19, the operating space of the position where the tension and compression sensor 18 is installed is made as large as possible, so as to facilitate the replacement, maintenance, etc. of the tension and compression sensor 18, thereby improving the convenience of the user.

[0050] In one embodiment, the short nacelle parameter testing device for the vertical takeoff and landing aircraft further includes a spherical bearing 17, and the tension and compression sensor 18 is fixedly connected to the rocker arm 16 through the spherical bearing 17. The spherical bearing 17 can adopt standard parts on the market, so as to reduce costs and facilitate maintenance.

[0051] In one embodiment, the short nacelle parameter testing device for the vertical takeoff and landing aircraft further includes a rotational speed sensor 14, and the rotational speed sensor 14 is fixedly arranged on the rocker arm 16 for detecting the rotational speed of the propeller 1. Specifically, a fixing bracket 15 for installing the sensor is fixed on the rocker arm 16. When installing the rotational speed sensor 14 on the fixing bracket 15, those skilled in the art can understand that since the fixing bracket 15 does not need to be disassembled frequently, it can be fixed to the rocker arm 16 by welding, while the rotational speed sensor 14 can be detachably fixed to the fixing bracket 15 by threaded connection, so as to facilitate maintenance and replacement. In the embodiment of the present invention, the rotational speed sensor 14 is used to detect the rotational speed of the propeller 1, so as to measure the thrust generated by the propeller under the corresponding rotational speed, providing important parameters for the design of the aircraft and being beneficial to improving the performance of the aircraft.

[0052] In one embodiment, the vertical takeoff and landing aircraft nacelle parameter testing device further includes a noise sensor 33 and an air temperature, humidity and pressure sensor 32, and both the noise sensor 33 and the air temperature, humidity and pressure sensor 32 are fixed on the mounting bench 27. Specifically, mounting seats for mounting the noise sensor 33 and the air temperature, humidity and pressure sensor 32 are respectively welded on the mounting bench 27, and the noise sensor 33 and the air temperature, humidity and pressure sensor 32 are respectively fixed on the mounting seats. In this embodiment, the noise sensor 33 can be used to detect the noise generated by the engine 2 and the propeller 1 during the working state and the environmental conditions, so as to provide design references for designers and facilitate design optimization. Of course, in the embodiments of the present invention, those skilled in the art can also increase or decrease the number of sensors according to needs. For example, a vibration sensor can be added to detect the influence of the engine 2 on the vibration of the rocker arm 16 during operation; or, a wind speed sensor 11 can be added to detect the wind speed generated when the propeller 1 rotates. Therefore, those skilled in the art can conveniently detect aircraft parameters by setting corresponding sensors at corresponding positions on the frame, which brings great convenience to verifying the rationality of the design. Of course, in order to further increase the convenience of installing or disassembling the sensors, in the embodiments of the present invention, a plurality of mounting holes can be preset on the mounting bench 27 for mounting the sensors, so as to simplify the process of installing and disassembling the sensors.

[0053] In one embodiment, the mounting bench 27 includes a top plate and a frame body. The frame body can be formed by welding channel steel or square steel profiles. The top plate is fixed above the frame body and is used for mounting the connecting seat 22, the simulation wing 34, etc. In the embodiments of the present invention, the frame body can be formed by welding standard profiles, which saves costs on the one hand and is convenient for maintenance on the other hand. For the top plate with relatively high flatness requirements, in the embodiments of the present invention, it is preferably a steel flat plate. Utilizing the high strength performance of steel, on the one hand, the top plate is durable; on the other hand, it can ensure the stability of the test parameters.

[0054] The embodiments of the present application also provide an embodiment of the overall use of a short nacelle parameter test device for a vertical takeoff and landing aircraft. In this embodiment, first, a servo is used to push the rocker to rotate. At this time, the tensile and compressive force generated by the servo when pushing the rocker can be measured by a tensile and compressive sensor installed on the servo. When the servo pushes the installation component to form a certain angle with the simulation wing, the wind will blow onto the simulation wing. At this time, the wind pressure generated by the propeller is measured by a pressure sensor installed under the simulation wing, and the angle is measured by a tilt angle sensor. The rudder surface of the simulation wing can be angle-controlled by a variable-angle connecting rod. During the process of the engine driving the propeller to rotate, the tensile force and torque generated by the engine can be measured by a tensile and torsion sensor. At this time, a rotational speed sensor installed above the rocker is used to measure the rotational speed of the propeller; the acceleration of the engine is measured by an acceleration sensor, etc. At the same time, the ambient temperature and humidity can also be measured by a temperature, humidity, and pressure sensor; a noise sensor is used to measure parameters such as the noise generated by the propeller. In the present application, each sensor can be adjusted as needed, and no specific regulations are made in this embodiment.

[0055] Although some specific embodiments of the present invention have been described in detail by way of examples, those skilled in the art should understand that the above examples are only for illustration and not for limiting the scope of the present invention. Those skilled in the art should understand that the above embodiments can be modified without departing from the scope and spirit of the present invention. The scope of the present invention is defined by the appended claims.

Claims

1. A nacelle parameter testing device for a vertical takeoff and landing aircraft, characterized in that, it includes a mounting assembly, a mounting bench, a servo, a rocker arm and a tension and compression sensor; The mounting assembly is used to mount the engine, and the driving end of the engine is used to mount the propeller; The servo is fixed on one side of the mounting bench, the driving end of the servo is fixedly connected to one end of the tension and compression sensor, the other end of the tension and compression sensor is fixedly connected to the middle of the rocker arm, and the servo can drive the rocker arm to rotate through the tension and compression sensor; The first end of the rocker arm is rotatably connected to the upper end of the mounting bench, and the second end of the rocker arm extends out of the mounting bench from one side of the servo and is fixedly connected to the mounting assembly; The nacelle parameter testing device for a vertical takeoff and landing aircraft further includes an adapter. The driving end of the servo is fixedly connected to the tension and compression sensor through the adapter; one end of the adapter is fixedly connected to the driving end of the servo, and the other end of the adapter is fixedly connected to the tension and compression sensor.

2. The nacelle parameter testing device for a vertical takeoff and landing aircraft according to claim 1, characterized in that, The mounting assembly includes a connecting piece, a sliding shaft, a tension and torsion integrated sensor, a connecting plate, a mounting plate and a footrest; The engine, the sliding shaft, the tension and torsion integrated sensor and the connecting plate are fixedly connected in sequence, and the end of the connecting piece away from the sliding shaft is used to be fixedly connected to the engine; The axial direction of the sliding shaft is perpendicular to the rotation direction of the propeller; The bottom end of the connecting plate is fixedly connected to the mounting plate; The bottom end of the footrest is fixedly connected to the mounting plate, and the upper end of the footrest is fixedly connected to the second end of the rocker arm.

3. The nacelle parameter testing device for a vertical takeoff and landing aircraft according to claim 2, characterized in that, The mounting assembly further includes a sliding bearing. The sliding bearing is fixed on the mounting plate and sleeved on the sliding shaft, and the sliding shaft can slide axially relative to the sliding bearing.

4. The nacelle parameter testing device for a vertical takeoff and landing aircraft according to claim 2, characterized in that, The mounting assembly further includes a first flange. The connecting piece is fixedly connected to the sliding shaft through the first flange.

5. The nacelle parameter testing device for a vertical takeoff and landing aircraft according to claim 4, characterized in that, The mounting assembly further includes a shock pad. The shock pad is located between the connecting piece and the first flange.

6. The nacelle parameter testing device for a vertical takeoff and landing aircraft according to claim 4, characterized in that, The nacelle parameter testing device for a vertical takeoff and landing aircraft further includes a plurality of acceleration sensors. The plurality of acceleration sensors are installed on the connecting piece and / or the first flange for detecting acceleration.

7. The nacelle parameter testing device for a vertical takeoff and landing aircraft according to claim 2, characterized in that, The mounting assembly further includes a second flange. The sliding shaft is fixedly connected to the tension and torsion integrated sensor through the second flange.

8. The nacelle parameter testing device for a vertical takeoff and landing aircraft according to claim 1, characterized in that, The short nacelle parameter testing device for the vertical takeoff and landing aircraft further includes a nacelle connecting rod and a rotary bearing. The first end of the nacelle connecting rod is fixedly connected to the first end of the rocker arm; At least a part of the middle of the nacelle connecting rod is fixedly connected to the inner ring of the rotary bearing, and the nacelle connecting rod is rotatable; The outer ring of the rotary bearing is fixedly connected to the upper end of the mounting bench.

9. The short nacelle parameter testing device for the vertical takeoff and landing aircraft according to claim 8, characterized in that, the short nacelle parameter testing device for the vertical takeoff and landing aircraft further includes an inclination sensor, and the inclination sensor is fixedly arranged at the second end of the nacelle connecting rod.

10. The short nacelle parameter testing device for the vertical takeoff and landing aircraft according to claim 8, characterized in that, the short nacelle parameter testing device for the vertical takeoff and landing aircraft further includes a connecting seat. The lower end of the connecting seat is fixedly connected to the upper end of the mounting bench, and the rotary bearing is fixedly connected to the upper end of the connecting seat.

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