Mars rotor take-off and landing performance test system under near-earth effect

Abstract

The invention discloses a Mars rotor take-off and landing performance test system under a near-earth effect, which belongs to the technical field of aviation test measurement and comprises a lifting mechanism, a force measuring system and a rotor mechanism. The force measuring system is installed on the lifting mechanism, and the rotor wing mechanism is installed on the force measuring system. The lifting mechanism can drive the force measuring system and the rotor wing mechanism to ascend and descend, and the force measuring system is used for measuring the lifting force and the torque when the rotor wing rotates. The test system is simple in structure, the performance of the rotor wing can be measured after rapid assembly, and the defects that an existing rotor wing test bed is limited in function, complex in mechanical structure, heavy in structural weight and complex in system, and a special environment is needed for testing are overcome.

Description

Technical Field

[0001] The invention belongs to the technical field of aviation test and measurement, and in particular relates to a Mars rotor take-off and landing performance test system under near-earth effect. Background Art

[0002] At present, general rotor test benches are mainly divided into fixed rotor test benches that simulate the hovering state, mobile rotor test benches that simulate forward flight, and tilt-rotor test benches that simulate tilt-rotor aircraft according to the flight state of the rotor being measured; the characteristics of various rotor test benches are as follows: (1) Fixed rotor test benches are relatively common, such as the 2m-class rotor test bench at Nanjing University of Aeronautics and Astronautics. This test bench is mainly used to test the hovering performance and flow field analysis of the rotor. It can also be placed in a wind tunnel to perform forward flight tests. However, the main support part of this type of test bench is relatively large, which will cause significant interference to the near and far flow fields of the rotor in the wind tunnel, and the support with a large frontal area will cause a certain blocking effect on the wind tunnel. When simulating forward flight, it involves a complex process of various rotor trim and parameter adjustments. Moreover, most of the trim and parameter adjustments are based on previous theoretical calculations, so there is still a certain difference in the simulation of the actual forward flight of the rotor. Therefore, the types of tests that can be performed on fixed rotor test benches are limited. Even if you want to simulate forward flight, you have to use a wind tunnel to achieve it, which increases the cost of the test.

[0003] (2) On the one hand, the mobile rotor test bench is difficult to build, occupies a large area, and has high construction costs; on the other hand, it is easily affected by the external weather environment during the test, and it is difficult to find suitable test conditions;

[0004] (3) Research on simulated tilt-rotor test benches focuses on scaled models (low cost, convenient for flow field analysis but with size effect), full-scale tests (reliable data but high cost) and hybrid physical-virtual platforms (flexible but complex systems). Challenges such as multi-mode conversion stability and the contradiction between lightweight and strength need to be addressed. The future trend will rely on digital twins, artificial intelligence optimization and multi-test bench collaboration to improve the R&D efficiency and safety of the next generation of tilt-rotor aircraft. Summary of the invention

[0005] The present invention provides a Mars rotor take-off and landing performance test system under near-Earth effect, which can solve the shortcomings of the existing rotor test bench, such as limited functions, complex mechanical structure, heavy structure weight, complex system, and special environment required for testing.

[0006] To achieve the above objectives, the present invention adopts the following technical solutions: A Mars rotor take-off and landing performance test system under near-Earth effect comprises: a test bench support, a lifting mechanism, a force measuring system, and a rotor mechanism; the lifting mechanism is installed on the test bench support, the force measuring system is installed on the lifting mechanism, and the rotor mechanism is installed on the force measuring system; the lifting mechanism can drive the force measuring system and the rotor mechanism to rise and fall, and the force measuring system is used to measure the lift and torque when the rotor rotates.

[0007] The test bench support is composed of a bottom plate, two L-shaped bottom mounting seats and a connecting piece, and the connecting piece is connected between the bottom mounting seats by bolts.

[0008] The lifting mechanism includes a linear bearing mounting plate, an optical axis bearing, an electric servo push rod, a threaded column, and an optical axis mounting seat; the electric servo push rod is fixed between the bottom mounting seat and the connecting plate, and the lifting and lowering movement of the electric servo push rod is realized by the retainer of the electric servo push rod; the square linear bearing mounting plate is fixed to the push rod push-out position of the electric servo push rod, and the four optical axis bearings are fixed to the four corners of the linear bearing mounting plate by bolts, and the four optical axes are installed in the optical axis bearings, and the optical axes can be lifted and lowered together with the electric servo push rod; the four optical axes respectively pass through the lifting mechanism and the force measuring system, which can enhance the stability of the entire system in the vertical direction.

[0009] The force measuring system includes an upper mounting plate, an optical axis mounting seat, a pressure sensor mounting plate, a pressure sensor, a torque balance mounting plate, and a torque sensor; a threaded column is arranged above the electric servo push rod, which is connected to the upper mounting plate through a threaded hole in the center of the upper mounting plate, and the pressure sensor mounting plate is fixed together above the upper mounting plate through four optical axis mounting seats; the pressure sensor is fixed above the pressure sensor mounting plate, and is used to measure the lift when the rotor rotates; the pressure sensor is connected to the torque balance mounting plate through a spring, and the torque balance mounting plate and the pressure sensor mounting plate are connected and fixed by four optical axes, four optical axis bearings are fixed at the four corners of the torque balance by bolts, and the optical axis is installed in the optical axis bearings, and the torque sensor is fixed to the torque balance mounting plate by four bolts, and is used to measure the torque when the rotor rotates.

[0010] The rotor mechanism consists of an extended connecting rod, a rotor motor and a rotor. The extended connecting rod is fixed to the torque sensor by bolts. The main function of the extended connecting rod is to reduce the aerodynamic interference of the torque balance mounting plate on the rotor. The rotor motor is fixed to the top of the extended connecting rod by bolts. The two blades of the rotor are connected together by a rotor blade clamp and fixed to the rotating shaft of the rotor motor after connection.

[0011] Beneficial effects: The present invention provides a Mars rotor take-off and landing performance test system under the near-earth effect. The height of the rotor mechanism from the ground can be adjusted by a lifting mechanism to complete the test of the rotor performance during the dynamic process of take-off and landing under the near-earth effect. The lift and torque of the rotor are measured by a decoupled force measurement system. A pressure sensor and a torque sensor are used to measure the lift and torque of the rotor respectively. The decoupled force measurement system saves costs compared to a six-component sensor. The test system of the present invention has a simple structure and can be quickly assembled to measure the performance of the rotor. It solves the problems of the traditional rotor test platform, such as complex mechanical structure, heavy structural weight, complex system, and some test benches need the cooperation of wind tunnels to complete the test. Complex theoretical calculation preparation work is required before the test, and the use cost is high and the time cost is large. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 Schematic diagram of the overall structure of a system for testing the take-off and landing performance of a Mars rotor under the near-Earth effect in an embodiment of the present invention; Figure 2 It is a schematic diagram of a test bench support in a Mars rotor take-off and landing performance test system under near-Earth effect in an embodiment of the present invention; Figure 3 It is a schematic diagram of the lifting mechanism in the Mars rotor take-off and landing performance test system under the near-Earth effect in an embodiment of the present invention; Figure 4 It is a schematic diagram of a force measurement system in a Mars rotor take-off and landing performance test system under near-Earth effect in an embodiment of the present invention; Figure 5 Schematic diagram of the rotor mechanism in the Mars rotor take-off and landing performance test system under the near-Earth effect in an embodiment of the present invention; In the figure: 1-test bench support, 2-lifting mechanism, 3-force measuring system, 4-rotor mechanism, 101-base plate, 102-bottom mounting seat, 103-mounting seat connecting plate, 201-electric servo push rod, 202-linear bearing mounting plate, 203-optical axis bearing a, 204-optical axis, 205-threaded rod, 301-upper mounting plate, 302-pressure sensor mounting plate, 303-optical axis mounting seat, 304-pressure sensor, 305-pre-tightening bolt, 306-torque balance mounting plate, 307-optical axis bearing b, 308-torque sensor, 401-extension connecting rod, 402-rotor motor, 403-rotor, 404-rotor blade clamp. DETAILED DESCRIPTION

[0013] The present invention is described in detail below with reference to the accompanying drawings and specific embodiments: like Figure 1 As shown, a Mars rotor take-off and landing performance test system under near-Earth effect includes a test bench support 1, a lifting mechanism 2, a force measurement system 3, and a rotor mechanism 4; like Figure 2 As shown, the test bench support 1 includes a base plate 101, a bottom mounting seat 102, and a mounting seat connecting piece 103. Two L-shaped bottom mounting seats 102 are fixed to the center of the base plate 101 by bolts. In order to reinforce the bottom structure of the test bench support 1, two square mounting seat connecting pieces 103 are fixed between the two bottom mounting seats 102 by bolts. The lifting mechanism 2 is installed between the bottom mounting seat 102 and the mounting seat connecting piece 103.

[0014] like Figure 3 As shown, the lifting mechanism 2 includes an electric servo push rod 201, a linear bearing mounting plate 202, an optical axis bearing a203, an optical axis 204, and a threaded rod 205; the linear bearing mounting plate 202 is fixed to the rod extension of the electric servo push rod 201, and four optical axis bearings a203 are installed at the four corners of the linear bearing mounting plate 202, and each optical axis bearing is fixed to the linear bearing mounting plate by four bolts; four optical axes 204 with a length of 720 mm and a diameter of 10 mm are installed in the optical axis bearings, and the optical axes 204 can be lifted and lowered together with the electric servo push rod 201, and the four optical axes 204 run through the lifting mechanism 2 and the force measuring system 3, thereby enhancing the stability of the entire system in the vertical direction during the lifting process; the top of the electric servo push rod 201 is connected to the force measuring system 3 through a threaded rod 205, so that the electric servo push rod 201 can move with the force measuring system 3 and the rotor mechanism 4 during the lifting process.

[0015] like Figure 4 As shown, the force measuring system 3 includes an upper mounting plate 301, a pressure sensor mounting plate 302, an optical axis mounting seat 303, a pressure sensor 304, a pre-tightening bolt 305, a torque balance mounting plate 306, an optical axis bearing b307, and a torque sensor 308; the upper mounting plate 301 is connected to the threaded rod 205 through a threaded hole in the center of the bottom and is fixed above the electric servo push rod 201, and the pressure sensor mounting plate 302 is fixed to the upper mounting plate 301 using four optical axis mounting seats 303, wherein the pressure sensor mounting plate 302 is fixed to the upper mounting plate 301 together. The force sensor mounting plate 302 is located above the upper mounting plate 301, the pressure sensor 304 is fixed in the center of the pressure sensor mounting plate 302, and is connected to the torque balance mounting plate 306 through pre-tightening bolts at the top, and four optical axis bearings b307 are fixed to the four corners of the torque balance mounting plate 306 by bolts; the torque sensor 308 is fixed above the torque balance mounting plate 306; four optical axes 204 pass through the optical axis mounting seat 303 and the optical axis bearings b307 to enhance the stability of the entire force measurement system.

[0016] like Figure 5As shown, the rotor mechanism 4 includes an extended connecting rod 401, a rotor motor 402, a rotor 403, and a rotor blade clamp 404; the extended connecting rod 401 is coaxially fixed above the torque sensor 308 by bolts, and the diameter of the extended connecting rod 401 is slightly smaller than the diameter of the torque sensor 308; the rotor motor 402 is coaxially fixed above the extended connecting rod 401, and the two rotors 403 are fixed to the rotating shaft of the rotor motor by the rotor blade clamp 404. When the rotor test is performed, the torque of the rotor 403 during rotation is measured by the installed torque sensor 308, and the pulling force of the rotor 403 is measured by the pressure sensor 304, and finally the required measurement value is obtained.

[0017] During operation, the test bench support 1 is fixed on the ground and the lifting mechanism 2 is fixed on the test bench support 1. The vertical height between the rotor 403 and the ground is changed by adjusting the lifting mechanism 2 to simulate the height of the rotor from the ground when taking off and landing. At this time, the rotor motor 402 is turned on, and the force of the rotor rotation is transmitted to the force measuring system 3. The tension and torque generated by the rotation of the rotor 403 are measured by the force measuring system 3.

[0018] The above description is only a preferred embodiment of the present invention. It should be pointed out that those skilled in the art can make corresponding changes and adjustments to the technology of the present invention without departing from the basic principles of the present invention. These changes and adjustments all fall within the protection scope of the present invention.

Claims

1. A Mars rotor take-off and landing performance test system under near-Earth effect, characterized in that: include: A lifting mechanism, a force measuring system, and a rotor mechanism; the force measuring system is installed on the lifting mechanism, and the rotor mechanism is installed on the force measuring system; the lifting mechanism can drive the force measuring system and the rotor mechanism to rise and fall, and the force measuring system is used to measure the lift and torque when the rotor rotates.

2. The Mars rotor take-off and landing performance test system under near-Earth effect according to claim 1, characterized in that: The system comprises a test bench support, and the lifting mechanism is installed on the test bench support.

3. The Mars rotor take-off and landing performance test system under near-Earth effect according to claim 1, characterized in that: The lifting mechanism includes an electric servo push rod, a linear bearing mounting plate, an optical axis bearing, and an optical axis; the linear bearing mounting plate is fixed to the protruding part of the rod of the electric servo push rod, and four optical axis bearings are installed at the four corners of the linear bearing mounting plate, and each optical axis bearing is fixed to the linear bearing mounting plate by four bolts; the four optical axes are installed in the optical axis bearings, and the optical axes can be lifted and lowered together with the electric servo push rod.

4. The Mars rotor take-off and landing performance test system under near-Earth effect according to claim 3, characterized in that: Four optical axes run through the lifting mechanism and the force measurement system respectively, enhancing the vertical stability of the entire system during the lifting process.

5. The Mars rotor take-off and landing performance test system under near-Earth effect according to claim 3, characterized in that: The top of the electric servo push rod is connected to the force measuring system through a threaded rod, so that the electric servo push rod can move with the force measuring system and the rotor mechanism during the lifting process.

6. The Mars rotor take-off and landing performance test system under near-Earth effect according to claim 1 or 5, characterized in that: The force measuring system includes an upper mounting plate, a pressure sensor mounting plate, a pressure sensor, a pre-tightening bolt, a torque balance mounting plate, and a torque sensor; the upper mounting plate is connected to a threaded rod at the top of an electric servo push rod in a lifting mechanism via a threaded hole at the center of the bottom, the pressure sensor mounting plate is located above the upper mounting plate, the pressure sensor is fixed at the center of the pressure sensor mounting plate, and is connected to the torque balance mounting plate via a pre-tightening bolt at the top, and the torque sensor is fixed above the torque balance mounting plate.

7. The Mars rotor take-off and landing performance test system under near-Earth effect according to claim 6, characterized in that: The four corners of the pressure sensor mounting plate are fixedly connected to the upper mounting plate through four optical axis mounting seats.

8. The Mars rotor take-off and landing performance test system under near-Earth effect according to claim 7, characterized in that: Four optical axis bearings are fixed to the four corners of the moment balance mounting plate by bolts; the four optical axes penetrate through the optical axis mounting seat and the optical axis bearings to enhance the stability of the entire force measuring system.

9. The Mars rotor take-off and landing performance test system under near-Earth effect according to claim 1, characterized in that: The rotor mechanism includes an extended connecting rod, a rotor motor, a rotor, and a rotor blade clamp; the extended connecting rod is coaxially fixed above the torque sensor by bolts, the rotor motor is coaxially fixed above the extended connecting rod, and the two rotors are connected by the rotor blade clamp and fixed on the rotating shaft of the rotor motor.

10. The Mars rotor take-off and landing performance test system under near-Earth effect according to claim 9, characterized in that: The diameter of the extended connecting rod is slightly smaller than the diameter of the torque sensor.

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