A high-pressure air-activated propeller propulsion system mechanical testing system and method

Abstract

This invention discloses a mechanical testing system for a high-pressure air-excited propeller propulsion system, comprising: several mechanical testing devices, each including a simulated propeller blade, a high-pressure air blowing system, a motor, and a motor support; wherein the simulated propeller blade is connected to the motor, the motor is fixed by the motor support, the motor drives the simulated propeller blade to rotate at high speed, and the high-pressure air blowing system applies high-pressure air loading to the rotating simulated propeller blade; when the motor drives the simulated propeller blade to rotate, the high-pressure air blowing generates an approximate square wave excitation on the simulated propeller blade; by adjusting the motor speeds of multiple mechanical testing devices, beat vibration excitation testing is achieved. This invention, through the design of the simulated propeller blade and the high-pressure air blowing system, can effectively simulate key load types such as periodic torques.

Description

Technical Field

[0001] This invention relates to a mechanical testing system and method for a high-pressure gas-excited propeller propulsion system, belonging to the field of mechanical testing technology. Background Technology

[0002] For ultralight high-altitude aircraft, the periodic non-uniform forces generated by the propeller propulsion system under the influence of airflow can cause significant vibration loads on the airframe and onboard equipment. Effective and quantitative simulation of these aerodynamic forces on the ground is crucial for analyzing aircraft vibration loads.

[0003] Three intractable problems exist when conducting ground mechanical tests on high-altitude propeller propulsion systems:

[0004] (1) Because the air density at ground level is different from that at high altitude, a motor with several times to tens of times the power is needed at ground level to make the blade speed the same as at high altitude. However, the weight of the motor is much greater than that of the original motor, which makes the test system and the on-board system very different and affects the accuracy of the test.

[0005] (2) It is difficult to generate key frequency-doubled excitation loads such as 1p load (periodic bending moment load of the blade on the motor shaft caused by airflow on the non-vertical blade disk surface) on the real blade, thus making it impossible to simulate the dynamic response characteristics of the propulsion system well.

[0006] (3) When conducting a full-machine vibration test with multiple blades rotating simultaneously, it is difficult to generate controllable flapping excitation because it is difficult to apply a definite value of excitation to the actual rotating blades, which affects the comprehensiveness of the full-machine vibration test.

[0007] There is no perfect solution to these problems yet. The existing technologies include the following:

[0008] (1) The striking method is adopted, that is, the propulsion system blades are struck and the response of the machine body and equipment parts is measured. However, the blades do not rotate in this method, and the response of the propulsion system and the whole machine is quite different from the rotation state. In addition, the striking force varies greatly, making it difficult to perform quantitative analysis.

[0009] (2) Periodic excitation of fixed parts such as the propulsion system motor using a vibrator cannot effectively simulate the bending moment of the blades on the motor shaft, thus affecting the comprehensiveness of the test. The present invention uses a high-pressure air nozzle to blow air backward on one simulated blade fan surface and air forward on another simulated blade fan surface, thereby forming a pair of force couples and thus applying torque to the propulsion system. Summary of the Invention

[0010] The technical problem solved by the present invention is to overcome the shortcomings of the prior art and provide a mechanical testing system for a high-pressure air-excited propeller propulsion system. By simulating the design of the blades and the high-pressure blowing system, it can better simulate key load types such as periodic torque.

[0011] The technical solution of this invention is:

[0012] This invention discloses a mechanical testing system for a high-pressure air-excited propeller propulsion system, comprising: several mechanical testing devices, each including a simulated propeller blade, a high-pressure air blowing system, a motor, and a motor support; wherein, the simulated propeller blade is connected to the motor, the motor is fixed by the motor support, the motor drives the simulated propeller blade to rotate at high speed, and the high-pressure air blowing system applies high-pressure air loading to the rotating simulated propeller blade; when the motor drives the simulated propeller blade to rotate, the high-pressure air blowing generates an approximate square wave excitation on the simulated propeller blade; by adjusting the motor speed of multiple mechanical testing devices, a beat vibration excitation test is achieved.

[0013] Furthermore, in the above-mentioned test system, the simulated blade includes a stiffness simulation rod, a fixed fixture, and an air-blowing fan blade; wherein, the air-blowing fan blade is connected to the end of the stiffness simulation rod, and the end of the stiffness simulation rod away from the air-blowing fan blade is connected to the fixed fixture.

[0014] Furthermore, in the above-mentioned testing system, the end of the stiffness simulation rod connected to the air blowing fan blade and the end connected to the fixed fixture are both cylindrical hollow structures with a flat hollow structure in the middle, which serves to adjust the stiffness.

[0015] Furthermore, in the aforementioned testing system, the air-blowing fan blade has an arc-shaped box structure with a circular hole on one side near the center, which matches the end of the fixing fixture.

[0016] Furthermore, in the above-mentioned test system, the surface of the air-blowing fan blades is smooth and flat.

[0017] Furthermore, in the aforementioned test system, two simulated blades are fixed to the motor bearings using a fixture.

[0018] Furthermore, in the above-mentioned test system, the high-pressure blowing system includes a high-pressure jet pipe and a gas control device; wherein, the gas control device controls the high-pressure jet pipe to blow air onto the surface of the blowing fan blades.

[0019] Furthermore, in the above-mentioned test system, the high-pressure jet pipe includes two air outlets, which blow air in opposite directions on the same plane and load the two air-blowing fan blades respectively.

[0020] Furthermore, in the aforementioned testing system, the structural weight and inertia of the simulated blade are matched with those of the real blade, and the mass characteristics of the simulated blade are the same as those of the real blade.

[0021] This invention discloses a mechanical testing method for a high-pressure gas-excited propeller propulsion system, using a mechanical testing system for a high-pressure gas-excited propeller propulsion system, comprising:

[0022] S1. Install and secure the motor bracket, motor, and simulated blades in place;

[0023] S2. Use a high-pressure jet pipe to blow air into the electronic scale to calibrate the vertical offset. By measuring the numerical stability, calibrate the application of aerodynamic force of the high-pressure blowing system.

[0024] S3. Install acceleration sensors and strain sensors on the simulated blades, motor bearings, and motor brackets.

[0025] S4. Turn on and adjust the motor speed, turn on the high-pressure air blowing system, and measure the dynamic response of the system under test through the acceleration sensor and strain sensor.

[0026] The advantages of this invention over the prior art are as follows:

[0027] (1) The present invention designs a blower blade with low torsional resistance, and the upper motor can drive the simulated blade to achieve high-speed ground test.

[0028] (2) The present invention designs a stiffness simulation rod with a flat stiffness adjustment zone and a hollowed-out air blowing fan blade, so that the simulated blade has the same weight, inertia and stiffness as the real blade, and the simulated blade has the same excitation response characteristics as the real blade.

[0029] (3) The present invention designs a high-pressure gas blowing loading system, which uses high-pressure gas loading to ensure the accuracy and consistency of the test force.

[0030] (4) The present invention designs multiple sets of high-pressure air blowing and air loading systems that work together, and can conduct multiple sets of propulsion system vibration excitation tests. Attached Figure Description

[0031] Figure 1 The three views of the air-blowing fan blade of the present invention are shown in (a) front view, (b) side view, and (c) top view.

[0032] Figure 2 The following are plan views of the stiffness simulation rod of the present invention: (a) is the front view, and (b) is the side view.

[0033] Figure 3 The following are plan and perspective views of the simulated blade and central fixed tooling assembly of the present invention; (a) is a front view, (b) is a side view, and (c) is a perspective view.

[0034] Figure 4This is an assembly diagram of the simulated propeller blade, central fixed fixture, motor, motor support rod, and wing of the present invention.

[0035] Figure 5 This is a side view of a single loading system of the present invention;

[0036] Figure 6 This is a three-dimensional view of a single loading system of the present invention;

[0037] Figure 7 This is a schematic diagram of multiple propulsion system flapping excitation tests conducted according to the present invention. Detailed Implementation

[0038] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0039] like Figure 7 As shown, this embodiment provides a mechanical testing system for a high-pressure gas-excited propeller propulsion system, including: several mechanical testing devices, such as... Figure 6 As shown, it includes a simulated blade, a high-pressure blowing system 6, a motor 4, and a motor bracket 5; wherein, the simulated blade is connected to the motor 4, and the motor 4 is fixed by the motor bracket 5, as shown. Figure 4 As shown, motor 4 drives the simulated blade to rotate at high speed, and high-pressure air blowing system 6 applies high-pressure air to the rotating simulated blade. When the motor drives the simulated blade to rotate, the high-pressure air blowing generates an approximate square wave excitation on the simulated blade. By adjusting the motor speed of multiple mechanical testing devices, the beat vibration excitation test is realized.

[0040] Preferably, such as Figure 3 As shown, the simulated blade includes a stiffness simulation rod 1, a fixed fixture 3, and an air-blowing fan blade 2; wherein, the air-blowing fan blade 2 is connected to the end of the stiffness simulation rod 1, and the end of the stiffness simulation rod 1 away from the air-blowing fan blade 2 is connected to the fixed fixture 3.

[0041] Preferably, such as Figure 2 As shown, the end of the stiffness simulation rod 1 connected to the air blower blade 2 and the end connected to the fixed fixture 3 are both cylindrical hollow structures with a flat hollow structure in the middle, which serves to adjust the stiffness.

[0042] Preferably, such as Figure 1 As shown, the air blowing fan blade 2 has an arc-shaped box structure, with a round hole on one side near the center, which matches the end of the fixing fixture 3.

[0043] Preferably, the surface of the air-blowing fan blade 2 is smooth and flat.

[0044] Preferably, the two simulated blades are fixed to the bearings of the motor by a fixing fixture 3.

[0045] Preferably, the high-pressure blowing system 6 includes a high-pressure jet pipe and a gas control device; wherein the gas control device controls the high-pressure jet pipe to blow air onto the surface of the blowing fan blade 2.

[0046] Preferably, the high-pressure jet pipe includes two air outlets, which are on the same plane and blow air in opposite directions onto two air-blowing fan blades. For example... Figure 5 As shown.

[0047] Preferably, the structural weight and inertia of the simulated blade are matched with those of the real blade, and the mass characteristics of the simulated blade are the same as those of the real blade.

[0048] This invention discloses a mechanical testing method for a high-pressure gas-excited propeller propulsion system, using a mechanical testing system for a high-pressure gas-excited propeller propulsion system, comprising:

[0049] S1. Install and secure the motor bracket 5, motor 4 and simulated blades in place;

[0050] S2. Use a high-pressure jet pipe to blow air into the electronic scale to calibrate the vertical offset. By measuring the numerical stability, calibrate the application of the pneumatic force of the high-pressure blowing system 6.

[0051] S3. Install acceleration sensors and strain sensors on the simulated blades, bearings of motor 4, and motor brackets.

[0052] S4. Turn on and adjust the speed of motor 4, turn on the high-pressure blowing system 6, and measure the dynamic response of the system under test through the acceleration sensor and strain sensor.

[0053] Example

[0054] This embodiment provides a mechanical testing system for a high-pressure gas-excited propeller propulsion system, including:

[0055] The simulated blade consists of a stiffness simulation rod 1 and an air-blowing fan blade 2. The stiffness simulation rod is mostly a cylindrical hollow structure with a flat stiffness adjustment area at the end. The hollow structure matches the weight and inertia of the simulated blade to those of a real blade, while the flat stiffness adjustment area matches the stiffness of the simulated blade to those of a real blade. The air-blowing fan blade is also a hollow structure to facilitate mass adjustment, ensuring that the simulated blade has the same mass characteristics as a real blade. The smooth and flat surface of the air-blowing fan blade facilitates the generation of stable loads when subjected to high-pressure air impact.

[0056] Two simulated blades are fixed to the motor shaft by the central fixing fixture 3.

[0057] A high-pressure blowing system 6 is used to blow air onto the rotating simulated blades. The high-pressure jet pipe is fixed. When the motor rotates, the high-pressure gas generates an approximate square wave excitation on the system.

[0058] In full machine mode, multiple systems are combined, and vibration excitation is achieved by fine-tuning the speed of multiple motors.

[0059] Specific usage instructions:

[0060] (1) Install and secure the motor bracket 5, motor 4 and simulated blades in place;

[0061] (2) Blow air onto the fan surface at a constant pressure through the high-pressure air pipe and calibrate the aerodynamic force applied by the high-pressure blowing system;

[0062] (3) Turn on and adjust the motor speed, turn on the high-pressure blowing system 6, and measure the dynamic response of the system;

[0063] (4) After the single propulsion system test is completed, the vibration excitation test of multiple test systems of the whole machine is carried out. During the test, multiple motors rotate to the rated speed at the same time. Then the blowing system starts to work to realize the loading of aerodynamic force. The motors and simulated blades of each system will start to vibrate and respond. The vibration responses of multiple systems are coupled (mutually influence) to form a comprehensive response.

[0064] The above description is only the best specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the protection scope of the present invention.

[0065] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A mechanical testing system for a high-pressure gas-excited propeller propulsion system, characterized in that, include: Several mechanical testing devices, the mechanical testing devices including simulated blades, high-pressure air blowing system (6), motor (4) and motor bracket (5); wherein, the simulated blades are connected to the motor (4), the motor (4) is fixed by the motor bracket (5), the motor (4) drives the simulated blades to rotate at high speed, the high-pressure air blowing system (6) applies high-pressure air to the rotating simulated blades, when the motor drives the simulated blades to rotate, the high-pressure air generates an approximate square wave excitation on the simulated blades; by adjusting the motor speed of multiple mechanical testing devices, the beat vibration excitation test is realized; The simulated blade includes a stiffness simulation rod (1), a fixing fixture (3), and an air-blowing fan blade (2); wherein the air-blowing fan blade (2) is connected to the end of the stiffness simulation rod (1), and the end of the stiffness simulation rod (1) away from the air-blowing fan blade (2) is connected to the fixing fixture (3). The end of the stiffness simulation rod (1) connected to the air blower (2) and the end connected to the fixed fixture (3) are both cylindrical hollow structures with a flat hollow structure in the middle, which plays a role in stiffness adjustment. The blowing fan blade (2) has an arc-shaped box structure; the high-pressure blowing system (6) includes a high-pressure jet pipe and gas control equipment; The high-pressure jet pipe includes two air outlets, which blow air in opposite directions on the same plane and are loaded onto two air-blowing fan blades. The simulated blade's structural weight and inertia match those of the real blade, and its mass characteristics are identical to those of the real blade.

2. The mechanical testing system for a high-pressure gas-excited propeller propulsion system according to claim 1, characterized in that: The blower blade (2) has a circular hole on one side near the center, which matches the end of the fixing fixture (3).

3. The mechanical testing system for a high-pressure gas-excited propeller propulsion system according to claim 2, characterized in that: The surface of the blower blade (2) is smooth and flat.

4. The mechanical testing system for a high-pressure gas-excited propeller propulsion system according to claim 2, characterized in that: Two simulated blades are fixed to the bearings of the motor by a fixture (3).

5. The mechanical testing system for a high-pressure gas-excited propeller propulsion system according to claim 1, characterized in that: The gas control device controls the high-pressure jet pipe to blow air onto the surface of the blowing fan blade (2).

6. A mechanical testing method for a high-pressure gas-excited propeller propulsion system, characterized in that, The mechanical testing system for a high-pressure gas-excited propeller propulsion system as described in claims 1-5 includes: S1. Install and secure the motor bracket (5), motor (4) and simulated blades in place; S2. Use a high-pressure jet pipe to blow air into the electronic scale to calibrate the vertical offset. By measuring the numerical stability, calibrate the application of aerodynamic force of the high-pressure blowing system (6). S3. Install acceleration sensors and strain sensors on the bearings and motor brackets of the simulated blades and motor (4); S4. Turn on and adjust the speed of the motor (4), turn on the high-pressure blowing system (6), and measure the dynamic response of the system under test through the acceleration sensor and the strain sensor.

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