Engine gyroscopic effect simulation method and system for full-aircraft drop test

Abstract

The invention belongs to the field of aviation structure strength tests, and particularly relates to an engine gyroscopic effect simulation method and system for a full-aircraft drop test, and the system comprises blades, a propeller hub, a bearing, a shaft sleeve, a transmission shaft and a motor. The motor is arranged in an aircraft nacelle, the transmission shaft and the motor are coaxially arranged, one end of the transmission shaft is connected with the motor, and the other end of the transmission shaft is connected with a propeller hub and a tested propeller blade. The propeller hub is coaxially arranged on the inner side of the propeller blade; an engine mounting pull rod is arranged on the aircraft nacelle; the bearing and the shaft sleeve are connected between the transmission shaft and the engine mounting pull rod; and after the motor receives the driving signal, the blades can be driven to rotate through the transmission shaft. The gravity center distribution and inertia of the engine can be simulated in the test process, the gyroscopic effect caused by rotation of the engine can be simulated, the rotating speed of the device is consistent with the rotating speed of the aircraft propeller engine, the simulation result can be more accurate, the cost is low, and implementation is convenient.

Description

Technical Field

[0001] This application belongs to the field of aerospace structural strength testing, and specifically relates to a method and system for simulating engine gyroscopic effects in whole-aircraft drop tests. Background Technology

[0002] Most aircraft must undergo full-aircraft drop tests during the development process. Currently, there are two common methods for conducting full-aircraft drop tests: one is to use a real engine for testing, which is usually more expensive; the other is to use dummy parts with similar shape and mass to simulate the aircraft engine. This method only simulates the engine's center of gravity distribution and inertia, and cannot simulate the gyroscopic effect caused by the engine's rotation.

[0003] Therefore, how to simulate the gyroscopic effect caused by engine rotation is a problem that needs to be solved. Summary of the Invention

[0004] To address the aforementioned issues, this application provides a method and system for simulating the gyroscopic effect of an engine in a full-engine drop test, thereby resolving the problem of difficulty in simulating the gyroscopic effect caused by engine rotation in the prior art.

[0005] The technical solution of this application is: a method for simulating the gyroscopic effect of an engine for a full-aircraft drop test, including a blade, a hub, a bearing, a bushing, a drive shaft, and an electric motor;

[0006] The electric motor is located inside the aircraft nacelle, and the drive shaft is coaxially arranged with the electric motor. One end of the drive shaft is connected to the electric motor, and the other end is connected to the rotor hub and the test rotor blade. The rotor hub is coaxially arranged inside the rotor blade.

[0007] An engine mounting rod is installed on the aircraft nacelle, and the bearing and bushing are connected between the drive shaft and the engine mounting rod;

[0008] When the motor receives a drive signal, it can drive the blades to rotate through the transmission shaft.

[0009] Preferably, a propeller cap is provided on the outer side of the propeller hub, and the propeller cap is a circular, convex structure.

[0010] Preferably, the blades include blades and an outer connecting disk, and the blades are arranged in six groups at intervals along the outer circumferential direction of the outer connecting disk.

[0011] Preferably, the propeller hub includes a support plate and an inner connecting plate. The inner connecting plate and the outer connecting plate are coaxially arranged and detachably connected. There are multiple sets of support plates, which are arranged at intervals along the inner circumferential side of the inner connecting plate.

[0012] Preferably, the drive shaft is a stepped shaft, with the smaller diameter end connected to the motor and the larger diameter end fixedly connected to the wheel hub.

[0013] Preferably, there are two bearings, which are respectively connected between the two ends of the bushing and the drive shaft.

[0014] Another technical solution of this application is: a method for simulating the gyroscopic effect of an engine for a full-aircraft drop test, comprising:

[0015] Obtain the actual size and weight of the blades, and design the size and weight of the experimental blades to be consistent with the actual size and weight of the blades;

[0016] Sensors capable of collecting torque, angular velocity, and rotational speed are installed on the drive shaft and blades;

[0017] The back-end equipment outputs a control command with a set power to the motor. The motor drives the transmission shaft to rotate at the set speed, which in turn drives the blades to rotate. The torque, angular velocity, and rotational speed on the transmission shaft and blades are collected by sensors.

[0018] The gyroscopic effect data of the propeller blades are determined by torque, angular velocity, and rotational speed.

[0019] Preferably, the minimum speed of the motor is greater than 3000 rpm.

[0020] Preferably, the combined weight of the drive shaft and the motor is equal to the mass of the engine drive mechanism.

[0021] Preferably, the motor is configured with a speed range and a drive step size, and the motor is applied sequentially to different speeds within the speed range according to the set step size.

[0022] Preferably, the drive shaft is a stepped shaft, with the smaller diameter end connected to the motor and the larger diameter end fixedly connected to the wheel hub.

[0023] Preferably, there are two bearings, which are respectively connected between the two ends of the bushing and the drive shaft.

[0024] The engine gyroscopic effect simulation method and system for full-engine drop testing disclosed in this application have the following advantages:

[0025] It can not only simulate the center of gravity distribution and inertia of the engine during the test, but also simulate the gyroscopic effect caused by the engine rotation. Its rotation speed is consistent with that of the aircraft propeller engine, which makes the simulation results more accurate, and the cost is low and easy to implement.

[0026] It can completely simulate the gyroscopic effect of a rotating propeller engine, with the rotational speed adjustable as needed, and is easy to implement during testing. It can simulate the engine's center of gravity distribution and inertia during testing, resulting in more accurate test results at a lower cost. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the overall structure of this application;

[0028] Figure 2 This is a schematic diagram of the blade structure of this application;

[0029] Figure 3 This is a schematic diagram of the propeller hub structure of this application;

[0030] Figure 4 This is a schematic diagram of the bearing and bushing structure of this application;

[0031] Figure 5 This is a schematic diagram of the propeller cap structure of this application;

[0032] Figure 6 This is a schematic diagram of the transmission shaft structure of this application.

[0033] 1. Blade; 2. Hub; 3. Bearing; 4. Bushing; 5. Drive shaft; 6. Motor; 7. Blade cap. Detailed Implementation

[0034] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0035] The first aspect of this application provides an engine gyroscopic effect simulation system for full-aircraft drop testing, such as... Figures 1-6 As shown, it includes blade 1, hub 2, bearing 3, bushing 4, drive shaft 5, and motor 6.

[0036] The electric motor 6 is located in the aircraft nacelle. The drive shaft 5 is coaxially arranged with the electric motor 6. One end of the drive shaft 5 is connected to the electric motor 6, and the other end is connected to the rotor hub 2 and the test rotor blade 1. The rotor hub 2 is coaxially arranged inside the rotor blade 1.

[0037] The aircraft nacelle is equipped with an engine mounting rod, and bearing 3 and bushing 4 are connected between the drive shaft 5 and the engine mounting rod.

[0038] When the motor 6 receives the drive signal, it can drive the blade 1 to rotate through the transmission shaft 5.

[0039] The propeller blade 1 is made according to the shape, size and weight of the real engine propeller blade 1. By controlling the electric motor 6 to work in the working state of a real engine under normal landing, the propeller blade 1 rotates in a manner close to the real landing condition, thereby simulating the actual gyroscopic effect of the engine.

[0040] It can completely simulate the gyroscopic effect of a rotating propeller engine, with the rotational speed adjustable as needed, and is easy to implement during testing. It can simulate the engine's center of gravity distribution and inertia during testing, resulting in more accurate test results at a lower cost.

[0041] In a specific example, the parameters of each part are shown in the table below:

[0042] Table 1. Component List for Propeller Dummy Model

[0043]

[0044] Preferably, the outer side of the propeller hub 2 is provided with a propeller cap 7, which is a circular convex structure that protects the propeller hub 2.

[0045] Preferably, the blade 1 includes blades and an outer connecting disk. There are six sets of blades arranged at intervals along the outer circumferential direction of the outer connecting disk to simulate an actual blade.

[0046] Preferably, the propeller hub 2 includes a support plate and an inner connecting plate. The inner connecting plate and the outer connecting plate are coaxially arranged and detachably connected. There are multiple sets of support plates, which are arranged at intervals along the inner circumferential side of the inner connecting plate.

[0047] Preferably, the drive shaft 5 is a stepped shaft, with the end of the drive shaft 5 with a smaller diameter connected to the motor 6 and the end with a larger diameter fixedly connected to the wheel hub to ensure transmission efficiency.

[0048] Preferably, there are two bearings 3, which are respectively connected between the two ends of the bushing 4 and the drive shaft 5 to prevent the drive shaft 5 from deviating.

[0049] As another specific implementation, a method for simulating the engine gyroscopic effect in a full-aircraft drop test includes:

[0050] Obtain the dimensions and weight of the actual blade 1, and design the dimensions and weight of the experimental blade 1 to be consistent with the dimensions and weight of the actual blade 1;

[0051] Sensors capable of collecting torque, angular velocity, and rotational speed are installed on the drive shaft 5 and the blade 1;

[0052] The background equipment outputs a control command with a set power to the motor 6. The motor 6 drives the transmission shaft 5 to rotate at the set speed, which in turn drives the blade 1 to rotate. The torque, angular velocity and rotation speed on the transmission shaft 5 and the blade 1 are collected by the sensor.

[0053] The gyroscopic effect data of blade 1 were determined by torque, angular velocity, and rotational speed.

[0054] Preferably, the minimum speed of the motor 6 is greater than 3000 rpm.

[0055] Preferably, the combined weight of the drive shaft 5 and the motor is equal to the mass of the engine drive mechanism.

[0056] Preferably, the motor 6 is configured with a speed range and a drive step size, and the motor 6 sequentially applies loads to different speeds within the speed range according to the set step size.

[0057] Preferably, the drive shaft 5 is a stepped shaft, with the end of the drive shaft 5 with a smaller diameter connected to the motor 6 and the end with a larger diameter fixedly connected to the wheel hub.

[0058] Preferably, there are two bearings 3, which are respectively connected between the two ends of the bushing 4 and the drive shaft 5.

[0059] This application has the following advantages:

[0060] The above design not only simulates the engine's center of gravity distribution and inertia during the test, but also simulates the gyroscopic effect caused by the engine's rotation. Its rotation speed is consistent with that of the aircraft propeller engine, making the simulation results more accurate, and the cost is low and easy to implement.

[0061] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A simulation system for engine gyroscopic effects in a full-engine drop test, characterized in that, It includes blades (1), hub (2), bearings (3), bushings (4), drive shaft (5), and motor (6); The electric motor (6) is located in the aircraft nacelle. The drive shaft (5) is coaxially arranged with the electric motor (6). One end of the drive shaft (5) is connected to the electric motor (6), and the other end is connected to the rotor hub (2) and the test rotor blade (1). The rotor hub (2) is coaxially arranged inside the rotor blade (1). An engine mounting rod is provided on the aircraft nacelle, and the bearing (3) and bushing (4) are connected between the drive shaft (5) and the engine mounting rod; When the motor (6) receives the drive signal, it can drive the blade (1) to rotate through the transmission shaft (5).

2. The engine gyroscopic effect simulation system for full-engine drop testing as described in claim 1, characterized in that, The outer side of the propeller hub (2) is provided with a propeller cap (7), which is a circular convex structure.

3. The engine gyroscopic effect simulation system for full-engine drop testing as described in claim 1, characterized in that, The blade (1) includes blades and an outer connecting disk. There are six sets of blades arranged at intervals along the outer circumferential direction of the outer connecting disk.

4. The engine gyroscopic effect simulation system for full-engine drop testing as described in claim 3, characterized in that, The propeller hub (2) includes a support plate and an inner connecting plate. The inner connecting plate and the outer connecting plate are coaxially arranged and detachably connected. There are multiple sets of support plates, which are arranged at intervals along the inner circumferential side of the inner connecting plate.

5. The engine gyroscopic effect simulation system for full-engine drop testing as described in claim 1, characterized in that, The drive shaft (5) is a stepped shaft. The end of the drive shaft (5) with a smaller diameter is connected to the motor (6), and the end with a larger diameter is fixedly connected to the wheel hub.

6. The engine gyroscopic effect simulation system for full-engine drop testing as described in claim 1, characterized in that, There are two bearings (3), which are respectively connected between the two ends of the bushing (4) and the drive shaft (5).

7. A method for simulating engine gyroscopic effects in a full-aircraft drop test, employing the system described in any one of claims 1-6, characterized in that, include: Obtain the size and weight of the real blade (1), and design the size and weight of the experimental blade (1) to be consistent with the size and weight of the real blade (1); Sensors capable of acquiring torque, angular velocity and rotational speed are installed on the drive shaft (5) and the blade (1); The background equipment outputs a control command with a set power to the motor (6). The motor (6) drives the transmission shaft (5) to rotate according to the set speed, which in turn drives the blade (1) to rotate. The torque, angular velocity and speed on the transmission shaft (5) and blade (1) are collected by the sensor. The gyroscopic effect data of the blade (1) were determined by torque, angular velocity and rotational speed.

8. The engine gyroscopic effect simulation method for full-aircraft drop testing as described in claim 7, characterized in that, The minimum speed of the electric motor (6) is greater than 3000 rpm.

9. The engine gyroscopic effect simulation method for full-aircraft drop testing as described in claim 7, characterized in that, The combined weight of the drive shaft (5) and the motor is equal to the mass of the engine drive mechanism.

10. The engine gyroscopic effect simulation method for full-aircraft drop testing as described in claim 7, characterized in that, The speed range and drive step size are set for the motor (6), and the motor (6) loads different speeds within the speed range in sequence according to the set step size.

11. The engine gyroscopic effect simulation method for full-aircraft drop testing as described in claim 7, characterized in that, The drive shaft (5) is a stepped shaft. The end of the drive shaft (5) with a smaller diameter is connected to the motor (6), and the end with a larger diameter is fixedly connected to the wheel hub.

12. The engine gyroscopic effect simulation method for full-aircraft drop testing as described in claim 7, characterized in that, There are two bearings (3), which are respectively connected between the two ends of the bushing (4) and the drive shaft (5).

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