Propeller hub overhead-based vibration active control test device and method

Abstract

The invention belongs to the field of active vibration control of helicopters, and relates to an active vibration control test device and method based on an overhead propeller hub. The device comprises a propeller hub overhead vibration active control system, a controlled object of the propeller hub overhead vibration active control system and a vibration excitation system.

Description

Technical Field

[0001] The invention belongs to the field of active vibration control of helicopters, and relates to a vibration active control test device and method based on the top placement of a hub. Background Art

[0002] Active vibration control based on top of the hub is an advanced technology in the international helicopter field. It aims at reducing the vibration of the hub at the source of vibration and "offsetting vibration with vibration", which can comprehensively reduce the vibration load transmitted to the fuselage. The Lynx helicopter has been equipped with a hub-mounted vibration control system, which has achieved excellent vibration control effects. The vibration control system based on top of the hub mainly includes a hub-mounted actuator, a hub-mounted vibration active controller, software, vibration sensors and rotor speed sensors. The development of targeted test methods and equipment is a key link in the development of vibration control systems based on top of the hub, which is still a blank in China. Summary of the invention

[0003] Purpose of the invention: To propose a vibration active control test method and device based on the top placement of the hub, so as to fill the gap in the relevant technical field in China.

[0004] Technical solution:

[0005] In a first aspect, a vibration active control test device based on a hub top is provided, comprising: a hub top vibration active control system and a controlled object thereof, and a vibration excitation system;

[0006] The hub top vibration active control system includes: a system host computer, a hub top vibration active controller, a hub top vibration active control actuator, a collector ring, a rotor speed sensor, and a control acceleration sensor. The controlled objects of the hub top vibration active control system are the hub and the test bench.

[0007] The excitation system includes: exciter, coordinated loading system, data acquisition system, host computer, reference acceleration sensor;

[0008] The hub top vibration active control system is an adaptive control system, with the hub top vibration active controller as the control center. The rotor speed signal is collected by the rotor sensor and input into the controller, and the vibration signal collected by the control acceleration sensor is input into the hub top vibration active controller. The hub top vibration active controller uses the hub top vibration control algorithm to solve the two types of signals, calculate and form control instructions, and the instructions are input into the hub top vibration active control actuator through the collector ring. The hub top vibration active control actuator has a built-in driving algorithm to solve and execute the control instructions, and outputs the actuation force in real time to offset the vibration of the sensor part caused by the exciter, so as to realize active vibration control; the system host computer is the system master control center, which is used to send instructions to the controller;

[0009] The excitation system is used to implement the excitation force, simulate the excitation of the helicopter rotor on the hub, obtain the reference acceleration vibration signal through the data acquisition system, calculate the control command through the host computer, and then transmit the control command to the coordinated loading system to drive the exciter to execute the corresponding excitation to the shaft.

[0010] Furthermore, the hub actuator and the collector ring are installed on the hub rotation plane, and the hub is driven to rotate by the rotating shaft to achieve the rotor speed.

[0011] Furthermore, the exciter has a contact point with the rotating shaft to generate an in-plane exciting force, and the excitation function is realized through the host computer and the coordinated loading system.

[0012] In the second aspect, a hub-top-based vibration active control test method is provided, which is implemented using the above-mentioned hub-top-based vibration active control test device, and the method includes three types of tests carried out in sequence: 1) system interface inspection test, 2) hub-top-mounted vibration active controller and hub-top-mounted vibration active control actuator function test test, and 3) system function performance test test.

[0013] Further, the system interface inspection test includes:

[0014] Step 1: Connect the components of the device without power supply and check the correctness of the hardware interface design;

[0015] Step 2: After confirming that the hardware interface of the entire device is connected correctly, power on and check each component;

[0016] Step 3: Carry out functional verification of the hub-mounted active vibration controller and the hub-mounted active vibration control actuator through the collector ring interface. When the device is in normal working condition, set the controller to output a current command signal, and the command signal is transmitted to the actuator through the collector ring to drive the actuator to work, and measure and record the actuator output force data;

[0017] Step 4: Carry out functional verification of the interface between the hub-mounted active vibration controller and the rotor speed sensor. When the system is in normal working condition, the main shaft rotates, and the rotor speed sensor measures the main shaft speed and transmits it to the controller to confirm that the controller receives the speed signal.

[0018] Step 5: Carry out functional verification of the interface between the hub-mounted active vibration controller and the control acceleration sensor. When the system is in normal working condition, start the exciter to vibrate the shaft, control the acceleration sensor to measure the vibration signal of the test bench, transmit it to the controller, and confirm that the controller receives the vibration signal.

[0019] Furthermore, the function test of the hub-mounted vibration active controller and the hub-mounted vibration active control actuator includes:

[0020] Step 6: Carry out a basic test of the controller function. When the system is in normal working condition, the system host computer sends a command to the controller, and the controller analyzes the control command to form the current drive signal of the actuator, and measures and records the controller output command signal;

[0021] Step 7: Carry out a basic test of the actuator function. When the system is in normal working condition, the controller sends an output force command, which is transmitted to the actuator through the collector ring. The frequency and amplitude of the actuating force are measured and recorded.

[0022] Further, the system functional performance test includes:

[0023] Step 8: The system does not start the vibration reduction function state, does not start the exciter, measures the system response, and tests the system response and stability at a stable rotor speed; and tests the system response and stability at a variable rotor speed;

[0024] Step 9: Start the vibration exciter and test the system response under three conditions: system response and stability test under stable rotor speed; system response and stability test under variable rotor speed; rotor speed through eccentric mass natural frequency response test;

[0025] Step 10: Simulate the ground speed and flight state of the helicopter, and model the secondary path of the system under the conditions of constant and variable rotor speed; control system adjustment and participation in verification tests to verify the effectiveness of the system's vibration reduction function;

[0026] Step 11: Load the vibration load on the exciter, and test the function and performance of the hub-mounted vibration active control system under stable load state and fast load change state.

[0027] Beneficial effects:

[0028] The present invention proposes a vibration active control test method based on the top of the hub, and plans strict and comprehensive method steps for the interface, components and system testing of the hub top vibration active control system, and verification of the system vibration reduction function. It can effectively evaluate the functional performance of the hub top pin vibration active control system, and is an indispensable key link in the development and verification of the system. The present invention proposes a vibration active control test device based on the top of the hub, including key components such as a controller, an actuator, a collector ring, an exciter, and a sensor. The device is reasonably and reliably designed, and has high localization accessibility. Each device can fully meet the test task requirements of the hub top vibration active control system, laying an important equipment foundation for the successful development of the system. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is a relationship block diagram of a vibration active control test device based on the top of the hub.

[0030] Figure 2It is a principle block diagram of the vibration active control test based on the top of the hub. DETAILED DESCRIPTION

[0031] The present invention provides a vibration active control test device based on the top of the propeller hub, which is used to perform the test method, such as Figure 1 As shown, the device includes: a DC power supply 1, a hub top-mounted vibration active control actuator 2 (referred to as hub actuator 2), a hub top-mounted vibration active controller 3 (referred to as controller 3), a collector ring 4, a hub 5, a test bench 6, an exciter 7, a coordinated loading system 8, a data acquisition system 9, a host computer 10, a rotor speed sensor 11, a control acceleration sensor 12, and a reference acceleration sensor 13.

[0032] The hub top vibration active control system includes: a DC power supply, a system host computer, a hub top vibration active controller, a hub top vibration active control actuator, a collector ring, a rotor speed sensor, and a control acceleration sensor. The controlled objects of the hub top vibration active control system are the hub and the test bench.

[0033] The excitation system includes: an exciter, a coordinated loading system, a data acquisition system, a host computer, and a reference acceleration sensor.

[0034] DC power supply: used to power the controller, collector ring, and system host computer.

[0035] System host computer: The system master control center, used to send instructions to the controller.

[0036] Hub actuator: used for hub actuation and output control force.

[0037] Controller: collects, solves and outputs control signals.

[0038] Collector ring: used for power supply and data transmission.

[0039] Hub: Provides the plane of rotation.

[0040] Rotating shaft: can rotate to realize the rotor speed and the point where the exciting force is applied.

[0041] Test bench: used to simulate the body structure, provide system boundaries, and install sensors.

[0042] Exciter: Generates in-plane exciting force.

[0043] Coordinated loading system: receives instructions from the host computer and drives the exciter to generate corresponding vibration.

[0044] Data acquisition system: collect reference acceleration signals.

[0045] Host computer: Integrate and solve reference acceleration signals and output instructions to the coordinated loading system.

[0046] Rotor speed sensor: collects shaft speed signals.

[0047] Control acceleration sensor: collect vibration acceleration signal.

[0048] Reference acceleration sensor: collects vibration acceleration signals.

[0049] like Figure 2 As shown, the test principle:

[0050] The hub top vibration active control test mainly includes two systems, the hub top vibration active control system and the excitation system.

[0051] The hub top vibration active control system is an adaptive control system with a controller as the control center. The rotor speed signal is collected by the rotor sensor and input into the controller. The vibration signal is collected by the control acceleration sensor and input into the controller. The controller uses the hub top vibration control algorithm to solve the two types of signals, calculate and form control instructions, which are input into the hub actuator through the collector ring. The hub actuator has a built-in drive algorithm to solve and execute the controller instructions, and outputs the actuation force in real time to offset the vibration of the sensor part caused by the exciter, thereby realizing active vibration control.

[0052] Excitation system: The excitation system is used to apply excitation force to the test device to simulate the excitation of the helicopter rotor to the hub. The reference acceleration vibration signal is obtained through the data acquisition system, and the control command is calculated by the host computer. The host computer transmits the control command to the coordinated loading system to drive the exciter to perform the corresponding excitation to the shaft.

[0053] The controller, collector ring and system host computer are powered by a DC power supply. The system host computer is the system control center, which can send instructions to the controller and record information.

[0054] The controller transmits the output force command to the hub actuator through the collector ring.

[0055] The hub actuator and collector ring are installed on the hub rotation plane, and the rotor speed is achieved by driving the hub to rotate through the rotating shaft.

[0056] The control acceleration sensor and the reference acceleration sensor are installed on the test bench to test the vibration of the test bench.

[0057] The exciter has a contact point with the rotating shaft, which can generate an in-plane exciting force. The excitation function is realized through the host computer and the coordinated loading system.

[0058] A vibration active control test method based on the hub top, the test method includes three types of tests carried out in sequence: ① system interface inspection test, ② main component function test test, ③ system function performance test test. Overall main steps:

[0059] ①System interface inspection test

[0060] Step 1: Connect the components of the system without power supply and check the correctness of the hardware interface design;

[0061] Step 2: After confirming that the hardware interface of the entire system is connected correctly, power on and check each component of the system;

[0062] Step 3: Carry out functional verification of the interface between the controller and the actuator through the collector ring. When the system is in normal working condition, set the controller to output a current command signal, which is transmitted to the actuator through the collector ring to drive the actuator to work, and measure and record the actuator output force data;

[0063] Step 4: Carry out functional verification of the interface between the controller and the rotor speed sensor. When the system is in normal working condition, the main shaft rotates, and the rotor speed sensor measures the main shaft speed and transmits it to the controller to confirm that the controller receives the speed signal.

[0064] Step 5: Carry out functional verification of the interface between the controller and the control acceleration sensor. When the system is in normal working state, start the exciter to excite the shaft, control the acceleration sensor to measure the vibration signal of the test bench, transmit it to the controller, and confirm that the controller receives the vibration signal;

[0065] ②Main component function test

[0066] Step 6: Test the main functions of the controller. When the system is in normal working condition, the system host computer sends a command to the controller, which analyzes the control command to form the current drive signal of the actuator, and measures and records the controller output command signal.

[0067] Step 7: Test the main functions of the actuator. When the system is in normal working condition, the controller sends an output force command, which is transmitted to the actuator through the collector ring. The frequency and amplitude of the actuating force are measured and recorded.

[0068] ③System function performance test

[0069] Step 8: The system does not start the vibration reduction function state, does not start the exciter, measures the system response, and tests the system response and stability at a stable rotor speed; and tests the system response and stability at a variable rotor speed;

[0070] Step 9: Start the vibration exciter and test the system response under three conditions: system response and stability test under stable rotor speed; system response and stability test under variable rotor speed; rotor speed through eccentric mass natural frequency response test;

[0071] Step 10: Simulate the ground speed and flight state of the helicopter, and model the secondary path of the system under the conditions of constant and variable rotor speed; the control system is adjusted to participate in the verification test to verify the effectiveness of the system's vibration reduction function.

[0072] Step 11: Load the vibration load on the exciter, and test the function and performance of the hub-mounted vibration active control system under stable load state and fast load change state.

Claims

1. A vibration active control test device based on hub top placement, characterized in that: include: Hub top vibration active control system and its controlled object and excitation system; The hub top vibration active control system includes: a system host computer, a hub top vibration active controller, a hub top vibration active control actuator, a collector ring, a rotor speed sensor, and a control acceleration sensor. The controlled objects of the hub top vibration active control system are the hub and the test bench. The excitation system includes: exciter, coordinated loading system, data acquisition system, host computer, reference acceleration sensor; The hub top vibration active control system is an adaptive control system, with the hub top vibration active controller as the control center. The rotor speed signal is collected by the rotor sensor and input into the controller, and the vibration signal collected by the control acceleration sensor is input into the hub top vibration active controller. The hub top vibration active controller uses the hub top vibration control algorithm to solve the two types of signals, calculate and form control instructions, and the instructions are input into the hub top vibration active control actuator through the collector ring. The hub top vibration active control actuator has a built-in driving algorithm to solve and execute the control instructions, and outputs the actuation force in real time to offset the vibration of the sensor part caused by the exciter, so as to realize active vibration control; the system host computer is the system master control center, which is used to send instructions to the controller; The excitation system is used to implement the excitation force, simulate the excitation of the helicopter rotor on the hub, obtain the reference acceleration vibration signal through the data acquisition system, calculate the control command through the host computer, and then transmit the control command to the coordinated loading system to drive the exciter to execute the corresponding excitation to the shaft.

2. The device according to claim 1, characterized in that The hub actuator and collector ring are installed on the hub rotation plane, and the rotor speed is achieved by driving the hub to rotate through the rotating shaft.

3. The device according to claim 2, characterized in that The control acceleration sensor and the reference acceleration sensor are installed on the test bench to test the vibration of the test bench.

4. The device according to claim 3, characterized in that The exciter has a contact point with the rotating shaft, generating an in-plane exciting force, and the excitation function is realized through the host computer and the coordinated loading system.

5. A vibration active control test method based on hub top placement, characterized in that: The method is implemented using the hub-top based vibration active control test device as described in any one of claims 1 to 4, and comprises three types of tests carried out in sequence: 1) a system interface inspection test, 2) a function test test of a hub-top vibration active controller and a hub-top vibration active control actuator, and 3) a system function performance test test.

6. The method according to claim 5, characterized in that System interface inspection test, including: Step 1: Connect the components of the device without power supply and check the correctness of the hardware interface design; Step 2: After confirming that the hardware interface of the entire device is connected correctly, power on and check each component; Step 3: Carry out functional verification of the hub-mounted active vibration controller and the hub-mounted active vibration control actuator through the collector ring interface. When the device is in normal working condition, set the controller to output a current command signal, and the command signal is transmitted to the actuator through the collector ring to drive the actuator to work, and measure and record the actuator output force data; Step 4: Carry out functional verification of the interface between the hub-mounted active vibration controller and the rotor speed sensor. When the system is in normal working condition, the main shaft rotates, and the rotor speed sensor measures the main shaft speed and transmits it to the controller to confirm that the controller receives the speed signal. Step 5: Carry out functional verification of the interface between the hub-mounted active vibration controller and the control acceleration sensor. When the system is in normal working condition, start the exciter to vibrate the shaft, control the acceleration sensor to measure the vibration signal of the test bench, transmit it to the controller, and confirm that the controller receives the vibration signal.

7. The method according to claim 6, characterized in that Functional test of hub-mounted vibration active controller and hub-mounted vibration active control actuator, including: Step 6: Carry out a basic test of the controller function. When the system is in normal working condition, the system host computer sends a command to the controller, and the controller analyzes the control command to form the current drive signal of the actuator, and measures and records the controller output command signal; Step 7: Carry out a basic test of the actuator function. When the system is in normal working condition, the controller sends an output force command, which is transmitted to the actuator through the collector ring. The frequency and amplitude of the actuating force are measured and recorded.

8. The method according to claim 6, characterized in that System functional performance test, including: Step 8: The system does not start the vibration reduction function state, does not start the exciter, measures the system response, and tests the system response and stability at a stable rotor speed; and tests the system response and stability at a variable rotor speed; Step 9: Start the vibration exciter and test the system response under three conditions: system response and stability test under stable rotor speed; system response and stability test under variable rotor speed; rotor speed through eccentric mass natural frequency response test; Step 10: Simulate the ground speed and flight state of the helicopter, and model the secondary path of the system under the conditions of constant and variable rotor speed; control system adjustment and participation in verification tests to verify the effectiveness of the system's vibration reduction function; Step 11: Load the vibration load on the exciter, and test the function and performance of the hub-mounted vibration active control system under stable load state and fast load change state.

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