A vibration active control test device and method based on hub top mounting

Abstract

The application belongs to the field of helicopter vibration active control, and relates to a vibration active control test device and method based on hub top mounting. The device comprises a hub top-mounted vibration active control system and a controlled object thereof, and an 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 a hub top placement. Background Art

[0002] Active vibration control based on a top-mounted hub is an advanced technology in the international helicopter industry. It targets vibration at the hub, the source of vibration, and "offsets vibration with vibration," comprehensively reducing the vibration loads transmitted to the airframe. The Lynx helicopter is equipped with a top-mounted hub vibration control system, achieving excellent vibration control results. This hub-mounted vibration control system primarily consists of a hub-mounted actuator, a hub-mounted active vibration controller, software, vibration sensors, and rotor speed sensors. Developing targeted test methods and equipment is a key step in the development of hub-mounted vibration control systems, a field not currently available in China. Summary of the Invention

[0003] Purpose of the invention: To propose a vibration active control test method and device based on hub top placement, filling 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-mounted vibration active control system includes: a system host computer, a hub-mounted vibration active controller, a hub-mounted vibration active control actuator, a slip ring, a rotor speed sensor, and a control acceleration sensor. The controlled objects of the hub-mounted 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-mounted vibration active control system is an adaptive control system with a hub-mounted vibration active controller as the control center. The rotor speed signal is collected by the rotor sensor and input into the controller. The vibration signal collected by the control acceleration sensor is input into the hub-mounted vibration active controller. The hub-mounted vibration active controller uses the hub-mounted vibration control algorithm to solve the two types of signals, calculate and form a control instruction, and the instruction is input into the hub-mounted vibration active control actuator through the collector ring. The hub-mounted vibration active control actuator has a built-in driving algorithm to solve and execute the control instruction, and outputs an actuating force in real time to offset the vibration of the sensor part caused by the exciter, thereby realizing active vibration control. The system host computer is the system's overall control center, used to send instructions to the controller.

[0009] The excitation system is used to implement the excitation force, simulating the excitation of the helicopter rotor on the hub. The reference acceleration vibration signal is obtained through the data acquisition system. The control command is calculated by the host computer, and the host computer transmits the control command to the coordinated loading system to drive the exciter to perform 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, generating an in-plane exciting force, and the excitation function is realized through the host computer and the coordinated loading system.

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

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

[0014] Step 1: Connect the components of the device without power 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: Conduct functional verification of the hub-mounted active vibration controller and the hub-mounted active vibration control actuator through the slip ring interface. Under normal operating conditions, the controller is set to output a current command signal, which is transmitted to the actuator through the slip ring to drive the actuator to work. The actuator output force data is measured and recorded.

[0017] Step 4: Perform functional verification of the interface between the hub-mounted active vibration controller and the rotor speed sensor. Under normal system operation, 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 rotating 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 functional test of the hub-mounted active vibration controller and the hub-mounted active vibration control actuator includes:

[0020] Step 6: Conduct 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, which analyzes the control command to form the current drive signal of the actuator. The controller outputs the command signal and measures and records it.

[0021] Step 7: Conduct 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 slip ring. The frequency and amplitude of the actuating force are measured and recorded.

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

[0023] Step 8: Measure the system response without starting the vibration reduction function and the exciter. Test the system response and stability at a constant rotor speed. Test 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 at steady rotor speed; system response and stability test at variable rotor speed; rotor speed test of eccentric mass natural frequency response;

[0025] Step 10: Simulate the helicopter's ground speed and flight conditions, and model the system's secondary pathways under constant and variable rotor speed conditions; conduct control system adjustments and participate 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 active vibration control system under stable load and fast-changing load conditions.

[0027] Beneficial effects:

[0028] The present invention proposes a vibration active control test method based on the top of the hub. It plans a rigorous and comprehensive method and steps for testing the interface, components and systems of the hub-mounted vibration active control system, and verifying the system's vibration reduction function. It can effectively evaluate the functional performance of the hub-mounted 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 domestic accessibility. Each device can fully meet the test task requirements of the hub-mounted vibration active control system, laying an important equipment foundation for the successful development of the system. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0030] Figure 2This 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 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-mounted active vibration control actuator 2 (referred to as hub actuator 2), a hub-mounted active vibration 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-mounted vibration active control system includes: a DC power supply, a system host computer, a hub-mounted vibration active controller, a hub-mounted vibration active control actuator, a slip ring, a rotor speed sensor, and a control acceleration sensor. The controlled objects of the hub-mounted 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, slip ring, and system host computer.

[0035] System host computer: The system's main 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] Slip 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: collects reference acceleration signals.

[0045] Host computer: Integrates and solves the reference acceleration signal and outputs instructions to the coordinated loading system.

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

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

[0048] Reference accelerometer: 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-mounted 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-mounted vibration control algorithm to solve the two types of signals, calculate and form a control instruction, which is input into the hub actuator through the collector ring. The hub actuator has a built-in drive algorithm to solve and execute the controller instruction, and outputs the actuating 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 applies excitation force to the test device, simulating the vibration of a helicopter rotor on the hub. A reference acceleration vibration signal is obtained through the data acquisition system. The host computer calculates and controls the signal, which is then transmitted to the coordinated loading system, driving the vibrator to apply the corresponding vibration to the rotor shaft.

[0053] The controller, slip ring, and system host computer are powered by a DC power supply. The system host computer is the system's overall 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 slip ring.

[0055] The hub actuator and the collector ring are installed on the hub rotating 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 excitation force. The excitation function is realized through the host computer and the coordinated loading system.

[0058] A vibration active control test method based on hub top placement, 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. The overall main steps are:

[0059] ①System interface inspection test

[0060] Step 1: Connect all system components without powering on 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: Conduct functional verification of the interface between the controller and the actuator via the slip ring. Under normal system operation, set the controller to output a current command signal. The command signal is transmitted to the actuator via the slip ring, driving the actuator to work. Measure and record the actuator output force data.

[0063] Step 4: Perform functional verification of the interface between the controller and the rotor speed sensor. Under normal system operation, 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: Perform functional verification of the interface between the controller and the control accelerometer. When the system is in normal working condition, start the exciter to vibrate the shaft. The control accelerometer measures the vibration signal of the test bench and transmits it to the controller to 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. The controller outputs the command signal and measures and records it.

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

[0068] ③System function performance test

[0069] Step 8: Measure the system response without starting the vibration reduction function and the exciter. Test the system response and stability at a constant rotor speed. Test 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 at steady rotor speed; system response and stability test at variable rotor speed; rotor speed test of eccentric mass natural frequency response;

[0071] Step 10: Simulate the helicopter's ground speed and flight conditions, and model the system's secondary pathways under conditions of constant and variable rotor speeds; conduct control system adjustments and participate in verification tests 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 active vibration control system under stable load and fast-changing load conditions.

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-mounted vibration active control system includes: a system host computer, a hub-mounted vibration active controller, a hub-mounted vibration active control actuator, a slip ring, a rotor speed sensor, and a control acceleration sensor. The controlled objects of the hub-mounted 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-mounted vibration active control system is an adaptive control system with a hub-mounted vibration active controller as the control center. The rotor speed signal is collected by the rotor sensor and input into the controller. The vibration signal collected by the control acceleration sensor is input into the hub-mounted vibration active controller. The hub-mounted vibration active controller uses the hub-mounted vibration control algorithm to solve the two types of signals, calculate and form a control instruction, and the instruction is input into the hub-mounted vibration active control actuator through the collector ring. The hub-mounted vibration active control actuator has a built-in driving algorithm to solve and execute the control instruction, and outputs an actuating force in real time to offset the vibration of the sensor part caused by the exciter, thereby realizing active vibration control. The system host computer is the system's overall control center, used to send instructions to the controller. The excitation system is used to implement the excitation force, simulating the excitation of the helicopter rotor on the hub. The reference acceleration vibration signal is obtained through the data acquisition system. The control command is calculated by the host computer, and the host computer transmits the control command to the coordinated loading system to drive the exciter to perform the corresponding excitation to the shaft.

2. The device according to claim 1, characterized in that The hub actuator and the collector ring are installed on the hub rotating 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 described in any one of claims 1 to 4, and the method includes three types of tests carried out in sequence: 1) system interface inspection test, 2) function test test of the hub-top vibration active controller and the hub-top vibration active control actuator, and 3) 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 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: Conduct functional verification of the hub-mounted active vibration controller and the hub-mounted active vibration control actuator through the slip ring interface. Under normal operating conditions, the controller is set to output a current command signal, which is transmitted to the actuator through the slip ring to drive the actuator to work. The actuator output force data is measured and recorded. Step 4: Perform functional verification of the interface between the hub-mounted active vibration controller and the rotor speed sensor. Under normal system operation, 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 rotating 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 the hub-mounted active vibration controller and hub-mounted active vibration control actuator, including: Step 6: Conduct 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, which analyzes the control command to form the current drive signal of the actuator. The controller outputs the command signal and measures and records it. Step 7: Conduct 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 slip 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: Measure the system response without starting the vibration reduction function and the exciter. Test the system response and stability at a constant rotor speed. Test 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 at steady rotor speed; system response and stability test at variable rotor speed; rotor speed test of eccentric mass natural frequency response; Step 10: Simulate the helicopter's ground speed and flight conditions, and model the system's secondary pathways under constant and variable rotor speed conditions; conduct control system adjustments and participate 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 active vibration control system under stable load and fast-changing load conditions.

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