Ground verification device and method for helicopter rotor anti-icing and deicing electric control system

Abstract

The invention belongs to the field of rotor anti-icing and de-icing systems, and discloses a helicopter rotor anti-icing and de-icing electric control system ground verification device and method, and the device comprises an icing signal simulator, a high-speed turntable, a low-speed turntable, a console, a main rotor simulation load and a tail rotor simulation load. The icing signal simulator is connected with the anti-icing and deicing electric control system controller and is used for providing an icing simulation signal; the lower rotary table is used for driving the simulation main propeller hub to rotate, and the high-speed rotary table is used for driving the simulation tail propeller hub to rotate; the console is used for controlling the high-speed turntable and the low-speed turntable; collector rings are arranged on the simulation main rotor and the tail rotor; and the main rotor simulation load and the tail rotor simulation load are connected with the collector ring and are respectively used for simulating the electric power of the main rotor heating subsystem and the tail rotor heating subsystem.

Description

Technical Field

[0001] The invention belongs to the field of rotor anti-icing and deicing systems, and in particular relates to a ground verification device and method for a helicopter rotor anti-icing and deicing electronic control system. Background Art

[0002] my country has a vast territory and complex climatic conditions. In the coastal areas, especially in the coastal areas north of the Yangtze River, there are widespread icing climate conditions in spring and winter, and the icing clouds are mainly concentrated in most of the flight activity space of helicopters below 6,000 to 7,000 meters. With the continuous expansion of the use of helicopters, they have been developed and applied to lifesaving, exploration, emergency rescue, public security and firefighting. Users have higher and higher requirements for the safety of helicopter use. Not only do they require helicopters to be able to fly normally at low altitudes on land and sea, but they also require helicopters to be able to fly safely and normally at high altitudes and under icing weather conditions, and to perform specific tasks, which requires helicopters to have anti-icing and de-icing capabilities.

[0003] The helicopter rotor anti-icing system uses electric heating to achieve the main rotor blade de-icing and tail rotor blade anti-icing functions. In order to ensure the rationality and correctness of the design of the rotor anti-icing electronic control system, the entire system must be tested on the ground before installation to verify the control logic, interface relationship, load characteristics and matching relationship of each component of the rotor anti-icing electronic control system. The existing technology lacks effective and reliable testing technology for the helicopter rotor anti-icing electronic control system before installation. Summary of the invention

[0004] Purpose of the invention: In view of the problem that the existing pre-installation test technology of helicopter rotor anti-icing and deicing electronic control systems is immature, the present invention provides a ground verification device and method for a helicopter rotor anti-icing and deicing electronic control system.

[0005] Technical Solution

[0006] A ground verification device for a helicopter rotor anti-icing and de-icing electric control system, comprising: an icing signal simulator, a high-speed turntable, a low-speed turntable, a control console, a main rotor simulation load, and a tail rotor simulation load;

[0007] The icing signal simulator is connected to the anti-icing and de-icing electronic control system controller to provide an icing simulation signal;

[0008] The lower turntable is used to drive the simulated main rotor hub to rotate, and the high-speed turntable is used to drive the simulated tail rotor hub to rotate;

[0009] The control console is used to control the high-speed turntable and the low-speed turntable;

[0010] The simulated main rotor and tail rotor are provided with collector rings;

[0011] The main rotor simulated load and the tail rotor simulated load are connected to the collector ring and are used to simulate the electrical power consumption of the main rotor and tail rotor heating subsystems respectively.

[0012] Furthermore, the main propeller simulation load includes N groups of load combinations for simulating heating elements on N blades, each group of loads is divided into M small groups to simulate M heating zones, each heating zone includes three independent loads to simulate three metal heating elements with equal resistance, and the three independent loads are connected in a star shape and correspond to the three-phase electricity of the alternating current.

[0013] Furthermore, the main simulated load is a single sliding rheostat with a resistance of 12Ω and a rated power of 5KW.

[0014] Furthermore, the tail rotor simulation load includes P groups of load combinations, and each group of loads includes three heating resistors with the same resistance value;

[0015] The tail rotor simulation load uses a single sliding rheostat with a resistance of 9Ω and a rated power of 3KW.

[0016] Furthermore, the icing signal simulator is used to simulate the icing signal output by the icing detector, the atmospheric environment temperature signal, and the tail rotor internal temperature signal.

[0017] A ground verification method for a helicopter rotor anti-icing and de-icing electronic control system includes the following contents:

[0018] Automatic mode light icing test with collector ring not in operation;

[0019] Manual mode slight icing test with collector ring not in operation;

[0020] Anti-icing and de-icing system function test at constant speed;

[0021] Fault injection testing.

[0022] Furthermore, the automatic mode slight icing test process with the collector ring not in operation is as follows:

[0023] A1) Reliably connect the test cables to each finished test piece, signal simulator, and ground power supply to confirm that the model is correct and the power supply is correct;

[0024] A2) Turn on the "self-check" switch on the rotor anti-icing control panel, and the indicator lights for monitoring the simulated load of the main rotor and the simulated load of the tail rotor should light up cyclically according to the control sequence. Finally, the "main rotor" and "tail rotor" indicators on the rotor anti-icing control panel light up, indicating that the system circuit and control logic are correct;

[0025] A3) Turn the anti-icing mode selector switch on the rotor anti-icing control panel to the "automatic" position;

[0026] A4) Set the atmospheric temperature signal to "T1", which is close to the atmospheric temperature of the aircraft's flight environment;

[0027] A5) Set the tail rotor internal temperature signal to be lower than "T2", which is closer to the actual temperature;

[0028] A6) The signal simulator is set to output slight icing;

[0029] A7) Turn on the "anti-icing" switch on the rotor anti-icing control panel. When the "icing" alarm is given, the anti-icing system will work and the main and tail rotor simulated loads will be automatically turned on.

[0030] A8) The "Icing" warning light and the "Rotor Anti-Icing" warning light are on;

[0031] A9) The test system monitors and records the main and tail rotor heating operating voltage and current values ​​during a cycle;

[0032] A10) simultaneously recording the information received on the icing signal simulator;

[0033] A11) Slowly adjust the temperature setting knob of the tail rotor on the test bench until the three-phase current output from the anti-icing distribution box to the tail rotor heating pad is 0, and record the upper temperature limit T11 of the tail rotor stopping heating;

[0034] A12) Slowly adjust the tail rotor internal temperature setting knob on the test bench until the three-phase current output from the anti-icing distribution box to the tail rotor heating pad is not 0, and record the lower limit value T12 of the temperature at which the tail rotor starts heating at this time;

[0035] A13) Disconnect the anti-ice switch on the rotor anti-ice control panel.

[0036] Furthermore, the manual mode slight icing test process with the collector ring not in operation is as follows:

[0037] B1) Reliably connect the test cables to each finished test piece, signal simulator, and ground power supply to confirm that the model is correct and the power supply is correct;

[0038] B2) Turn on the "self-check" switch on the rotor anti-icing control panel, and the indicator lights for monitoring the simulated load of the main rotor and the simulated load of the tail rotor should light up cyclically according to the control sequence. Finally, the "main rotor" and "tail rotor" indicators on the rotor anti-icing control panel light up, indicating that the system circuit and control logic are correct;

[0039] B3) Turn the anti-icing mode selector switch on the rotor anti-icing control panel to the "manual" position;

[0040] B4) Set the atmospheric environment temperature signal to "T3", which is close to the atmospheric temperature of the aircraft's flight environment;

[0041] B5) Set the tail rotor internal temperature signal to a value lower than "T4" so that it is closer to the actual temperature;

[0042] B6) The signal simulator is set to output slight icing;

[0043] B7) Turn on the "anti-icing" switch on the rotor anti-icing control panel, and when the "icing" alarm is given, the anti-icing system will work and the main and tail rotor simulated loads will be automatically turned on;

[0044] B8) The "Icing" warning light and the "Rotor Anti-Icing" warning light are on;

[0045] B9) The test system monitors and records the main and tail rotor heating operating voltage and current values ​​during a cycle;

[0046] B10) simultaneously recording the electromechanical information received on the signal simulator;

[0047] B11) Slowly adjust the temperature setting knob of the tail rotor on the test bench until the three-phase current output from the anti-icing distribution box to the tail rotor heating pad is 0, and record the upper temperature limit T21 when the tail rotor stops heating;

[0048] B12) Slowly adjust the tail rotor internal temperature setting knob on the test bench until the three-phase current output from the anti-icing distribution box to the tail rotor heating pad is not 0, and record the lower limit value T22 of the temperature at which the tail rotor starts to heat.

[0049] B13) Disconnect the anti-ice switch on the rotor anti-ice control panel.

[0050] Furthermore, the function test process of the anti-icing system at a constant speed is as follows:

[0051] Control the low-speed turntable and the high-speed turntable to reach the test speed, the rated speed of the main rotor is 212r / min, the rated speed of the tail rotor is 1013r / min, turn on the rotor anti-icing system, and repeat steps A1-A13.

[0052] Further, the fault injection test process is as follows:

[0053] C1) Disconnect all simulated loads on the main propeller. At this time, the alarm system outputs the "main propeller de-icing failure" warning light. Check the communication data with the electromechanical management system. It should be "main propeller de-icing failure";

[0054] C2) Restore the system to its initial state, start the rotor anti-icing system, and the system works normally;

[0055] C3) Disconnect the simulated load of one set of main propellers. At this time, the alarm system outputs the main caution light of "main propeller de-icing failure". Check the communication data with the electromechanical management system. It should be "main propeller de-icing failure";

[0056] C4) Restore the system to its initial state, start the rotor anti-icing system, and the system works normally;

[0057] C5) Disconnect the simulated load of the tail rotor. At this time, the warning system outputs the "tail rotor anti-icing failure" warning light. Check the communication data with the electromechanical management system. It should be "tail rotor anti-icing failure";

[0058] C6) Restore the system to its initial state, start the rotor anti-icing system, and the system works normally;

[0059] C7) Set the temperature sensor I switch on the test console to the "off position". At this time, the warning system outputs the "tail rotor temperature sensor failure" main warning light. Check the communication data with the electromechanical management system. It should be "tail rotor temperature sensor failure";

[0060] C8) Restore the system to its initial state, start the rotor anti-icing system, and the system works normally;

[0061] C9) Set the temperature sensor I switch and the temperature sensor II switch on the test console to the "off" position. At this time, the warning system outputs the "tail rotor temperature sensor failure" main warning light. Check the communication data with the electromechanical management system. It should be "tail rotor temperature sensor failure";

[0062] C10) Restore the system to its initial state, start the rotor anti-icing system, and the system works normally;

[0063] C11) Set the switch of the ice detector simulator on the test bench to the "off" position. At this time, the warning system outputs the "ice detection failure" main warning light. Check the communication data with the electromechanical management system. It should be "ice detection failure";

[0064] C12) Restore the system to its initial state, start the rotor anti-icing system, and the system works normally;

[0065] C13) Set the atmospheric temperature sensor simulator switch on the test bench to the "off" position. At this time, the alarm system outputs the "main rotor de-icing failure" and "tail rotor anti-icing failure" warning lights. Check the communication data with the electromechanical management system, which should be "atmospheric temperature sensor failure".

[0066] In summary, the beneficial effects of the present invention are as follows:

[0067] This patent innovatively established the ground verification technology environment of the rotor anti-icing and de-icing electronic control system in the electrical test room for the first time:

[0068] a) The output signals of sensors such as atmospheric temperature, ice detection, and blade internal temperature under moderate icing weather conditions are simulated by a signal simulator to create input conditions for the rotor anti-icing controller.

[0069] b) Set up the RS-422 communication interface through the host computer to communicate with the anti-icing controller, and simultaneously detect its communication function and the working status and fault information of its system.

[0070] c) The main and tail rotor simulation load boxes are used to simulate the power consumption of 5 sections of each of the 6 main rotors, and the power consumption of 3 sections of each of the 5 tail rotors, as well as the working status indication of each section.

[0071] d) By establishing a rotor anti-icing main and tail rotor collector ring assembly operation test bench, the main and tail rotor collector ring assemblies are installed and operated at the actual operating speed. A high-power multi-loop process collector ring is used to convert the main and tail rotor circuits in the operating state to the ground static state, and then connected to the main and tail rotor heating power supply simulation load box, thereby creating an electronic control system and the aircraft's close to the actual working state.

[0072] Through the above-mentioned innovations, the verification problem of the rotor anti-icing and de-icing electronic control system before installation has been solved, and the following goals have been achieved: verifying the correctness of the system design and finished product matching; checking the correctness and coordination of the system interface relationship; checking the correctness and coordination of the system control logic design; checking the correctness of the system power supply method and the matching of power devices; assessing the reliability and stability of the system's working performance; providing a test basis for system improvement or finalization; and laying the foundation for ground simulation tests of the rotor anti-icing and de-icing electronic control systems of subsequent models. BRIEF DESCRIPTION OF THE DRAWINGS

[0073] Figure 1 Principle block diagram of the rotor anti-icing and de-icing electronic control system verification device;

[0074] Figure 2 Icing signal simulator structure diagram;

[0075] Figure 3 Schematic diagram of low-speed turntable;

[0076] Figure 4 Schematic diagram of high-speed turntable;

[0077] Figure 5 Overall principle diagram of the control system;

[0078] Figure 6 Schematic diagram of the simulated load connection of a single main propeller;

[0079] Figure 7 Tail rotor load connection diagram. DETAILED DESCRIPTION

[0080] The rotor anti-icing electronic control system includes rotor anti-icing control and power transmission functions. Due to the particularity of helicopters, it is necessary to install main and tail rotor collector rings and other components to transmit power from the static components of the whole aircraft to the main and tail rotor blades and other rotating components. Therefore, this project studies the ground verification technology of the rotor anti-icing electronic control system, focusing on the construction of the electronic control system test model, the input signal simulation of the detection subsystem and the simulation of the heating subsystem, as well as the monitoring technology of the system working parameters. The principle block diagram of the verification technology is as follows: Figure 1 shown.

[0081] (1) The rotor anti-icing and de-icing electronic control system verification technical environment includes the following equipment:

[0082] a) Icing signal simulator: used to simulate various parameters of the detection subsystem. The icing signal simulator is interconnected with the industrial computer, and parameter setting and display are realized through the computer interface. When the system is working, by setting the human-machine interface, the industrial computer controls the icing signal simulation module to output the frequency signal through the serial port to simulate the frequency information during icing; and adjusts the temperature sensors in the atmospheric temperature sensor simulation module and the tail rotor internal temperature sensor simulation module through the adjustment knobs on the panel. The industrial computer samples the voltage at both ends of the temperature sensor, performs calculations, and displays the calculation results on the human-machine interface; the input heating DC power supply and heating AC power supply are displayed through indicator lights. Monitoring signals such as fault signals, icing signals and status signals are input to the industrial computer through the signal processing module and displayed on the monitor. The structural block diagram is as follows Figure 2 shown.

[0083] b) Anti-icing operation test bench: including low-speed turntable, high-speed turntable, turntable electrical interface and turntable control system.

[0084] (1) Low-speed turntable design:

[0085] The mechanical body of the low-speed single-axis turntable is composed of a base, a table and a precision shaft system, and the structure is a "T-type" structure. The turntable structure is determined based on the load weight, shape and size, installation requirements, and the turntable rotation angle range, and considering the performance requirements and maintenance performance of the turntable system, such as Figure 3 The turntable should leave inlet and outlet ports for the main propeller collector ring assembly and the main propeller simulated load.

[0086] The turntable base area is ≤1.5m×1.5m. The central axis hole is used to pass the vertical pipe of the main propeller collector ring assembly.

[0087] The room where the two turntables are placed is 8m×9m. The high-speed and low-speed turntable frame bases are the same, weighing about 2.5 tons, and the center hole spacing is 3.5m.

[0088] When the turntable drives the simulated hub to rotate, the output voltage of the main propeller distributor or the main propeller collector ring is transferred to the high-power load through the high-power process collector ring to complete the simulation of the working state of the main propeller distributor and the main propeller collector ring. The main propeller distributor has 6 cables connected to the fixed load resistor. The platform base frame is fixed to the ground with M20 bolts and is the basic structure of the turntable. There are 16 bolts in total, arranged 4 horizontally and 4 vertically, with a bolt hole spacing of 300mm. The distributor to be tested is installed on the platform structure through a bracket and does not rotate during the test. The static end of the collector ring to be tested is connected to the power output shaft through a flange. The collector ring of the turntable is installed on the power output shaft and the static end is installed on the platform structure.

[0089] The main propeller distributor is installed on the upper part of the shaft through a flange. The rotor of the main propeller collector ring assembly rotates with the distributor. The lower end of the vertical pipe of the main propeller collector ring assembly is fixed to the platform body and is concentric with the shaft. The shaft table has a hole group for installing the fixture.

[0090] The turntable is set and controlled by the industrial computer to adjust and stabilize the motor speed. The turntable cabinet is connected to the high-dynamic servo motor, servo driver, speed sensor, electromagnetic brake, etc. through power cables and control cables. The cable length is not less than 15m.

[0091] The torque of the AC servo motor is transmitted to the spindle through the reducer, and an incremental photoelectric encoder is used as an angle measuring element.

[0092] The surface of the table is scraped to ensure the flatness of the mounting surface. The mounting surface has 4 circles, each with 8 evenly distributed M8 screw holes, which can meet the requirements of various forms of load installation. The outer circle of the table is engraved and can be used as a dial at the same time. The shaft system is supported by a pair of back-to-back angular contact ball bearings. The angular contact ball bearings have high rotation accuracy and good torsional and bending rigidity, which can ensure the rotation accuracy of the shaft system. At the same time, the ball bearings can expand and contract in the axial direction to prevent assembly stress or stress caused by the expansion of the shaft system after operation and heating. The shaft and bearing seat are made of bearing steel, matched with the bearings, and artificial aging and stability treatment are carried out.

[0093] (II) High-speed turntable design:

[0094] The mechanical body of the high-speed single-axis turntable is composed of a base, a table and a precision shaft system, and the structure is a "T-shaped" structure. The turntable structure is determined based on the load weight, shape and size, installation requirements, and the turntable rotation angle range, and considering the performance requirements and maintenance performance of the turntable system. Figure 4 .

[0095] The cable lead of the rotating tail rotor collector ring is connected to a fixed load resistor through a high-power process collector ring conversion device. The tail rotor collector ring has 5 cables.

[0096] The safety net is a stainless steel wire mesh with a height of 1.2m and a mesh size of 1 mesh / inch. The net has a bracket and the center of the net is 3.5m from the ground.

[0097] The high-speed turntable is changed from horizontal axis output to vertical axis output, and a protective net is used.

[0098] (III) Turntable electrical interface

[0099] The electrical interface between the turntable and the product is mainly the interface between the high-power process collector ring and the product. Among them, the interface between the main rotor distributor, main rotor simulated load and high-power process collector ring of the low-speed turntable is a square disk socket, and the interface between the tail rotor collector ring, tail rotor simulated load and high-power process collector ring of the high-speed turntable is a socket.

[0100] (IV) Turntable control system

[0101] It mainly includes drive motor, driver and encoder.

[0102] c) Anti-icing test console: used to control two AC servo motors, control the start and stop of two turntables, speed adjustment, and speed display; provide a platform for installing the finished test pieces of the anti-icing system and connecting cables; provide a power switch that can realize the signal of simulating the switching of APU and main power supply;

[0103] The computer detects and displays the working status of the anti-icing system; the indicator light simulates the fault signal and prompt signal indication of the alarm system; the communication function and data between the controller and the electromechanical management system are checked through the RS422 communication interface.

[0104] The control system in the test console is an important part of the entire equipment. Its main functions can be summarized as: implementing the system's control strategy, completing the system's technical performance and functions, and ensuring the system works normally, safely and reliably.

[0105] The control system of this system still adopts the distributed control system (DCS) mechanism, and its principle structure is as follows Figure 5 As shown, the upper and lower computers form a two-level control structure to realize the decentralized direct control and centralized comprehensive monitoring and management functions of the system. The control system consists of a comprehensive management level, a direct control level and a monitoring system unit.

[0106] d) Simulated load: used to simulate the power consumption of the main and tail rotor heating subsystems, and can indicate the heating working status of each zone.

[0107] (I) Main propeller simulated load

[0108] Since the main propeller simulation load needs to fully simulate the working state of the main propeller during deicing and heating, the composition and connection method of the simulation load are exactly the same as the setting of the main propeller deicing and heating element. Figure 6 .

[0109] The main propeller simulation load is composed of 6 groups of loads to simulate the heating elements on the 6 blades, and one more group of loads is reserved for extended performance. Each group of loads is divided into 5 groups to simulate the 5 heating zones of the blades. The 5 groups are composed of 3 independent loads to simulate the 3 metal heating elements with equal resistance on the blades. The 3 loads in each group are connected in a star connection, corresponding to ΦA, ΦB, and three phases of three-phase AC respectively. The ΦC phase of the 5 heating zones shares 1 wire. All loads are connected to the transfer terminals in the cabinet, specific line connections are made on the terminals, and then connected to the cabinet sockets, so the total number of resistors is 6*5*3=90.

[0110] The main propeller simulation load uses a single sliding rheostat with a resistance of 12Ω, a rated power of 5000W, and a resistance of 10.1Ω.

[0111] (II) Tail rotor load simulation

[0112] Since the tail rotor simulation load needs to fully simulate the working state of the tail rotor during de-icing and heating, the composition and connection method of the simulation load are exactly the same as the setting of the tail rotor de-icing heating element.

[0113] The heating pad resistors R1, R2 and R3 on each blade are simulated by three loads with the same resistance value. The five blades are simulated by a total of 15 loads with the same resistance value. After the five R1s are connected in series, they just form one side of the triangle connection of the tail rotor heating pad resistor. All loads are connected to the transfer terminal in the cabinet, and specific line connections are made on the terminal, and then connected to the cabinet socket. The connection diagram is as follows Figure 7 :

[0114] The tail rotor simulation load uses a single sliding rheostat with a resistance of 9Ω and a rated power of 3000W, and the resistance value is 6.2Ω.

[0115] (2) Test environment simulation and test methods:

[0116] Test environment simulation:

[0117] a) Simulate the detection subsystem equipment. According to the characteristics of the helicopter rotor anti-icing system, sort out the detection subsystem parameters required for the normal operation of the electronic control system, including: the icing signal output by the icing detector; the atmospheric environment temperature signal; the tail rotor internal temperature sensor signal.

[0118] b) Simulate the onboard environment of the electronic control system. According to the system installation characteristics, the main rotor collector ring, main rotor distributor and tail rotor collector ring are rotating parts. Therefore, in order to verify the working status of the electronic control system when the helicopter is rotating, a turntable is needed to simulate the rotation of the main and tail rotors of the helicopter. Among them, the low-speed operating table is used to simulate the rotation of the main rotor, and the high-speed operating table is used to simulate the rotation of the tail rotor.

[0119] c) Simulate the heating subsystem. Since the heating subsystem is installed in the main and tail rotor blades and is a moving part, considering the construction of the test environment, a high-power process collector ring is added to each of the main and tail rotor collector rings to achieve the dynamic to static conversion function of the main and tail rotor heating electrical signals. The heating subsystem uses a high-power resistive load to simulate its power.

[0120] Test method:

[0121] a) Function test when the collector ring is not in operation (for example, slight icing in automatic mode):

[0122] 1) Reliably connect the test cable to each finished test piece, signal simulator, ground power supply, etc. to confirm that the model is correct and the power supply is correct;

[0123] 2) Turn on the "self-check" switch on the rotor anti-icing control panel, and the indicator lights for monitoring the simulated load of the main rotor and the simulated load of the tail rotor should light up cyclically according to the control sequence. Finally, the "main rotor" and "tail rotor" indicators on the rotor anti-icing control panel light up, indicating that the system circuit and control logic are correct;

[0124] 3) Turn the anti-icing mode selection switch on the rotor anti-icing control panel to the "automatic" position;

[0125] 4) Set the atmospheric temperature sensor simulator temperature to "T1", specifically -15°C;

[0126] 5) Set the tail rotor internal temperature sensor simulator temperature to below "T2", specifically 60°C;

[0127] 6) The signal simulator is set to output slight icing (LWC = 0.2 g / m3) and the electromechanical information reception is started;

[0128] 7) Turn on the "anti-icing" switch on the rotor anti-icing control panel, and when the "icing" alarm is given, the anti-icing system will work and automatically connect the main and tail rotor simulated loads;

[0129] 8) The "Icing" warning light and the "Rotor Anti-Icing" warning light are on;

[0130] 9) The test system monitors and records the main and tail rotor heating operating voltage and current values ​​during a cycle;

[0131] 10) Simultaneously record the electromechanical information received on the signal simulator;

[0132] 11) Slowly adjust the temperature setting knob of the tail rotor on the test bench until the three-phase current output from the anti-icing distribution box to the tail rotor heating pad is 0, and record the upper temperature limit T1 at which the tail rotor stops heating;

[0133] 12) Slowly adjust the tail rotor internal temperature setting knob on the test bench until the three-phase current output from the anti-icing distribution box to the tail rotor heating pad is not 0, and record the lower limit value T2 of the temperature at which the tail rotor starts to heat at this time;

[0134] 13) Disconnect the anti-ice switch on the rotor anti-ice control panel.

[0135] Note: The parameter values ​​for the light icing state are to set the atmospheric temperature sensor simulator temperature to "-10°C"; set the tail rotor internal temperature sensor simulator temperature to below "60°C"; set the signal simulator to output light icing (LWC = 0.4g / m3), and the rest are the same as a) above;

[0136] The parameter values ​​for the moderate icing state are: setting the atmospheric temperature sensor simulator temperature to "0°C"; setting the tail rotor internal temperature sensor simulator temperature to below "60°C"; setting the signal simulator to light icing (LWC = 0.8g / m3) output, and the rest are consistent with a) above.

[0137] b) Functional test when the collector ring is not in operation (taking manual mode with slight icing as an example):

[0138] 1) Reliably connect the test cable to each finished test piece, signal simulator, ground power supply, etc. to confirm that the model is correct and the power supply is correct;

[0139] 2) Turn on the "self-check" switch on the rotor anti-icing control panel, and the indicator lights for monitoring the simulated load of the main rotor and the simulated load of the tail rotor should light up cyclically according to the control sequence. Finally, the "main rotor" and "tail rotor" indicators on the rotor anti-icing control panel light up, indicating that the system circuit and control logic are correct;

[0140] 3) Turn the anti-icing working mode selection switch on the rotor anti-icing control panel to the "manual" position;

[0141] 4) Set the atmospheric temperature sensor simulator temperature to "T3", specifically -15°C;

[0142] 5) Set the tail rotor internal temperature sensor simulator temperature to below "T4", specifically 60°C;

[0143] 6) The signal simulator is set to output slight icing (LWC = 0.2 g / m3) and the electromechanical information reception is started;

[0144] 7) Turn on the "anti-icing" switch on the rotor anti-icing control panel, and when the "icing" alarm is given, the anti-icing system will work and automatically connect the main and tail rotor simulated loads;

[0145] 8) The "Icing" warning light and the "Rotor Anti-Icing" warning light are on;

[0146] 9) The test system monitors and records the main and tail rotor heating operating voltage and current values ​​during a cycle;

[0147] 10) Simultaneously record the electromechanical information received on the signal simulator;

[0148] 11) Slowly adjust the temperature setting knob of the tail rotor on the test bench until the three-phase current output from the anti-icing distribution box to the tail rotor heating pad is 0, and record the upper temperature limit T1 at which the tail rotor stops heating;

[0149] 12) Slowly adjust the tail rotor internal temperature setting knob on the test bench until the three-phase current output from the anti-icing distribution box to the tail rotor heating pad is not 0, and record the lower limit value T2 of the temperature at which the tail rotor starts to heat at this time;

[0150] 13) Disconnect the anti-ice switch on the rotor anti-ice control panel.

[0151] Note: The parameter values ​​for the light icing state are to set the atmospheric temperature sensor simulator temperature to "-10°C"; set the tail rotor internal temperature sensor simulator temperature to below "60°C"; set the signal simulator to output light icing (LWC = 0.4g / m3), and the rest are the same as above b);

[0152] The parameter values ​​for the moderate icing state are: setting the atmospheric temperature sensor simulator temperature to "0°C"; setting the tail rotor internal temperature sensor simulator temperature to below "60°C"; setting the signal simulator to light icing (LWC = 0.8g / m3) output, and the rest are consistent with the above b).

[0153] c) Anti-icing and de-icing system function test at rated speed:

[0154] Connect the anti-icing operation test bench, so that the main and tail rotor operation test benches reach the test speed requirements (main rotor rated speed 212r / min, tail rotor rated speed 1013r / min). Connect the rotor anti-icing system, and perform the above a) operation again when the system is in normal working condition.

[0155] d) Anti-icing system fault injection test:

[0156] (I) Power supply system fault injection test

[0157] Under the simulated single-fault condition, the power supply conversion function test between the AC power system generator and the APU is carried out to measure the conversion time of the power conversion contactor.

[0158] Continue with the following operations while the rotor anti-icing system is operating normally:

[0159] 1) The test system records the voltage at the simulated load end of the tail rotor;

[0160] 2) Switch the power switch on the anti-icing test console to the APU position, and the test system monitors and records the tail rotor heating operating voltage and current values;

[0161] 3) The voltage disconnection time of the tail rotor simulated load end is measured as the power supply conversion time t.

[0162] (II) Anti-icing system fault injection test

[0163] When the rotor anti-icing system is in normal working condition, check the light warning signal output by the system to the warning system, check the communication information with the electromechanical management system, and continue the following operations:

[0164] 1) Disconnect all main propeller simulated loads. At this time, the alarm system outputs the "main propeller de-icing failure" warning light. Check the communication data with the electromechanical management system, which should be "main propeller de-icing failure".

[0165] 2) Restore the system to its initial state, start the rotor anti-icing system, and the system works normally

[0166] 3) Disconnect the simulated load of one set of main propellers. At this time, the alarm system outputs the main caution light of "main propeller de-icing failure". Check the communication data with the electromechanical management system, which should be "main propeller de-icing failure".

[0167] 4) Restore the system to its initial state, start the rotor anti-icing system, and the system works normally

[0168] 5) Disconnect the simulated load on the tail rotor. At this time, the alarm system outputs the "tail rotor anti-icing failure" warning light. Check the communication data with the electromechanical management system, which should be "tail rotor anti-icing failure".

[0169] 6) Restore the system to its initial state, start the rotor anti-icing system, and the system works normally

[0170] 7) Set the temperature sensor I switch on the test console to the "off position". The alarm system will then output the "tail rotor temperature sensor fault" main caution light. Check the communication data with the electromechanical management system, which should indicate "tail rotor temperature sensor fault".

[0171] 8) Restore the system to its initial state, start the rotor anti-icing system, and the system works normally

[0172] 9) Set the temperature sensor I switch and the temperature sensor II switch on the test console to the "off" position. The alarm system will then output the "tail rotor temperature sensor failure" main caution light. Check the communication data with the electromechanical management system, which should indicate "tail rotor temperature sensor failure".

[0173] 10) Restore the system to its initial state, start the rotor anti-icing system, and the system works normally

[0174] 11) Set the switch of the ice detector simulator on the test bench to the "off" position. At this time, the alarm system outputs the "ice detection failure" main warning light. Check the communication data with the electromechanical management system, which should be "ice detection failure".

[0175] 12) Restore the system to its initial state, start the rotor anti-icing system, and the system works normally

[0176] 13) Set the atmospheric temperature sensor simulator switch on the test bench to the "off" position. At this time, the alarm system outputs the "main rotor de-icing failure" and "tail rotor anti-icing failure" warning lights. Check the communication data with the electromechanical management system, which should be "atmospheric temperature sensor failure".

[0177] (3) The key technologies of this patent are mainly the following:

[0178] a) Key technology 1: Simulation technology of icing meteorological environment parameters.

[0179] Solution: Power electronics technology, computer technology, intelligent digital signal generator, etc. are used to simulate the icing signal, atmospheric temperature signal and tail rotor internal temperature feedback signal, and establish the input conditions for the rotor anti-icing system.

[0180] b) Key Technology 2: The ground simulation test of the electric control system requires the main and tail rotor collector rings and the main rotor distributor to be loaded and tested in the operating state, where the load of the main rotor distributor needs to simulate the power consumption of 90 partitions of the 6 main rotor heating components. Therefore, how to truly simulate the working state of the finished product on the aircraft and realize the loading of the simulated load of the main rotor heating component in the operating state is the key technology of this test method.

[0181] Solution: Servo motors, distributed control system (DCS) technology and computer technology are used to drive and control the operation of the collector ring assembly. The operating part is directly driven by a hollow motor, which simulates the actual installation situation on the aircraft to the greatest extent. The dynamic to static conversion is achieved through high-power multi-channel process collector rings, which solves the problem of loading simulated loads under the actual operating conditions of the main and tail rotor heating components, and realizes the function of finished product verification of the rotor anti-icing and de-icing electronic control system.

Claims

1. A ground verification device for a helicopter rotor anti-icing and de-icing electronic control system, characterized in that: include: Icing signal simulator, high-speed turntable, low-speed turntable, control console, main rotor simulation load and tail rotor simulation load; The icing signal simulator is connected to the anti-icing and de-icing electronic control system controller to provide an icing simulation signal; The lower turntable is used to drive the simulated main rotor hub to rotate, and the high-speed turntable is used to drive the simulated tail rotor hub to rotate; The control console is used to control the high-speed turntable and the low-speed turntable; The simulated main rotor and tail rotor are provided with collector rings; The main rotor simulated load and the tail rotor simulated load are connected to the collector ring and are used to simulate the electrical power consumption of the main rotor and tail rotor heating subsystems respectively.

2. The device according to claim 1, characterized in that: The main propeller simulation load includes N groups of load combinations for simulating the heating elements on N blades. Each group of loads is divided into M groups to simulate M heating zones. Each heating zone includes three independent loads to simulate three metal heating elements with equal resistance. The three independent loads are connected in a star shape and correspond to the three-phase electricity of the alternating current.

3. The device according to claim 2, characterized in that: The load and rated power of the sliding rheostat simulated by the main general are greater than those of the sliding rheostat simulated by the tail rotor.

4. The device according to claim 3, characterized in that: The tail rotor simulation load includes P groups of load combinations, and each group of loads includes three heating resistors with the same resistance.

5. The device according to claim 4, characterized in that: The icing signal simulator is used to simulate the icing signal output by the icing detector, the atmospheric environment temperature signal, and the tail rotor internal temperature signal.

6. A ground verification method for a helicopter rotor anti-icing and de-icing electronic control system, implemented based on any of the above-mentioned devices, characterized in that: Includes the following: Automatic mode light icing test with collector ring not in operation; Manual mode slight icing test with collector ring not in operation; Anti-icing and de-icing system function test at constant speed; Fault injection testing.

7. The method according to claim 6, characterized in that: The procedure for the automatic mode light icing test with the collector ring not in operation is as follows: A1) Reliably connect the test cables to each finished test piece, signal simulator, and ground power supply to confirm that the model is correct and the power supply is correct; A2) Turn on the "self-check" switch on the rotor anti-icing control panel, and the indicator lights for monitoring the simulated load of the main rotor and the simulated load of the tail rotor should light up cyclically according to the control sequence. Finally, the "main rotor" and "tail rotor" indicators on the rotor anti-icing control panel light up, indicating that the system circuit and control logic are correct; A3) Turn the anti-icing mode selector switch on the rotor anti-icing control panel to the "automatic" position; A4) Set the atmospheric environment temperature signal to "T1"; A5) Set the tail rotor internal temperature signal to below "T2"; A6) The signal simulator is set to output slight icing; A7) Turn on the "anti-icing" switch on the rotor anti-icing control panel. When the "icing" alarm is given, the anti-icing system will work and the main and tail rotor simulated loads will be automatically turned on. A8) The "Icing" warning light and the "Rotor Anti-Icing" warning light are on; A9) The test system monitors and records the main and tail rotor heating operating voltage and current values ​​during a cycle; A10) simultaneously recording the information received on the icing signal simulator; A11) Slowly adjust the temperature setting knob of the tail rotor on the test bench until the three-phase current output from the anti-icing distribution box to the tail rotor heating pad is 0, and record the upper temperature limit T11 of the tail rotor stopping heating; A12) Slowly adjust the tail rotor internal temperature setting knob on the test bench until the three-phase current output from the anti-icing distribution box to the tail rotor heating pad is not 0, and record the lower limit value T12 of the temperature at which the tail rotor starts heating at this time; A13) Disconnect the anti-ice switch on the rotor anti-ice control panel.

8. The method according to claim 6, characterized in that: The manual mode light icing test procedure with the collector ring not in operation is as follows: B1) Reliably connect the test cables to each finished test piece, signal simulator, and ground power supply to confirm that the model is correct and the power supply is correct; B2) Turn on the "self-check" switch on the rotor anti-icing control panel, and the indicator lights for monitoring the simulated load of the main rotor and the simulated load of the tail rotor should light up cyclically according to the control sequence. Finally, the "main rotor" and "tail rotor" indicators on the rotor anti-icing control panel light up, indicating that the system circuit and control logic are correct; B3) Turn the anti-icing mode selector switch on the rotor anti-icing control panel to the "manual" position; B4) Set the atmospheric environment temperature signal to "T3"; B5) Set the tail rotor internal temperature signal to be lower than "T4"; B6) The signal simulator is set to output slight icing; B7) Turn on the "anti-icing" switch on the rotor anti-icing control panel, and when the "icing" alarm is given, the anti-icing system will work and the main and tail rotor simulated loads will be automatically turned on; B8) The "Icing" warning light and the "Rotor Anti-Icing" warning light are on; B9) The test system monitors and records the main and tail rotor heating operating voltage and current values ​​during a cycle; B10) simultaneously recording the electromechanical information received on the signal simulator; B11) Slowly adjust the temperature setting knob of the tail rotor on the test bench until the three-phase current output from the anti-icing distribution box to the tail rotor heating pad is 0, and record the upper temperature limit T21 when the tail rotor stops heating; B12) Slowly adjust the tail rotor internal temperature setting knob on the test bench until the three-phase current output from the anti-icing distribution box to the tail rotor heating pad is not 0, and record the lower limit value T22 of the temperature at which the tail rotor starts to heat. B13) Disconnect the anti-ice switch on the rotor anti-ice control panel.

9. The method according to claim 6, characterized in that: The function test process of the anti-icing and de-icing system at a constant speed is as follows: Control the low-speed turntable and the high-speed turntable to reach the test speed, the rated speed of the main rotor is 212r / min, the rated speed of the tail rotor is 1013r / min, turn on the rotor anti-icing system, and repeat steps A1-A13.

10. The method according to claim 6, characterized in that: The fault injection test process is as follows: C1) Disconnect all simulated loads on the main propeller. At this time, the alarm system outputs the "main propeller de-icing failure" warning light. Check the communication data with the electromechanical management system. It should be "main propeller de-icing failure"; C2) Restore the system to its initial state, start the rotor anti-icing system, and the system works normally; C3) Disconnect the simulated load of one set of main propellers. At this time, the alarm system outputs the main caution light of "main propeller de-icing failure". Check the communication data with the electromechanical management system, which should be "main propeller de-icing failure"; C4) Restore the system to its initial state, start the rotor anti-icing system, and the system works normally; C5) Disconnect the simulated load of the tail rotor. At this time, the warning system outputs the "tail rotor anti-icing failure" warning light. Check the communication data with the electromechanical management system. It should be "tail rotor anti-icing failure"; C6) Restore the system to its initial state, start the rotor anti-icing system, and the system works normally; C7) Set the temperature sensor I switch on the test console to the "off position". At this time, the alarm system outputs the "tail rotor temperature sensor failure" main warning light. Check the communication data with the electromechanical management system. It should be "tail rotor temperature sensor failure"; C8) Restore the system to its initial state, start the rotor anti-icing system, and the system works normally; C9) Set the temperature sensor I switch and the temperature sensor II switch on the test console to the "off" position. At this time, the alarm system outputs the "tail rotor temperature sensor failure" main warning light. Check the communication data with the electromechanical management system. It should be "tail rotor temperature sensor failure"; C10) Restore the system to its initial state, start the rotor anti-icing system, and the system works normally; C11) Set the switch of the ice detector simulator on the test bench to the "off" position. At this time, the warning system outputs the "ice detection failure" main warning light. Check the communication data with the electromechanical management system. It should be "ice detection failure"; C12) Restore the system to its initial state, start the rotor anti-icing system, and the system works normally; C13) Set the atmospheric temperature sensor simulator switch on the test bench to the "off" position. At this time, the alarm system outputs the "main propeller de-icing failure" and "tail propeller anti-icing failure" warning lights. Check the communication data with the electromechanical management system, which should be "atmospheric temperature sensor failure".

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