A manned rotor control system for ground-based combined testing of civil helicopters

Abstract

The application provides a manned rotor control system for civil helicopter ground joint test, which comprises a flight control system displacement sensor 1, an analog signal acquisition device 2, a data acquisition and processing computer 3, a control display computer 4, a control display computer support 5, a test cable 6 and a data cable 7, wherein the flight control system displacement sensor 1 comprises at least four displacement sensors, each displacement sensor is connected with the input end of the analog signal acquisition device 2 through the test cable 6, the output end of the analog signal acquisition device 2 is connected with the input end of the data acquisition and processing computer 3 through the data cable 7, and the output end of the data acquisition and processing computer 3 is connected with the control display computer 4 through the data cable 7; the control display computer 4 is arranged in the cockpit instrument panel 5.3 of the helicopter; the flight control system displacement sensor 1 is used for measuring the input quantity of the control system booster on the helicopter.

Description

Technical Field

[0001] This invention relates to helicopter ground joint testing technology, specifically to a manned rotor control system for civil helicopter ground joint testing. Background Technology

[0002] The purpose of the joint ground test for civil helicopters is to assess the helicopter's rotor, transmission, and power systems' ability to operate continuously and normally within the limits specified by the applicant, as well as the matching and coordination of the various systems, ensuring that there are no performance degradations due to excessive wear or mechanical loads, and that related structural components do not suffer harmful permanent deformation or damage. This verifies compliance with airworthiness provisions such as CCAR-29.307, 923, and 927. The test items mainly include cyclic durability tests. During the test, the rotor system (including the main rotor and tail rotor) needs to be fixed in the specified control position for a period ranging from 10 seconds to 30 minutes, and each test requires switching between different control positions.

[0003] The AC313A helicopter ground joint test is the first helicopter ground joint test in China to achieve test control using an onboard manned pilot. Test control includes engine start control and rotor control. Engine start control is consistent with actual piloting, while rotor control differs significantly from the pilot's operation during actual flight. In actual flight, the pilot controls the helicopter's flight attitude and heading by operating the collective pitch stick, control stick, and pedals. In the ground joint test, after operating the collective pitch stick, control stick, and pedals, the test pilot needs to maintain or switch the test control position based on the numerical feedback of four parameters: rotor collective pitch, rotor longitudinal cyclic pitch, rotor lateral cyclic pitch, and tail rotor pitch. Since the helicopter does not display these four control position parameters, the AC313A helicopter ground joint test requires the design of a system to assist the pilot in rotor control. Summary of the Invention

[0004] The technical problem solved by this invention is to provide a manned rotor control system for ground joint testing of civil helicopters, based on the principle of helicopter control parameter measurement, to meet the test control requirements of AC313A helicopter ground joint testing. This system can display control position parameters and assist the pilot in conducting rotor control tests.

[0005] Technical solution: A manned rotor control system for ground-based joint testing of a civil helicopter, the system comprising a flight control system displacement sensor 1, an analog signal acquisition device 2, a data acquisition and processing computer 3, a control display computer 4, a control display computer bracket 5, test cables 6, and data cables 7, wherein:

[0006] The flight control system displacement sensor 1 includes at least four displacement sensors. Each displacement sensor is connected to the input terminal of the analog signal acquisition device 2 via a test cable 6. The output terminal of the analog signal acquisition device 2 is connected to the input terminal of the data acquisition and processing computer 3 via a data cable 7. The output terminal of the data acquisition and processing computer 3 is connected to the control display computer 4 via a data cable 7. The control display computer 4 is located inside the helicopter's cockpit instrument panel 5.3. The flight control system displacement sensor 1 is used on the helicopter to measure the input of the control system booster in order to measure the motion stroke of the booster. The measurement results are recorded and saved by the flight parameter acquisition recorder.

[0007] Specifically, the flight control system displacement sensor 1 includes a forward displacement sensor, a left displacement sensor, a right displacement sensor, and a tail displacement sensor.

[0008] Specifically, the forward displacement sensor is located at the front control booster of the helicopter;

[0009] The left displacement sensor is located at the left control booster of the helicopter;

[0010] The right displacement sensor is located at the right control booster of the helicopter;

[0011] The tail displacement sensor is located at the helicopter heading control booster.

[0012] Specifically, the display interface on the control display computer 4 includes a rotor collective pitch bar chart 8.1, an X-Y coordinate chart, and a tail rotor pitch bar chart 8.10.

[0013] Specifically, the rotor collective pitch bar chart 8.1 has a collective pitch test target value line 8.2 and a current collective pitch value cursor 8.3. If the collective pitch test target value line 8.2 and the current collective pitch value cursor 8.3 coincide, a collective pitch value timing window 8.4 will appear next to the current collective pitch value cursor 8.3 to time the time the rotor collective pitch stays at the test target value. If the current collective pitch value cursor 8.3 leaves the collective pitch test target value line 8.2 for more than a preset time, the timing will stop and the collective pitch value timing window 8.4 will disappear.

[0014] Specifically, the X-coordinate of the X-Y coordinate graph is the rotor's lateral periodic pitch scale line 8.6, and the Y-coordinate is the rotor's longitudinal periodic pitch scale line 8.5. The X-Y coordinate graph is set with a periodic pitch test target value circle 8.8 and a periodic pitch value vernier 8.7. The X value of the periodic pitch value vernier 8.7 is the lateral periodic pitch, and the Y value is the longitudinal periodic pitch. When the periodic pitch value vernier 8.7 is within the periodic pitch test target value circle 8.8, a periodic pitch value timing window 8.9 will appear next to the periodic pitch value vernier 8.7 to time the time when the rotor's longitudinal / lateral periodic pitch stays at the test target value. If the rotor's longitudinal / lateral periodic pitch deviates from the test target value for more than a preset time, the timing will stop and the periodic pitch value timing window 8.9 will disappear.

[0015] Specifically, the tail rotor pitch bar chart 8.10 has a tail rotor pitch test target value line 8.11 and a current tail rotor pitch value cursor 8.12. When the tail rotor pitch test target value line 8.11 and the current tail rotor pitch value cursor 8.12 coincide, a tail rotor pitch value timing window 8.13 will appear next to the current tail rotor pitch value cursor 8.12 to time the time the tail rotor pitch stays at the test target value. If the tail rotor distance exceeds the test target value for more than a preset time, the timing will stop and the tail rotor pitch value timing window 8.13 will disappear.

[0016] Specifically, the control display computer 4 is mounted on the helicopter's cockpit instrument panel 5.3 via a control display computer bracket 5. Holes are added to the cockpit instrument panel 5.3, and the control display computer bracket 5 is fixed using standard bolts 5.2 and standard nuts 5.1.

[0017] Technical Effects: This invention presents a manned rotor control technology for civil helicopter ground joint testing. It can provide real-time, accurate, and effective feedback of four control position parameters not available on the aircraft itself—rotor collective pitch, rotor longitudinal cyclic pitch, rotor lateral cyclic pitch, and tail rotor pitch—to the pilot on the test aircraft, ensuring the successful implementation of manned helicopter ground joint testing. This invention is the first to achieve manned rotor control in helicopter ground joint testing, providing a new technical means for civil helicopter ground joint testing in my country, improving the country's comprehensive helicopter testing capabilities, and holding significant importance for the advancement of my country's aviation technology. Using this manned rotor control technology, the control of helicopter ground joint testing is safe, reliable, and effective, and can be used to verify compliance with airworthiness provisions such as CCAR-29.307, 923, and 927. Attached Figure Description

[0018] Figure 1 A schematic diagram of a manned rotor control system for a ground joint test of a civil helicopter provided in this application;

[0019] Figure 2A schematic diagram of a control display computer installed on the dashboard in the cockpit, as provided in this application;

[0020] Figure 3 This application provides a design diagram of a software interface for manipulating and displaying a computer;

[0021] The components are as follows: 1 - Flight control system displacement sensor; 2 - Analog signal acquisition equipment; 3 - Data acquisition and processing computer; 4 - Control display computer; 5 - Control display computer bracket; 6 - Test cable; 7 - Data cable; 5.1 - Standard part nut; 5.2 - Standard part bolt; 5.3 - Cockpit instrument panel; 8.1 - Rotor collective pitch bar chart; 8.2 - Collective pitch test target value line; 8.3 - Current collective pitch value vernier; 8.4 - Collective pitch value timing window; 8.5 - Rotor longitudinal periodic pitch scale line; 8.6 - Rotor lateral periodic pitch scale line; 8.7 - Periodic pitch value vernier; 8.8 - Periodic pitch test target value circle; 8.9 - Periodic pitch value timing window; 8.10 - Tail rotor pitch bar chart; 8.11 - Tail rotor pitch test target value line; 8.12 - Current tail rotor pitch value vernier; 8.13 - Tail rotor pitch value timing window. Detailed Implementation

[0022] This invention utilizes displacement sensors in the onboard flight control system to provide a manned rotor control technology for ground joint testing of civil helicopters, enabling pilots to control the rotor according to the requirements of ground joint testing. The rotor control technology is simple and effective to operate, solving the problem of achieving rotor control by a manned pilot on the AC313A helicopter ground joint test aircraft.

[0023] The AC313A helicopter ground joint test is the first helicopter ground joint test in China to achieve test control using an onboard manned pilot. Currently, my country lacks similar technology. No relevant publicly available foreign literature was found.

[0024] Helicopter control parameter measurement principle:

[0025] Displacement sensors are installed on the helicopter at the front booster, left booster, right booster, and tail booster (also known as the heading booster) to measure the displacement of the booster piston rods. Based on the measurement results and the mechanical transmission ratio of the main rotor blade and tail rotor blade pitch, the superposition matrix of the control system can be calculated. Furthermore, the displacement sensor measurements can be converted into actual rotor collective pitch, rotor longitudinal cyclic pitch, rotor lateral cyclic pitch, and tail rotor pitch.

[0026] like Figure 1As shown, this application provides a manned rotor control system for a civil helicopter ground joint test, including a flight control system displacement sensor 1, an analog signal acquisition device 2, a data acquisition and processing computer 3, a control display computer 4, a control display computer bracket 5, test cables 6, and data cables 7, wherein:

[0027] The flight control system displacement sensor 1 includes at least four displacement sensors. Each displacement sensor is connected to the input terminal of the analog signal acquisition device 2 via a test cable 6. The output terminal of the analog signal acquisition device 2 is connected to the input terminal of the data acquisition and processing computer 3 via a data cable 7. The output terminal of the data acquisition and processing computer 3 is connected to the control display computer 4 via a data cable 7. The control display computer 4 is located inside the helicopter's cockpit instrument panel 5.3. The flight control system displacement sensor 1 is used on the helicopter to measure the input of the control system booster in order to measure the motion stroke of the booster. The measurement results are recorded and saved by the flight parameter acquisition recorder.

[0028] Specifically, the flight control system displacement sensor 1 includes a forward displacement sensor, a left displacement sensor, a right displacement sensor, and a tail displacement sensor.

[0029] The types of displacement sensors include angular displacement sensors and linear displacement sensors. This application does not specifically limit the types of displacement sensors.

[0030] More specifically, the forward displacement sensor is located at the forward control booster of the helicopter, the left displacement sensor is located at the left control booster of the helicopter, the right displacement sensor is located at the right control booster of the helicopter, and the tail displacement sensor is located at the heading control booster of the helicopter.

[0031] Specifically, the computer 4 that controls the display includes tablet computers, etc.

[0032] Specifically, in the joint ground test of the helicopter, the signals from the four displacement sensors 1 of the flight control system are input to the analog signal acquisition device 2 through the test cable 6. The analog signal acquisition device 2 collects voltage signals and communicates with the data acquisition and processing computer 3 through the data cable 7. The data acquisition and processing computer 3 converts the collected voltage signals into control position data according to the control angle measurement principle, and communicates with the control display computer 4 installed in the cockpit through the data cable 7. The processed control position data is displayed on the control display computer 4, providing real-time feedback for the rotor control operation of the test aircraft pilot.

[0033] In practical applications, helicopter ground joint tests are used for AC313A helicopter ground joint tests, and this application embodiment does not limit this.

[0034] The tests showed that the technical solution effectively enabled manned rotor control on the AC313A helicopter ground joint test aircraft.

[0035] Specifically, such as Figure 2 As shown, the control display computer 4 is mounted on the cockpit instrument panel 5.3 of the helicopter via the control display computer bracket 5. Holes are added to the cockpit instrument panel 5.3 and the control display computer bracket 5 is fixed using standard bolts 5.2 and standard nuts 5.1.

[0036] It should be noted that there is an uninstalled screen on the dashboard 5.3 of the ground-based test vehicle's cockpit. This screen can be used to display the control display computer 4 for the operator to observe during the test. The control display computer 4 is secured behind the dashboard 5.3 using the control display computer bracket 5.

[0037] Specifically, such as Figure 3 As shown, the display interface on the control display computer 4 includes a rotor collective pitch bar chart 8.1, an X-Y coordinate graph, and a tail rotor pitch bar chart 8.10, wherein:

[0038] Preferably, the rotor collective pitch histogram 8.1 has a collective pitch test target value line 8.2 and a current collective pitch value cursor 8.3; if the collective pitch test target value line 8.2 and the current collective pitch value cursor 8.3 coincide, a collective pitch value timing window 8.4 will appear next to the current collective pitch value cursor 8.3 to time the time the rotor collective pitch stays at the test target value; if the current collective pitch value cursor 8.3 leaves the collective pitch test target value line 8.2 for more than a preset time, the timing will stop and the collective pitch value timing window 8.4 will disappear.

[0039] Preferably, the X-coordinate of the X-Y coordinate graph is the rotor's lateral periodic pitch scale line 8.6, and the Y-coordinate is the rotor's longitudinal periodic pitch scale line 8.5. The X-Y coordinate graph is set with a periodic pitch test target value circle 8.8 and a periodic pitch value vernier 8.7. The X value of the periodic pitch value vernier 8.7 is the lateral periodic pitch, and the Y value is the longitudinal periodic pitch. When the periodic pitch value vernier 8.7 is within the periodic pitch test target value circle 8.8, a periodic pitch value timing window 8.9 will appear next to the periodic pitch value vernier 8.7 to time the time when the rotor's longitudinal / lateral periodic pitch stays at the test target value. If the rotor's longitudinal / lateral periodic pitch deviates from the test target value for more than a preset time, the timing will stop and the periodic pitch value timing window 8.9 will disappear.

[0040] Among them, the target value circle 8.8 of the periodic pitch test is the acceptable range of the preset horizontal / vertical periodic pitch values ​​for a certain ground joint test state. The X and Y values ​​of the center coordinates of the circle are the preset values ​​of the horizontal / vertical periodic pitch of the test, and the radius of the circle is the maximum acceptable deviation value.

[0041] Preferably, the tail rotor pitch bar chart 8.10 is provided with a tail rotor pitch test target value line 8.11 and a current tail rotor pitch value vernier 8.12. When the tail rotor pitch test target value line 8.11 and the current tail rotor pitch value vernier 8.12 coincide, a tail rotor pitch value timing window 8.13 will appear next to the current tail rotor pitch value vernier 8.12 to time the time the tail rotor pitch stays at the test target value. If the tail rotor distance exceeds the test target value for more than a preset time, the timing will stop and the tail rotor pitch value timing window 8.13 will be hidden.

[0042] In summary, the manned rotor control technology for ground joint testing of civil helicopters designed in this invention can, in real time, accurately, and effectively, feed back four control position parameters not available on the aircraft—rotor collective pitch, rotor longitudinal cyclic pitch, rotor lateral cyclic pitch, and tail rotor pitch—to the pilot on the test aircraft, ensuring the implementation of ground joint testing of helicopters in manned mode. This invention is the first to realize manned rotor control for helicopter ground joint testing, providing a new technical means for ground joint testing of civil helicopters in my country, improving the comprehensive testing level of helicopters in my country, and having significant implications for the advancement of my country's aviation technology. Using the manned rotor control technology of this invention, the control of helicopter ground joint testing is safe, reliable, and effective, and can be used to verify compliance with airworthiness provisions such as CCAR-29.307, 923, and 927.

Claims

1. A manned rotor control system for ground-based joint testing of a civilian helicopter, characterized in that, The system includes a flight control system displacement sensor (1), an analog signal acquisition device (2), a data acquisition and processing computer (3), a control display computer (4), a control display computer bracket (5), test cables (6), and data cables (7), wherein: The flight control system displacement sensor (1) includes at least four displacement sensors. Each displacement sensor is connected to the input end of the analog signal acquisition device (2) via a test cable (6). The output end of the analog signal acquisition device (2) is connected to the input end of the data acquisition and processing computer (3) via a data cable (7). The output end of the data acquisition and processing computer (3) is connected to the control display computer (4) via a data cable (7). The control display computer (4) is located in the cockpit instrument panel (5.3) of the helicopter. The flight control system displacement sensor (1) is used on the helicopter to measure the input of the control system booster in order to measure the motion stroke of the booster. The measurement results are recorded and saved by the flight parameter acquisition recorder. The flight control system displacement sensors (1) include a forward displacement sensor, a left displacement sensor, a right displacement sensor and a tail displacement sensor; the forward displacement sensor is located at the forward control booster of the helicopter; the left displacement sensor is located at the left control booster of the helicopter; the right displacement sensor is located at the right control booster of the helicopter; the tail displacement sensor is located at the heading control booster of the helicopter; the display interface on the control display computer (4) includes a rotor collective pitch bar chart (8.1), an XY coordinate chart and a tail rotor pitch bar chart (8.10).

2. The system according to claim 1, characterized in that, The rotor collective pitch bar chart (8.1) has a collective pitch test target value line (8.2) and a current collective pitch value cursor (8.3). If the collective pitch test target value line (8.2) and the current collective pitch value cursor (8.3) coincide, a collective pitch value timing window (8.4) will appear next to the current collective pitch value cursor (8.3) to time the time the rotor collective pitch stays at the test target value. If the current collective pitch value cursor (8.3) leaves the collective pitch test target value line (8.2) for more than a preset time, the timing will stop and the collective pitch value timing window (8.4) will disappear.

3. The system according to claim 1, characterized in that, The X-coordinate of the XY coordinate graph is the rotor's lateral periodic pitch scale line (8.6), and the Y-coordinate is the rotor's longitudinal periodic pitch scale line (8.5). The XY coordinate graph is set with a periodic pitch test target value circle (8.8) and a periodic pitch value cursor (8.7). The X value of the periodic pitch value cursor (8.7) is the lateral periodic pitch, and the Y value is the longitudinal periodic pitch. When the periodic pitch value cursor (8.7) is within the periodic pitch test target value circle (8.8), a periodic pitch value timing window (8.9) will appear next to the periodic pitch value cursor (8.7) to time the time when the rotor's longitudinal / lateral periodic pitch stays at the test target value. If the rotor's longitudinal / lateral periodic pitch is more than the test target value by a preset time, the timing will stop and the periodic pitch value timing window (8.9) will be hidden.

4. The system according to claim 1, characterized in that, The tail rotor pitch bar chart (8.10) is set with a tail rotor pitch test target value line (8.11) and a current tail rotor pitch value cursor (8.12). When the tail rotor pitch test target value line (8.11) and the current tail rotor pitch value cursor (8.12) coincide, a tail rotor pitch value timing window (8.13) will appear next to the current tail rotor pitch value cursor (8.12) to time the time the tail rotor pitch stays at the test target value. If the tail rotor distance exceeds the test target value for more than a preset time, the timing will stop and the tail rotor pitch value timing window (8.13) will be hidden.

5. The system according to claim 1, characterized in that, The control display computer (4) is mounted on the cockpit instrument panel (5.3) of the helicopter via the control display computer bracket (5). Holes are added to the cockpit instrument panel (5.3) and the control display computer bracket (5) is fixed with standard bolts (5.2) and standard nuts (5.1).

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