Ground integrated multi-system linkage control test method

Abstract

The invention belongs to the field of aviation flight control hydraulic system tests, and particularly relates to a test method for ground integrated multi-system linkage control, which utilizes existing test equipment resources to identify associated signals and build an equipment framework for realizing test functions. A test management system and a signal simulation system are additionally arranged between a mechanical pump driving device and a main flight control tester, and a network of a test site is utilized to realize transmission of a control signal of the mechanical pump driving device to the test management system through the Ethernet and then transmission of the control signal to the signal simulation system through a reflection memory network; control signal conversion is realized in the signal simulation system, and an existing equipment simulation platform and a software environment are utilized to realize a function module for controlling the action of a control surface by parameters on a machine.

Description

Technical Field

[0001] The present invention belongs to the field of aviation flight control hydraulic system testing, and relates to a testing method for boundary tests in an iron bird integrated test bench for a certain type of aircraft, and to a testing method for ground integrated multi-system linkage control. Background Art

[0002] Aircraft system boundary testing is a crucial test to verify whether the aircraft system design meets flight envelope requirements. These tests are often conducted by simulating extreme conditions. During the AG600 iron bird tests, numerous boundary tests of the hydraulic system and flight control system were conducted. These tests were previously performed using various system testers and a test management system.

[0003] Conventional boundary tests involve little cross-linking control of onboard systems; the equipment involved in the test is fixed; and the signal transmission link is simple, mostly level 2 transmission, from signal setting to system actuation.

[0004] The RAT function test during the AG600's airworthiness verification test (iron bird test) verifies whether the hydraulic energy (emergency energy) can meet the pressure and flow requirements of the flight control system during engine failure (during a shutdown) when the pilot makes extensive control surface movements to maintain flight attitude. This test requires the aircraft's three-axis control surfaces to synchronize and move according to preset commands as the engine speed decreases from the normal speed (2058 rpm) to 1600 rpm. The performance indicators of the aircraft's hydraulic system are tested during this process.

[0005] To realize this test function, the engine speed simulated by the mechanical pump drive device needs to be used as the parameter input of the main flight control system tester to drive the three-axis control surface output movement. Since the external signal interface of the main flight control system tester for controlling the three-axis movement of the aircraft is not open to the outside world, the engine speed cannot be directly obtained through the test network for control.

[0006] If manual coordination is used, the operator of the mechanical pump drive (outputting engine speed) must, after receiving the command to shut down the mechanical pump, issue a motion command to the MFC tester when the speed drops to 1600 rpm at a rate of Δn = 2058 / 30 = 68.6 rpm. This test process involves a high rate of speed change, resulting in significant delays between the observer identifying the expected speed, issuing the control surface movement command, and the MFC tester operator outputting the command. This also requires high coordination, resulting in a low success rate for the pre-test, where only one of the five tests was "passed." This makes the typical three-repeat test difficult to implement, and also presents significant challenges for subsequent data analysis. Summary of the Invention

[0007] Purpose of the Invention

[0008] It is necessary to innovate and invent a set of multi-system linkage control test solutions based on the existing test conditions and software and hardware to solve the problems of difficulty in achieving automatic control and time delays in manual collaboration, so as to ensure the smooth implementation of the test.

[0009] Technical Solution

[0010] A ground-based integrated multi-system linkage control test method utilizes existing test equipment resources, identifies related signals, and builds an equipment architecture that implements test functions. A test management system and signal simulation system are added between the mechanical pump drive unit and the main flight control tester. Using the test site network, control signals from the mechanical pump drive unit are transmitted to the test management system via Ethernet and then to the signal simulation system via a reflective memory network. Control signal conversion is implemented in the signal simulation system, and the existing equipment simulation platform and software environment are utilized to implement a functional module for controlling control surface movements using onboard parameters.

[0011] The specific steps are as follows:

[0012] Step 1: Use the airborne signal ANLG / CD1C_1 / 2 / 3 / 4-001 input from the primary flight control system tester. The 1 / 2 / 3 / 4 throttle angles are associated with the engine speed and are also valid control signals for the primary flight control system tester (2-11). The 429 bus signal for the 1 / 2 / 3 / 4 throttle angles is only valid during the automatic flight control phase.

[0013] Step 2: Analyze the functions of existing test equipment to identify test equipment that can achieve link coupling between the test network and the airborne equipment, and build a functional architecture. This functional analysis identified a signal simulation system that can simulate analog signals and communicate with the airborne equipment remote data concentration unit.

[0014] In step 3, the mechanical pump drive device sends the simulated engine speed to the test management system via Ethernet, and the test management system sends it to the public network end via the reflective memory. The signal simulation system obtains the simulated engine speed signal from the reflective memory public network end, and uses the parameter conversion module compiled by the simulation platform of the signal simulation system to convert the engine speed signal DA into a 0-5V analog throttle angle signal, which is sent to the remote data acquisition unit of the airborne equipment to realize the link coupling between the equipment signal and the airborne equipment signal.

[0015] Step 4: Based on the signal simulation system simulation platform, the 1 / 2 / 3 / 4 engine speed signals are bound to the digital channels as inputs to the signal conversion simulation module. After logical conversion, they are converted into 1 / 2 / 3 / 4 throttle angles. These signals are bound to the analog channels as simulation outputs of the signal conversion module, thus converting the engine speed signals into engine throttle angle signals that can be recognized by the airborne system and sent to the remote data unit.

[0016] In step 5, the remote data acquisition unit transmits the 1 / 2 / 3 / 4 throttle angle signals to the remote data interface unit via the onboard 429 bus, and then transmits the 1 / 2 / 3 / 4 throttle angle signals to the flight control module via the 429 bus. The main flight control system tester reads the parameters of the flight control module, receives the 1 / 2 / 3 / 4 throttle angle signals (i.e., engine speed signals), and uses the script programming language environment open to the main flight control system tester to use the 1 / 2 / 3 / 4 throttle angles as control signals. The rudder action command signals are output through the rudder action control module, thereby realizing the control of the rudder by the engine speed signal.

[0017] Furthermore, the test method is implemented based on test equipment, airborne equipment, test software and a test network.

[0018] Furthermore, the test equipment includes a mechanical pump drive device, a main flight control system tester, a test management system, and a signal simulation system.

[0019] Furthermore, the airborne equipment includes a remote data concentration unit, a remote data interface unit, and a flight control module.

[0020] Furthermore, the test software includes a signal conversion simulation module and a rudder motion control module.

[0021] Furthermore, the test network includes Ethernet, reflective memory network, and clock synchronization network.

[0022] Furthermore, the signal simulation system is specifically VeriStand.

[0023] Furthermore, the script programming language environment is specifically Python.

[0024] The beneficial effects of this application are:

[0025] During this process, the testers of this invention broke with traditional thinking, analyzing the interconnectedness of the test equipment and airborne systems, and meticulously sorting out the internal and external interface relationships of the key equipment involved in this test. By leveraging the coupling relationship between the test network and airborne communications and implementing a multi-system linkage control test plan, the test mission was successfully completed, successfully achieving the main flight control system outputting control surface displacement when the mechanical pump drive speed dropped to 1600 r / min. The ground-integrated multi-system linkage control test method successfully completed the dynamic control test of the RAT functional test, resulting in valid test data, high test efficiency, and precise parameter control. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 This is a diagram of the ground integrated multi-system linkage control test plan; Figure 2 This is the signal coupling link diagram between the test network and the airborne equipment; Figure 3 Convert the flow chart for the signal conversion simulation module; Figure 4 Compile the rudder motion control module script diagram for Python. DETAILED DESCRIPTION

[0027] In order to make the purpose, technical solutions and advantages of the implementation of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the embodiments of the present invention. In the examples, the same or similar reference numerals throughout represent the same or similar originals or elements with the same or similar functions. The described embodiments are part of the embodiments of the present invention, not all of the embodiments. The embodiments described below by reference are illustrative and intended to be used to explain the present invention, and should not be understood as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention. The following is a detailed description in conjunction with the embodiments of the present invention.

[0028] a) Invented a network architecture for transmitting test signals between airborne equipment and ground simulation equipment.

[0029] b) A working module was invented to convert ground analog signals into airborne signals in a simulation environment.

[0030] c) Invented a Python script that converts onboard control signals into control commands for control surface movements.

[0031] d) A signal conversion and multi-level transmission test method was invented to achieve automated control of the test.

[0032] To achieve automated operation of this test condition, establishing communication between the main flight control tester and external systems was crucial to resolving this issue. During this process, test personnel broke with conventional thinking, analyzing the interconnections between test equipment and onboard systems, and meticulously analyzing the internal and external interfaces of key equipment involved in this test. Leveraging the coupling between the test network and onboard communications, they developed a novel test method that addressed the unique requirements of this test.

[0033] a) Explore a multi-system joint control concept and functional implementation architecture

[0034] After analyzing existing equipment resources and considering that the test requirements couldn't be manually implemented and the control signals couldn't be directly used as drivers, we innovated and utilized existing test equipment resources to identify related signals and build an equipment architecture that could implement the test functions. Specifically, a test management system and signal simulation system were added between the mechanical pump drive (control signal) and the main flight control tester (drive system). This resolved the main flight control tester's closed external interface issue.

[0035] b) Using the onboard signal communication link, find a method to achieve parameter communication and conversion between test equipment through the test network.

[0036] Based on the above-mentioned test architecture, the network at the test site was used to transmit the control signal of the mechanical pump drive device to the test management system via Ethernet, and then to the signal simulation system via the reflective memory network. In the signal simulation system, the control signal conversion was realized, that is, the speed signal was converted into a throttle angle signal that could be recognized by the main flight control system tester, which was used as the control parameter to drive the control surface movement.

[0037] c) Utilize the existing equipment simulation platform and software environment to innovate functional modules for realizing on-board parameter control of control surface movements.

[0038] Based on the VeriStand simulation platform of the signal simulation system, a signal conversion code was compiled through the signal conversion module to convert the engine speed signal into a throttle angle signal that can be recognized on the aircraft; then, using the existing open programming language environment of the main flight control system tester, the throttle angle was used as the control signal, and a program function code that can drive the three-axis movement of the control surface was compiled using Python, ultimately realizing the control of the control surface by speed.

[0039] d) The concept and architecture of this test method realize the resource integration of existing equipment and expand the functional scope of equipment. It can be widely used to complete complex boundary tests and extended tests of various aircraft systems, providing a platform for test verification.

[0040] e) The use of software function modules in this method has been used to edit the output of non-standard command curves for hydraulic systems and flight control systems. The multi-system joint control concept has also been applied to frequency response tests, stability reserve tests, and system boundary tests.

[0041] f) The implementation process of this test method can be applied to ground tests with different system cascades and non-uniform signal interfaces of the underlying models. By using correlation parameters to achieve a transition from indirect correlation to direct control, it can be used in semi-physical simulation tests of UAVs, providing an effective approach for the logical verification of UAV control systems.

[0042] 9 Working Principle

[0043] To achieve automated operation of this test condition, establishing communication between the main flight control tester and external systems was crucial to resolving this issue. During this process, test personnel analyzed the interconnections between the test equipment and onboard systems, meticulously analyzing the internal and external interfaces of key equipment involved in this test. Leveraging the coupling between the test network and onboard communications, they developed a novel test method that addressed the unique requirements of this test.

[0044] Example

[0045] The ground integrated multi-system linkage control scheme mainly consists of test equipment, airborne equipment, test software (including signal conversion simulation module and control surface action control module) and test network. Figure 1 .

[0046] 8.3 Design Plan

[0047] a) Finding correlation signals

[0048] By combing through the internal and external signals of key test equipment and airborne systems, the airborne signal ANLG / CD1C_1 / 2 / 3 / 4-001 1 / 2 / 3 / 4 throttle angle (2-6) that can be used as the input of the main flight control system tester was found. This signal is related to the engine speed and is also an effective control signal for the main flight control system tester (2-11). The 429 bus signal of the 1 / 2 / 3 / 4 throttle angle is only valid in the automatic flight control phase, and the flight control law is invalid. Its occupation does not affect the integrity of the system.

[0049] b) Complete the connection and coupling of the test network and the airborne equipment signal link

[0050] After identifying the test control-related signals, the functionality of the existing test equipment was analyzed to identify test equipment that could achieve link coupling between the test network and the airborne equipment, thereby building a functional architecture. This functional analysis identified a signal simulation system (2-5), which has the capabilities of simulating analog signals and communicating with the airborne equipment remote data concentration unit (2-6).

[0051] After the key signals and key equipment are identified, the mechanical pump drive device (2-1) transmits the simulated engine speed to the test management system (2-3) via Ethernet (2-2). The test management system (2-3) transmits the signal to the public network via the reflective memory (2-4). The signal simulation system (2-5) obtains the simulated engine speed signal from the reflective memory public network. Using the parameter conversion module programmed by the simulation platform of the signal simulation system (2-5), the engine speed signal is converted into a (0-5V) analog throttle angle signal (2-6) and sent to the airborne equipment remote data acquisition unit (2-7). This achieves link coupling between the equipment signal and the airborne equipment signal.

[0052] c) Implementation of test control function

[0053] After completing the signal link connection and coupling, based on the VeriStand simulation platform (3-1) of the signal simulation system, the 1 / 2 / 3 / 4 engine speed (3-2) signal is bound to the digital channel as the input of the signal conversion simulation module (3-3), converted into 1 / 2 / 3 / 4 throttle angles (3-4) through logical conversion, and bound to the analog channel as the simulation output of the signal conversion module (3-5), realizing the conversion of the engine speed signal into an engine throttle angle signal that can be recognized by the airborne system; and sent to the remote data unit (3-6). The conversion process of the signal conversion simulation module of the signal simulation system is shown in Figure 3 .

[0054] The remote data acquisition unit (2-6) transmits the 1 / 2 / 3 / 4 throttle angle signals to the remote data interface unit (2-8) via the onboard 429 bus, and then transmits the 1 / 2 / 3 / 4 throttle angle signals to the flight control module (2-9) via the 429 bus. The main flight control system tester (2-11) reads the parameters of the flight control module (2-9) and receives the 1 / 2 / 3 / 4 throttle angle signals (i.e., engine speed signals). Using the Python script programming language environment open to the main flight control system tester (2-11), the 1 / 2 / 3 / 4 throttle angles are used as control signals (2-10). The rudder action command signals are output through the rudder action control module (2-12), ultimately achieving control of the rudder by the engine speed signal. For Python scripting of the rudder action control module, see [2-10]. Figure 4 .

[0055] In addition, unless otherwise defined, the technical or scientific terms used in the description of this application should have the ordinary meanings understood by those of ordinary skill in the art to which this application belongs. The words "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer" used in the description of this application are only used to indicate relative directions or positional relationships, and do not imply that the device or component must have a specific orientation, be constructed, or operate in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. Therefore, they should not be understood as limitations on this application. The words "first," "second," "third," and similar terms used in the description of this application are used only for descriptive purposes to distinguish different components and should not be understood to indicate or imply relative importance. The words "one," "an," or "the" used in the description of this application should not be understood as absolute limitations on quantity, but should be understood as meaning the presence of at least one. The words "include" or "comprises" used in the description of this application mean that the element or object listed before the word includes the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0056] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "install", "connect", "connect" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or a connection between two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0057] The above description is only a specific embodiment of the present invention and is not intended to limit the present invention. Within the spirit and principles of the present invention, any technician familiar with the profession may use the technical content disclosed above to change or modify it into an equivalent embodiment with equivalent changes and apply it to other fields. However, any simple modification, equivalent change and modification made to the above embodiment based on the technical essence of the present invention without departing from the content of the technical solution of the present invention, any modification, equivalent replacement, improvement, etc. made should be included in the scope of protection of the present invention.

Claims

1. A test method for ground integrated multi-system linkage control, characterized in that: Identify related signals and build an equipment architecture that realizes the test function; add a test management system and a signal simulation system between the mechanical pump drive device and the main flight control tester, and use the network at the test site to realize the transmission of the control signal of the mechanical pump drive device to the test management system through Ethernet, and then to the signal simulation system through the reflective memory network; realize the conversion of control signals in the signal simulation system, and use the existing equipment simulation platform and software environment to realize the functional module of on-board parameter control of control surface action.

2. The method according to claim 1, wherein The specific steps are as follows: Step 1: Use the airborne signal ANLG / CD1C_1 / 2 / 3 / 4-001 input from the primary flight control system tester. The 1 / 2 / 3 / 4 throttle angles are associated with the engine speed and are also valid control signals for the primary flight control system tester. The 429 bus signals for the 1 / 2 / 3 / 4 throttle angles are valid only during the automatic flight control phase. Step 2: Analyze the functions of existing test equipment, identify test equipment that can achieve link coupling between the test network and airborne equipment, and build a functional architecture; Through functional analysis, a signal simulation system was found, which has the functions of analog signal simulation and communication with the remote data concentration unit of the onboard equipment; Step 3: The mechanical pump drive device sends the simulated engine speed to the test management system via Ethernet. The test management system sends the signal to the public network via the reflective memory. The signal simulation system obtains the simulated engine speed signal from the reflective memory public network. The signal simulation system uses a parameter conversion module programmed by the simulation platform to convert the engine speed signal DA into a 0-5V analog throttle angle signal. The signal is then sent to the airborne equipment remote data acquisition unit, achieving link coupling between the equipment signal and the airborne equipment signal. Step 4: Based on the signal simulation system simulation platform, the 1 / 2 / 3 / 4 engine speed signals are bound to the digital channels as inputs to the signal conversion simulation module. After logical conversion, they are converted into 1 / 2 / 3 / 4 throttle angles. These signals are bound to the analog channels as simulation outputs of the signal conversion module, thus converting the engine speed signals into engine throttle angle signals that can be recognized by the airborne system and sent to the remote data unit. In step 5, the remote data acquisition unit transmits the 1 / 2 / 3 / 4 throttle angle signals to the remote data interface unit via the onboard 429 bus, and then transmits the 1 / 2 / 3 / 4 throttle angle signals to the flight control module via the 429 bus. The main flight control system tester reads the parameters of the flight control module, receives the 1 / 2 / 3 / 4 throttle angle signals, and uses the script programming language environment open to the main flight control system tester to use the 1 / 2 / 3 / 4 throttle angles as control signals. The rudder action command signals are output through the rudder action control module, thereby realizing the control of the rudder by the engine speed signal.

3. The method according to claim 2, wherein The test method is implemented based on test equipment, airborne equipment, test software and a test network.

4. The method according to claim 3, wherein The test equipment includes a mechanical pump driving device, a main flight control system tester, a test management system, and a signal simulation system.

5. The method according to claim 3, wherein The airborne equipment includes a remote data concentration unit, a remote data interface unit, and a flight control module.

6. The method according to claim 3, wherein The test software includes a signal conversion simulation module and a rudder action control module.

7. The method according to claim 3, wherein The test network includes Ethernet, reflective memory network and clock synchronization network.

8. The method according to claim 4, wherein The signal simulation system is specifically VeriStand.

9. The method according to claim 2, wherein The script programming language environment is specifically Python.

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