A redundant primary flight control equivalent system and identification test method

Abstract

The embodiment of the present application is about a redundant main flight control equivalent system and an identification test method. The redundant main flight control equivalent system includes a control machine and a flight control computer. The flight control computer has a flight control module and an auxiliary control module. The control machine and the auxiliary control module are used to receive external signals, and the flight control module is used to process external signals; wherein the flight control module is connected to the control machine through a first line, and the flight control module is connected to the auxiliary control module through a second line; the flight control module is self-wrap-around connected through a first loop line, the control machine and the flight control module are mutually loop-around connected through a second loop line, and the auxiliary control module and the flight control module are mutually loop-around connected through a third loop line. The embodiment of the present application calls the various functional modules of the redundant main flight control equivalent system to the greatest extent, constructs system-level operating conditions under the condition of limited equipment, and is also conducive to cost control.

Description

Technical Field

[0001] The present application relates to the field of flight control technology, and in particular to a redundant main flight control equivalent system and an identification test method. Background Art

[0002] The flight control system is a key system for aircraft safety control. It receives control commands from the cockpit, drives the aircraft control surfaces to control the aircraft's flight attitude. As the core of the flight control system, the primary flight control system is mainly responsible for comprehensive processing of the cockpit pilot's control commands and the status of external sensors. The primary flight control system generates control commands for the control surfaces through redundant input signal monitoring and voting, and control law calculation to achieve motion control, such as the motion control of the control surfaces in the three axes of vertical and horizontal navigation.

[0003] In the related technology, system-level testing and verification are required for the flight control system to meet the requirements of comprehensive characterization of the equipment's working characteristics. Therefore, existing flight control systems generally adopt redundant configurations, but this requires a large number of electronic equipment such as multiple flight control computers and multiple control machines to achieve, which is not only costly, but also unable to build system-level operating conditions when equipment is limited.

[0004] Therefore, it is necessary to provide a new technical solution to improve one or more problems existing in the above solutions.

[0005] It should be noted that the information disclosed in the above background technology section is only used to enhance the understanding of the background of the present application, and therefore may include information that does not constitute the prior art known to ordinary technicians in the field. Summary of the invention

[0006] The purpose of the embodiments of the present application is to provide a redundant main flight control equivalent system and an identification test method, to establish system-level operating conditions under limited equipment, and also to facilitate cost control.

[0007] According to a first aspect of an embodiment of the present application, a redundant main flight control equivalent system is provided, the redundant main flight control equivalent system comprising a control machine and a flight control computer, the flight control computer comprising a flight control module and an auxiliary control module, the control machine and the auxiliary control module are used to receive external signals, and the flight control module is used to process the external signals; wherein,

[0008] The flight control module is connected to the control machine via a first line, and the flight control module is connected to the auxiliary control module via a second line;

[0009] The flight control module is connected to itself via a first loop circuit, the control machine and the flight control module are connected to each other via a second loop circuit, and the auxiliary control module and the flight control module are connected to each other via a third loop circuit.

[0010] In an exemplary embodiment of the present application, the flight control module is provided with a first channel interface, the first channel interface includes a first sending channel interface and a first receiving channel interface, and the first loop line connects the first sending channel interface and the first receiving channel interface.

[0011] In an exemplary embodiment of the present application, the first transmission channel interface and the first reception channel interface both include a high-end channel interface and a low-end channel interface, and the first bypass line includes a high-end channel bypass line and a low-end channel bypass line; wherein,

[0012] The high-end channel wraparound line connects the high-end channel interface of the first sending channel interface and the high-end channel interface of the first receiving channel interface, and the low-end channel wraparound line connects the low-end channel interface of the first sending channel interface and the low-end channel interface of the first receiving channel interface.

[0013] In an exemplary embodiment of the present application, the flight control module is provided with a second channel interface, the second channel interface includes a second sending channel interface and a second receiving channel interface, the auxiliary control module is provided with a third channel interface, the third channel interface includes a third sending channel interface and a third receiving channel interface; wherein,

[0014] The third loop lines are provided with two groups, one group of the third loop lines connects the second sending channel interface and the third receiving channel interface, and the other group of the third loop lines connects the third sending channel interface and the second receiving channel interface.

[0015] In an exemplary embodiment of the present application, the flight control module is provided with a fourth channel interface, the fourth channel interface includes a fourth sending channel interface and a fourth receiving channel interface, the control machine is provided with a fifth channel interface, the fifth channel interface includes a fifth sending channel interface and a fifth receiving channel interface; wherein,

[0016] Two groups of the second loop lines are provided, one group of the second loop lines connects the fourth sending channel interface and the fifth receiving channel interface, and the other group of the second loop lines connects the fifth sending channel interface and the fourth receiving channel interface.

[0017] In an exemplary embodiment of the present application, the first line, the second line, the first wraparound line, the second wraparound line and the third wraparound line are all SIB buses.

[0018] According to a second aspect of an embodiment of the present application, an identification test method is provided for verifying the above-mentioned redundant primary flight control equivalent system, and the identification test method comprises:

[0019] Set the initialization scenario so that the redundant main flight control equivalent system can be started in the air;

[0020] The redundant main flight control equivalent system receives an external test signal, and performs equivalent wrapping processing on the external test signal to obtain a signal to be verified;

[0021] Performing system redundancy signal integrity confirmation on the signal to be verified;

[0022] The signal to be verified is solved and processed by the redundant main flight control equivalent system to obtain the control instruction to be verified, and it is confirmed whether the control instruction to be verified is correct.

[0023] In an exemplary embodiment of the present application, the redundant main flight control equivalent system receives an external test signal, and performs equivalent wrapping processing on the external test signal to obtain a signal to be verified, including:

[0024] The control machine and the auxiliary control module receive the external test signal;

[0025] The control machine and the auxiliary control module respectively rewind the external test signal and transmit it to the flight control module;

[0026] The flight control module self-rewinds the external test signal to obtain multiple channels of the to-be-verified signals.

[0027] In an exemplary embodiment of the present application, the redundant main flight control equivalent system receives an external test signal, performs equivalent wrapping processing on the external test signal, and obtains a signal to be verified, further comprising:

[0028] Monitoring the signal to be verified by the flight control module;

[0029] Confirm whether the signal to be verified has any fault.

[0030] In an exemplary embodiment of the present application, before the redundant primary flight control equivalent system receives an external test signal, it also includes:

[0031] The external test signal is simulated, wherein the external test signal includes a cockpit signal and a sensor signal.

[0032] The technical solution provided by this application may have the following beneficial effects:

[0033] In an embodiment of the present application, a redundant main flight control equivalent system includes a control machine and a flight control computer, and for one control machine and one flight control computer, on the basis of connecting the flight control module to the control machine through a first line and connecting the flight control module to the auxiliary control module through a second line, this embodiment further performs a self-wrap connection on the flight control module of the flight control computer to equivalently produce the interface cross-linking characteristics of the two flight control modules when there are two flight control computers, and further performs a self-wrap connection on the control machine and the flight control module, and a self-wrap connection on the auxiliary control module and the flight control module to equivalently produce the interface cross-linking characteristics of the two control machines and the two flight control modules when there are two control machines and two flight control computers, and the interface cross-linking characteristics of the two auxiliary control modules and the two flight control modules, so that the redundant main flight control equivalent system of this embodiment can achieve the same system-level testing effect as multiple control machines and multiple flight control computers by using one control machine and one flight control computer. This embodiment calls upon the functional modules of the redundant main flight control equivalent system to the greatest extent, constructs system-level operating conditions under limited equipment, and is also beneficial to cost control.

[0034] It should be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] The drawings herein are incorporated into the specification and constitute a part of the specification, illustrate embodiments consistent with the present application, and together with the specification are used to explain the principles of the present application. Obviously, the drawings described below are only some embodiments of the present application, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0036] Figure 1 A schematic diagram showing a redundant primary flight control equivalent system in an exemplary embodiment of the present application;

[0037] Figure 2 A schematic diagram showing a complete set of primary flight control systems of the prior art;

[0038] Figure 3 A flow chart showing the steps of an identification test method in an exemplary embodiment of the present application.

[0039] Reference numerals:

[0040] 100, control machine; 111, fifth channel interface; 112, sixth channel interface;

[0041] 200, flight control computer; 210, flight control module; 211, first channel interface; 212, second channel interface; 213, fourth channel interface; 214, seventh channel interface; 215, ninth channel interface; 220, auxiliary control module; 221, third channel interface; 222, eighth channel interface;

[0042] 300, first circuit; 400, second circuit; 500, first loop circuit; 600, second loop circuit; 700, third loop circuit. DETAILED DESCRIPTION

[0043] Example embodiments will now be described more fully with reference to the accompanying drawings. However, example embodiments can be implemented in a variety of forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that this application will be more comprehensive and complete and fully convey the concepts of the example embodiments to those skilled in the art. The described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.

[0044] In addition, the drawings are only schematic illustrations of the present application and are not necessarily drawn to scale. The same reference numerals in the drawings represent the same or similar parts, and their repeated descriptions will be omitted. Some of the block diagrams shown in the drawings are functional entities and do not necessarily correspond to physically or logically independent entities.

[0045] In this example implementation, a redundant primary flight control equivalent system is first provided. Figure 1 As shown in , the redundant main flight control equivalent system includes a control machine 100 and a flight control computer 200, the flight control computer 200 includes a flight control module 210 and an auxiliary control module 220, the control machine 100 and the auxiliary control module 220 are used to receive external signals, and the flight control module 210 is used to process external signals. Among them, the flight control module 210 is connected to the control machine 100 through a first line 300, and the flight control module 210 is connected to the auxiliary control module 220 through a second line 400; the flight control module 210 is self-wound through a first winding line 500, the control machine 100 and the flight control module 210 are mutually wound through a second winding line 600, and the auxiliary control module 220 and the flight control module 210 are mutually wound through a third winding line 700.

[0046] In the embodiment of the present application, the redundant main flight control equivalent system includes a control machine 100 and a flight control computer 200, and for a control machine 100 and a flight control computer 200, this embodiment further connects the flight control module 210 to the control machine 100 through a first line 300 and connects the flight control module 210 to the auxiliary control module 220 through a second line 400, and further connects the flight control module 210 of the flight control computer 200 to the self-wrap connection, so as to equivalently produce the interface cross-linking characteristics of the two flight control modules 210 when two flight control computers 200 are provided, and further connects the control machine 100 to the auxiliary control module 220 through a second line 400. 00 is connected to the flight control module 210 in a revolving manner, and the auxiliary control module 220 is connected to the flight control module 210 in a revolving manner, so as to equivalently show the interface cross-linking characteristics of the two control machines 100 and the two flight control modules 210 when there are two control machines 100 and two flight control computers 200, and the interface cross-linking characteristics of the two auxiliary control modules 220 and the two flight control modules 210, so that the redundant main flight control equivalent system of this embodiment can achieve the same system-level test effect as multiple control machines 100 and multiple flight control computers 200 by using one control machine 100 and one flight control computer 200. This embodiment calls each functional module of the redundant main flight control equivalent system to the maximum extent, constructs system-level operating conditions under limited equipment, and is also conducive to cost control.

[0047] Next, we will refer to Figure 1 The above-mentioned redundant main flight control equivalent system in this example implementation is described in more detail.

[0048] Before discussing the redundant primary flight control equivalent system provided by this embodiment, an example of a complete set of primary flight control systems in the prior art is first given to facilitate understanding of the redundant primary flight control equivalent system provided by this embodiment. Figure 2 As shown in , a complete set of main flight control system in the prior art may include a first flight control computer, a second flight control computer, a first control machine and a second control machine. The first flight control computer is composed of a first flight control module and a first auxiliary control module, and the second flight control computer is composed of a second flight control module and a second auxiliary control module. Figure 2 In the complete set of main flight control system shown in , the first flight control computer and the second flight control computer, the first control machine and the second control machine and the first flight control computer respectively, the first control machine and the second control machine and the second flight control computer respectively, the first auxiliary control module and the second auxiliary control module and the first flight control computer respectively, and the first auxiliary control module and the second auxiliary control module and the second flight control computer respectively all communicate through the system bus.

[0049] It should also be noted that the redundant main flight control equivalent system provided in this embodiment has the characteristics that each device is independent, redundant and interchangeable, and the electrical interface and signal interface are completely consistent. The flight control computer 200 in the redundant main flight control equivalent system of this embodiment selects the system dual-redundant main flight control computer, and the control machine 100 selects the dual-redundant servo control electronic equipment. The dual-redundant main flight control computer and the dual-redundant servo control electronic equipment of the system are wrapped around by the interface equivalent, representing the interconnection relationship of the redundant devices, and having the ability to verify the cross-transmission of redundant signals, thereby achieving the working goal of representing the full set of main flight control systems through one flight control computer 200 and one control machine 100.

[0050] In one embodiment, the flight control module 210 is provided with a first channel interface 211 , the first channel interface 211 includes a first sending channel interface and a first receiving channel interface, and the first loop line 500 connects the first sending channel interface and the first receiving channel interface.

[0051] The first transmission channel interface of the flight control module 210 can send signals or commands to the outside through the first bypass line 500, and the first receiving channel interface of the flight control module 210 can receive external signals or commands through the first bypass line 500, so as to equivalently output Figure 2 The communication characteristics between the first flight control module and the second flight control module shown in ensure the integrity of the external interface of the flight control module 210.

[0052] Optionally, the first sending channel interface and the first receiving channel interface both include a high-end channel interface and a low-end channel interface, and the first bypass line 500 includes a high-end channel bypass line and a low-end channel bypass line; wherein the high-end channel bypass line connects the high-end channel interface of the first sending channel interface and the high-end channel interface of the first receiving channel interface, and the low-end channel bypass line connects the low-end channel interface of the first sending channel interface and the low-end channel interface of the first receiving channel interface.

[0053] The high-end channel interface of the above-mentioned first sending channel interface is looped back to the high-end channel interface of the first receiving channel interface through the high-end channel loop line, and the low-end channel interface of the first sending channel interface is looped back to the low-end channel interface of the first receiving channel interface through the low-end channel loop line, ensuring the interface consistency of the first sending channel interface and the first receiving channel interface of the flight control module 210.

[0054] It should be noted that Figure 1Tx+ and Tx- at the first channel interface 211 in the figure represent the first transmission channel interface, specifically, Tx+ represents the high-end channel interface of the first transmission channel interface, and Tx- represents the low-end channel interface of the first transmission channel interface. Rx+ and Rx- at the first channel interface 211 represent the first receiving channel interface, specifically, Rx+ represents the high-end channel interface of the first receiving channel interface, and Rx- represents the low-end channel interface of the first receiving channel interface.

[0055] In one embodiment, the flight control module 210 is provided with a second channel interface 212, the second channel interface 212 includes a second sending channel interface and a second receiving channel interface, and the auxiliary control module 220 is provided with a third channel interface 221, the third channel interface 221 includes a third sending channel interface and a third receiving channel interface; wherein, the third loop circuit 700 is provided with two groups, one group of the third loop circuit 700 connects the second sending channel interface and the third receiving channel interface, and the other group of the third loop circuit 700 connects the third sending channel interface and the second receiving channel interface.

[0056] The second transmission channel interface of the flight control module 210 can send signals or commands to the outside through a set of third loop lines 700, and the second receiving channel interface of the flight control module 210 can receive external signals or commands through another set of third loop lines 700, so as to equivalently output Figure 2 The communication characteristics between the first flight control module and the second auxiliary control module shown in ensure the integrity of the external interface of the flight control module 210.

[0057] Accordingly, the third transmission channel interface of the auxiliary control module 220 can send signals or commands to the outside through a group of third loop lines 700, and the third receiving channel interface of the auxiliary control module 220 can receive external signals or commands through another group of third loop lines 700, so as to equivalently output the following: Figure 2 The communication characteristics between the first auxiliary control module and the second flight control module shown in ensure the integrity of the external interface of the auxiliary control module 220.

[0058] Specifically, the second sending channel interface and the third receiving channel interface both include a high-end channel interface and a low-end channel interface, and each group of third bypass lines 700 includes a high-end channel bypass line and a low-end channel bypass line; wherein, the high-end channel bypass line of the third bypass line 700 connects the high-end channel interface of the second sending channel interface and the high-end channel interface of the third receiving channel interface, and the low-end channel bypass line of the third bypass line 700 connects the low-end channel interface of the second sending channel interface and the low-end channel interface of the third receiving channel interface.

[0059] The high-end channel interface of the above-mentioned second sending channel interface is looped back to the high-end channel interface of the third receiving channel interface through the corresponding high-end channel loop circuit of the third loop circuit 700, and the low-end channel interface of the second sending channel interface is looped back to the low-end channel interface of the third receiving channel interface through the corresponding low-end channel loop circuit of the third loop circuit 700, thereby ensuring the interface consistency of the second sending channel interface of the flight control module 210 and the third receiving channel interface of the auxiliary control module 220.

[0060] Specifically, the second receiving channel interface and the third sending channel interface both include a high-end channel interface and a low-end channel interface, and each group of third bypass lines 700 includes a high-end channel bypass line and a low-end channel bypass line; wherein, the high-end channel bypass line of the third bypass line 700 connects the high-end channel interface of the third sending channel interface and the high-end channel interface of the second receiving channel interface, and the low-end channel bypass line of the third bypass line 700 connects the low-end channel interface of the third sending channel interface and the low-end channel interface of the second receiving channel interface.

[0061] The high-end channel interface of the above-mentioned third sending channel interface is looped back to the high-end channel interface of the second receiving channel interface through the corresponding high-end channel loop circuit of the third loop circuit 700, and the low-end channel interface of the third sending channel interface is looped back to the low-end channel interface of the second receiving channel interface through the corresponding low-end channel loop circuit of the third loop circuit 700, thereby ensuring the interface consistency between the second receiving channel interface of the flight control module 210 and the third sending channel interface of the auxiliary control module 220.

[0062] It should be noted that Figure 1 Tx+ and Tx- at the second channel interface 212 in the figure represent the second transmission channel interface, specifically, Tx+ represents the high-end channel interface of the second transmission channel interface, and Tx- represents the low-end channel interface of the second transmission channel interface. Rx+ and Rx- at the second channel interface 212 represent the second receiving channel interface, specifically, Rx+ represents the high-end channel interface of the second receiving channel interface, and Rx- represents the low-end channel interface of the second receiving channel interface.

[0063] It should be noted that Figure 1 Tx+ and Tx- at the third channel interface 221 in the figure represent the third transmission channel interface, specifically, Tx+ represents the high-end channel interface of the third transmission channel interface, and Tx- represents the low-end channel interface of the third transmission channel interface. Rx+ and Rx- at the third channel interface 221 represent the third receiving channel interface, specifically, Rx+ represents the high-end channel interface of the third receiving channel interface, and Rx- represents the low-end channel interface of the third receiving channel interface.

[0064] In one embodiment, the flight control module 210 is provided with a fourth channel interface 213, the fourth channel interface 213 includes a fourth sending channel interface and a fourth receiving channel interface, and the control machine 100 is provided with a fifth channel interface 111, and the fifth channel interface 111 includes a fifth sending channel interface and a fifth receiving channel interface; wherein, the second loop circuit 600 is provided with two groups, one group of the second loop circuit 600 connects the fourth sending channel interface and the fifth receiving channel interface, and the other group of the second loop circuit 600 connects the fifth sending channel interface and the fourth receiving channel interface.

[0065] The fourth transmission channel interface of the flight control module 210 can send signals or commands to the outside through a set of second loop lines 600, and the fourth receiving channel interface of the flight control module 210 can receive external signals or commands through another set of second loop lines 600, so as to equivalently output the following: Figure 2 The communication characteristics between the first flight control module and the second control machine shown in ensure the integrity of the external interface of the flight control module 210.

[0066] Accordingly, the fifth transmission channel interface of the control machine 100 can send signals or commands to the outside through a group of second loop lines 600, and the fifth receiving channel interface of the control machine 100 can receive external signals or commands through another group of second loop lines 600, so as to equivalently output the following: Figure 2 The communication characteristics between the first control machine and the second flight control module shown in ensure the integrity of the external interface of the control machine 100.

[0067] Specifically, the fourth sending channel interface and the fifth receiving channel interface both include a high-end channel interface and a low-end channel interface, and each group of second bypass lines 600 includes a high-end channel bypass line and a low-end channel bypass line; wherein, the high-end channel bypass line of the second bypass line 600 connects the high-end channel interface of the fourth sending channel interface and the high-end channel interface of the fifth receiving channel interface, and the low-end channel bypass line of the second bypass line 600 connects the low-end channel interface of the fourth sending channel interface and the low-end channel interface of the fifth receiving channel interface.

[0068] The high-end channel interface of the above-mentioned fourth sending channel interface is looped back to the high-end channel interface of the fifth receiving channel interface through the high-end channel loop circuit of the corresponding second loop circuit 600, and the low-end channel interface of the fourth sending channel interface is looped back to the low-end channel interface of the fifth receiving channel interface through the low-end channel loop circuit of the corresponding second loop circuit 600, thereby ensuring the interface consistency of the fourth sending channel interface of the flight control module 210 and the fifth receiving channel interface of the control machine 100.

[0069] Specifically, the fourth receiving channel interface and the fifth sending channel interface both include a high-end channel interface and a low-end channel interface, and each group of second bypass lines 600 includes a high-end channel bypass line and a low-end channel bypass line; wherein, the high-end channel bypass line of the second bypass line 600 connects the high-end channel interface of the fifth sending channel interface and the high-end channel interface of the fourth receiving channel interface, and the low-end channel bypass line of the second bypass line 600 connects the low-end channel interface of the fifth sending channel interface and the low-end channel interface of the fourth receiving channel interface.

[0070] The high-end channel interface of the above-mentioned fifth sending channel interface is looped back to the high-end channel interface of the fourth receiving channel interface through the high-end channel loop circuit of the corresponding second loop circuit 600, and the low-end channel interface of the fifth sending channel interface is looped back to the low-end channel interface of the fourth receiving channel interface through the low-end channel loop circuit of the corresponding second loop circuit 600, ensuring the interface consistency of the fourth receiving channel interface of the flight control module 210 and the fifth sending channel interface of the control machine 100.

[0071] It should be noted that Figure 1 Tx+ and Tx- at the fourth channel interface 213 in the figure represent the fourth transmission channel interface, specifically, Tx+ represents the high-end channel interface of the fourth transmission channel interface, and Tx- represents the low-end channel interface of the fourth transmission channel interface. Rx+ and Rx- at the fourth channel interface 213 represent the fourth receiving channel interface, specifically, Rx+ represents the high-end channel interface of the fourth receiving channel interface, and Rx- represents the low-end channel interface of the fourth receiving channel interface.

[0072] It should be noted that Figure 1 Tx+ and Tx- at the fifth channel interface 111 in the figure represent the fifth transmission channel interface, specifically, Tx+ represents the high-end channel interface of the fifth transmission channel interface, and Tx- represents the low-end channel interface of the fifth transmission channel interface. Rx+ and Rx- at the fifth channel interface 111 represent the fifth receiving channel interface, specifically, Rx+ represents the high-end channel interface of the fifth receiving channel interface, and Rx- represents the low-end channel interface of the fifth receiving channel interface.

[0073] In the redundant main flight control equivalent system of this embodiment, the physical medium of the electrical interface of the equivalent loop must be consistent with the design status of the complete main flight control system. A serial point-to-point communication bus is used to ensure the integrity of all external interfaces of the flight control computer 200 and the control machine 100 as the loop objects, thereby ensuring the reliability of the data link.

[0074] In one embodiment, the control machine 100 is provided with a sixth channel interface 112, and the flight control module 210 is provided with a seventh channel interface 214. The first line 300 connects the sixth channel interface 112 and the seventh channel interface 214 to enable signal transmission between the sixth channel interface 112 of the control machine 100 and the seventh channel interface 214 of the flight control module 210.

[0075] In one embodiment, the auxiliary control module 220 is provided with an eighth channel interface 222, and the flight control module 210 is provided with a ninth channel interface 215, and the second line 400 connects the eighth channel interface 222 and the ninth channel interface 215 to enable signal transmission between the eighth channel interface 222 of the auxiliary control module 220 and the ninth channel interface 215 of the flight control module 210.

[0076] It should be noted that the sixth channel interface 112 set on the above-mentioned control machine 100, the eighth channel interface 222 set on the auxiliary control module 220, and the seventh channel interface 214 and the ninth channel interface 215 set on the flight control module 210 belong to the basic communication connection relationship between a flight control computer 200 and a control machine 100, that is, when the control machine 100 and the auxiliary control module 220 collect single-channel signals, they must be transmitted to the flight control module 210 through the corresponding interface and the corresponding line.

[0077] Further, the sixth channel interface 112 includes a sixth sending channel interface and a sixth receiving channel interface, and the seventh channel interface 214 includes a seventh sending channel interface and a seventh receiving channel interface; wherein, the first line 300 is provided with two groups, one group of the first line 300 connects the sixth sending channel interface and the seventh receiving channel interface, and the other group of the first line 300 connects the seventh sending channel interface and the sixth receiving channel interface.

[0078] Specifically, the sixth sending channel interface, the sixth receiving channel interface, the seventh sending channel interface and the seventh receiving channel interface all include a high-end channel interface and a low-end channel interface, and each group of first lines 300 includes a high-end channel line and a low-end channel line; wherein, the high-end channel lines of one group of first lines 300 are connected to the high-end channel interface of the sixth sending channel interface and the high-end channel interface of the seventh receiving channel interface, and the high-end channel lines of another group of first lines 300 are connected to the high-end channel interface of the seventh sending channel interface and the high-end channel interface of the sixth receiving channel interface; the low-end channel lines of one group of first lines 300 are connected to the low-end channel interface of the sixth sending channel interface and the low-end channel interface of the seventh receiving channel interface, and the low-end channel lines of another group of first lines 300 are connected to the low-end channel interface of the seventh sending channel interface and the low-end channel interface of the sixth receiving channel interface.

[0079] Further, the above-mentioned eighth channel interface 222 includes an eighth sending channel interface and an eighth receiving channel interface, and the above-mentioned ninth channel interface 215 includes a ninth sending channel interface and a ninth receiving channel interface; wherein, the second line 400 is provided with two groups, one group of second lines 400 connects the eighth sending channel interface and the ninth receiving channel interface, and the other group of second lines 400 connects the ninth sending channel interface and the eighth receiving channel interface.

[0080] Specifically, the eighth sending channel interface, the eighth receiving channel interface, the ninth sending channel interface and the ninth receiving channel interface all include a high-end channel interface and a low-end channel interface, and each group of second lines 400 includes a high-end channel line and a low-end channel line; wherein, the high-end channel lines of one group of second lines 400 are connected to the high-end channel interface of the eighth sending channel interface and the high-end channel interface of the ninth receiving channel interface, and the high-end channel lines of another group of second lines 400 are connected to the high-end channel interface of the ninth sending channel interface and the high-end channel interface of the eighth receiving channel interface; the low-end channel lines of one group of second lines 400 are connected to the low-end channel interface of the eighth sending channel interface and the low-end channel interface of the ninth receiving channel interface, and the low-end channel lines of another group of second lines 400 are connected to the low-end channel interface of the ninth sending channel interface and the low-end channel interface of the eighth receiving channel interface.

[0081] It should be noted that Figure 1 Tx+ and Tx- at the sixth channel interface 112 in the figure represent the sixth transmission channel interface, specifically, Tx+ represents the high-end channel interface of the sixth transmission channel interface, and Tx- represents the low-end channel interface of the sixth transmission channel interface. Rx+ and Rx- at the sixth channel interface 112 represent the sixth receiving channel interface, specifically, Rx+ represents the high-end channel interface of the sixth receiving channel interface, and Rx- represents the low-end channel interface of the sixth receiving channel interface.

[0082] It should be noted that Figure 1 Tx+ and Tx- at the seventh channel interface 214 in the figure represent the seventh transmission channel interface, specifically, Tx+ represents the high-end channel interface of the seventh transmission channel interface, and Tx- represents the low-end channel interface of the seventh transmission channel interface. Rx+ and Rx- at the seventh channel interface 214 represent the seventh receiving channel interface, specifically, Rx+ represents the high-end channel interface of the seventh receiving channel interface, and Rx- represents the low-end channel interface of the seventh receiving channel interface.

[0083] It should be noted that Figure 1Tx+ and Tx- at the eighth channel interface 222 in the figure represent the eighth transmission channel interface, specifically, Tx+ represents the high-end channel interface of the eighth transmission channel interface, and Tx- represents the low-end channel interface of the eighth transmission channel interface. Rx+ and Rx- at the eighth channel interface 222 represent the eighth receiving channel interface, specifically, Rx+ represents the high-end channel interface of the eighth receiving channel interface, and Rx- represents the low-end channel interface of the eighth receiving channel interface.

[0084] It should be noted that Figure 1 Tx+ and Tx- at the ninth channel interface 215 in the figure represent the ninth transmission channel interface, specifically, Tx+ represents the high-end channel interface of the ninth transmission channel interface, and Tx- represents the low-end channel interface of the ninth transmission channel interface. Rx+ and Rx- at the ninth channel interface 215 represent the ninth receiving channel interface, specifically, Rx+ represents the high-end channel interface of the ninth receiving channel interface, and Rx- represents the low-end channel interface of the ninth receiving channel interface.

[0085] Optionally, the first line 300, the second line 400, the first loop line 500, the second loop line 600 and the third loop line 700 used in this embodiment are all SIB buses. The System Internal Bus (SIB) is a standard bus protocol of a large domestic passenger aircraft, which uses heartbeat words, cyclic redundancy checks, etc. to ensure the reliability of bus data transmission.

[0086] It should be noted that the reference Figure 1 As shown in the figure, Tx+ and Rx+ in the figure can be understood as the high-end channel interface of the high-end signal of the SIB bus in terms of interface characteristics, and Tx- and Rx- in the figure can be understood as the low-end channel interface of the low-end signal of the SIB bus in terms of interface characteristics.

[0087] It should also be noted that the flight control module 210 and the auxiliary control module 220 in this embodiment are both equipped with functional units such as a control unit, a signal processing unit, a solution unit and a storage unit to perform corresponding processing on the signal.

[0088] Furthermore, in this exemplary embodiment, an identification test method is also provided to verify the above-mentioned redundant primary flight control equivalent system. Figure 3 As shown in , the identification test method includes:

[0089] Step S101: setting an initialization scene so that the redundant main flight control equivalent system starts in the air;

[0090] Step S102: the redundant main flight control equivalent system receives the external test signal, and performs equivalent wrapping processing on the external test signal to obtain a signal to be verified;

[0091] Step S103: performing system redundancy signal integrity confirmation on the signal to be verified;

[0092] Step S104: The signal to be verified is solved and processed by the redundant main flight control equivalent system to obtain the control instruction to be verified, and confirm whether the control instruction to be verified is correct.

[0093] In the embodiments of the present application, on the one hand, by first performing an initialization scene setting, and in the initialization scene setting, the redundant main flight control equivalent system is started in the air, so that the redundant main flight control equivalent system will determine that the aircraft is in the air according to the initialization scene setting, and therefore no longer performs the power-on self-detection, that is, the channel numbers of the control machine 100 and the auxiliary control module 220 are no longer detected and the validity is checked, which effectively avoids the channel number conflict problem of electronic equipment caused by the ground power-on initialization process; on the other hand, the system redundancy signal integrity is confirmed by confirming the signal to be verified after the equivalent wrapping processing of the redundant main flight control equivalent system to verify whether the redundancy signal of the equivalent system is complete, and the control instruction to be verified obtained by solving the redundant main flight control equivalent system is confirmed to identify whether the control function of the equivalent system is complete.

[0094] Next, the above-mentioned identification test method in this exemplary embodiment will be described in more detail.

[0095] Before discussing the identification test method provided in this embodiment, the necessity of the identification test method is first explained. Civil aircraft are required to carry out compliance tests for transport aircraft airworthiness standards. The identification test is an equipment identification test that indicates the qualification of the equipment. When indicating the working characteristics of airborne equipment in extreme environments such as electromagnetic environment and lightning, it must be carried out in a system environment. Component-level tests cannot reflect the load-carrying operating characteristics of each device, and cannot verify the degree to which cross-linked equipment can withstand mutual interference. The redundant main flight control equivalent system provided in this application is used as the test object to carry out equipment identification tests to verify the equipment qualification of the redundant main flight control equivalent system.

[0096] In one embodiment, before the redundant primary flight control equivalent system receives the external test signal, the following steps are further included:

[0097] Simulate external test signals, which include cockpit signals and sensor signals.

[0098] The above-mentioned step of simulating external test signals can ensure the normal operation of the redundant main flight control equivalent system. In this embodiment, a simulation device is used to simulate external test signals, wherein cockpit signals may include but are not limited to cockpit signals such as rods, plates, and pedals, and sensor acquisition signals may include but are not limited to sensor signals such as atmosphere, inertial navigation, and heading attitude.

[0099] In one embodiment, the redundant main flight control equivalent system receives an external test signal, and performs equivalent wrapping processing on the external test signal to obtain a signal to be verified, including the following steps:

[0100] Step S1021: the control machine 100 and the auxiliary control module 220 receive an external test signal;

[0101] Step S1022: the control machine 100 and the auxiliary control module 220 respectively rewind the external test signal and transmit it to the flight control module 210;

[0102] Step S1023: the flight control module 210 self-rewinds the external test signal to obtain multiple channels of signals to be verified.

[0103] The above steps S1022 and S1023 are used to wrap the received external test signal to produce an equivalent test environment for the complete main flight control system; and the obtained signal to be verified is verified through subsequent steps S103 and S104, which proves that the redundant main flight control equivalent system can produce an equivalent test environment for the complete main flight control system.

[0104] In order to more clearly understand how to use the redundant main flight control equivalent system to wrap the external test signal to equivalently produce a test environment for a complete main flight control system, an embodiment is given below to illustrate the specific equivalent wrapping process in step S102.

[0105] The fifth channel interface 111 and the sixth channel interface 112 of the control machine 100 receive two cockpit signals, and the sixth channel interface 112 of the control machine 100 transmits one of the cockpit signals to the seventh channel interface 214 of the flight control module 210 using the first line 300, and the fifth channel interface 111 of the control machine 100 transmits the other cockpit signal to the fourth channel interface 213 of the flight control module 210 using the second loop line 600; thus equivalently outputting the following Figure 2 As shown in the figure, the first control machine and the second control machine are used to respectively receive corresponding cockpit signals, and respectively transmit the received cockpit signals to the test environment of the first flight control module and the second flight control module accordingly.

[0106] The second channel interface 221 and the eighth channel interface 222 of the auxiliary control module 220 receive two cockpit signals. The eighth channel interface 222 of the auxiliary control module 220 transmits one of the cockpit signals to the ninth channel interface 215 of the flight control module 210 using the second line 400, and the third channel interface 221 of the auxiliary control module 220 transmits the other cockpit signal to the second channel interface 212 of the flight control module 210 using the third loop line 700; thus equivalently outputting the following Figure 2As shown in the figure, the first auxiliary control module and the second auxiliary control module are used to respectively receive corresponding cockpit signals, and the cockpit signals received by each are correspondingly transmitted to the test environment of the first flight control module and the second flight control module.

[0107] Finally, the flight control module 210 uses the first channel interface 211 to self-rewind the received cockpit signal, that is, from the first sending channel interface of the first channel interface 211 to the first receiving channel interface via the first rewind line 500, 8 channels of signals to be verified can be obtained; thus equivalently outputting Figure 2 The test environment for cockpit signal transmission between the first flight control module and the second flight control module shown in FIG.

[0108] Specifically, the following Table 1 shows the test data of the complete main flight control system of the prior art during the system integrity check, and Table 2 shows the test data of the redundant main flight control equivalent system of the present application during the system integrity check, so as to verify that the redundant main flight control equivalent system proposed in the present application can be equivalent to the multi-channel signal that is the same as the complete main flight control system of the prior art and has no redundancy loss. It should be noted that capt_col_posn1_vld, capt_col_posn2_vld, capt_col_posn3_vld, and capt_col_posn4_vld in Table 1 and Table 2 respectively represent 4 main control stick signal inputs, and fo_col_posn1_vld, fo_col_posn2_vld, fo_col_posn3_vld, and fo_col_posn4_vld respectively represent 4 co-control stick signal inputs; when any control stick signal is lost, the system integrity check will declare the control stick signal as invalid, that is, 0-invalid is indicated at the position corresponding to the signal column capt_col_posnX_vld.

[0109] Table 1 Control stick signals of a complete set of primary flight control systems in the prior art

[0110]

[0111] Table 2 Control stick signals of the redundant primary flight control equivalent system of this application

[0112]

[0113] By comparing the data in Table 1 and Table 2, it can be seen that the two are completely consistent, indicating that the redundant main flight control equivalent system proposed in this application has equivalently wound out 8 control stick signal inputs that are the same as the full set of main flight control systems in the prior art, including 4 main control stick signal inputs and 4 co-control stick signal inputs, and in the system integrity check, all of these 8 control stick signals are declared as 1-Valid, indicating that the control stick signals equivalently wound out by the redundant main flight control equivalent system of this application have no redundancy loss, and all control stick signals are valid. In this way, it can be confirmed that the system redundancy signal integrity in step S103 meets the requirements.

[0114] Specifically, in step S104, the flight control module 210 of the redundant primary flight control equivalent system solves the multiple signals to be verified obtained by the wraparound in step S1023 to verify whether the control instruction to be verified is correct. For example, when the cockpit stick position is at zero and the flight control system maintains the initialization scene, if the control instruction of the rudder surface solved by the flight control module 210 of the redundant primary flight control equivalent system is zero, and in this test scene, the control instruction of the rudder surface solved by the full set of primary flight control systems is also zero, then it is determined that the control instruction to be verified is correct, otherwise the control instruction to be verified is wrong.

[0115] Specifically, the following Table 3 shows a complete set of main flight control system control instructions of the prior art, and Table 4 shows the redundant main flight control equivalent system control instructions of the present application.

[0116] Table 3 Control instructions of a complete set of main flight control systems in the prior art

[0117]

[0118] Table 4 Control instructions of the redundant main flight control equivalent system of this application

[0119]

[0120] It can be seen from Tables 3 and 4 above that, taking the left outer elevator actuator control command, the right outer aileron actuator control command, the upper rudder actuator control command, the left inner spoiler actuator control command, the right inner spoiler actuator control command, the right outer elevator actuator control command and the left outer aileron actuator control command as examples, the control command obtained by the redundant main flight control equivalent system of the present application for solving the multiple signals to be verified is basically consistent with the control command obtained by the full set of main flight control systems in the prior art for solving the multiple actuator signals, and the error is within ±2. It can be considered that the redundant main flight control equivalent system of the present application is basically consistent with the full set of main flight control systems in the prior art.

[0121] The above step S104 verifies that the control instruction to be verified is correct, which indicates that the redundant main flight control equivalent system realizes the same working mode as the full set of main flight control systems, and the redundant main flight control equivalent system has the same working characteristics as the full set of main flight control systems. On the one hand, the system input signal is complete, especially the redundant external sensor signal collected by the system, and there is no loss of redundancy and failure in the equivalent system; on the other hand, the system control function is complete, including the system working mode, system working state or system control instruction, which are completely consistent with the full set of main flight control systems, without control logic errors and reduction of control performance.

[0122] In one embodiment, the redundant main flight control equivalent system receives an external test signal, performs wraparound processing on the external test signal, and after obtaining a signal to be verified, further comprises the following steps:

[0123] The flight control module 210 monitors the signal to be verified;

[0124] Check whether the signal to be verified has any fault.

[0125] The flight control module 210 can use its built-in monitor to monitor multiple channels of to-be-verified signals in the flight control module 210 in real time, and perform fault diagnosis on the to-be-verified signals. For example, the effectiveness of the redundant main flight control equivalent system can be further identified by detecting whether there is a latch fault in the to-be-verified signals. Of course, other types of fault diagnosis can also be performed on the monitored to-be-verified signals according to different identification test requirements.

[0126] It should be explained that a latching fault generally refers to a fault in the system where the system cannot work normally due to some reason and enters a locked state.

[0127] It should be noted that the redundant main flight control equivalent system is identified by the identification test method provided in this embodiment, and the redundant main flight control equivalent system that meets the identification standards such as system redundancy signal integrity, complete system control function and fault-free monitoring can be used for formal testing. The formal test process can be explained by the following simple example: first, an external interference signal, such as an electromagnetic interference signal or a lightning interference signal, is applied to the redundant main flight control equivalent system; then, the output signal after the redundancy main flight control equivalent system is wrapped and resolved is collected, and a jitter judgment is performed on the output signal; the anti-disturbance capability of the airborne equipment is confirmed by the jitter judgment. Of course, other aspects of the output signal of the redundant main flight control equivalent system can also be judged to characterize other performances of the airborne equipment.

[0128] Those skilled in the art will readily appreciate other embodiments of the present application after considering the specification and practicing the invention disclosed herein. The present application is intended to cover any modification, use or adaptation of the present application, which follows the general principles of the present application and includes common knowledge or customary technical means in the art that are not disclosed in the present application.

Claims

1. A redundant primary flight control equivalent system, characterized in that: The redundant main flight control equivalent system includes a control machine and a flight control computer, the flight control computer includes a flight control module and an auxiliary control module, the control machine and the auxiliary control module are used to receive external signals, and the flight control module is used to process the external signals; wherein, The flight control module is connected to the control machine via a first line, and the flight control module is connected to the auxiliary control module via a second line; The flight control module is connected to itself by a first winding line, the control machine and the flight control module are connected to each other by a second winding line, and the auxiliary control module and the flight control module are connected to each other by a third winding line; The flight control module is provided with a first channel interface, the first channel interface includes a first sending channel interface and a first receiving channel interface, and the first loop line connects the first sending channel interface and the first receiving channel interface; The flight control module is provided with a second channel interface, the second channel interface includes a second sending channel interface and a second receiving channel interface, the auxiliary control module is provided with a third channel interface, the third channel interface includes a third sending channel interface and a third receiving channel interface; wherein, The third loop circuit is provided with two groups, one group of the third loop circuit is connected to the second sending channel interface and the third receiving channel interface, and the other group of the third loop circuit is connected to the third sending channel interface and the second receiving channel interface; The flight control module is provided with a fourth channel interface, the fourth channel interface includes a fourth sending channel interface and a fourth receiving channel interface, the control machine is provided with a fifth channel interface, the fifth channel interface includes a fifth sending channel interface and a fifth receiving channel interface; wherein, Two groups of the second loop lines are provided, one group of the second loop lines connects the fourth sending channel interface and the fifth receiving channel interface, and the other group of the second loop lines connects the fifth sending channel interface and the fourth receiving channel interface.

2. The redundant primary flight control equivalent system according to claim 1, characterized in that: The first transmission channel interface and the first reception channel interface both include a high-end channel interface and a low-end channel interface, and the first loop circuit includes a high-end channel loop circuit and a low-end channel loop circuit; wherein, The high-end channel wraparound line connects the high-end channel interface of the first sending channel interface and the high-end channel interface of the first receiving channel interface, and the low-end channel wraparound line connects the low-end channel interface of the first sending channel interface and the low-end channel interface of the first receiving channel interface.

3. The redundant primary flight control equivalent system according to claim 1, characterized in that: The first line, the second line, the first wraparound line, the second wraparound line, and the third wraparound line are all SIB buses.

4. An identification test method for verifying the redundant primary flight control equivalent system according to any one of claims 1 to 3, characterized in that: The identification test method comprises: Set the initialization scenario so that the redundant main flight control equivalent system can be started in the air; The redundant main flight control equivalent system receives an external test signal, and performs equivalent wrapping processing on the external test signal to obtain a signal to be verified; Performing system redundancy signal integrity confirmation on the signal to be verified; The redundant main flight control equivalent system is used to solve the signal to be verified to obtain the control instruction to be verified, and confirm whether the control instruction to be verified is correct; The redundant main flight control equivalent system receives an external test signal, and performs equivalent wrapping processing on the external test signal to obtain a signal to be verified, including: The control machine and the auxiliary control module receive the external test signal; The control machine and the auxiliary control module respectively rewind the external test signal and transmit it to the flight control module; The fifth channel interface and the sixth channel interface of the control machine receive two external test signals, the sixth channel interface of the control machine transmits one of the external test signals to the seventh channel interface of the flight control module by using the first line, and the fifth channel interface of the control machine transmits the other external test signal to the fourth channel interface of the flight control module by using the second loop line; The third channel interface and the eighth channel interface of the auxiliary control module receive two external test signals, the eighth channel interface of the auxiliary control module transmits one of the external test signals to the ninth channel interface of the flight control module by using the second line, and the third channel interface of the auxiliary control module transmits the other external test signal to the second channel interface of the flight control module by using the third loop line; The flight control module self-rewinds the external test signal to obtain multiple channels of the to-be-verified signals.

5. The identification test method according to claim 4, characterized in that: The redundant main flight control equivalent system receives an external test signal, performs equivalent wrapping processing on the external test signal, and obtains a signal to be verified, further comprising: Monitoring the signal to be verified by the flight control module; Confirm whether the signal to be verified has any fault.

6. The identification test method according to claim 4, characterized in that: Before the redundant main flight control equivalent system receives the external test signal, it also includes: The external test signal is simulated, wherein the external test signal includes an external test signal and a sensor signal.

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