Landing gear position indication system and indication method

Abstract

The present invention discloses a landing gear position indication system and indication method, which obtains signals collected by multiple position sensors at various parts of the landing gear; performs an OR operation on the analog-to-digital converted signals of the position sensors located at the same part of the landing gear to obtain a first indication result; and / or performs an AND operation on the analog-to-digital converted signals of the position sensors located at different parts of the landing gear to obtain a second indication result. The lower position indication result of the landing gear related to the safety type I failure event is connected to the indicator light box and displayed through a hard wire, and the landing gear position indication result is connected to the integrated indicator through a bus and displayed. The present invention meets the requirements of independence while realizing the redundancy function, and has the characteristics of simple system architecture, high reliability and high safety, providing a strong guarantee for the accurate landing gear position indication and the flight safety of the aircraft.

Description

Technical Field

[0001] The present invention relates to the field of aircraft landing gear, and in particular to a landing gear position indicating system and indicating method. Background Art

[0002] To ensure flight safety and enhance the proper functioning of the landing gear system, providing pilots with timely and effective information on the landing gear's position and status to ensure safe flight and landing has become a key design requirement for landing gear control systems. To ensure real-time and accurate landing gear position indication, approaches such as hardware redundancy, homologous position and status calculation, and independent hardware and software design and verification by multiple teams are often employed. These approaches often result in complex system functional design and device interconnections, resulting in significant and difficult post-integration verification workload and high development costs. The higher safety requirements of civil aircraft, in particular, necessitate a simpler, highly secure, reliable, and functionally independent position indication device. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to provide a landing gear position indication system and an indication method in view of the deficiencies in the existing technology, so as to improve the reliability and accuracy of the indication system.

[0004] To solve the above technical problems, the technical solution adopted by the present invention is: a landing gear position indication system, comprising:

[0005] Two sets of position sensors, the first set of position sensors and the second set of position sensors each include a plurality of down-lock sensors for detecting safety Category I failure events; the first set of position sensors and the second set of position sensors also include a plurality of up-lock sensors and wheel load sensors;

[0006] a first solving unit, configured to perform comprehensive calculations on signals collected by the first and second position sensors to obtain landing gear position indication information, and share the first position sensor information with the second solving unit;

[0007] a second solving unit, configured to perform comprehensive calculations on the signals collected by the first and second position sensors to obtain landing gear position indication information, and share the second position sensor information with the first solving unit;

[0008] The comprehensive operation implementation process includes:

[0009] Performing a parity OR operation on the analog-to-digital converted signals of position sensors located at the same location of the landing gear; and / or,

[0010] Perform out-of-place AND operations on the analog-to-digital converted signals of position sensors located at different parts of the landing gear.

[0011] The present invention's indication system has a simple structure, does not involve complex hardware structures, and does not require complex position state homology solutions. This solves the problems of the prior art, such as complex functions, complex equipment interconnections, complex signal homology solutions, difficult integration verification, and high development costs. While achieving redundancy, the present invention also meets the requirements of independence. It also features a simple system architecture, high reliability, and high safety, providing a strong guarantee for accurate landing gear position indication and aircraft flight safety.

[0012] In the present invention, in order to facilitate the indication of information, the first solution unit is connected to the indicator light box via a hard line.

[0013] In the present invention, in order to facilitate indication of information, the first solution unit and the second solution unit are both connected to the comprehensive indicator via a bus.

[0014] In the present invention, the first solving unit is further used to perform analog-to-digital conversion on the signal collected by the down-lock sensor in the first group of position sensors, and perform a logical AND operation on the converted signal.

[0015] In the present invention, the first solving unit transmits the result of the logic AND operation to the indicator light box.

[0016] In the present invention, the down-lock sensor in the first group of position sensors is connected to the analog-to-digital conversion circuit in the first solution unit through a gating module.

[0017] In the present invention, the down-lock sensor in the second group of position sensors is connected to the analog-to-digital conversion circuit in the second resolution unit via a gating module.

[0018] The gating module can be used to transmit sensor signals to different circuits, so that different solutions can be performed on the sensor signals according to business needs. The gating module can be a transfer switch.

[0019] The present invention also provides a landing gear position indication method, which comprises the following steps:

[0020] Acquire signals collected by multiple position sensors at various parts of the landing gear;

[0021] performing an OR operation on analog-to-digital converted signals of position sensors located at the same portion of the landing gear to obtain a first indication result; and / or,

[0022] An AND operation is performed on analog-to-digital converted signals of position sensors located at different positions of the landing gear to obtain a second indication result.

[0023] In the present invention, different logical operations can be selected according to actual needs. For example, an OR operation can be selected according to actual needs, an AND operation can be selected according to needs, or a combination of an OR operation and an AND operation can be selected according to needs.

[0024] In the present invention, at least two position sensors are installed at each part of the landing gear.

[0025] The method of the present invention further includes: issuing indication information according to the first indication result and / or the second indication result.

[0026] Compared with the existing technology, the beneficial effects of the present invention are: the present invention meets the requirements of independence while realizing redundant functions, and has the characteristics of simple system architecture, high reliability and high safety, providing strong guarantees for accurate landing gear position indication and aircraft flight safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a block diagram of the overall architecture and indication logic principle of an embodiment of the present invention. DETAILED DESCRIPTION

[0028] To make the objectives, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts shall fall within the scope of protection of the present invention.

[0029] In this document, the terms "first", "second" and other similar words are not intended to imply any order, quantity and importance, but are merely used to distinguish different elements. In this document, the terms "one", "an" and other similar words are not intended to indicate that there is only one of the things described, but rather that the relevant description is only for one of the things described, and the things described may have one or more. In this document, the terms "comprise", "include" and other similar words are intended to indicate logical relationships, and cannot be regarded as indicating relationships in spatial structure. For example, "A includes B" is intended to indicate that B logically belongs to A, and does not mean that B is spatially located inside A. In addition, the meanings of the terms "comprise", "include" and other similar words should be regarded as open, not closed. For example, "A includes B" is intended to indicate that B belongs to A, but B does not necessarily constitute the whole of A, and A may also include other elements such as C, D, and E.

[0030] Example 1

[0031] Embodiment 1 of the present invention provides a landing gear position indication system, comprising two solution units, two sets of position sensors, one indicator light box, and one integrated indicator. The two solution units and two sets of position sensors constitute dual redundancy of position signal input and independent analysis and synthesis, the one indicator light box and one integrated indicator constitute dual redundancy of independent channel output of indication information, and the dual redundancy of position signal input and independent analysis and synthesis, and the dual redundancy of independent channel output of indication information constitute an independent non-similar indication architecture. Among them:

[0032] 1) The two solver units are physically identical, forming a dual-redundancy analytical synthesis architecture. They are dynamically identified as solver unit 1 and solver unit 2 according to their installation locations. The core modules within the solver units include sensor signal hardware acquisition and solver circuits, sensor signal hardware synthesis circuits, sensor signal analog-to-digital converters (ADCs), microprocessors, bus circuits, and embedded software.

[0033] 2) Two groups of position sensors are identical inductive proximity sensors, grouped as sensor 1x and sensor 2x, forming a dual-redundancy architecture for position signal input. Based on the different locations where the sensors are installed in the upper and lower lock mechanisms of the front / main landing gear actuators, wheel mechanisms, and their respective representations of the upper and lower locks of the front / main landing gear, the wheels touching the ground, and other states, the sensors are divided into upper lock sensors, lower lock sensors, wheel load sensors, and other categories. In order to achieve the position indication Class A function with an unannounced landing gear failure rate of 1E-9, the lower lock sensors that affect safety Class I failure events are designated as position sensor 1x.dg and position sensor 2x.dg, and the remaining upper lock sensors and wheel load sensors are designated as position sensor 1x.og and position sensor 2x.og;

[0034] 3) The indicator light box and the integrated indicator are completely physically independent and non-similar, and use signal lights and graphics as information output methods respectively, forming a dual-redundancy architecture for indicator signal output.

[0035] ① The indicator light box is an analog signal receiving device that provides indicators for upper position, lower position, and non-position or inconsistent status. Non-position indicates that the landing gear is in the process of retraction or extension or has timed out, while inconsistent status indicates that the calculated signals of position sensor 1x.dg and position sensor 2x.dg are inconsistent, serving as a reminder and warning.

[0036] ② The integrated indicator is a bus digital signal receiving device that outputs the bus digital signal (such as ARINC429) in a graphical manner.

[0037] The logical function principle is as follows:

[0038] 1) The hardware circuit and software functional modules of the solution unit realize independent analysis and synthesis of position signals, ensuring the independent and non-similar sources of position indication information. Among them:

[0039] ① The hardware circuit outputs an indication analog signal. The main working principle is as follows: the sensor signal acquisition and resolution hardware circuit of the resolution unit 1 independently realizes the signal acquisition and resolution of the position sensor 1x.dg. After the sensor signal hardware integrated circuit performs a logical AND operation on the sensor signals of different positions, it directly outputs an indication analog signal to the indicator light box, and at the same time sends the resolved sensor signal to the microprocessor; the sensor signal hardware acquisition and resolution are mainly realized by the ADC circuit and the signal resolution GF161 dedicated chip (or similar chip) circuit, and the sensor signal hardware integrated circuit is mainly realized by the logic AND gate circuit;

[0040] ②The software function module outputs the digital signal indicating the bus. The main working principle is:

[0041] The microprocessor of the solution unit 1 schedules the sensor signal analog-to-digital conversion ADC to perform analog-to-digital conversion on the position sensor 1x.og, and performs a comprehensive operation on the position sensor 1x.og solution signal output by the hardware circuit, the position sensor 2x.og and the solution signal of the position sensor 2x.og shared by the solution unit 2, etc. The embedded software of the microprocessor performs a comprehensive operation according to the different installation positions of the actual sensors and the redundancy relationship formed therefrom, using the logical calculation method of out-of-position and between the redundancy sensors at different positions and using the logical calculation method of parity or between the redundancy sensors at the same position, to obtain the landing gear position indication information, output the indication bus digital signal through the bus circuit, and at the same time share the solution signals of the position sensor 1x.dg and the position sensor 1x.og with the solution unit 2 through the internal bus (such as ARINC429);

[0042] In the embodiment of the present invention, a comprehensive operation is performed by adopting a logical calculation method of out-of-position AND between redundancy sensors at different positions and a logical calculation method of parity OR between sensors at the same position. The specific process of obtaining the landing gear position indication information is as follows:

[0043] Take the left main start-down position indication signal as an example:

[0044] 1. Logical OR operation of the redundancy sensors at the same position (i.e., parity OR): perform logical OR operation on the left main start-up and down-to-position sensor 1 signal and the left main start-up and down-to-position sensor 2 signal;

[0045] 2. Logical OR operation of the redundancy sensors at the same position (i.e., parity OR): Logical OR operation of the left master down lock sensor 1 signal and the left master down lock sensor 2 signal;

[0046] 3. Logical AND operation of redundancy sensors at different positions (i.e., out-of-position AND): Perform a logical AND operation on the results of steps 1 and 2, and the result is the left main start-down position indication signal.

[0047] The microprocessor of the solver unit 2 schedules the ADC to realize analog-to-digital conversion of the position sensors 2x.dg and 2x.og, and the solution signals of the position sensors 1x.dg and 1x.og shared by the solver unit 1 are integrated by the embedded software of the microprocessor according to the different installation positions of the actual sensors and the redundancy relationship formed therefrom, with the redundancy sensors at different positions adopting the logic calculation method of out-of-position and and the redundancy sensors at the same position adopting the logic calculation method of in-position or, to obtain the landing gear position indication information, and output the indication bus digital signal through the bus circuit. At the same time, the solution signals of the position sensors 2x.dg and 2x.og are shared with the solver unit 1 through the internal bus (such as ARINC429), and its hardware solver circuit and hardware integrated circuit are both in an inactive state.

[0048] 2) The indicator light box outputs the indication analog signal of the solution unit 1 through a signal light;

[0049] 3) The integrated indicator graphically outputs the received indication bus digital signal. The integrated indicator receives the indication bus digital signals output by both solver unit 1 and solver unit 2. By default, it displays the indication bus digital signal of solver unit 1 and can seamlessly switch to display the indication bus digital signal of solver unit 2.

[0050] Example 2

[0051] Embodiment 2 of the present invention provides an indication method corresponding to the above-mentioned embodiment 1, the method comprising:

[0052] Acquire signals collected by multiple position sensors at various parts of the landing gear;

[0053] In the embodiment of the present invention, at least two position sensors are installed at each position of the landing gear.

[0054] performing an OR operation on analog-to-digital converted signals of position sensors located at the same portion of the landing gear to obtain a first indication result; and / or,

[0055] An AND operation is performed on analog-to-digital converted signals of position sensors located at different positions of the landing gear to obtain a second indication result.

[0056] In the embodiment of the present invention, different logical operations can be selected according to actual needs, and the OR operation and the AND operation can be used in combination or separately.

[0057] The embodiment of the present invention further issues indication information according to the first indication result and / or the second indication result.

[0058] Example 3

[0059] Embodiment 3 of the present invention provides a terminal device corresponding to the above embodiment 2. The terminal device can be a processing device for a client, such as a mobile phone, a laptop computer, a tablet computer, a desktop computer, etc., to execute the method of the above embodiment.

[0060] The terminal device of this embodiment includes a memory, a processor, and a computer program stored in the memory; the processor executes the computer program in the memory to implement the steps of the method in the above-mentioned embodiment 1.

[0061] In some implementations, the memory may be a high-speed random access memory (RAM), and may also include a non-volatile memory, such as at least one disk storage.

[0062] In other implementations, the processor may be a central processing unit (CPU), a digital signal processor (DSP), or other general-purpose processors, which are not limited here.

[0063] Example 4

[0064] Embodiment 4 of the present invention provides a computer-readable storage medium corresponding to the above embodiment 2, on which a computer program / instruction is stored. When the computer program / instruction is executed by a processor, the steps of the method of embodiment 1 are implemented.

[0065] Computer readable storage media can be tangible devices that hold and store instructions used by instruction execution devices. Computer readable storage media can be, for example, but not limited to, electronic storage devices, magnetic storage devices, optical storage devices, electromagnetic storage devices, semiconductor storage devices, or any combination thereof.

[0066] Those skilled in the art will appreciate that the embodiments of the present application can be provided as methods, systems, or computer program products. Therefore, the application can adopt the form of a complete hardware embodiment, a complete software embodiment, or an embodiment in combination with software and hardware. Moreover, the application can adopt the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) that contain computer-usable program code. The scheme in the embodiment of the present application can be implemented in various computer languages, for example, object-oriented programming language Java and literal translation scripting language JavaScript, etc.

[0067] The present application is described with reference to the flowcharts and / or block diagrams of the methods, devices (systems), and computer program products according to the embodiments of the present application. It should be understood that each process and / or box in the flowchart and / or block diagram, as well as the combination of the processes and / or boxes in the flowchart and / or block diagram, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing device to produce a machine, so that the instructions executed by the processor of the computer or other programmable data processing device generate instructions for implementing the steps in the process. Figure 1 a process or multiple processes and / or boxes Figure 1 A device that provides the functions specified in a block or multiple blocks.

[0068] These computer program instructions can also be loaded onto a computer or other programmable data processing device so that a series of operational steps are executed on the computer or other programmable device to produce a computer-implemented process, thereby providing the instructions executed on the computer or other programmable device for implementing the process. Figure 1 a process or multiple processes and / or boxes Figure 1 A step that specifies a function in one or more boxes.

[0069] Although the preferred embodiments of the present application have been described, those skilled in the art may make additional changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the present application.

[0070] Obviously, those skilled in the art may make various changes and modifications to this application without departing from the spirit and scope of this application. Thus, if these modifications and variations of this application fall within the scope of the claims of this application and their equivalents, this application is intended to include these modifications and variations.

Claims

1. A landing gear position indication system, characterized in that: include: Two sets of position sensors, the first set of position sensors and the second set of position sensors each include a plurality of down-lock sensors for detecting a Class I failure event; the first set of position sensors and the second set of position sensors also include a plurality of up-lock sensors and wheel load sensors; a first solving unit, configured to perform comprehensive calculations on signals collected by the first and second position sensors to obtain landing gear position indication information, and share the first position sensor information with the second solving unit; a second solving unit, configured to perform comprehensive calculations on the signals collected by the first and second position sensors to obtain landing gear position indication information, and share the second position sensor information with the first solving unit; The comprehensive operation implementation process includes: Performing a parity OR operation on the analog-to-digital converted signals of position sensors located at the same location of the landing gear; and / or, Perform out-of-place AND operations on the analog-to-digital converted signals of position sensors located at different parts of the landing gear.

2. The landing gear position indication system according to claim 1, characterized in that: The first solving unit is connected to the indicator light box via a hard line.

3. The landing gear position indication system according to claim 1, characterized in that: The first solving unit and the second solving unit are both connected to the comprehensive indicator via a bus.

4. The landing gear position indication system according to claim 1, characterized in that: The down-lock sensor in the first group of position sensors is connected to the analog-to-digital conversion circuit in the first resolution unit through the gating module.

5. The landing gear position indication system according to claim 1, characterized in that: The analog-to-digital conversion circuit of the first solution unit performs analog-to-digital conversion on the down-lock sensor signals in the first group of position sensors, and performs a logic AND operation on the converted signals.

6. The landing gear position indication system according to claim 5, characterized in that: The first solving unit transmits the result of the logic AND operation to the indicator light box.

7. A landing gear position indication method, characterized in that: The following steps are involved: Acquire signals collected by multiple position sensors at various parts of the landing gear; performing an OR operation on analog-to-digital converted signals of position sensors located at the same portion of the landing gear to obtain a first indication result; and / or, An AND operation is performed on analog-to-digital converted signals of position sensors located at different positions of the landing gear to obtain a second indication result.

8. The landing gear position indication method according to claim 7, characterized in that: At least two position sensors are installed at each part of the landing gear.

9. The landing gear position indication method according to claim 7, characterized in that: Also includes: Instruction information is issued according to the first instruction result and / or the second instruction result.

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