A redundancy voting method for wheel bearing signals

Abstract

This invention belongs to the field of aircraft technology and relates to a redundancy voting method for wheel load signals. By employing a reliable redundancy voting method, the classical majority monitoring voting method cannot effectively identify single-wheel contact during the landing phase, enabling the wheel load signals to accurately represent the aircraft's flight status. This ensures that the pilot can precisely control the aircraft's attitude, facilitating a safe landing.

Description

Technical Field

[0001] This invention belongs to the field of aviation aircraft technology and relates to a redundancy voting method for wheel-borne signals. Background Technology

[0002] In aircraft design, the wheel load signal serves as a status signal indicating the aircraft's flight phase (ground taxiing, in-flight), and is typically used as an on / off indicator for the longitudinal integrator in the control law. It is generally configured with a mechanical dual-redundancy and an electrical quadruple-redundancy system, consisting of a left main wheel load switch and a right main wheel load switch. This signal is monitored and voted on using the classic discrete signal monitoring and voting method (majority monitoring and voting method).

[0003] During landing or go-around training, crosswinds or pilot inexperience can easily lead to one main engine wheel touching the ground. In this situation, the classic majority monitoring voting method determines that the left / right main engine wheel states are inconsistent, i.e., a singular fault. The fail-safe value is set to "load," the control law disconnects the longitudinal integrator, and neutral speed stability is lost. If the aircraft goes around, the pilot will have to operate according to positive speed stability, increasing the pilot's control workload, especially making it difficult to control the aircraft's attitude during landing. Summary of the Invention

[0004] Purpose of the invention

[0005] This invention designs a redundancy monitoring and voting method for wheel load signals, which can effectively identify the ground contact landing situation with a single main main wheel during the landing phase, and can also promptly vote on a method that can indicate the actual flight phase of the aircraft.

[0006] Technical Solution

[0007] A redundancy voting method for wheel bearing signals includes the following steps:

[0008] Step 1: When the landing gear signal is normal, if the landing gear is retracted, regardless of whether the left / right wheel load collection value is "loaded" or "not loaded", the wheel load voting value will be "not loaded".

[0009] Step 2, if the landing gear is deployed when the landing gear signal is normal:

[0010] When all the load-bearing values ​​of the quadruple-redundant wheels are valid, the load-bearing values ​​of the left and right wheels are added together, and the possible results are 4, 3, 2, 1, and 0.

[0011] When the sum of the collected values ​​is 4 or 0, the wheel bearing capacity voting value is obtained by majority vote of the left / right wheel bearing capacity collected values;

[0012] When the sum of the collected values ​​is 3 or 1, the wheel load voting value is obtained by the majority vote of the left / right wheel load collected values. After time t, the channel that is inconsistent with the majority channel collected values ​​is isolated, and the process proceeds to the judgment of the validity of the triple redundancy collected values.

[0013] When the sum of the collected values ​​is 2, the wheel load-bearing value is determined by the airspeed. If the airspeed is <X km / h, the load-bearing value is taken; otherwise, the no-load value is taken.

[0014] Furthermore, when the load-bearing values ​​of the triple-redundant wheels are valid, the load-bearing values ​​of the left and right wheels are added together, and the possible results are 3, 2, 1, and 0.

[0015] When the sum of the collected values ​​is 3 or 0, the wheel bearing capacity voting value is obtained by majority vote of the left / right wheel bearing capacity collected values;

[0016] When the sum of the collected values ​​is 2, if the left (or right) wheel load voting value corresponding to the normal channel is 1, then the wheel load voting value is "loaded". After time t, the channel with inconsistent collected values ​​with the majority channel is isolated, and the process proceeds to the judgment of the validity of the dual-redundancy collected values. If the left (or right) wheel load voting value is 2, then the wheel load voting value is determined by the airspeed. If the airspeed is <X km / h, the wheel load is taken; otherwise, the wheel load is not taken.

[0017] When the sum of the collected values ​​is 1, the wheel load voting value is determined by the airspeed. If the airspeed is <X km / h, the load is taken; otherwise, the load is not taken. After time t, the channel corresponding to the collected value of 1 is isolated, and the process is switched to the judgment of the validity of the dual-redundancy collected values.

[0018] Furthermore, when the load-bearing values ​​of the dual-redundant wheels are valid, if the valid load-bearing values ​​are from the same wheel (left or right wheel), the load-bearing value is determined by the airspeed. If the airspeed is < X km / h, the load is taken; otherwise, no load is taken. If the valid load-bearing values ​​are from different wheels, the valid values ​​of the left and right wheels are added together, and the possible results are 2, 1, and 0.

[0019] When the sum of the collected values ​​is 2 or 0, the wheel bearing capacity voting value is obtained by majority vote of the left / right wheel bearing capacity collected values;

[0020] When the sum of the collected values ​​is 1, the load-bearing collected values ​​of the left / right wheels are set to fault. The wheel load-bearing voting value is determined by the airspeed. If the airspeed is <X km / h, the load-bearing value is taken; otherwise, the no-load value is taken.

[0021] Furthermore, in the event of a landing gear signal failure, based on the landing gear structural strength and the tolerance of the control law parameters, a specific flight altitude and airspeed can be assumed. In this case, the landing gear is lowered; otherwise, the landing gear is retracted. The voting method for the wheel bearing signal is still the same as steps 1 and 2 above.

[0022] Furthermore, the method is applicable to aircraft with a tricycle configuration.

[0023] Furthermore, the tricycle-type aircraft uses the left and right main wheels for logical judgment.

[0024] Furthermore, the method is applicable to the aircraft's landing roll phase.

[0025] Furthermore, the aircraft approach and landing phase specifically refers to the moment when the left and right wheels of the aircraft touch the ground, but before the front wheel has made contact with the ground.

[0026] Furthermore, X is specifically 230-280 km / h. The selection principle for X km / h is based on the minimum touchdown speed at landing calculated from the aircraft's aerodynamic platform, combined with the flight evaluation conducted by the pilot on a ground-based flight quality simulator.

[0027] The beneficial effects of this application are as follows:

[0028] If the landing gear load signal uses the classic majority monitoring and voting method during takeoff and landing, a failure in the landing gear load signal will cause differences in the aircraft's handling characteristics. If the control mode with longitudinal integrator is still used after the main landing gear has landed, the aircraft nose will pitch up during the continuous stick operation. If this cannot be corrected in time, it may lead to flight accidents such as tail strikes or runway overruns.

[0029] The present invention provides a redundancy voting method for wheel load signals, which can effectively solve the problem that the classic majority monitoring voting method cannot effectively identify single-sided wheel contact when a single main wheel touches the ground during the landing phase. This allows the wheel load signals to effectively and accurately represent the flight status of the aircraft, ensuring that the pilot can accurately control the aircraft's attitude and land the aircraft safely. Attached Figure Description

[0030] Figure 1 This is a schematic diagram of the electrical connection between the wheel bearing switch and the flight control computer;

[0031] Figure 2 This is a schematic diagram of the redundancy voting method. Detailed Implementation

[0032] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions in the embodiments of this invention will be described in more detail below. In the examples, the same or similar reference numerals denote the same or similar components or elements having the same or similar functions throughout. The described embodiments are some, but not all, of the embodiments of this invention. The embodiments described below with reference to reference are exemplary and intended to explain this invention, and should not be construed as limiting the invention. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention. The embodiments of this invention will be described in detail below.

[0033] When an aircraft encounters a crosswind greater than 10 m / s during landing, to overcome the crosswind's influence and align with the runway line, it lands with a fixed bank angle. This can easily lead to the left and right main landing gear not touching the ground simultaneously. Consequently, the flight control system receives a 2:2 singular fault in the load signals for the left and right main landing gear, indicating that the left wheel is electrically loaded while the right wheel is electrically unloaded. According to the classic majority voting method, the vote should be the fail-safe value "loaded," causing the control law to disconnect the longitudinal integrator, losing neutral speed stability. After a time t, the load signals for the left and right wheels are isolated, and the landing gear signal is used for judgment: if the landing gear is deployed, it is considered loaded; otherwise, it is unloaded. If the aircraft attempts a go-around, the pilot will need to operate according to positive speed stability, increasing the pilot's workload, especially making it difficult to control the aircraft's attitude during landing.

[0034] ① When the landing gear signal is normal, if the landing gear is retracted, regardless of whether the load collection value of the left / right wheel is "loaded" or "not loaded", the wheel load voting value will be "not loaded";

[0035] ② If the landing gear is deployed when the landing gear signal is normal:

[0036] When all the load-bearing values ​​of the quadruple-redundant wheels are valid, the load-bearing values ​​of the left and right wheels are added together, and the possible results are 4, 3, 2, 1, and 0.

[0037] When the sum of the collected values ​​is 4, 3, 1 or 0, the wheel load voting value is obtained by majority vote of the left / right wheel load collected values, and the fault channel is isolated at this time;

[0038] When the sum of the collected values ​​is 2, the wheel load voting value is determined by the airspeed. If the airspeed is <X km / h, the load is taken; otherwise, the unloaded value is taken. In this case, no channel isolation is performed.

[0039] When the load-bearing capacity of the triple-redundant wheel is valid, the load-bearing capacity of the left and right wheels is added together, and the possible results are 3, 2, 1, and 0.

[0040] When the sum of the collected values ​​is 3 or 0, the wheel bearing capacity voting value is obtained by majority vote of the left / right wheel bearing capacity collected values;

[0041] When the sum of the collected values ​​is 2, if the left (or right) wheel load voting value corresponding to the normal channel is 1, then the wheel load voting value is "loaded"; if the left (or right) wheel load voting value is 2, then the wheel load voting value is determined by the airspeed. If the airspeed is <Xkm / h, the load is taken; otherwise, the unload is taken. At this time, the faulty channel is isolated according to the collected values ​​of the left / right wheel load.

[0042] When the sum of the collected values ​​is 1, if the left (or right) wheel load voting value corresponding to the normal channel is 0, then the wheel load voting value is "not loaded"; if the left (or right) wheel load voting value corresponding to the normal channel is 1, then the wheel load voting value is determined by the airspeed. If the airspeed is <X km / h, the wheel load is taken as loaded; otherwise, the wheel load is taken as not loaded.

[0043] When the load-bearing values ​​of the dual-redundant wheels are valid, if the valid load-bearing values ​​are from the same wheel (left or right wheel), the load-bearing value is determined by the airspeed. If the airspeed is <X km / h, the load is taken; otherwise, no load is taken. If the valid load-bearing values ​​are from different wheels, the valid values ​​of the left and right wheels are added together, and the possible results are 2, 1, and 0.

[0044] When the sum of the collected values ​​is 2 or 0, the wheel bearing capacity voting value is obtained by majority vote of the left / right wheel bearing capacity collected values;

[0045] When the sum of the collected values ​​is 1, the load-bearing collected values ​​of the left / right wheels are set to fault. The wheel load-bearing voting value is determined by the airspeed. If the airspeed is <X km / h, the load-bearing value is taken; otherwise, the no-load value is taken.

[0046] ③ When the landing gear signal fails, based on the landing gear structural strength and the tolerance of the control law parameters, a specific flight altitude and airspeed can be assumed. If the landing gear is lowered, it will be lowered; otherwise, it will be retracted. At this time, the voting algorithm for the wheel bearing signal is still the same as ①② above.

[0047] Example

[0048] The redundancy voting method for wheel bearing signals includes the following steps:

[0049] Step 1: When the landing gear signal is normal, if the landing gear is retracted, regardless of whether the left / right wheel load collection value is "loaded" or "not loaded", the wheel load voting value will be "not loaded".

[0050] Step 2, if the landing gear is deployed when the landing gear signal is normal:

[0051] When all the load-bearing values ​​of the quadruple-redundant wheels are valid, the load-bearing values ​​of the left and right wheels are added together, and the possible results are 4, 3, 2, 1, and 0.

[0052] When the sum of the collected values ​​is 4 or 0, the wheel bearing capacity voting value is obtained by majority vote of the left / right wheel bearing capacity collected values;

[0053] When the sum of the collected values ​​is 3 or 1, the wheel load voting value is obtained by the majority vote of the left / right wheel load collected values. After time t, the channel that is inconsistent with the majority channel collected values ​​is isolated, and the process proceeds to the judgment of the validity of the triple redundancy collected values.

[0054] When the sum of the collected values ​​is 2, the wheel load-bearing value is determined by the airspeed. If the airspeed is <X km / h, the load-bearing value is taken; otherwise, the no-load value is taken.

[0055] Furthermore, when the load-bearing values ​​of the triple-redundant wheels are valid, the load-bearing values ​​of the left and right wheels are added together, and the possible results are 3, 2, 1, and 0.

[0056] When the sum of the collected values ​​is 3 or 0, the wheel bearing capacity voting value is obtained by majority vote of the left / right wheel bearing capacity collected values;

[0057] When the sum of the collected values ​​is 2, if the left (or right) wheel load voting value corresponding to the normal channel is 1, then the wheel load voting value is "loaded". After time t, the channel with inconsistent collected values ​​with the majority channel is isolated, and the process proceeds to the judgment of the validity of the dual-redundancy collected values. If the left (or right) wheel load voting value is 2, then the wheel load voting value is determined by the airspeed. If the airspeed is <X km / h, the wheel load is taken; otherwise, the wheel load is not taken.

[0058] When the sum of the collected values ​​is 1, the wheel load voting value is determined by the airspeed. If the airspeed is <X km / h, the load is taken; otherwise, the load is not taken. After time t, the channel corresponding to the collected value of 1 is isolated, and the process is switched to the judgment of the validity of the dual-redundancy collected values.

[0059] In one embodiment of the present invention, when the load-bearing acquisition value of the dual-redundant wheels is valid, if the valid load-bearing acquisition value is the same wheel signal (left or right wheel), the wheel load-bearing voting value is determined by the airspeed. If the airspeed is <X km / h, the load is taken; otherwise, no load is taken. If the valid load-bearing acquisition value is the same wheel signal, the valid acquisition values ​​of the left and right wheels are added together, and the possible results are 2, 1, and 0.

[0060] When the sum of the collected values ​​is 2 or 0, the wheel bearing capacity voting value is obtained by majority vote of the left / right wheel bearing capacity collected values;

[0061] When the sum of the collected values ​​is 1, the load-bearing collected values ​​of the left / right wheels are set to fault. The wheel load-bearing voting value is determined by the airspeed. If the airspeed is <X km / h, the load-bearing value is taken; otherwise, the no-load value is taken.

[0062] In one embodiment of the present invention, when the landing gear signal fails, the landing gear is lowered if a specific flight altitude and airspeed are assumed based on the landing gear structural strength and the tolerance of the control law parameters; otherwise, the landing gear is retracted. At this time, the voting method for the wheel bearing signal is still the same as steps 1 and 2 above.

[0063] In one embodiment of the present invention, the method is applicable to aircraft with a tricycle layout.

[0064] In one embodiment of the present invention, the tricycle-type aircraft uses the left and right main landing gear wheels for logical determination.

[0065] In one embodiment of the present invention, the method is applicable to the landing rollout phase of an aircraft.

[0066] In one embodiment of the present invention, the aircraft approach and landing phase specifically refers to the moment when the left and right wheels of the aircraft touch the ground, but before the front wheel has made contact with the ground.

[0067] In one embodiment of the present invention, X is specifically 230-280 km / h. The selection principle for X km / h is based on the minimum touchdown speed at landing obtained from performance calculations on the aircraft aerodynamic platform, combined with the flight evaluation conducted by the pilot on a ground flight quality simulator.

[0068] It will be understood by those skilled in the art that, unless otherwise defined, all terms used herein (including technical and scientific terms) have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. It should also be understood that terms such as those defined in general dictionaries should be understood to have the same meaning as in the context of the prior art, and should not be interpreted in an idealized or overly formal sense unless defined as herein. The specific embodiments described above further illustrate the purpose, technical solution, and beneficial effects of the present invention. It should be understood that the above descriptions are merely specific embodiments of the present invention and are not intended to limit the present invention. Within the spirit and principles of the present invention, any person skilled in the art may use the disclosed technical content to make changes or modifications to create equivalent embodiments applicable to other fields. However, any simple modifications, equivalent changes, and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention, any modifications, equivalent substitutions, improvements, etc., should be included within the protection scope of the present invention.

Claims

1. A redundancy voting method for wheel bearing signals, characterized in that, Includes the following steps: Step 1: When the landing gear signal is normal, if the landing gear is retracted, regardless of whether the left / right wheel load collection value is "loaded" or "not loaded", the wheel load voting value will be "not loaded". Step 2, if the landing gear is deployed when the landing gear signal is normal: When all the load-bearing values ​​of the quadruple-redundant wheels are valid, the load-bearing values ​​of the left and right wheels are added together, and the possible results are 4, 3, 2, 1, and 0. When the sum of the collected values ​​is 4 or 0, the wheel bearing capacity voting value is obtained by majority vote of the left / right wheel bearing capacity collected values; When the sum of the collected values ​​is 3 or 1, the wheel load voting value is obtained by the majority vote of the left / right wheel load collected values. After time t, the channel that is inconsistent with the majority channel collected values ​​is isolated, and the process proceeds to the judgment of the validity of the triple redundancy collected values. When the sum of the collected values ​​is 2, the wheel load-bearing value is determined by the airspeed. If the airspeed is <X km / h, the load-bearing value is taken; otherwise, the unloaded value is taken. X is specifically 230-280 km / h.

2. The method as described in claim 1, characterized in that, When the load-bearing capacity of the triple-redundant wheel is valid, the load-bearing capacity of the left and right wheels is added together, and the possible results are 3, 2, 1, and 0. When the sum of the collected values ​​is 3 or 0, the wheel bearing capacity voting value is obtained by majority vote of the left / right wheel bearing capacity collected values; When the sum of the collected values ​​is 2, if the left or right wheel load voting value corresponding to the normal channel is 1, then the wheel load voting value is "loaded". After time t, the channel that is inconsistent with the majority channel collected values ​​is isolated and the process moves to the judgment of the validity of the dual-redundancy collected values. If the left or right wheel load voting value is 2, then the wheel load voting value is determined by the airspeed. If the airspeed is < X km / h, the load is taken; otherwise, the unload is taken. When the sum of the collected values ​​is 1, the wheel load voting value is determined by the airspeed. If the airspeed is < X km / h, the load is taken; otherwise, the load is not taken. After time t, the channel corresponding to the collected value of 1 is isolated, and the process moves to the judgment of the validity of the dual-redundancy collected values.

3. The method as described in claim 2, characterized in that, When the load-bearing values ​​of the dual-redundant wheels are valid, if the valid load-bearing values ​​are from the same wheel, the load-bearing value is determined by the airspeed. If the airspeed is < X km / h, the load is taken; otherwise, the load is not taken. If the valid load-bearing values ​​are from different wheels, the valid load-bearing values ​​of the left and right wheels are added together, and the possible results are 2, 1, and 0. When the sum of the collected values ​​is 2 or 0, the wheel bearing capacity voting value is obtained by majority vote of the left / right wheel bearing capacity collected values; When the sum of the collected values ​​is 1, the load-bearing collected values ​​of the left / right wheels are set to fault. The wheel load-bearing voting value is determined by the airspeed. If the airspeed is < X km / h, the load-bearing value is taken; otherwise, the no-load value is taken.

4. The method as described in claim 3, characterized in that, When the landing gear signal fails, based on the landing gear structural strength and the tolerance of the control law parameters, a specific flight altitude and airspeed can be assumed. If the landing gear is lowered, it will be lowered; otherwise, it will be retracted. At this time, the voting method for the wheel bearing signal is still the same as steps 1 and 2 above.

5. The method as described in claim 4, characterized in that, The method is applicable to aircraft with a tricycle configuration.

6. The method as described in claim 5, characterized in that, The aircraft with the tricycle front layout uses the left and right main landing gear wheels for logical judgment.

7. The method as described in claim 6, characterized in that, The method is applicable to the landing rollout phase of an aircraft.

8. The method as described in claim 7, characterized in that, The aircraft approach and landing phase specifically refers to the moment when the left and right wheels of the aircraft touch the ground, but before the front wheel has made contact with the ground.

9. The method as described in claim 8, characterized in that, The selection principle for X km / h is based on the minimum touchdown speed at landing, which is obtained from performance calculations on the aircraft's aerodynamic platform, combined with the flight evaluation conducted by the pilot on a ground flight quality simulator.

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