CN-122009125-A - Brake control method suitable for marine environment aircraft

CN122009125ACN 122009125 ACN122009125 ACN 122009125ACN-122009125-A

Abstract

The invention relates to the technical field of aircraft braking, in particular to a braking control method suitable for an aircraft in a marine environment, which comprises the steps that a pilot performs braking operation on the aircraft; the method comprises the steps of detecting whether a braking function in a normal channel braking system fails, judging whether the emergency channel braking system fails, switching to the emergency channel braking system to perform braking anti-skid control when the emergency channel braking system fails, detecting whether the braking function in the normal channel braking system fails, judging whether the emergency channel braking system fails or not at the moment, and degrading the novel anti-skid function by using logic and non-instruction braking inhibition technology, so that the braking safety of an airplane under various working conditions can be ensured.

Inventors

LIU SUQI
XUE YANFENG
WANG XU
LIU XU
CHEN YU
LIU CHANGWEI

Assignees

西安航空制动科技有限公司

Dates

Publication Date: 20260512
Application Date: 20260324

Claims (10)

1. A brake control method suitable for an aircraft in a marine environment is characterized in that, a brake control system including a normal channel brake system and an emergency channel brake system, the method comprising: the pilot performs braking operation on the aircraft; When detecting that the braking function in the normal channel braking system fails, judging whether the emergency channel braking system fails or not; When the emergency channel braking system has faults, judging whether the fault state can finish braking and anti-skid operation, if so, switching to the emergency channel braking system to perform braking anti-skid control, if not, triggering non-skid and pulse braking alarm, automatically limiting the braking pressure within the range of less than or equal to 5MPa, using normal channel control output, and outputting the braking pressure with pulse fluctuation of +/-0.5 MPa; Detecting that the braking function in the normal channel braking system is not faulty, and judging whether the emergency channel braking system is faulty or not at the moment when the anti-skid function in the normal channel braking system is faulty; When the emergency channel has no fault, switching to the emergency channel braking system to perform braking anti-skid control; when the emergency channel braking system has faults, judging whether the fault state can finish braking and anti-skid operation, if so, switching to the emergency channel braking system to perform braking anti-skid control, if not, directly cutting off the control right of the normal and emergency braking channels, and giving an upward alarm, and at the moment, selecting to use traction braking to perform braking control to brake the aircraft.
2. The method for controlling the braking of an aircraft in marine environment according to claim 1, wherein when a traction brake switch is turned on to brake, the traction brake switch is a cockpit panel switch, a relay for controlling the traction brake to work after being turned on is turned on, a 28V power supply of an emergency bus bar on the aircraft is directly communicated to a constant-value pressure reducing valve of the emergency brake valve, and the constant-value pressure reducing valve brakes according to a constant-value pressure of 6MPa after receiving 28V power supply to brake the aircraft.
3. The method according to claim 1, wherein when the braking operation is performed on the aircraft, the lock valve is opened to perform the braking operation when the braking command is not less than 30%.
4. The brake control method applicable to the marine aircraft according to claim 1, wherein the normal channel brake system and the emergency channel brake system comprise a brake command sensor, a brake control unit, a wheel speed sensor and a pressure sensor, the normal channel brake system further comprises a normal brake combination valve, and the emergency channel brake system further comprises an emergency brake combination valve.
5. The method according to claim 4, wherein the brake command sensor senses a brake pedal angle when a pilot performs a braking operation on the aircraft, converts a pedal angle signal into a voltage signal and transmits the voltage signal to the brake control unit, the brake control unit receives the command voltage signal, outputs a 28V solenoid valve power supply signal for unlocking when judging that unlocking is required, calculates a theoretical brake current value required to be output by a corresponding brake pressure, outputs the brake current to the normal brake combination valve, switches to the emergency channel when the normal channel is insufficient to complete a braking action, and outputs the current to the emergency brake combination valve.
6. The method for controlling the braking of an aircraft in a marine environment according to claim 5, wherein the wheel speed sensor senses the wheel speed of the aircraft, converts the wheel speed signal into an approximately sine wave signal and transmits the approximately sine wave signal to the brake control unit for providing the wheel speed of the aircraft, and the pressure sensor transmits the pressure signal to the brake control unit in the form of current by sensing the pressure output by the servo valve.
7. The method of claim 6, wherein the brake control unit is responsible for collecting wheel speed and pressure data, and according to the theoretical brake current value, the wheel speed signal and the brake pressure signal, the actual brake current value is finally output by resolving through the anti-skid control logic.
8. The method for controlling braking of an aircraft in marine environment according to claim 4, wherein detecting the normal channel braking system comprises detecting whether a brake command sensor, a brake control unit, a wheel speed sensor and a pressure sensor are faulty, and if not, adopting the normal channel braking system to brake.
9. The method of claim 4, wherein determining whether the emergency channel braking system has a fault comprises: Detecting whether the emergency brake combined valve fails or not by a brake command sensor, a brake control unit, a wheel speed sensor and a pressure sensor, and determining the current failure level of an emergency channel brake system; before judging whether the emergency channel braking system has faults, determining the current fault level of the normal channel braking system; And comparing the current fault level of the normal channel braking system with the current fault level of the emergency channel braking system, and determining whether to switch to the emergency channel braking system for control.
10. The brake control method applicable to the marine aircraft according to claim 4, wherein the fault classification comprises the steps of enabling a fault to be a normal fault of the aircraft, enabling the fault to be a 1-level fault, enabling the fault to be a communication fault of the aircraft once, enabling the fault to be a 2-level fault, enabling the fault to be a non-skid fault of the aircraft, enabling the fault to be a 3-level fault, enabling the fault to be a pressure deviation fault of the aircraft, enabling the fault to be a 4-level fault, enabling the fault to be an engine oil source fault, enabling the fault to be a 5-level fault, and enabling the fault to be a brake fault of the aircraft, and enabling the fault to be a 6-level fault.

Description

Brake control method suitable for marine environment aircraft Technical Field The invention relates to the technical field of aircraft braking, in particular to a braking control method suitable for an aircraft in a marine environment. Background The braking system of the aircraft is a key system in the process of taking off and landing of the aircraft, and is one of important systems for affecting the safety of the aircraft. The aircraft braking system has the special challenges that the land-based aircraft is serious in fault result, if the traditional hydraulic braking system is in anti-skid failure during landing, the wheel is easy to lock by using high-pressure braking to cause tire burst accident, the non-instruction braking result is serious, if the non-instruction braking occurs during the process of accelerating running or ejection, the speed of the aircraft is insufficient and the aircraft cannot take off, the aircraft is high in possibility of rushing out of a runway, the environment of part of the runway is severe, the friction coefficient of a high-salt fog corrosion and wet-skid steel plate runway fluctuates by more than 30%, the braking distance is extremely short, the length of part of the runway is generally about 200 meters, and the full braking is required to be completed within a specified distance. The prior art adopts an anti-skid switch to use or close the anti-skid function, but directly outputs 100% of brake pressure after the anti-skid is closed, the tire burst risk is higher, the pressure is reduced to 70% (about 5.6 MPa) when the anti-skid switch is closed in the prior art, the locking of a wheel under the working condition of low adhesive force can not be avoided, and as a result, the prior art does not relate to the non-instruction brake inhibition technology, and if the non-instruction brake occurs, the aircraft accident is easy to cause. Disclosure of Invention In order to overcome the defects in the background art, the invention provides a brake control method suitable for an aircraft in a marine environment, aiming at the problems that the braking under the anti-skid fault is easy to cause the aircraft wheels to lock and burst, the aircraft rushes out of a runway due to non-instruction braking before taking off, and the like. The method can ensure the braking safety of the aircraft during landing and ensure the braking safety of the aircraft under various working conditions. The invention aims to provide a brake control method suitable for an aircraft in a marine environment, which adopts a brake control system comprising a normal channel brake system and an emergency channel brake system, and comprises the following steps: the pilot performs braking operation on the aircraft; When detecting that the braking function in the normal channel braking system fails, judging whether the emergency channel braking system fails or not; When the emergency channel braking system has faults, judging whether the fault state can finish braking and anti-skid operation, if so, switching to the emergency channel braking system to perform braking anti-skid control, if not, triggering non-skid and pulse braking alarm, automatically limiting the braking pressure within the range of less than or equal to 5MPa, using normal channel control output, and outputting the braking pressure with pulse fluctuation of +/-0.5 MPa; Detecting that the braking function in the normal channel braking system is not faulty, and judging whether the emergency channel braking system is faulty or not at the moment when the anti-skid function in the normal channel braking system is faulty; When the emergency channel has no fault, switching to the emergency channel braking system to perform braking anti-skid control; when the emergency channel braking system has faults, judging whether the fault state can finish braking and anti-skid operation, if so, switching to the emergency channel braking system to perform braking anti-skid control, if not, directly cutting off the control right of the normal and emergency braking channels, and giving an upward alarm, and at the moment, selecting to use traction braking to perform braking control to brake the aircraft. In one embodiment, when the traction brake switch is turned on to brake, the traction brake switch is a panel switch of a cockpit, a relay for controlling the traction brake to work after being turned on is turned on, a 28V power supply of an emergency bus bar on the aircraft is directly communicated to a fixed-value pressure reducing valve of the emergency brake valve, and the fixed-value pressure reducing valve brakes according to a fixed-value pressure of 6MPa after receiving 28V power supply to brake the aircraft. In one embodiment, when the braking operation is performed on the aircraft, the lock valve is opened to perform the braking operation when the braking command is more than or equal to 30%. In one embodiment, the brake control system comprises a brake co