Aircraft landing automatic braking system and method thereof

Abstract

The invention relates to an aircraft landing automatic braking system and method, and the aircraft landing automatic braking system comprises an automatic braking switch, an aircraft management computer and an aircraft wheel braking system; after the automatic brake switch is turned on, the airplane enters an airplane automatic brake mode; in the automatic braking mode of the airplane, the airplane management computer judges whether the airplane is grounded or not according to the received airplane speed, the main landing gear airplane wheel bearing state and the main airplane wheel rotating speed; after the airplane is grounded, the airplane management computer judges whether a braking condition is met or not according to the position of a throttle lever and the state of a spoiler; when the braking condition is met, the airplane management computer calculates the braking distance and the braking deceleration rate; the airplane management computer issues a braking instruction to an airplane wheel braking system according to the braking deceleration rate; after receiving the braking instruction, the airplane wheel braking system automatically applies braking pressure according to the braking deceleration rate, so that the airplane decelerates at the braking deceleration rate, braking is completed, and then the airplane exits from the automatic braking mode.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aircraft brake control design, and particularly relates to an automatic landing brake system for an aircraft and a method thereof. BACKGROUND

[0002] The wheel brake system is a key system for achieving ground deceleration and auxiliary directional control during the take-off and landing of an aircraft, and its performance is directly related to the operation safety of the aircraft. In order to reduce the operation burden of the pilot during the landing, which is a high-load flight stage, and improve the stability and comfort of the brake process, the wheel brake system of a modern civil aircraft is usually configured with an automatic brake function, and an automatic brake selection switch is installed in the cockpit.

[0003] The low, medium and high gears are set on the automatic brake selection switch, and each gear corresponds to a deceleration rate. Before the landing of the aircraft, the pilot needs to make a comprehensive judgment according to the actual weight of the aircraft, runway conditions, weather conditions and other factors, manually select a suitable gear, and after the aircraft touches the ground, when the brake condition is met (such as the throttle lever being in the slow position and the spoiler being opened), the wheel brake system automatically applies brake pressure, so that the aircraft decelerates at the deceleration rate corresponding to the selected gear, and the brake is completed.

[0004] However, the manual gear type automatic brake scheme has obvious technical defects:

[0005] Firstly, the pilot's attention is mainly paid to the operation of the aircraft during the landing stage, and the pilot has a large operation burden. Additional analysis and selection of a suitable brake gear will greatly increase the operation burden of the pilot.

[0006] Secondly, there is a risk of judgment error in the selection of the brake gear by the pilot. If the selected brake gear is too high (the deceleration rate is too large), the aircraft will decelerate too fast, which will reduce the comfort of the passengers, intensify the wear of the tires and brake components, and affect the economy; if the selected brake gear is too low (the deceleration rate is too small), the brake distance will be too long, which directly threatens the flight safety when the runway is limited or an emergency occurs.

[0007] The present application is proposed in view of the above technical defects. SUMMARY

[0008] The purpose of the present application is to provide an automatic landing brake system for an aircraft and a method thereof, so as to automatically and intelligently determine the optimal deceleration rate during the landing of the aircraft, and to automatically brake, thereby reducing the operation burden of the pilot and the risk of judgment error.

[0009] The technical scheme of the present application is:

[0010] An automatic landing brake system for an aircraft, comprising: an automatic brake switch, an aircraft management computer and a wheel brake system.

[0011] After the automatic brake switch is opened, the airplane enters an airplane automatic brake mode;

[0012] In the airplane automatic brake mode, the airplane management computer judges whether the airplane is grounded according to the received airplane speed, the main landing gear wheel load state and the main wheel rotation speed;

[0013] After the airplane is grounded, the airplane management computer judges whether the brake condition is met according to the throttle lever position and the spoiler state;

[0014] When the brake condition is met, the airplane management computer calculates the brake distance and the brake deceleration rate;

[0015] The airplane management computer issues a brake instruction to the wheel brake system and follows the brake deceleration rate;

[0016] After receiving the brake instruction, the wheel brake system automatically applies brake pressure according to the brake deceleration rate, so that the airplane decelerates at the brake deceleration rate, completes the brake, and then exits the automatic brake mode.

[0017] According to at least one embodiment of the present application, in the above-mentioned airplane landing automatic brake system, when the brake pedal is pressed beyond the preset stroke in the automatic brake mode, the automatic brake mode is exited.

[0018] According to at least one embodiment of the present application, in the above-mentioned airplane landing automatic brake system, the automatic brake switch is a press type or a pull type.

[0019] According to at least one embodiment of the present application, in the above-mentioned airplane landing automatic brake system, the automatic brake switch is arranged in the cockpit.

[0020] According to at least one embodiment of the present application, in the above-mentioned airplane landing automatic brake system, when the airplane speed is lower than the flight speed threshold value, the main landing gear wheels are all loaded, and the main wheel rotation speed exceeds the idle speed threshold value, the airplane management computer judges that the airplane is grounded.

[0021] According to at least one embodiment of the present application, in the above-mentioned airplane landing automatic brake system, the flight speed threshold value and the idle speed threshold value are 50 km / h.

[0022] According to at least one embodiment of the present application, in the above-mentioned airplane landing automatic brake system, when the throttle lever is in the slow position and the spoiler is opened, the airplane management computer judges that the brake condition is met.

[0023] According to at least one embodiment of the present application, in the above-mentioned airplane landing automatic brake system, the airplane management computer calculates the brake distance, and specifically:

[0024] ;

[0025] wherein,

[0026] is the braking distance;

[0027] is the taxiing distance;

[0028] is the buffer distance.

[0029] According to at least one embodiment of the present application, in the above-mentioned automatic braking system for airplane landing, the buffer distance is 200 meters.

[0030] According to at least one embodiment of the present application, in the above-mentioned automatic braking system for airplane landing, the airplane management computer calculates the braking deceleration rate, specifically:

[0031] ;

[0032] wherein,

[0033] is the braking deceleration rate;

[0034] is the airplane speed;

[0035] is the airplane speed at the exit point.

[0036] According to at least one embodiment of the present application, in the above-mentioned automatic braking system for airplane landing, the preset distance is 70%.

[0037] According to at least one embodiment of the present application, in the above-mentioned automatic braking system for airplane landing, after the wheel braking system receives the braking instruction, it judges whether the braking deceleration rate is within the applicable range of the wheel braking system. If not, it returns the braking deceleration rate out-of-range information to the airplane management computer. The airplane management computer re-adjusts the exit point, calculates the braking distance and the braking deceleration rate, and then issues the braking instruction again through the bus to the wheel braking system according to the braking deceleration rate.

[0038] An automatic braking method for airplane landing, based on the above-mentioned automatic braking system for airplane landing, comprising:

[0039] Turning on the automatic braking switch before landing to make the airplane enter the automatic braking mode;

[0040] After the aircraft enters the automatic braking mode, the aircraft management computer is used to determine whether the aircraft is grounded according to the received aircraft speed, the main landing gear wheel load state and the main wheel rotation speed. After the aircraft is grounded, whether the braking condition is met is determined according to the throttle lever position and the spoiler state. When the braking condition is met, the aircraft management computer calculates the braking distance and the braking deceleration rate, and then sends the braking instruction to the wheel brake system according to the braking deceleration rate, so that the wheel brake system automatically applies the brake pressure according to the braking deceleration rate, the aircraft decelerates at the braking deceleration rate, the braking is completed, and the automatic braking mode is exited.

[0041] According to at least one embodiment of the present application, the aircraft landing automatic braking method described above further comprises:

[0042] When an abnormal emergency condition occurs, the down-pedal rudder exceeds the preset stroke, and the aircraft exits the automatic braking mode.

[0043] The present application has at least the following beneficial technical effects:

[0044] The present application provides an aircraft landing automatic braking system and method. Through highly integrated and intelligent control logic, the system can automatically calculate the braking deceleration rate, realize the automatic selection of the braking gear by the pilot, realize the automation of the aircraft braking process, and thus reduce the pilot's operating burden, improve the safety, economy and convenience of the braking during the landing of the aircraft. BRIEF DESCRIPTION OF DRAWINGS

[0045] Figure 1 Fig. 1 is a schematic diagram of an aircraft landing automatic braking system provided by an embodiment of the present application;

[0046] Figure 2 Fig. 2 is a schematic diagram of an aircraft landing automatic braking method provided by an embodiment of the present application.

[0047] In order to better illustrate the present embodiment, some contents in the drawings may be omitted, enlarged or reduced, and are only used for exemplary description, and cannot be understood as a limitation on the present application. DETAILED DESCRIPTION

[0048] In order to make the technical solutions of the present application and the advantages thereof clearer, the technical solutions of the present application will be further clearly and completely described below with reference to the drawings. It should be understood that the specific embodiments described herein are only part of the embodiments of the present application, and are only used to explain the present application, but not to limit the present application. It should be noted that, in order to facilitate description, only parts related to the present application are shown in the drawings, and other related parts can be referred to the general design.

[0049] In addition, unless otherwise defined, technical terms or scientific terms used in the description of the present application shall be understood as having the common meaning to those of ordinary skill in the art to which the present application belongs. The "comprising" used in the description of the present application indicates that the concept appearing before the word encompasses the concepts listed after the word and its equivalents, without excluding other associated concepts.

[0050] In addition, the words indicating the orientation used in the description of the present application are only used to indicate the relative direction or positional relationship, and when the absolute position of the described object changes, the relative positional relationship may also change accordingly. It should be noted that, unless otherwise specified and limited, the "installation", "connection" and the like used in the description of the present application should be understood in a broad sense, for example, the connection can be a fixed connection or a detachable connection; can be a mechanical connection or an electrical connection; can be directly connected or indirectly connected through an intermediate medium, and those skilled in the art can understand the specific meaning of the present application according to the specific circumstances.

[0051] An automatic braking system for an aircraft landing, as shown in Figure 1 , comprising an automatic braking switch, an aircraft management computer, and a wheel brake system.

[0052] The automatic braking switch is a push type or a pull type, which is arranged in the cockpit. After being turned on, the aircraft enters a mode without the need for the pilot to manually select the brake gear, thereby reducing the pilot's operation burden and the risk of misjudgment during the landing of the aircraft.

[0053] In the automatic braking mode of the aircraft, the aircraft management computer determines whether the aircraft is grounded according to the received aircraft speed, the load state of the main landing gear wheels, and the rotation speed of the main wheels.

[0054] When the aircraft speed is lower than a flight speed threshold, the main landing gear wheels are all loaded, and the rotation speed of the main wheels exceeds an idle speed threshold, it is determined that the aircraft is grounded, wherein the flight speed threshold and the idle speed threshold can be 50 km / h, and are selected according to the actual use of the aircraft.

[0055] After the aircraft is grounded, the aircraft management computer determines whether the braking condition is met according to the position of the throttle lever and the state of the spoiler.

[0056] When the throttle lever is in the slow position and the spoiler is open, it is determined that the braking condition is met.

[0057] When the braking condition is met, the aircraft management computer calculates the braking distance and the deceleration rate.

[0058] ;

[0059] wherein,

[0060] is the brake distance;

[0061] is the taxi distance, i.e. the distance from the aircraft to the exit point, the exit point being selected as the runway exit;

[0062] is the buffer distance, which is selected according to the actual situation, and is usually 200 meters.

[0063]

[0064] wherein,

[0065] is the brake deceleration rate;

[0066] is the aircraft speed;

[0067] is the speed of the aircraft to the exit point.

[0068] The aircraft management computer issues a brake command to the wheel brake system through the bus according to the brake deceleration rate.

[0069] After receiving the brake command, the wheel brake system determines whether the brake deceleration rate is within the range applicable to the wheel brake system. If not, the wheel brake system returns brake deceleration rate out-of-range information to the aircraft management computer. The aircraft management computer re-adjusts the exit point, calculates the brake distance and the brake deceleration rate, and then issues a brake command to the wheel brake system through the bus according to the brake deceleration rate.

[0070] If the brake deceleration rate is within the range applicable to the wheel brake system, the wheel brake system automatically applies brake pressure according to the brake deceleration rate, so that the aircraft decelerates at a constant brake deceleration rate, achieving more reasonable deceleration rate control, completing braking, and further causing the aircraft to exit the automatic braking mode.

[0071] In the automatic braking mode, the automatic braking mode is exited and switched to the manual braking mode when the brake pedal is pressed beyond a preset stroke, thereby ensuring that the pilot has the highest control right and facilitating the handling of abnormal situations. The preset stroke can be 70%.

[0072] An aircraft landing automatic braking method is implemented based on the above-mentioned aircraft landing automatic braking system, as shown in Figure 2 .

[0073] The automatic braking switch is turned on before the aircraft lands, so that the aircraft enters the automatic braking mode.

[0074] ​After the aircraft enters the automatic braking mode, the aircraft management computer judges whether the aircraft is grounded according to the received aircraft speed, main landing gear wheel load state and main wheel rotation speed. After the aircraft is grounded, the aircraft management computer judges whether the braking condition is met according to the throttle lever position and spoiler state. When the braking condition is met, the aircraft management computer calculates the braking distance and deceleration rate, and then sends the braking instruction to the wheel brake system according to the braking deceleration rate, so that the wheel brake system automatically applies brake pressure according to the constant braking deceleration rate, the aircraft decelerates at the braking deceleration rate, the braking is completed, and the automatic braking mode is exited.

[0075] When an abnormal emergency condition occurs, the lower brake pedal exceeds the preset stroke, the aircraft exits the automatic braking mode and switches to the manual braking mode, and the aircraft is manually controlled.

[0076] The above embodiment discloses an aircraft landing automatic braking system and method thereof:

[0077] Simplified operation: The complex multi-gear selection is simplified to "one-key start", which can greatly reduce the pilot's manipulation burden in the landing stage.

[0078] Intelligent optimization: The reasonable braking deceleration rate is automatically calculated, which takes into account safety, comfort and economy.

[0079] Safe and reliable: Multiple condition judgments and data validity checks are introduced, and a manual operation priority principle is set, which can ensure the safety of aircraft operation.

[0080] So far, the technical solution of the present application has been described in combination with the preferred embodiments shown in the drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without deviating from the principles of the present application, those skilled in the art can make equivalent changes or replacements to related technical features, and the technical solutions after these changes or replacements will fall within the protection scope of the present application.

Claims

1. An automatic braking system for aircraft landing, characterized in that, include: Automatic brake switch, aircraft management computer, wheel brake system; After the automatic braking switch is turned on, the aircraft enters the automatic braking mode. In automatic braking mode, the aircraft management computer determines whether the aircraft has touched down based on the received aircraft speed, main landing gear wheel load status, and main landing gear wheel speed. After the aircraft touches down, the aircraft management computer determines whether the braking conditions are met based on the throttle position and spoiler status. When braking conditions are met, the aircraft management computer calculates the braking distance and braking deceleration rate. The aircraft management computer sends braking commands to the wheel braking system according to the braking deceleration rate; After receiving a braking command, the wheel braking system automatically applies braking pressure according to the braking deceleration rate, causing the aircraft to decelerate at the braking deceleration rate, thus completing the braking and causing the aircraft to exit the automatic braking mode.

2. The automatic braking system for aircraft landing according to claim 1, characterized in that, In automatic braking mode, the automatic braking mode will be deactivated when the brake pedal is pressed down beyond the preset travel distance.

3. The automatic braking system for aircraft landing according to claim 2, characterized in that, The automatic brake switch is either a push-button or a lever-type switch.

4. The automatic braking system for aircraft landing according to claim 3, characterized in that, The automatic braking switch is located inside the cockpit.

5. The automatic braking system for aircraft landing according to claim 4, characterized in that, When the aircraft speed is below the flight speed threshold, all main landing gear wheels are under load, and the main landing gear speed exceeds the no-load speed threshold, the aircraft management computer determines that the aircraft has touched down.

6. The automatic braking system for aircraft landing according to claim 5, characterized in that, The flight speed threshold and the unloaded speed threshold are both set to 50 km / h.

7. The automatic braking system for aircraft landing according to claim 6, characterized in that, When the throttle lever is in the idle position and the spoilers are open, the aircraft management computer determines that the braking conditions are met.

8. The automatic braking system for aircraft landing according to claim 7, characterized in that, The aircraft management computer calculates the braking distance, specifically as follows: ； in, Braking distance; This refers to the gliding distance; This is for buffer distance.

9. The automatic braking system for aircraft landing according to claim 8, characterized in that, Buffer distance Take 200 meters.

10. The automatic braking system for aircraft landing according to claim 9, characterized in that, The aircraft management computer calculates the braking deceleration rate, specifically: ； in, This refers to the braking deceleration rate; For aircraft speed; This refers to the speed of the aircraft as it approaches the exit point.

11. The aircraft landing automatic braking system according to claim 10, characterized in that, The preset itinerary can be set to 70%.

12. The aircraft landing automatic braking system according to claim 11, characterized in that, After receiving a braking command, the wheel braking system determines whether the braking deceleration rate is within the applicable range of the wheel braking system. If not, it returns information that the braking deceleration rate exceeds the limit to the aircraft management computer. The aircraft management computer then readjusts the exit point, calculates the braking distance and braking deceleration rate, and sends a braking command to the wheel braking system again via the bus according to the braking deceleration rate.

13. An automatic braking method for aircraft landing, implemented based on the automatic braking system for aircraft landing as described in claim 12, characterized in that, include: Activate the automatic braking switch before the aircraft lands to put the aircraft into automatic braking mode; After the aircraft enters automatic braking mode, the aircraft management computer uses the received aircraft speed, main landing gear wheel load status, and main landing gear wheel speed to determine whether the aircraft has touched down. After the aircraft touches down, it uses the throttle position and spoiler status to determine whether the braking conditions are met. If the braking conditions are met, the aircraft management computer calculates the braking distance and braking deceleration rate, and then issues a braking command to the wheel braking system according to the braking deceleration rate. The wheel braking system then automatically applies braking pressure according to the braking deceleration rate, causing the aircraft to decelerate at the braking deceleration rate, completing the braking process, and exiting automatic braking mode.

14. The automatic braking method for aircraft landing according to claim 13, characterized in that, Also includes: In the event of an abnormal emergency, pressing the brake pedal beyond the preset travel distance will cause the aircraft to exit automatic braking mode.

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