• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a method for controlling the maneuvering of the undercarriages of an aircraft, in which at least one of the pulling steps is performed on the bunker hatches to relieve the trap hook of the hatches. actuating the hatch hook (s) to release the hatches and opening hatches in response to the detection of a flight situation conducive to the occurrence of a maneuver order, even before the maneuver order is received .
    公开号:FR3013681A1
    申请号:FR1361528
    申请日:2013-11-22
    公开日:2015-05-29
    发明作者:Gilbert Lecourtier
    申请人:Messier Bugatti Dowty SA；
    IPC主号:
    专利说明:

    [0001] The invention relates to a method for reducing the apparent maneuvering time of landing gear of an aircraft. TECHNOLOGICAL BACKGROUND OF THE INVENTION Aircraft flying at a certain speed are equipped with retractable undercarriages which are operable between an extended position and a retracted position in a hold of the aircraft closed by hatches. For this purpose, the hatches are moved by a trap actuator and retained in the closed position by one or more hatches hooks. Similarly, the undercarriage is moved by a landing gear actuator and retained in the retracted position by a landing gear hook. The undercarriage also includes an unlocking actuator for unlocking it while it is locked in the deployed position and thus allowing it to be raised to the retracted position. The deployment maneuver of a landing gear generally comprises the following successive steps: a. Traction on the bunker hatches to relieve the trap hook of the hatches; b. Actuating the trap hook (s) to release the hatches; vs. Opening hatches d. Traction on the undercarriage to relieve the restraint hook of the undercarriage; e. Actuating the landing gear hook to release the undercarriage; f. Moving the undercarriage to bring it from the retracted position to the deployed position, causing the automatic locking of the undercarriage when it arrives in the deployed position; boy Wut. Closing of the hatches, causing the automatic retrying of the retaining hook when the traps arrive in the closed position.
    [0002] The lifting maneuver of an undercarriage comprises the following successive steps: a. Traction on the bunker hatches to relieve the trap hook of the hatches; b. Actuating the trap hook (s) to release the hatches; vs. Opening hatches d. Unlocking the undercarriage; e. Displacing the undercarriage, from the deployed position to the retracted position causing the landing gear hook to automatically reset when the undercarriage arrives in the retracted position; f. Closure of the hatches, causing the automatic reset of the hatch hook or hooks when the hatches arrive in the closed position. These steps, which are generally initiated by the pilot's actuation of a control member (a button, a lever, take a certain time, typically ten to twenty seconds, all the more so that it should take the delays, detections and confirmation of position, and the logical processing by the control unit managing these maneuvers, are presently present, and there is a need to reduce this time, especially the lifting sequence of the undercarriage. landing gear in the extended position disturb the aerodynamic flow around the aircraft, are source of noise, and form obstacles that should be retracted to ensure the safety of the aircraft.
    [0003] A first reflex of the skilled person would be to increase the size of the actuators used to move the hatches and the undercarriage, to accelerate the movement. However, this solution is expensive. OBJECT OF THE INVENTION The object of the invention is to accelerate the maneuvering of landing gear in a simple manner. PRESENTATION OF THE INVENTION In order to achieve this goal, there is provided a method of controlling at least one deployment or retraction maneuver of at least one undercarriage of an aircraft, said maneuvers comprising at least following steps: Deployment Maneuver: a. Traction on the bunker hatches to relieve the trap hook of the hatches; b. Actuating the trap hook (s) to release the hatches; vs. Opening hatches d. Traction on the undercarriage to relieve the restraint hook of the undercarriage; e. Actuating the landing gear hook to release the undercarriage; f. Moving the undercarriage to bring it from the retracted position to the deployed position, causing the automatic locking of the undercarriage when it arrives in the deployed position; boy Wut. Closing of the hatches, causing the automatic retrying of the retaining hook when the traps arrive in the closed position. Retraction Maneuver: a. Traction on the hatches of the cargo hold to relieve the trap hook of the hatches; b. Actuating the trap hook (s) to release the hatches; vs. Opening hatches d. Unlocking the undercarriage; e. Moving the undercarriage from the deployed position to the retracted position, causing the landing gear hook to automatically reset when the undercarriage arrives in the retracted position; f. Closing the hatches, causing the hatch hook (s) to automatically reset when the hatches arrive in the closed position. The method of the invention comprises the following actions: - before receiving a maneuver command, and in response to the detection of a flight situation favorable to the occurrence of said maneuver command, execution of at least one one of the first three stages of the maneuver concerned; - after receiving the order of maneuver, execution of the remaining steps of the maneuver.
    [0004] Of course, the method is implemented by the computer of the aircraft responsible for managing the undercarriages. Thus, when the pilot or the onboard computer launches the order of operation of the undercarriage, part of the steps of the maneuver has already been performed, which saves a little time. Thus, the apparent duration of the maneuver, that is to say the time elapsed between the order of maneuver and the end of the maneuver is decreased. This method can be implemented by simply changing the programming of the computer managing the undercarriages, without modifying the actuators of the hatches and the undercarriage. The take-off and landing phases are now detailed. When the aircraft takes off, the undercarriage is of course in the deployed position and the hatches are closed and retained by the hook or hooks. The computer responsible for managing the undercarriages detects a flight situation during which the undercarriages are likely to be retracted. In practice, this detection is carried out by the computer which monitors the sensor outputs or flight information for logical processing. For example, the flight situation in which the retraction maneuver command can occur is detected when the following logic condition is recognized as true by the computer: - the wheels of the undercarriage no longer touch the ground; And the speed of the aircraft is greater than a given threshold speed Vs1; The first information is easily obtained using the sensor "Weight on Wheels" which is usually placed on the compass of the undercarriage and indicates if the damper of it is relaxed, sign that the wheels of the undercarriage do not touch the ground anymore. The second information comes from the inertial unit of the aircraft. The two pieces of information are processed by a logic circuit to trigger the execution of the first step (s) of the retraction maneuver.
    [0005] In response to this detection, the computer controls the traction on the hatches, the actuation of the hooks of the hatches, and the opening of the hatches (or only the first two stages, or only the first stage). Therefore, when the driver presses the landing gear retraction button and thus gives the retraction maneuver command, the computer only has to perform the remaining steps of the retraction maneuver. The time thus gained is not negligible, since it can amount to several seconds.
    [0006] During landing, the landing gear is retracted in the hold and retained by the landing gear hook, and the hatches are closed and retained by the hatch hook or hooks. The computer that manages the undercarriages monitors sensor outputs and flight information for logical processing.
    [0007] For example, the flight situation in which the deployment maneuver command can intervene is detected when the following logical condition is recognized as true by the computer: the speed of the aircraft is less than a given threshold speed Vs2; - AND (the height from the ground is less than a given threshold height Hl OR the high lift flaps are deployed) In response to this detection, the computer commands the traction on the hatches, the actuation of the hooks or hooks hatches, and the opening of hatches (or only the first two stages, or only the first stage). Therefore, when the pilot presses the landing gear deployment button and thus gives the deployment maneuver command, the computer only has to perform the remaining steps of the deployment maneuver. The time thus gained is not negligible, since it can amount to several seconds.
    [0008] It will be noted that the first three stages are common to both maneuvers. They can therefore be controlled upon detection of a flight situation conducive to the occurrence of a deployment maneuver order or a retraction maneuver order.
    权利要求:
    Claims (3)
    [0001]
    REVENDICATIONS1. A method of controlling at least one deployment or retraction maneuver of at least one undercarriage of an aircraft that is executed in response to a deployment or retraction maneuver command, said maneuver comprising at least the following steps: Maneuver Deployment: a. Traction on the bunker hatches to relieve the trap hook of the hatches; b. Actuating the trap hook (s) to release the hatches; vs. Opening hatches d. Traction on the undercarriage to relieve the restraint hook of the undercarriage; e. Actuating the landing gear hook to release the undercarriage; f. Displacing the undercarriage from the retracted position to the deployed position, causing the landing gear to automatically lock when it reaches the deployed position; boy Wut. Closing of the hatches, causing the automatic reset of the retaining hook when the traps arrive in the closed position. Retraction Maneuver: a. Traction on the hatches of the cargo hold to relieve the trap hook of the hatches; b. Actuating the trap hook (s) to release the hatches; vs. Opening hatches d. Unlocking the undercarriage; e. Displacing the undercarriage, from the deployed position to the retracted position causing the landing gear hook to automatically reset when the undercarriage arrives in the retracted position; Closing the hatches, causing the hatch hook (s) to automatically reset when the hatches arrive in the closed position; the method of the invention comprising the following actions: before receiving the maneuver command, and in response to the detection of a flight situation conducive to the occurrence of a maneuver command, execution of at least l one of the first three steps (a, b, c) of the maneuver concerned; - after receiving the order of maneuver, execution of the remaining steps of the maneuver.
    [0002]
    2. The method according to claim 1, wherein the flight situation in which the retraction maneuver command can occur is detected when the following logical condition is true: the wheels of the undercarriage no longer touch the ground; And the speed of the aircraft is greater than a given threshold speed Vs1;
    [0003]
    3. Method according to claim 1, wherein the flight situation in which the deployment maneuver order can occur is detected when the following logical condition is recognized as true by the computer: the speed of the aircraft is less than a given threshold speed Vs2; - AND (the height above the ground is less than a given threshold height Hl OR the high lift flaps are deployed)
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    同族专利:
    公开号 | 公开日
    US9517837B2|2016-12-13|
    CN104648659B|2017-11-03|
    FR3013681B1|2017-06-09|
    CN104648659A|2015-05-27|
    US20150144735A1|2015-05-28|
    EP2876047B1|2019-03-06|
    EP2876047A1|2015-05-27|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US6854689B1|2004-02-09|2005-02-15|The Boeing Company|Methods and systems for operating aircraft landing gears|
    EP2082956A2|2008-01-23|2009-07-29|The Boeing Company|Electrically activated aircraft landing gear control system and method|
    US6575405B2|1999-03-30|2003-06-10|The Boeing Company|Control system and method for a semi-levered landing gear for an aircraft|
    US6927702B2|2001-06-11|2005-08-09|Robert D. Wiplinger|Landing gear warning system|
    FR2875475B1|2004-09-21|2008-02-08|Airbus France Sas|SYSTEM FOR MANEUVERING A LANDING TRAIN FOR AN AIRCRAFT AND AN AIRCRAFT HAVING SUCH A SYSTEM|
    JP2006142869A|2004-11-16|2006-06-08|Kayaba Ind Co Ltd|Landing gear ascending/descending system for aircraft|
    GB0511417D0|2005-06-03|2005-07-13|Airbus Uk Ltd|Landing gear|
    US8123161B1|2008-06-03|2012-02-28|Hamilton Sundstrand Corporation|Aircraft landing gear unlock actuator|
    US8162255B2|2008-10-06|2012-04-24|The Boeing Company|Aerodynamically-assisted landing gear|
    US8686590B2|2011-03-14|2014-04-01|Simmonds Precision Products, Inc.|Wireless power transmission system and method for an aircraft sensor system|
    GB201113030D0|2011-07-28|2011-09-14|Airbus Operations Ltd|Aircraft landing gear|
    GB2498208B|2012-01-06|2017-12-20|Ge Aviat Systems Ltd|Electrical actuator incorporating a free play mechanism to eliminate force fighting|
    FR3013681B1|2013-11-22|2017-06-09|Messier-Bugatti-Dowty|METHOD FOR REDUCING APPROPRIATE MANEUVER TIME OF AIRCRAFT IMPELLERS|FR3013681B1|2013-11-22|2017-06-09|Messier-Bugatti-Dowty|METHOD FOR REDUCING APPROPRIATE MANEUVER TIME OF AIRCRAFT IMPELLERS|
    GB2563437A|2017-06-16|2018-12-19|Airbus Operations Ltd|Landing gear controller|
    US10266253B1|2017-11-10|2019-04-23|The Boeing Company|Methods and apparatus for controlling landing gear shrink|
    GB2571708A|2018-02-28|2019-09-11|Airbus Operations Ltd|Landing gear system control|
    GB2580954A|2019-01-31|2020-08-05|Airbus Operations Ltd|Landing gear deployment|
    法律状态:
    2015-06-26| PLFP| Fee payment|Year of fee payment: 3 |
    2016-11-18| PLFP| Fee payment|Year of fee payment: 4 |
    2017-06-23| CD| Change of name or company name|Owner name: MESSIER-BUGATTI-DOWTY, FR Effective date: 20170518 |
    2017-11-21| PLFP| Fee payment|Year of fee payment: 5 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 7 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 8 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1361528A|FR3013681B1|2013-11-22|2013-11-22|METHOD FOR REDUCING APPROPRIATE MANEUVER TIME OF AIRCRAFT IMPELLERS|FR1361528A| FR3013681B1|2013-11-22|2013-11-22|METHOD FOR REDUCING APPROPRIATE MANEUVER TIME OF AIRCRAFT IMPELLERS|
    US14/541,451| US9517837B2|2013-11-22|2014-11-14|Method for reducing the apparent manoeuvring time for landing gear of an aircraft|
    EP14193530.4A| EP2876047B1|2013-11-22|2014-11-17|Method for reducing the apparent operation time of aircraft landing gear|
    CN201410673576.4A| CN104648659B|2013-11-22|2014-11-21|Method for the obvious manipulation time of the take-off and landing device that reduces aircraft|
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