• 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 mobile vehicle (10) for supplying pressurized air to an aircraft (A), said vehicle being configured to tow the aircraft during its movements on the ground and comprising pneumatic means (20) adapted to provide pressurized air to the aircraft, said pneumatic means being manually connectable to a high-pressure connector (A2) of the aircraft and remotely disconnectable from said connector. The invention allows an aircraft to be moved by the vehicle to the runway threshold without its engines being started. The invention thus allows airlines to achieve substantial savings in fuel. During the movement of the aircraft, the pneumatic means of the vehicle provide the pneumatic supply necessary for the proper functioning of the aircraft systems. The remote disconnection of the pneumatic means meets the airport security requirements in that it prevents an operator from leaving the vehicle on the taxiways to disconnect the pneumatic means of the aircraft.
    公开号:FR3039520A1
    申请号:FR1557357
    申请日:2015-07-31
    公开日:2017-02-03
    发明作者:Didier Gendre；Kevin Goburdhun；Alexandre Fouillot
    申请人:Airbus SAS；
    IPC主号:
    专利说明:

    TRACTION VEHICLE FOR MANEUVERING AN AIRCRAFT AND FOR PROVIDING PRESSURIZED AIR TO AN AIRCRAFT DURING THE TAXI PHASE PRIOR TO TAKING OFF
    The present invention relates to the field of aircraft ground service and more particularly relates to a traction vehicle for maneuvering an aircraft and for supplying pressurized air to said aircraft during the taxi phase before take-off.
    The taxi phase of an aircraft before takeoff is the phase during which the aircraft moves to the threshold of a runway by taxiways.
    To ensure its movement on the taxiways, an aircraft typically uses its engines. The operation of ground engines consumes a significant amount of fuel and this problem is exacerbated by the formation of aircraft queues that form before the threshold of the runway.
    A solution to this problem is to tow the aircraft, engine off, on the taxiways using traction vehicles dedicated to the ground service of aircraft.
    This solution involves providing a pneumatic supply to the aircraft during towing in order to operate certain systems of the aircraft (air conditioning, ventilation of the avionics, etc.) and to be able to start the engines before the threshold of the runway. Some towing vehicles are equipped with pneumatic means manually connectable to the aircraft to provide such a pneumatic supply. On the other hand, the manual disconnection of these pneumatic means from the aircraft requires that an operator descend on the lanes which is formally prohibited by the aeronautical regulations. As a result, this solution is not implemented. The object of the invention is to solve this problem. For this purpose, the invention relates to a traction vehicle for maneuvering an aircraft and for supplying pressurized air to said aircraft, said vehicle being configured to tow the aircraft during its movements on the ground and comprising pneumatic means adapted to provide the air under pressure to the aircraft and being manually connectable to a high-pressure connector of the aircraft and remotely disconnectable (via an automatic disconnection) of said connector. The invention allows the aircraft to be moved by the vehicle to the runway threshold without its engines are started. The invention thus allows airlines to achieve substantial savings in fuel. Indeed, the fuel consumption of the vehicle, both for towing the aircraft and for providing it with pressurized air, is very low in comparison with the consumption of an aircraft engine, even in idle mode. . During the movement of the aircraft, the pneumatic means of the vehicle provide the pneumatic supply necessary for the proper functioning of the aircraft systems. This power supply is particularly necessary for starting the engines before the threshold of the track.
    The remote disconnection of the pneumatic means meets the airport security requirements in that it prevents an operator from leaving the vehicle on the taxiways to disconnect the pneumatic means from the aircraft.
    The characteristics of the invention mentioned above, as well as others, will emerge more clearly on reading the following description of exemplary embodiments, said description being given in relation to the attached drawings, among which: FIG. 1 is a diagram of the vehicle according to one embodiment of the invention, said vehicle comprising pneumatic means and control means for controlling the pneumatic means, said pneumatic means comprising an air pipe provided with a tip connectable manually to high-pressure connector of the aircraft for supplying pressurized air to said aircraft and automatically disconnectable from said connector under control means control; FIG. 2 is a schematic view of the control means of the mobile vehicle represented in FIG. 1; FIG. 3 is a schematic view of the tip of the air pipe shown in FIG. 1; FIG. 4 is a diagrammatic view of a device for hooking up the air hose shown in FIG. 1 to the fuselage of an aircraft, said device being able to be manually hooked to the fuselage of an aircraft and capable of being lifted remotely. under control of the control means shown in Figure 2; and FIG. 5 is a view similar to FIG. 1 showing the vehicle according to another embodiment of the invention in which the pneumatic means are connected to the aircraft, said means comprising a plurality of hooking devices such as shown in Figure 4 attached to the fuselage of the aircraft to keep the pipe under the fuselage away from the ground during towing of the aircraft.
    With reference to Figures 1 and 2, the vehicle 10 according to one embodiment of the invention is configured to tow an aircraft A and is equipped with pneumatic means 20 for supplying pressurized air to said aircraft A during towing.
    The vehicle 10 is of the type of those present at airports for the ground service of aircraft. In particular, the mobile vehicle is a motorized wheeled traction vehicle adapted to tow an aircraft on the taxiways of the airport. The vehicle conventionally comprises a chassis (not shown) to which the wheels are attached, and, mounted on the chassis, a cockpit 12 of the vehicle, pneumatic means 20, coupling means 13 of the vehicle to the front axle Al of the vehicle. aircraft as well as control means 30 (not shown in FIG. 1) for controlling the coupling means 13 and the pneumatic means 20.
    The coupling means 13, such as for example a system for lifting and fixing the wheel of the front axle Al of the aircraft on a vehicle support plate, are well known to those skilled in the art and will not be detailed further in the art. description. When the coupling means 13 are coupled to the front axle A1, the vehicle 10 can be used to tow the aircraft A on the taxiways.
    The control means 30 comprise a central unit 31 arranged in the vehicle 10 and which is electrically connected to sensors 32 as well as to a plurality of actuators 33 arranged on the pneumatic means 20 and the coupling means 13. The unit central is further connected to a man-machine interface 34 disposed in the cockpit of the vehicle 12, by which the operator of the vehicle can interact with the actuators 33 to control the pneumatic means 20 and the coupling means 13.
    The pneumatic means 20 are configured to be manually connected to the aircraft A by an operator and are controllable from the cockpit 12 of the vehicle via the control means 30. The control means 30 also make it possible to display on the human-machine interface 34 operating data of the pneumatic means obtained by the sensors 32.
    According to the invention, the pneumatic means 20 can be disconnected from the aircraft A remotely via the actuators 33 of the control means 30 via the interaction of an operator with the man-machine interface 34.
    The pneumatic means 20 comprise an air compressor 21, a flexible air hose 22 connected to the compressor 21, a nozzle 23 located at the free end of the air hose and which makes it possible to connect the hose to a high-pressure connector. A2 of the aircraft. The actuators 33 of the control means for disconnecting the pneumatic means 20 from the aircraft are electrically connected to the central unit 31 via a network of electrical cables arranged on the pipe 22.
    The air compressor 21 is housed in a compartment of the vehicle and has the function of supplying compressed air to the pipe 22 to which the compressor is connected. The operation of the compressor is controlled (via at least one actuator 33 of the controlled switch type) and monitored (via at least one sensor 32) by the central unit 31.
    Referring to Figure 3, the tip 23 is of cylindrical shape, and is intended to be fitted around the high pressure connector A2 of the aircraft. The tip 23 comprises a damping device 24 and a connection / disconnection device 25 of the tip associated with actuators 33 control means. The connection / disconnection device 25 of the nozzle allows manual connection of the nozzle to the high-pressure connector A2 and remote disconnection (automatic) of said connector via activation of the actuators 33.
    In known manner, the high-pressure connector A2 of an aircraft is in the form of a vertical cylindrical piece (relative to the fuselage) having a groove on its periphery and which is arranged in a duct located under the fuselage of the aircraft. aircraft, between its landing gear before Al and its main landing gear (not shown). The conduit comprises a valve in pivot connection with the fuselage of the aircraft A to close or access the conduit. In the closed position of the valve, the latter represents a surface in continuity with the skin of the fuselage of the aircraft. The valve is manually openable and constrained in the closed position under the action of a spring.
    The connection / disconnection device 25 comprises a circular cage 300 arranged at the end of the endpiece 23. The cage encloses a plurality of balls 301 and, associated with each ball, also encloses a compression spring (not shown) and a actuator 33 (not shown) control means, for example of the solenoid type.
    The cage 300 is formed of two circular rings 302-303 welded together, with a ring 302 of larger diameter forming the outer periphery of the cage and a ring 303 of smaller diameter forming the inner periphery of the cage. Each ring comprises openings (not shown) opposite openings in the other ring. Each opening has a diameter equal to at most 90% of that of a ball 301 so that each ball inserted between the two openings can move radially between the two openings towards the outside of the cage 300 and partly out of the cage (inner or outer periphery side) while being conscripted into the cage.
    For each ball 301, the compression spring is inserted between the ball 301 and the ring 302 of larger diameter in order to constrain the movement of the ball towards the ring 303 of smaller diameter. In addition, each ball 301 is equipped with a finger attached to an arm of the actuator 33 associated with the ball. The actuator 33 is activatable by the central unit 31 in order to push the ball 301 towards the ring 302 of greater diameter with a force greater than that of the compression spring. When the actuator 33 is not activated, it exerts no force on the ball.
    In operation, when the operator inserts the nozzle 23 around the high-pressure connector A2, the balls 301 pushed by the spring will be inserted in the groove of the high-pressure connector A2 and will therefore allow the nozzle 23 to be retained. connected to said connector. When the actuators 33 of the cage are activated (turned on simultaneously), they push the balls 301 of the groove of the high-pressure connector A2 so that the tip 23 falls to the ground under its own weight.
    The damping device 24 is constituted by a protective ring of metal or elastic material surrounding the end piece 23 and which aims to protect the tip when the latter falls to the ground.
    With reference to FIGS. 4 and 5, the pneumatic means preferably comprise at least one attachment device 400 of the hose to the fuselage of the aircraft A. The implementation of an attachment device is advantageous in order to maintain the pipe 22 below the fuselage at a distance from the ground to avoid damaging the pipe 22 during the running of the aircraft, particularly in the case where the high-pressure connector A2 is away from the front axle A1 of the aircraft.
    An attachment device 400 comprises a frame 401 having a first face 401a and a second face 401b substantially parallel to each other, with a pneumatic suction cup 403 arranged at the first face 401a, and a damping device (not shown in Figures 4 and 5) arranged on the side of the second side 401b. The attachment device 400 further comprises a vacuum pump 404 associated with the suction cup 403 in order to be able to hook the attachment device to a fuselage A, as well as an arming / disarming device 405 of the suction cup associated with a actuator 33 control means. The arming / disarming device 405 allows manual arming (attachment of the suction cup to the fuselage) of the suction cup 403 and disarming (disengagement of the suction cup) at a distance from said suction cup 403 via activation of the actuator 33.
    The pneumatic cup 403 comprises a base 403a attached to the first face 401a and a lip 403b attached to the base. The circular base 403a is molded into a first relatively rigid material while the lip 403b, intended to be brought into contact with the fuselage A of an aircraft, surrounds the base 403a and is made of a second relatively flexible material.
    The vacuum pump 404 comprises a cylindrical casing 404a arranged in the frame 401 and opening at a first end 404b outside the frame at its second face 401b and at a second end 404c at an opening 403c made in the base of the suction cup 403. The pump 404 comprises a movable piston 406 in the casing 404a and a support rod 407 of the piston. The piston 406 delimits two chambers in the casing, namely a first chamber 410 between the first end 404b of the casing and the piston and a second chamber between the second end 404c of the casing and the piston. The piston 406 is fixed to the rod 407 which extends in the first chamber along the longitudinal axis of the envelope 404a. In the remainder of the description, the upper position of the rod, the position of the rod for which the piston 406 is located at the first end 404b of the envelope, will be called the upper position of the rod.
    The arming / disarming device 405 comprises at least one handle 405a, retaining means 405c for holding the rod 407 in the up position, and a compression spring 408 arranged in the first chamber to constrain the piston to move towards the second room. The retaining means 405c for holding the rod 407 in the up position are associated with the actuator 33 of the control means 30, of the servocontrol type, which enables the stem to be released when it is activated by the central unit 31.
    Note that in Figures 4 and 5, the arming / disarming device 405 comprises two handles 405a operable by an operator.
    Each handle 405a comprises a hollow frame 405b in which the air pipe 22 is fixed which is fixed to the handle via conventional devices of the retaining ring type. The handle 405a is articulated to the frame 401 and is integral with the rod 407 so that actuation of the handle has the effect of moving the rod. Due to the force exerted by the compression spring 408, the handle 405a has a rest position substantially perpendicular to the frame 401 and in which the piston 406 is plated at the second end 404c of the casing. The actuation of the handle 405a by the operator, that is to say a rotation of the handle to a position where the latter is substantially parallel to the frame 401 of the attachment device 400, moves the rod 407 to the first end 404b of the envelope to the upper position of the rod. Such displacement of the rod brings the piston 406 to the first end 404b of the envelope which has the effect of creating a vacuum in the pneumatic cup 403 when the lip 403b is in contact with a fuselage of the aircraft A.
    The retaining means 405c of the rod in the high position comprise a notch 420 arranged on the rod 407 at a predetermined position and a rigid tongue 421 fixed to the frame via a movable mechanism 430 coupled to the actuator 33. The tongue 421 extends perpendicular to the rod and comprises a free end 421a at the rod. The movable mechanism 430 comprises a movable axis 431, perpendicular to the rod, which is fixed to the tongue 421 through a compression spring 432 constraining the free end of the tongue to come into contact with the rod. The movable axle 431 is fixed at its other end to the actuator 33 which, when it is activated, moves the mobile axle 431 in translation along an axis perpendicular to the rod 407 so that the free end 421a of the tongue moves away from the stem.
    In operation, when the notch 420 is located opposite the tongue 421, the free end 421a of the latter, constrained by the spring 432, fits into the notch 420 and thus blocks any movement of the rod 407. The rod 407 is then locked in the high position and a depression can be maintained in the pneumatic cup 403 when its lip 403b is in contact with a fuselage A. When the actuator 33 is activated, the free end 421a of the tongue is disengaging the notch 420 and the rod 407 is then no longer retained. Therefore, the piston 406 pushed by the spring 408 moves towards the second end 404c of the envelope which allows to blow air at the base 403a of the pneumatic sucker. When the suction cup 403 is bonded to the fuselage A, the movement of the piston 406 towards the second end of the envelope 404c makes it possible to detach the suction cup 403 and to make the attachment device 400 fall to the ground under the effect of its weight.
    The device for damping the attachment device is constituted by a foam part or an air balloon which aims to dampen the shock when the attachment device 400 falls to the ground.
    The vehicle 10 preferably comprises a storage compartment S in which the air pipe 22, the nozzle 23 and the hooking devices 400 (if the pneumatic means are provided with it) can be stored when the pipe 22 is not deployed. For this purpose, the control means 30 advantageously comprise an actuator 33, of the electric motor type, associated with a reel E arranged in the storage compartment S and on which the pipe 22 is wound in order to be able to automatically wind up the pipe 22 and the gripping devices 400 attached to the hose at the request of an operator interacting with the man-machine interface 34.
    With reference to FIG. 5, a use of the vehicle 10 according to the invention will now be described for moving an aircraft A on the taxiways in order to reach the runway threshold. It will be noted in the example illustrated in FIG. 5 that the pneumatic means 20 of the vehicle 10 comprise a plurality of hooking devices 400.
    In a first step, the mobile vehicle 10 is coupled to the train A1 before the aircraft via the coupling means 13 of the vehicle. The operator exits the vehicle and unrolls the pipe 22 and opens the hatch to manually connect the nozzle 23 of the pipe to the high-pressure connector A2 of the aircraft. The tip 23 connected to the high-pressure connector A2 keeps the hatch open.
    In addition, so that the pipe 22 does not drag on the ground, the operator places and arms one by one each of the hooks 400 under the fuselage by acting on the handles 405a so that they are hung under the fuselage via 403. In this manner, the air pipe 22, held by the handles 405a of the various attachment devices 400, is suspended under the fuselage A of the aircraft and the latter can roll without risk of damaging the engine. 22. The operator then goes back up to the cockpit 12 of the vehicle 10 and once the sensors 32 of the electronic means indicate that the hose 22 and the hooking devices 400 are hooked correctly, the operator starts, by acting on the man-machine interface 34, the air compressor 21 to supply pressurized air to the aircraft via the pipe.
    The pilots of the aircraft Apeuvent then start up the systems of the aircraft A as the air conditioning of the cabin or the ventilation of the avionics systems.
    In a next step, the vehicle 10 tows the aircraft A on the traffic lanes allocated by the control tower to the runway threshold. During this step, the A3 engines of the aircraft are not lit and the propulsion of the aircraft is only provided by the vehicle 10 according to the invention.
    Once the aircraft has reached the runway threshold, the pilots start each of the engines (one by one) using the pressurized air supplied by the compressor 21 to start the blower of the A3 engines.
    After authorization of the pilots of the aircraft, the operator acts on human-machine interface 34 to disconnect the vehicle 10 from the front axle A1 of the aircraft as well as to disconnect the pneumatic means 20. In order to disconnect the pneumatic means, a signal electrical power is sent simultaneously by the central unit 31 to the actuators 33 of the connection / disconnection device 25 of the nozzle 23 and to the actuator 33 of the arming / disarming device 405 of each attachment device 400.
    The pipe 22 and the attachment devices 400 then fall to the ground under the effect of their own weight and the operator can wind the pipe 22 and the hooks 400 in the behavior of the vehicle by controlling the operation of the reel E via the human-machine interface 34. Following this last step, the vehicle 10 can leave to join the parking areas and the aircraft A can take off. The invention allows the aircraft A to be moved by the vehicle 10 to the runway threshold without its engines being started. The invention thus allows airlines to achieve substantial savings in fuel. Indeed, the fuel consumption of the vehicle 10, both for towing the aircraft A and for supplying it with pressurized air, is very low in comparison with the consumption of an aircraft engine A3, even in idle speed. During the displacement of the aircraft, the pneumatic means 20 of the vehicle provide the pneumatic supply necessary for the proper functioning of the systems of the aircraft A. This power supply is in particular necessary for starting the A3 engines before the threshold of the runway.
    The remote disconnection of the pneumatic means 20 meets the airport security requirements in that it prevents an operator from leaving the vehicle on the taxiways to manually disconnect the pneumatic means 20 from the aircraft.
    The embodiments described above of the arming / disarming device 25 of the end piece 23 and the arming / disarming device 405 of each attachment device 400 are only given by way of examples. Other embodiments of these devices, within the reach of those skilled in the art, are conceivable without departing from the scope of the present invention.
    权利要求:
    Claims (5)
    [1" id="c-fr-0001]
    1) A traction vehicle (10) for maneuvering an aircraft and for supplying pressurized air to said aircraft (A), said vehicle (10) being configured to tow the aircraft during its movements on the ground and comprising pneumatic means ( 20), adapted to supply air under pressure to the aircraft, said pneumatic means (20) being manually connectable to a high-pressure connector (A2) of the aircraft, characterized in that the pneumatic means are automatically disconnectable from said connector (A2).
    [0002]
    2) Vehicle (10) according to claim 1, characterized in that it comprises means (30) for controlling said pneumatic means (20), said control means (30) comprising actuators (33) associated with the pneumatic means ( 20), activating the actuators (33) for disconnecting the pneumatic means (20) from the high-pressure connector (A2) of the aircraft.
    [0003]
    3) Vehicle (10) according to claim 2, characterized in that the control means (30) comprise a man-machine interface (34) arranged in a cockpit (12) of the vehicle (10), said actuators being activatable via an interaction of an operator with the human-machine interface (34).
    [0004]
    4) Vehicle (10) according to any one of claims 2 to 3, characterized in that the pneumatic means (20) comprise a compressor (21), an air hose (22) connected to the compressor, and a nozzle ( 23) arranged at a free end of the pipe, said nozzle comprising a connection / disconnection device (25) of the nozzle (23) for manually connecting the nozzle (23) to the high-pressure connector (A2) of the aircraft, actuators (33) control means (30) being associated with the connection / disconnection device for disconnecting the tip (23) of said connector (A2) at the activation of said actuators (33).
    [0005]
    5) Vehicle (10) according to claim 4, characterized in that the pneumatic means (20) comprise at least one attachment device (400) attached to the pipe (22), each attachment device having a pneumatic suction cup (403 ) associated with a vacuum pump (404) and intended to be attached to the fuselage of an aircraft (A), the suction pad being further associated with a device for arming / disarming (405) the suction cup to manually hook the device attaching to the fuselage of the aircraft (A) via the suction cup, an actuator (33) of the control means (30) being associated with the arming / disarming device (405) to unhook the attachment device (400) said fuselage upon activation of said actuator.
    类似技术:
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    同族专利:
    公开号 | 公开日
    FR3039520B1|2018-11-02|
    US10227144B2|2019-03-12|
    US20170029136A1|2017-02-02|
    CN106394921A|2017-02-15|
    CN106394921B|2021-03-23|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2968923A|1955-05-06|1961-01-24|North American Aviation Inc|Mobile starter for jet aircraft engines|
    GB2175550A|1985-05-28|1986-12-03|Air Traction Ind|Aircraft ground-handling vehicle|
    US5381987A|1994-05-31|1995-01-17|Carns; William A.|Utility vehicle for towing and servicing aircraft|
    US6424891B1|1999-03-31|2002-07-23|The United States Of America As Represented By The Secretary Of The Air Force|Aircraft ground power unit|
    US4289095A|1979-07-05|1981-09-15|Scherr Ronald R|Preheater for aircraft engines|
    US7461516B2|2005-11-22|2008-12-09|Illinois Tool Works Inc.|Modular aircraft ground support cart|US10124911B2|2016-03-18|2018-11-13|Hamilton Sundstrand Corporation|Taxi tug with auxiliary power services|
    GB2556062B|2016-11-16|2020-01-15|Ge Aviat Systems Ltd|Taxi vehicle for moving an aircraft|
    CN107807543B|2017-11-20|2020-11-10|中国运载火箭技术研究院|Automatic release separation control system and method and traction running test device|
    CN112722312B|2021-02-09|2021-08-13|中国民航大学|Emergency rescue vehicle and emergency rescue method for airplane substitute wheel|
    法律状态:
    2016-07-21| PLFP| Fee payment|Year of fee payment: 2 |
    2017-02-03| PLSC| Search report ready|Effective date: 20170203 |
    2017-07-24| PLFP| Fee payment|Year of fee payment: 3 |
    2018-07-25| PLFP| Fee payment|Year of fee payment: 4 |
    2020-07-21| PLFP| Fee payment|Year of fee payment: 6 |
    2021-07-27| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1557357A|FR3039520B1|2015-07-31|2015-07-31|TRACTION VEHICLE FOR MANEUVERING AN AIRCRAFT AND FOR PROVIDING AIR PRESSURE TO AN AIRCRAFT DURING THE TAXI PHASE PRIOR TO TAKING OFF|FR1557357A| FR3039520B1|2015-07-31|2015-07-31|TRACTION VEHICLE FOR MANEUVERING AN AIRCRAFT AND FOR PROVIDING AIR PRESSURE TO AN AIRCRAFT DURING THE TAXI PHASE PRIOR TO TAKING OFF|
    US15/218,792| US10227144B2|2015-07-31|2016-07-25|Towing vehicle for maneuvering an aircraft and for supplying pressurized air to an aircraft during the taxiing phase before takeoff|
    CN201610608674.9A| CN106394921B|2015-07-31|2016-07-28|Towing vehicle for moving an aircraft and supplying pressurized air to the aircraft|
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