• 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:
    Aircraft landing gear carrying at least two wheels (4) and intended to be mounted movably on an aircraft structure between an extended position and a retracted position, characterized in that the wheels are rotatably mounted on axles (3) borne by arms (2) articulated in the lower part of a box (1) of the undercarriage, each arm being associated with a damper (5) coupled on the one hand to the arm and on the other hand to a collar (6) which extends around the box and which is slidably mounted on the box between a high position in which the collar bears against an abutment (7) of the box when the undercarriage is in the extended position, and a low position towards which the collar is brought during the maneuvering of the landing gear from the extended position to the retracted position, so as to bring the wheels together.
    公开号:FR3079813A1
    申请号:FR1852932
    申请日:2018-04-04
    公开日:2019-10-11
    发明作者:Nicolas ANTONI；Vincent Raimbault
    申请人:Safran Landing Systems SAS；
    IPC主号:
    专利说明:

    The invention relates to an aircraft undercarriage whose transverse dimensions can be reduced in the retracted position to facilitate its storage in the hold.
    BACKGROUND OF THE INVENTION
    Landers are known which are mounted mobile on an aircraft between a deployed position and a retracted position comprising several wheels, in particular landers provided with a bogie for carrying four or more wheels. These undercarriages, in particular if they carry braked wheels, are wide and occupy a large volume in the hold when they are retracted.
    OBJECT OF THE INVENTION
    The invention aims to propose an aircraft undercarriage whose lateral dimensions can be reduced during its retraction to facilitate its storage in the hold.
    PRESENTATION OF THE INVENTION
    With a view to achieving this goal, an aircraft undercarriage carrying at least two wheels is provided and intended to be mounted mobile on an aircraft structure between a deployed position and a retracted position. According to the invention, the wheels are mounted rotating on axles carried by articulated arms in the lower part of a box of the undercarriage, each arm being associated with a shock absorber coupled on the one hand to the arm and on the other hand to a collar which extends around the box and which is slidably mounted on the box between a high position in which the collar is in abutment against a stop of the box when the undercarriage is in the deployed position, and a low position towards which the collar is brought during the maneuver of the undercarriage from the deployed position to the retracted position, so as to bring the wheels closer.
    When the undercarriage is in the deployed position and the aircraft is on the ground, the forces coming from the wheels are transmitted by being filtered by the shock absorbers at the collar, which transmits these forces to the box via the stop. The bringing of the collar in the low position during the maneuver of the undercarriage towards the retracted position brings the wheels closer to the central axis of the box, which reduces the lateral dimensions of the undercarriage, which therefore facilitates its storage in flight in a hold of the aircraft.
    According to a particular aspect of the invention, the collar is connected by a link to a bracing member with two articulated elements intended to stabilize the undercarriage in the deployed position.
    In the deployed position, the two elements of the bracing member are kept in the aligned position, which stabilizes the box. The link maintains the collar in the high position, in the immediate vicinity or in abutment against the stop of the box. During the maneuver of the undercarriage towards the retracted position, the alignment of the two elements of the bracing member is broken, and the relative movement of one of these two elements relative to the box is exploited to ensure that the link pushes the collar towards the low position, which brings the wheels closer and reduces the lateral size of the undercarriage. Thus, there is no need for any specific actuator, nor for any locking of the collar. During the deployment maneuver, the link pulls the collar to bring it back to the high position, which spreads the wheels and brings them back to their landing position.
    DESCRIPTION OF THE FIGURES
    The invention will be better understood in the light of the following description of particular embodiments of the invention, with reference to the figures of the accompanying drawings, among which
    - Figure 1 is a side view of a undercarriage with four wheels and two arms according to a first particular embodiment of the invention, seen here in the deployed position while the aircraft is in flight;
    - Figure 2 is a front view of the undercarriage of Figure 1;
    - Figure 3 is a front view of the undercarriage of Figure 1, in the retracted position;
    - Figure 4 is a view of 1 undercarriage according to arrow IV of Figure 3 while it is in the retracted position;
    - Figure 5 is a front view of a undercarriage with two wheels and two arms according to a second particular embodiment of the invention, seen here in the deployed position while the aircraft is in flight;
    - Figure 6 is a front view of the undercarriage of Figure 5, seen here in the deployed position while the aircraft is on the ground;
    - Figure 7 is a front view of the undercarriage of Figure 5, seen here in the retracted position;
    - Figure 8 is a schematic top view of a undercarriage with four wheels and four arms according to a third particular embodiment of one invention;
    - Figure 9 is a schematic top view of a undercarriage with four wheels and four arms according to a fourth particular embodiment of the invention.
    DETAILED DESCRIPTION OF THE INVENTION
    In accordance with a first particular embodiment of the invention illustrated in FIGS. 1 to 4, the undercarriage illustrated comprises a box 1 articulated on the structure of the aircraft along an axis XI so that the undercarriage is movable between a position deployed illustrated in FIGS. 1 and 2, and a retracted position illustrated in FIGS. 3 and 4. The operating actuator has not been shown for clarity. On the lower part of the box 1 are articulated two arms 2 along substantially horizontal axes X2 when the undercarriage is in the deployed position. The arms 2 here extend forward and backward with reference to a direction of advance of the aircraft. Here each of the arms 2 carries an axle 3 receiving two rotating wheels 4 (one of the wheels has been omitted in Figures 1 and 4 for clarity). Shock absorbers 5 are each coupled between each of the arms 2 and a collar 6 extending around the box 1 to absorb the vertical kinetic energy of the aircraft on landing and to filter the irregularities of the ground during taxiing.
    According to the invention, the collar 6 is slidably mounted on the box 1 between a high position illustrated in FIGS. 1 and 2 in which the collar 6 is in abutment against an upper stop 7 of the box 1, and a low position illustrated in FIGS. 3 and 4. The sliding of the collar 6 during the retraction maneuver has the effect of changing the lateral dimensions E of the undercarriage in the deployed position to a lateral dimensions E 'which is smaller in the retracted position by bringing the wheels closer together, which facilitates its storage in the hold in the retracted position.
    The collar 6 can be moved by any actuation means, in particular by a dedicated actuator, which imposes an actuation sequence. Here, and according to a particular arrangement of the invention, the relative movement of one of the elements of a bracing member 10 of the box 1 is used to move the collar
    6. More specifically, the bracing member here is an alignment strut comprising two elements 11, 12 hinged together, the first element 12 also being articulated on the structure of the aircraft, while the second element 12 is articulated on the box along an axis X3. These two elements 11, 12 come into alignment when the undercarriage is in the deployed position and are held there by a stabilization member, not shown. The collar 6 is coupled to a horn 13 of the second bracing element 12 by means of a link 14 so that in the deployed position, the link 14 forces the collar 6 to be in the immediate vicinity or against the stop 7 of the box 1. An elastic member or a light mechanism may be provided between the connecting rod 14 and the collar 6 so that the forces coming from the support of the wheels on the ground confirm the collar 6 against the stop 7 without introducing into the member bracing 10 of efforts unnecessarily stressing it.
    During the maneuver of the undercarriage towards the retracted position illustrated in FIGS. 3 and 4, the alignment of the elements 11, 12 of the bracing member 10 is broken, causing a relative rotational movement between the second element 12 and the box 1 around the axis X3. This movement causes the collar 6 to slide, pushed by the link 14 towards its low position on the box 1. This sliding has the effect of bringing the wheels 4 closer together, thereby reducing the lateral size of the undercarriage. The movement and maintenance of the collar 6 by the bracing member 10 makes it possible to dispense with any dedicated actuating member, as well as any member for locking the collar.
    According to now a second particular embodiment of the invention illustrated in FIGS. 5 to 7 and in which the references of the elements common to the previous embodiment are increased by a hundred, the box 101 is always articulated along an axis XI on the structure of the aircraft. Here it carries two arms 102 articulated in the lower part of the box 101, but extending laterally by reference to a direction of advance of the aircraft. Here each of the arms 102 carries an axle 103 carrying in rotation a single wheel 104. In the deployed position in flight illustrated in FIG. 5, the plane of the wheels is oblique, but it straightens up on the ground as illustrated in FIG. 6 when the shock absorbers are compressed by the weight of the aircraft. Shock absorbers 105 are coupled to the arms 102, and to a collar 106 slidably mounted on the box 101. As previously, the collar 106 is held in the high position when the undercarriage is in the deployed position, and brought back to the low position when the undercarriage is in the retracted position, which has the effect of reducing the lateral size of the undercarriage. The position of the collar 106 is also controlled by the element 112 of the bracing member 110 which is articulated on the box 101 by means of a link 114 coupled to the element 112 and to the collar 106, according to the same mode d actuation.
    The invention is applicable to any type of wheel arrangement on the undercarriage. Figures 8 and 9 show the application of the invention to four-wheel undercarriages 204,304 each of which is carried by an arm. In FIG. 8, two of the arms 202 extend longitudinally and two of the arms 202 extending transversely by reference to a direction of advance of the aircraft in order to propose an arrangement of the wheels 204 crosswise. The articulation axes of the arms 203 on the bottom of the box 201 are always substantially horizontal when the undercarriage is in the deployed position, and they extend longitudinally and laterally with reference to a direction of advance of the aircraft. In FIG. 9, the arms 302 extend in oblique directions with reference to a direction of advance of the aircraft in order to propose an arrangement of the arms in a cross which leads to a more conventional arrangement of the wheels 304 which would be that of a four-wheel bogie undercarriage. The articulation axes of the arms 303 on the bottom of the box 301 are always substantially horizontal when the undercarriage is in the deployed position, and they extend obliquely with reference to a direction of advance of the aircraft. It is of course possible to apply the invention to a six-wheel undercarriage.
    According to a practical arrangement, the collar is produced between two parts assembled around a cylindrical part of the box. Advantageously provide a sliding connection without the possibility of rotation of the collar, for example by retaining a non-circular profile for the cylindrical part of the box on which the collar slides.
    The invention is not limited to what has just been described, but on the contrary covers any variant coming within the scope defined by the claims. In particular, it is possible to apply the invention to a landing gear leg braced by two struts. In addition, the collar can be ordered independently of the strut (s). Maintaining the collar in the high or low position and moving it from one to the other of the positions may be carried out by any means. One can in particular use an actuator and dedicated locking means, or even exploit the relative movement between the structure of the aircraft and the box during the maneuver of the undercarriage from the deployed position to the retracted position, for example by using a connecting rod articulated on the one hand on the structure of the aircraft and on the other hand on the collar. In general, any other relative movement making it possible to move the collar from the high position to the low position can be exploited. The connection between the collar and the element of which the relative movement is exploited can be carried out by any mechanical means such as rod, rack.
    权利要求:
    Claims (8)
    [1" id="c-fr-0001]
    1. Aircraft undercarriage carrying at least two wheels (4; 104; 204; 304), and intended to be mounted mobile on an aircraft structure between a deployed position and a retracted position, characterized in that the wheels are mounted rotating on axles (3; 103) carried by arms (2; 102; 202; 3 02) articulated in the lower part of a box (1; 101; 201; 301) of the undercarriage, each arm being associated with a shock absorber (5; 105) coupled on the one hand to the arm and on the other hand to a collar (6; 106) which extends around the box and which is slidably mounted on the box between a high position in which the collar is in abutment against a stop (7; 107) of the box when the undercarriage is in the deployed position, and a low position towards which the collar is brought during the maneuver of the undercarriage from the deployed position to the retracted position, so as to bring the wheels together.
    [2" id="c-fr-0002]
    2. Landing gear according to claim 1, wherein the collar (6; 106) is connected to an element (12; 112) of a brace (10; 110) of the undercarriage, so that the collar is moved by the effect of a relative movement of the element of the bracing member and of the box.
    [3" id="c-fr-0003]
    3. undercarriage according to claim 2, wherein the collar (6; 106) is connected by a link (4; 104) to the element (12; 112) of the bracing member which is articulated on the box (l ; 101).
    [4" id="c-fr-0004]
    4. Landing gear according to claim 1, wherein the collar is in two parts and is assembled around a cylindrical part of the box.
    [5" id="c-fr-0005]
    5. Landing gear according to claim 1, comprising two arms (2) extending longitudinally by reference to a direction of advance of the aircraft and each carrying two wheels (4).
    [6" id="c-fr-0006]
    6. Landing gear according to claim 1, comprising two arms (102) extending transversely by reference to a direction of advance of the aircraft, and each carrying a wheel (102).
    5
    [7" id="c-fr-0007]
    7. Landing gear according to claim 1, comprising four arms (202) each carrying a wheel (204), two arms (202) extending longitudinally and two arms (202) extending transversely by reference to a direction of advance of the aircraft, in a 10-cross arrangement.
    [8" id="c-fr-0008]
    8. Landing gear according to claim 1, comprising four arms (302) each carrying a wheel (304), the arms extending obliquely by reference to a direction of advance of the aircraft in a cross arrangement.
    类似技术:
    公开号 | 公开日 | 专利标题
    EP3549860B1|2020-10-28|Folding aircraft undercarriage
    EP2582578B1|2014-06-11|Main landing gear of an aircraft, comprising two walking beams joined to the structure of the aircraft in an articulated manner
    EP1581424B1|2006-08-16|Landing gear strut damper, and landing gear with independent struts comprising same
    CA2092490A1|1993-10-01|Retractable landing gear for aerodynes, especially for helicopters
    CA2744503C|2013-04-23|Device for retracting aircraft landing gear
    EP2841321B1|2016-08-03|Baby stroller frame and baby stroller with an improved folding mechanism
    CA2767857C|2014-11-18|Nose gear of an aircraft comprising a single control device for retraction and steering
    CA2116841A1|1994-09-09|Retractable landing gear for jumbo jet aircraft
    CA1315258C|1993-03-30|Undercarriage system for aircraft
    EP0385831B1|1992-07-08|Landing gear with wheels pivoting during its retraction
    WO2011157808A1|2011-12-22|Main landing gear of an aircraft, comprising two walking beams and a deformable parallelogram structure
    FR2688190A1|1993-09-10|REINFORCABLE LANDING TRAIN.
    EP0631929A1|1995-01-04|Aircraft landing gear of the sideway retraction type
    EP0705758A1|1996-04-10|Aircraft landing gear of the sideways retraction type
    EP0607721A1|1994-07-27|Retractable landing-gear for wide-body aircraft
    WO2011006747A1|2011-01-20|Double action cylinder for the steering and retraction of a landing gear
    EP0615901A1|1994-09-21|Aircraft landing gear with lateral retraction
    EP1106501A1|2001-06-13|Aircraft auxiliary nose landing gear
    EP0635426A1|1995-01-25|Aircraft landing gear with lateral retraction
    BE408511A|
    FR2713192A1|1995-06-09|Aircraft undercarriage with sideways retraction
    同族专利:
    公开号 | 公开日
    CA3038612C|2020-10-27|
    US20190308720A1|2019-10-10|
    FR3079813B1|2022-02-04|
    EP3549860A1|2019-10-09|
    CA3038612A1|2019-10-04|
    EP3549860B1|2020-10-28|
    CN110341941A|2019-10-18|
    US11167841B2|2021-11-09|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2811326A|1954-02-05|1957-10-29|Fairchild Engine & Airplane|Retractable aircraft landing gear|
    EP0631929A1|1993-07-01|1995-01-04|Messier-Eram|Aircraft landing gear of the sideway retraction type|
    WO2011157807A1|2010-06-16|2011-12-22|Messier-Bugatti-Dowty|Main landing gear of an aircraft, comprising two walking beams joined to the structure of the aircraft in an articulated manner|
    US2578200A|1948-07-26|1951-12-11|Dowty Equipment Ltd|Mechanism to minimize pitching in braked aircraft bogie undercarriages|
    US2579180A|1949-03-15|1951-12-18|Cons Vultee Aircraft Corp|Tandem-wheel shock absorbing aircraft landing gear|
    US2960289A|1958-07-07|1960-11-15|Cleveland Pneumatic Ind Inc|Aircraft landing gear|
    US2997261A|1958-07-07|1961-08-22|Cleveland Pneumatic Ind Inc|Landing gear|
    FR2961481B1|2010-06-16|2013-06-28|Messier Dowty Sa|MAIN AIRCRAFT ATTRACTOR WITH TWO BALANCERS AND DEFORMABLE PARALLELOGRAM STRUCTURE.|US11008091B2|2018-05-03|2021-05-18|The Boeing Company|Body mounted shrinking landing gear|
    GB2592204A|2020-02-18|2021-08-25|Airbus Operations Ltd|Modular landing gear|
    CN112634609A|2020-12-14|2021-04-09|成都飞航智云科技有限公司|Situation early warning system based on knowledge base|
    法律状态:
    2019-03-20| PLFP| Fee payment|Year of fee payment: 2 |
    2019-10-11| PLSC| Publication of the preliminary search report|Effective date: 20191011 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 3 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1852932A|FR3079813B1|2018-04-04|2018-04-04|AIRCRAFT LANDER WITH "UMbrella" FOLDING|
    FR1852932|2018-04-04|FR1852932A| FR3079813B1|2018-04-04|2018-04-04|AIRCRAFT LANDER WITH "UMbrella" FOLDING|
    EP19165310.4A| EP3549860B1|2018-04-04|2019-03-26|Folding aircraft undercarriage|
    CA3038612A| CA3038612C|2018-04-04|2019-03-29|Aircraft landing gear with << umbrella >> retraction|
    CN201910256953.7A| CN110341941A|2018-04-04|2019-04-01|A kind of " umbrella folding " aircraft landing gear|
    US16/375,367| US11167841B2|2018-04-04|2019-04-04|Umbrella-folding aircraft undercarriage|
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