• 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:
    Landing gear (1) for a light aircraft or an unmanned aircraft, comprising a spring-loaded telescopic strut (5) with an outer cylinder (20) and an inner cylinder (30) partially disposed in the outer cylinder (20) ), wherein the inner cylinder (30) is movable relative to the outer cylinder (20), and wherein the outer cylinder (20) and the inner cylinder (30) respectively have a rectangular cross section.
    公开号:FR3013680A3
    申请号:FR1461330
    申请日:2014-11-24
    公开日:2015-05-29
    发明作者:Johannes Tonskotter
    申请人:IABG Industrieanlagen Betriebsgesellschaft mbH；
    IPC主号:
    专利说明:

    [0001] The invention relates to an undercarriage for a light aircraft or an unmanned aircraft according to claim 1 and to the claim. 3 and an aircraft equipped with such a landing gear according to claim 20.
    [0002] As critical safety components, landing gear is subject to particularly stringent requirements regarding load capacity and reliability. Known landing gear are therefore expensive, very complex, heavy and require a lot of maintenance. This is a particular problem for ultra-light aircraft.
    [0003] The object of the present invention is therefore to provide a spring landing gear for an aircraft which, while respecting safety requirements, is technically simple, requires little or no maintenance and is inexpensive, and which Besides, it has a low weight.
    [0004] This object is achieved by the landing gear for a light aircraft or an unmanned aircraft according to claim 1 and according to claim 3, as well as by an aircraft equipped with such a landing gear according to claim 20.
    [0005] In particular, the goal is achieved by a landing gear for a light aircraft or an unmanned aircraft, comprising a spring-loaded telescopic strut with an outer cylinder and an inner cylinder partially disposed in the outer cylinder, wherein the cylinder interior is movable relative to the outer cylinder, and wherein the outer cylinder and the inner cylinder respectively have a rectangular cross section. An advantage of this is that a twisting or twisting of the inner cylinder with respect to the outer cylinder is prevented. As a result, no torsion linkage or nose gear fork is required to ensure a non-rotational connection between the outer cylinder and the inner cylinder. The landing gear is therefore technically simple, requires little or no maintenance, has a low weight and is inexpensive.
    [0006] According to another embodiment, the outer cylinder and the inner cylinder respectively have a square cross section. As a result, torsional rigidity is further increased and hence better protection against rotation of the inner cylinder relative to the outer cylinder is ensured.
    [0007] In particular, the goal is achieved by a landing gear for an aircraft, comprising a spring loaded telescopic strut with an outer cylinder and an inner cylinder partially disposed in the outer cylinder, wherein the inner cylinder is movable relative to the outer cylinder, and wherein the outer cylinder and / or the inner cylinder are made of an aluminum alloy, in particular with high strength. An advantage of this is that the landing gear has a low weight and requires little or no maintenance. In addition, the landing gear is technically simple.
    [0008] The landing gear is partially or fully retractable in the aircraft. As a result, only minimal additional resistance, or no additional resistance, is caused in flight by the landing gear. According to another embodiment of the invention, the telescopic spring strut comprises an elastomeric spring element, in particular a self-damping elastomeric spring element, for damping movements of the inner cylinder relative to the outer cylinder. . An advantage of this is that the landing gear maintenance demand is further reduced. In addition, the weight of the landing gear is further reduced. In addition, there is no need here for a hydraulic system, which is particularly heavy and difficult to maintain. This reduces weight and lowers maintenance costs. The outer surface of the inner cylinder may comprise several layers, in particular nickel with PTFE inclusions. In this way, an outer surface of the inner cylinder is formed which is particularly hard and resistant to wear. As a result, maintenance costs decrease further. In addition, the life of the landing gear is increased. In addition, the resistance due to friction between the outer cylinder and the inner cylinder is thus reduced. This results in less wear. According to another embodiment, the landing gear comprises a scraper ring adapted to the shape of the outer and inner cylinder to prevent the penetration of sludge and / or dust into the interior space of the outer cylinder. In this way, fouling of the interior space of the outer cylinder is essentially technically prevented. This increases the safety of the landing gear, because the resistance due to friction between the outer cylinder and the inner cylinder is not changed because of the penetration or the presence of mud, dust and / or foreign substances .
    [0009] The landing gear may further include an electric linear actuator for retracting the landing gear into the aircraft and for removing the landing gear from the aircraft. In this way, the electrical function of retraction and exit of the landing gear is technically simple. In addition, there is no need for a hydraulic system, which is particularly heavy and difficult to maintain. This reduces weight and lowers maintenance costs. The linear actuator may include electronically adjustable limit switches. It is thus possible to observe in a technically simple and safe way the complete retraction or the complete exit of the landing gear. The linear actuator can be mounted floating. An advantage of this arrangement is that the landing gear can be pulled out and retracted unmistakably, even in the event of severe fluctuations in temperature. In addition, further actuation of the articulated spacer during retraction and exit may be omitted. The landing gear may further comprise a mechanical and / or electrical locking device for locking the landing gear in the retracted state. This ensures that the landing gear remains securely in the retracted position during flight. This increases the operational safety. In addition, the landing gear may include an unlocking device for the electrical and / or manual release of the landing gear from the locked state. This makes it technically simple to release the landing gear, if necessary also in case of emergency or in case of power failure. The landing gear can be configured such that, after release of the lock in the retracted state, the landing gear can move into the released state by gravity. Thus, even in the case of power interruption and / or mechanical problems, the landing gear can be safely removed.
    [0010] According to another embodiment, the landing gear comprises an articulated spacer for locking the landing gear in the outgoing state, the articulated spacer being configured in such a way that the articulated spacer is folded during re-entry of the landing gear. In this way, a secure locking of the landing gear in the released state is ensured in a technically simple manner. According to another embodiment, the landing gear comprises a wheel, the orientation of the wheel or the axis of the wheel relative to the aircraft can be modified. In this way, the control of the aircraft on the ground is possible in a technically simple manner, in particular for a front wheel of the landing gear. According to another embodiment, the landing gear further comprises a return torsion spring for the return of the wheel in the direction of flight of the aircraft when the wheel is not loaded. This ensures that when the wheel is not loaded, the wheel is oriented in a predetermined direction, namely the flight direction of the aircraft. In particular when the landing gear is retracted, the wheel is thus in a predetermined position. This is also the case during landing in the out of gear state.
    [0011] According to another embodiment, the landing gear comprises an electric rotation actuator for adjusting the orientation of the wheel or the axis of the wheel relative to the aircraft. In particular when the landing gear is retracted, the wheel can thus be moved to a predetermined position. During landing, the wheel or the wheel axle may be oriented in the outbound state in a predetermined direction relative to the aircraft. In addition, during taxiing, that is to say during a slow movement of the aircraft or the aircraft on the ground, the orientation of the wheel relative to the aircraft or to the aircraft can be modified (actively) and the aircraft or aircraft can be guided.
    [0012] According to another embodiment, the landing gear comprises a signal transmission device for transmitting a fault signal to a display device in the event of a failure of the landing gear functionality, in particular in the event of failure of the landing gear output electrical function. In this way, a fault message can be displayed or transmitted for example in the cockpit in the event of landing gear failure. In addition, the display device indicates, in case of mechanical output of the landing gear, whether the landing gear has been fully extended or to what degree (output) the landing gear is precisely. discloses and claims also an ultra-light airplane or a light aircraft or an aircraft, in particular an unmanned aircraft, equipped with a landing gear having one of the aforementioned combination of features or more than one of the aforementioned combination of features.
    [0013] Preferred embodiments flow from the secondary claims. The invention will be explained in more detail below with the aid of drawings illustrating exemplary embodiments, in which: Figure 1 is a perspective view of an embodiment of the landing gear according to the invention; Figure 2 is a partially transparent perspective view of a portion of the landing gear of Figure 1; Figure 3 is a perspective view of another embodiment of the landing gear according to the invention; and Figure 4 is a partially transparent perspective view of a portion of the landing gear of Figure 3. In the following description, the same numerical references were used for identical or equivalent parts. Figure 1 shows a perspective view of an embodiment of the landing gear 1 according to the invention. Landing gear 1 is a main landing gear of an aircraft (not shown). Landing gear 1 is retractable in the aircraft. In Figure 1, the landing gear is shown in the extended state. The main landing gear 1 comprises a telescopic spring strut 5 with an upper outer cylinder 20 and a lower inner cylinder 30, which is partially in the upper outer cylinder 20. In principle, it is also conceivable that the lower cylinder is the outer cylinder and the upper cylinder is the inner cylinder. The inner cylinder 30 is movably or slidably disposed along the longitudinal direction of the outer cylinder 20 or along the longitudinal direction of the inner cylinder 30 (in FIG. 2 essentially from top to bottom or from bottom to top). The lower inner cylinder 30 comprises a main wheel half-fork 13, to which a main wheel 10 is fixed by means of a wheel axle 15, so that the wheel 10 can rotate about the wheel axle 15 Instead of the wheel or in addition to the wheel, one can imagine a ski skate and / or a float, which floats on the water. This is valid for the front wheel 70 as well as the main wheel 10. The landing gear 1 can be electrically actuated.
    [0014] The upper outer cylinder 20 and the lower inner cylinder 30 have a rectangular cross-section or a rectangular cross-sectional area. The cross-section or the cross-sectional area may in particular be square. The cross section refers to a cross section that is perpendicular to the outer surface of the outer cylinder 20 or the inner cylinder 30. The cross sectional area extends in Figure 1 or Figure 2 parallel to the axis of rotation 45. When the airplane is on the ground, the cross-sectional area extends parallel to the ground surface.
    [0015] The size or shape of the inner cylinder 30 is adapted to the size and shape of the outer cylinder 20, so that there is only a zero or small distance (adjustment with play) between the outer cylinder 20 and the portion of the inner cylinder 30 therein.
    [0016] Due to the rectangular or square shape of the cross section of the outer cylinder 20 and the inner cylinder 30, a torsional rigidity is reached between the two cylinders 20, 30. A torsion linkage as in the conventional landing gear n ' is not necessary. Similarly, one can save or omit a front wheel fork or torsion rod. Figure 2 shows a partially transparent perspective view of a landing gear portion 1 of Figure 1, in which the outer surfaces the telescopic strut spring 5 are transparent or translucent, so that the internal structure is visible. The internal structure of the outer cylinder 20 and the inner cylinder 30 is visible in FIG. 2. The landing gear 1 is pivotally mounted about a return / exit axis of rotation 45. The axis of rotation of Inlet / outlet 45 is disposed at the upper end (in FIG. 1 and FIG. 2) of the outer cylinder 20. The outer cylinder 20, the inner cylinder 30 with the main wheel half-fork 13 and the main wheel 10 can be rotated about this axis 45. Through the outer cylinder 20 and through the inner cylinder 30, there is an uninterrupted elastomeric spring element 35. The elastomeric spring element 35 extends in FIG. the axis of rotation of return / exit 45 to the lower end of the inner cylinder 30, to which the main wheel half-fork 13 is mounted or fixed. One end of the elastomeric spring member 35 touches the upper end of the upper outer cylinder 20 respectively the in-turn / exit rotational axis 45. The other end (lower end) of the elastomeric spring member 35 touches the lower end of the lower inner cylinder 30. The elastomeric spring element 35 has a plurality of individual cylindrical elements 37 with separating disks 36, which are arranged in a series. The individual elements 37 each have the same distance from each other. The separation discs 36 are made in the form of circular discs. The individual elements 37 are made in the form of cylinders. The separation discs 36 have a larger diameter than the individual members 37. The separation discs 36 are spacers, which separate the individual members 37 from one another and guide them. The elastomeric spring element 35 is intended to damp the movement or displacements of the inner cylinder 30 with respect to the outer cylinder 20. For example, when the wheel 10 is placed on the landing strip, the cylinder The inner cylinder 30 is subjected to a force, by which the inner cylinder 30 is moved towards the outer cylinder 20. The inner cylinder 30 is pushed further into the outer cylinder 20. The telescopic spring strut is compressed. The lower end of the inner cylinder 30 is in contact with the lower end of the elastomeric spring element 35. The lower end of the inner cylinder 30 pushes against the elastomeric spring element 35, when the telescopic strut The force acting on the elastomeric spring member 35 compresses the elastomeric spring member 35. This movement or force is dampened by the elastomeric spring element 35, such that the movement is only partially retransmitted to the outer cylinder 20 or to the upper end of the outer cylinder 20, which is in contact with the upper end of the spring element Elastomer 35. Movements of the lower inner cylinder 30 are thus only damped retransmitted to the upper outer cylinder 20 and by are also only damped to the chassis of the aircraft. The elastomeric spring member 35 is made of an elastic material, for example a rubber material. Due to the elastomeric spring element 35, the movement between the inner cylinder 30 and the outer cylinder 20 is sufficiently damped, so that the main wheel half-fork 13 does not strike the end of the outer cylinder 20, when the plane is touching down. A scraper ring 22 is disposed at the lower end of the outer cylinder 20. The scraper ring 22 is adapted to the shape and size of the inner cylinder 30, the outer cylinder 20 and the elastomeric spring member 35. The scraper ring 22 has cutouts such that there remains on the underside of the outer cylinder 20 an opening, through which the inner cylinder 30 extends. The scraper ring 22 is intended to ensure the tightness of the the inner space of the outer cylinder 20. This prevents foreign substances, such as sludge and / or dust, from entering the inner space of the outer cylinder 20 or between the inner cylinder portion 30, which it is found inside the outer cylinder 20, and the outer cylinder 20. This ensures that the friction and wear between the inner cylinder 30 and the outer cylinder 20 remain low. The telescopic spring strut or the outer cylinder 20 and / or the inner cylinder 30 are made of a high strength aluminum alloy. The outer surface of the lower inner cylinder 30 is manufactured by a multilayer process to produce the desired or controlled sliding ability. In particular, the multilayer process comprises nickel deposition with inclusion (s) of PTFE, that is to say inclusions of polytetrafluoroethylene. This results in lower wear of the lower inner cylinder 30. The inner surface of the upper outer cylinder 20 comprises a low wear hard nickel layer. Landing gear 1 is retractable into the aircraft and extendable out of the aircraft. The landing gear 1 can be partially retractable in the aircraft or fully retractable in the aircraft. The landing gear 1 comprises an articulated spacer 50, with a hinge 52 which is located approximately in the middle of the articulated spacer 50. The articulated spacer 50 is connected at one of its ends to the upper outer cylinder 20 at the end. bottom of it. At the other end of the articulated spacer 50, there is a linear actuator 40 connected to the articulated spacer. The linear actuator 40 moves a telescopic actuator member 42 or spacer, which is attached to the in / out rotation axis 45 such that the in / out rotational axis 45 can rotate. relative to the telescopic actuator member 42. The distance from the linear actuator 40 to the retractable / output rotational axis 45 can be varied by means thereof, or the telescopic actuator element. 42 of this spacer. In Figure 1, there is shown the maximum distance of the linear actuator 40 to the axis of rotation of return / exit 45, for which the articulated spacer 52 is fully compressed. The articulated spacer 50 may in particular be biased by a spring. With a torsion spring, the hinged spacer 50 is locked in the unfolded or extended position without other devices. For retraction of the landing gear 1, the linear actuator 40 moves towards the axis of rotation of return / exit 45. As a result, the articulated spacer 50 is folded by means of the hinge 52. As a result, the upper outer cylinder 20 and the lower inner cylinder 30 rotate together about the axis of rotation 45. In the fully retracted state, the upper outer cylinder 20 is in a rotated position of about 90 ° around of the return / exit axis of rotation 45 in comparison with the position shown in FIG. 1. The position shown in FIG. 1 represents the position on landing or while taxiing the aircraft on the ground surface. . The electric linear actuator 40 is floatably mounted. This means that the electric linear actuator 40 itself is not assembled directly to (the aircraft fuselage) or is not directly attached thereto. The electric linear actuator 40 is connected to (the fuselage of) the aircraft by the telescopic actuator member 42 and the return / exit rotation axis 45. The telescopic actuator member 42 is connected by a end (left in Figure 1) to the axis of rotation of return / exit 45 and the opposite end opposite (right in Figure 1) to the electric linear actuator 40. The linear actuator 40 is connected to a end of the articulated spacer 50. The other end of the articulated spacer 50 is connected to the lower end of the upper outer cylinder 20. The articulated spacer 50, the upper outer cylinder 20 and the telescopic actuator element 42 and the linear actuator 40 form a triangle. Even when stresses or slight bends appear, for example due to temperature variations, the telescopic actuator member 42 is securely retracted into the linear actuator 40 or reliably pulled out of it. ci and thus the landing gear 1 is returned or safely released. The electric linear actuator 40 has electronically adjustable limit switches. By means of these limit switches, the retracted position and the landing gear 1 output position can be ascertained in a technically simple and reliable manner. The landing gear 1 further has a mechanical lock (not shown), by means of which the landing gear 1 can be locked in the retracted position. The lock can be unlocked or released electrically or, in an emergency, mechanically. In addition, the landing gear 1 has a mechanical emergency unlocking for the landing gear 1 output by the action of gravity. In addition, the landing gear 1 comprises a signal transmission device (not shown), which produces a fault signal when the landing gear 1 functionality fails, particularly in the case of a landing gear. failure of the function of the electric control of the landing gear 1 output by means of the linear actuator 40. This fault signal can for example be transmitted to a display (LED) in the cockpit, which lights up correspondingly in case of disappearance of the (electric) maneuverability of the landing gear 1 and which also displays, during emergency unlocking, the state of the landing gear. In particular, this display (LED) of the signal transmission device and the signal transmission device are fed globally by a backup power supply. The outer surface of the lower inner cylinder 30 is manufactured by a multilayer process to achieve the desired or controlled sliding ability. In particular, the multilayer process comprises nickel deposition with inclusion (s) of PTFE, that is to say inclusions of polytetrafluoroethylene. This results in less wear of the lower inner cylinder 30. The inner surface of the upper outer cylinder 20 comprises a hard, low wear nickel layer.
    [0017] Figure 3 shows a perspective view of another embodiment of the landing gear 1 according to the invention. Figure 4 shows a partially transparent perspective view of a portion of the landing gear 1 of Figure 3, in which outer surfaces of the telescopic spring strut 5 or the landing gear 1 are transparent or translucent so that the internal structure is visible. The landing gear 1 according to FIGS. 3 and 4 is made analogously to the landing gear of FIGS. 1 and 2. As for the landing gear according to FIGS. 1 and 2, the telescopic strut with spring or the outer cylinder 20 and the inner cylinder 30 are made of a high strength aluminum alloy. In the embodiment illustrated in FIGS. 3 and 4, PTFE sliding bushings are driven into the outer cylinder 20. The outer surface of the lower inner cylinder 30 and the inner surface of the upper outer cylinder 20 each comprise a layer of nickel. hard, low wear. Figure 3 shows a landing gear before an airplane. The spring loaded telescopic strut 5 of the landing gear 1 has an upper outer cylinder 20 and a lower inner cylinder 30. The cross-section or the cross-sectional area of the outer cylinder 20 and the inner cylinder 30 are substantially circular. The cross-section relates to a cross section, which extends perpendicularly to the outer surface of the outer cylinder 20 or inner cylinder 30. The cross-sectional area extends, in FIG. 3 and FIG. Return / exit rotation axis 45. When the aircraft is on the ground, the cross-sectional area is slightly inclined with respect to the ground surface.
    [0018] The lower inner cylinder 30 is rotatable relative to the outer cylinder 20, about the longitudinal axis of the inner cylinder 30, which is parallel to the longitudinal axis of the outer cylinder 20. To minimize friction and wear, the outer cylinder 20 has in the lower region sliding bushes, for example made of PTFE, in which the inner cylinder 30 is rotatably mounted. The upper outer cylinder 20 is prevented from rotating / fixed without rotation to the aircraft. At the lower end of the inner cylinder 30 there is a front wheel fork 75 which carries a rotatable front wheel 70.
    [0019] The landing gear comprises an articulated spacer 50, which however is behind (on the right in FIG. 3) the upper outer cylinder 20. The articulated spacer 50 extends in service parallel to the longitudinal axis of the aircraft . The two ends of the articulated spacer 50 are connected to the upper outer cylinder 20 respectively to the electric linear actuator 40 (electric motor). In FIG. 3, the linear actuator 40 is assembled (fixedly) to the aircraft by the hinge of the articulated spacer 50. The linear actuator 40 moves a telescopic actuator member 42 outwardly or toward the The other end of the telescopic actuator member 42 is connected to a lever member 47, which is rotatably connected to the return / exit rotation axis 45. retraction of the landing gear 1, the linear actuator 40 attracts the telescopic actuator member 42 towards it, which rotates the lever element 47 about the axis of rotation of in / out 45. Of this In this manner, the articulated spacer 50 is folded and the upper outer cylinder 20 and the lower inner cylinder 30 are retracted into the aircraft (to the right and upwards in Figure 3). The landing gear 1 has, for the return of the front wheel 70 in the direction of flight, a torsion spring 80 acting in both directions. The torsion spring 80 acts on the nosewheel 70 through a torsion bar 85 in the spring loaded telescopic strut 5. Particularly in unmanned aircraft, the landing gear 1 may the place thereof include an electric rotation actuator, which recalls the front wheel 70 in the direction of flight. By means of the electric rotation actuator, the nose wheel 70 may be oriented at any angle to the direction of flight of the aircraft. The landing gear 1 also has, as can be seen in FIG. 4, an elastomer spring element 35. The scraper ring 22 is adapted to the circular shape of the cross section of the lower inner cylinder 30 and the outer cylinder upper and thus ensures the sealing of the lower opening of the upper outer cylinder 20.
    [0020] In particular, the landing gear 1 is suitable for aircraft, particularly for light aircraft and / or ultra-light airplanes and / or unmanned aircraft, called drones (unmanned aerial vehicle, unoccupied or unmanned aerial vehicle) . The landing gear 1 is preferably suitable for aircraft of this nature, which are propelled electrically. The landing gear 1 is particularly suitable for ultra-light aircraft up to about 450 kg initial mass. The landing gear 1 is also suitable for a multiplicity of aircraft, which are not planes literally, that is to say also for example for rotorcraft, gyros, helicopters. Due to the retractability of the landing gear 1, the aerodynamics of the aircraft is improved and the resistance of the air during the flight is reduced.
    [0021] A light aircraft and / or an ultra-light airplane and / or an unmanned aircraft with a main landing gear according to the first embodiment shown in Figure 1 and Figure 2 and described in the corresponding description, and with a landing gear according to the embodiment which is shown in Figure 3 and Figure 4 and described in the corresponding description. Digital reference list 1 landing gear 5 telescopic spring strut 10 main wheel 13 main wheel half-fork 15 wheel axle 20 outer cylinder 22 scraper ring 30 inner cylinder elastomer spring element 36 separating discs 37 elements individual actuator linear actuator elastomer spring member 42 telescopic actuator member retraction / output rotation axis 47 articulated spacer lever member 52 articulated spacer hinge
    权利要求:
    Claims (1)
    [0001]
    CLAIMS1 / Landing gear (1) for a light aircraft or an unmanned aircraft, comprising a telescopic spring strut (5) with an outer cylinder (20) and an inner cylinder (30) partially disposed in the outer cylinder (20), wherein the inner cylinder (30) is movable relative to the outer cylinder (20), and wherein the outer cylinder (20) and the inner cylinder (30) respectively have a rectangular cross section. Landing gear (1) according to claim 1, characterized in that the outer cylinder (20) and the inner cylinder (30) have a square cross-section, respectively. Landing gear (1) for an aircraft, comprising a spring-loaded telescopic strut (5) with an outer cylinder (20) and an inner cylinder (30) partially disposed in the outer cylinder (20), wherein the cylinder interior (30) is movable relative to the outer cylinder (20), and wherein the outer cylinder (20) and / or the inner cylinder (30) are made of an aluminum alloy. Landing gear (1) according to any one of the preceding claims, characterized in that the landing gear (1) is partially or fully retractable in the aircraft. Landing gear (1) according to one of the preceding claims, characterized in that the telescopic spring strut (5) comprises an elastomeric spring element (35), in particular a self-damping elastomeric spring element. (35) for damping movements of the inner cylinder (30) relative to the outer cylinder (20). Landing gear (1) according to any one of the preceding claims, characterized in that the outer surface of the inner cylinder (30) comprises several layers, in particular nickel with PTFE inclusions. 10/15 3/20 4/25 5/30 6/357 / Landing gear (1) according to any one of the preceding claims, characterized in that the inner surface of the outer cylinder (20) has a layer of nickel. 8 / Landing gear (1) according to any one of the preceding claims, characterized in that the landing gear (1) comprises a scraper ring (22) adapted to the shape of the outer cylinder and the inner cylinder ( 30) to prevent the entry of sludge and / or dust into the interior space of the outer cylinder (20). 9 / Landing gear (1) according to any one of the preceding claims, characterized by an electric linear actuator (40) for retracting the landing gear (1) in the aircraft and for removing the landing gear ( 1) off the plane. 10 / landing gear (1) according to any one of the preceding claims, in particular according to claim 9, characterized in that the linear actuator (40) comprises electronically adjustable limit switches. 11 / landing gear (1) according to any one of the preceding claims, in particular according to claim 9 or 10, characterized in that the linear actuator (40) is mounted floating. 12 / landing gear (1) according to any one of the preceding claims, in particular according to any one of claims 4 to 11, characterized by a mechanical and / or electric locking device for locking the landing gear (1) in the retracted state. 13 / Landing gear (1) according to any one of the preceding claims, in particular according to claim 12, characterized by an unlocking device for the electric and / or manual release of the landing gear (1) from of the blocked state. 3514 / Landing gear (1) according to any one of the preceding claims, in particular according to claim 12 or 13, characterized in that the landing gear (1) is configured in such a way that, after the release of the locking in the retracted state, the landing gear (1) is movable in the released state by means of gravity. 15 / Landing gear (1) according to any one of the preceding claims, characterized by an articulated spacer (50) for locking the landing gear (1) in the extended state, in which the articulated spacer ( 50) is configured in such a way that the articulated spacer (50) is folded when the landing gear (1) is retracted. 16 / landing gear (1) according to any one of the preceding claims, in particular according to any one of claims 3 to 15, characterized in that the landing gear (1) comprises a wheel (70), wherein the orientation of the wheel (70) relative to the aircraft is variable. 17 / landing gear (1) according to any one of the preceding claims, in particular according to claim 16, characterized by a return torsion spring for the return of the orientation of the wheel (70) in the direction of flight of the aircraft when the wheel (70) is not loaded. 18 / landing gear (1) according to any one of the preceding claims, in particular according to claim 16, characterized by an electric rotation actuator for adjusting the orientation of the wheel (70) relative to the plane. 19 / landing gear (1) according to any one of the preceding claims, characterized by a signal transmission device for transmitting a fault signal to a display device in the event of a failure of the functionality of the landing gear (1), in particular in case of failure of the landing gear output electric function (1). 20 / Aircraft equipped with a landing gear (1) according to any one of the preceding claims.
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    同族专利:
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    引用文献:
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    EP3135581B1|2015-08-25|2018-03-21|Safran Landing Systems UK Limited|Aircraft landing gear assembly|
    EP3375708A1|2017-03-17|2018-09-19|Safran Landing Systems UK Limited|Aircraft landing gear assembly|
    CN108438212A|2018-01-18|2018-08-24|倪惠芳|A kind of UAV Landing auxiliary device|
    CN108557060B|2018-04-28|2019-03-12|泊鹭（荆门）飞机有限公司|A kind of damping undercarriage|
    CN109050887B|2018-08-22|2020-04-03|晨龙飞机（荆门）有限公司|Aircraft undercarriage with reserve braced system|
    CN112550685A|2020-12-24|2021-03-26|王允|Emergency landing gear of airplane|
    法律状态:
    2015-11-30| PLFP| Fee payment|Year of fee payment: 2 |
    2016-11-29| PLFP| Fee payment|Year of fee payment: 3 |
    2017-11-29| PLFP| Fee payment|Year of fee payment: 4 |
    2019-11-26| PLFP| Fee payment|Year of fee payment: 6 |
    2021-08-06| ST| Notification of lapse|Effective date: 20210706 |
    优先权:
    申请号 | 申请日 | 专利标题
    DE201320105380|DE202013105380U1|2013-11-26|2013-11-26|Chassis for a light aircraft or an unmanned aerial vehicle and aircraft with such a chassis|
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