Door retraction device for landing gear of an aircraft

Abstract

The application discloses a hatch retraction device for landing gear of an aircraft, the aircraft comprising a landing gear rotatably mounted within a cabin of the aircraft, and two facing hatches adapted to close the cabin when the landing gear is retracted; the hatch retraction device of the landing gear comprises two retraction mechanisms respectively cooperating with the hatches, each retraction mechanism comprising a connecting part, a first end of the connecting part being rotatably connected with the landing gear; a base, the base being mounted inside the cabin; a transmission part, the transmission part being mounted on the base, a second end of the connecting part being rotatably mounted to the transmission part; and a hinge part, a first end of the hinge part being connected with the transmission part, a second end of the hinge part being connected with the hatch, rotation of the landing gear in a longitudinal vertical plane driving the hinge part to rotate in a transverse vertical plane relative to the base through the connecting part and the transmission part, so that the hatch is switched between an open state of opening the cabin and a closed state of closing the landing gear in the cabin.

Description

Technical Field

[0001] At least one embodiment of the present invention relates to the field of aircraft landing gear and door technology, specifically to a door retraction device for aircraft landing gear. Background Technology

[0002] In traditional aircraft, such as airplanes and drones, landing gear is used for landing, takeoff, and movement on the ground. After takeoff, for flight safety, the landing gear needs to be retracted into the fuselage through an opening, and then closed by a door located at the bottom of the aircraft. With the door open, it opens outwards to the underside of the aircraft's fuselage, exposing an opening that allows the landing gear to be lowered to the outside. Generally, the lowering and retraction of the landing gear is performed independently of the door opening and closing operation, requiring a separate door retraction mechanism.

[0003] Furthermore, most aircraft employ traditional swing-door opening and closing structures, with the door standing vertically beneath the fuselage when open. However, flying-wing aircraft lack a vertical tail and rudder; their directional control relies primarily on ailerons or drag rudders on the outer wing sections, achieved through specific combinations and opening / closing angles to perform yaw maneuvers and maintain yaw stability. Because the door stands vertically beneath the fuselage, it forms a control surface with forces similar to the vertical tail and rudder. When crosswinds or UAV sideslip occur, the aerodynamic forces acting on this control surface additionally increase the aircraft's yaw moment, making directional control difficult and requiring larger control surface deflection angles to perform yaw maneuvers and regain stability. The presence of this control surface is detrimental to the yaw stability of flying-wing aircraft. Therefore, applying the traditional swing-door opening and closing structure to flying-wing aircraft places an increased burden on the structural strength design of the ailerons or drag rudders and on the aircraft's flight control. Summary of the Invention

[0004] In view of this, the present invention provides a door retraction device for the landing gear of an aircraft, which eliminates the need for an additional power source to drive the door opening and closing, thus simplifying the aircraft system.

[0005] According to an embodiment of the present invention, a landing gear door retraction device for an aircraft is provided. The aircraft includes landing gear rotatably mounted in the aircraft's cabin and two facing doors adapted to close the cabin when the landing gear is retracted. The landing gear door retraction device includes two retraction mechanisms that respectively cooperate with the doors. Each retraction mechanism includes: a connecting portion, a first end of which is rotatably connected to the landing gear; a base, mounted inside the cabin; a transmission portion, mounted on the base, a second end of which is rotatably mounted to the transmission portion; and a hinge portion, a first end of which is connected to the transmission portion and a second end of which is connected to the door. The rotation of the landing gear in a longitudinal vertical plane drives the hinge portion to rotate relative to the base in a transverse vertical plane through the connecting portion and the transmission portion, thereby switching the door between an open state with the cabin open and a closed state with the landing gear enclosed in the cabin.

[0006] According to an embodiment of the present invention, the transmission part includes: a drive part, which is coupled to the second end of the connecting part; and a rotating part, which includes a gear shaft rotatably mounted on the base and extending in the longitudinal direction, the first end of the hinge part being mounted to the rotating part, the drive part being coupled to the rotating part, such that the connecting part drives the rotating part to rotate through the drive part, thereby driving the hatch to switch between an open state and a closed state.

[0007] According to an embodiment of the present invention, the drive unit includes: a guide rail mounted on the base and extending in a vertical direction; and a rack movably mounted on the guide rail, with a second end of a connecting portion rotatably mounted to the rack, such that rotation of the landing gear relative to the cabin drives the rack to move linearly in the vertical direction via the connecting portion; the rotating unit further includes a gear connected to the gear shaft, the gear meshing with the rack.

[0008] According to an embodiment of the present invention, the second end of the connecting portion is rotatably mounted to a plug extending horizontally from the side of the rack, the extension direction of the plug being perpendicular to the extension direction of the gear shaft, such that the extension direction of the teeth of the gear is perpendicular to the extension direction of the teeth of the rack.

[0009] According to an embodiment of the present invention, the connecting part includes: a connecting rod, the first end of which is rotatably connected to the driving part; and a pin, one end of which is rotatably connected to the second end of the connecting rod, and the other end of which is rotatably connected to the landing gear.

[0010] According to an embodiment of the present invention, the connecting rod includes a first connecting rod and a second connecting rod respectively connected to the drive unit and the pin shaft, wherein the first connecting rod and the second connecting rod are adjustablely connected to change the length of the connecting rod.

[0011] According to an embodiment of the present invention, the second end of the connecting rod is provided with two support arms extending in the axial direction of the connecting rod, and the pin includes a first shaft rotatably mounted on the two support arms and a second shaft extending vertically from the middle of the first shaft, the second shaft being rotatably connected to the landing gear.

[0012] According to an embodiment of the present invention, the rack includes: a base; and a strip-shaped boss protruding from the base, wherein a plurality of teeth of the rack are horizontally formed on the end face of the boss; the guide rail is provided with a sliding groove adapted to slide with the base and the boss of the rack respectively and extending in a vertical direction, wherein a receiving hole is provided on the side wall of the sliding groove that engages with the boss and extends transversely through the side wall; and a locking assembly is installed inside the receiving hole and configured to lock the gear when the hatch is in the open state.

[0013] According to an embodiment of the present invention, the locking assembly includes: a connecting post extending axially from the gear; a locking member rotatably mounted inside the receiving hole; and a driving member rotatably mounted inside the receiving hole, configured to drive the locking member to rotate between a locked state and a released state; in the locked state, the locking member engages with the connecting post to prevent the gear from driving the hinge portion to rotate in a direction that allows the hatch to close, thereby keeping the hatch in an open state; in the released state, the locking member disengages from the connecting post to allow the gear to drive the hinge portion to rotate.

[0014] According to an embodiment of the present invention, the locking component includes: a first turntable rotatably mounted inside the receiving hole via a first rotating shaft; a locking arm extending outward along the tangential direction of the first turntable; and a locking hook formed at the end of the locking arm, which rotates with the first turntable between a locked state in which the locking hook is engaged with the connecting post and a released state in which the locking hook is disengaged from the connecting post.

[0015] According to an embodiment of the present invention, the connecting post has an engagement groove extending in the axial direction for engaging with the locking hook.

[0016] According to an embodiment of the present invention, the driving component includes: a second turntable rotatably mounted inside the receiving hole via a second rotating shaft and engaging with the first turntable to drive the first turntable to rotate; a cam portion extending radially from the outer edge of the second turntable and configured to engage with the rack; and an energy storage component mounted on the second rotating shaft and configured to have an energy storage state and an energy release state; during the process of the landing gear retracting and driving the rack to rise, the rack engages with the cam portion to drive the second turntable to rotate, causing the locking component to separate from the connecting post, while the energy storage component enters an energy storage state to store kinetic energy; when the landing gear is lowered to the point where the hatch is in the open state, the rack separates from the cam portion to allow the energy storage component to release kinetic energy and drive the second turntable to rotate in the opposite direction, causing the locking hook of the locking component to engage in the engagement groove of the connecting post, thereby preventing the gear from rotating further.

[0017] According to an embodiment of the present invention, the energy storage component is a torsion spring, and the upper part of the rack is provided with a slot; during the upward movement of the rack, the bottom of the slot engages with the cam portion, causing the cam portion to drive the second turntable to rotate against the torque of the torsion spring and store kinetic energy, and the locking component separates from the connecting post; during the downward movement of the rack, the cam portion enters the slot under the torque of the torsion spring, causing the second turntable to rotate in the opposite direction and drive the locking component to engage with the connecting post.

[0018] According to an embodiment of the present invention, a first meshing tooth is formed on the first turntable, which is distributed in the circumferential direction, and a second meshing tooth is formed on the second turntable, which meshes with the first meshing tooth.

[0019] According to an embodiment of the present invention, the gear includes a plurality of third meshing teeth arranged consecutively on a portion of the outer periphery of the gear, and a fourth meshing tooth spaced apart from the first or last end of the plurality of third meshing teeth; wherein, during the initial upward movement of the rack, the rack engages with the driving component, causing the locking component to disengage from the connecting post, and the rack engages with the fourth meshing tooth to drive the gear to rotate past the interval to engage with the third meshing tooth; when the rack moves downward to the position where it completes engagement with the third meshing tooth, the locking component engages with the connecting post and enters a locked state to prevent the gear from continuing to rotate, while the rack can continue to move downward.

[0020] According to an embodiment of the present invention, a stop block extending in a radial direction is further formed at the end of the gear shaft, and a protrusion is formed on the outer side of the base so that when the landing gear is lowered to the open position of the hatch, the stop block abuts against the protrusion to prevent the gear from continuing to rotate, thereby preventing the hatch from opening further.

[0021] According to an embodiment of the present invention, during the opening of the cabin or the closing process of enclosing the landing gear within the cabin, the geometric plane of the cabin door is substantially parallel to the ground.

[0022] According to embodiments of the present invention, the present invention also provides an aircraft, comprising: a plurality of cabins, each cabin having an opening; a plurality of landing gears rotatably mounted in the plurality of cabins of the aircraft, each landing gear having a lowered state extending to the outside of the cabin through the opening and a retracted state retracted to the inside of the cabin; a plurality of doors, each cabin having a set of doors adapted to open or close the opening; and a plurality of door retraction devices for the landing gear of the aircraft as described in the above embodiments, each door retraction device being connected between the door and the landing gear, such that when the landing gear transitions between the lowered state and the retracted state, the door retraction device drives the door to transition between an open state and a closed state.

[0023] According to the above embodiments of the landing gear door retraction device for aircraft, the rotation of the landing gear in the longitudinal vertical plane drives the hinge portion to rotate relative to the base in the transverse vertical plane via the connecting portion and the transmission portion, thereby switching the door between an open state with the cabin open and a closed state with the landing gear enclosed within the cabin. On the one hand, the opening and closing of the door is driven by the lowering and retraction of the landing gear, eliminating the need for a separate power source to control the door's opening and closing. In other words, the landing gear door retraction device of the above embodiments allows the door to open or close as the landing gear is lowered or retracted, without requiring an additional power source to drive the door's opening and closing, thus simplifying the aircraft system. Attached Figure Description

[0024] Figure 1 This is a partial perspective view of an aircraft according to an embodiment of the present invention with the landing gear enclosed within the cabin and the hatch closed.

[0025] Figure 2 This is a partial perspective view of an aircraft in the open state of the landing gear doors and the cabin, according to an embodiment of the present invention.

[0026] Figure 3 This is a first-view perspective perspective schematic diagram of the retraction mechanism of a landing gear door retraction device for an aircraft, according to an embodiment of the present invention.

[0027] Figure 4 This is a second-view perspective perspective schematic diagram of the retraction mechanism of a landing gear door retraction device for an aircraft, according to an embodiment of the present invention.

[0028] Figure 5 This is a perspective view of the guide rail for a landing gear door retraction device for an aircraft, according to an embodiment of the present invention.

[0029] Figure 6 This is an assembly diagram of the rack and pinion of a landing gear door retraction device for an aircraft, according to an embodiment of the present invention.

[0030] Figure 7 This is a perspective view of the linkage of a landing gear door retraction device for an aircraft according to an embodiment of the present invention;

[0031] Figure 8 This is a perspective view of the pin of a landing gear door retraction device for an aircraft according to an embodiment of the present invention;

[0032] Figure 9 This is an assembly diagram of the rotating part and connecting column of a landing gear door retraction device for an aircraft according to an embodiment of the present invention;

[0033] Figure 10 This is a perspective view of the hinge of a landing gear door retraction device for an aircraft according to an embodiment of the present invention;

[0034] Figure 11 This is a perspective view of the drive component of a landing gear door retraction device for an aircraft, according to an embodiment of the present invention;

[0035] Figure 12 This is a perspective view of the locking component of a landing gear door retraction device for an aircraft, according to an embodiment of the present invention;

[0036] Figure 13 This is a perspective view of the base of a landing gear door retraction device for an aircraft, according to an embodiment of the present invention.

[0037] Figure 14 This is a perspective view of the first bracket of the landing gear door retraction device for an aircraft according to an embodiment of the present invention;

[0038] Figure 15 This is a perspective view of the second bracket of the landing gear door retraction device for an aircraft according to an embodiment of the present invention;

[0039] Figure 16This is a partially enlarged perspective view of a first-view three-dimensional schematic diagram of a landing gear door retraction device for an aircraft according to an embodiment of the present invention, with the door closed when the landing gear is enclosed in the cabin.

[0040] Figure 17 This is a partially enlarged perspective view of a landing gear door retraction device for an aircraft according to an embodiment of the present invention, with the landing gear door opened to its maximum extent.

[0041] Figure 18 This is a partially enlarged perspective view of a landing gear door retraction device for an aircraft in the landing gear deployed state, according to an embodiment of the present invention.

[0042] Figure 19 This is a partially enlarged three-dimensional schematic diagram from a second perspective of the landing gear door retraction device for an aircraft according to an embodiment of the present invention, with the door closed when the landing gear is enclosed in the cabin.

[0043] Figure 20 This is a partially enlarged perspective view of a landing gear door retraction device for an aircraft according to an embodiment of the present invention, with the landing gear door opened to its maximum extent; and

[0044] Figure 21 This is a partially enlarged three-dimensional schematic diagram from a second perspective of an embodiment of the present invention, showing the landing gear door retraction device for an aircraft in the landing gear lowered state.

[0045] In the picture:

[0046] 1-Hatch door;

[0047] 2-Landing gear; 21-Connecting end;

[0048] 3-Receiving and releasing mechanism;

[0049] 31-Connecting part;

[0050] 311-Connecting rod; 3111-First connecting rod; 3112-Second connecting rod; 3113-Support arm; 3114-Locking nut;

[0051] 312 - Pin; 3121 - First shaft; 3122 - Second shaft;

[0052] 32-Transmission unit;

[0053] 33-Hinge section;

[0054] 331-Hinge; 3311-Straight segment; 3312-Bent segment;

[0055] 34-Base; 341-Protrusion; 342-First support; 343-Second support;

[0056] 35 - Drive unit;

[0057] 351-Guide rail; 3511-Sliding groove; 3512-Receiving hole; 3513-Mounting hole; 3514-Protrusion;

[0058] 352-Rack; 3521-Base; 3522-Boss; 3523-Slot;

[0059] 353-Plug;

[0060] 36 - Rotating part;

[0061] 361 - Gear shaft; 3611 - Stop block;

[0062] 362 - Gear; 3621 - Third meshing tooth; 3622 - Fourth meshing tooth;

[0063] 37-Locking assembly;

[0064] 371-Connecting post; 3711-Matching groove;

[0065] 372-Locking component; 3721-First pivot; 3722-First turntable; 3723-Locking arm; 3724-Locking hook; 3725-First meshing tooth;

[0066] 373-Drive component; 3731-Second rotating shaft; 3732-Second turntable; 3733-Cam part; 3734-Energy storage component; 3735-Torsion spring; 3736-Second meshing tooth;

[0067] 4-Cargo compartment; 41-Opening. Detailed Implementation

[0068] To make the objectives, technical solutions, and advantages of the present invention clearer, the present invention will be further described in detail below with reference to specific embodiments and accompanying drawings.

[0069] According to one aspect of the invention, a landing gear door retraction device for an aircraft is provided. The aircraft includes landing gear rotatably mounted inside the aircraft cabin, and two facing doors suitable for closing the cabin when the landing gear is retracted. The landing gear door retraction device includes two retraction mechanisms that respectively cooperate with the doors. Each retraction mechanism includes: a connecting portion, a first end of which is rotatably connected to the landing gear; a base, mounted inside the cabin; a transmission portion, mounted on the base, a second end of which is rotatably mounted to the transmission portion; and a hinge portion, a first end of which is connected to the transmission portion, and a second end of which is connected to the door. Rotation of the landing gear in a longitudinal vertical plane drives the hinge portion to rotate relative to the base in a transverse vertical plane via the connecting portion and the transmission portion, thereby switching the doors between an open state with the cabin open and a closed state with the landing gear enclosed inside the cabin.

[0070] Figure 1 This is a partial perspective view of an aircraft according to an embodiment of the present invention with the landing gear enclosed within the cabin and the hatch closed. Figure 2 This is a partial perspective view of an aircraft in the open state of the landing gear doors and the cabin, according to an embodiment of the present invention. Figure 3 This is a first-view perspective perspective schematic diagram of the retraction mechanism of a landing gear door retraction device for an aircraft, according to an embodiment of the present invention. Figure 4 This is a second-view perspective perspective view of the retraction mechanism of the landing gear door retraction device for an aircraft, according to an embodiment of the present invention.

[0071] According to an exemplary embodiment of the present invention, please refer to Figures 1-4 A landing gear door retraction device for an aircraft is provided. The aircraft includes landing gear 2 rotatably mounted within the aircraft cabin, and two laterally facing doors 1 suitable for closing the cabin when the landing gear 2 is retracted. The landing gear door retraction device includes two retraction mechanisms 3, each cooperating with a door 1. Each retraction mechanism 3 includes a connecting portion 31, a base 34, a transmission portion 32, and a hinge portion 33. A first end of the connecting portion 31 is rotatably connected to the landing gear 2. The base 34 is mounted inside the cabin. The transmission portion 32 is mounted on the base 34. A second end of the connecting portion 31 is rotatably mounted to the transmission portion 32. A first end of the hinge portion 33 is connected to the transmission portion 32, and a second end of the hinge portion 33 is connected to the door 1. The rotation of the landing gear 2 in the longitudinal vertical plane drives the hinge part 33 to rotate relative to the base 34 in the transverse vertical plane through the connecting part 31 and the transmission part 32, so that the door 1 switches between the open state of opening the cabin and the closed state of enclosing the landing gear 2 in the cabin.

[0072] In this embodiment, the rotation of the landing gear 2 in the longitudinal vertical plane drives the hinge 33 to rotate relative to the base 34 in the transverse vertical plane via the connecting part 31 and the transmission part 32, thereby switching the door 1 between an open state with the cabin open and a closed state with the landing gear 2 enclosed within the cabin. On the one hand, the opening and closing of the door 1 is driven by the lowering and retraction of the landing gear 2, eliminating the need for a separate power source to control the opening and closing of the door 1. In other words, the landing gear door retraction device of this embodiment allows the door 1 to open or close as the landing gear 2 is lowered or retracted, without requiring an additional power source to control the opening and closing of the door 1, thus simplifying the aircraft system.

[0073] In some embodiments, the aircraft includes conventional manned aircraft and unmanned aerial vehicles, such as aircraft with a flying wing configuration. Generally, aircraft with a flying wing configuration do not have a vertical tail and rudder; their heading control is mainly achieved by using ailerons or drag rudders on the outer wing sections in a certain combination and opening angle to achieve yaw maneuvers and yaw stability.

[0074] In some embodiments, the landing gear door retraction device ensures that the geometric plane of door 1 is approximately parallel to the ground during the opening of the cabin or the closing process of enclosing the landing gear 2 within the cabin. It is understood that the outer contour of door 1 matches the outer contour of the UAV cabin for a smooth connection; therefore, the cross-section of door 1 is generally arc-shaped, flat, or a combination of partially arc-shaped and flat. The geometric plane of door 1 represents its projection onto the plane when it is laid flat. Thus, when door 1 is open, it is located parallel to the underside of the fuselage, without a control surface similar to the vertical tail rudder. When there is crosswind or UAV sideslip, the smaller aerodynamic force acts on door 1, reducing the impact on the UAV's yaw moment, facilitating directional control of the UAV, and alleviating the structural strength design burden of ailerons or drag rudders, as well as the flight control burden of the UAV.

[0075] In some exemplary embodiments, reference is made to Figures 3-4 The transmission unit 32 includes a drive unit 35 and a rotating unit 36. The drive unit 35 is engaged with the second end of the connecting part 31. The rotating part 36 includes a gear shaft 361 rotatably mounted on the base 34 and extending in the longitudinal direction. The first end of the hinge part 33 is mounted to the rotating part 36. The drive unit 35 is engaged with the rotating part 36, such that the connecting part 31 drives the rotating part 36 to rotate via the drive unit 35, thereby driving the hatch 1 to switch between an open state and a closed state. Therefore, the transmission unit 32 converts the rotation of the connecting part 31 in the longitudinal vertical plane into the rotation of the hinge part 33 relative to the base 34 in the transverse vertical plane, thereby driving the hatch 1 to switch between an open state and a closed state.

[0076] Figure 5This is a perspective view of the guide rail for a landing gear door retraction device for an aircraft, according to an embodiment of the present invention. Figure 6 This is an assembly diagram of the rack and pinion of a landing gear door retraction device for an aircraft, according to an embodiment of the present invention.

[0077] In some exemplary embodiments, reference is made to Figures 1-6 The drive unit 35 includes a guide rail 351 and a rack 352. The guide rail 351 is mounted on the base 34 and extends vertically. The rack 352 is movably mounted on the guide rail 351, and the second end of the connecting part 31 is rotatably mounted to the rack 352, such that the rotation of the landing gear 2 relative to the cabin drives the rack 352 to move linearly in the vertical direction relative to the guide rail 351 through the connecting part 31.

[0078] Figure 13 This is a perspective view of the base of a landing gear door retraction device for an aircraft, according to an embodiment of the present invention. Figure 14 This is a perspective view of the first bracket of the landing gear door retraction device for an aircraft according to an embodiment of the present invention; Figure 15 This is a perspective view of the second bracket of the landing gear door retraction device for an aircraft, according to an embodiment of the present invention.

[0079] It should be noted that, in this embodiment, reference is made to... Figure 4 as well as Figures 13-15 The guide rail 351 is mounted on the base 34 via a first bracket 342 and a second bracket 343, which are respectively mounted on the upper and lower ends of the base 34. The bottom of the second bracket 343 is an arc-shaped section and, after installation, is located below the gear 362, which can partially block sand and gravel from the ground. By setting the first bracket 342 and the second bracket 343, a multi-bracket and multi-end mounting method is formed between the guide rail 351 and the base 34, which can greatly enhance the installation rigidity of the guide rail 351 and ensure the stability and reliability of the rack 352's movement. Furthermore, in this embodiment, the movement trajectory of the rack 352 must be parallel to the plane where the connecting rod 311 rotates and the plane where the landing gear 2 rotates, and the plane where the gear 362 rotates must be perpendicular to the plane where the landing gear 2 rotates; otherwise, there will be a dead zone and the rack will jam.

[0080] In some exemplary embodiments, reference is made to Figures 3-4 as well as Figure 6 The rotating part 36 also includes a gear 362 connected to the gear shaft 361, and the gear 362 meshes with the rack 352. The second end of the connecting part 31 ( Figure 3The lower end of the connecting part 31 is rotatably mounted to a horizontally extending insert 353 extending from the side of the rack 352. The extending direction of the insert 353 is perpendicular to the extending direction of the gear shaft 361, such that the extending direction of the teeth of the gear 362 is perpendicular to the extending direction of the teeth of the rack 352. In other words, the teeth of the gear 362 and the teeth of the rack 352 mesh together from the side, thus realizing that the rotation plane of the connecting part 31 is perpendicular to the rotation plane of the gear 362.

[0081] Figure 10 This is a perspective view of the hinge of a landing gear door retraction device for an aircraft, according to an embodiment of the present invention.

[0082] In some exemplary embodiments, reference is made to Figure 10 The hinge portion 33 is a hinge 331, which is constructed in a generally curved gooseneck shape. Specifically, the hinge 331 includes a straight segment 3311 and a curved segment 3312 formed at one end of the straight segment 3311 and curved in a generally U-shape toward the other end of the straight segment 3311, so that when the hatch 1 is in the open state, it avoids interference with the edge of the aircraft's fuselage skin. See also... Figure 1 and Figure 2 Each hatch 1 is connected to two pairs of hinges 331 that open longitudinally, and each pair of hinges 331 is arranged longitudinally. Further, in each hatch 1, the four connection points of the four hinges 331 pivoting on the hatch 1 and the four connection points pivoting on the base 34 are arranged in a parallelogram. Thus, during the opening of the hatch 1 or the closing process of enclosing the landing gear 2 within the hatch, the geometric plane of the hatch 1 remains approximately parallel to the ground. In each hatch 1, a transmission unit 32 is mounted on one of the four hinges 331. Further, as... Figure 2 As shown, during the opening of the hatch 1 and the hatch body, the edge of the hatch opening partially enters the interior of the curved section 3312.

[0083] Furthermore, the first end of the gear shaft 361 and the hinge 331 are connected by a keyway or thread. After the gear shaft 361 and the hinge 331 are connected, they cannot generate relative movement, so that the gear shaft 361 can drive the hinge 331 to rotate.

[0084] In some exemplary embodiments, reference is made to Figures 1-4 The connecting part 31 includes a connecting rod 311 and a pin 312. The first end of the connecting rod 311 is rotatably connected to the drive part 35. One end of the pin 312 is rotatably connected to the second end of the connecting rod 311, and the other end is rotatably connected to the landing gear 2.

[0085] It should be noted that, in this embodiment, the landing gear 2 is provided with a connecting end 21 that allows the pin 312 to be inserted, so that the pin 312 can be rotatably connected to the landing gear 2. The pin 312 and the connecting end 21 provided on the landing gear 2 are in clearance fit.

[0086] Figure 7 This is a perspective view of the linkage of a landing gear door retraction device for an aircraft, according to an embodiment of the present invention.

[0087] In some exemplary embodiments, reference is made to Figures 3-4 as well as Figure 7 The connecting rod 311 includes a first connecting rod 3111 and a second connecting rod 3112 respectively connected to the drive unit 35 and the pin 312. The first connecting rod 3111 and the second connecting rod 3112 are adjustablely connected to change the length of the connecting rod 311.

[0088] It should be noted that, in this embodiment, one end of the second connecting rod 3112 extends into the interior of the first connecting rod 3111 and is threadedly connected to the first connecting rod 3111, allowing the second connecting rod 3112 and the first connecting rod 3111 to be telescopically connected to adjust the length of the connecting rod 311. A locking nut 3114 is also fitted over the end of the second connecting rod 3112 that extends into the first connecting rod 3111. After the relative positions of the second connecting rod 3112 and the first connecting rod 3111 are adjusted, the locking nut 3114 locks the relative positions of the second connecting rod 3112 and the first connecting rod 3111.

[0089] Figure 8 This is a perspective view of the pin of the landing gear door retraction device for an aircraft according to an embodiment of the present invention.

[0090] In some exemplary embodiments, reference is made to Figures 3-4 as well as Figures 7-8 The second end of the connecting rod 311 is provided with two support arms 3113 extending in the axial direction of the connecting rod 311. The pin 312 includes a first shaft 3121 rotatably mounted on the two support arms 3113 and a second shaft 3122 extending vertically from the middle of the first shaft 3121. The second shaft 3122 is rotatably connected to the connecting end 21 on the landing gear 2.

[0091] In some exemplary embodiments, reference is made to Figures 4-6The rack 352 includes a base 3521 and a strip-shaped boss 3522. The strip-shaped boss 3522 protrudes from the base 3521, and multiple teeth of the rack 352 are horizontally formed on the end face of the boss 3522 opposite to the base 3521. The guide rail 351 is provided with a sliding groove 3511 that is suitable for slidingly engaging with the base 3521 and the boss 3522 of the rack 352 respectively and extends in a vertical direction. The side wall of the sliding groove 3511 that engages with the boss 3522 is provided with a receiving hole 3512 that extends laterally through the side wall. The locking assembly 37 is installed inside the receiving hole 3512 and is configured to lock the gear 362 when the hatch 1 is in the open state, so as to prevent the gear 362 from driving the hinge part 33 to rotate in the direction that allows the hatch 1 to close.

[0092] Figure 9 This is an assembly diagram of the rotating part and connecting column of a landing gear door retraction device for an aircraft, according to an embodiment of the present invention.

[0093] In some exemplary embodiments, reference is made to Figures 1-4 as well as Figure 9 The locking assembly 37 includes a connecting post 371, a locking member 372, and a driving member 373. The connecting post 371 extends axially from the gear 362. The locking member 372 is rotatably mounted inside the receiving hole 3512. The driving member 373 is rotatably mounted inside the receiving hole 3512 and is configured to drive the locking member 372 to rotate between a locked state and a released state. In the locked state, the locking member 372 engages with the connecting post 371 to prevent the gear 362 from driving the hinge portion 33 to rotate in a direction that allows the hatch 1 to close, thus keeping the hatch 1 in the open state. In the released state, the locking member 372 disengages from the connecting post 371 to allow the gear 362 to drive the hinge portion 33 to rotate.

[0094] Figure 12 This is a perspective view of the locking component of a landing gear door retraction device for an aircraft, according to an embodiment of the present invention.

[0095] In some exemplary embodiments, reference is made to Figure 4 , Figure 7 as well as Figure 12 The locking component 372 includes a first turntable 3722, a locking arm 3723, and a locking hook 3724. The first turntable 3722 is rotatably mounted inside the receiving hole 3512 via a first pivot 3721. The locking arm 3723 extends outward along the tangent direction of the first turntable 3722. The locking hook 3724 is formed at the end of the locking arm 3723 and rotates with the first turntable 3722 between a locked state in which the locking hook 3724 is engaged with the connecting post 371 and a released state in which the locking hook 3724 is disengaged from the connecting post 371.

[0096] In some exemplary embodiments, reference is made to Figure 4 , Figure 9 as well as Figure 12 The connecting post 371 has an axially extending engagement groove 3711 for engaging with the locking hook 3724.

[0097] Figure 11 This is a perspective view of the drive component of a landing gear door retraction device for an aircraft, according to an embodiment of the present invention.

[0098] In some exemplary embodiments, reference is made to Figures 1-5 , Figure 9 as well as Figures 11-12 The drive component 373 includes a second turntable 3732, a cam portion 3733, and an energy storage component 3734. The second turntable 3732 is rotatably mounted inside the receiving hole 3512 via a second rotating shaft 3731 and meshes with the first turntable 3722 to drive the first turntable 3722 to rotate. The rotation planes of both the first turntable 3722 and the second turntable 3732 are parallel to the rotation plane of the gear 362. The cam portion 3733 extends radially from the outer edge of the second turntable 3732 and is configured to engage with the rack 352. The energy storage component 3734 is mounted on the second rotating shaft 3731 and is configured to have an energy storage state and an energy release state. During the retraction of the landing gear 2, which drives the rack 352 to rise, the rack 352 engages with the cam portion 3733 to drive the second turntable 3732 to rotate, causing the locking component 372 to separate from the connecting post 371. At the same time, the energy storage component 3734 enters the energy storage state to store kinetic energy. When the landing gear 2 is lowered to the point that the door 1 is in the open position, the rack 352 separates from the cam portion 3733 to allow the energy storage component 3734 to release kinetic energy and drive the second turntable 3732 to rotate in the opposite direction, so that the locking hook 3724 of the locking component 372 engages in the engagement groove 3711 of the connecting column 371, thereby preventing the gear 362 from rotating further.

[0099] Figure 16 This is a partially enlarged perspective view of a first-view three-dimensional schematic diagram of a landing gear door retraction device for an aircraft according to an embodiment of the present invention, with the door closed when the landing gear is enclosed in the cabin.

[0100] Figure 17 This is a partially enlarged perspective view of a landing gear door retraction device for an aircraft in the case of the present invention with the door opened to its maximum extent. Figure 18 This is a first-view perspective perspective of a landing gear door retraction device for an aircraft according to an embodiment of the present invention, in the landing gear lowered state. Figure 19 This is a partially enlarged three-dimensional schematic diagram from a second perspective of the landing gear door retraction device for an aircraft according to an embodiment of the present invention, with the door closed when the landing gear is enclosed in the cabin. Figure 20 This is a partially enlarged perspective view of a landing gear door retraction device for an aircraft according to an embodiment of the present invention, with the door fully opened; and Figure 21 This is a partially enlarged three-dimensional schematic diagram from a second perspective of an embodiment of the present invention, showing the landing gear door retraction device for an aircraft in the landing gear lowered state.

[0101] In some exemplary embodiments, reference is made to Figure 6 , Figure 9 , Figures 11-12 as well as Figures 16-21 The energy storage component 3734 is a torsion spring 3735, and the upper part of the rack 352 is provided with a slot 3523. During the upward movement of the rack 352, the bottom of the slot 3523 engages with the cam portion 3733, causing the cam portion 3733 to drive the second turntable 3732 to rotate against the torque of the torsion spring 3735, and causing the torsion spring 3735 to store kinetic energy due to elastic deformation. This causes the locking component 372 to separate from the connecting post 371. During the downward movement of the rack 352, the cam portion 3733, under the torque of the torsion spring 3735, enters the slot 3523, causing the second turntable 3732 to rotate in the opposite direction and engaging the locking component 372 with the connecting post 371.

[0102] It should be noted that, in this embodiment, during the upward movement of the rack 352, the cam 3733 drives the second turntable 3732 to rotate against the torque of the torsion spring 3735, causing the torsion spring 3735 to store elastic potential energy due to elastic deformation. During the downward movement of the rack 352, the cam 3733 is subjected to the torque of the torsion spring 3735, converting the stored elastic potential energy into the kinetic energy of the cam 3733 and the second turntable 3732 rotating in the opposite direction.

[0103] In some exemplary embodiments, reference is made to Figure 6 The slot 3523 extends vertically, forming on the upper part of the rack 352 and communicating with the top of the rack 352. Further, referring to... Figures 4-5 as well as Figure 11 The guide rail 351 has two mounting holes 3513 communicating with the receiving hole 3512, which are suitable for mounting the locking component 372 and the driving component 373. At the position where the receiving hole 3512 is located on the guide rail 351, a protrusion 3514 is formed extending outward in a direction away from the rack 352. The second rotating shaft 3731 has a blind hole (not shown in the figure). One end of the torsion spring 3735 extends into the blind hole and is fixed, while the other end is bent and abuts against a stop (not shown in the figure) extending from the surface of the protrusion 3514, so that the torsion spring 3735 cannot rotate during the process of being torsional and deformed and storing kinetic energy.

[0104] In some exemplary embodiments, reference is made to Figures 11-12The first turntable 3722 has first meshing teeth 3725 distributed in the circumferential direction, and the second turntable 3732 has second meshing teeth 3736 that mesh with the first meshing teeth 3725.

[0105] In some exemplary embodiments, reference is made to Figure 6 , Figure 9 , Figures 11-12 as well as Figures 19-21 The gear 362 includes a plurality of consecutively arranged third meshing teeth 3621 disposed on a portion of the outer periphery of the gear 362, and a fourth meshing tooth 3622 spaced apart from the beginning or end of the plurality of third meshing teeth 3621. During the initial upward movement of the rack 352, the rack 352 engages with the drive component 373, causing the locking component 372 to disengage from the connecting post 371, and the rack 352 engages with the fourth meshing tooth 3622, thereby driving the gear 362 to rotate past the interval between the third meshing teeth 3621 and the fourth meshing tooth 3622 until it engages with the third meshing tooth 3621. When the rack 352 moves downward to the position where it completes engagement with the third meshing tooth 3621, the locking component 372 engages with the connecting post 371 and enters a locked state, preventing the gear 362 from continuing to rotate, while the rack 352 can still continue to move downward.

[0106] It should be noted that in this embodiment, the gear 362 and the rack 352 mesh at right angles. In addition, various gear meshing methods such as spur meshing and helical gear meshing can also be used; the rack 352 and gear 362 can be designed and matched as needed.

[0107] In some exemplary embodiments, reference is made to Figures 2-3 , Figure 9 as well as Figures 16-18 The end of the gear shaft 361 extending from the base 34 also has a stop block 3611 extending radially. A protrusion 341 is formed on the outer side of the base 34. When the landing gear 2 is lowered to the open position of the hatch 1, the gear shaft 361 rotates to the point where the stop block 3611 abuts against the protrusion 341, preventing the gear 362 from continuing to rotate and thus preventing the hatch 1 from opening further. In this way, when the landing gear 2 is lowered to the open position of the hatch 1, the locking hook 3724 of the locking member 372 engages with the engagement groove 3711 of the connecting post 371, thereby preventing the gear 362 from reversing (…). Figure 17 and Figure 18 Counterclockwise in the middle, Figure 20 The gear 362 rotates clockwise; simultaneously, the stop block 3611 abuts against the protrusion 341 to prevent the gear 362 from continuing to rotate clockwise. Figure 17 and Figure 18 Clockwise in the middle, Figure 20The door is rotated counterclockwise (in the middle) to prevent it from opening further. In this way, the door is kept fully open.

[0108] It should be noted that, in this embodiment, the end of the gear shaft 361 is provided with a groove (not shown in the figure) that allows the protrusion 341 to extend into, so that the protrusion 341 is detachably attached to the end of the gear shaft 361.

[0109] In some exemplary embodiments, reference is made to Figure 2 During the opening of the cabin or the closing process of retracting the landing gear 2 into the cabin, the geometric plane of the door 1 is approximately parallel to the ground.

[0110] Furthermore, in this embodiment, two parallel bases 34 are installed at the near and far ends of each door 1. Each base 34 has a hinge 331. The rotation of the landing gear 2 in the longitudinal vertical plane is driven by the connecting part 31 and the transmission part 32, causing the hinge 331 connected to the transmission part 32 to rotate relative to the base 34 in the transverse vertical plane. This ensures that during the opening of the door 1 or the closing process of enclosing the landing gear 2 within the door, the geometric plane of the door 1 is approximately parallel to the ground. After the door 1 is opened, it is close to the lower fuselage skin. The four bases 34 on the two doors 1 are arranged approximately symmetrically to ensure that the geometric plane of the door 1 is approximately parallel to the ground during the opening of the door 1 or the closing process of enclosing the landing gear 2 within the door.

[0111] The following reference Figures 1-4 ,as well as Figures 16-21 This embodiment describes the operation process of opening and closing the drive door 1 of the landing gear door retraction device for an aircraft.

[0112] During the process of landing gear 2 entering the lowered state, the aircraft's retraction actuator (not shown in the figure) operates, causing landing gear 2 to move from the retracted state in the longitudinal vertical plane (see...). Figure 1 ) to the put-down state (see Figure 2 When the lever 311 rotates, the connecting rod 311 moves accordingly, driving the rack 352 to descend along the guide rail 351 (see...). Figure 3 and Figure 4 ); The hinge 331 rotates relative to the base 34 in the horizontal and vertical planes via gear 362 and gear shaft 361, and the hatch 1 gradually opens from the closed state. During this process, as Figure 19As shown, the end of the cam portion 3733 of the drive component 373 slides against the side surface of the boss 3522 of the rack 352, and the torsion spring 3735 is in a twisted, energy-storing state; when the rack 352 descends to the point where the slot 3523 on the rack 352 meets the cam portion 3733 of the drive component 373, the cam portion 3733 of the drive component 373 rotates into the slot 3523 due to the torque of the torsion spring 3735, which is the energy-storing component 3734, and releases kinetic energy. At the same time, the second turntable 3732 rotates and drives the locking hook 3724 of the locking component 372 to engage with the engagement groove 3711 of the connecting post 371, so that the locking component 372 enters the locked state, preventing the gear 362 from reversing ( Figure 17 and Figure 18 Counterclockwise in the middle, Figure 20 Rotate clockwise (in the middle), in other words, as Figures 19-21 As shown, to prevent gear 362 from rotating clockwise, thus preventing the hatch 1 from rotating in the closing direction; simultaneously, when rack 352 descends to the position where it engages with the third meshing tooth 3621 of gear 362, the stop block 3611 of gear shaft 361 abuts against the protrusion 341 of base 34, preventing gear 362 from continuing to rotate. In other words, as shown... Figures 19-21 As shown, gear 362 can no longer rotate counterclockwise. At this point, the hatch 1 is opened to its maximum extent (i.e., fully open), preventing the hatch 1 from opening further. It should be noted that when the hatch 1 is fully open, the landing gear 2 drives the rack 352 to continue moving until the landing gear 2 is in the fully lowered state.

[0113] During the process of landing gear 2 moving from the lowered state to the retracted state, the aircraft's retraction actuator operates, causing landing gear 2 to rotate rearward in the longitudinal vertical plane. Linkage 311 follows suit, driving rack 352 to rise along guide rail 351. When landing gear 2 rises to a certain angle, the cam portion 3733 of drive component 373 enters the slot 3523 of rack 352, and the bottom of slot 3523 drives the cam portion 3733 and drive component 373 to rotate against the torque of torsion spring 3735. Figure 20(Rotating clockwise), the torsion spring 3735 stores kinetic energy; simultaneously, the locking hook 3724 of the drive locking component 372 separates from the engagement groove 3711 of the connecting column 371, so that the locking component 372 is in the unlocked state, and the stop block 3611 of the gear shaft 361 separates from the protrusion 341 of the base 34; then, the end of the cam portion 3733 of the drive component 373 slides against the side surface of the boss 3522 of the rack 352, and the energy storage component 3734 remains in the energy storage state with the increase of stored kinetic energy as the drive component 373 rotates; at the same time, the rack 352 meshes with the fourth meshing tooth 3622 to drive the gear 362 to rotate across the interval to mesh with the third meshing tooth 3621, thereby driving the hinge 331 to rotate relative to the base 34 in the horizontal and vertical plane through the gear shaft 361, and the hatch 1 begins to close until the landing gear 2 is fully retracted, and the hatch 1 also enters the fully closed state.

[0114] Furthermore, the landing gear door retraction device of this embodiment ensures that during the opening of the door 1 or the closing of the landing gear 2 within the door, the geometric plane of the door 1 is approximately parallel to the ground. There is no control surface similar to the vertical tail rudder in terms of force. When there is crosswind or UAV sideslip, the aerodynamic force acting on the door is relatively small, reducing the impact on the UAV's yaw moment and facilitating heading control. The door retraction device does not require an additional power source for opening and closing the door 1, is small in size and light in weight, and is easy to install, overcoming the technical defects that may exist during the lowering and retraction of the landing gear 2 and the opening and closing of the door 1. The door retraction device is highly versatile and suitable for aircraft with landing gear, such as flying-wing UAVs and manned aircraft, as well as for traditional aircraft configurations where the horizontal opening style of the door requires consideration of the coordinated retraction and installation of the door and landing gear. The landing gear door retraction device of this embodiment is not limited to applications in... Figures 1-2 The double-door configuration shown, combined with the nose landing gear, can also be applied to single-door configurations combined with the main landing gear.

[0115] According to an exemplary embodiment of the present invention, please refer to Figures 1-2The invention also provides an aircraft comprising multiple cabins 4, multiple landing gears 2, multiple sets of doors 1, and multiple door retraction devices for the landing gears of the aircraft as described in the above embodiments. Each cabin 4 has an opening 41. The multiple landing gears 2 are rotatably mounted within the multiple cabins 4 of the aircraft, and each landing gear 2 has a lowered state (lowered to the outside of the cabin 4 through the opening 41) and a retracted state (retracted to the inside of the cabin 4). Each cabin 4 is equipped with a set of doors 1, suitable for opening or closing the opening 41. Each door retraction device is connected between the door 1 and the landing gear 2, such that when the landing gear 2 is switched between the lowered and retracted states, the door retraction device drives the door 1 to switch between an open and closed state.

[0116] It should be noted that in this embodiment, each set of doors 1 consists of two facing doors mounted on the nose landing gear bay. Alternatively, each set of doors 1 may also be a single door mounted on the main landing gear bay.

[0117] The specific embodiments described above further illustrate the purpose, technical solution, and beneficial effects of the present invention. It should be understood that the above descriptions are merely specific embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A landing gear door retraction device for an aircraft, the aircraft including landing gear (2) rotatably mounted in the aircraft cabin, and two facing doors (1) adapted to close the cabin when the landing gear (2) is retracted; the landing gear door retraction device includes two retraction mechanisms (3) respectively cooperating with the doors (1), each of the retraction mechanisms (3) including: A connecting part (31), the first end of which is rotatably connected to the landing gear (2); The base (34) is installed inside the cabin; A transmission part (32) is mounted on the base (34), and the second end of the connecting part (31) is rotatably mounted to the transmission part (32); and The hinge part (33) has its first end connected to the transmission part (32) and its second end connected to the hatch (1). The rotation of the landing gear (2) in the longitudinal vertical plane is driven by the connecting part (31) and the transmission part (32) to rotate the hinge part (33) relative to the base (34) in the transverse vertical plane, so that the hatch (1) can switch between the open state of opening the cabin and the closed state of closing the landing gear (2) inside the cabin.

2. The landing gear door retraction device for an aircraft according to claim 1, wherein, The transmission unit (32) includes: The driving part (35) is coupled to the second end of the connecting part (31); and The rotating part (36) includes a gear shaft (361) rotatably mounted on the base (34) and extending in the longitudinal direction. The first end of the hinge part (33) is mounted to the rotating part (36). The driving part (35) is engaged with the rotating part (36) such that the connecting part (31) drives the rotating part (36) to rotate through the driving part (35), thereby driving the hatch (1) to switch between an open state and a closed state.

3. The landing gear door retraction device for an aircraft according to claim 2, wherein, The drive unit (35) includes: Guide rail (351), mounted on the base (34) and extending vertically; and A rack (352) is movably mounted on the guide rail (351), and the second end of the connecting part (31) is rotatably mounted to the rack (352), so that the rotation of the landing gear (2) relative to the cabin drives the rack (352) to move linearly in the vertical direction through the connecting part (31); The rotating part (36) further includes a gear (362) connected to the gear shaft (361), the gear (362) meshing with the rack (352).

4. The landing gear door retraction device for an aircraft according to claim 3, wherein, The second end of the connecting part (31) is rotatably mounted to a plug (353) extending horizontally from the side of the rack (352), the extension direction of the plug (353) being perpendicular to the extension direction of the gear shaft (361), such that the extension direction of the teeth of the gear (362) is perpendicular to the extension direction of the teeth of the rack (352).

5. The landing gear door retraction device for an aircraft according to claim 3, wherein, The connecting part (31) includes: Linkage (311), the first end of which is rotatably connected to the drive unit (35); and A pin (312) is provided, one end of which is rotatably connected to the second end of the connecting rod (311), and the other end of which is rotatably connected to the landing gear (2).

6. The landing gear door retraction device for an aircraft according to claim 5, wherein, The connecting rod (311) includes a first connecting rod (3111) and a second connecting rod (3112) respectively connected to the drive unit (35) and the pin (312). The first connecting rod (3111) and the second connecting rod (3112) are adjustablely connected to change the length of the connecting rod (311).

7. The landing gear door retraction device for an aircraft according to claim 5, wherein, The second end of the connecting rod (311) is provided with two support arms (3113) extending in the axial direction of the connecting rod (311). The pin (312) includes a first shaft (3121) rotatably mounted on the two support arms (3113) and a second shaft (3122) extending vertically from the middle of the first shaft (3121). The second shaft (3122) is rotatably connected to the landing gear (2).

8. The landing gear door retraction device for an aircraft according to claim 3, wherein, The rack (352) includes: Base (3521); and A strip-shaped boss (3522) is formed protruding from the base (3521), and a plurality of teeth of the rack (352) are formed horizontally on the end face of the boss (3522); The guide rail (351) is provided with a sliding groove (3511) that is suitable for slidingly engaging with the base (3521) and the boss (3522) of the rack (352) respectively and extending in the vertical direction. The side wall of the sliding groove (3511) that engages with the boss (3522) is provided with a receiving hole (3512) that extends horizontally through the side wall. A locking assembly (37), installed inside the receiving hole (3512), is configured to lock the gear (362) when the hatch (1) is in the open state.

9. The landing gear door retraction device for an aircraft according to claim 8, wherein, The locking assembly (37) includes: A connecting post (371) extends axially from the gear (362); A locking member (372) is rotatably mounted inside the receiving hole (3512); and A drive component (373), rotatably mounted inside the receiving hole (3512), is configured to drive the locking component (372) to rotate between a locked state and a released state; in the locked state, the locking component (372) engages with the connecting post (371) to prevent the gear (362) from driving the hinge portion (33) to rotate in a direction that allows the hatch (1) to close, thereby keeping the hatch (1) in the open state; in the released state, the locking component (372) disengages from the connecting post (371) to allow the gear (362) to drive the hinge portion (33) to rotate.

10. The landing gear door retraction device for an aircraft according to claim 9, wherein, The locking component (372) includes: The first turntable (3722) is rotatably mounted inside the receiving hole (3512) via the first rotating shaft (3721); The locking arm (3723) extends outward along the tangential direction of the first turntable (3722); and A locking hook (3724) is formed at the end of the locking arm (3723) and rotates with the first turntable (3722) between a locked state in which the locking hook (3724) is engaged with the connecting post (371) and a released state in which the locking hook (3724) is separated from the connecting post (371).

11. The landing gear door retraction device for an aircraft according to claim 10, wherein, The connecting post (371) has an engagement groove (3711) extending in the axial direction for engaging with the locking hook (3724).

12. The door retraction device for landing gear of an aircraft according to claim 11, wherein, The drive component (373) includes: The second turntable (3732) is rotatably mounted inside the receiving hole (3512) via the second rotating shaft (3731) and engages with the first turntable (3722) to drive the first turntable (3722) to rotate; A cam portion (3733), extending radially from the outer edge of the second turntable (3732), is configured to engage with the rack (352); and An energy storage component (3734), mounted on the second rotating shaft (3731), is configured to have both an energy storage state and an energy release state. During the retraction of the landing gear (2), which causes the rack (352) to rise, the rack (352) engages with the cam portion (3733) to drive the second turntable (3732) to rotate, causing the locking component (372) to separate from the connecting post (371). Simultaneously, the energy storage component (3734) enters a state of storing kinetic energy. In the energy storage state, when the landing gear (2) is lowered to the point where the door (1) is in the open state, the rack (352) separates from the cam (3733) to allow the energy storage component (3734) to release kinetic energy and drive the second turntable (3732) to rotate in the opposite direction, so that the locking hook (3724) of the locking component (372) engages in the engagement groove (3711) of the connecting column (371), thereby preventing the gear (362) from rotating further.

13. The landing gear door retraction device for an aircraft according to claim 12, wherein, The energy storage component (3734) is a torsion spring (3735), and the upper part of the rack (352) is provided with a slot (3523). During the upward movement of the rack (352), the bottom of the slot (3523) engages with the cam (3733), causing the cam (3733) to drive the second turntable (3732) to rotate against the torque of the torsion spring (3735) and store kinetic energy. The locking component (372) separates from the connecting post (371). During the downward movement of the rack (352), the cam (3733) enters the slot (3523) under the torque of the torsion spring (3735), causing the second turntable (3732) to rotate in the opposite direction and drive the locking component (372) to engage with the connecting post (371).

14. The door retraction device for landing gear of an aircraft according to claim 12, wherein, The first turntable (3722) has a first meshing tooth (3725) distributed in the circumferential direction, and the second turntable (3732) has a second meshing tooth (3736) that meshes with the first meshing tooth (3725).

15. The landing gear door retraction device for an aircraft according to claim 9, wherein, The gear (362) includes a plurality of third meshing teeth (3621) arranged in succession on a portion of the outer periphery of the gear (362), and a fourth meshing tooth (3622) spaced apart from the head or tail end of the plurality of third meshing teeth (3621); During the initial upward movement of the rack (352), the rack (352) engages with the drive component (373), causing the locking component (372) to disengage from the connecting post (371), and the rack (352) engages with the fourth meshing tooth (3622) to drive the gear (362) to rotate past the interval and engage with the third meshing tooth (3621); when the rack (352) moves downward to the position where it completes engagement with the third meshing tooth (3621), the locking component (372) engages with the connecting post (371) and enters a locked state to prevent the gear (362) from continuing to rotate, while the rack (352) can continue to move downward.

16. The landing gear door retraction device for an aircraft according to any one of claims 3-15, wherein, The end of the gear shaft (361) is also formed with a stop block (3611) extending in the radial direction, and the outer side of the base (34) is formed with a protrusion (341) so that when the landing gear (2) is lowered to the open state of the door (1), the stop block (3611) abuts against the protrusion (341) to prevent the gear (362) from continuing to rotate, thereby preventing the door (1) from opening further.

17. A door retraction device for landing gear of an aircraft according to any one of claims 2-15, wherein, During the opening of the cabin or the closing process of enclosing the landing gear (2) within the cabin, the geometric plane of the cabin door (1) is approximately parallel to the ground.

18. An aircraft comprising: Multiple compartments (4), each compartment (4) having an opening (41); Multiple landing gears (2) are rotatably mounted in multiple cabins (4) of the aircraft. Each landing gear (2) has a lowered state that is lowered to the outside of the cabin (4) through the opening (41) and a retracted state that is retracted to the inside of the cabin (4). Multiple sets of hatches (1), each of the compartments (4) is equipped with a set of hatches (1) suitable for opening or closing the openings (41); and A plurality of door retraction devices for landing gear of an aircraft according to any one of claims 1-17, each of the door retraction devices being connected between the door (1) and the landing gear (2) such that the door (1) is driven by the door retraction device to switch between an open state and a closed state when the landing gear (2) switches between the lowered state and the retracted state.

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