Landing gear door strut mechanism, aircraft landing gear and aircraft

Abstract

The invention provides a landing gear door strut mechanism, an aircraft landing gear and an aircraft, wherein the landing gear door strut mechanism comprises a wheel support column, an oblique strut assembly, a lower lock assembly and an actuator assembly, wherein the actuator assembly comprises an actuator body, a driving rod and a forced push member, and the lower lock assembly comprises a lower lock buckle and a lower elastic member; when the actuator assembly is extended, the driving rod drives the forced push member to apply an action force to an unlocking protrusion, forcing the lower lock buckle to rotate to an unlocking position, and the oblique strut assembly is folded, so that the landing gear door strut mechanism is changed to a retracted state; when the actuator assembly is shortened, the driving rod drives the forced push member to move in the opposite direction, and the restoring force of the lower elastic member forces the lower lock buckle to rotate from the unlocking position to the locking position, the oblique strut assembly is unfolded, the lower lock buckle engages with a second oblique strut, and the landing gear door strut mechanism is changed to a lowered state. The landing gear door strut mechanism has a simple structure and can drive the oblique strut to move and the lock mechanism to move only by retracting and extending the actuator.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft, and in particular to a landing gear door strut mechanism, an aircraft landing gear and an aircraft. Background Art

[0002] The aircraft landing gear system includes a landing gear strut, a landing gear retracting and extending actuator cylinder and a landing gear door strut mechanism. The landing gear door strut mechanism includes an upper oblique strut, a lower oblique strut and a locking mechanism. The upper oblique strut and the lower oblique strut are hinged to each other. The retracting and extending actuator cylinder is hinged to the upper oblique strut. When the retracting and extending actuator cylinder is operated, the upper oblique strut and the lower oblique strut are rotated relative to each other, and the upper oblique strut and the lower oblique strut are transformed between a straight-line extended expanded state and a folded state.

[0003] The locking mechanism of the diagonal brace is an important part of the landing gear door brace mechanism. The locking mechanism is driven by another lock actuator. The locking mechanism mainly includes a lock catch that can be driven and rotatably connected to one of the diagonal braces. When the diagonal brace is fully deployed, the lock actuator works to make the lock catch lock the butt joint of the two diagonal braces. In this way, after the landing gear is lowered, the diagonal brace can maintain the deployed state and reliably support the landing gear strut. When the diagonal brace needs to be folded, the lock actuator drives the lock catch to leave the above-mentioned butt joint, so that the two diagonal braces resume rotation and unlock, thereby realizing the retraction of the landing gear.

[0004] It is now necessary to improve the landing gear system for small aircraft. According to the above, the existing aircraft landing gear system includes two actuators, namely the landing gear actuator and the lock actuator, which does not meet the actual requirements of small aircraft for simple structure and light weight. Summary of the invention

[0005] The first object of the present invention is to provide a landing gear door strut mechanism which has a simple structure and can drive the diagonal struts and the locking mechanism to move only by retracting and extending the actuating cylinder.

[0006] A second object of the present invention is to provide an aircraft landing gear having the above-mentioned landing gear door strut mechanism.

[0007] A third object of the present invention is to provide an aircraft having the above-mentioned aircraft landing gear.

[0008] To achieve the above-mentioned first purpose, the present invention provides a landing gear door strut mechanism, including a wheel support column, two ends of the wheel support column are equipped with a wheel mounting portion and a first frame connecting portion; an oblique strut assembly, the first end of the oblique strut assembly is provided with a second frame connecting portion, and the second end of the oblique strut assembly is hinged with the middle of the wheel support column; the landing gear door strut mechanism also includes: an actuating cylinder assembly, the actuating cylinder assembly includes an actuating cylinder body, a driving rod and a forced pushing member, the actuating cylinder body is hinged to one end of the wheel support column close to the first frame hinge portion, and the forced pushing member is arranged at the end of the driving rod; a lower lock assembly, the lower lock assembly includes a lower lock buckle and a lower elastic member; the oblique strut assembly includes a first oblique strut and a second oblique strut, the two ends of the first oblique strut are respectively hinged with the second frame connecting portion and the second oblique strut, a first strut hinge shaft is provided in the middle of the first oblique strut, and the forced pushing member is connected to the first The diagonal support rod is hinged; the lower lock buckle and the first diagonal support rod are hinged through the first hinge axis and can rotate around the first hinge axis between a locked position and an unlocked position, and the first hinge axis is parallel to the first support rod hinge axis; the lower lock buckle is provided with an unlocking protrusion, and the lower elastic member connects the lower lock buckle and the first diagonal support rod; when the actuator cylinder body drives the driving rod to extend, the driving rod drives the forced pushing member to move, and the forced pushing member applies a force to the unlocking protrusion, forcing the lower lock buckle to rotate to the unlocking position, and the first diagonal support rod can be folded relative to the second diagonal support rod to change the landing gear door support rod mechanism from a lowered state to a retracted state; when the actuator cylinder body drives the driving rod to retract, the driving rod drives the forced pushing member to move in the opposite direction, and the restoring force of the lower elastic member forces the lower lock buckle to rotate from the unlocked position to the locked position, the end of the first diagonal support rod is connected to the end of the second diagonal support rod, the lower lock buckle engages the second diagonal support rod, and the landing gear door support rod mechanism changes from a retracted state to a lowered state.

[0009] It can be seen from the above scheme that the retraction and extension of the landing gear door strut mechanism is driven by the actuator assembly, which is realized by the diagonal strut assembly connected to the landing gear and the door strut. When the landing gear door strut mechanism is retracted, the actuator assembly drives the lock mechanism to open, the first diagonal strut is folded relative to the second diagonal strut, and at the same time, the second diagonal strut drives the door strut to move, and the door strut pulls the rotating joint on the door to close the door; when the landing gear door strut mechanism is lowered, the actuator assembly drives the first diagonal strut to unfold relative to the second diagonal strut, the lock mechanism locks the first diagonal strut with the second diagonal strut, and at the same time, the second diagonal strut drives the door strut to move, and the door strut pushes the rotating joint on the door to open the door. Therefore, the landing gear door strut mechanism has a simple structure and only needs to retract and extend the actuator to drive the diagonal strut to move and drive the lock mechanism to move.

[0010] A preferred solution is that the diagonal brace assembly has a folded state and an unfolded state. In the folded state, the first diagonal brace is arranged at an acute angle to the second diagonal brace, and in the unfolded state, the first diagonal brace is arranged at a right angle to the second diagonal brace.

[0011] A preferred solution is that the forced push member is provided with a forced push surface, which is arranged at one end of the forced push member away from the actuator body and inclined upward, and the unlocking protrusion can abut against the forced push surface.

[0012] As can be seen from the above, by designing the inclined pushing surface, the unlocking protrusion can be subjected to a force in a preset direction to ensure that the lower lock buckle can be stably unlocked.

[0013] A preferred solution is that a snap-fit ​​groove is provided on the lower lock buckle, and in the length direction of the lower lock buckle, the snap-fit ​​groove and the unlocking protrusion are respectively located on both sides of the first hinge axis; the first diagonal support rod and the second diagonal support rod are hinged through the second hinge axis, the second hinge axis is parallel to the first hinge axis, and the first diagonal support rod is provided with a first snap-fit ​​protrusion on the side away from the second hinge axis, and the second diagonal support rod is provided with a second snap-fit ​​protrusion on the side away from the second hinge axis; when the diagonal support rod assembly is in an expanded state, the first snap-fit ​​protrusion and the second snap-fit ​​protrusion overlap along the length direction of the diagonal support rod assembly, and the first snap-fit ​​protrusion and the second snap-fit ​​protrusion are both snapped with the snap-fit ​​groove.

[0014] As can be seen from the above, by setting a first locking protrusion on the side of the first diagonal support rod away from the second hinge axis, and setting a second locking protrusion on the side of the second diagonal support rod away from the second hinge axis, the two locking protrusions are overlapped and snapped with the snapping groove, the two overlapping locking protrusions will be in the snapping groove and restricted from rotation, and the first diagonal support rod and the second diagonal support rod can be stably snapped together through a simple structure.

[0015] A preferred solution is that, in the axial direction of the first hinge shaft, the lower elastic member and the forced pushing member are respectively arranged on two opposite sides of the lower lock buckle.

[0016] It can be seen that the various components are arranged in reasonable positions to avoid interference with each other during operation, thereby avoiding affecting the smoothness of the operation of the landing gear door strut mechanism.

[0017] A preferred solution is that a waist-shaped hole is provided on the forced pushing member, the hinge shaft of the first support rod cooperates with the waist-shaped hole, and the waist-shaped hole extends along the extension direction of the driving rod.

[0018] It can be seen that when the actuator body drives the driving rod to extend, the forced push piece moves under the restriction of the waist-shaped hole, thereby driving the diagonal support rod mechanism to bend and retract the landing gear. At the same time, the forced push piece applies a force to the unlocking protrusion, forcing the lower lock buckle to rotate to the unlocking position. When the actuator body drives the driving rod to contract, the driving rod drives the forced push piece to move in the opposite direction, thereby driving the diagonal support rod mechanism to unfold and lower the landing gear. At the same time, the restoring force of the lower elastic member forces the lower lock buckle to rotate from the unlocking position to the locking position, so that the landing gear remains in the lowered position. When the actuator assembly drives the landing gear door support rod mechanism to change from the lowered state to the retracted state, since the sliding resistance of the first support rod hinge shaft in the waist-shaped hole is small and the resistance to opening the landing gear is large, therefore, when the actuator extends, it will first move along the waist-shaped hole and push the unlocking protrusion, forcing the lower lock buckle to unlock, and only after reaching the limit position of the waist-shaped hole will it start to drive the second diagonal support rod to swing and fold. It can be seen that the present invention utilizes the characteristics of the waist-shaped hole, through the change of the relative displacement of the force-bearing parts, and through the transmission of force, realizes the unlocking and locking of the diagonal strut locking mechanism connected to the retractable actuator cylinder. Therefore, there is no need to additionally set up a second lock actuator cylinder, which meets the various usage requirements of small aircraft with simplified structure, strong practicality and light weight.

[0019] A preferred solution is that the landing gear door strut mechanism also includes an upper lock assembly, which includes an upper lock buckle, an upper lock connecting rod, an upper elastic member and an upper lock ring; the upper lock buckle is hinged to the wheel support column through a support column hinge shaft and can rotate around the support column hinge shaft between a second locked position and a second unlocked position, and the support column hinge shaft is parallel to the first strut hinge shaft; the first end of the upper lock connecting rod is hinged to the wheel support column, the first end of the upper lock connecting rod is located near the actuator body, and the second end of the upper lock connecting rod is hinged to the upper lock buckle Hinged; the upper elastic member connects the upper lock buckle and the wheel support column; the upper lock ring is provided with a third frame connection portion and a lock ring portion. During the process of the landing gear door strut mechanism changing from the lowered state to the retracted state, the actuator body drives the diagonal strut assembly to fold, and the second diagonal strut drives the wheel support column to rotate around the first frame connection portion, and the upper lock buckle is buckled with the lock ring portion; during the process of the landing gear door strut mechanism changing from the retracted state to the lowered state, the upper lock link applies a force to the upper lock buckle, forcing the upper lock buckle to separate from the lock ring portion.

[0020] It can be seen that in the process of the landing gear door strut mechanism changing from the lowered state to the retracted state, the actuator body can drive the diagonal strut assembly to fold, the second diagonal strut drives the wheel support column to rotate around the first frame connection part, and the upper lock buckle is engaged with the lock ring part, so that the entire landing gear door strut mechanism is stably maintained in the retracted position; in the process of the landing gear door strut mechanism changing from the retracted state to the lowered state, the upper lock connecting rod applies a force to the upper lock buckle, forcing the upper lock buckle to separate from the lock ring part, so that the landing gear door strut mechanism can be unfolded and lowered. Therefore, the landing gear door strut mechanism can simultaneously realize the retraction and lowering of the diagonal strut assembly, as well as the locking and unlocking of the upper lock assembly and the lower lock assembly, by only one actuator. The design of the entire mechanism is reasonable and ingenious, while simplifying the structure and reducing the cost.

[0021] A further solution is that the upper lock connecting rod and the upper lock buckle are hinged through a third hinge shaft; an upper hook is provided on the upper lock buckle, and in the length direction of the upper lock buckle, the support column hinge shaft and the upper hook are respectively located on both sides of the third hinge shaft; the connection position between the upper elastic member and the upper lock buckle is located between the third hinge shaft and the support column hinge shaft; the upper elastic member, the upper lock connecting rod and the upper hook are all located on the same side of the upper lock buckle.

[0022] It can be seen that by arranging the upper elastic member, the upper lock connecting rod and the upper hook on the same side of the upper lock buckle, it is convenient for the upper elastic member to apply a force to the upper lock buckle, so that the upper lock buckle remains in the buckled position. At the same time, it is convenient for the upper lock connecting rod to apply a force to the upper hook, so that the upper lock buckle is disengaged from the locking ring part.

[0023] To achieve the above second objective, the present invention provides an aircraft landing gear, comprising the above landing gear door strut mechanism.

[0024] To achieve the third objective, the present invention provides an aircraft, comprising the above-mentioned aircraft landing gear. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a structural diagram of an embodiment of an aircraft landing gear of the present invention in a lowered state.

[0026] Figure 2 It is a structural diagram of an embodiment of an aircraft landing gear of the present invention with some components hidden.

[0027] Figure 3 yes Figure 2 Enlarged view of point A in the middle.

[0028] Figure 4 It is a structural exploded view of the diagonal brace assembly, the lower lock buckle and the forced push member in the embodiment of the aircraft landing gear of the present invention.

[0029] Figure 5It is a structural diagram of a diagonal brace assembly and a lower lock assembly in an embodiment of an aircraft landing gear of the present invention.

[0030] Figure 6 It is a structural diagram of an embodiment of an aircraft landing gear of the present invention in a retracted state from a first perspective, wherein a cabin door is hidden in the diagram.

[0031] Figure 7 for Figure 6 Enlarged view of point B in the middle.

[0032] Figure 8 It is a structural diagram of the aircraft landing gear embodiment of the present invention in the retracted state from a second viewing angle, in which the cabin door is hidden.

[0033] Fig. 9 for Figure 8 Enlarged view of point C in the middle.

[0034] Fig.10 It is a structural diagram of a door brace in an embodiment of an aircraft landing gear of the present invention.

[0035] Fig.11 It is a structural exploded view of a door brace in an embodiment of an aircraft landing gear of the present invention.

[0036] Fig.12 It is a cross-sectional view of a door brace in an embodiment of an aircraft landing gear of the present invention. DETAILED DESCRIPTION

[0037] See also Figures 1 to 3 The aircraft of this embodiment includes a fuselage (not shown) and an aircraft landing gear 1 , and the aircraft landing gear 1 includes a landing gear door strut mechanism 11 , wheels 12 and a door 13 .

[0038] The landing gear door strut mechanism 11 of the present embodiment includes a wheel support column 2 , an oblique strut assembly 3 , an actuator assembly 4 , a locking mechanism 5 and a door strut 6 .

[0039] A wheel mounting portion 21 and a first fuselage connecting portion 22 are installed at both ends of the wheel support column 2. The wheel 12 is installed at the wheel mounting portion 21. The first fuselage connecting portion 22 is hinged to the fuselage of the aircraft, and the wheel support column 2 can swing around the first fuselage connecting portion 22.

[0040] The first end of the diagonal strut assembly 3 is provided with a second fuselage connection portion 31, and the second end of the diagonal strut assembly 3 is hinged to the middle part of the wheel support column 2. The diagonal strut assembly 3 includes a first diagonal strut 32 and a second diagonal strut 33 hinged to each other, and the second fuselage connection portion 31 is fixed to the fuselage. The first diagonal strut 32 and the second diagonal strut 33 are both straight rods.

[0041] See also Figure 1 and Figure 6 , Figure 1The figure shows the landing gear door strut mechanism 11 of the aircraft landing gear 1 in the lowered state. Figure 6 The figure shows the landing gear door strut mechanism 11 of the aircraft landing gear 1 in the retracted state. The first hinged portion 321 of the first diagonal strut 32 and the second hinged portion 331 of the second diagonal strut 33 are hingedly connected through the second hinge shaft 34. Figure 1 When the aircraft landing gear 1 is lowered, the diagonal brace assembly 3 is in an extended state, and the first diagonal brace 32 and the second diagonal brace 33 are extended in a straight line along the extension direction of the second diagonal brace 33, that is, the two are arranged at a right angle. Figure 6 When the aircraft landing gear 1 is shown in the retracted state, the diagonal brace assembly 3 is in a folded state, and the first diagonal brace 32 and the second diagonal brace 33 are folded and arranged at an acute angle.

[0042] The connecting end of the actuator assembly 4 is connected to one end of the wheel support column 2 close to the first fuselage connecting portion 22, and the driving end of the actuator assembly 4 is connected to the first diagonal brace 32. When the actuator assembly 4 drives the landing gear door brace mechanism 11 to change from the lowered state to the stowed state, the actuator assembly 4 can drive the lower lock assembly 8 in the lock mechanism 5 to open, and the first diagonal brace 32 is folded relative to the second diagonal brace 33. When the actuator assembly 4 drives the landing gear door brace mechanism 11 to change from the stowed state to the lowered state, the actuator assembly 4 can drive the first diagonal brace 32 to unfold relative to the second diagonal brace 33, and the lower lock assembly 8 in the lock mechanism 5 locks the first diagonal brace 32 with the second diagonal brace 33.

[0043] The actuator assembly 4 includes an actuator body 41, a driving rod 42 and a forced push piece 43. The actuator body 41 is hinged to the wheel support column 2 through an actuator hinge shaft 40, and the forced push piece 43 is arranged at the end of the driving rod 42. The two ends of the first oblique support rod 32 are respectively hinged to the second fuselage connecting portion 31 and the second oblique support rod 33. The middle part of the first oblique support rod 32 is provided with a first support rod hinge shaft 322. The forced push piece 43 is provided with a waist-shaped hole 431, which extends along the extension direction of the driving rod 42. The first support rod hinge shaft 322 is slidably matched with the waist-shaped hole 431, and the forced push piece 43 is hinged to the first oblique support rod 32 through the first support rod hinge shaft 322.

[0044] See also Figures 2 to 5The lock mechanism 5 includes an upper lock assembly 7 and a lower lock assembly 8. The lower lock assembly 8 includes a lower lock buckle 81 and a lower elastic member 82. The lower elastic member 82 is a tension spring. The lower lock buckle 81 is hinged to the first diagonal support rod 32 through a first hinge shaft 83 and can rotate around the first hinge shaft 83 between a first locking position and a first unlocking position. The first hinge shaft 83 is parallel to the first support rod hinge shaft 322. In the axial direction of the first hinge shaft 83, the lower elastic member 82 and the forced push member 43 are respectively arranged on opposite sides of the lower lock buckle 81. When the diagonal support rod assembly 3 is in the unfolded state, the lower lock buckle 81 is in the first locking position and buckles the second diagonal support rod 33. The two ends of the lower elastic member 82 are respectively connected to the lower lock buckle 81 and the first diagonal support rod 32.

[0045] The lower lock buckle 81 is provided with an unlocking protrusion 811, and the pushing member 43 is provided with a pushing surface 430. The pushing surface 430 is arranged at one end of the pushing member 43 away from the actuator cylinder body 41, and when the aircraft landing gear 1 is in a lowered state, the pushing surface 430 is inclined upward, and the unlocking protrusion 811 can abut against the pushing surface 430, so that the pushing surface 430 can apply an unlocking force to the unlocking protrusion 811.

[0046] The lower lock buckle 81 is provided with a snap-fit ​​groove 812. In the length direction of the lower lock buckle 81, the snap-fit ​​groove 812 and the unlocking protrusion 811 are respectively located on both sides of the first hinge shaft 83. The first diagonal support rod 32 and the second diagonal support rod 33 are hinged through the second hinge shaft 34. The second hinge shaft 34 is parallel to the first hinge shaft 83. The first diagonal support rod 32 is provided with a first snap-fit ​​protrusion 323 on the side away from the second hinge shaft 34, and the second diagonal support rod 33 is provided with a second snap-fit ​​protrusion 332 on the side away from the second hinge shaft 34. When the diagonal support rod assembly 3 is in the unfolded state, the first snap-fit ​​protrusion 323 and the second snap-fit ​​protrusion 332 overlap along the length direction of the diagonal support rod assembly 3, and the first snap-fit ​​protrusion 323 and the second snap-fit ​​protrusion 332 are both snap-fitted with the snap-fit ​​groove 812.

[0047] See also Figure 2 , Figure 6 and Figure 7 The upper lock assembly 7 includes an upper lock buckle 71, an upper lock link 72, an upper elastic member 73 and an upper lock ring 74. The upper lock buckle 71 is hinged to the wheel support column 2 through the support column hinge shaft 23 and can rotate around the support column hinge shaft 23 between the second locking position and the second unlocking position. The support column hinge shaft 23 is parallel to the first support rod hinge shaft 322. The first end of the upper lock link 72 is hinged to the wheel support column 2, the first end of the upper lock link 72 is located near the actuator hinge shaft 40, and the second end of the upper lock link 72 is hinged to the upper lock buckle 71. The two ends of the upper elastic member 73 are respectively connected to the upper lock buckle 71 and the wheel support column 2. The upper elastic member 73 is a tension spring.

[0048] The upper locking ring 74 is provided with a third fuselage connection portion 741 and a locking ring portion 742. The upper locking ring 74 is fixedly connected to the fuselage through the third fuselage connection portion 741. When the landing gear door strut mechanism 11 is changed from the lowered state to the stowed state, the actuator body 41 drives the diagonal strut assembly 3 to fold, and the second diagonal strut 33 drives the wheel support column 2 to rotate around the first fuselage connection portion 22. The upper locking buckle 71 is engaged with the locking ring portion 742, so that the entire landing gear door strut mechanism 11 is stably maintained in the stowed position. When the landing gear door strut mechanism 11 is changed from the stowed state to the lowered state, the upper locking link 72 applies a force to the upper locking buckle 71, forcing the upper locking buckle 71 to separate from the locking ring portion 742, so that the landing gear door strut mechanism 11 can be unfolded and lowered.

[0049] The upper lock link 72 is hinged to the upper lock buckle 71 through the third hinge shaft 75. The upper lock buckle 71 is provided with an upper hook 711. In the length direction of the upper lock buckle 71, the support column hinge shaft 23 and the upper hook 711 are respectively located on both sides of the third hinge shaft 75, and the connection position of the upper elastic member 73 and the upper lock buckle 71 is located between the third hinge shaft 75 and the support column hinge shaft 23. The upper elastic member 73, the upper lock link 72 and the upper hook 711 are all located on the same side of the upper lock buckle 71. By arranging the upper elastic member 73, the upper lock link 72 and the upper hook 711 on the same side of the upper lock buckle 71, it is convenient for the upper elastic member 73 to apply a force to the upper lock buckle 71, so that the upper lock buckle 71 is kept in the buckled position, and it is convenient for the upper lock link 72 to apply a force to the upper hook 711, so that the upper lock buckle 71 is separated from the lock ring part 742.

[0050] See also Figure 1 , Figures 8 to 12 A connecting rod 333 is fixedly connected to the middle of the second diagonal brace 33, and the connecting rod 333 extends in a direction perpendicular to the second diagonal brace 33. Door braces 6 are arranged at both ends of the connecting rod 333, and the two door braces 6 are arranged in parallel and perpendicular to the connecting rod 333. In the extending direction of the connecting rod 333, the wheel support column 2 is located between the two door braces 6.

[0051] The door support rod 6 includes a support rod outer tube 61, a support rod elastic member 62, a door connecting rod 63 and a landing gear connecting rod 64. The door connecting rod 63, the support rod elastic member 62 and the landing gear connecting rod 64 are all installed in the support rod outer tube 61 and arranged in sequence along the axial direction of the support rod outer tube 61. The two ends of the support rod elastic member 62 are respectively connected to the door connecting rod 63 and the landing gear connecting rod 64. The door connecting rod 63 is fixedly connected to the support rod outer tube 61 by a fixing member 611. The landing gear connecting rod 64 is connected to the support rod outer tube 61 along the axial direction of the support rod outer tube 61. Then, the first end of the door link 63 is provided with a door connection part 631, and the door connection part 631 is provided with a joint bearing 65. The door link 63 is connected to the door 13 through the joint bearing 65. The door 13 is also provided with three connection buckles 131, which are arranged along the length direction of the door 13 and are all arranged on the same side in the width direction of the door 13. The door 13 is hinged to the fuselage through the connection buckles 131, and the door strut 6 is connected to the connection buckle 131 located in the middle of the length direction of the door 13. The first end of the landing gear link 64 is connected to the connecting rod 333, and the second end of the landing gear link 64 is provided with a guide column 641. The peripheral wall of the strut outer tube 61 is provided with a guide opening 612 extending along the axial direction of the strut outer tube 61, and the guide column 641 extends into the guide opening 612 and slidably cooperates with the guide opening 612. The second end of the door connecting rod 63 is connected to the second end of the landing gear connecting rod 64 through the support rod elastic member 62. The support rod elastic member 62 is a spring.

[0052] See also Figures 1 to 3 ,as well as Figures 6 to 9 The process of the aircraft landing gear 1 changing from the lowered state to the retracted state is as follows: the actuator body 41 drives the above-mentioned driving rod 42 to extend outward, the driving rod 42 drives the forced pushing member 43 to move, the forced pushing member 43 moves under the restriction of the waist-shaped hole 431, and the forced pushing surface 430 of the forced pushing member 43 applies a force to the unlocking protrusion 811, forcing the lower lock buckle 81 to rotate around the first hinge shaft 83 to the first unlocking position. At this time, the lower lock buckle 81 is separated from the first engaging protrusion 323 and the second engaging protrusion 332. Then, the driving rod 42 continues to extend outward, and after the first strut hinge shaft 322 reaches the limit position of the waist-shaped hole 431, the driving rod 42 that continues to extend outward begins to drive the first diagonal strut 32 to swing and fold, and the first diagonal strut 32 drives the second diagonal strut 33 to swing and fold, and at the same time, the second diagonal strut 33 drives the wheel support column 2 to swing and fold. When the diagonal strut assembly 3 and the wheel support column 2 swing to the limit position, the upper hook 711 of the upper lock buckle 71 is engaged with the locking ring part 742 of the upper locking ring 74. At the same time, under the action of the upper elastic member 73, the upper hook 711 and the locking ring part 742 are maintained in a locked state, so that the landing gear door strut mechanism 11 is changed from a lowered state to a retracted state. During this process, the second diagonal strut 33 drives the door strut 6 to move, and the door strut 6 pulls the rotating joint on the door 13 to close the door 13.

[0053] The process of changing the aircraft landing gear 1 from the retracted state to the lowered state is as follows: the actuator body 41 drives the above-mentioned drive rod 42 to retract, the drive rod 42 drives the forced push member 43 to move in the opposite direction, drives the first diagonal support rod 32 to rotate in the opposite direction around the first support rod hinge shaft 322, the first diagonal support rod 32 pulls the second diagonal support rod 33 to rotate, the second diagonal support rod 33 drives the wheel support column 2 to rotate around the first fuselage connecting part 22, the upper lock link 72 overcomes the elastic force of the upper elastic member 73 and pushes the upper lock buckle 71 to the side away from the upper elastic member 73, forcing the upper lock buckle 71 to separate from the lock ring part 742, so that the landing gear door support rod mechanism 11 can be unfolded and lowered. At the same time, the elastic force of the lower elastic member 82 forces the lower lock 81 to rotate from the unlocked position to the locked position. At this time, the end of the first diagonal support rod 32 is butted against the end of the second diagonal support rod 33, and the first engaging protrusion 323 and the second engaging protrusion 332 overlap along the length direction of the diagonal support rod assembly 3 and then engage with the engaging groove 812. In this process, the second diagonal support rod 33 drives the door support rod 6 to move, and the door support rod 6 pushes the rotating joint on the door 13 to open the door 13.

[0054] As can be seen from the above, the retraction and extension of the landing gear door strut mechanism is driven by the actuator assembly, which is realized by the diagonal strut assembly connected to the landing gear and the door strut. When the landing gear door strut mechanism is retracted, the actuator assembly drives the lock mechanism to open, the first diagonal strut is folded relative to the second diagonal strut, and at the same time, the second diagonal strut drives the door strut to move, and the door strut pulls the rotating joint on the door to close the door; when the landing gear door strut mechanism is lowered, the actuator assembly drives the first diagonal strut to unfold relative to the second diagonal strut, the lock mechanism locks the first diagonal strut with the second diagonal strut, and at the same time, the second diagonal strut drives the door strut to move, and the door strut pushes the rotating joint on the door to open the door. During the process of retracting and extending the landing gear door strut mechanism, the length of the door strut is constantly changing. The length of the door strut is adjusted by the strut elastic member, so that the door strut can continuously adapt to the movement of the diagonal strut assembly and the door. The structure is simple and has automatic adjustment and buffering functions. The strut elastic member can also eliminate the impact of adverse loads on the landing gear system. Therefore, compared with the prior art, the landing gear door strut mechanism uses a door strut to connect the door and the landing gear. Only by the action of the retracting and extending actuator can the diagonal strut assembly and the locking mechanism be driven to move. The door opens and closes with the retracting and extending of the landing gear. At the same time, the door strut is provided with an elastic member, which can eliminate the adverse impact of external loads on the door and the landing gear. The structure is simple, light, low cost, and easy to implement.

[0055] Finally, it should be emphasized that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various changes and modifications. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. Landing gear door support rod mechanism, including: A wheel support column, wherein two ends of the wheel support column are provided with a wheel mounting portion and a first frame connecting portion; An oblique brace assembly, wherein a first end of the oblique brace assembly is provided with a second frame connection portion, and a second end of the oblique brace assembly is hinged to a middle portion of the wheel support column; Characterized in that, the landing gear door support rod mechanism also includes: An actuator assembly, the actuator assembly comprising an actuator body, a driving rod and a forced push piece, the actuator body being hinged to one end of the wheel support column close to the first frame connection portion, and the forced push piece being arranged at the end of the driving rod; A lower lock assembly, the lower lock assembly comprising a lower lock buckle and a lower elastic member; The diagonal brace assembly comprises a first diagonal brace and a second diagonal brace, the two ends of the first diagonal brace are respectively hinged to the second frame connection portion and the second diagonal brace, a first brace hinge shaft is provided at the middle of the first diagonal brace, and the forced push member is hinged to the first diagonal brace through the first brace hinge shaft; The lower lock buckle is hinged to the first diagonal support rod through a first hinge shaft and can rotate around the first hinge shaft between a locked position and an unlocked position, and the first hinge shaft is parallel to the first support rod hinge shaft; The lower lock buckle is provided with an unlocking protrusion, and the lower elastic member connects the lower lock buckle and the first diagonal support rod; When the actuator body drives the driving rod to extend, the driving rod drives the forced push member to move, and the forced push member applies a force to the unlocking protrusion to force the lower lock buckle to rotate to the unlocking position, and the first diagonal support rod can be folded relative to the second diagonal support rod, so that the landing gear door support rod mechanism is changed from a lowered state to a retracted state; When the actuator body drives the drive rod to retract, the drive rod drives the forced push member to move in the opposite direction, and the restoring force of the lower elastic member forces the lower lock buckle to rotate from the unlocked position to the locked position, and the end of the first diagonal support rod is connected with the end of the second diagonal support rod, and the lower lock buckle is buckled with the second diagonal support rod, and the landing gear door support rod mechanism is changed from the retracted state to the lowered state; The lower lock buckle is provided with a buckling groove, and in the length direction of the lower lock buckle, the buckling groove and the unlocking protrusion are respectively located on both sides of the first hinge shaft; The first diagonal brace rod and the second diagonal brace rod are hingedly connected via a second hinge shaft, the second hinge shaft is parallel to the first hinge shaft, a first engaging protrusion is provided on a side of the first diagonal brace rod away from the second hinge shaft, and a second engaging protrusion is provided on a side of the second diagonal brace rod away from the second hinge shaft; When the diagonal brace assembly is in an unfolded state, the first engaging protrusion and the second engaging protrusion overlap along the length direction of the diagonal brace assembly, and the first engaging protrusion and the second engaging protrusion are both engaged with the engaging groove; The landing gear door strut mechanism further comprises an upper lock assembly, wherein the upper lock assembly comprises an upper lock buckle, an upper lock connecting rod, an upper elastic member and an upper lock ring; The upper lock buckle is hinged to the wheel support column through a support column hinge shaft and can rotate around the support column hinge shaft between a second locking position and a second unlocking position, and the support column hinge shaft is parallel to the first support rod hinge shaft; The first end of the upper lock connecting rod is hinged to the wheel support column, the first end of the upper lock connecting rod is located close to the actuator body, and the second end of the upper lock connecting rod is hinged to the upper lock buckle; The upper elastic member connects the upper lock buckle and the wheel support column; The upper locking ring is provided with a third frame connection portion and a locking ring portion. When the landing gear door strut mechanism is changed from the lowered state to the stowed state, the actuator body drives the diagonal strut assembly to fold, the second diagonal strut drives the wheel support column to rotate around the first frame connection portion, and the upper locking buckle is buckled with the locking ring portion. During the transformation of the landing gear door strut mechanism from the stowed state to the lowered state, the upper lock link applies a force to the upper lock buckle, forcing the upper lock buckle to separate from the lock ring portion; The upper lock connecting rod is hinged to the upper lock buckle via a third hinge shaft; The upper lock buckle is provided with an upper hook, and in the length direction of the upper lock buckle, the support column hinge shaft and the upper hook are respectively located on both sides of the third hinge shaft; The connection position between the upper elastic member and the upper lock buckle is located between the third hinge shaft and the support column hinge shaft; The upper elastic member, the upper lock connecting rod and the upper hook are all located on the same side of the upper lock buckle.

2. The landing gear door brace mechanism according to claim 1, characterized in that: The diagonal brace assembly has a folded state and an unfolded state. In the folded state, the first diagonal brace is arranged at an acute angle to the second diagonal brace, and in the unfolded state, the first diagonal brace is arranged at a right angle to the second diagonal brace.

3. The landing gear door brace mechanism according to claim 1, characterized in that: The forced pushing member is provided with a forced pushing surface, which is arranged at one end of the forced pushing member away from the actuating cylinder body and inclined upward, and the unlocking protrusion can abut against the forced pushing surface.

4. The landing gear door brace mechanism according to any one of claims 1 to 3, characterized in that: In the axial direction of the first hinge shaft, the lower elastic member and the forced pushing member are respectively arranged on two opposite sides of the lower lock buckle.

5. The landing gear door brace mechanism according to any one of claims 1 to 3, characterized in that: The forced push member is provided with a waist-shaped hole, the first support rod hinge shaft cooperates with the waist-shaped hole, and the waist-shaped hole extends along the extension direction of the driving rod.

6. Aircraft landing gear, characterized in that: It comprises a landing gear door brace mechanism as claimed in any one of claims 1 to 5.

7. An aircraft, characterized in that Comprising an aircraft landing gear as claimed in claim 6.

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