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. The landing gear door strut mechanism comprises a wheel support column, an oblique strut assembly, an actuator assembly, a lower lock assembly and a door strut. During the process of retracting the aircraft landing gear, the actuator assembly drives the lower lock assembly to open, and the first oblique strut is folded relative to the second oblique strut; during the process of lowering the aircraft landing gear, the actuator assembly drives the first oblique strut to unfold relative to the second oblique strut, and the lower lock assembly locks the first oblique strut with the second oblique strut; the door strut comprises a strut elastic member, a door connecting rod and a landing gear connecting rod, the first end of the door connecting rod is provided with a door connecting part, the first end of the landing gear connecting rod is connected to the middle part of the second oblique strut, and the second end of the door connecting rod is connected to the second end of the landing gear connecting rod through the strut elastic member. The landing gear door strut mechanism has automatic adjustment and buffering functions, and the oblique strut assembly and the lock mechanism can be driven to move by only retracting and releasing 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] In order to reduce air resistance, existing aircraft with retractable landing gear will use a door to cover and store the landing gear. The door can be retracted and extended with the movement of the landing gear, or a separate power source can be set. The follow-up type is simple and reliable, but the door strut is generally a connecting rod mechanism with a fixed length. When the outside world applies a load to the door, the load is directly transmitted to the landing gear, which has an additional impact on the landing gear retraction and extension system, and in severe cases, it can cause abnormal landing gear retraction and extension function.

[0003] To overcome the above problems, the existing solutions are usually to control the length of the connecting rod mechanism by driving a hydraulic rod or the like. However, for the landing gear system of a small aircraft, on the one hand, this control method is complex and costly. On the other hand, during the folding and unfolding of the door strut, the landing gear and the door are constantly moving relative to each other, and the movement direction is complex. The use of a hydraulic rod cannot timely buffer the relative movement between the two, thereby causing the door strut to deform, or the door strut and the door to get stuck, making it impossible to smoothly achieve the folding and lowering of the landing gear.

[0004] In addition, in the existing aircraft landing gear system, two actuators are usually required to respectively drive the diagonal struts to fold and unfold and to lock in two states, which has many parts, a complex structure and high cost. 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, automatic adjustment and buffering functions, and can drive the diagonal strut assembly and the locking mechanism to move by only retracting and extending the actuator.

[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, wherein both ends of the wheel support column are equipped with a wheel mounting portion and a first fuselage connecting portion; an oblique strut assembly, wherein the first end of the oblique strut assembly is provided with a second fuselage connecting portion, the second end of the oblique strut assembly is hinged to the middle portion of the wheel support column, the oblique strut assembly includes a first oblique strut and a second oblique strut hinged to each other, and the second fuselage connecting portion is connected to the first oblique strut; the landing gear door strut mechanism also includes an actuator assembly, a lower lock assembly and a door strut; the connecting end of the actuator assembly is connected to one end of the wheel support column close to the first fuselage connecting portion, and the driving end of the actuator assembly is connected to the first oblique strut; the actuator assembly drives During the process of the landing gear door strut mechanism changing from a lowered state to a retracted state, the actuator assembly drives the lower lock assembly to open, and the first diagonal strut is folded relative to the second diagonal strut; during the process of the actuator assembly driving the landing gear door strut mechanism to change from a retracted state to a lowered state, the actuator assembly drives the first diagonal strut to unfold relative to the second diagonal strut, and the lower lock assembly locks the first diagonal strut with the second diagonal strut; the door strut includes a strut elastic member and a door connecting rod and a landing gear connecting rod arranged along the axial direction of the door strut, the first end of the door connecting rod is provided with a door connecting portion, the first end of the landing gear connecting rod is connected to the middle part of the second diagonal strut, and the second end of the door connecting rod is connected to the second end of the landing gear connecting rod through the strut elastic member.

[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 lower lock assembly 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 lower lock assembly 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 lower lock assembly 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.

[0010] A further solution is that the door strut also includes a strut outer tube, the door connecting rod, the strut elastic member and the landing gear connecting rod are all installed in the strut outer tube and arranged in sequence along the axial direction of the strut outer tube, and the two ends of the strut elastic member are respectively connected to the door connecting rod and the landing gear connecting rod; the door connecting rod is fixedly connected to the strut outer tube, and the landing gear connecting rod is slidably connected to the strut outer tube along the axial direction of the strut outer tube.

[0011] It can be seen that the door connecting rod, the strut elastic member and the landing gear connecting rod are all installed in the strut outer tube, which can ensure the stability of the landing gear connecting rod relative to the door connecting rod.

[0012] A preferred solution is that a spherical bearing is provided at the hatch connection portion.

[0013] It can be seen that the provision of the spherical bearing can improve the freedom of movement of the door relative to the door connecting rod, thereby ensuring smooth opening and closing of the door during the retraction and extension of the landing gear door strut mechanism.

[0014] A preferred solution is that a connecting rod is provided in the middle of the second diagonal strut, and the connecting rod extends in a direction perpendicular to the second diagonal strut; door struts are provided at both ends of the connecting rod, and the two door struts are arranged in parallel and perpendicular to the connecting rod; in the extension direction of the connecting rod, the wheel support column is located between the two door struts.

[0015] It can be seen that the two door struts are connected by a connecting rod to ensure synchronous control of the two doors, thereby ensuring the consistency of the movement of the two doors.

[0016] A preferred solution is that the actuator assembly includes an actuator body, a drive rod and a forced push piece, the actuator body is hinged to the wheel support column, and the forced push piece is arranged at the end of the drive rod; the two ends of the first oblique support rod are respectively hinged to the second fuselage connection part and the second oblique support rod, the middle part of the first oblique support rod is provided with a first support rod hinge shaft, a waist-shaped hole is provided on the forced push piece, and the first support rod hinge shaft cooperates with the waist-shaped hole; the lower lock assembly includes a lower lock buckle and a lower elastic member; the lower lock buckle is hinged to the first oblique support rod through the first hinge shaft and can be moved around the first hinge shaft between a locked position and an unlocked position Rotate, when the diagonal support rod assembly is in the expanded state, the lower lock buckle is in the locked position and engages the second diagonal support rod; the lower lock buckle is provided with an unlocking protrusion, and the two ends of the lower elastic member are respectively connected to the lower lock buckle and the first diagonal support rod; when the actuator body drives the above-mentioned driving rod to extend, the forced push member moves under the restriction of the waist-shaped hole and applies a force to the unlocking protrusion, forcing the lower lock buckle to rotate to the unlocking position; when the actuator body drives the above-mentioned driving rod to retract, 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.

[0017] 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 use of the retractable actuator to drive the folding and unfolding of the diagonal support rod and the unlocking and closing of the locking mechanism. Therefore, there is no need to additionally set up a second lock actuator, which meets the various usage requirements of small aircraft with simplified structure, strong practicality and light weight.

[0018] A further 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; the waist-shaped hole extends along the extension direction of the drive rod.

[0019] 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.

[0020] A further 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 a first snap-fit ​​protrusion is provided on the side of the first diagonal support rod away from the second hinge axis, and a second snap-fit ​​protrusion is provided on the side of the second diagonal support rod 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.

[0021] 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.

[0022] A further 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.

[0023] 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.

[0024] To achieve the above second objective, the present invention provides an aircraft landing gear, comprising the above landing gear door strut mechanism.

[0025] To achieve the third objective, the present invention provides an aircraft, comprising the above-mentioned aircraft landing gear. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is a structural diagram of an embodiment of an aircraft landing gear of the present invention in a lowered state.

[0027] Figure 2 It is a structural diagram of an embodiment of an aircraft landing gear of the present invention with some components hidden.

[0028] Figure 3 yes Figure 2 Enlarged view of point A in the middle.

[0029] 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.

[0030] Figure 5 It 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.

[0031] 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.

[0032] Figure 7 for Figure 6 Enlarged view of point B in the middle.

[0033] 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.

[0034] Fig. 9 for Figure 8 Enlarged view of point C in the middle.

[0035] Fig.10 It is a structural diagram of a door brace in an embodiment of an aircraft landing gear of the present invention.

[0036] Fig.11 It is a structural exploded view of a door brace in an embodiment of an aircraft landing gear of the present invention.

[0037] 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

[0038] 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 .

[0039] 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 .

[0040] 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.

[0041] 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.

[0042] See also Figure 1 and Figure 6 , Figure 1 The 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.

[0043] 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.

[0044] 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.

[0045] See also Figures 2 to 5 The 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.

[0046] 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.

[0047] 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.

[0048] 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.

[0049] 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.

[0050] 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.

[0051] 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.

[0052] 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.

[0053] 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.

[0054] 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.

[0055] 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.

[0056] 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 a wheel mounting portion and a first fuselage connecting portion are mounted on both ends of the wheel support column; An oblique brace assembly, wherein a first end of the oblique brace assembly is provided with a second fuselage connection portion, a second end of the oblique brace assembly is hinged to a middle portion of the wheel support column, the oblique brace assembly comprises a first oblique brace and a second oblique brace hinged to each other, and the second fuselage connection portion is connected to the first oblique brace; Features: The landing gear door strut mechanism also includes an actuator assembly, a lower lock assembly and a door strut; The connecting end of the actuator assembly is connected to one end of the wheel support column close to the first fuselage connecting portion, and the driving end of the actuator assembly is connected to the first diagonal support rod; When the actuating cylinder assembly drives the landing gear door strut mechanism to change from a lowered state to a retracted state, the actuating cylinder assembly drives the lower lock assembly to open, and the first diagonal strut is folded relative to the second diagonal strut; When the actuating cylinder assembly drives the landing gear door strut mechanism to change from the stowed state to the lowered state, the actuating cylinder assembly drives the first diagonal strut to unfold relative to the second diagonal strut, and the lower lock assembly locks the first diagonal strut with the second diagonal strut; The door strut comprises a strut elastic member, and a door link and a landing gear link arranged along the axial direction of the door strut, the first end of the door link is provided with a door connecting portion, the first end of the landing gear link is connected to the middle part of the second oblique strut, and the second end of the door link is connected to the second end of the landing gear link through the strut elastic member; The door strut also includes a strut outer tube, the door connecting rod, the strut elastic member and the landing gear connecting rod are all installed in the strut outer tube and arranged in sequence along the axial direction of the strut outer tube, and the two ends of the strut elastic member are respectively connected to the door connecting rod and the landing gear connecting rod; The door connecting rod is fixedly connected to the support rod outer tube, and the landing gear connecting rod is slidably connected to the support rod outer tube along the axial direction of the support rod outer tube; The actuator assembly comprises an actuator body, a driving rod and a forced push piece, wherein the actuator body is hinged to the wheel support column, and the forced push piece is arranged at the end of the driving rod; The two ends of the first oblique support rod are respectively hinged to the second fuselage connecting part and the second oblique support rod, the middle part of the first oblique support rod is provided with a first support rod hinge shaft, the forced push member is provided with a waist-shaped hole, and the first support rod hinge shaft cooperates with the waist-shaped hole; The lower lock assembly comprises a lower lock buckle and a lower elastic member; 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. When the diagonal support rod assembly is in an unfolded state, the lower lock buckle is in a locked position and buckles the second diagonal support rod; The lower lock buckle is provided with an unlocking protrusion, and the two ends of the lower elastic member are respectively connected to the lower lock buckle and the first diagonal support rod; When the actuator body drives the driving rod to extend, the forced push member moves under the restriction of the waist-shaped hole and 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 retract, 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 forced push member is provided with a forced push surface, which is arranged at one end of the forced push member away from the actuating cylinder body and inclined upward, and the unlocking protrusion can abut against the forced push surface; The waist-shaped hole extends along the extension direction of the driving rod; 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 expanded state, the first engaging protrusion and the second engaging protrusion overlap along the length direction of the diagonal brace assembly, and both the first engaging protrusion and the second engaging protrusion are engaged with the engaging groove.

2. The landing gear door brace mechanism according to claim 1, characterized in that: A spherical bearing is arranged at the door connection portion.

3. The landing gear door brace mechanism according to claim 1, characterized in that: A connecting rod is provided in the middle of the second diagonal brace, and the connecting rod extends in a direction perpendicular to the second diagonal brace; The door struts are arranged at both ends of the connecting rod, and the two door struts are arranged in parallel and perpendicular to the connecting rod; In the extending direction of the connecting rod, the wheel supporting column is located between the two door struts.

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. Aircraft landing gear, characterized in that: It comprises a landing gear door brace mechanism as claimed in any one of claims 1 to 4.

6. An aircraft, characterized in that Comprising an aircraft landing gear as claimed in claim 5.

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