Landing gear diagonal strut mechanism, aircraft landing gear and aircraft

Abstract

The present invention provides a landing gear diagonal brace mechanism, an aircraft landing gear and an aircraft, wherein the locking mechanism of the landing gear diagonal brace mechanism further comprises a forcing member, a first column connecting member, a connecting rod member and a second column connecting member; the forcing member is provided with a first waist-shaped hole, the first column connecting member is fixedly connected to the first diagonal brace, and the first column connecting member cooperates with the first waist-shaped hole; the first diagonal brace is provided with a second waist-shaped hole, the second column connecting member is fixedly connected to the connecting rod member, and the second column connecting member cooperates with the second waist-shaped hole; the connecting rod member is hinged with the locking member, and driven by the retractable actuator, the forcing member moves along the first waist-shaped hole and pushes the second column connecting member to move along the second waist-shaped hole to force the locking member to swing. The aircraft landing gear comprises the above-mentioned landing gear diagonal brace mechanism. The aircraft comprises the above-mentioned aircraft landing gear. The present invention uses an actuator to simultaneously drive the diagonal brace and the locking mechanism to move, thereby meeting the multi-faceted use requirements of a small aircraft with a simplified structure, strong practicality and light weight.

Description

Technical Field

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

[0002] The aircraft landing gear system includes a landing gear strut, a landing gear retractable actuator cylinder and a landing gear diagonal strut mechanism. The landing gear diagonal strut mechanism includes an upper diagonal strut, a lower diagonal strut and a locking mechanism. The upper diagonal strut and the lower diagonal strut are hinged to each other. The retractable actuator cylinder is hinged to the upper diagonal strut. When the retractable actuator cylinder is operated, the upper diagonal strut and the lower diagonal strut are rotated relative to each other, and the upper diagonal strut and the lower diagonal 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 diagonal brace mechanism of the landing gear. The locking mechanism is driven by another locking cylinder. 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 locking cylinder 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 locking cylinder 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 diagonal brace mechanism which can drive the diagonal brace and the locking mechanism to move only by retracting and extending an actuating cylinder.

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

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

[0008] The first purpose of the present invention provides a landing gear diagonal strut mechanism comprising a first diagonal strut, a second diagonal strut, a locking mechanism and a retractable actuator, the locking mechanism comprising a locking member, the locking member is connected to the first diagonal strut and can rotate around a first axis between a locked position and an unlocked position, when the landing gear diagonal strut mechanism is in an expanded state, the locking member in the locked position engages with the second diagonal strut; the locking mechanism also comprises a forcing member, a first column connecting member, a connecting rod member, a second column connecting member and an elastic member; the forcing member is provided with a first waist-shaped hole, the first column connecting member is fixedly connected to the first diagonal strut, and the first column connecting member cooperates with the first waist-shaped hole; the first diagonal strut is provided with a second waist-shaped hole, the second column connecting member is fixedly connected to the first end of the connecting rod member, and the first The two-column connecting member cooperates with the second waist-shaped hole; the elastic member is pulled between the extended middle part of the connecting rod and the first diagonal support rod, the second end of the connecting rod and the locking member are hinged at the second axis, the first end of the forcing member is connected to the retracting actuator cylinder, and the second end of the forcing member abuts against the second column connecting member; in the process of the retracting actuator cylinder driving the landing gear diagonal support rod mechanism to change from the deployed state to the folded state, the forcing member moves under the restriction of the first waist-shaped hole and pushes the second column connecting member to move along the second waist-shaped hole under the drive of the retracting actuator cylinder, the connecting rod moves with the second column connecting member and forces the locking member to rotate from the locked position to the unlocked position; the action force of the elastic member tends to force the locking member to rotate from the unlocked position to the locked position.

[0009] It can be seen from the above scheme that the present invention uses the landing gear retracting and extending actuator to drive the diagonal strut movement and simultaneously links the locking member as the basis for improvement. In the improvement of the present invention, it is not only considered how to reduce components and which components to reduce, but also how to ensure that the landing gear movement still works normally after reducing the components. It is necessary to consider how to design the linkage structure to maintain the previous action rules of the retracting and extending actuator and the previous action rules of the locking member, while also satisfying the swing of the locking member and the swing of the second diagonal strut in accordance with the timeline, ensuring that it is unlocked first and then swung. Mainly, it is achieved based on the first waist-shaped hole and the second waist-shaped hole. When the actuator is extended, it will drive the diagonal strut mechanism to bend and retract the landing gear. The contraction of the actuator will drive the diagonal strut mechanism to unfold and lower the landing gear. The landing gear diagonal support rod mechanism is in the deployed state and the lock catch is in the locked position as the initial state. Since the sliding resistance of the first column connecting member in the first waist-shaped hole is small and the resistance of opening the landing gear is large, when the actuator is extended, it will first move along the first waist-shaped hole to push the second column connecting member, and then the linkage lock catch will be unlocked. After reaching the limit position of the first waist-shaped hole, it will 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 member, through the transmission of force, to achieve the unlocking and locking of the diagonal support rod locking mechanism by connecting the retractable actuator cylinder, successfully eliminating the second lock actuator cylinder in the prior art, and meeting the multi-party use requirements of the simplified structure, strong practicality and light weight of small aircraft.

[0010] A further solution is that the length direction of the first waist-shaped hole is the same as the length direction of the forcing member, the length direction of the second waist-shaped hole is the same as the length direction of the first diagonal support rod, and along the length direction of the first diagonal support rod, the position of the first column connecting member is closer to the second diagonal support rod than the position of the second waist-shaped hole; the length direction of the first waist-shaped hole is inclined to the length direction of the second waist-shaped hole, and under the axial projection of the first column connecting member, the second end of the forcing member is provided with an arm portion which extends outwardly from its own length direction and whose width gradually narrows, and the arm portion abuts against the second column connecting member.

[0011] As can be seen from the above, it is necessary to further consider the pushing effect of the forcing member on the second column connecting member. Generally, the actuator will be inclined to the first diagonal support rod. If the pushing direction of the forcing member is consistent with the length direction of the actuator, a low displacement conversion ratio will occur. If the pushing direction of the forcing member is perpendicular to the length direction of the actuator, that is, similar to a flat push, although this method can have the largest displacement conversion amount, it can enable the second column connecting member to move a greater distance in the second waist-shaped hole, but the resistance increases when pushing. If the resistance is greater than the resistance of the open landing gear, the problem of unlocking later than folding may occur, resulting in failure to unlock normally. In addition, in fact, the swing amplitude required for unlocking the lock is not large, and the swing amplitude of the lock can be increased at the same angle by improving the arm length from the lock to the first axis. Therefore, the present invention further tilts the arm portion on the forcing member for forcing abutment, so that the direction of the arm portion is inclined to the length direction of the actuator, which meets the swing amplitude requirement of the lock, and also reduces the resistance to ensure the sequence of the lock action and the second diagonal support rod action, and ensure the effectiveness of the unlocking first and then folding action.

[0012] A further solution is that the first diagonal support rod includes a first extension end away from the second diagonal support rod, the first diagonal support rod is provided with a protruding first connecting seat at a position close to the first extension end, and the second waist-shaped hole is provided on the first connecting seat.

[0013] As can be seen from the above, according to the above, the present invention needs to make further considerations on the rotation range of the locking member. For this purpose, the arm length from the first axis along which the locking member rotates to the locking portion, the length of the connecting rod that drags the locking member to swing, the distance from the first axis to the second axis, etc., all need to have sufficient space for adjustment, especially the above arm length needs to have a certain size. For this reason, the present invention sets the first connecting seat with the second waist-shaped hole as far away from the second diagonal support rod as possible, so that from the second waist-shaped hole to the second diagonal support rod, the connecting rod and the locking member have better adjustment space, so as to achieve a more ideal motion conversion ratio from the translation of the second column connecting member to the swing of the locking member, and to achieve more accurate movement and sequence of movements.

[0014] A further solution is that the first column connecting member adopts a first bolt, and the landing gear diagonal strut mechanism also includes a first nut and a first spring pin. The first bolt passes through the first through hole and the first waist-shaped hole of the first diagonal strut and then cooperates with the first nut thread and is locked by the first spring pin; the second column connecting member adopts a second bolt, and the landing gear diagonal strut mechanism also includes a second nut and a second spring pin. The second bolt passes through the second through hole and the second waist-shaped hole of the connecting rod and then cooperates with the second nut thread and is locked by the second spring pin.

[0015] As can be seen from the above, this arrangement reduces the difficulty of disassembling, assembling and adjusting the lock mechanism while ensuring the reliability of the structure.

[0016] A further solution is that a raised second connecting seat is provided on the first diagonal support rod, the raised direction of the second connecting seat is the same as that of the first connecting seat, the second connecting seat is provided with a first connecting portion extending along the length direction of the first diagonal support rod, and the first connecting portion is staggered from the connecting rod member in the axial direction; a third connecting seat is provided in the extended middle part of the connecting rod member, the second connecting portion is provided on the third connecting seat, and the second connecting portion is staggered from the connecting rod member in the axial direction; the elastic member is a tension spring, and the two ends of the tension spring are respectively pulled between the second connecting portion and the third connecting seat.

[0017] As can be seen from the above, it is necessary to further consider the arrangement of the elastic member and to avoid the elastic member from hindering the action of the lock mechanism. To this end, the present invention locks the first and second connecting parts of the torsion spring at both ends, and the first and second connecting parts are both outside the plane where the diagonal support rod mechanism is located. In this way, the spring and the diagonal support rod mechanism are staggered in three-dimensional space, and there will be no interference and obstruction between the two during the action, ensuring the effectiveness of the action process.

[0018] Another further solution is that the locking member includes a locking portion for locking with the second diagonal support rod, the locking portion, the first axis and the second axis are distributed in a triangle, and a first distance from the first axis to the locking portion is greater than a distance from the first axis to the second axis.

[0019] As can be seen from the above, this arrangement makes the arm length from the first axis to the snap-fitting part longer, and can make the locking part swing with a larger amplitude at the same swing angle. In this way, the connecting rod can unlock the locking part with a smaller displacement, reducing the design difficulty of the linkage structure of the locking mechanism.

[0020] A further solution is that the snap-fitting portion includes a snap-fitting recess; the first diagonal strut includes a first flange portion, and the second diagonal strut includes a second flange portion. When the landing gear diagonal strut mechanism is in an expanded state, the first flange portion overlaps with the second flange portion, and the first flange portion and the second flange portion are restricted by the snap-fitting recess from the front and rear sides of the length direction of the first diagonal strut.

[0021] As can be seen from the above, in the existing diagonal support rod mechanism, the first inclined surface of the lock part in the locked position only buckles the second inclined surface of the second diagonal support rod. This design method actually has a high matching accuracy between the lock part and the second diagonal support rod. Both the front and rear sides of the swing direction of the lock part need to be structurally reinforced, otherwise the risk of disengagement is high. The main purpose of the present invention is to simplify the structure. For this purpose, the lock part is set as a square concave buckling recess and a flange part is set on the diagonal support rod. After the two flange parts are overlapped and the buckling part is buckled, the two overlapping flange parts will be in the buckling recess and restricted from rotating. Under this setting method, the force of separating the two flange parts will not cause the lock part to swing, so there will be no risk of disengagement, and the setting of the reinforcement structure can also be reduced.

[0022] A further solution is that the hinge between the first diagonal strut and the second diagonal strut protrudes from the first outer side of the landing gear diagonal strut mechanism, the first edge of the first flange portion and the second edge of the second flange portion protrude from the second outer side of the landing gear diagonal strut mechanism opposite to the first outer side, and the engaging recess engages the first edge and the second edge; the retractable actuator is arranged on the first outer side, and the first connecting seat, the second connecting seat, the connecting rod member, the elastic member and the locking member are all arranged on the second outer side.

[0023] As can be seen from the above, the position of the lower locking mechanism is arranged away from the position after the second diagonal support rod is folded, so as not to affect the folding of the second diagonal support rod, thereby ensuring that the landing gear retraction and extension action is effectively performed.

[0024] The second object of the present invention is to provide an aircraft landing gear comprising the above-mentioned landing gear diagonal strut mechanism.

[0025] The third object of the present invention is to provide an aircraft comprising the above-mentioned aircraft landing gear. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is a structural diagram of the landing gear diagonal brace mechanism embodiment of the present invention in the unfolded state.

[0027] Figure 2 for Figure 1 Enlarged view of point A in the middle.

[0028] Figure 3 for Figure 1 Enlarged view of point B in the middle.

[0029] Figure 4 It is a structural diagram of the landing gear diagonal brace mechanism embodiment of the present invention in a folded state.

[0030] Figure 5 for Figure 4 Enlarged view of point C in the middle.

[0031] Figure 6 for Figure 4 Enlarged view of point D in the middle. DETAILED DESCRIPTION

[0032] See also Figures 1 to 3 The aircraft of the present invention includes an aircraft landing gear, and the aircraft landing gear includes the landing gear diagonal brace rod mechanism of the present embodiment. The landing gear diagonal brace rod mechanism of the present embodiment includes a first diagonal brace rod 1, a second diagonal brace rod 2, a retractable actuator cylinder 3 and a locking mechanism. The locking mechanism includes a forcing member 4, a connecting rod member 5, a first bolt member 61, a second bolt member 62, a tension spring 7 and a locking member 8, wherein the first bolt member 61 includes a first bolt 611, a first nut 612 and a first spring pin 613, the second bolt member 62 includes a second bolt 621, a second nut 622 and a second spring pin 623, the first bolt 611 and the second bolt 621 are respectively the first column connecting member and the second column connecting member in the present invention, and the tension spring 7 is the elastic member of the present invention.

[0033] See first Figure 1 and Figure 4 , Figure 1 The figure shows the landing gear diagonal strut mechanism in the deployed state. Figure 4 The figure shows the landing gear diagonal brace mechanism in the folded state. The first diagonal brace 1 and the second diagonal brace 2 are both straight rods, and the first hinged portion 19 of the first diagonal brace 1 and the second hinged portion 29 of the second diagonal brace 2 are hinged to the third axis 93 through a third bolt member. Figure 1 In the unfolded state shown, the first diagonal brace rod 1 and the second diagonal brace rod 2 are unfolded colinearly along a straight line in the y-axis direction. In this state, the y-axis direction shows the length direction of the first diagonal brace rod 1 and the second diagonal brace rod 2 . Figure 4 In the folded state shown, the first diagonal brace rod 1 and the second diagonal brace rod 2 are folded and are respectively located on two straight lines parallel to each other.

[0034] Combination Figure 1 and Figure 3 In the dimension direction of the landing gear diagonal brace mechanism shown in the x-axis direction, the landing gear diagonal brace mechanism includes a first outer side 101 and a second outer side 102 arranged opposite to each other. Mainly, the first outer side 101 and the second outer side 102 refer to the outer side of the first diagonal brace 1 or the second diagonal brace 2, respectively. The hinge between the first diagonal brace 1 and the second diagonal brace 2, where the third axis 93 is located, protrudes from the first outer side 101 of the landing gear diagonal brace mechanism, and the hinge between the first diagonal brace 1 and the second diagonal brace 2 protrudes from the first outer side 101 of the landing gear diagonal brace mechanism. Figure 4 In the folded state, the second diagonal brace 2 is also located at the first outer side 101. In addition, the first diagonal brace 1 includes a first flange portion 17, and the second diagonal brace 2 includes a second flange portion 27. When the landing gear diagonal brace mechanism is in the unfolded state, the first flange portion 17 overlaps with the second flange portion 27, and the first edge 171 of the first flange portion 17 and the second edge 271 of the second flange portion 27 protrude from the second outer side 102 of the landing gear diagonal brace mechanism. In addition, the retractable actuator 3 is also located at the first outer side 101.

[0035] See also Figures 1 to 3 In this embodiment, in the lock mechanism, except for the forcing member 4 spanning between the first outer side 101 and the second outer side 102, other components such as the connecting rod 5, the tension spring 7 and the lock member 8 are mainly arranged on the second outer side 102. The forcing member 4 is provided with a first waist-shaped hole 40, and the length direction of the first waist-shaped hole 40 is consistent with the length direction of the forcing member 4. Figure 2 As shown in the u-axis direction; the first bolt 611 is fixedly connected to the first diagonal support rod 1, the first bolt 611 cooperates with the first waist-shaped hole 40, and the first bolt 611 passes through the first through hole of the first diagonal support rod 1 and the first waist-shaped hole 40 and then cooperates with the first nut 612 threadedly and is locked by the first spring pin 613.

[0036] The first end 41 of the forcing member 4 in the length direction is connected to the retractable actuator 3, and the forcing member 4 extends along the u-axis direction shown in the figure. It can be seen that the length direction of the forcing member 4 is inclined to the length direction of the first diagonal support rod 1; the second end of the forcing member 4 in the length direction, which is opposite to the first end 41, is provided with an arm 42 extending incline to its own length direction and gradually narrowing in width under the axial projection of the first bolt 611, and the length direction of the arm 42 is indented. Figure 2 The v-axis direction is shown. Figure 2 In this embodiment, relative to the y-axis direction, the v-axis direction is more inclined to the x-axis direction, that is, under the axial projection of the first bolt 611, relative to the length direction of the first diagonal support rod 1, the angle between the length direction of the arm portion 42 and the length direction of the first diagonal support rod 1 is greater than 45 degrees.

[0037] The first diagonal brace 1 includes a first extension end 109 away from the second diagonal brace 2 and a second extension end 108 close to the second diagonal brace 2. The first flange portion 17 is connected to the second extension end 108; the first diagonal brace 1 is provided with a first connection seat 11 protruding from the second outer side 102 at a position close to the first extension end 109, and a second waist-shaped hole 110 is provided on the first connection seat 11, and the length direction of the second waist-shaped hole 110 is the same as the length direction of the first diagonal brace 1. Along the length direction of the first diagonal brace 1, the position of the first bolt 611 is closer to the second diagonal brace 2 than the position of the second waist-shaped hole 110; the length direction of the first waist-shaped hole 40 is inclined to the length direction of the second waist-shaped hole 110.

[0038] The second bolt 621 is fixed to the first end 51 of the connecting rod 5, and the second bolt 621 is matched with the second waist-shaped hole 110. The second bolt 621 passes through the second through hole of the connecting rod 5 and the second waist-shaped hole 110, and then is threadedly matched with the second nut 622 and locked by the second spring pin 623. The arm portion 42 on the second end of the forcing member 4 abuts against the second bolt 621.

[0039] See also Figures 1 to 3, the first diagonal brace 1 is provided with a second connection seat 12 protruding from the second outer side 102, the protruding direction of the second connection seat 12 is the same as the protruding direction of the first connection seat 11, and the second connection seat is provided with a first connection portion 121 extending along the length direction of the first diagonal brace 1, the first connection portion 121 is a connection plate, and in the axial direction of the first axis 91, the first connection portion 121 is staggered with the connecting rod 5. A third connection seat 53 is provided in the extended middle part of the connecting rod 5, and a second connection portion 531 is provided on the third connection seat 53, and the second connection portion 531 is a connection plate, and in the axial direction, the second connection portion 531 is staggered with the connecting rod 5, and the two ends of the tension spring 7 are pulled between the first connection portion 121 and the second connection portion 531 respectively. Among them, the z-axis direction shown in the figure is the above-mentioned axial direction, the first axis 91, the second axis 92 and the third axis 93 are parallel to each other, and the axial direction is the axial direction of the first axis 91.

[0040] See also Figure 3 The locking member 8 includes a locking portion. In the present embodiment, the locking portion is a locking recess 810 with a square inner contour. The locking recess 810, the first axis 91 and the second axis 92 are distributed in a triangular shape. The first distance L1 from the first axis 91 to the locking recess 810 is greater than the distance L2 from the first axis 91 to the second axis 92. The locking member 8 is hinged to the above-mentioned second connecting seat 12 at the first axis 91, and the second end 52 of the connecting rod 5 opposite to the first end 51 is hinged to the locking member 8 at the second axis 92. In the present embodiment, the position of the first axis 91 is not close to the second diagonal support rod 2. By providing an extension portion 81 starting from the first axis 91 and having a longer length on the locking member 8, the locking recess 810 is provided at the tail of the extension portion 81, so that the locking recess 810 can be fastened to the second diagonal support rod 2, and it is ensured that the locking member 8 can swing sufficiently during the linkage process to meet the requirements of reaching the locked position and the unlocked position.

[0041] See also Figures 1 to 3 The tension spring 7 is pulled between the extended middle portion of the connecting rod 5 and the first diagonal support rod 1, and the force of the tension spring 7 tends to force the lock member 8 to rotate from the unlocking position to the locking position. Figure 1 In the unfolded state shown, the first flange portion 17 and the second flange portion 27 overlap each other, and the locking member 8 is in the locked position. At this time, the locking recess 810 locks the first edge 171 of the first flange portion 17 and the second edge 271 of the second flange portion 27. The first flange portion 17 and the second flange portion 27 are restricted from the front and rear sides of the length direction of the first diagonal support rod 1 by the locking recess 810, and the restriction effect is maintained under the action of the torsion spring 7, thereby achieving locking.

[0042] Combination Figures 4 to 6 When the retractable actuator 3 is extended, it will drive the diagonal support rod mechanism to bend and retract the landing gear. When the retractable actuator 3 is contracted, it will drive the diagonal support rod mechanism to expand and lower the landing gear. Figures 1 to 3The landing gear diagonal strut mechanism is in the deployed state and the lock member 8 is in the locked position as the initial state. Since the sliding resistance of the first bolt 611 in the first waist-shaped hole 40 is small and the resistance of opening the landing gear is large, when the retracting and releasing cylinder 3 is extended, the forcing member 4 is driven first. The forcing member 4 moves under the restriction of the first waist-shaped hole 40 and causes the arm 42 to push the second bolt 621 to move along the second waist-shaped hole 110. The connecting rod 5 moves with the second bolt 621 and pulls the lock member 8, forcing the lock member 8 to rotate from the locked position to the unlocked position. After the linkage lock member 8 is unlocked, after the first bolt 611 reaches the limit position of the first waist-shaped hole 40, the retracting and releasing cylinder 3 that continues to extend begins to drive the second diagonal strut 2 to swing and fold.

[0043] It can be seen that the present invention is based on the design of the first waist-shaped hole 40 and the second waist-shaped hole 110, and under the premise of maintaining the previous action rules of the retractable actuator 3 and the previous action rules of the lock member 8, it can also meet the swing of the lock member 8 and the swing of the second diagonal support rod 2 in accordance with the timeline, ensuring that the lock is unlocked first and then swung. Of course, more importantly, the retractable actuator 3 is connected to the diagonal support rod lock mechanism to unlock and lock, successfully eliminating the second lock actuator in the prior art, and meeting the simplified structure, strong practicality, and light weight of the small aircraft. Multiple use requirements.

[0044] In this embodiment, preferably, the first bolt 611 and / or the second bolt 621 include a partial screw rod, and the first bolt 611 and / or the second bolt 621 include an optical axis segment and a threaded segment connected in sequence, the optical axis segment is used for rotational connection or abutment, and the threaded segment is used for threaded connection.

[0045] In other embodiments, the first column connecting member and / or the second column connecting member is an optical axis member.

[0046] In other embodiments, the elastic member is a spring sheet capable of generating tension.

[0047] In other embodiments, the locking portion is an L-shaped buckle, and the locking portion is only buckled with the structure on the second diagonal support rod but not with the first diagonal support rod.

[0048] 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. A landing gear diagonal brace mechanism, comprising a first diagonal brace, a second diagonal brace, a locking mechanism and a retractable actuator, wherein the locking mechanism comprises a locking member, the locking member is connected to the first diagonal brace and can rotate around a first axis between a locking position and an unlocking position, and when the landing gear diagonal brace mechanism is in an extended state, the locking member in the locking position is engaged with the second diagonal brace; Features: The locking mechanism further comprises a forcing member, a first column connecting member, a connecting rod member, a second column connecting member and an elastic member; The forcing member is provided with a first waist-shaped hole, the first column connecting member is fixedly connected to the first diagonal support rod, and the first column connecting member is matched with the first waist-shaped hole; The first diagonal brace is provided with a second waist-shaped hole, the second column connecting member is fixedly connected to the first end of the connecting rod, and the second column connecting member is matched with the second waist-shaped hole; The elastic member is pulled between the extended middle portion of the connecting rod and the first diagonal support rod, the second end of the connecting rod is hinged to the locking member at the second axis, the first end of the forcing member is connected to the retractable actuator, and the second end of the forcing member is in contact with the second column connecting member; In the process of the retractable actuator cylinder driving the landing gear diagonal support rod mechanism to change from the deployed state to the folded state, the forcing member is driven by the retractable actuator cylinder to move under the restriction of the first waist-shaped hole and push the second column connecting member to move along the second waist-shaped hole, and the connecting rod moves with the second column connecting member and forces the locking member to rotate from the locked position to the unlocked position; The force of the elastic member tends to force the locking member to rotate from the unlocking position to the locking position; The length direction of the first waist-shaped hole is the same as the length direction of the forcing member, the length direction of the second waist-shaped hole is the same as the length direction of the first diagonal brace, and along the length direction of the first diagonal brace, the position of the first column connecting member is closer to the second diagonal brace than the position of the second waist-shaped hole; The length direction of the first waist-shaped hole is inclined to the length direction of the second waist-shaped hole. Under the axial projection of the first column connecting piece, the second end of the forcing piece is provided with an arm portion extending obliquely to its own length direction and with a gradually narrowing width, and the arm portion abuts against the second column connecting piece; The first diagonal brace comprises a first extending end away from the second diagonal brace, the first diagonal brace is provided with a protruding first connecting seat at a position close to the first extending end, and the second waist-shaped hole is provided on the first connecting seat; A protruding second connection seat is provided on the first diagonal support rod, the protruding direction of the second connection seat is the same as the protruding direction of the first connection seat, and a first connection portion extending along the length direction of the first diagonal support rod is provided on the second connection seat, and in the axial direction, the first connection portion is staggered with the connecting rod member; A third connecting seat is provided at the extended middle portion of the connecting rod, a second connecting portion is provided on the third connecting seat, and the second connecting portion is staggered with the connecting rod in the axial direction; The elastic member is a tension spring, and two ends of the tension spring are respectively pulled between the second connecting portion and the third connecting seat; The locking member comprises a buckling portion for buckling with the second diagonal support rod, the buckling portion, the first axis and the second axis are distributed in a triangle, and a first distance from the first axis to the buckling portion is greater than a distance from the first axis to the second axis; The buckling portion includes a buckling recess; The first diagonal brace includes a first flange portion, and the second diagonal brace includes a second flange portion. When the landing gear diagonal brace mechanism is in the deployed state, the first flange portion overlaps with the second flange portion, and the first flange portion and the second flange portion are restricted by the buckling recess from both front and rear sides of the length direction of the first diagonal brace; The hinge between the first diagonal brace and the second diagonal brace protrudes from a first outer side of the landing gear diagonal brace mechanism, the first edge of the first flange portion and the second edge of the second flange portion protrude from a second outer side of the landing gear diagonal brace mechanism opposite to the first outer side, and the buckling recess buckles the first edge and the second edge; The retractable actuator is arranged on the first outer side, and the first connecting seat, the second connecting seat, the connecting rod, the elastic member and the locking member are all arranged on the second outer side.

2. The landing gear diagonal brace mechanism according to claim 1, characterized in that: The first column connecting member adopts a first bolt, and the landing gear diagonal support rod mechanism also includes a first nut and a first spring pin. The first bolt passes through the first through hole of the first diagonal support rod and the first waist-shaped hole, and then cooperates with the first nut thread and is locked by the first spring pin; The second column connecting member adopts a second bolt, and the landing gear diagonal support rod mechanism also includes a second nut and a second spring pin. After the second bolt passes through the second through hole of the connecting rod member and the second waist-shaped hole, it is threadedly matched with the second nut and locked by the second spring pin.

3. Aircraft landing gear, characterized in that: The landing gear diagonal brace mechanism comprises the above-mentioned any one of claims 1 to 2.

4. An aircraft, characterized in that The invention comprises an aircraft landing gear as described in claim 3 above.

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