CN118753496B - Landing gear diagonal strut mechanism, aircraft landing gear and aircraft - Google Patents
Landing gear diagonal strut mechanism, aircraft landing gear and aircraft Download PDFInfo
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- CN118753496B CN118753496B CN202411215097.8A CN202411215097A CN118753496B CN 118753496 B CN118753496 B CN 118753496B CN 202411215097 A CN202411215097 A CN 202411215097A CN 118753496 B CN118753496 B CN 118753496B
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- 238000006073 displacement reaction Methods 0.000 description 4
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/26—Control or locking systems therefor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
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- Aviation & Aerospace Engineering (AREA)
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Abstract
本发明提供一种起落架斜撑杆机构、飞机起落架和飞机，起落架斜撑杆机构的锁机构还包括逼迫件、第一柱连接件、连杆件和第二柱连接件；逼迫件设置第一腰型孔，第一柱连接件与第一斜撑杆固接，第一柱连接件与第一腰型孔配合；第一斜撑杆设置第二腰型孔，第二柱连接件与连杆件固接，第二柱连接件与第二腰型孔配合；连杆件与锁扣件铰接，收放作动筒带动下，逼迫件沿第一腰型孔移动并推动第二柱连接件沿第二腰型孔移动以逼迫锁扣件摆动。飞机起落架包括上述的起落架斜撑杆机构。飞机包括上述的飞机起落架。本发明由一个作动筒同时带动斜撑杆动作以及带动锁机构动作，满足小型飞机的简化结构、实用性强、重量轻的多方使用需求。
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
The invention relates to the technical field of aircrafts, in particular to an undercarriage diagonal bracing mechanism, an aircraft undercarriage and an aircraft.
Background
The landing gear system comprises landing gear struts, a retraction actuator and a landing gear diagonal brace mechanism of the landing gear, wherein the landing gear diagonal brace mechanism comprises an upper diagonal brace, a lower diagonal brace and a lock mechanism, the upper diagonal brace and the lower diagonal brace are mutually hinged, the retraction actuator is hinged with the upper diagonal brace, the retraction actuator works to enable the upper diagonal brace and the lower diagonal brace to relatively rotate, and the upper diagonal brace and the lower diagonal brace are transformed between an unfolding state and a folding state which are extended in a straight line.
The lock mechanism of the diagonal brace is used as an important component of the diagonal brace mechanism of the landing gear, the lock mechanism is driven by another lock actuator, the lock mechanism mainly comprises a lock catch piece which can be driven and is rotationally connected to one diagonal brace, when the diagonal brace is completely unfolded, the lock actuator works to lock the butt joint parts of the two diagonal braces by the lock catch piece, so that after the landing gear is put down, the diagonal brace can keep in an unfolded state to reliably support the landing gear support. When the diagonal braces need to be folded, the lock actuating cylinder drives the lock catch piece to leave the butt joint part, so that the two diagonal braces are restored to rotate to unlock, and the landing gear is folded.
There is a need for improvements in landing gear systems for small aircraft. In view of the foregoing, existing aircraft landing gear systems, including two rams, a landing gear ram and a lock ram, do not meet the practical requirements of a compact aircraft for simplicity and light weight.
Disclosure of Invention
The first object of the present invention is to provide a landing gear diagonal bracing mechanism which can drive the diagonal bracing to act and drive the lock mechanism to act only by retracting the actuating cylinder.
A second object of the present invention is to provide an aircraft landing gear having the landing gear diagonal strut mechanism described above.
A third object of the present invention is to provide an aircraft with an aircraft landing gear as described above.
The landing gear diagonal brace mechanism comprises a first diagonal brace, a second diagonal brace, a locking mechanism and a retraction actuator, wherein the locking mechanism comprises a locking piece, the locking piece is connected with the first diagonal brace and can rotate around a first axis between a locking position and an unlocking position, when the landing gear diagonal brace mechanism is in an unfolding state, the locking piece in the locking position is buckled with the second diagonal brace, the locking mechanism further comprises a forcing piece, a first column connecting piece, a second column connecting piece and an elastic piece, the forcing piece is provided with a first waist-shaped hole, the first column connecting piece is fixedly connected with the first diagonal brace, the first column connecting piece is matched with the first waist-shaped hole, the first diagonal brace is provided with a second waist-shaped hole, the second column connecting piece is fixedly connected with a first end of the connecting piece, the second end of the connecting piece is hinged with the second axis between the first diagonal brace and the locking piece, the first end of the forcing piece is connected with the retraction actuator, the second end of the second column connecting piece is connected with the second column connecting piece, the second column connecting piece is driven by the second column connecting piece, the first end of the second column connecting piece is in the second waist-shaped hole, the first waist-shaped hole is driven by the second column connecting piece, the second column connecting piece is driven by the second column connecting piece to move from the second column connecting piece to the locking piece to the retraction actuator, the locking mechanism is driven by the second waist-shaped hole, the second waist-shaped connecting piece is driven by the second waist-shaped connecting piece to move from the first waist-shaped connecting piece to the first waist-shaped hinge, and drive the locking piece to the locking piece from the first waist-shaped hinge, and push rod to the first waist-shaped hinge.
The proposal shows that the invention adopts the landing gear retraction actuator cylinder to drive the diagonal brace to act and simultaneously links the locking piece as an improvement basis. In the improvement of the invention, not only how to reduce the parts and which parts are reduced, but also how to ensure that the landing gear still works normally after the parts are reduced. The linkage structure is designed to ensure that the locking piece swings and the second diagonal brace swings according to a time line and the locking piece is unlocked and then swings on the premise that the former action rule of the retractable actuating cylinder and the former action rule of the locking piece are maintained. Mainly based on a first waist-shaped hole and a second waist-shaped hole. When the actuating cylinder stretches, the inclined strut mechanism is driven to bend and retract the landing gear, and when the actuating cylinder contracts, the inclined strut mechanism is driven to expand and release the landing gear. The landing gear diagonal bracing mechanism is in an unfolding state, the locking piece is in a locking position and is in an initial state, and the first column connecting piece slides in the first waist-shaped hole to have smaller sliding resistance and larger landing gear supporting resistance, so that when the actuating cylinder stretches, the actuating cylinder moves along the first waist-shaped hole to push the second column connecting piece, then the locking piece is linked to unlock, and the second diagonal bracing rod is driven to swing and fold after reaching the limit position of the first waist-shaped hole. Therefore, the invention utilizes the characteristic of the kidney-shaped hole, realizes unlocking and locking by communicating the telescopic actuator cylinder with the diagonal bracing rod lock mechanism through force transmission through the change of the relative displacement of the stressed piece, successfully cancels the second lock actuator cylinder in the prior art, and meets the multi-direction use requirements of simplified structure, strong practicability and light weight of the small aircraft.
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, the position of the first column connecting member is closer to the second diagonal brace than the position of the second waist-shaped hole along the length direction of the first diagonal brace, the length direction of the first waist-shaped hole is inclined to the length direction of the second waist-shaped hole, the second end of the forcing member is provided with an arm part which is inclined to the length direction of the forcing member and gradually narrows in width under the axial projection of the first column connecting member, and the arm part is in abutting contact with the second column connecting member.
From the above, it is necessary to further consider the pushing effect of the urging member on the second column connecting member. Generally, the actuator cylinder is arranged obliquely to the first diagonal brace, if the pushing direction of the forcing member is consistent with the length direction of the actuator cylinder, the problem of low displacement conversion ratio can be generated, if the pushing direction of the forcing member is perpendicular to the length direction of the actuator cylinder, namely similar to flat pushing, although the mode can have the maximum displacement conversion amount, the second column connecting member can move a larger distance in the second waist-shaped hole, but the resistance is increased during pushing, if the resistance is larger than the resistance of the supporting gear, the problem that the unlocking is later than the folding can occur, and the normal unlocking can not be caused, and in fact, the swing amplitude of the locking part is not large by improving the arm length of the locking part to the first axis, and the swing amplitude of the locking part can be increased under the same angle.
Still further, the first diagonal brace comprises a first extension end far away from the second diagonal brace, the first diagonal brace is provided with a raised first connection seat at a position close to the first extension end, and the second waist-shaped hole is arranged on the first connection seat.
From the above, it can be seen that the present invention needs to further consider the rotation range of the locking member, for which, the arm length from the first axis to the locking portion, the length of the link member for dragging the locking member to swing, the distance from the first axis to the second axis, etc. on the locking member need to be adjusted sufficiently, and especially the arm length needs to have a certain size. Therefore, the first connecting seat provided with the second waist-shaped hole is arranged far away from the second diagonal brace as far as possible, so that the connecting rod piece and the locking piece have better adjustment space from the second waist-shaped hole to the second diagonal brace, and the movement quantity conversion ratio from the translation of the second column connecting piece to the swinging of the locking piece can be more ideal, and the movement precision and the movement sequence accuracy can be more favorably realized.
The landing gear diagonal brace mechanism further comprises a second nut and a second spring pin, wherein the second bolt is used for the second column connecting piece, and the second bolt is matched with the second nut in a threaded manner and is locked by the second spring pin after passing through the second through hole and the second waist-shaped hole of the connecting piece.
Therefore, the structure reliability is ensured on the premise of reducing the difficulty of the disassembly and assembly adjustment of the lock mechanism.
According to still further scheme, a second protruding connecting seat is arranged on the first diagonal brace, the protruding direction of the second connecting seat is the same as that of the first connecting seat, a first connecting portion extending along the length direction of the first diagonal brace is arranged on the second connecting seat, the first connecting portion is staggered with the connecting rod piece in the axial direction, a third connecting seat is arranged in the middle of the extending portion of the connecting rod piece, a second connecting portion is arranged on the third connecting seat, the second connecting portion is staggered with the connecting rod piece in the axial direction, the elastic piece is a tension spring, and two ends of the tension spring are respectively pulled between the second connecting portion and the third connecting seat.
From the above, the arrangement of the elastic member needs to be considered further, so as to avoid the elastic member from obstructing the action of the lock mechanism. Therefore, the first connecting part and the second connecting part which are connected with the two ends of the torsion spring are locked, and the first connecting part and the second connecting part are positioned outside the plane where the diagonal bracing rod mechanism is positioned, so that the spring and the diagonal bracing rod mechanism are staggered in three-dimensional space, interference and obstruction can not occur in the action between the spring and the diagonal bracing rod mechanism, and the effective action flow is ensured.
In addition, the locking piece comprises a locking part which is used for being locked with the second inclined stay bar, the locking part, the first axle center and the second axle center are distributed in a triangle shape, and the first distance from the first axle center to the locking part is larger than the second axle center.
From the above, this setting makes the arm length from first axle center to buckling part longer, can make the buckling part change swing degree bigger under the same angle of changeing, so, the unblock of hasp piece can be accomplished to the displacement that link spare can be less, reduces the design degree of difficulty of lock mechanism linkage structure.
The first inclined strut comprises a first flange part, the second inclined strut comprises a second flange part, when the landing gear inclined strut mechanism is in an unfolding state, the first flange part is overlapped with the second flange part, and the first flange part and the second flange part are limited from the front side and the rear side of the length direction of the first inclined strut by the buckling concave part.
From the above, in the existing diagonal bracing mechanism, the first inclined plane of the locking part at the locking position only buckles the second inclined plane of the second diagonal bracing, the design mode is higher in matching precision of the locking part and the second diagonal bracing actually, structural reinforcement is required on the front side and the rear side of the swinging direction of the locking part, and otherwise, the tripping risk is higher. The main point of the invention is to simplify the structure, therefore, the lock catch part is arranged into a square concave buckling concave position, the flange part is arranged on the diagonal brace, after the buckling parts are buckled after the two flange parts are overlapped, the two overlapped flange parts are positioned in the buckling concave position and are limited to rotate, under the arrangement mode, the acting force of separating the two flange parts can not generate the separation of swinging the lock catch part, thus the release risk is avoided, and the arrangement of the reinforcing structure is reduced.
In a still further scheme, the hinge joint between the first inclined strut and the second inclined strut is protruded out of the first outer side of the landing gear inclined strut mechanism, the first edge of the first flange part and the second edge of the second flange part are protruded out of the second outer side opposite to the first outer side of the landing gear inclined strut mechanism, the first edge and the second edge are buckled in the buckling concave position, the retraction actuator is arranged on the first outer side, and the first connecting seat, the second connecting seat, the connecting rod piece, the elastic piece and the locking piece are all arranged on the second outer side.
From the above, the position of the lower locking mechanism avoids the position of the second diagonal brace after being folded, does not influence the folding of the second diagonal brace, and ensures that the retraction and extension actions of the landing gear are effectively carried out.
A second object of the present invention provides an aircraft landing gear comprising a landing gear diagonal strut mechanism as described above.
The third object of the present invention provides an aircraft comprising an aircraft landing gear as described above.
Drawings
FIG. 1 is a block diagram of an embodiment of a landing gear diagonal strut mechanism of the present invention in an extended state.
Fig. 2 is an enlarged view at a in fig. 1.
Fig. 3 is an enlarged view at B in fig. 1.
Figure 4 is a block diagram of a folded state of an embodiment of the landing gear diagonal strut mechanism of the present invention.
Fig. 5 is an enlarged view at C in fig. 4.
Fig. 6 is an enlarged view of D in fig. 4.
Detailed Description
Referring to fig. 1 to 3, the aircraft of the present invention includes an aircraft landing gear including a landing gear diagonal brace mechanism of the present embodiment, the landing gear diagonal brace mechanism of the present embodiment including a first diagonal brace 1, a second diagonal brace 2, a retraction cylinder 3, and a lock mechanism including a forcing member 4, a link member 5, a first bolt member 61, a second bolt member 62, a tension spring 7, and a locker 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 a first post connector and a second post connector in the present invention, respectively, and the tension spring 7 is an elastic member of the present invention.
Referring first to fig. 1 and 4, fig. 1 shows the landing gear diagonal strut mechanism in an extended state and fig. 4 shows the landing gear diagonal strut mechanism in a folded state. The first diagonal brace 1 and the second diagonal brace 2 are straight bars, the first hinge portion 19 of the first diagonal brace 1 and the second hinge portion 29 of the second diagonal brace 2 are hinged to the third axis 93 by a third bolt member, and in the unfolded state shown in fig. 1, the first diagonal brace 1 and the second diagonal brace 2 are unfolded in a straight line along the y-axis direction in which the y-axis direction is shown to indicate the length direction of the first diagonal brace 1 and the second diagonal brace 2. In the folded state shown in fig. 4, the first diagonal brace 1 and the second diagonal brace 2 are folded so as to be positioned on two straight lines parallel to each other, respectively.
Referring to fig. 1 and 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 that are disposed opposite to each other, and mainly, the first outer side 101 and the second outer side 102 refer to the outside of the outer wall surface of the first diagonal brace 1 or the second diagonal brace 2, respectively. The hinge between the first diagonal strut 1 and the second diagonal strut 2, where the third centre 93 is located, projects beyond the first outer side 101 of the landing gear diagonal strut mechanism, and in the folded condition, the second diagonal strut 2 is also located at the first outer side 101, as seen in fig. 4. In addition, the first diagonal brace 1 comprises a first flange portion 17 and the second diagonal brace 2 comprises a second flange portion 27, the first flange portion 17 overlapping the second flange portion 27 when the landing gear diagonal brace mechanism is in the deployed state, the first edge 171 of the first flange portion 17 and the second edge 271 of the second flange portion 27 protruding from the landing gear diagonal brace mechanism at the second outer side 102. The retraction jack 3 is also located on the first outer side 101.
Referring to fig. 1 to 3, in the lock mechanism, the link member 5, the tension spring 7, the lock catch member 8, and other components are mainly provided on the second outer side 102 except that the urging member 4 spans between the first outer side 101 and the second outer side 102. The forcing member 4 is provided with a first waist-shaped hole 40, the length direction of the first waist-shaped hole 40 is consistent with the length direction of the forcing member 4, the length direction is shown as the u-axis direction in fig. 2, a first bolt 611 is fixedly connected with the first diagonal brace 1, the first bolt 611 is matched with the first waist-shaped hole 40, and the first bolt 611 passes through the first through hole of the first diagonal brace 1 and the first waist-shaped hole 40, is in threaded fit with a first nut 612 and is locked by a first spring pin 613.
The first end 41 of the forcing member 4 in the length direction is connected to the retraction jack 3, the forcing member 4 extends along the u-axis direction as shown in the drawing, it can be seen that the length direction of the forcing member 4 is inclined to the length direction of the first diagonal brace 1, the second end of the forcing member 4 opposite to the first end 41 in the length direction is provided with an arm portion 42 extending in the length direction and gradually narrowing in width, under the axial projection of the first bolt 611, the length direction of the arm portion 42 is shown in the v-axis direction in fig. 2. Referring to fig. 2, in the present embodiment, the v-axis direction is more biased to the x-axis direction with respect to the y-axis direction, that is, the angle between the length direction of the arm 42 and the length direction of the first diagonal brace 1 is greater than 45 degrees with respect to the length direction of the first diagonal brace 1 under the axial projection of the first bolt 611.
The first diagonal brace 1 comprises a first extended end 109 remote from the second diagonal brace 2 and a second extended end 108 adjacent to the second diagonal brace 2. The first flange 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, the second waist-shaped hole 110 is provided on the first connection seat 11, the length direction of the second waist-shaped hole 110 is the same as the length direction of the first diagonal brace 1, the first bolt 611 is positioned closer to the second diagonal brace 2 than the second waist-shaped hole 110 along the length direction of the first diagonal brace 1, and the length direction of the first waist-shaped hole 40 is inclined to the length direction of the second waist-shaped hole 110.
The second bolt 621 is fixedly connected to the first end 51 of the link member 5, and the second bolt 621 is engaged with the second waist-shaped hole 110. The second bolt 621 passes through the second through hole of the link member 5 and the second waist-shaped hole 110 to be screw-engaged with the second nut 622 and locked by the second spring pin 623. The arm 42 on the second end of the urging member 4 abuts against the second bolt 621.
Referring to fig. 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, the second connection seat is provided with a first connection portion 121 protruding along the length direction of the first diagonal brace 1, the first connection portion 121 is a connection plate, and the first connection portion 121 is staggered with the connection member 5 in the axial direction of the first axis 91. The extending middle part of the connecting rod piece 5 is provided with a third connecting seat 53, the third connecting seat 53 is provided with a second connecting part 531, the second connecting part 531 is a connecting plate, the second connecting part 531 is staggered with the connecting rod piece 5 in the axial direction, and two ends of the tension spring 7 are respectively pulled between the first connecting part 121 and the second connecting part 531. The z-axis direction is the axial direction, and 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.
Referring to fig. 3, the locking member 8 includes a locking portion, in this embodiment, the locking portion is a locking concave portion 810 with a square inner contour, the locking concave portion 810, the first axis 91 and the second axis 92 are distributed in a triangle shape, a first distance L1 from the first axis 91 to the locking concave portion 810 is greater than a distance L2 from the first axis 91 to the second axis 92, the locking member 8 and the second connecting seat 12 are hinged to the first axis 91, a second end 52 of the connecting member 5 opposite to the first end 51 is hinged to the locking member 8 and is hinged to the second axis 92, in this embodiment, the position of the first axis 91 is not close to the second diagonal brace 2, and the locking concave portion 810 is disposed at the tail of the extending portion 81 by providing an extending portion 81 starting from the first axis 91 on the locking member 8, so that the locking concave portion 810 can be locked to the second diagonal brace 2, and in the process, the locking member 8 can be caused to swing sufficiently to meet the requirements of being able to reach the locking position and the unlocking position.
Referring to fig. 1 to 3, the tension spring 7 is drawn between the extended middle portion of the link member 5 and the first diagonal brace 1, the urging force of the tension spring 7 tends to urge the latch member 8 to rotate from the unlocking position to the locking position, in the unfolded state shown in fig. 1, the first flange portion 17 and the second flange portion 27 are overlapped with each other, the latch member 8 is in the locking position, at which time the engagement concave portion 810 engages 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 restrained by the engagement concave portion 810 from both front and rear sides in the longitudinal direction of the first diagonal brace 1, and the restraining effect is maintained by the torsion spring 7, thereby achieving locking.
Referring to fig. 4 to 6, when the retraction jack 3 extends, the diagonal bracing mechanism is driven to bend and retract the landing gear, and when the retraction jack 3 contracts, the diagonal bracing mechanism is driven to expand and release the landing gear. With the landing gear diagonal bracing mechanism shown in fig. 1 to 3 in the deployed state and the locking member 8 in the locked position in the initial state, since the first bolt 611 has small sliding resistance in the first waist-shaped hole 40 and large landing gear resistance in the deployed state, when the retraction cylinder 3 is extended, the urging member 4 is first driven, the urging member 4 moves under the restriction of the first waist-shaped hole 40 and the arm 42 pushes the second bolt 621 to move along the second waist-shaped hole 110, and the link member 5 moves along with the second bolt 621 and pushes the locking member 8 and the urging locking member 8 to rotate from the locked position to the unlocked position. After the linkage locking piece 8 is unlocked, after the first bolt 611 reaches the limit position of the first waist-shaped hole 40, the continuously-extending retraction actuator cylinder 3 starts to drive the second diagonal brace 2 to swing and fold.
Therefore, the invention is based on the design of the first waist-shaped hole 40 and the second waist-shaped hole 110, so that the swing of the locking piece 8 and the swing of the second diagonal brace 2 can be performed successively according to a time line on the premise of keeping the past action rule of the retractable actuating cylinder 3 and the past action rule of the locking piece 8, and the locking piece is ensured to be unlocked first and then swung. Of course, more importantly, the unlocking and locking of the telescopic actuator cylinder 3 communicated with the diagonal bracing rod lock mechanism are realized, the second lock actuator cylinder in the prior art is successfully canceled, and the multi-direction use requirements of a small aircraft, such as simplified structure, strong practicability and light weight, are met.
In this embodiment, preferably, the first bolt 611 and/or the second bolt 621 include a partial screw, and the first bolt 611 and/or the second bolt 621 include an optical axis section and a threaded section connected in sequence, the optical axis section being used for rotational connection or abutment, and the threaded section being used for threaded connection.
In other embodiments, the first and/or second post connectors are optical axis members.
In other embodiments, the elastic member is a spring capable of generating a tensile force.
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 brace but not the first diagonal brace.
Finally, it should be emphasized that the foregoing description is merely illustrative of the preferred embodiments of the invention, and that various changes and modifications can be made by those skilled in the art without departing from the spirit and principles of the invention, and any such modifications, equivalents, improvements, etc. are intended to be included within the scope of the invention.
Claims (4)
1. The landing gear diagonal bracing mechanism comprises a first diagonal bracing, a second diagonal bracing, a locking mechanism and a retraction actuating cylinder, wherein the locking mechanism comprises a locking piece, the locking piece is connected with the first diagonal bracing and can rotate around a first axis between a locking position and an unlocking position, and when the landing gear diagonal bracing mechanism is in an unfolding state, the locking piece at the locking position locks the second diagonal bracing;
the method is characterized in that:
The lock mechanism further comprises a forcing member, a first column connecting member, a link member, a second column connecting member and an elastic member;
the forcing piece is provided with a first waist-shaped hole, the first column connecting piece is fixedly connected with the first diagonal brace, and the first column connecting piece is matched with the first waist-shaped hole;
The first inclined stay rod is provided with a second waist-shaped hole, the second column connecting piece is fixedly connected to the first end of the connecting rod piece, and the second column connecting piece is matched with the second waist-shaped hole;
the elastic piece is pulled between the extending middle part of the link piece and the first diagonal brace, the second end of the link piece is hinged with the locking piece to a second axis, the first end of the forcing piece is connected with the retraction actuator, and the second end of the forcing piece is abutted with the second column connecting piece;
In the process that the retraction actuator cylinder drives the landing gear diagonal bracing mechanism to change from the unfolding state to the folding state, the retraction actuator cylinder drives the forcing member to move under the limit 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 member moves along with the second column connecting member and forces the locking member to rotate from the locking position to the unlocking position;
The acting force of the elastic piece tends to force the locking piece 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 piece, the length direction of the second waist-shaped hole is the same as the length direction of the first diagonal brace, and the position of the first column connecting piece is closer to the second diagonal brace than the position of the second waist-shaped hole along the length direction of the first diagonal brace;
the length direction of the first waist-shaped hole is inclined to the length direction of the second waist-shaped hole, the second end of the forcing member is provided with an arm part which extends obliquely to the length direction of the forcing member and gradually narrows in width under the axial projection of the first column connecting member, and the arm part is abutted with the second column connecting member;
The first inclined stay rod comprises a first extending end far away from the second inclined stay rod, a first protruding connecting seat is arranged on the first inclined stay rod at a position close to the first extending end, and the second waist-shaped hole is formed in the first connecting seat;
The first diagonal brace is provided with a second protruding connecting seat, the protruding 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 part extending along the length direction of the first diagonal brace, and in the axial direction, the first connecting part is staggered with the connecting rod piece;
the extending middle part of the connecting rod piece is provided with a third connecting seat, the third connecting seat is provided with a second connecting part, and the second connecting part is staggered with the connecting rod piece in the axial direction;
The elastic piece is a tension spring, and two ends of the tension spring are respectively pulled between the second connecting part and the third connecting seat;
The locking piece comprises a buckling part which is used for being buckled with the second inclined stay bar, the buckling part, the first axle center and the second axle center are distributed in a triangle shape, and the first distance from the first axle center to the buckling part is larger than the distance from the first axle center to the second axle center;
the buckling part comprises a buckling concave position;
The first diagonal brace comprises a first flange part, the second diagonal brace comprises a second flange part, when the landing gear diagonal brace mechanism is in the unfolding state, the first flange part is overlapped with the second flange part, and the first flange part and the second flange part are limited from the front side and the rear side of the length direction of the first diagonal brace by the buckling concave position;
The hinge joint between the first diagonal brace and the second diagonal brace is protruded out of a first outer side of the landing gear diagonal brace mechanism, a first edge of the first flange part and a second edge of the second flange part are protruded out of a second outer side, opposite to the first outer side, of the landing gear diagonal brace mechanism, and the buckling concave position buckles the first edge and the second edge;
the retractable actuator cylinder is arranged on the first outer side, and the first connecting seat, the second connecting seat, the connecting rod piece, the elastic piece and the locking piece are all arranged on the second outer side.
2. The landing gear diagonal brace mechanism according to claim 1, wherein:
The first column connecting piece adopts a first bolt, the landing gear diagonal brace mechanism further comprises a first nut and a first spring pin, and the first bolt is in threaded fit with the first nut and is locked by the first spring pin after passing through a first through hole of the first diagonal brace and the first waist-shaped hole;
The second column connecting piece adopts the second bolt, undercarriage diagonal brace mechanism still includes second nut and second spring pin, the second bolt pass the second through-hole of link spare and behind the second waist hole with the second nut screw thread cooperation is locked by the second spring pin.
3. An aircraft landing gear comprising a landing gear diagonal strut mechanism according to any one of claims 1 to 2.
4. An aircraft comprising an aircraft landing gear according to claim 3.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411215097.8A CN118753496B (en) | 2024-09-02 | 2024-09-02 | Landing gear diagonal strut mechanism, aircraft landing gear and aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202411215097.8A CN118753496B (en) | 2024-09-02 | 2024-09-02 | Landing gear diagonal strut mechanism, aircraft landing gear and aircraft |
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| Publication Number | Publication Date |
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| CN118753496A CN118753496A (en) | 2024-10-11 |
| CN118753496B true CN118753496B (en) | 2025-02-14 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202411215097.8A Active CN118753496B (en) | 2024-09-02 | 2024-09-02 | Landing gear diagonal strut mechanism, aircraft landing gear and aircraft |
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Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117429600A (en) * | 2023-10-10 | 2024-01-23 | 中电科芜湖通用航空产业技术研究院有限公司 | Locking mechanism of aircraft landing gear and aircraft landing gear |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2686856B1 (en) * | 1992-02-03 | 1994-03-18 | Messier Bugatti | LOCKING DEVICE FOR LOCKING, IN THE UPPER TRAIN POSITION, OF AN AIRCRAFT LANDING TRAIN. |
| CN104309799A (en) * | 2014-10-20 | 2015-01-28 | 中国运载火箭技术研究院 | Aircraft cabin door lock mechanism |
| CN118182827B (en) * | 2024-05-14 | 2024-07-26 | 中航通飞研究院有限公司 | Aircraft brake and steering integrated control system and aircraft |
| CN118182823B (en) * | 2024-05-15 | 2024-07-26 | 中航通飞研究院有限公司 | Airplane landing gear diagonal brace mechanism with self-locking function, airplane landing gear and airplane |
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Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117429600A (en) * | 2023-10-10 | 2024-01-23 | 中电科芜湖通用航空产业技术研究院有限公司 | Locking mechanism of aircraft landing gear and aircraft landing gear |
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| CN118753496A (en) | 2024-10-11 |
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