Rocker arm main landing gear, aircraft and retraction method

Abstract

The present invention provides a rocker-type main landing gear, an aircraft, and a retraction and extension method. The rocker-type main landing gear includes an actuator, a crossbeam, a wheel, a buffer, a pull rod, a first connecting rod, a support arm, a second connecting rod, a rotary joint, and a rocker arm. One end of the pull rod is hinged to the crossbeam, the other end of the pull rod is hinged to one end of the first connecting rod, the other end of the first connecting rod is hinged to the support arm, the support arm is hinged to the crossbeam and the second connecting rod respectively, the rotary joint is hinged to the second connecting rod, the rocker arm, and the buffer respectively, and the rotary joint is also connected to the crossbeam; the buffer is hinged to the rocker arm, and the wheel is mounted on the rocker arm. The main landing gear of the present invention has the smallest profile in the retracted state, the storage space in the landing gear compartment is compact, and the mechanism is safe and reliable.

Description

Technical Field

[0001] The present invention relates to the technical field of aviation aircraft, and in particular to a rocker-arm main landing gear, an aircraft, and a retraction and extension method. Background Art

[0002] like Figure 1 As shown, the landing gear of the existing aircraft includes an actuator 1, a crossbeam 2, a buffer 8 and a wheel 10. The actuator 1 is hinged to one end of the crossbeam 2, the buffer 8 is hinged to the other end of the crossbeam 2, and the telescopic rod of the buffer 8 is connected to the wheel 10. When the actuator 1 retracts, it drives the crossbeam 2 to rotate clockwise, thereby causing the buffer 8 and the wheel 10 to rotate counterclockwise to be stored in the landing gear compartment of the fuselage 100. After the landing gear of this structure is retracted, the folded size is large, so that the wheel 10 will extend beyond the bulkhead of the fuselage, affecting the aerodynamic shape and storage space of the aircraft, and an additional independent hydraulic drive mechanism is required to change the retracted posture of the landing gear and lock it, resulting in the overall overweight of the landing gear. Summary of the Invention

[0003] The object of the present invention is to provide a rocker arm type main landing gear, an aircraft and a retraction and deployment method, so that the retracted main landing gear has a smaller profile and the mechanism is safer and more reliable.

[0004] The technical solution of the present invention is: a rocker-type main landing gear, including an actuator, a crossbeam, a wheel, a buffer, a pull rod, a first connecting rod, a support arm, a second connecting rod, a rotary joint and a rocker arm, one end of the pull rod is hinged to the crossbeam, the other end of the pull rod is hinged to one end of the first connecting rod, the other end of the first connecting rod is hinged to the support arm, the support arm is hinged to the crossbeam and the second connecting rod respectively, the rotary joint is hinged to the second connecting rod, the rocker arm and the buffer respectively, and the rotary joint is also connected to the crossbeam; the buffer is hinged to the rocker arm, and the wheel is installed on the rocker arm; the actuator acts on the crossbeam in a telescopic manner, so that the pull rod, the first connecting rod, the support arm, the second connecting rod and the rotary joint are folded or unfolded on the same plane, and the rocker arm is folded or unfolded along with it beside the plane.

[0005] Preferably, the crossbeam includes a first arm and a second arm connected vertically, the end of the first arm is provided with a first hinged hole for hinged to the body of the aircraft, the inner side of the corner between the first arm and the second arm is provided with a second hinged hole for hinged to the actuator cylinder, the end of the second arm is provided with a fourth hinged hole for hinged to the rotary joint, and the second arm is also provided with a third hinged hole for hinged to the support arm.

[0006] Preferably, a first support plate is provided on the second arm, the first support plate and the first arm are arranged on opposite sides of the second arm, the first support plate is located between the second reaming hole and the fourth reaming hole, and the third reaming hole is provided on the first support plate.

[0007] Preferably, the rotary joint includes a first body, a first plate provided at one end of the first body, a second plate provided at the other end of the first body, and a third plate vertically connected to one side of the first body, the first plate is connected to the crossbeam, the first body is provided with a fifth hinged hole for hinged connection of the rocker arm, the second plate is provided with a sixth hinged hole for hinged connection with the buffer, and the third plate is provided with a seventh hinged hole for hinged connection with the second connecting rod.

[0008] Preferably, the rocker arm includes a second body, an axle provided at one end of the second body, and a fourth plate provided at the other end of the second body, the wheel is mounted on the axle, the fourth plate is provided with a ninth reamed hole for hinged connection with the rotary joint, and the second body is provided with an eighth reamed hole for hinged connection with the buffer.

[0009] Preferably, the pull rod includes a third body and a rotating shaft vertically connected to one end of the third body, the other end of the third body is provided with a tenth hinge hole for hinged connection with the first connecting rod, and the rotating shaft is hinged to the crossbeam.

[0010] Preferably, the support arm includes a fifth plate and a triangular plate connected to one end of the fifth plate, the other end of the fifth plate is provided with an eleventh hinged hole for hinged to the crossbeam, one top angle of the triangular plate is provided with a twelfth hinged hole for hinged to the first connecting rod, and the other top angle of the triangular plate is provided with a thirteenth hinged hole for hinged to the second connecting rod.

[0011] Preferably, a connecting line H is provided between the hinge point of the first connecting rod and the pull rod and the thirteenth reaming hole. When the landing gear is in the folded position, the twelfth reaming hole is located on the side of the connecting line H away from the actuator cylinder.

[0012] The present invention further provides an aircraft, comprising an airframe and the above-mentioned rocker-type main landing gear, wherein the actuator cylinder and the crossbeam are hinged to the airframe.

[0013] The present invention also provides a method for retracting and extending the main landing gear of an aircraft, which is performed using the above-mentioned aircraft, comprising:

[0014] Start the actuator to retract, driving the crossbeam to rotate clockwise; the follower mechanism formed by the pull rod, the first connecting rod and the support arm has a downward deflection, so the pull rod rotates counterclockwise around the crossbeam, driving the support arm to rotate clockwise around the crossbeam, and the second connecting rod drives the rotary joint to rotate counterclockwise around the crossbeam, causing the buffer and rocker arm on the rotary joint to also rotate counterclockwise until the landing gear is retracted into the fuselage and the actuator is locked; start the actuator to extend, and move in the opposite direction according to the above steps to lower the landing gear and make the wheels contact the ground.

[0015] Compared with the related art, the present invention has the following beneficial effects:

[0016] 1. The rocker-type main landing gear is equipped with a new pull rod, a first connecting rod, a support arm, a second connecting rod, and a rotary joint to form a follower mechanism. This follower mechanism makes the main landing gear smaller in the retracted state, compacts the storage space in the landing gear bay, and ensures a safe and reliable mechanism.

[0017] 2. Optimize the design of the structure of the pull rod, first link, support arm, second link and rotary joint to make the folding and lowering movements smoother and effectively lockable after folding;

[0018] 3. When the landing gear is in the folded position, the twelfth reaming hole is located on the side of the connecting line H away from the actuator, so that the component force transmitted by gravity to the support arm is insufficient to overcome the deflection to allow the mechanism to rotate, thereby achieving safe locking of the landing gear. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 A schematic diagram of a conventional rocker-type main landing gear in a retracted position;

[0020] Figure 2 A schematic diagram of the rocker arm main landing gear provided by the present invention in the lowered position;

[0021] Figure 3 is a structural diagram of the beam;

[0022] Figure 4 It is a structural diagram of a rotary joint;

[0023] Figure 5 for Figure 4 Side view of

[0024] Figure 6 It is a structural diagram of the rocker arm;

[0025] Figure 7 It is a structural diagram of the pull rod;

[0026] Figure 8 A schematic diagram of the follower mechanism provided by the present invention in the retracted position;

[0027] Figure 9 This is a schematic diagram of the rocker arm main landing gear provided by the present invention in the retracted position.

[0028] In the accompanying drawings: 1. Actuator; 11. First outer cylinder; 12. First piston rod; 2. Crossbeam; 21. First arm; 22. Second arm; 23. First support plate; 24. First reaming hole; 25. Second reaming hole; 26. Third reaming hole; 27. Fourth reaming hole; 3. Pull rod; 31. Third body; 32. Rotating shaft; 33. Tenth reaming hole; 4. First connecting rod; 5. Support arm; 51. Fifth plate; 52. Triangular plate; 53. Eleventh reaming hole; 54. Twelfth reaming hole; 55. Thirteenth reaming hole Reamed hole; 6. Second connecting rod; 7. Rotary joint; 71. First body; 72. First plate; 73. Second plate; 74. Third plate; 75. Fifth reamed hole; 76. Sixth reamed hole; 77. Seventh reamed hole; 78. Second support plate; 8. Buffer; 81. Second outer cylinder; 82. Second piston rod; 9. Rocker arm; 91. Second body; 92. Rotating shaft; 93. Fourth plate; 94. Eighth reamed hole; 95. Ninth reamed hole; 96. Third support plate; 10. Wheel; 100. Airframe. DETAILED DESCRIPTION

[0029] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with the embodiments. It should be noted that the embodiments and features of the embodiments may be combined unless they conflict. For ease of description, the words "upper," "lower," "left," and "right" appear below merely to indicate the directions of upper, lower, left, and right in the accompanying drawings and do not limit the structure.

[0030] like Figure 2 As shown, the rocker-type main landing gear provided in this embodiment includes an actuator 1, a crossbeam 2, a pull rod 3, a first connecting rod 4, a support arm 5, a second connecting rod 6, a buffer 8, a rocker arm 9, and a wheel 10. The actuator 1 includes a first outer tube 11 and a first piston rod 12 with one end extending and retracting within the first outer tube 11. The buffer 8 includes a second outer tube 81 and a second piston rod 82 with one end extending and retracting within the second outer tube 81.

[0031] like Figure 3 As shown, the crossbeam 2 includes a first arm 21 and a second arm 22 connected vertically. The end of the first arm 21 is provided with a first reaming hole 24 for hinged connection to the aircraft body 100. A second reaming hole 25 is provided inside the corner between the first arm 21 and the second arm 22 for hinged connection to the first piston rod 12 of the actuator 1. The end of the second arm 22 is provided with a fourth reaming hole 27 for hinged connection to the rotary joint 7. A first support plate 23 is provided on the second arm 22. The first support plate 23 and the first arm 21 are provided on opposite sides of the second arm 22. The first support plate 23 is located between the second reaming hole 25 and the fourth reaming hole 27. The third reaming hole 26 is provided on the first support plate 23.

[0032] like Figure 4 、 Figure 5As shown, the rotary joint 7 includes a first body 71, a first plate 72 provided at one end of the first body 71, a second plate 73 provided at the other end of the first body 71, and a third plate 74 perpendicularly connected to one side of the first body 71. The first plate 72 is connected to the crossbeam 2. The first body 71 is provided with a second support plate 78, which is provided with a fifth reamed hole 75 for articulating the rocker arm 9. The second plate 73 is provided with a sixth reamed hole 76 for articulating the buffer 8, and the third plate 74 is provided with a seventh reamed hole 77 for articulating the second connecting rod 6.

[0033] like Figure 6 As shown, the rocker arm 9 includes a second body 91, an axle 92 disposed at one end of the second body 91, and a fourth plate 93 disposed at the other end of the second body 91. A third support plate 96 is vertically mounted on the second body 91. The third support plate 96 has an eighth reamed hole 94 for articulating with the second piston rod 82 of the buffer 8. The wheel 10 is mounted on the axle 92, and the fourth plate 93 has a ninth reamed hole 95 for articulating with the rotary joint 7.

[0034] like Figure 7 As shown, the pull rod 3 includes a third body 31 and a rotating shaft 32 vertically connected to one end of the third body 31. The other end of the third body 31 is provided with a tenth reaming hole 33 for hinged connection with the first connecting rod 4. The rotating shaft 32 is inserted into the second reaming hole 25 and the hole on the first piston rod 12, and is hinged to the actuator 1 and the crossbeam 2.

[0035] like Figure 2 As shown, the support arm 5 includes a fifth plate 51 and a triangular plate 52 connected to one end of the fifth plate 51. The other end of the fifth plate 51 is provided with an eleventh reaming hole 53 for hinged connection to the crossbeam 2. One vertex corner of the triangular plate 52 is provided with a twelfth reaming hole 54 for hinged connection to the first connecting rod 4, and the other vertex corner of the triangular plate 52 is provided with a thirteenth reaming hole 55 for hinged connection to the second connecting rod 6.

[0036] like Figure 2-Figure 7 As shown, the tenth hinged hole 33 is hinged to one end of the first connecting rod 4, and the other end of the first connecting rod 4 is hinged to the twelfth hinged hole 54. The eleventh hinged hole 53 is hinged to the third hinged hole 26. One end of the second connecting rod 6 is hinged to the thirteenth hinged hole 55, and the other end of the second connecting rod 6 is hinged to the seventh hinged hole 77. The second outer cylinder 81 of the buffer 8 is hinged to the sixth hinged hole 76 on the second plate 73. The ninth hinged hole 95 on the fourth plate 93 of the rocker arm 9 is hinged to the fifth hinged hole 75 on the second support plate 78. The second piston rod 82 of the buffer 8 is hinged to the eighth hinged hole 94 on the third support plate 96 of the rocker arm 9. The above-mentioned hinged holes are hinged through hinge shafts.

[0037] The present invention further provides an aircraft, comprising a body 100 and the above-mentioned rocker-type main landing gear, wherein the first outer cylinder 11 of the actuator cylinder 1 and the first reaming hole 24 on the first arm 21 of the crossbeam 2 are hinged to the body 100 .

[0038] The present invention also provides a method for retracting and extending the main landing gear of an aircraft, which is performed using the above-mentioned aircraft, comprising:

[0039] Start the actuator 1 to retract, driving the beam 2 to rotate clockwise; the follower mechanism formed by the pull rod 3, the first connecting rod 4 and the support arm 5 has a downward deflection, so the pull rod 3 rotates counterclockwise around the beam 2, driving the support arm 5 to rotate clockwise around the beam 2, and the second connecting rod 6 drives the rotary joint 7 to rotate counterclockwise around the beam 2, causing the buffer 8 and the rocker arm 9 on the rotary joint 7 to also rotate counterclockwise until the landing gear is retracted into the body and the actuator 1 is locked; start the actuator 1 to extend, and move in the opposite direction according to the above steps to lower the landing gear and the wheel 10 contacts the ground.

[0040] like Figure 2 、 Figure 9 As shown, the actuator 1 acts on the crossbeam 2 in a telescopic manner, so that the pull rod 3, the first connecting rod 4, the support arm 5, the second connecting rod 6 and the rotary joint 7 are folded or unfolded on the same plane, and the rocker arm 9 is folded or unfolded beside the plane.

[0041] like Figure 8 As shown, a connecting line H is provided between the hinge point of the first connecting rod 4 and the tenth hinge hole 33 of the pull rod 3 and the hinge point of the second connecting rod 6 and the thirteenth hinge hole 55. When the landing gear is in the folded position, the twelfth hinge hole 54 is located on the side of the connecting line H away from the actuator 1 ( Figure 8 (As shown on the left side of the figure), the arm 5, first link 4, and pull rod 3 form a connection mechanism with a deflection toward the left. The force component transmitted by gravity to the arm 5 is insufficient to overcome the deflection and allow the follower mechanism to rotate, so the main landing gear is safely locked in the retracted state.

[0042] like Figure 9 As shown, the newly added follower mechanism (pull rod, first link, support arm, second link and rotary joint) can achieve the smallest outline in the retracted state, and the storage space in the landing gear bay is compact without affecting the aircraft's aerodynamic shape and storage space.

[0043] The above descriptions are merely embodiments of the present invention and are not intended to limit the patent scope of the present invention. Any equivalent structure or equivalent process transformation made using the contents of the present invention's description and drawings, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present invention.

Claims

1. A rocker-type main landing gear, comprising an actuator (1), a crossbeam (2), a wheel (10) and a buffer (8), characterized in that: The invention also includes a pull rod (3), a first connecting rod (4), a support arm (5), a second connecting rod (6), a rotary joint (7) and a rocker arm (9), wherein one end of the pull rod (3) is hinged to the cross beam (2), the other end of the pull rod (3) is hinged to one end of the first connecting rod (4), the other end of the first connecting rod (4) is hinged to the support arm (5), the support arm (5) is hinged to the cross beam (2) and the second connecting rod (6), the rotary joint (7) is hinged to the second connecting rod (6), the rocker arm (9) and the support arm (5). ) and the buffer (8) are hinged, and the rotary joint (7) is also connected to the crossbeam (2); the buffer (8) is hinged to the rocker arm (9), and the wheel (10) is installed on the rocker arm (9); the actuator (1) acts on the crossbeam (2) in a telescopic manner, so that the pull rod (3), the first connecting rod (4), the support arm (5), the second connecting rod (6) and the rotary joint (7) are folded or unfolded on the same plane, and the rocker arm (9) is folded or unfolded next to the plane; The support arm (5) includes a fifth plate (51) and a triangular plate (52) connected to one end of the fifth plate (51); the other end of the fifth plate (51) is provided with an eleventh reaming hole (53) for hinged connection with the crossbeam (2); one vertex of the triangular plate (52) is provided with a twelfth reaming hole (54) for hinged connection with the first connecting rod (4); and the other vertex of the triangular plate (52) is provided with a thirteenth reaming hole (55) for hinged connection with the second connecting rod (6).

2. The rocker arm main landing gear according to claim 1, characterized in that: The crossbeam (2) includes a first arm (21) and a second arm (22) connected vertically. The end of the first arm (21) is provided with a first reaming hole (24) for hinged connection with the body of the aircraft. The inner side of the corner between the first arm (21) and the second arm (22) is provided with a second reaming hole (25) for hinged connection with the actuator (1). The end of the second arm (22) is provided with a fourth reaming hole (27) for hinged connection with the rotary joint (7). The second arm (22) is also provided with a third reaming hole (26) for hinged connection with the support arm (5).

3. The rocker arm type main landing gear according to claim 2, characterized in that: A first support plate (23) is provided on the second arm (22), the first support plate (23) and the first arm (21) are respectively provided on opposite sides of the second arm (22), the first support plate (23) is located between the second reaming hole (25) and the fourth reaming hole (27), and the third reaming hole (26) is provided on the first support plate (23).

4. The rocker arm main landing gear according to claim 1, characterized in that: The rotary joint (7) includes a first body (71), a first plate (72) provided at one end of the first body (71), a second plate (73) provided at the other end of the first body (71), and a third plate (74) vertically connected to one side of the first body (71), the first plate (72) is connected to the crossbeam (2), the first body (71) is provided with a fifth reaming hole (75) for hinged connection of the rocker arm (9), the second plate (73) is provided with a sixth reaming hole (76) for hinged connection with the buffer (8), and the third plate (74) is provided with a seventh reaming hole (77) for hinged connection with the second connecting rod (6).

5. The rocker arm type main landing gear according to claim 1, characterized in that: The rocker arm (9) comprises a second body (91), a wheel axle (92) provided at one end of the second body (91), and a fourth plate (93) provided at the other end of the second body (91), the wheel (10) being mounted on the wheel axle (92), the fourth plate (93) being provided with a ninth reaming hole (95) for articulating with the rotary joint (7), and the second body (91) being provided with an eighth reaming hole (94) for articulating with the buffer (8).

6. The rocker arm type main landing gear according to claim 1, characterized in that: The pull rod (3) includes a third body (31), a rotating shaft (32) vertically connected to one end of the third body (31), and the other end of the third body (31) is provided with a tenth reaming hole (33) for hinged connection with the first connecting rod (4), and the rotating shaft (32) is hinged to the crossbeam (2).

7. The rocker arm type main landing gear according to claim 1, characterized in that: A connecting line H is provided between the hinge point of the first connecting rod (4) and the pull rod (3) and the thirteenth reaming hole (55). When the landing gear is in the folded position, the twelfth reaming hole (54) is located on the side of the connecting line H away from the actuator (1).

8. An aircraft, comprising a body (100), characterized in that: It also includes a rocker-type main landing gear according to any one of claims 1 to 7, wherein the actuator (1) and the crossbeam (2) are hinged to the machine body (100).

9. A method for retracting and extending an aircraft main landing gear, performed using the aircraft according to claim 8, characterized in that: include: The actuator (1) is started to retract, driving the crossbeam (2) to rotate clockwise; the deflection of the follower mechanism formed by the pull rod (3), the first connecting rod (4) and the support arm (5) is downward, so the pull rod (3) rotates counterclockwise around the crossbeam (2), driving the support arm (5) to rotate clockwise around the crossbeam (2), and the second connecting rod (6) drives the rotary joint (7) to rotate counterclockwise around the crossbeam (2), causing the buffer (8) and the rocker arm (9) on the rotary joint (7) to also rotate counterclockwise until the landing gear is retracted into the body (100) and the actuator (1) is locked; the actuator (1) is started to extend, and the above steps are reversed to move the landing gear downward and the wheels (10) are in contact with the ground.

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