Rolling type undercarriage with lateral displacement adjustment function

Abstract

The invention discloses a rolling type undercarriage with lateral displacement adjustment. The rolling type undercarriage comprises a buffer assembly (5), a rocker arm assembly (7), a T-shaped connector (2), a limiting connector (3), a sliding way (4), a guide rod (1) and an airplane wheel tire (6). An upper end lug of the buffer assembly (5) is hinged to an airplane body connector, and a lower end lug of the buffer assembly (5) is hinged to a double-lug lug in the middle of the rocker arm assembly (7). An airplane wheel tire (6) is mounted on a wheel shaft at the lower end part of the rocker arm assembly (7) through a bearing, a transverse shaft of the T-shaped joint (2) is clamped between double lugs at the upper end part of the rocker arm assembly (7), and a fixed included angle is formed between a longitudinal shaft of the T-shaped joint (2) and the rocker arm assembly (7); the two limiting connectors (3) penetrate into the rocker arm assembly (7) from the two sides of double lugs and are inserted into annular cavities in the two ends of a transverse shaft of the T-shaped connector (2), and the T-shaped connector (2) and the limiting connectors (3) are locked through screws. An up-and-down slide way (4) is arranged on the aircraft body structure, and the end cylindrical parts of the two limiting connectors (3) are arranged between the up-and-down slide way (4) and can laterally move and rotate in the slide way; a lug piece at one end of the guide rod (1) is hinged to a machine body, and a lug piece at the other end is hinged to double lugs at the lower end of the T-shaped connector (2). Lateral displacement of tires during landing can be effectively reduced, the landing stability of the rolling landing gear is improved, and meanwhile the impact load during landing is reduced.

Description

Technical Field

[0001] The invention belongs to the technical field of helicopter landing gear structure design, and in particular relates to a roll-type landing gear with lateral displacement adjustment. Background Art

[0002] The landing gear is a device for the aircraft to slide and move flexibly on the ground. Currently, the common helicopter wheeled landing gears include strut type, rocker type, semi-rocker type, roll type and other configurations. The main load-bearing component of the strut type landing gear is the buffer strut, which is connected to the fuselage structure on the top and the wheel on the bottom. It is loaded as a beam column, but this configuration is not conducive to bearing the impact of heading and lateral, and will produce additional bending moment, which is not good for sealing performance. The rocker type landing gear has two branches. One separates the buffer strut from the load-bearing strut, and both ends of the buffer strut are hinged to the fuselage and the rocker arm, which is the rocker type landing gear (pitch), and the other combines the buffer strut with the strut, one end of the buffer strut is fixed to the fuselage, and the other end is hinged to the rocker arm, which is the semi-rocker type landing gear. Among them, the roll type landing gear is also a type of rocker type, the difference is that the connecting axis between the rocker arm and the fuselage is in the heading direction. When landing, the landing gear moves up and down laterally to absorb the landing energy. Roll-type landing gear is mostly used on small helicopters. Since the lateral width of the helicopter is narrow, a larger lateral wheelbase is required to improve the parking stability of the helicopter, so the roll-type landing gear came into being.

[0003] Most existing roll-type landing gears are arranged in an eight-shaped pattern, with rockers arranged on both sides of the fuselage, and the buffers are hinged to the fuselage and rockers respectively. When the helicopter lands, the ground load is transferred to the buffers through the wheels and rockers, and the buffers are compressed to absorb the landing energy. During this movement, the wheels are lifted relative to the fuselage coordinate system while moving to both sides of the fuselage. On rough landing sites such as ship decks, friction will prevent the tires from moving sideways, which will increase tire wear and can even cause tire dislodgement in severe cases, causing damage to the helicopter body structure. Summary of the invention

[0004] The purpose of the present invention is to provide a roll-type landing gear with lateral displacement adjustment, which can effectively reduce the lateral displacement of the tire during landing, improve the landing stability of the roll-type landing gear, and reduce the impact load during landing.

[0005] The present invention provides a roll-type landing gear with lateral displacement adjustment, comprising: a buffer assembly 5, a rocker assembly 7, a T-joint 2, a limit joint 3, a slideway 4, a guide rod 1 and a wheel tire 6;

[0006] The upper end ear piece of the buffer assembly 5 is hinged to the aircraft fuselage joint, and the lower end ear piece is hinged to the double ear pieces in the middle of the rocker arm assembly 7;

[0007] The wheel axle at the lower end of the rocker assembly 7 is mounted with a wheel tire 6 through a bearing, and the middle clamp of the two ears at the upper end is provided with a transverse axis of the T-joint 2, and the longitudinal axis of the T-joint 2 forms a fixed angle with the rocker assembly 7;

[0008] Two limit joints 3 are inserted from both sides of the two ears of the rocker arm assembly 7 and inserted into the annular cavities at both ends of the transverse axis of the T-joint 2. The T-joint 2 and the limit joint 3 are locked by screws;

[0009] An upper and lower slideway 4 is provided on the aircraft fuselage structure, and the end cylindrical parts of the two limit joints 3 are placed between the upper and lower slideways 4, and can realize lateral movement and rotation in the slideway;

[0010] The ear piece at one end of the guide rod 1 is hinged to the machine body, and the ear piece at the other end is hinged to the two ears at the lower end of the T-shaped joint 2.

[0011] Optionally, a gasket is provided between the transverse axis of the T-joint 2 and the two ears of the rocker arm assembly 7 to prevent the T-joint 2 from moving.

[0012] Optionally, the limit joint 3 and the double-ear joint of the rocker arm assembly 7 are fixedly connected by a hexagonal boss and a groove.

[0013] Optionally, the angle formed by the T-joint 2 and the rocker arm assembly 7 is 101°.

[0014] Optionally, the slide 4 includes two groups of slide units; each group of slide units includes two upper and lower slide rails, and a limit joint 3 is arranged in one group of slide units; the direction of the slide rail is perpendicular to the heading of the aircraft.

[0015] Optionally, the length of the slide rail is 130-150 mm.

[0016] Optionally, 4-5 countersunk holes are provided on each slide rail, and bolts are used to connect the slide rail to the fuselage structure.

[0017] Optionally, the length of the guide rod 1 is 80 mm, and under the joint action of the guide rod (1) and the buffer assembly 5, the limit joint 3 does not exceed the slide travel.

[0018] The present invention provides a roll-type landing gear with lateral displacement adjustment, which releases the freedom of movement of the rocker arm in the lateral direction (Y direction in the body coordinate system) and fully utilizes the spatial movement of the mechanism, so that the lateral wheelbase of the roll-type landing gear remains basically unchanged during the cushioning landing. At the same time, when the ground load is transmitted to the rocker arm through the tire at the moment of landing, the rocker arm shaft can slide on the slideway with the limit joint to release the impact load. It can effectively solve the problem of lateral slippage of the tire during the landing of the existing roll-type landing gear, reduce tire wear, resolve potential tire derailment problems, improve the parking stability of the helicopter, increase the service life of the tire, and reduce the impact load during landing. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic diagram of the landing gear structure of the present invention;

[0020] Figure 2 An exploded view of the upper connection of the rocker arm assembly in the present invention;

[0021] Figure 3 A schematic diagram of the buffering operation of the landing gear of the present invention;

[0022] Figure 4 It is a working comparison diagram of the existing rolling landing gear and the landing gear of the present invention;

[0023] Description of reference numerals:

[0024] Guide rod 1, T-joint 2, limit joint 3, slideway 4, buffer assembly 5, wheel tire 6, rocker arm assembly 7. DETAILED DESCRIPTION

[0025] The roll type landing gear with lateral displacement adjustment provided by the present invention is explained below with reference to the accompanying drawings.

[0026] like Figure 1-4 As shown, the present invention provides a roll-type landing gear with lateral displacement adjustment, comprising: a buffer assembly 5, a rocker arm assembly 7, a T-joint 2, a limit joint 3, a slideway 4, a guide rod 1 and a wheel tire 6;

[0027] The upper end ear piece of the buffer assembly 5 is hinged to the aircraft fuselage joint, and the lower end ear piece is hinged to the double ear pieces in the middle of the rocker arm assembly 7;

[0028] The wheel axle at the lower end of the rocker assembly 7 is mounted with a wheel tire 6 through a bearing, and the middle clamp of the two ears at the upper end is provided with a transverse axis of the T-joint 2, and the longitudinal axis of the T-joint 2 forms a fixed angle with the rocker assembly 7;

[0029] Two limit joints 3 are inserted from both sides of the two ears of the rocker arm assembly 7 and inserted into the annular cavities at both ends of the transverse axis of the T-joint 2. The T-joint 2 and the limit joint 3 are locked by screws;

[0030] An upper and lower slideway 4 is provided on the aircraft fuselage structure, and the end cylindrical parts of the two limit joints 3 are placed between the upper and lower slideways 4, and can realize lateral movement and rotation in the slideway;

[0031] The ear piece at one end of the guide rod 1 is hinged to the machine body, and the ear piece at the other end is hinged to the two ears at the lower end of the T-shaped joint 2.

[0032] Optionally, a gasket is provided between the transverse axis of the T-joint 2 and the two ears of the rocker arm assembly 7 to prevent the T-joint 2 from moving.

[0033] Optionally, the limit joint 3 and the double-ear joint of the rocker arm assembly 7 are fixedly connected by a hexagonal boss and a groove.

[0034] Optionally, the angle formed by the T-joint 2 and the rocker arm assembly 7 is 101°.

[0035] Optionally, the slide 4 includes two groups of slide units; each group of slide units includes two upper and lower slide rails, and a limit joint 3 is arranged in one group of slide units; the direction of the slide rail is perpendicular to the heading of the aircraft.

[0036] Optionally, the length of the slide rail is 130-150 mm.

[0037] Optionally, 4-5 countersunk holes are provided on each slide rail, and bolts are used to connect the slide rail to the fuselage structure.

[0038] Optionally, the length of the guide rod 1 is 80 mm, and under the joint action of the guide rod (1) and the buffer assembly 5, the limit joint 3 does not exceed the slide travel.

[0039] In order to reduce the influence of lateral displacement on the roll-type landing gear, the present invention provides a roll-type landing gear with a lateral displacement adjustment mechanism, which is composed of Figure 1 As shown, it is composed of a buffer assembly 5, a rocker arm assembly 7, a T-joint 2, a limit joint 3, a slideway 4, a guide rod 1 and a wheel tire 6.

[0040] The upper ear piece of the buffer assembly 5 is hinged to the body joint, and the lower ear piece is hinged to the double ear pieces of the rocker arm assembly 7;

[0041] The wheel axle at the lower end of the rocker assembly 7 is mounted with a wheel tire 6 through a bearing, and the upper double ears are fixedly connected to the T-joint 2, so that the T-joint 2 and the rocker assembly 7 form an angle of a fixed angle, and 101° is taken as an example in the present invention. The fixing is achieved by placing the rotating shaft of the T-joint 2 in the middle of the double ear joint of the rocker assembly 7, and using two gaskets to limit the movement of the T-joint 2 between the double ears of the rocker assembly 7, using two limit joints 3 to penetrate from both sides of the double ears of the rocker assembly 7, and the outer hexagonal boss of the middle section of the limit joint 3 is inserted into the inner hexagonal groove on the outer side of the double ear joint of the rocker assembly 7, and the cylindrical part at the end of the limit joint 3 is inserted into the annular cavity of the T-joint 2, and two bolts are used to pass through the through holes on the T-joint 2 and the limit joint 3 and locked, thereby realizing the axial and circumferential fixation of the T-joint 2, the rocker assembly 7 and the limit joint 3, such as Figure 2 As shown;

[0042] The slideway 4 is fixed on the fuselage structure, and the end cylindrical parts of the two limit joints 3 are placed between the upper and lower slideways 4, and can achieve lateral movement and rotation in the slideway;

[0043] The ear piece at one end of the guide rod 1 is hinged to the machine body, and the ear piece at the other end is hinged to the two ears at the lower end of the T-shaped joint 2.

[0044] The roll landing gear of the present invention fully utilizes the spatial movement of the mechanism by releasing the freedom of movement of the rocker arm in the lateral direction (Y direction in the body coordinate system), so that the lateral wheelbase of the roll landing gear remains basically unchanged during the cushioned landing. At the same time, at the moment of landing, when the ground load is transmitted to the rocker arm through the tire, the rocker arm shaft can slide on the slideway along with the limit joint to release the impact load.

Claims

1. A roll-type landing gear with lateral displacement adjustment, characterized in that: include: A buffer assembly (5), a rocker arm assembly (7), a T-joint (2), a limit joint (3), a slideway (4), a guide rod (1) and a wheel tire (6); The upper end ear piece of the buffer assembly (5) is hinged to the aircraft fuselage joint, and the lower end ear piece is hinged to the double ear pieces in the middle of the rocker arm assembly (7); The wheel axle at the lower end of the rocker arm assembly (7) is mounted with a wheel tire (6) via a bearing, and the middle clamp of the two ears at the upper end is provided with a transverse axis of a T-joint (2), and the longitudinal axis of the T-joint (2) forms a fixed angle with the rocker arm assembly (7); Two limit joints (3) are inserted from both sides of the two ears of the rocker arm assembly (7) and inserted into the annular cavities at both ends of the transverse axis of the T-joint (2). The T-joint (2) and the limit joint (3) are locked by screws; An upper and lower slideway (4) is arranged on the aircraft fuselage structure, and the end cylindrical parts of the two limit joints (3) are placed between the upper and lower slideways (4), and can realize lateral movement and rotation in the slideway; The ear piece at one end of the guide rod (1) is hinged to the machine body, and the ear piece at the other end is hinged to the two ears at the lower end of the T-shaped joint (2).

2. The roll type landing gear with lateral displacement adjustment according to claim 1, characterized in that: A gasket is also provided between the transverse axis of the T-shaped joint (2) and the two ears of the rocker arm assembly (7) to prevent the T-shaped joint (2) from moving.

3. The roll type landing gear with lateral displacement adjustment according to claim 1, characterized in that: The limit joint (3) and the double-ear joint of the rocker arm assembly (7) are fixedly connected by adopting a hexagonal boss and a groove.

4. The roll type landing gear with lateral displacement adjustment according to claim 1, characterized in that: The included angle formed by the T-joint (2) and the rocker arm assembly (7) is 101°.

5. The roll type landing gear with lateral displacement adjustment according to claim 1, characterized in that: The slideway (4) comprises two groups of slideway units; each group of slideway units comprises two upper and lower slide rails, and a limit joint (3) is arranged in one group of slideway units; the direction of the slide rail is perpendicular to the heading of the aircraft.

6. The roll type landing gear with lateral displacement adjustment according to claim 5, characterized in that: The length of the slide rail is 130-150mm.

7. The roll type landing gear with lateral displacement adjustment according to claim 6, characterized in that: 4-5 countersunk holes are set on each slide rail, and bolts are used to connect the slide rail to the fuselage structure.

8. The roll type landing gear with lateral displacement adjustment according to claim 1, characterized in that: The length of the guide rod (1) is 80 mm. Under the joint action of the guide rod (1) and the buffer assembly (5), the limit joint (3) does not exceed the travel of the slideway.

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