Rolling wheel type undercarriage and helicopter

Abstract

The invention provides a rolling wheel type undercarriage and a helicopter. The rolling wheel type undercarriage comprises a first airplane wheel assembly (3) and a second airplane wheel assembly (4), one end of the rocker arm assembly (2) is connected with the first airplane wheel assembly, and the other end of the rocker arm assembly is connected with a helicopter body; one end of the buffer assembly (1) is connected with the rocker arm assembly, and the other end of the buffer assembly is connected with a helicopter body; compared with a traditional supporting column type undercarriage and a traditional rocker arm type undercarriage (pitching type), the rolling wheel type undercarriage is symmetrically distributed on the two sides of a helicopter body, the transverse span of the undercarriage can be effectively increased, and the requirement for helicopter stopping stability is met.

Description

Technical Field

[0001] The present application belongs to the technical field of helicopter landing gear structure design, and in particular relates to a roll wheel landing gear and a helicopter. Background Art

[0002] The landing gear is an important component of a helicopter. Its main functions are to absorb landing energy, transfer loads and achieve ground movement.

[0003] At present, the traditional helicopter landing gear is basically of the pillar type (see Figure 1 ), rocker arm configuration. When the helicopter body is wide and the center of gravity is low, the traditional landing gear configuration can meet the requirements of helicopter parking stability. When the helicopter body is narrow and the center of gravity is high, the installation point and tire contact point of the traditional landing gear are close to the fuselage, that is, the lateral span between the two main landing gears is small, which cannot meet the requirements of helicopter parking stability.

[0004] To solve the problem of helicopter parking stability, one method is to tilt the strut landing gear to the side at a small angle. When the strut landing gear tilts to the outside, the buffer strut is compressed during landing, the lateral wheelbase becomes shorter, and the tires and the ground produce sliding friction. The ground friction exerts a bending moment on the buffer strut, which not only affects the sealing of the oil cavity and air cavity in the buffer strut, but also increases the friction inside the buffer strut, which is easy to cause a jam. Summary of the invention

[0005] Purpose of the invention: In order to solve the problem of helicopter parking stability, the present application provides a roll wheel landing gear that increases the lateral span of the landing gear, and the wheels can slide laterally, which can meet the helicopter parking stability requirements.

[0006] In a first aspect, the present application provides a rolling wheel landing gear, the rolling wheel landing gear comprising:

[0007] a first wheel assembly;

[0008] A rocker arm assembly, one end of which is connected to the first wheel assembly, and the other end of which is connected to the helicopter fuselage;

[0009] A buffer assembly, one end of which is connected to the rocker arm assembly, and the other end of which is connected to the helicopter fuselage.

[0010] Preferably, the first wheel assembly 3 includes a first wheel 31, a tire 32 and a wheel lock 33;

[0011] Among them, the first wheel is composed of a wheel hub, a half-hub, a tapered roller bearing, a sealing ring, a wheel lock and a connecting piece; the wheel hub and the half-hub are connected by bolts, and are fixed and prevented from loosening by self-locking nuts; the sealing ring is installed at the junction of the wheel hub and the half-hub, and has the function of sealing the gas in the tire; the tapered roller bearing is installed at both ends of the wheel hub and the half-hub, and has the function of realizing the rolling of the wheel; the wheel lock is installed on the outside of the wheel hub by bolts, and has the function of locking the wheel; the tire has no inner tube, and fits tightly with the rim of the wheel hub and the half-hub through internal gas pressure.

[0012] Preferably, the rocker arm assembly 2 includes a rocker arm, a bushing, a tube shaft, a nut, an axle and a connecting piece;

[0013] Among them, bushings are installed at the rocker arm interfaces to prevent the rocker arm itself from wear; the upper end of the rocker arm assembly 2 is connected to the first fuselage joint 4 through a tube shaft, fixed with a nut, and prevented from loosening by a cotter pin; the lower end of the rocker arm assembly 2 is connected to the wheel axle by bolts, fixed with nuts, and prevented from loosening by a cotter pin; the first wheel assembly 3 is installed on the wheel axle, and the outer ring of the tapered roller bearing is supported by a bushing to prevent the tapered roller bearing from falling out; there are threads on the wheel axle, and nuts are installed to fix the first wheel assembly 3, and a locking washer is used to prevent loosening; the rocker arm assembly and the buffer assembly 1 are connected with bolts, fixed with nuts, and prevented from loosening by a cotter pin.

[0014] Preferably, the buffer assembly 1 includes an outer cylinder, a piston rod, a bushing, a sealing ring, a throttle valve, a floating piston, oil, nitrogen and a connecting piece;

[0015] Among them, the bushing is installed inside the outer tube, connected with threads, and prevented from loosening by a safety wire. In addition to supporting the piston rod, the bushing also has the function of preventing the piston from falling out of the outer tube; a throttle valve is installed at one end of the piston rod. The throttle valve is the core component of the buffer and has the function of generating damping and consuming energy; the throttle valve and part of the piston rod are inserted into the outer tube; sealing rings are installed on the inner ring of the outer tube and the outer ring of the piston rod to form a closed space inside the outer tube and the piston rod; the floating piston is placed inside the piston rod to divide the closed space formed by the outer tube and the piston rod into two parts: an oil chamber and an air chamber; the outer tube and the second fuselage joint 5 are connected by bolts, fixed with nuts, and prevented from loosening by a cotter pin; the piston rod and the rocker arm assembly 2 are connected by bolts, fixed with nuts, and prevented from loosening by a cotter pin.

[0016] In a second aspect, the present application also provides a helicopter, comprising the roll wheel landing gear as described above.

[0017] In a third aspect, the present application further provides a rolling wheel landing gear, the rolling wheel landing gear comprising:

[0018] A second wheel assembly 6;

[0019] A connecting rod mechanism 9, one end of which is connected to the second wheel assembly, and the other end of which is connected to the helicopter fuselage;

[0020] A buffer assembly 1, one end of which is connected to the connecting rod mechanism, and the other end of which is connected to the helicopter fuselage.

[0021] Preferably, the second wheel assembly includes: a left half wheel hub 61, a right half wheel hub 62, a roller 63, a wheel lock 64 and a connecting piece;

[0022] Among them, the left half wheel hub 61 and the right half wheel hub 62 are connected by bolts and fixed and prevented from loosening by self-locking nuts; the roller 63 is evenly installed on the outer edges of the left half wheel hub 61 and the right half wheel hub 62 by bolts and nuts, and the roller 63 can rotate around its own axis; the wheel lock 64 is installed on the outer side of the right half wheel hub by bolts, and has the function of locking the wheel.

[0023] Preferably, the connecting rod mechanism 9 includes an upper rocker arm assembly 81, a lower rocker arm assembly 82, a T-shaped piece 83, a bushing and a connecting piece;

[0024] Among them, bushings are installed at the interfaces of the upper rocker arm assembly 81, the lower rocker arm assembly 82, and the T-piece 83, which have the function of preventing the straight body from being worn; the upper end of the upper rocker arm assembly 81 is connected to the first fuselage joint by bolts, fixed with nuts, and prevented from loosening by a cotter pin; the lower end of the upper rocker arm assembly 81 is connected to the T-piece 83 by bolts, fixed with nuts, and prevented from loosening by a cotter pin; the upper rocker arm assembly 81 is connected to the buffer assembly 1 by bolts, fixed with nuts, and prevented from loosening by a cotter pin; the upper end of the lower rocker arm assembly 82 is connected to the third fuselage joint 8 by bolts, fixed with nuts, and prevented from loosening by a cotter pin; the lower end of the lower rocker arm assembly 82 is connected to the T-piece 83 by bolts, fixed with nuts, and prevented from loosening by a cotter pin; an axle is designed on the T-piece 83; the first wheel assembly 3 is installed on the axle, and the outer ring of the tapered roller bearing is supported by a bushing to prevent the tapered roller bearing from falling out; there are threads on the axle, nuts are installed to fix the first wheel assembly 3, and a locking washer is used to prevent loosening.

[0025] In a fourth aspect, the present application also provides a helicopter, comprising the roll wheel landing gear as described above.

[0026] This application has the following technical effects:

[0027] Compared with the traditional strut landing gear and rocker arm landing gear (pitch-type), the roll wheel landing gear of the present invention is symmetrically distributed on both sides of the fuselage, which can effectively increase the lateral span of the landing gear and meet the parking stability requirements of the helicopter. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 A schematic diagram of a strut-type landing gear arrangement provided in an embodiment of the present application;

[0029] Figure 2 A schematic diagram of the structure of a roll-type landing gear provided in an embodiment of the present application;

[0030] Figure 3 A schematic structural diagram of a wheel assembly provided in an embodiment of the present application;

[0031] Figure 4 A schematic diagram of the motion state of a rolling wheel landing gear provided in an embodiment of the present application;

[0032] Figure 5 A schematic structural diagram of a helicopter equipped with a rolling wheel landing gear provided in an embodiment of the present application;

[0033] Figure 6 A schematic diagram of a rolling wheel landing gear structure provided in an embodiment of the present application;

[0034] Figure 7 A schematic diagram of the structure of a wheel assembly provided in an embodiment of the present application;

[0035] Figure 8 A detailed schematic diagram of a wheel assembly provided in an embodiment of the present application;

[0036] Fig. 9 A schematic diagram of a left half wheel hub structure provided in an embodiment of the present application;

[0037] Fig.10 A schematic diagram of a right half wheel hub structure provided in an embodiment of the present application;

[0038] Fig.11 A schematic diagram of a wheel lock installation provided in an embodiment of the present application;

[0039] Fig.12 A schematic diagram of the structure of an upper rocker arm assembly provided in an embodiment of the present application;

[0040] Fig.13 A schematic diagram of the structure of a lower rocker arm assembly provided in an embodiment of the present application;

[0041] Fig.14 A schematic diagram of the motion state of a rolling wheel landing gear provided in an embodiment of the present application;

[0042] Among them: 1-buffer assembly; 2-rocker arm assembly; 3-first wheel assembly; 31-first wheel; 32-tire; 33-wheel lock; 4-first fuselage joint; 5-second fuselage joint; 6-second wheel assembly; 61-left half wheel hub; 62-right half wheel hub; 63-roller; 64-wheel lock; 7-third fuselage joint; 8-connecting rod mechanism; 81-upper rocker arm assembly; 82-lower rocker arm assembly; 83-T-shaped piece. DETAILED DESCRIPTION

[0043] See also Figure 1-Figure 14 The present invention provides a rolling wheel landing gear, which is composed of Figure 2 As shown, it is composed of a buffer assembly 1, a rocker assembly 2, a first wheel assembly 3, etc. The first wheel assembly is composed of Figure 3 shown.

[0044] The upper ear of the buffer assembly 1 is hinged to the second fuselage joint 5, and the lower ear is hinged to the two ears of the rocker assembly 2. The buffer assembly 1 can rotate around the axis of the upper and lower ear holes; and the upper and lower ears of the buffer assembly 1 are installed with spherical bearings to prevent the buffer from bearing bending moment and not causing jamming. The main function of the buffer is to absorb energy.

[0045] The two ears at the upper end of the rocker arm assembly 2 are hinged to the first fuselage joint 4 and connected to the first wheel assembly 3 through the wheel axle. The rocker arm assembly 2 can rotate around the axis of the ear holes at the upper and lower ends of itself.

[0046] The first wheel assembly 3 is installed on the rocker arm assembly 2 through the wheel axle, and has the function of transmitting load and buffering landing load.

[0047] The motion state of the rolling wheel landing gear is as follows Figure 4 shown.

[0048] The arrangement of the rolling wheel landing gear on the helicopter is as follows: Figure 5 shown.

[0049] The present invention provides a transversely rolling landing gear, which is composed of Figure 6 As shown, it is composed of a buffer assembly 1, a connecting rod mechanism 8, a second wheel assembly 6, etc.

[0050] The upper ear of the buffer assembly 1 is hinged to the second fuselage nose 5, and the lower ear is hinged to the upper rocker arm assembly 81. The buffer assembly 1 can rotate around the axis of the upper and lower ear holes; and the upper and lower ears of the buffer assembly 1 are installed with spherical bearings to prevent the buffer from being subjected to bending moment.

[0051] The upper end double ears of the upper rocker arm assembly 81 are hinged to the first fuselage joint 4, and the lower end double ears are hinged to the T-shaped piece 83. The upper rocker arm assembly 81 can rotate around the axis of the upper and lower end ear holes of itself. Figure 7 shown.

[0052] The upper two ears of the lower rocker arm assembly 82 are hinged to the third fuselage joint 7, and the lower two ears are hinged to the T-shaped piece 83. The lower rocker arm assembly 82 can rotate around the axis of the upper and lower ear holes. Figure 7 shown.

[0053] The lower end of the T-shaped member 83 is provided with an axle, and the second wheel assembly 6 is installed through the axle. Figure 7 shown.

[0054] The main body of the second wheel assembly 6 is composed of a left half wheel hub 61, a right half wheel hub 62, a roller 63 and a wheel lock 64. Figure 8 The left half wheel hub 61 and the right half wheel hub 62 are fixedly connected by bolts, and the rollers of the two should be evenly staggered during installation, as shown in FIG. Fig. 9 As shown. Rolling bearings are installed on the left half hub 61 and the right half hub 62, so that the wheel can rotate around the wheel axle. Four rollers 63 are installed on the left half hub 61, and the rollers 63 are evenly distributed around the left half hub 61, and the rollers 63 can rotate around their own axes, as shown. Fig.10 The right half wheel hub 62 is equipped with four rollers 63, which are evenly distributed around the right half wheel hub 62 and can rotate around their own axes. Fig.11 The right half of the hub 62 is provided with a hole on the side for installing the wheel lock 64, such as Fig.12 The wheel lock 64 can lock the wheel in any position.

[0055] Point A is the intersection of the axis of the two ear holes at the upper end of the upper rocker arm assembly 81 and the axis of the upper rocker arm assembly 81, and point B is the intersection of the axis of the two ear holes at the lower end of the upper rocker arm assembly 81 and the axis of the upper rocker arm assembly 81. Fig.13 Point C is the intersection of the axis of the two ear holes at the lower end of the lower rocker arm assembly 82 and the axis of the lower rocker arm assembly 82, and point D is the intersection of the axis of the two ear holes at the upper end of the lower rocker arm assembly 82 and the axis of the lower rocker arm assembly 82. Fig.14 shown.

[0056] like Figure 6 As shown, the plane ABCD is perpendicular to the heading of the helicopter and the horizontal plane; the quadrilateral ABCD formed by sequentially connecting AB, BC, CD and DA is a parallelogram; AD and BC are perpendicular to the horizontal plane, and BC is the axis of the T-shaped piece 83. The axis of the T-shaped piece 83 is perpendicular to the axis of the wheel axle. The parallelogram structure formed by the upper rocker arm assembly 81, the lower rocker arm assembly 82, the T-shaped piece 83, the first fuselage joint 4 and the second fuselage joint 7 can make the wheel always perpendicular to the horizontal plane when moving, ensuring that the wheel is fully in contact with the ground.

[0057] The roll-type landing gear of the present invention utilizes a parallelogram structure to keep the wheels perpendicular to the ground at all times; rollers are installed on the wheels to have the functions of longitudinal rolling and transverse rolling.

Claims

1. A rolling wheel landing gear, characterized in that: The rolling wheel landing gear comprises: A first wheel assembly (3); A rocker arm assembly (2), one end of which is connected to the first wheel assembly, and the other end of which is connected to the helicopter fuselage; A buffer assembly (1), one end of which is connected to the rocker arm assembly, and the other end of which is connected to a helicopter fuselage.

2. The roll wheel landing gear according to claim 1, characterized in that: The first wheel assembly (3) comprises a first wheel (31), a tire (32) and a wheel lock (33); Among them, the first wheel is composed of a wheel hub, a half-hub, a tapered roller bearing, a sealing ring, a wheel lock and a connecting piece; the wheel hub and the half-hub are connected by bolts, and are fixed and prevented from loosening by self-locking nuts; the sealing ring is installed at the junction of the wheel hub and the half-hub, and has the function of sealing the gas in the tire; the tapered roller bearing is installed at both ends of the wheel hub and the half-hub, and has the function of realizing the rolling of the wheel; the wheel lock is installed on the outside of the wheel hub by bolts, and has the function of locking the wheel; the tire has no inner tube, and fits tightly with the rim of the wheel hub and the half-hub through internal gas pressure.

3. The roll wheel landing gear according to claim 2, characterized in that: The rocker arm assembly (2) comprises a rocker arm, a bushing, a pipe shaft, a nut, a wheel shaft and a connecting piece; Wherein, bushings are installed at the rocker arm interfaces to prevent the rocker arm itself from being worn; the upper end of the rocker arm assembly (2) is connected to the first fuselage joint (4) through a pipe shaft, fixed with a nut, and prevented from loosening by a cotter pin; the lower end of the rocker arm assembly (2) is connected to the wheel axle through bolts, fixed with a nut, and prevented from loosening by a cotter pin; the first wheel assembly (3) is installed on the wheel axle, and the outer ring of the tapered roller bearing is supported by a bushing to prevent the tapered roller bearing from falling out; the wheel axle is provided with threads, and nuts are installed to fix the first wheel assembly (3), and a locking washer is used to prevent loosening; the rocker arm assembly and the buffer assembly (1) are connected by bolts, fixed with nuts, and prevented from loosening by a cotter pin.

4. The roll wheel landing gear according to claim 3, characterized in that: The buffer assembly (1) comprises an outer cylinder, a piston rod, a bushing, a sealing ring, a throttle valve, a floating piston, oil, nitrogen and connecting parts; The bushing is installed inside the outer tube, connected by threads, and prevented from loosening by a safety wire. In addition to supporting the piston rod, the bushing also has the function of preventing the piston from falling out of the outer tube; a throttle valve is installed at one end of the piston rod. The throttle valve is the core component of the buffer and has the function of generating damping and consuming energy; the throttle valve and part of the piston rod are inserted into the outer tube; sealing rings are installed on the inner ring of the outer tube and the outer ring of the piston rod to form a closed space inside the outer tube and the piston rod; the floating piston is placed inside the piston rod to divide the closed space formed by the outer tube and the piston rod into two parts: an oil chamber and an air chamber; the outer tube and the second fuselage joint (5) are connected by bolts, fixed by nuts, and prevented from loosening by a cotter pin; the piston rod and the rocker arm assembly (2) are connected by bolts, fixed by nuts, and prevented from loosening by a cotter pin.

5. A helicopter, characterized in that: The helicopter comprises a rolling wheel landing gear as claimed in any one of claims 1 to 4.

6. A rolling wheel landing gear, characterized in that: The rolling wheel landing gear comprises: A second wheel assembly (6); A connecting rod mechanism (9), one end of which is connected to the second wheel assembly, and the other end of which is connected to the helicopter fuselage; A buffer assembly (1), one end of which is connected to the connecting rod mechanism, and the other end of which is connected to the helicopter fuselage.

7. The roll wheel landing gear according to claim 6, characterized in that: The second wheel assembly comprises: a left half wheel hub (61), a right half wheel hub (62), a roller (63), a wheel lock (64) and a connecting piece; The left wheel hub (61) and the right wheel hub (62) are connected by bolts and fixed and prevented from loosening by self-locking nuts; the roller (63) is evenly installed on the outer edges of the left wheel hub (61) and the right wheel hub (62) by bolts and nuts, and the roller (63) can rotate around its own axis; the machine wheel lock (64) is installed on the outer side of the right wheel hub by bolts and has the function of locking the machine wheel.

8. The rolling wheel landing gear according to claim 7, characterized in that: The connecting rod mechanism (9) comprises an upper rocker arm assembly (81), a lower rocker arm assembly (82), a T-shaped piece (83), a bushing and a connecting piece; Wherein, bushings are installed at the interfaces of the upper rocker arm assembly (81), the lower rocker arm assembly (82) and the T-shaped piece (83), which have the function of preventing the straight body from being worn; the upper end of the upper rocker arm assembly (81) is connected to the first fuselage joint by bolts, fixed by nuts, and prevented from loosening by cotter pins; the lower end of the upper rocker arm assembly (81) is connected to the T-shaped piece (83) by bolts, fixed by nuts, and prevented from loosening by cotter pins; the upper rocker arm assembly (81) is connected to the buffer assembly (1) by bolts, fixed by nuts, and prevented from loosening by cotter pins The upper end of the lower rocker arm assembly (82) is connected to the third fuselage joint (8) by bolts, fixed by nuts, and prevented from loosening by a split pin; the lower end of the lower rocker arm assembly (82) is connected to the T-shaped piece (83) by bolts, fixed by nuts, and prevented from loosening by a split pin; the T-shaped piece (83) is provided with a wheel axle; the first wheel assembly (3) is installed on the wheel axle, and the outer ring of the tapered roller bearing is supported by a bushing to prevent the tapered roller bearing from falling out; the wheel axle is provided with threads, nuts are installed to fix the first wheel assembly (3), and a locking washer is used to prevent loosening.

9. A helicopter, characterized in that: The helicopter comprises a rolling wheel landing gear as claimed in any one of claims 6 to 8.

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