CN103523212A - Nose landing gear of aircraft - Google Patents

Abstract

The invention belongs to the field of aircraft engineering, and provides a nose landing gear of an aircraft. The nose landing gear is arranged on an aircraft structure through two mounting shafts on a buffer support column, and can rotate around the mounting shafts; one end of a stay bar folding and release actuating cylinder is provided with a joint bearing; the joint bearing is connected with a shaft of the buffer support column and is fixed by a nut; the other end of the stay bar folding and release actuating cylinder is arranged on a body structure joint through a threaded shaft; a wheel fork is arranged on an inner cylinder of the buffer support column through a bolt; a wheel and a tire are arranged on the wheel fork by using a wheel shaft; the upper end of an upper anti-twist arm is arranged on an annular body joint; the lower end of a lower anti-twist arm is arranged on a joint of the wheel fork.; the upper anti-twist arm and the lower anti-twist arm are connected by a quick-release pin. The nose landing gear has a simple structure and complete functions on the premise of guaranteeing the strength and the rigidity of the landing gear, and is suitable for small-sized aircrafts.

Description

Aircraft nose-gear

Technical field

The invention belongs to aeronautical engineering field, relate to a kind of aircraft nose-gear.

Background technology

Although the alighting gear of present generation aircraft is of a great variety, the alighting gear that is applicable to blimp is actually rare.Along with the particularly develop rapidly of unmanned plane of blimp, particularly urgent to being applicable to the demand of the alighting gear that blimp and function are complete.

Summary of the invention

The technical problem to be solved in the present invention: a kind of deployable and collapsible aircraft nose-gear that can meet blimp, unmanned plane operating needs is provided, guaranteeing under the prerequisite of alighting gear strength and stiffness, make every effort to landing gear structure simple, complete function, and make its structural weight reach the lightest.

Technical scheme of the present invention: a kind of aircraft nose-gear, comprising:

The pressurized strut of folding and unfolding strut, installation shaft, damper leg, upper anti-arm, lower anti-turn round arm, wheel fork, wheel shaft, wheel, the tire turned round;

Described aircraft nose-gear is arranged on aircaft configuration by 2 installation shaft on damper leg, and described aircraft nose-gear can rotate around installation shaft; One end of folding and unfolding strut pressurized strut is with oscillating bearing, and oscillating bearing is connected with the axle of damper leg, by nut, is fixed; The folding and unfolding strut pressurized strut other end is arranged on housing construction joint by threaded shaft;

Wheel fork is arranged on the inner core of damper leg by bolt; Wheel and tire are arranged on wheel fork with wheel shaft; Above prevent that turning round arm upper end is contained on ring body joint; The lower anti-lower end of turning round arm is contained on the joint of wheel fork; The upper anti-arm of turning round prevents that with lower turning round arm is connected by Quick-release pin.

Beneficial effect of the present invention: advantage of the present invention is:

1) deft design, simple and compact for structure, complete function, can adapt to the handling characteristics of blimp, unmanned plane, meets operating needs.

2) adopt high strength aluminum alloy as material of main part, guaranteeing, under the prerequisite of in-use performance and intensity, rigidity requirement, effectively to have alleviated structural weight; As: wheel fork, urceolus, anti-ly turn round the vitals such as arm and all adopt aluminum alloy die forgings.

3) adopt non-maintaining self-lubricating AIRFLON cushion layer technique, reduced and safeguarded link and maintenance workload.

4) adopt the built-in upper and lower lock side of retractable actuating cylinder formula, make that jack is simple in structure, lightweight, reliability is high.

5) adopt the square cross section tire of good rigidity, make nose-gear there is good anti-sway performance.

Accompanying drawing explanation

Fig. 1 is aircraft nose-gear composition diagram of the present invention.

Fig. 2 installs schematic diagram in aircraft nose-gear wheel auto back of the present invention.

Fig. 3 is aircraft nose-gear shimmy-damper scheme of installation of the present invention.

The specific embodiment

Nose-gear design of the present invention has adopted simple column support type, monowheel chassis (see figure 1).Be provided with in wheel auto back and install, when alighting gear damper leg extends entirely, make wheel automatically get back to center position.In addition, in order to prevent shimmy of front wheels, shimmy-damper is installed on nose-gear, and employing is beneficial to anti-sway square cross section tire.

The folding and unfolding of alighting gear is completed by the retractable actuating cylinder 2 of HYDRAULIC CONTROL SYSTEM, and retractable actuating cylinder piston rod 3 shortens alighting gear and takes in backward in fuselage; Retractable actuating cylinder piston rod 3 stretches out gear down, and the inner two ends of strut pressurized strut are designed with mechanical lock, at gear up or extended position, alighting gear is locked.

Nose-gear mainly contains following component part: folding and unfolding strut pressurized strut 2, installation shaft 5, damper leg 6, shimmy-damper 7, upper anti-arm 11, lower anti-turn round arm 13, wheel fork 14, wheel shaft 15, wheel 16, the tire 17 turned round;

Nose-gear is arranged on aircaft configuration by 2 installation shaft 5 on damper leg 6, and nose-gear can rotate around installation shaft 5; One end of folding and unfolding strut pressurized strut 2 is with oscillating bearing, and oscillating bearing is connected with the axle 4 of damper leg 6, by nut, is fixed; Folding and unfolding strut pressurized strut 2 other ends are arranged on housing construction joint by threaded shaft 1;

Wheel fork 14 is arranged on the inner core 10 of damper leg 6 by bolt; Wheel 16 and tire 17 use wheel shafts 15 are arranged on wheel fork 14; Above prevent that turning round arm 11 upper ends is contained on ring body 8 joints; The lower anti-lower end of turning round arm 13 is contained on the joint of wheel fork 14; The upper anti-arm 11 of turning round prevents that with lower turning round arm 13 is connected by Quick-release pin 12.

Damper leg 6 forms the buffer system of main landing gear together with tire 17, when alighting gear stand under load, damper leg 6, in compression and stretching motion process, is crossed the damping hole on flow regulating valve by the fluid in energy disperser with high velocity stream, producing retardance, is that heat energy dissipates by aircraft landing kinetic transformation.And tire 17 also can while absorption portion energy.

In damper leg 6, be designed with in wheel auto back and install, by two cam mechanisms, form (see figure 2).Rotatable cam 18 is arranged on inner core 10, with wheel, moves; Another cam 19 is arranged on the fixed parts of damper leg 6.When damper leg extends entirely, rotating cam 2 moves along the profile of cam 4, makes wheel get back to center position.

Shimmy-damper 7 is arranged on (see figure 3) on damper leg 6.Have 2 bolts to be arranged on the joint of damper leg 6, the rocking arm of shimmy-damper 7 is connected on ring body 8.During the swing of wheel, above anti-ly turn round arm 11 and the lower anti-arm 13 of turning round drives ring bodies 8 to rotate around damper leg 6 axis, the rocking arm by shimmy-damper 7 makes its piston movement, utilizes aperture that fluid high velocity stream is made a living beyond the Great Wall to produce damping and carrys out consumed energy, prevents shimmy.

Claims (1)

1. an aircraft nose-gear, is characterized in that, comprising:

The pressurized strut of folding and unfolding strut, installation shaft, damper leg, upper anti-arm, lower anti-turn round arm, wheel fork, wheel shaft, wheel, the tire turned round;

Described aircraft nose-gear is arranged on aircaft configuration by 2 installation shaft on damper leg, and described aircraft nose-gear can rotate around installation shaft; One end of folding and unfolding strut pressurized strut is with oscillating bearing, and oscillating bearing is connected with the axle of damper leg, by nut, is fixed; The folding and unfolding strut pressurized strut other end is arranged on housing construction joint by threaded shaft;

Wheel fork is arranged on the inner core of damper leg by bolt; Wheel and tire are arranged on wheel fork with wheel shaft; Above prevent that turning round arm upper end is contained on ring body joint; The lower anti-lower end of turning round arm is contained on the joint of wheel fork; The upper anti-arm of turning round prevents that with lower turning round arm is connected by Quick-release pin.

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