CN2255403Y

CN2255403Y - Alighting carriage for plane

Info

Publication number: CN2255403Y
Application number: CN 95237862
Authority: CN
Inventors: 徐裕龄
Original assignee: Individual
Current assignee: Individual
Priority date: 1995-10-26
Filing date: 1995-10-26
Publication date: 1997-06-04
Anticipated expiration: 2005-10-26

Abstract

The utility model relates to a lifting carriage for a plane. One end of an upper crank arm perch (1) is hinged with a plane body, and the other end is hinged with a lower crank arm perch (2) of which the other end is hinged with a tackle (3). A hydraulic oil cylinder (4) and a hydraulic oil cylinder (5) are arranged between the plane body and the upper crank arm perch (1), and a hydraulic oil cylinder (6) is also arranged between the upper crank arm perch and the lower crank arm perch (2). A hydraulic oil cylinder (7) and a hydraulic oil cylinder (8) are arranged between the lower crank arm perch and the tackle (3). The utility model has the advantages of simple structure and convenient function; while in use, the utility model can extend to be vertical to the plane body or can be folded to be parallel to the plane body according to the flying requirement and can be put in a landing carriage bin with the tackle.

Description

A kind of undercarriage

The utility model relates to a kind of undercarriage.

Some modern aircrafts, as Soviet Union-27, Mi Ge-29 is the big angles-of-attack of energy all, even fuselage perpendicular to ground-surface situation under, still can keep stable state of flight, structure is very complicated, huge because the needs of state of flight all are provided with for these aircrafts, performance mono-undercarriage and complicated aircraft lifting and landing control mechanism, not only increased aircraft manufacturing cost, increased the weight of aircraft, the price of aircraft has been risen, and increased the possibility of aircraft et out of order.

The purpose of this utility model is to provide a kind of undercarriage simple in structure, multi-purpose, and it is adapted to the aircraft of big angles-of-attack, makes it to slide routinely to run landing, again can V.

The purpose of this utility model is to realize like this, it comprises the bar of cranking arm (1), lower bent lever bar (2), an end and the fuselage of bar (1) of cranking arm wherein is hinged, the other end and lower bent lever bar (2) are hinged, the other end of lower bent lever bar (2) and coaster (3) are hinged, fuselage and on crank arm hydraulic ram (4) and hydraulic ram (5) be housed between the bar (1), between bar and the lower bent lever bar (2) hydraulic ram (6) is housed also last cranking arm, hydraulic ram (7) and hydraulic ram (8) are housed between lower bent lever bar (2) and coaster (3).

The utility model is simple in structure, and effect is convenient, in use, can be by the needs of flight, by the control of machine inner control system upper and lower crank arm be extended into vertical with fuselage, perhaps be folded into parallel with fuselage, with the coaster folding and unfolding in landing gear compartment.

Below in conjunction with accompanying drawing structure of the present utility model is done detailed explanation

Fig. 1 is a constructional drawing of the present utility model

Fig. 2 is the utility model side-looking structural representation

The structural representation that Fig. 3 draws in fully for the utility model

Fig. 4 is the aircraft alighting gear working state figure that takes off vertically

Fig. 5 is an aircraft rolling start alighting gear working state figure

Fig. 6 is the aircraft working state figure

The utility model comprises the bar of cranking arm (1), lower bent lever bar (2), an end and the airframe of bar (1) of cranking arm wherein is hinged, the other end and lower bent lever bar (2) are hinged, the other end of lower bent lever bar (2) and coaster (3) are hinged, fuselage and on crank arm hydraulic ram (4) and hydraulic ram (5) be housed between the bar (1), hydraulic ram (4) is contained in the left side of the bar of cranking arm (1), hydraulic ram (5) is contained in the right of the bar of cranking arm (1), its cylinder block with on the bar (1) of cranking arm link to each other, piston rod links to each other with airframe, between bar and the lower bent lever bar (2) hydraulic ram (6) is housed also last cranking arm, hydraulic ram (7) and hydraulic ram (8) are housed between lower bent lever bar (2) and coaster (3), wherein hydraulic ram (7) is contained in the left side of lower bent lever bar, hydraulic ram (8) is contained in the right of the bar of cranking arm (1), and the cylinder body body links to each other with lower bent lever bar (2), and piston rod links to each other with coaster (3).

Coaster (3) is then by car body (9), spike (10), and wheel (11) constitutes.

The upper and lower action of cranking arm of this alighting gear is controlled by hydraulic ram (4) (5) (6), the upper and lower different attitudes of cranking arm of action control of different oil cylinders, the attitude of coaster (3) is then by hydraulic ram (7) (8) control, and it requires to keep coaster (3) and ground to be in horizontality all the time.The control of hydraulic ram is then controlled by the control system of interior of aircraft.

Three kinds of exemplary operation states below in conjunction with the description of drawings alighting gear:

The 1st kind of state (see figure 1):

When oil cylinder (4) is in the shortest position, oil cylinder (5) is in the longest position, and oil cylinder (6) is in the shortest position, last lower bent lever full extension is wholely cranked arm perpendicular to the groundly, and oil cylinder (7) is in the shortest position, oil cylinder (8) is in the longest position, makes coaster parallel to the ground.

The 2nd kind of state

When oil cylinder (4), oil cylinder (5) mediates, the position that oil cylinder (6) mediates, and last lower bent lever is＞font state, oil cylinder (7), oil cylinder (8) all mediates, and makes coaster reverse 45 degree backs parallel to the ground.

Three state: (see figure 3)

When oil cylinder (4) is in the longest position, oil cylinder (5) is in the shortest position, and oil cylinder (6) is in the longest position, last lower bent lever is folding fully, oil cylinder (7) is in the longest position, and oil cylinder (8) is in the shortest position, make coaster parallel to the ground and with folding parallel the folding of cranking arm.

(see figure 5) is when the sliding race of aircraft landing, alighting gear bends to suitable angle, determined the terrain clearance and the angle of attack of aircraft, lifted spike, aircraft is landing routinely, slide when going to certain speed if take off, stretching, extension is cranked arm, and improves fuselage, increases the angle of attack, the aircraft cunning is jumped up and is flown, thereby has shortened ground run distance.

When (see figure 4) takes off vertically when aircraft, at first stretch to go up lower bent lever, aircraft is adjusted to big angle of attack state, start the engine then, aircraft can take off vertically, and vertical landing is then opposite.

Claims

A kind of undercarriage, it is characterized in that comprising the bar (1) of cranking arm, lower bent lever bar (2), an end and the fuselage of bar (1) of cranking arm wherein is hinged, the other end and lower bent lever bar (2) are hinged, the other end of lower bent lever bar (2) and coaster (3) are hinged, fuselage and on crank arm hydraulic ram (4) and hydraulic ram (5) be housed between the bar (1), between bar and the lower bent lever bar (2) hydraulic ram (6) is housed also last cranking arm, hydraulic ram (7) and hydraulic ram (8) are housed between lower bent lever bar (2) and coaster (3).