CN112829961A

CN112829961A - Aircraft carrier catapult

Info

Publication number: CN112829961A
Application number: CN202110212955.3A
Authority: CN
Inventors: 王运宏
Original assignee: Individual
Current assignee: Individual
Priority date: 2021-02-19
Filing date: 2021-02-19
Publication date: 2021-05-25

Abstract

The invention belongs to a kind of water surface large-scale naval vessel and aircraft carrier use the aircraft carrier take off the catapult name used for using fighter aircraft is aircraft carrier catapult, only use catapult on the American aircraft carrier in the world at present; other countries and China all use the takeoff mode of the ski-jump type fighter, and the disadvantage is that the takeoff speed is slow, the good oil quantity is large, the aircraft flies a little far, the attack range of the fighter is influenced … …, and the like.

Description

Aircraft carrier catapult

(I) technical field

The invention belongs to a special purpose for large-tonnage ships sailing on water, such as aircraft carriers.

(II) background of the invention

With the continuous development of science and technology, only American aircraft carriers in the world use ejection devices, also called ejectors, and the shape takeoff fighters using a slide device (with arc-shaped upward slopes for the heads of the ships) in other countries comprise two aircraft carriers currently used in China. Its disadvantages are slow take-off speed, high oil quantity, not far flying, and influence on attack range of warplane. (the inventor has an immature suggestion that the speed can be regulated by using a direct current motor, such as a motor used in high-speed rail with the speed of 300-

Disclosure of the invention

The invention aims to solve the problem that the aircraft carrier in China adopts the ski-jump takeoff mode at present, and the defects of the ski-jump takeoff mode are as described above.

(IV) description of the drawings

FIG. 1 is a plan view of the deck of the aircraft carrier with the nose and the front of the flying lead stop of the present invention taken as lines (a-A chute front cross-sectional view).

In the figure: the aircraft carrier warplane takeoff chute 1 is concave, the slider extends out of the chute 2, the groove parking push brace rod 3 and the push brace rod mechanism 6.

FIG. 2 is a head view of a planetary reducer according to the present invention; (B-B chute full-length section view)

4 is the running direction of the steel wire rope, 5 is the pin, 7 is the stiffening plate, 8 is the slide block, and 9 is the front wheel of the fighter plane.

10 is a front wheel support of the fighter plane, 12 is a steel wire rope pulley, and 13 is a steel wire rope riding wheel;

FIG. 3 is a front view of the slider;

FIG. 4 is a left side view of the slider;

FIG. 5 is a top view of the slider;

FIG. 6 is a motor and planetary reducer assembly; (C-C represents the structure of the driven wheel)

In the figure: 14, pulleys 4+4 on the sliding block are 8 pulleys; 15, pulleys 4+4 below the sliding block are 8 pulleys; 16 is a slider right pulley 4+4 which is 8 pulleys; 17 is a slider left pulley 4+ 4-8 pulleys; 18 is a direct current main motor; 19 is a motor and planetary reducer connector; 20 is a planetary reducer left-turn unit; and 21 is a right-turning unit of the passive speed reducer.

Detailed Description

The invention relates to a catapult for an aircraft carrier; firstly, various switches are opened, the barrier plate is laid flat, the fighter is dragged to a flying line for parking, the trailer is separated from a stepped place, the slow-regulating direct-current auxiliary motor 22 drags the slide block 8 to the front wheel 9 of the fighter, and meanwhile, the push stay bar 6 is also lifted to be close to the front wheel strut 10; the power supply 22 is turned off. When the warplane is refueled to the speed of 280 plus 300 kilometers, the warplane is thrown to the front of the aircraft carrier by pressing the button ejector of the main direct current motor, and the slide block 8 is contacted to form a switch to automatically stop the main direct current motor. The slide block 8 can automatically return to the groove at the original parking place. Since 1 has a slope of 0-20 degrees plus its own weight, it returns to its original position.

Claims

1. The aircraft carrier catapult uses a planetary reducer.

2. The reducer of the invention has two coaxial turning directions, one turning direction is clockwise 21, and the other turning direction is anticlockwise 20.

3. The invention has 20+21 positive and negative directions on the same shaft, 18 main direct current motors on the shaft and 22 auxiliary direct current motors on the shaft.

4. In the figure: 1, forming a groove in the shape of a flying chute of a fighter plane; 2 is a sliding opening with a sliding chute extending out; and 3, the groove is used for parking the push stay bar.

5. The slider is moved out of the front view of fig. 3, the left view of fig. 4, and the top view of fig. 5.

6. The sliding chute of the invention (A-A) has a sectional shape of the front surface, and 3 is a groove parking push stay bar shape.

7. The catapult on the aircraft carrier has a chute with a slope of 0-20 degrees and a straight slope (without an arc).