CN102795348A

CN102795348A - Multi-pipe combined ejector of aircraft carrier

Info

Publication number: CN102795348A
Application number: CN2012101447691A
Authority: CN
Inventors: 银世德
Original assignee: Individual
Current assignee: Individual
Priority date: 2012-05-04
Filing date: 2012-05-04
Publication date: 2012-11-28

Abstract

The invention provides an aircraft carrier ejector and especially provides a multi-pipe combined ejector of an aircraft carrier. The multi-pipe combined ejector is a boosting device capable of improving the taking off speed of the carrier plane when the carrier plane on the aircraft carrier takes off and belongs to the field of military. The multi-pipe combined ejector provided by the invention utilizes a most advanced and unique combination of a double-pipe spring array, a cylinder and a piston to drive the ejector to perform multilevel ejection within a controllable time to gradually accelerate so as to enable the carrier plane to stably and safely take off within the shortest time and at a fastest speed under a full load state, the multi-pipe combined ejector provided by the invention has the advantages of simple structure, convenience in maintenance and repair, long service life, small weight and low manufacturing cost, so that the multi-pipe combination ejector is the most ideal carrier plane ejector in the world currently. The multi-pipe combined ejector provided by the invention comprises an ejector front cover, a piston, a plane tractor, a front oil hole, a first level spring group, a steel rope, an ejector shell, an engine oil pipe, a second level spring group, an engine oil controller, a snap spring, a traction scored pulley, a back oil hole, a main gear, a slide gear, a shifting fork, a starting wheel shaft, a traction rope starting wheel, a main gear shaft, a conical wheel, an ejector back cover, a second ejector shell, a brake wheel and an oil brake, etc.

Description

Aircraft carrier multitube combination ejector

The present invention provides a kind of aircraft carrier ejector, and especially a kind of aircraft carrier multitube combination ejector belongs to military domain.

At present, have the majority state of aircraft carrier in the world, generally all adopting steam-type ejector, its shortcoming is to maintain enough steam for a long time, and cylinder piston must have higher sealing property, otherwise can make the safety when taking off can not get guaranteeing.The electromagnetic launch device is technical very strong simultaneously, is difficult in the short time grasp.In decades, a lot of countries have all carried out conscientiously research to the spring loaded ereisma, all because initial velocity is high; Aviator and aircraft are caused damage, and acceleration/accel is low again, the speed that the aircraft out of reach is taken off; And the present invention has adopted a kind of most advanced, multitube spring battle array and cylinder, piston in combination, makes ejector in the controlled time, carries out multistage launching; Quicken step by step, make carrier-borne aircraft under the fully loaded situation, steadily take off safely.Advantage of the present invention is: simple in structure, long service life, in light weight, cost is low, bigger than single tube ejector elastic force, little good manufacturing of parts is optimal in the world at present carrier-based aircraft ejector.

The present invention includes: ejector protecgulum, piston, aircraft tractor, preceding oilhole, first order spring assembly, cable wire, ejector shell, oil pipe, second stage spring assembly, oil control device, jump ring, traction sheave, back oilhole, main gear, cliding gear, shift fork, startup wheel shaft, hauling rope, starter cup, main gear shaft, bevel wheel, ejector bonnet, second ejector shell, brake wheel, oil stop device, the 3rd pipe ejector, etc.

Explain according to accompanying drawing: Fig. 1 is the scheme drawing of first, second ejector of aircraft carrier.The scheme drawing of Fig. 2 the 3rd ejector.Fig. 3 is the front view of aircraft carrier multitube combination ejector.Ejector protecgulum (1); Piston (2); Aircraft tractor (3); Preceding oilhole (4); First order spring assembly (5); Cable wire (6); Ejector shell (7); Oil pipe (8); Hauling rope (9); Second stage spring assembly (10); Oil control device (11); Jump ring (12); Traction sheave (13); Back oilhole (14); Main gear (15); Starter cup (16); Cliding gear (17); Shift fork (18); Start wheel shaft (19); Main gear shaft (20); Bevel wheel (21); Ejector bonnet (22); Second ejector shell (23); Brake wheel (24); The oil device (25) of stopping; The 3rd ejector (26)

Practical implementation is: according to accompanying drawing 1, earlier with first, second ejector shell (7), be installed in side by side under the aircraft carrier deck, bevel wheel (21) be installed on the main gear shaft (20) again; Main gear shaft (20) is put into ejector shell (7), and bearing fixing is used at two ends, at an end of main gear shaft (20), main gear (15) and traction sheave (13) is installed; The other end is installed brake wheel (24), and jump ring (12) and other jump rings are installed in survey in the rear end of ejector shell (7), and cable wire (6) one ends are fixed on the plug helix of bevel wheel (21), then put into one-level spring assembly (5) and multistage spring assembly again; After the other end of cable wire (6) passes multistage spring assembly, be fixed on the piston (2), cliding gear (17) and starter cup (16) are mounted and fixed on the startup wheel shaft (19); Bearing fixing is used at two ends, and starter cup (16) is connected with electrical motor, and piston (2) is packed in the ejector shell (7); Fix ejector protecgulum (1), establish oil control device (11) in the middle of the oil pipe (8), oil pipe (8) one ends are connected with preceding oilhole (4); The other end is connected with back oilhole (14), and traction sheave (13) is connected with aircraft tractor (3) through hauling rope (9), and aircraft tractor (3) is connected with aircraft; With the 3rd ejector (26), the below that is installed in first, second ejector is middle and fixing, and main gear (15) and cliding gear (17) is meshing according to accompanying drawing 2; After all ejector parts install, all pour machine oil in the device, start DC motor in the warship stopping with oil in three ejector shells; Drive the playback of piston (2) and aircraft tractor (3), at this moment jump ring (12) and other jump rings block the spring of back, when aircraft begins to take off; Pull shift fork (18), cliding gear (17) is separated with main gear (15), brake wheel (24) separates with brake gear; Piston (2) is reach fast under the effect of first order spring assembly (5), and is simultaneously too fast in order to prevent the aircraft initial velocity, and at this moment brake gear begins brake; The anterior machine oil of ejector shell (7) inner carrier (2) begins compression, when aircraft soon takes off, loosens brake gear and oil control device (11) immediately; The front end machine oil of piston (2) is constantly reduced, and the oil cylinder internal pressure constantly reduces, and the speed of aircraft also improves constantly; Along with the ejection of first order spring assembly, it reduces the pressure of second stage spring, and second stage spring assembly is broken through stopping of jump ring and ejected; After second stage spring assembly (5) ejects, the third stage, and other spring assembly eject step by step, make aircraft leave warship and steadily take off; After piston crossed preceding oilhole (4), the anterior machine oil of piston did not outflow, so piston stops to move ahead under oil is stopped the device resistance.

Claims

1. an aircraft carrier multitube combination ejector is characterized in that: earlier with first, second ejector shell (7), be installed in side by side under the aircraft carrier deck; Bevel wheel (21) is installed on the main gear shaft (20) again, main gear shaft (20) is put into ejector shell (7), bearing fixing is used at two ends; At an end of main gear shaft (20), main gear (15) and traction sheave (13) are installed, the other end is installed brake wheel (24); Jump ring (12) and other jump rings are installed in the rear end of ejector shell (7) and survey, and cable wire (6) one ends are fixed on the plug helix of bevel wheel (21), then put into one-level spring assembly (5) and multistage spring assembly again; After the other end of cable wire (6) passes multistage spring assembly, be fixed on the piston (2) cliding gear (17) and starter cup (16); Be mounted and fixed on the startup wheel shaft (19), bearing fixing is used at two ends, and starter cup (16) is connected with electrical motor; Piston (2) is packed in the ejector shell (7), fix ejector protecgulum (1), establish oil control device (11) in the middle of the oil pipe (8); Oil pipe (8) one ends are connected with preceding oilhole (4), and the other end is connected with back oilhole (14), and traction sheave (13) is connected with aircraft tractor (3) through hauling rope (9); Aircraft tractor (3) is connected with aircraft; With the 3rd ejector (26), the below that is installed in first, second ejector is middle and fixing, and main gear (15) and cliding gear (17) is meshing according to accompanying drawing < 2 >.