CN103600848A - Double-pipe reciprocating aircraft carrier catapult - Google Patents
Double-pipe reciprocating aircraft carrier catapult Download PDFInfo
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- CN103600848A CN103600848A CN201310005373.3A CN201310005373A CN103600848A CN 103600848 A CN103600848 A CN 103600848A CN 201310005373 A CN201310005373 A CN 201310005373A CN 103600848 A CN103600848 A CN 103600848A
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- aircraft
- aircraft carrier
- pistons
- catapult
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Abstract
The invention provides an aircraft carrier catapult and particularly relates to a double-pipe reciprocating aircraft carrier catapult. The double-pipe reciprocating aircraft carrier catapult which is a boosting device which can improve the taking off speed of a shipboard aircraft when the shipboard aircraft of an aircraft carrier takes off is characterized in that pistons and spring sets are installed inside two catapults. According to the double-pipe reciprocating aircraft carrier catapult, a giant motor is firstly started rotating in the forward direction to drive the piston of one catapult to move backward to enable one spring set to be compressed; then cylinders which are arranged before the pistons are filled with engine oil; an oil pressure controller is started to enable the engine oil to be gradually discharged into the other catapulting cylinder when an aircraft takes off; the spring sets rapidly expand to push the pistons to move forward along with reduction of the pressure of the oil which is arranged before the pistons; the pistons haul the aircraft to rapidly take off through hauling cables; the large motor starts rotating reversely to enable the elastic force of the spring sets to be enhanced meanwhile the spring sets expand; when a second aircraft takes off, the second catapult is used, and the second aircraft takes off according to the same method. The double-pipe reciprocating aircraft carrier catapult has the advantages of being simple in structure, low in requirement for leak tightness of the cylinder pistons and low in utilization costs.
Description
Technical field
The invention provides a kind of aircraft carrier ejector, especially a kind of two-tube reciprocal aircraft carrier ejector, belongs to military domain.
Background technology
?at present, have in the world the majority state of aircraft carrier, generally all adopt steam-type ejector, this ejector, must maintain enough steam for a long time, and cylinder piston must have higher sealing property, otherwise can make ejector under power.Now a few countries is studied, Electromagnetical ejector on probation is technical very strong, in short time, be difficult to grasp, in decades, a lot of countries, to spring loaded ereisma, have all carried out conscientiously research, all because initial velocity is high, easily make aviator and aircraft cause damage, the speed low again with brief acceleration, aircraft out of reach is taken off, up to the present goes back neither one country and really grasps or use this technology.
summary of the invention
For above-mentioned deficiency, need to develop a kind of novel aircraft carrier ejector, make it save the energy, reduce costs, in view of this, the present invention has adopted a kind of mechanical braking, the two-tube reciprocating ejection device of oil pressure control and spring assembly, it is when taking off, first close oil pressure control, make two ejector spring assembly compressions, to in one of them ejector shell, fill with after machine oil, loosen the brake is taken turns gradually, open and there is both forward and reverse directions electrical motor immediately, open gradually oil pressure control, machine oil enters another ejector that is in compression immediately, along with the pressure before piston reduces gradually, multistage spring assembly is expanded gradually, expansion gradually along with multistage spring assembly, make again piston constantly move ahead, piston drives main shaft to rotate by hauling rope again, hauling block passes through again hauling rope, before giving tractor and aircraft, exert all one's strength, at this, start again the electrical motor forward with both forward and reverse directions simultaneously, make the airplane tractor very large power of having got back, to making after aircraft igniter, severing steel rod accelerates to move ahead, until steadily take off, piston arrives oil is stopped behind chamber and is stopped immediately moving ahead.Then, close oil pressure control, make electrical motor reversion, bevel wheel moves after affecting piston by cable wire, and spring assembly compression is resetted, machine oil after piston is by piston fuel-return valve, get back to the oil cabinet before piston, after the work of this ejector is complete, the machine oil of another ejector oil cabinet is full, wait at any time the second airplane is ejected, advantage of the present invention is: the performance requriements of the sealing of simple in structure, cylinder piston is tight, cost and operating costs low.This invention bag draw together ﹕ oil pressure control, hauling block, ejector shell, hauling rope, oil cabinet, piston oil return valve, multistage spring assembly, airplane tractor, bevel wheel, sheave, bonnet, brake wheel, oil stop chamber, piston, cable wire, oil hole, spring perch, reaction gear, there is both forward and reverse directions motor gear, there are the electrical motor, main shaft, flight deck of both forward and reverse directions etc.
Accompanying drawing explanation
Below in conjunction with accompanying drawing, the present invention is described in detail
Fig. 1 is the schematic diagram of existing two-tube reciprocal aircraft carrier ejector.
?fig. 2 is that aircraft launches schematic diagram on flight deck.
the present invention includes: oil pressure control (1), hauling block (2), ejector shell (3), hauling rope (4), oil cabinet (5), piston fuel-return valve (6), multistage spring assembly (7), airplane tractor (8), bevel wheel (9), sheave (10), bonnet (11), brake wheel (12), the oil chamber (13) of stopping, piston (14), cable wire (15), oil hole (16), spring perch (17), reaction gear (18), there is both forward and reverse directions motor gear (19), electrical motor (20) main shaft (21) with both forward and reverse directions, flight deck (22) etc.
the specific embodiment is
According to Fig. 1 first by two ejector shells (3), be arranged on side by side aircraft carrier deck (22) below, and parallel with aircraft carrier, the front end of two ejectors is connected with pipeline, oil pressure control (1) is established in centre.Then on piston (14), two piston oil return valves (6) are respectively set, again two pistons (14) are arranged in two ejector shells (3), multistage spring assembly (7) is then installed, two bevel wheeies (9) are arranged on two main shafts (18), main shaft (18) two ends are fixed on ejector shell (3) rear end with bearing, article two, cable wire (15) one end connects bevel wheel (9), the other end connects piston (14), sheave (10) is respectively installed in one end of two main shafts (21), sheave (10) connects hauling rope (4), hauling rope (4) other end is connected with airplane tractor (8) through hauling block (2), main gear (18) is then installed again, main gear (18) is with to have both forward and reverse directions motor gear (19) meshing, having both forward and reverse directions electrical motor (20) is connected with current controller and power supply, the other end of main shaft (20) is installed brake wheel (12).
Claims (3)
1. a two-tube reciprocal aircraft carrier ejector, it is characterized in that: according to scheming <1> first by two ejector shells (3), be arranged on side by side aircraft carrier deck (22) below, and parallel with aircraft carrier, the front end of two ejectors is connected with pipeline, and oil pressure control (1) is established in centre.
2. on piston (14), two piston oil return valves (6) are respectively set, again two pistons (14) are arranged in two ejector shells (3), multistage spring assembly (7) is then installed, two bevel wheeies (9) are arranged on two main shafts (18), main shaft (18) two ends are fixed on ejector shell (3) rear end with bearing, article two, cable wire (15) one end connects bevel wheel (9), the other end connects piston (14), the cable wire of two ejectors (15), when the upper winding of bevel wheel (9), direction must be contrary.
3. sheave (10) is respectively installed in one end of two main shafts (21), sheave (10) connects hauling rope (4), hauling rope (4) other end is connected with airplane tractor (8) through hauling block (2), main gear (18) is then installed again, main gear (18) is with to have both forward and reverse directions motor gear (19) meshing, have both forward and reverse directions electrical motor (20) and be connected with current controller and power supply, the other end of main shaft (20) is installed brake wheel (12).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310005373.3A CN103600848A (en) | 2013-01-08 | 2013-01-08 | Double-pipe reciprocating aircraft carrier catapult |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310005373.3A CN103600848A (en) | 2013-01-08 | 2013-01-08 | Double-pipe reciprocating aircraft carrier catapult |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103600848A true CN103600848A (en) | 2014-02-26 |
Family
ID=50119141
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310005373.3A Pending CN103600848A (en) | 2013-01-08 | 2013-01-08 | Double-pipe reciprocating aircraft carrier catapult |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103600848A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113978749A (en) * | 2018-05-08 | 2022-01-28 | 马斌久 | Novel spring aircraft carrier catapult |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102700721A (en) * | 2012-05-04 | 2012-10-03 | 银世德 | Combined catapult for aircraft carrier |
| CN102700720A (en) * | 2012-05-04 | 2012-10-03 | 银世德 | Double-tube combined catapult for aircraft carrier |
| CN102795348A (en) * | 2012-05-04 | 2012-11-28 | 银世德 | Multi-pipe combined ejector of aircraft carrier |
| CN102795347A (en) * | 2012-05-04 | 2012-11-28 | 银世德 | Two-tube spring ejector for aircraft carrier |
| CN102849223A (en) * | 2012-04-16 | 2013-01-02 | 银世德 | Novel spring catapult for aircraft carrier |
-
2013
- 2013-01-08 CN CN201310005373.3A patent/CN103600848A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102849223A (en) * | 2012-04-16 | 2013-01-02 | 银世德 | Novel spring catapult for aircraft carrier |
| CN102700721A (en) * | 2012-05-04 | 2012-10-03 | 银世德 | Combined catapult for aircraft carrier |
| CN102700720A (en) * | 2012-05-04 | 2012-10-03 | 银世德 | Double-tube combined catapult for aircraft carrier |
| CN102795348A (en) * | 2012-05-04 | 2012-11-28 | 银世德 | Multi-pipe combined ejector of aircraft carrier |
| CN102795347A (en) * | 2012-05-04 | 2012-11-28 | 银世德 | Two-tube spring ejector for aircraft carrier |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113978749A (en) * | 2018-05-08 | 2022-01-28 | 马斌久 | Novel spring aircraft carrier catapult |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
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| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20140226 |