CN103359297A - Combined catapult for aircraft carriers - Google Patents
Combined catapult for aircraft carriers Download PDFInfo
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- CN103359297A CN103359297A CN2012100895436A CN201210089543A CN103359297A CN 103359297 A CN103359297 A CN 103359297A CN 2012100895436 A CN2012100895436 A CN 2012100895436A CN 201210089543 A CN201210089543 A CN 201210089543A CN 103359297 A CN103359297 A CN 103359297A
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- aircraft
- jet engine
- linear motor
- catapult
- ejector
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Abstract
The invention relates to a combined catapult for aircraft carriers. The combined catapult is composed of a control system 7, a fuel injection system 6, and a power system. The power system is composed of a linear motor and an aircraft jet engine unit 5. When taking off from the aircraft carrier, an aircraft 1 is powered jointly by the built-in jet engine unit 5 composed of a jet engine, a linear motor and a catapult; when the required takeoff speed of the aircraft 1 is reached, the catapult jet engine unit 5 shuts off; the control system 7 applies reverse force to the linear motor; and the aircraft 1 leaves the catapult and is catapulted out. After experiencing the reverse force, a rotor 2 with the catapult jet engine unit 5 connected with the rotor quickly decelerate to stop and continues to apply reverse force to the linear motor, so that the rotor 2 of the linear motor and the catapult jet engine unit 5 are pulled back to the original positions; next catapulting is prepared after fuel is injected.
Description
Technical field
The present invention relates to the compound ejector of a kind of aircraft carrier, relate in particular to a kind of compound ejector of aircraft carrier with aero-jet engine and linear electric motors recombination boosting Assisted Take Off.
Background technology
At present on the aircraft carrier ship-board aircraft Assisted Take Off mode is mainly contained cunning that the deck end upwarps the jump up mode of flying, the steam catapult Assisted Take Off mode and studying also not the pure electromagnetic launch of the place in operation mode of taking off at present of flying.The sliding mode of flying of jumping up is simple in structure, cost is low, but the essence of the lift that takes off is still taken off by the power of aircraft self, tractive performance to aircraft requires very high, with present aero-engine technology the full oil of ship-board aircraft is completely upspring flies, shortened the hang time of aircraft, the fight that has affected carrier-borne aircraft is renderd a service; The steam catapult technical performance is ripe, and can give increases extra thrust when taking off, make aircraft completely oil completely upspring and fly, it is huge that but this ejector takes up space, complex structure, and consumption freshwater resources amount is large, afterburning terminal under power, cost is higher, and maintenance difficulties is large; Electromagnetical ejector is to lean on the electromagnetic force of linear electric motors to increase extra power to taking off, and techniques of linear motor reaches a standard at present, but carrier-borne power supply can't provide enough power, has limited the development of Electromagnetical ejector.The invention provides a kind of scheme power is provided for carrier-borne aircraft takes off, utilize exactly the comprehensive afterburning mode of linear electric motors and aero-jet engine to provide extra power for carrier-borne aircraft takes off, is exactly compound ejector technology.
Summary of the invention
The present invention relates to the compound ejector of a kind of aircraft carrier, it is characterized in that it is comprised of control system, fuel oil filling system and power system.Power system is to make a straight line motor below the aircraft-carrier-deck airstrip, many high-power jet aerial engine systems are installed on the mover of linear electric motors, and the slit by the deck on linear motor rotor stretches out a pushing arm to be promoted aircraft and travels forward.When taking off, the driving engine of the jet engine of ejector, aircraft self, linear electric motors give aircraft afterburning simultaneously, when reaching the design speed of taking off needs, airplane catapult is gone out, after airplane catapult is gone out, the jet engine of ejector is closed, linear electric motors adopt the mode of electromagnetic damping afterburning to the mover reversing sense, the jet engine speed that makes mover and link together drops to 0, continue oppositely afterburning, mover and ejector aero-engine group are withdrawn into reference position together, behind the oil of having annotated, prepare to launch next time.
Content of the present invention is: such as accompanying drawing 1, accompanying drawing 2, the compound ejector of a kind of aircraft carrier is characterized in that being comprised of control system 7, fuel oil filling system 6 and power system.Power system is to open a slit 9 along the airstrip length direction on aircraft-carrier-deck 3, along slit 9 length directions one high-performance linear motor stator electric 4 is installed aircraft-carrier-deck 3 times again, linear motor rotor 2 of supporting installation, linear motor rotor 2 can be done linear reciprocating motion along linear motor stator electric 4; One group of aero-jet engine 5 is installed in the below of linear motor rotor 2 take linear motor stator electric 4 as the axle left-right symmetric; The top of the mover 2 of linear electric motors connects a pushing arm 8, aircraft-carrier-deck is stretched out in the upper end of pushing arm 8 from slit 9, pushing arm 8 can be done straight-line motion along linear motor stator electric 4 with linear motor rotor 2, straight-line motion can be done along slit 9 in the upper end of pushing arm 8 on aircraft-carrier-deck 3, be convenient to aircraft 1 reinforcing above the deck.
Description of drawings
The present invention will be further described below in conjunction with accompanying drawing and embodiment:
Fig. 1, Fig. 2 are the compound ejector local structure of a kind of aircraft carrier of the present invention scheme drawings
The specific embodiment
Example, such as accompanying drawing 1, accompanying drawing 2, the compound ejector of a kind of aircraft carrier is comprised of control system 7, fuel oil filling system 6 and power system.Control system 7 is used for that the control power system afterburningly move, slows down, returned, the control of fuel up and aviator's synchronous operation and processing chance failure etc.Fuel oil filling system 6 is used to the quick fuel up of the aero-jet engine of ejector.Power system is to open a slit 9 at aircraft-carrier-deck 3 along the airstrip length direction, along slit 9 length directions one high-performance linear motor stator electric 4 is installed aircraft-carrier-deck 3 times again, with stator 4 is supporting a linear motor rotor 2 is installed again, linear motor rotor 2 can be done linear reciprocating motion along linear motor stator electric 4; Below linear motor rotor 2 take linear motor stator electric 4 as axle, left-right symmetric is installed one group of aero-jet engine 5, even numbers such as this preferably 2,4,6 of aero-jet engine of group or 8, it is one group that this example adopts 4 jet engines, and the size of thrust determines the quantity of driving engine as required.The mover 2 of linear electric motors upwards connects a pushing arm 8, stretches out the slit 9 of the upper end of pushing arm 8 from aircraft-carrier-deck 3, in order to be connected with the part of the force of aircraft 1; Pushing arm 8 can be done linear reciprocating motion along linear motor stator electric 4 with linear motor rotor 2, and the upper end of pushing arm 8 can be done linear reciprocating motion along slit 9 with linear motor rotor 2 on aircraft-carrier-deck 3, is convenient to aircraft 1 reinforcing above the deck.Ejection process is as follows: compound ejector linear motor rotor 2 and aero-jet engine group 5 stop at the start of a race end of aircraft carrier deck airstrip, the fuel oil of having annotated is waited for igniting, the aircraft 1 that wait is taken off rests in post position, adjust direction and position, the upper end of the stress point on the aircraft with pushing arm 8 linked to each other; After the power supply of linear electric motors and control program are ready, after the aviator receives the instruction of taking off, igniting aero-engine and ejector jet engine group 5, after reaching requirement, thrust discharges linear motor rotor 2, start simultaneously linear electric motors, ship-board aircraft 1 is at self jet engine, under ejector jet engine group 5 and the linear electric motors combined action carrier-borne aircraft 1 is accelerated, after speed reaches requirement, close ejector jet engine group 5, simultaneously linear electric motors are loaded the reversing sense electric current, linear motor rotor 2 and ejector jet engine group 5 are slowed down rapidly, aircraft 1 continues to continue to accelerate to take off under promoting carrying jet engine, breaks away from ejector.Control system applies the reversing sense propulsive effort to linear motor rotor 2, order about linear motor rotor 2 and ejector jet engine group 5 under the reversing sense electromagnetic force rapidly with Speed Reduction to 0, and stop after turning back to former post position.6 pairs of ejector jet engines of control system 7 control fuel oil filling systems group 5 fuel oil of having annotated is waited for again starting.
This structure had both overcome the sliding hypodynamic shortcoming that flies of jumping up, the deficiency that overcome again the steam catapult complex structure, needs to consume a large amount of fresh water, and utilized the aero-jet engine technology of present maturation, the thrust size can be used the driving engine quantity flexible configuration that increases and reduce the jet engine group.
Claims (4)
1. compound ejector of aircraft carrier is characterized in that power system is by linear electric motors and 5 compound compositions of aero-jet engine group.
2. according to the compound ejector of the described a kind of aircraft carrier of claim (1), it is characterized in that aero-jet engine is that both sides are symmetrical and installs.
3. according to claim (1), the compound ejector of (2) described aircraft carrier, it is characterized in that aero-jet engine group 5 and linear motor rotor 2 are fixedly connected into an integral body.
4. according to the described aero-jet engine of claim (3), it is characterized in that with aero-jet engine group 5 be installed in aircraft carrier deck 3 below.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012100895436A CN103359297A (en) | 2012-03-30 | 2012-03-30 | Combined catapult for aircraft carriers |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012100895436A CN103359297A (en) | 2012-03-30 | 2012-03-30 | Combined catapult for aircraft carriers |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103359297A true CN103359297A (en) | 2013-10-23 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012100895436A Pending CN103359297A (en) | 2012-03-30 | 2012-03-30 | Combined catapult for aircraft carriers |
Country Status (1)
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| CN (1) | CN103359297A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104554815A (en) * | 2015-01-19 | 2015-04-29 | 亚欧益盟科技（北京）有限公司 | Electromagnetic catapult |
| CN104554753A (en) * | 2013-10-10 | 2015-04-29 | 周虹 | General aircraft linear motor traction take-off acceleration launching device |
| CN104590579A (en) * | 2014-12-16 | 2015-05-06 | 李新亚 | Aircraft carrier airplane boost catapult launch method |
| CN104670447A (en) * | 2015-01-29 | 2015-06-03 | 赵凤银 | Aircraft carrier, ship and land-water jet runway system with efficient short-range slide or vertical take-off and landing aircraft units |
| CN105667820A (en) * | 2016-01-04 | 2016-06-15 | 济南环太机电技术有限公司 | Tunnel type shipboard aircraft catapult capable of using multiple types of energy |
| CN111216915A (en) * | 2018-11-26 | 2020-06-02 | 韩伟立 | Boosting ejection device |
| CN114435618A (en) * | 2022-03-18 | 2022-05-06 | 北京理工大学 | Aircraft traction ejection device and system and aircraft ejection control method |
| CN114537696A (en) * | 2022-03-18 | 2022-05-27 | 北京理工大学 | Aircraft engagement ejection device and system and aircraft ejection control method |
Citations (6)
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|---|---|---|---|---|
| FR2479138B1 (en) * | 1980-04-01 | 1983-06-10 | Andre Gilbert | |
| CA2328669A1 (en) * | 2000-12-15 | 2002-06-15 | Florencio Neto Palma | Airport takeoff-landing assisting shuttle |
| CN101314410A (en) * | 2007-05-31 | 2008-12-03 | 胡宣哲 | Numerical control electrohydraulic integration ejection method and device |
| CN201172483Y (en) * | 2008-01-01 | 2008-12-31 | 宣建民 | Electromagnetical ejector |
| CN101513936A (en) * | 2009-03-31 | 2009-08-26 | 王力丰 | Taking off device and taking off method for carrier-based aircraft |
| CN102343982A (en) * | 2011-07-21 | 2012-02-08 | 鲁小朔 | Semi-open interlayer booster takeoff runway of aircraft carrier |
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2012
- 2012-03-30 CN CN2012100895436A patent/CN103359297A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2479138B1 (en) * | 1980-04-01 | 1983-06-10 | Andre Gilbert | |
| CA2328669A1 (en) * | 2000-12-15 | 2002-06-15 | Florencio Neto Palma | Airport takeoff-landing assisting shuttle |
| CN101314410A (en) * | 2007-05-31 | 2008-12-03 | 胡宣哲 | Numerical control electrohydraulic integration ejection method and device |
| CN201172483Y (en) * | 2008-01-01 | 2008-12-31 | 宣建民 | Electromagnetical ejector |
| CN101513936A (en) * | 2009-03-31 | 2009-08-26 | 王力丰 | Taking off device and taking off method for carrier-based aircraft |
| CN102343982A (en) * | 2011-07-21 | 2012-02-08 | 鲁小朔 | Semi-open interlayer booster takeoff runway of aircraft carrier |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104554753A (en) * | 2013-10-10 | 2015-04-29 | 周虹 | General aircraft linear motor traction take-off acceleration launching device |
| CN104590579B (en) * | 2014-12-16 | 2017-02-22 | 李新亚 | Aircraft carrier airplane boost catapult launch method |
| CN104590579A (en) * | 2014-12-16 | 2015-05-06 | 李新亚 | Aircraft carrier airplane boost catapult launch method |
| CN104554815A (en) * | 2015-01-19 | 2015-04-29 | 亚欧益盟科技（北京）有限公司 | Electromagnetic catapult |
| CN104554815B (en) * | 2015-01-19 | 2017-06-20 | 亚欧益盟科技（北京）有限公司 | A kind of Electromagnetical ejector |
| CN104670447A (en) * | 2015-01-29 | 2015-06-03 | 赵凤银 | Aircraft carrier, ship and land-water jet runway system with efficient short-range slide or vertical take-off and landing aircraft units |
| CN105667820A (en) * | 2016-01-04 | 2016-06-15 | 济南环太机电技术有限公司 | Tunnel type shipboard aircraft catapult capable of using multiple types of energy |
| CN111216915A (en) * | 2018-11-26 | 2020-06-02 | 韩伟立 | Boosting ejection device |
| CN111216915B (en) * | 2018-11-26 | 2021-07-09 | 韩伟立 | Boosting ejection device |
| CN114435618A (en) * | 2022-03-18 | 2022-05-06 | 北京理工大学 | Aircraft traction ejection device and system and aircraft ejection control method |
| CN114537696A (en) * | 2022-03-18 | 2022-05-27 | 北京理工大学 | Aircraft engagement ejection device and system and aircraft ejection control method |
| CN114435618B (en) * | 2022-03-18 | 2024-03-05 | 北京理工大学 | Aircraft traction ejection device, system and aircraft ejection control method |
| CN114537696B (en) * | 2022-03-18 | 2024-03-08 | 北京理工大学 | Aircraft engagement ejection device, system and aircraft ejection control method |
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Application publication date: 20131023 |