CN106904290A - A kind of carrier-borne aircraft power-assisted catapult launcher - Google Patents
A kind of carrier-borne aircraft power-assisted catapult launcher Download PDFInfo
- Publication number
- CN106904290A CN106904290A CN201710196349.0A CN201710196349A CN106904290A CN 106904290 A CN106904290 A CN 106904290A CN 201710196349 A CN201710196349 A CN 201710196349A CN 106904290 A CN106904290 A CN 106904290A
- Authority
- CN
- China
- Prior art keywords
- aircraft
- power
- assisted
- jet engine
- deflector
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000009428 plumbing Methods 0.000 claims abstract description 8
- 239000002828 fuel tank Substances 0.000 claims abstract description 3
- 230000008450 motivation Effects 0.000 claims 1
- 239000013505 freshwater Substances 0.000 abstract description 4
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000001569 carbon dioxide Substances 0.000 description 1
- 229910002092 carbon dioxide Inorganic materials 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- VUZPPFZMUPKLLV-UHFFFAOYSA-N methane;hydrate Chemical compound C.O VUZPPFZMUPKLLV-UHFFFAOYSA-N 0.000 description 1
- 230000036632 reaction speed Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
- B64F1/10—Ground or aircraft-carrier-deck installations for launching aircraft using self-propelled vehicles
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The present invention is a kind of carrier-borne aircraft power-assisted catapult launcher, belongs to military equipment field, including：Electric four-wheel vehicle (1) power-assisted jet engine (2), the first deflector (3), the second deflector (4), push rod (5), aircraft (6), aircraft jet engine (7), aircraft plumbing bar (8), wherein, power-assisted jet engine is fixed above electric four-wheel vehicle, it is the first deflector before power-assisted jet engine, power-assisted jet engine is followed by the second deflector, electric four-wheeled front of the host fixes push rod, push rod front portion is fixed with wheel, push rod front end heads on aircraft plumbing bar, promotes airplane motion；The afterbody of aircraft is aircraft jet engine；Fuel tank is provided with above electric four-wheel vehicle.This launching apparatus is without fresh water；Small volume；Reaction is fast；Operating cost is low；Ejection vibration is small.
Description
Technical field
The invention belongs to military equipment, the especially catapult launcher of naval's carrier-borne aircraft.
Background technology
Aircraft on aircraft carrier is mostly the jet plane for fixing leaf, and typically using ski-jump take-off, this needs one
Takeoff runway more long, also difficulty fully loaded takeoff, taken off mode to improve, occur in that steam ejection takes off, it can overcome the disadvantages that above-mentioned side
The weak point of formula.But need a big boiler, the water in boiler it is boiled as the steam with very big pressure, it is necessary to
Several hours, reaction is slow, is not suitable with the quick demand of modern war.And need to be many with fresh water, the volume of catapult-launching gear is also huge.The
Three kinds is that electromagnetic launch takes off.Electromagnetic launch can make up the deficiency of aforesaid way, but, there need to be powerful electric power, can only be navigated in core
Used on mother, therefore, also need new launching apparatus
The content of the invention：
A kind of without fresh water the invention aims to provide, small volume, reaction is fast, a kind of low carrier-borne aircraft of operating cost
Power-assisted catapult launcher.
Realizing the technical scheme of above-mentioned purpose is, a kind of carrier-borne aircraft power-assisted catapult launcher, including：Electric four-wheel vehicle,
Power-assisted jet engine, the first deflector, the second deflector, push rod, aircraft, aircraft jet engine, aircraft plumbing bar, wherein,
Power-assisted jet engine is fixed above electric four-wheel vehicle, the first deflector, power-assisted spray are fixed before power-assisted jet engine
The second deflector is fixed behind gas engine, electric four-wheeled front of the host is fixed push rod, wheel, push rod front end are fixed with push rod
Aircraft plumbing bar is headed on, airplane motion is promoted, the afterbody of aircraft is aircraft jet engine；Oil is provided with above electric four-wheel vehicle
Case.
Further, the push rod is multistage bar, and multistage bar can be folded, so as to reduce volume；
Further, the push rod is hydraulically extensible bar.
Further, the horizontal sextant angle of the first deflector is big, the second deflector horizontal sextant angle is small.
Further, twice of the power of the power-assisted jet engine more than aircraft jet engine power.
Technique effect：
1. this launching apparatus is without fresh water；
2. small volume；
3, reaction is fast；
4, operating cost is low.
5. deflector follows aircraft to walk, and aircraft flame influences small to deck
Brief description of the drawings
Fig. 1 is a kind of schematic diagram of carrier-borne aircraft power-assisted catapult launcher
Shown in figure：Electric four-wheel vehicle 1, power-assisted jet engine 2, the first deflector 3, the second deflector 4, push rod 5, fly
Machine 6, aircraft jet engine 7, aircraft plumbing bar 8
Specific embodiment
One embodiment of the present invention is illustrated below in conjunction with the accompanying drawings.
A kind of carrier-borne aircraft power-assisted catapult launcher, including：Electric four-wheel vehicle 1, power-assisted jet engine 2, the first water conservancy diversion
Plate 3, the second deflector 4, push rod 5, aircraft 6, aircraft jet engine 7, aircraft plumbing bar 8, wherein, above electric four-wheel vehicle 1
Fixed power-assisted jet engine 2, is the first deflector 3 before power-assisted jet engine 2, behind power-assisted jet engine 2
It is the second deflector 4, electric four-wheel vehicle 1 above fixes push rod 5, and push rod front portion is fixed with wheel, and the front end of push rod 5 heads on aircraft and hangs down
Bar 8, promotes airplane motion；The afterbody of aircraft 6 is aircraft jet engine 7；Fuel tank is provided with above electric four-wheel vehicle 1.
Power-assisted jet engine 2 is first started during starting, restarts aircraft jet engine 7.When aircraft takes off soon, it is shut off
Power-assisted jet engine, starting electric four-wheel vehicle 1 makes catapult-launching gear return to original place, waits catapult-assisted take-off next time.
The catapult launcher need to use more powerful engine, more powerful engine is produced in a short time and is stranded
It is difficult big, but can be used in parallel with even three, two, the engine with same model on aircraft, although fuel consumption is big, but the time
Very short, the device is repeatable to be utilized, and operating cost is low, and manufacture difficulty is also low, and the time for having one month can just make model machine, enter
Row experiment, also without what risk in experiment, can first test on the ground in Lu.
Control system is provided with the electric four-wheel vehicle, can be by remote control control, this is being very simple technology.
This catapult launcher, body is known small, and reaction speed is fast, and operating cost is low, and emission is carbon dioxide and water, and
And, whole process has deflector Gen 2UU, and flame does not influence on deck, and degree of safety is high.
This catapult launcher, in addition to, the small-sized fight for other warships can be also made except on aircraft carrier
Machine or unmanned plane take off.
The electric four-wheel vehicle, or multiwheel vehicle, it would however also be possible to employ other power.
The electric four-wheel vehicle, or railcar.
Claims (5)
1. a kind of carrier-borne aircraft power-assisted catapult launcher, it is characterised in that：Including：Electric four-wheel vehicle (1) power-assisted jet engine
(2), the first deflector (3), the second deflector (4), push rod (5), aircraft (6), aircraft jet engine (7), aircraft plumbing bar
(8) power-assisted jet engine (2), wherein, is fixed above electric four-wheel vehicle (1), is before power-assisted jet engine (2)
One deflector (3), power-assisted jet engine (2) is followed by the second deflector (4), electric four-wheel vehicle (1) above fixed push rod
(5), push rod front portion is fixed with wheel, and push rod (5) front end heads on aircraft plumbing bar (8), promotes airplane motion；The afterbody of aircraft (6)
It is aircraft jet engine (7)；Electric four-wheel vehicle is provided with fuel tank above (1).
2. a kind of carrier-borne aircraft power-assisted catapult launcher according to claim 1, it is characterised in that：The push rod is multistage
Bar, multistage bar can be folded, so as to reduce volume.
3. a kind of carrier-borne aircraft power-assisted catapult launcher according to claim 1, it is characterised in that：The push rod (5) is
Hydraulically extensible bar.
4. a kind of carrier-borne aircraft power-assisted catapult launcher according to claim 1, it is characterised in that：First deflector (3)
Horizontal sextant angle is big, the second deflector (4) horizontal sextant angle is small.
5. a kind of carrier-borne aircraft power-assisted catapult launcher according to claim 1, it is characterised in that：The power-assisted jet hair
Twice of the power of motivation (2) more than aircraft jet engine (7) power.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710196349.0A CN106904290A (en) | 2017-03-20 | 2017-03-20 | A kind of carrier-borne aircraft power-assisted catapult launcher |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710196349.0A CN106904290A (en) | 2017-03-20 | 2017-03-20 | A kind of carrier-borne aircraft power-assisted catapult launcher |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106904290A true CN106904290A (en) | 2017-06-30 |
Family
ID=59195429
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710196349.0A Pending CN106904290A (en) | 2017-03-20 | 2017-03-20 | A kind of carrier-borne aircraft power-assisted catapult launcher |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106904290A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107444668A (en) * | 2017-08-02 | 2017-12-08 | 杨长云 | Air catapult |
| CN107813958A (en) * | 2017-10-13 | 2018-03-20 | 南京涵曦月自动化科技有限公司 | A kind of vehicle-mounted unmanned aerial vehicle control system and its control method |
| CN109229411A (en) * | 2017-07-11 | 2019-01-18 | 余华阳 | Vehicle type carrier-borne aircraft catapult launcher |
| CN113895644A (en) * | 2021-11-19 | 2022-01-07 | 中国航发沈阳发动机研究所 | High-temperature tail gas flow control device for take-off of airplane in front of flow deflector |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN200974500Y (en) * | 2006-11-02 | 2007-11-14 | 王人庆 | Vehicle-carrying airplane |
| CN101513936A (en) * | 2009-03-31 | 2009-08-26 | 王力丰 | Taking off device and taking off method for carrier-based aircraft |
| CN106218914A (en) * | 2016-09-22 | 2016-12-14 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Aircraft and railcar overlap-connected landing system and method |
-
2017
- 2017-03-20 CN CN201710196349.0A patent/CN106904290A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN200974500Y (en) * | 2006-11-02 | 2007-11-14 | 王人庆 | Vehicle-carrying airplane |
| CN101513936A (en) * | 2009-03-31 | 2009-08-26 | 王力丰 | Taking off device and taking off method for carrier-based aircraft |
| CN106218914A (en) * | 2016-09-22 | 2016-12-14 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Aircraft and railcar overlap-connected landing system and method |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109229411A (en) * | 2017-07-11 | 2019-01-18 | 余华阳 | Vehicle type carrier-borne aircraft catapult launcher |
| CN107444668A (en) * | 2017-08-02 | 2017-12-08 | 杨长云 | Air catapult |
| CN107444668B (en) * | 2017-08-02 | 2021-01-15 | 杨长云 | Air ejector |
| CN107813958A (en) * | 2017-10-13 | 2018-03-20 | 南京涵曦月自动化科技有限公司 | A kind of vehicle-mounted unmanned aerial vehicle control system and its control method |
| CN107813958B (en) * | 2017-10-13 | 2019-08-02 | 南京涵曦月自动化科技有限公司 | A kind of vehicle-mounted unmanned aerial vehicle control system and its control method |
| CN113895644A (en) * | 2021-11-19 | 2022-01-07 | 中国航发沈阳发动机研究所 | High-temperature tail gas flow control device for take-off of airplane in front of flow deflector |
| CN113895644B (en) * | 2021-11-19 | 2023-11-28 | 中国航发沈阳发动机研究所 | High-temperature tail gas flow control device for aircraft taking off in front of flow deflector |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170630 |