CN201882250U - Fuel gas catapult - Google Patents
Fuel gas catapult Download PDFInfo
- Publication number
- CN201882250U CN201882250U CN2010202911849U CN201020291184U CN201882250U CN 201882250 U CN201882250 U CN 201882250U CN 2010202911849 U CN2010202911849 U CN 2010202911849U CN 201020291184 U CN201020291184 U CN 201020291184U CN 201882250 U CN201882250 U CN 201882250U
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- CN
- China
- Prior art keywords
- piston
- cylinder
- chamber
- slide block
- bolt
- Prior art date
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Abstract
The utility model discloses a fuel gas catapult which comprises an accelerator, a decelerator and a return device. The accelerator consists of an explosion chamber, pulleys, a hollow fixed link, a sealing washer, a bolt, a cylinder, a piston, a piston ring, a steel rope, a guide ring, a slide block and a towing link, wherein the pulleys are arranged at two ends of the hollow fixed link which is arranged in the explosion chamber; the sealing washer is arranged between the explosion chamber and the cylinder and fixed by the bolt; the piston is arranged in the cylinder; the piston ring is sheathed on the piston; one end of the steel rope is fixed on the piston and the other end is wound through the pulleys and extends out from the hollow fixed link of the explosion chamber so as to be connected with the slide block; the slide block is arranged on the guide ring which is ring-shaped; and the slide block is also connected with the towing link. The decelerator consists of a deceleration chamber, a power supply, a coil and a conductive track, wherein two ends of the deceleration chamber are opened; air vents are distributed in the deceleration chamber; one end of the deceleration chamber is fixed with the other end of the cylinder through the bolt; the diameter of the deceleration chamber is greater than the diameter of the cylinder so that the air can be exhausted conveniently; and the coil and the conductive track are fixed in the deceleration chamber. The return device consists of a motor. As a result, the fuel gas catapult is formed. The fuel gas catapult of the utility model has the advantages of being simple in manufacturing process, light in weight, economical and practical and can be widely equipped in airports or on aircraft carriers.
Description
Technical field
The invention belongs to the combustion gas ejector, more particularly belong to the ejector that constitutes by acceleration device, speed reduction gearing and return mechanism.
Background technology
At present, need more than 2000 meter long runway when taking off, thereby make the construction on airport need tract, therefore aircraft can't be necessary to be equipped with ejector on airport and aircraft carrier from aircraft carrier by self power running take off.The manufacturing process complexity of existing various ejectors such as steam catapult, and need to be equipped with large-sized boiler; The cost of electromagnetic launch device is high, manufacturing process complexity, and quality is very big, meet requirements well.
Summary of the invention
Purpose of the present invention overcomes the deficiencies in the prior art exactly, provides a kind of manufacturing process fairly simple, and economical and practical ejector.
The objective of the invention is to be achieved through the following technical solutions.
The combustion gas ejector comprises acceleration device, speed reduction gearing and return mechanism.Acceleration device is made up of explosion chamber, pulley, hollow fixed link, tightening seal washer, bolt, cylinder, piston, piston ring, cable wire, guide ring, slide block, haulage rod.Pulley is contained in the two ends of hollow fixed link, hollow fixed link is contained in explosion chamber, fill up upper sealing washer between explosion chamber and cylinder, and good with bolt, piston is contained in the cylinder, and piston ring set is on piston, one end of cable wire is fixed on the piston, the other end is walked around pulley, stretches out from the hollow fixed link of explosion chamber, links to each other with slide block.Slide block is contained on the guide ring, and guide ring is annular.Slide block links to each other with haulage rod again.When explosive after explosion chamber blast, the high pressure gas of generation promote piston and advance at utmost speed in cylinder, cylinder by cable wire pulling slide block on the guide ring towards with the cylinder opposite sense on advance at utmost speed so that reduce the length of ejector.Slide block advances at utmost speed by haulage rod pulling aircraft again, makes aircraft obtain very big acceleration/accel, just can take off in short range.Speed reduction gearing is made up of reduction chamber, power supply, coil, strip conductor.The both ends open of reduction chamber is covered with deflation hole, and an end is fixed together by the other end of bolt and cylinder, and the diameter of reduction chamber is bigger than the diameter of cylinder, so that gas purging, coil and strip conductor are fixed in the reduction chamber.After taking off, slide block separates with haulage rod, slide block is because inertia, move along reversing sense after turning on guide ring, meanwhile, piston enters reduction chamber, piston and strip conductor, power supply are formed C/LOOP, the magnetic induction line that the cutting hot-wire coil produces produces huge resistance, and piston is stopped in reduction chamber fast.Return mechanism is made up of electrical motor, and after piston stopped, electrical motor pulling slide block was to original position, and piston is also moved to original position by cable wire simultaneously, prepares launching next time.
Advantage of the present invention is that manufacturing process is simple, and quality is light, and economical and practical.Can extensively be provided on airport or the aircraft carrier.
Description of drawings
Fig. 1 is the structural representation of combustion gas ejector of the present invention;
Fig. 2 is the explosion chamber structural representation;
Fig. 3 is a structural representation of air cylinder;
Fig. 4 is the speed reduction gearing structural representation.
Among the figure 1, explosion chamber; 2, cylinder; 3, reduction chamber; 4, pulley; 5, hollow fixed link; 6, cable wire; 7, guide ring; 8, slide block; 9, haulage rod; 10, piston; 11, piston ring; 12, coil; 13, strip conductor.
The specific embodiment
The invention will be further described below in conjunction with accompanying drawing.The combustion gas ejector comprises acceleration device, speed reduction gearing and return mechanism.Acceleration device is made up of explosion chamber, pulley, hollow fixed link, tightening seal washer, bolt, cylinder, piston, piston ring, cable wire, guide ring, slide block, haulage rod.Pulley is contained in the two ends of hollow fixed link, hollow fixed link is contained in explosion chamber, fill up upper sealing washer between explosion chamber and cylinder, and good with bolt, piston is contained in the cylinder, and piston ring set is on piston, one end of cable wire is fixed on the piston, the other end is walked around pulley, stretches out from the hollow fixed link of explosion chamber, links to each other with slide block.Slide block is contained on the guide ring, and guide ring is annular.Slide block links to each other with haulage rod again.Speed reduction gearing is made up of reduction chamber, power supply, coil, strip conductor.The both ends open of reduction chamber is covered with deflation hole, and an end is fixed together by the other end of bolt and cylinder, and the diameter of reduction chamber is bigger than the diameter of cylinder, so that gas purging, coil and strip conductor are fixed in the reduction chamber.Return mechanism is made up of electrical motor.Like this, just formed the combustion gas ejector.
Claims (2)
1. combustion gas ejector, it is characterized in that comprising acceleration device, speed reduction gearing and return mechanism, acceleration device is by explosion chamber, pulley, hollow fixed link, tightening seal washer, bolt, cylinder, piston, piston ring, cable wire, guide ring, slide block, haulage rod is formed, pulley is contained in the two ends of hollow fixed link, hollow fixed link is contained in explosion chamber, fill up upper sealing washer between explosion chamber and cylinder, and it is good with bolt, piston is contained in the cylinder, and piston ring set is on piston, and an end of cable wire is fixed on the piston, the other end is walked around pulley, stretch out from the hollow fixed link of explosion chamber, link to each other with slide block, slide block links to each other with haulage rod again, speed reduction gearing is by reduction chamber, power supply, coil, strip conductor is formed, the both ends open of reduction chamber is covered with deflation hole, and an end is fixed together by the other end of bolt and cylinder, the diameter of reduction chamber is bigger than the diameter of cylinder, so that gas purging, coil and strip conductor are fixed in the reduction chamber, and return mechanism is made up of electrical motor.
2. the described combustion gas ejector of claim 1 is characterized in that also comprising that guide ring is annular, and the sense of motion of slide block on guide ring is opposite with the sense of motion of cylinder, can reduce the length of ejector like this.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010202911849U CN201882250U (en) | 2010-08-04 | 2010-08-04 | Fuel gas catapult |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010202911849U CN201882250U (en) | 2010-08-04 | 2010-08-04 | Fuel gas catapult |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201882250U true CN201882250U (en) | 2011-06-29 |
Family
ID=44179789
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010202911849U Expired - Fee Related CN201882250U (en) | 2010-08-04 | 2010-08-04 | Fuel gas catapult |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201882250U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102951298A (en) * | 2012-11-28 | 2013-03-06 | 许守平 | Combustion-supporting type shipboard aircraft ejector |
| CN103057720A (en) * | 2012-06-04 | 2013-04-24 | 叶锋 | Gunpowder catapult |
| CN103183132A (en) * | 2011-12-29 | 2013-07-03 | 任明琪 | Power source unit body for ejecting, aircraft carrier gas and steam ejector and ejecting method |
| CN103604581A (en) * | 2013-11-15 | 2014-02-26 | 北京理工大学 | A gas ejection test apparatus |
| CN106081151A (en) * | 2016-08-16 | 2016-11-09 | 张跃亮 | A kind of gunpowder formula carrier-based aircraft catapult-launching gear |
| CN106742026A (en) * | 2017-01-10 | 2017-05-31 | 胡达广 | Intelligent aircraft catapult |
-
2010
- 2010-08-04 CN CN2010202911849U patent/CN201882250U/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103183132A (en) * | 2011-12-29 | 2013-07-03 | 任明琪 | Power source unit body for ejecting, aircraft carrier gas and steam ejector and ejecting method |
| WO2013097295A1 (en) * | 2011-12-29 | 2013-07-04 | Ren Mingqi | Power source unit body for catapulting, and aircraft carrier gas-steam catapult and catapulting method |
| CN103183132B (en) * | 2011-12-29 | 2015-09-09 | 任明琪 | Launch by power source unit body and aircraft carrier combustion and steam ejector and catapult technique |
| CN103057720A (en) * | 2012-06-04 | 2013-04-24 | 叶锋 | Gunpowder catapult |
| CN102951298A (en) * | 2012-11-28 | 2013-03-06 | 许守平 | Combustion-supporting type shipboard aircraft ejector |
| CN103604581A (en) * | 2013-11-15 | 2014-02-26 | 北京理工大学 | A gas ejection test apparatus |
| CN103604581B (en) * | 2013-11-15 | 2016-02-10 | 北京理工大学 | A kind of gas ejection test device |
| CN106081151A (en) * | 2016-08-16 | 2016-11-09 | 张跃亮 | A kind of gunpowder formula carrier-based aircraft catapult-launching gear |
| CN106742026A (en) * | 2017-01-10 | 2017-05-31 | 胡达广 | Intelligent aircraft catapult |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110629 Termination date: 20120804 |