CN102849222B - Block and launch energy-conservation dual-purpose apparatus - Google Patents
Block and launch energy-conservation dual-purpose apparatus Download PDFInfo
- Publication number
- CN102849222B CN102849222B CN201210393914.XA CN201210393914A CN102849222B CN 102849222 B CN102849222 B CN 102849222B CN 201210393914 A CN201210393914 A CN 201210393914A CN 102849222 B CN102849222 B CN 102849222B
- Authority
- CN
- China
- Prior art keywords
- spring
- aircraft
- gear
- bar
- energy
- 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.)
- Expired - Fee Related
Links
Abstract
The present invention relates to a kind of inertia impulsive force by landing aircraft aircraft carrier and be converted into the new kinetic energy blocking cataplane, and use the inertial impact force Compress Spring stored energy of aircraft landing and block aircraft, the more energy-conservation dual-purpose apparatus of machine automatization that the energy discharging spring store by instruction takes off with cataplane.With simple telescopic spring principle complete replacement in the world military Strong state monopolize the ejector high-end technology that nonnegotiable check cable and cataplane take off.And volume is little, structure is simple, Shi Shou Ming Long, and the operating cost of more than 50% saved by aircraft carrier.Be applicable to civil airport large-scale popularization, the soil of more than 50% and the operating cost of more than 30% are saved in airport.When blocking aircraft with short range runway, aircraft only can fly in very short distance such as 20 meters simultaneously.
Description
Technical field
The inertia impulsive force of landing aircraft aircraft carrier is converted into the elastic potential energy of blocking cataplane by the present invention, and relate to and a kind ofly use the inertia impulsive force Compress Spring stored energy of aircraft that aircraft carrier lands and block only aircraft, then discharge the energy-conservation dual-purpose apparatus that the energy that stores in spring takes off in order to cataplane by instruction.
Background technology
More advanced on existing aircraft carrier is use check cable to block aircraft, uses hydraulic catapult, steam ejection, electromagnetic launch to take off in addition.Technical sophistication, volume are large, the life-span is short, and operating cost is high.
In the summary of the invention of my 201210013485.9 patents of invention, short range aircraft rotates runway high-speed motion only aircraft, and power-assisted departing aeroplane, shortens more than 10 times of Fei machine Pao Dao Long degree.
Summary of the invention
The object of the invention is to complete by simple telescopic spring principle the high-end technology replacing check cable system and cataplane and take off.And use the inertial impact force Compress Spring stored energy of aircraft landing and block only aircraft, then discharge the energy-conservation dual-purpose apparatus that the energy that stores in spring takes off in order to cataplane by instruction.And volume is little, lightweight, structure is simple, Shi Shou Ming Long, and operation cost saves more than 50%.
The object of the present invention is achieved like this: by the enormous impact power of aircraft landing, and Compress Spring (or hydraulic pressure, vapour pressure) indentation, gets up energy storage.Decontrol the spring (or decontroling hydraulic pressure, the vapour pressure of compression) of compression when taking off, the very quick quick extension of spring is ejected, and discharge the energy of storage, cataplane takes off.
Beneficial effect of the present invention is also, electric energy that need not be powerful, becomes Strong Great inertia impulsive force during discarded aircraft landing, is converted into new energy.
Compared with prior art, beneficial effect of the present invention is also: the technology of complicating is simple technique, and the operating cost of more than 50% saved by aircraft carrier.Be applicable to civil airport large-scale popularization, the soil of more than 50% and the operating cost of more than 30% are saved in airport.
Accompanying drawing explanation
Fig. 1 looks schematic diagram under energy accumulation spring of the present invention.Histogram is in the left and right sides of runway centerline.
Fig. 2 is the supporting small distance movement runway schematic front view of the present invention.
Fig. 3 is the schematic side view of Fig. 2 A-A section of the present invention, and the motion structure figure of bearing wheed 17, with hatching Sheng Qu Long degree.
Fig. 4 is the schematic side view of Fig. 2 B-B section of the present invention.And the motion structure figure of driving gear 24, with hatching Sheng Qu Long degree.
Fig. 5 looks schematic diagram under bar in spring of the present invention.With cylindrical section technique of painting Sheng Qu Long degree.
The left figure of Fig. 6 is the front-view schematic diagram of pliers frame of the present invention.Right figure is the left view of frame.
Fig. 7 is the front-view schematic diagram of interior bar fixed cover of the present invention.
Fig. 8 is the front-view schematic diagram of pliers switch of the present invention.Move for stopping bar 2 in spring, and open the circle group shelves 38 of pliers 11.Pliers Long degree is saved with hatching.
Fig. 9 is that inverted the blocking of Fig. 1 energy accumulation spring of the present invention cable-styledly only flies schematic diagram.
To be the present invention only fly and the energy-conservation schematic diagram of catapult-assisted take-off the dual-purpose configuration of energy accumulation spring Fig. 1 and blocking Figure 10.
In accompanying drawing: 1 clashes into wheel, bar in 2 springs, 3 compressing springs, compressing spring in 4, 5 large compressing springs, 6 press spring bases, 7 sliding wheels, 8 stay cords, 9 winchs, 10 hooks, 11 pliers, 12 motors, 13 wheels, 14 runway plates, 15 roller axle supports, 16 roller axles, 17 bearing wheeds, 18 high-speed wheels, 19 power wheels, 20 times rails, 21 axis of a movable block, 22 electrical motors, 23 motor cabinets, 24 driving gears, 25 loose-leaves, bearing rail on 26, 27 plate teeth, 28 spring base paths, the prominent gear of 29 circle, 30 pliers frames, 31 close pincers spring, bar fixed cover in 32, 33 rollers, 34 gear rails, 36 pincers moving axis, 37 open pincers rope, 38 circle group shelves, 39 pliers handles, 40 sliding hooks, 41 check cables.42 aircrafts, 43 directed contracting gears, 44,45 aircraft trailing wheels, 46 aircraft nose wheels, 47 runways, 48 runway centerlines.
Detailed description of the invention:
Fig. 1 describes the energy accumulation spring of histogram in the runway centerline left and right sides.1 is clash into wheel, and there is sliding wheel 7 front portion, the power of rotating forward when clashing into by means of aircraft trailing wheel and rotating, and front portion to be connected in spring with on spring 3 on bar 2, and rotor wheel and inhibiting device are arranged at bottom, in order to along desired location forward slip Compress Spring.3 is compressing springs, and spring thickness is directly through little, and pressure is little, for aircraft buffer deceleration; 4 is middle compressing springs, and spring thickness is directly through comparatively large, and pressure is comparatively large, blocks aircraft forward slip; 5 is large compressing springs, and spring thickness is straight, and through large, pressure is especially big, continues to block aircraft forward slip, and more compressed pressure is larger, and power of blocking is larger, and to exceeding and the airplane inertial impulsive force that runs out to pressure, life aircraft only flies.6 is press spring bases, the end of fixing compressing spring 5.In spring, bar 2 is through press spring base center hole.8 is drag-lines, and be connected on winch 9 and hook 10,11 is pliers.
The supporting short range runway keystone configuration that Fig. 2 describes, connect runway plate 14 by some pieces of loose-leaves 25 and form short range runway, runway plate 14 upper flat, plate tooth 27 is arranged at bottom, runway plate 14 both sides are bearing wheed 17, runway plate 14 goes out driving gear 24 and drives, and electrical motor 22 drives driving gear 24 to rotate, and the plate tooth 27 of driving gear 24 and runway plate 14 is meshing, drive the reverse high speed rotating of short range runway, aircraft resembles people and flies in original place on a treadmill, consumes airplane inertial impulse force, blocks aircraft.
In Fig. 3,13 is wheels, is connected to the bottom of runway plate 14, bearing wheed 17, on motion on bearing rail 26.Power wheel 19, lower rail 20 moves.
Plate tooth 27 in Fig. 4, is connected to the bottom of runway plate 14, and driving gear 24 is meshing, and driving gear 24 drives runway plate 14 to rotate.
The column structure figure of bar 2 in the spring that Fig. 5 describes, be made up of spring base path 28 and umbrella shape cylinder, the large end of umbrella shape cylinder is the prominent gear 29 of circle, in spring, bar 2 one end is fixed on interior bar fixed cover 32, one end is fixed on clashes on wheel 1, in spring, bar 2 is through the big hole of press spring base 6, and in spring, bar 2 is stretched along with the contracting of compressing spring 3.4.5 and seesaws.And pull interior bar fixed cover 32 to move simultaneously.
Pliers frame 30 in Fig. 6, for placing pliers 11.The connection up and down of frame relevant pincers spring 31, closes pincers spring 31 and stretches Zhang and open and compress circle group shelves 38, the prominent gear 29 of circle block not by.
What Fig. 7 described is bar fixed cover in 32, and its inner circle is used for the end of bar 2 in retainer spring, and left and right roller 33 is arranged at bottom, for moving on rail.Gear rail 34 is stuck on rail, ensures the honest motion of bar 2 in spring.
In Fig. 8 36 is pincers moving axis, and 37 are out pincers rope, and one end connects pliers on 39, on one end connection clamp moving axis 36, stretches when pass pincers spring 31 is flat, and compress the spring base path 28 that circle group shelves 38 block bar 2 in spring, round prominent gear 29 blocks, and in spring, bar 2 can not move.
Drive pincers motor 12 to start, pincers moving axis 36 rotates, and opens pincers rope 37 and twists on pincers moving axis 36, pull pliers 39 to adduction, and back-pressure closes the indentation of pincers spring 31, and circle group shelves 38 Zhang opens, and in spring, bar 2 moves through.
In Fig. 9 40 is the sliding hooks on aircraft, is provided with rolling thing as bearing etc. in hook, and when the sliding hook 40 of aircraft 42 does not hang over check cable 41 center, sliding hook 40 automatic rolling is adjusted to the center of check cable 41.The inertia impulsive force of aircraft 42 pulls check cable 41, and check cable 41 is articulated on the hook 10 of bar 2 in spring, and in spring, bar 2 pulls directed contracting gear 43, and directed contracting gear 43 presses compressing spring 3.4,5. indentation, blocks only aircraft.
In Figure 10 45 is aircraft trailing wheels, and 46 is aircraft nose wheels, and 47 is airstrips, 48 is airstrip line of centerss, the compressing spring 3.4.5 of energy accumulation spring is configured in the side of airstrip line of centers respectively, except shock wheel 1 and sliding wheel 7 reveal that runway is flat and except top, all the other facilities can be hidden in runway bottom.The aircraft trailing wheel 45 of land connect melt to shock wheel 1 right, compressing spring 3.4.5 indentation, blocks aircraft.Short range runway 14 simultaneously reversing sense motion, blocks aircraft, jointly only aircraft.
When taking off, short range runway 14 forward moves and accelerates aircraft, drives pincers motor 12 simultaneously and starts, and circle group shelves 38 Zhang opens, and compressing spring 3.4.5 stretches suddenly, and cataplane takes off.
The present invention is achieved in that
As shown in Figure 10 Fig. 1, when the aircraft trailing wheel 45 of land connects and encounters shock wheel 1, clash into wheel 1 and press compressing spring 3.4.5 indentation, in spring, bar 2 drives interior bar fixed cover 32 to travel forward, and compressing spring 3 pressure is little, to slow down aircraft impulse force, when compressing spring 3 indentation props up compressing spring 4, the pressure of compressing spring 4 is comparatively large, and aircraft is compression more, and the pressure of spring is larger.When compressing spring 4 indentation props up compressing spring 5, the pressure of compressing spring 5 is larger, the inertia impulsive force that then aircraft will be larger just can change into the pressure of spring, and airplane inertial impulse force is more to preshoot, and the pressure of conversion is larger, when airplane inertial impulse force exhausts, the prominent gear 29 of circle blocks bar 2 in spring, closes pincers spring 31 and naturally stretches Zhang and open and compress circle group shelves 38, circle dash forward gear 29 not by, in spring, bar 2 stop motion, is all converted into the pressure reservoir of spring in the spring by the inertia impulsive force of aircraft.Aircraft is parked in original place.
When short range runway 14 coordinates compressing spring 3.4.5 to block aircraft, short range runway 14 also moves at the reversing sense at a high speed to airplane wheel, the short range runway 14 that aircraft moves at reversing sense consumes airplane inertial impulse force, blocks aircraft.When compressing spring 3.4.5 and short range runway 14 block aircraft simultaneously, aircraft only can fly in very short distance such as 20 meters.
When aircraft needs to take off, turning proceeds on short range runway 14 or on runway 47, two trailing wheels are near shock wheel 1, drive pincers motor 12 to start, circle group shelves 38 Zhang opens, and the compressing spring 3.4.5 of indentation stretches suddenly, discharges the pressure energy of spring, shock wheel 1, clashes into while wheel 1 launches away and is gone out by airplane catapult.
When short range runway 14 share, along the accelerated service of aircraft direction, power-assisted compressing spring 3.4.5, impelling is taken off.
The energy accumulation spring of short range runway 14 and Fig. 1, can separate single use separately, also can share.The length 10-20 rice of energy accumulation spring, can optionally design length.
By the energy accumulation spring composition group of Fig. 1, inversion is configured to block cable-styledly blocks aircraft, as shown in Figure 9, the sliding hook 40 of aircraft hooks check cable 41, check cable 41 pulls bar 2 in spring, directed contracting gear 43, directed contracting gear 43 presses compressing spring 3.4.5 indentation, and the pressure of compressing spring 3.4.5 runs out the inertia impulsive force of aircraft.Aircraft only flies.
When not having stored energy to need cataplane to take off, the compressing spring 3.4.5 state of nature of the energy accumulation spring in Fig. 1 is stretched Zhang and is opened.Detailed description of the invention starts winch 9, stay cord 8 pulls bar 2 in hook 10, spring, clashes into wheel 1 indentation and press compressing spring 3.4.5 to be retracted into the pressure energy of needs, winch 9 stops starting, the prominent gear 29 of circle, circle group shelves 38 stop bar 2 in spring, orientation contracting gear 43 moves, and store the pressure energy of compressing spring 3.4.5 indentation.
Drive pincers motor 12 to start, circle group shelves 38 Zhang opens, and the compressing spring 3.4.5 of indentation stretches suddenly, discharges the energy of storage, shock wheel 1, clashes into while wheel 1 launches away and is gone out by airplane catapult.
Claims (1)
1. one kind utilizes the inertial impact force Compress Spring of landing aircraft aircraft carrier in order to block aircraft, and inertial impact force is changed into elastic potential energy storage, the elastic potential energy that release stores launches energy-conservation dual-purpose apparatus in order to blocking of taking off of cataplane, it comprises sliding hook (40), check cable (41), spring, clash into wheel (1), bar (2) in spring, press spring base (6), interior bar fixed cover (32), pliers (11), close pincers spring (31), pliers frame (30), circle group gear (38), the prominent gear (29) of circle, directed contracting gear (43), motor (12), wherein spring comprises compressing spring (3), middle compressing spring (4) and large compressing spring (5), in spring, bar (2) is located among compressing spring (3), middle compressing spring (4) and large compressing spring (5), one end is taken turns (1) with shock and is connected, the other end is fixed on interior bar fixed cover (32), through press spring base (6) center hole, in spring, bar (2) seesaws along with the flexible of spring, pliers frame (30) is for placing pliers (11), the connection up and down of pliers frame (30) relevant pincers spring (31), close pincers spring (31) stretch out compress circle group gear (38), the prominent gear (29) of circle not by, aircraft landing, sliding hook (40) hooks check cable (41), check cable (41) pulls bar in spring (2) and directed contracting gear (43), (43) the Compress Spring indentation of directed contracting gear, the pressure of spring runs out the inertia impulsive force of aircraft, and aircraft only flies, open motor (12), pincers spring (31) are closed in compression, circle group gear (38) opens, in round dash forward gear (29) and spring, bar (2) moves through, spring stretches, discharge the elasticity of compression potential energy of spring, shock wheel (1), clash into wheel (1) and airplane catapult is taken off.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210393914.XA CN102849222B (en) | 2012-10-17 | 2012-10-17 | Block and launch energy-conservation dual-purpose apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210393914.XA CN102849222B (en) | 2012-10-17 | 2012-10-17 | Block and launch energy-conservation dual-purpose apparatus |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102849222A CN102849222A (en) | 2013-01-02 |
| CN102849222B true CN102849222B (en) | 2016-01-27 |
Family
ID=47396294
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210393914.XA Expired - Fee Related CN102849222B (en) | 2012-10-17 | 2012-10-17 | Block and launch energy-conservation dual-purpose apparatus |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102849222B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104229154B (en) * | 2014-06-09 | 2016-09-28 | 罗晓晖 | Lifting-hook formula hangs pool air bag aircraft |
| CN104691775B (en) * | 2015-03-17 | 2018-02-06 | 卢军 | External regeneration brake system |
| CN106553763A (en) * | 2015-09-30 | 2017-04-05 | 张承普 | Telescopic arrester wires |
| CN109866937A (en) * | 2017-12-02 | 2019-06-11 | 何韧 | A kind of method and device helping aircraft lands deceleration or the reinforcement that takes off |
| CN110539893A (en) * | 2019-09-07 | 2019-12-06 | 何韧 | method and device for helping landing deceleration or takeoff augmentation of aircraft |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3414333A (en) * | 1964-01-29 | 1968-12-03 | Grenobloise Etude Appl | Vehicle braking systems |
| CN202115706U (en) * | 2010-12-20 | 2012-01-18 | 西安韦德沃德航空科技有限公司 | Unmanned plane short take-off system |
| CN102358430A (en) * | 2011-07-27 | 2012-02-22 | 南京航空航天大学 | Ship-borne aircraft capturing and arresting device |
| CN102582842A (en) * | 2011-01-07 | 2012-07-18 | 上海市南洋模范中学 | Buffer anchoring rope |
| CN202345921U (en) * | 2011-10-13 | 2012-07-25 | 王力丰 | Shipboard aircraft lifting system for aircraft carrier |
| CN102673798A (en) * | 2009-08-18 | 2012-09-19 | 胡宣哲 | Cold ejection energy recovery device |
| CN102700721A (en) * | 2012-05-04 | 2012-10-03 | 银世德 | Combined catapult for aircraft carrier |
-
2012
- 2012-10-17 CN CN201210393914.XA patent/CN102849222B/en not_active Expired - Fee Related
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3414333A (en) * | 1964-01-29 | 1968-12-03 | Grenobloise Etude Appl | Vehicle braking systems |
| CN102673798A (en) * | 2009-08-18 | 2012-09-19 | 胡宣哲 | Cold ejection energy recovery device |
| CN202115706U (en) * | 2010-12-20 | 2012-01-18 | 西安韦德沃德航空科技有限公司 | Unmanned plane short take-off system |
| CN102582842A (en) * | 2011-01-07 | 2012-07-18 | 上海市南洋模范中学 | Buffer anchoring rope |
| CN102358430A (en) * | 2011-07-27 | 2012-02-22 | 南京航空航天大学 | Ship-borne aircraft capturing and arresting device |
| CN202345921U (en) * | 2011-10-13 | 2012-07-25 | 王力丰 | Shipboard aircraft lifting system for aircraft carrier |
| CN102700721A (en) * | 2012-05-04 | 2012-10-03 | 银世德 | Combined catapult for aircraft carrier |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102849222A (en) | 2013-01-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102849222B (en) | Block and launch energy-conservation dual-purpose apparatus | |
| CN103964200B (en) | A kind of automatic charging device of cubic hinge press | |
| CN203781328U (en) | Automatic discharging device in steel tube cutting machine | |
| CN103482067B (en) | A kind of Pneumatic type built-in load delivery device | |
| CN103693206A (en) | Autonomous circular launching and landing device for unmanned aerial vehicle | |
| CN203064205U (en) | Unmanned aerial vehicle ejector | |
| CN203832749U (en) | Aircraft landing gear | |
| CN102814810A (en) | Rescue device | |
| CN108001701A (en) | Movable unmanned helicopter catapult-launching gear | |
| CN110615114A (en) | Method and device for assisting landing and landing of airplane | |
| CN108116691B (en) | Hydraulic ejection method of unmanned aerial vehicle | |
| CN202180933U (en) | Aircraft short-distance take-off assisting device | |
| CN218227471U (en) | Insulating cylinder stripper | |
| CN103466099A (en) | High-speed ejector rack of unmanned measuring plane | |
| CN204085312U (en) | A kind of automatic gun wiping device | |
| CN110145661A (en) | A kind of electrom echanical power cabinet equipment mounting seat | |
| CN106080679B (en) | A kind of hand-push apparatus pulled with front | |
| RU2018113205A (en) | PLATFORM FOR TAKEOFF AND LANDING OF THE PLANE, SELF-MOVING ON RAILS | |
| CN108082523A (en) | A kind of method of unmanned plane transmitting | |
| CN103466098B (en) | High-speed ejector trolley of unmanned measuring plane | |
| CN203514888U (en) | Longitudinal moving mechanism of lifting longitudinal moving type stereoscopic parking equipment | |
| CN216424776U (en) | Launcher for unmanned aerial vehicle detection | |
| RU2617096C1 (en) | Launcher to launch unmanned aircraft | |
| CN203450378U (en) | High-speed ejection trolley of unmanned measuring machine | |
| CN103057717A (en) | Modular deck with power rods |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CB03 | Change of inventor or designer information |
Inventor after: Lu Lina Inventor before: Luo Guopei |
|
| CB03 | Change of inventor or designer information | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20171025 Address after: The two District Road East Street Yongming new embroidered 065400 area in Langfang city of Hebei province Xianghe county 1 Building 3 unit 312 room Patentee after: Lu Lina Address before: A street in Qingyang District of Chengdu City, Sichuan Province, No. 38 610015 Patentee before: Luo Guopei |
|
| TR01 | Transfer of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160127 Termination date: 20171017 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |