CN102774506A - Airplane forced landing trolley - Google Patents
Airplane forced landing trolley Download PDFInfo
- Publication number
- CN102774506A CN102774506A CN2012102206531A CN201210220653A CN102774506A CN 102774506 A CN102774506 A CN 102774506A CN 2012102206531 A CN2012102206531 A CN 2012102206531A CN 201210220653 A CN201210220653 A CN 201210220653A CN 102774506 A CN102774506 A CN 102774506A
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- flute profile
- blister cavities
- landing platform
- landing
- vehicle frame
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Abstract
The invention relates to an airplane forced landing auxiliary device, particularly relates to an air airplane forced landing trolley and effectively solves the problem that no device is capable of preventing fuselages from being damaged and fired when airplanes forcedly land at present. The air airplane forced landing trolley comprises a groove-shaped frame and a groove-shaped cavity landing platform, wherein the outer bottom surface of the groove-shaped cavity landing platform and the inner bottom surface of the groove-shaped frame are fixed, a plurality of wheels are arranged on the outer bottom surface of the groove-shaped frame, cavities are arranged in the groove-shaped cavity landing platform, a deceleration strip is axially arranged on the inner bottom surface of the groove-shaped cavity landing platform, a plurality of draining holes which are communicated with the cavities are axially arranged on the inner side surface of the groove-shaped cavity landing platform, and sealing plugs are plugged in the draining holes. The airplane forced landing auxiliary device is applicable to airplane forced landing.
Description
Technical field
The present invention relates to the forced landing auxiliary device, specifically is a kind of forced landing car.
Background technology
During forced landing, bump and violent friction can take place with airfield runway in fuselage.Wherein, bump can cause fuselage to damage and blast on fire the life security that seriously jeopardizes the passenger with violent friction.At present, when forced landing, airport personnel can be sprayed significant foam usually on airfield runway, to prevent fuselage blast on fire takes place.Be merely able to play the fire extinguishing effect yet spray foam, and can't avoid fuselage to be damaged fully, thereby this method can not effectively ensure passenger's life security because of bump and violent friction.Based on this, be necessary to invent a kind of device that when forced landing, can prevent fuselage damage and blast on fire simultaneously.Yet do not have a kind of like this device at present.
Summary of the invention
The present invention a kind ofly can prevent simultaneously that fuselage from damaging and the problem of the device of blast on fire when the forced landing in order to solve still not have at present, and a kind of forced landing car is provided.
The present invention adopts following technical scheme to realize: the forced landing car comprises flute profile vehicle frame and flute profile blister cavities landing platform; The outer bottom of flute profile blister cavities landing platform and the inner bottom surface of flute profile vehicle frame are fixed; Several wheels are installed on the outer bottom of flute profile vehicle frame; Flute profile blister cavities landing platform inside is provided with blister cavities; The inner bottom surface of flute profile blister cavities landing platform is provided with deceleration strip vertically; The medial surface of flute profile blister cavities landing platform is provided with the drain gutter that several are communicated with blister cavities vertically, and all is plugged with sealing plug on each drain gutter; The curved perk that all makes progress of the front end of the front end of flute profile vehicle frame and flute profile blister cavities landing platform; The groove width of the groove width of flute profile vehicle frame and flute profile blister cavities landing platform all vertically by after diminish gradually forward.
During work, airport personnel is drawn the forced landing car to the predetermined forced landing runway of aircraft, and in blister cavities, stores full water, on drain gutter, seals plug then.During forced landing; Airframe impinges upon in the vallecular cavity of flute profile blister cavities landing platform towards the front lower place; And slide forward at the vallecular cavity of effect of inertia lower edge flute profile blister cavities landing platform forward, make the vallecular cavity full face contact of belly and flute profile blister cavities landing platform and coincideing each other.The curved perk that all makes progress of the front end of the front end of flute profile vehicle frame and flute profile blister cavities landing platform; The groove width of the groove width of flute profile vehicle frame and flute profile blister cavities landing platform all vertically by after diminish gradually forward; This structure make flute profile blister cavities landing platform to fuselage by after played the obvolvent effect forward, prevented that fuselage from going out the vallecular cavity of flute profile blister cavities landing platform under effect of inertia forward.Simultaneously, violent friction takes place in deceleration strip and fuselage, has prevented that equally fuselage from going out the vallecular cavity of flute profile blister cavities landing platform under effect of inertia forward.Under the combined action of cohesive force and friction force, fuselage drives flute profile blister cavities landing platform and slides fast to the forward position runway, and slides forward synchronously with the realization of flute profile blister cavities landing platform fast.During the fuselage landing; Crimp takes place in blister cavities under the downward effect of impact of fuselage; Water in the blister cavities back down sealing plug and be sprayed at fuselage and deceleration strip on, eliminated because of deceleration strip and the violent fricative high temperature of fuselage, prevented that fuselage Yin Wendu is too high and blast on fire taken place.Simultaneously; Along with the water in the blister cavities reduces gradually, blister cavities has formed damping buffering to the fuselage of downward bump, has not only effectively prevented thus to rebound after the fuselage landing; And avoided fuselage and runway that directly bump takes place, prevented that thoroughly fuselage is damaged because of bump.Airframe and flute profile blister cavities landing platform continue to slide forward after realizing synchronously on the runway, until natural parking, accomplish the safety forced landing of aircraft thus.Based on above process; Forced landing car of the present invention adopts brand new; Damage and blast on fire because of bump with violent friction fuselage takes place when thoroughly having prevented forced landing, and compare with the method for spraying foam, forced landing car of the present invention has not only more effectively ensured passenger's life security; And cost is cheaper, and is more convenient to operate.
Further, the outer bottom front portion of flute profile vehicle frame is equipped with the buffer protection capsule.During work, in the buffer protection capsule, store full water.When airframe and flute profile blister cavities landing platform slided forward synchronously, if there is obstacle in the place ahead, the buffer protection capsule can avoid airframe and the flute profile vehicle frame is direct and obstacle bumps against, and plays the effect of buffer protection thus.
Further, comprise that also bullet send boost installation; Said bullet send boost installation to comprise pushing assisted plate, compression spring and pile body; The front surface of pushing assisted plate contacts with the aft end face of flute profile vehicle frame; The back surface of pushing assisted plate is fixed through compression spring and pile body; Fast breakdown is installed on the compression spring to close.During work, pile body is fixed on the runway at flute profile blister cavities landing platform rear.Fuselage impinges upon the moment of the vallecular cavity of flute profile blister cavities landing platform; Fast breakdown closes opens (fast breakdown closes and can opened or opened through induction fuselage bump by the airport personnel remote control); Make compression spring unclamp; Pushing assisted plate promotes the flute profile vehicle frame forward under the effect of spring thrust, give the flute profile vehicle frame acceleration/accel.Under the effect of this acceleration/accel, flute profile blister cavities landing platform just can be as early as possible realizes synchronously with airframe, prevented that further fuselage from going out the vallecular cavity of flute profile blister cavities landing platform under the effect of inertia forward, and further guaranteed the safety of forced landing.
In addition, the remote control brake device is installed on the wheel.During work, when airframe and flute profile blister cavities landing platform after realizing synchronously on the runway, airport personnel can be through remote controller control remote control brake device, makes airframe and flute profile blister cavities landing platform brake deceleration.
The present invention is rational in infrastructure, design is ingenious, and efficiently solving does not still have a kind of problem that when forced landing, can prevent the device of fuselage damage and blast on fire simultaneously at present, is applicable to forced landing.
Description of drawings
Fig. 1 is a structural representation of the present invention.
Fig. 2 is the birds-eye view of Fig. 1.
Fig. 3 is the A-A cutaway view of Fig. 1.
Among the figure: 1-flute profile vehicle frame, 2-flute profile blister cavities landing platform, 3-wheel, 4-blister cavities, 5-deceleration strip, 6-drain gutter, 7-buffer protection capsule, 8-pushing assisted plate, 9-compression spring, 10-pile body.
The specific embodiment
The forced landing car comprises flute profile vehicle frame 1 and flute profile blister cavities landing platform 2; The outer bottom of flute profile blister cavities landing platform 2 and the inner bottom surface of flute profile vehicle frame 1 are fixed; Several wheels 3 are installed on the outer bottom of flute profile vehicle frame 1; Flute profile blister cavities landing platform 2 inside are provided with blister cavities 4; The inner bottom surface of flute profile blister cavities landing platform 2 is provided with deceleration strip 5 vertically; The medial surface of flute profile blister cavities landing platform 2 is provided with several drain gutters 6 that is communicated with blister cavities 4 vertically, and all is plugged with sealing plug on each drain gutter 6; The curved perk that all makes progress of the front end of the front end of flute profile vehicle frame 1 and flute profile blister cavities landing platform 2; The groove width of the groove width of flute profile vehicle frame 1 and flute profile blister cavities landing platform 2 all vertically by after diminish gradually forward;
The outer bottom front portion of flute profile vehicle frame 1 is equipped with buffer protection capsule 7;
Comprise that also bullet send boost installation; Said bullet send boost installation to comprise pushing assisted plate 8, compression spring 9 and pile body 10; The front surface of pushing assisted plate 8 contacts with the aft end face of flute profile vehicle frame 1; The back surface of pushing assisted plate 8 is fixing with pile body 10 through compression spring 9; Fast breakdown is installed on the compression spring 9 to close;
The remote control brake device is installed on the wheel 3;
During practical implementation, flute profile blister cavities landing platform can be an one, also can be mosaic.The length that the length of flute profile blister cavities landing platform can be a bit larger tham airframe.The rear portion of flute profile blister cavities landing platform can adopt the relative heavier material of deadweight to process, and the front portion of flute profile blister cavities landing platform can adopt the relative lighter material of deadweight to process, and its objective is to turn over before flute profile blister cavities landing platform takes place when preventing the fuselage landing.The rear portion of flute profile blister cavities landing platform can be provided with gentle incline, so that the vallecular cavity of flute profile blister cavities landing platform more fully contacts with airframe and coincide.The number of pile body and spring can be provided with a plurality of according to actual needs, helps strengthening the thrust of pushing assisted plate, gives flute profile vehicle frame higher acceleration.
Claims (5)
1. a forced landing car is characterized in that: comprise flute profile vehicle frame (1) and flute profile blister cavities landing platform (2); The inner bottom surface of the outer bottom of flute profile blister cavities landing platform (2) and flute profile vehicle frame (1) is fixed; Several wheels (3) are installed on the outer bottom of flute profile vehicle frame (1); Flute profile blister cavities landing platform (2) inside is provided with blister cavities (4); The inner bottom surface of flute profile blister cavities landing platform (2) is provided with deceleration strip (5) vertically; The medial surface of flute profile blister cavities landing platform (2) is provided with several drain gutters (6) that is communicated with blister cavities (4) vertically, and all is plugged with sealing plug on each drain gutter (6); The curved perk that all makes progress of the front end of the front end of flute profile vehicle frame (1) and flute profile blister cavities landing platform (2); The groove width of the groove width of flute profile vehicle frame (1) and flute profile blister cavities landing platform (2) all vertically by after diminish gradually forward.
2. forced landing car according to claim 1 is characterized in that: the outer bottom front portion of flute profile vehicle frame (1) is equipped with buffer protection capsule (7).
3. forced landing car according to claim 1 and 2 is characterized in that: comprise that also bullet send boost installation; Said bullet send boost installation to comprise pushing assisted plate (8), compression spring (9) and pile body (10); The front surface of pushing assisted plate (8) contacts with the aft end face of flute profile vehicle frame (1); The back surface of pushing assisted plate (8) is fixing through compression spring (9) and pile body (10); Fast breakdown is installed on the compression spring (9) to close.
4. forced landing car according to claim 1 and 2 is characterized in that: wheel is equipped with the remote control brake device on (3).
5. forced landing car according to claim 3 is characterized in that: wheel is equipped with the remote control brake device on (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012102206531A CN102774506A (en) | 2012-06-29 | 2012-06-29 | Airplane forced landing trolley |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012102206531A CN102774506A (en) | 2012-06-29 | 2012-06-29 | Airplane forced landing trolley |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102774506A true CN102774506A (en) | 2012-11-14 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012102206531A Pending CN102774506A (en) | 2012-06-29 | 2012-06-29 | Airplane forced landing trolley |
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| Country | Link |
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| CN (1) | CN102774506A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105966637A (en) * | 2016-05-13 | 2016-09-28 | 西北工业大学 | Safety recovery device for fixed wing unmanned aerial vehicle |
| CN106043729A (en) * | 2016-06-30 | 2016-10-26 | 张春生 | Shipborne unmanned plane landing sliding device |
| CN112140327A (en) * | 2020-09-25 | 2020-12-29 | 尹述平 | Raw materials equal proportion mixing arrangement is used in pottery production |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1775627A (en) * | 2005-12-08 | 2006-05-24 | 唐金元 | Special runway for aircraft emergency forced landing |
| US20080308673A1 (en) * | 2006-04-19 | 2008-12-18 | Yuen Liu | Secure System and Method for Aircraft Emergency Landing |
| CN201343148Y (en) * | 2009-02-07 | 2009-11-11 | 李洪武 | Airplane forced landing cushioning platform |
| CN202969199U (en) * | 2012-12-11 | 2013-06-05 | 王西坤 | Safety takeoff/landing airport |
-
2012
- 2012-06-29 CN CN2012102206531A patent/CN102774506A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1775627A (en) * | 2005-12-08 | 2006-05-24 | 唐金元 | Special runway for aircraft emergency forced landing |
| US20080308673A1 (en) * | 2006-04-19 | 2008-12-18 | Yuen Liu | Secure System and Method for Aircraft Emergency Landing |
| CN201343148Y (en) * | 2009-02-07 | 2009-11-11 | 李洪武 | Airplane forced landing cushioning platform |
| CN202969199U (en) * | 2012-12-11 | 2013-06-05 | 王西坤 | Safety takeoff/landing airport |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105966637A (en) * | 2016-05-13 | 2016-09-28 | 西北工业大学 | Safety recovery device for fixed wing unmanned aerial vehicle |
| CN106043729A (en) * | 2016-06-30 | 2016-10-26 | 张春生 | Shipborne unmanned plane landing sliding device |
| CN112140327A (en) * | 2020-09-25 | 2020-12-29 | 尹述平 | Raw materials equal proportion mixing arrangement is used in pottery production |
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Application publication date: 20121114 |