CN202848036U - Aircraft crash-landing device - Google Patents
Aircraft crash-landing device Download PDFInfo
- Publication number
- CN202848036U CN202848036U CN 201220379654 CN201220379654U CN202848036U CN 202848036 U CN202848036 U CN 202848036U CN 201220379654 CN201220379654 CN 201220379654 CN 201220379654 U CN201220379654 U CN 201220379654U CN 202848036 U CN202848036 U CN 202848036U
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- CN
- China
- Prior art keywords
- landing platform
- landing
- distress
- platform
- aircraft
- 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
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Abstract
The utility model provides an aircraft crash-landing device which mainly consists of a landing platform, a turbine engine, a water tank, a hydraulic giant, wheels, an inflatable block wall, an operating gear and a illuminating apparatus, wherein the turbine engine, the water tank, the hydraulic giant, the operating gear and the illuminating apparatus are installed on the landing platform, the inflatable block wall is installed at the front end of the landing platform, and the wheels are connected with the landing platform through a shock absorber. The gravity of an aircraft is converted into heat energy and the heat energy releases through the shock absorber, thus the strong impact between the aircraft and the ground is avoided. The platform and the aircraft move simultaneously, and thus the friction force between the aircraft and the ground is reduced maximally. The hydraulic giant can put out fire and cool the aircraft, so as to avoid the aircraft hovering and dumping fuel in the air.
Description
Technical field
The utility model relates to a kind of forced landing device, or rather, relates to a kind of airplane forced landing device.
Background technology
The present aircraft in the world force-lands because of Landing Gear Valves, prior art is to utilize the aircraft bottom to slide in the runway friction by brave chaufeur technology passenger plane is stopped, because the easy blast on fire of the long-time overheated fuel tank of friction in body and ground, because having damping to make impact with the ground to rupture easily, body do not explode, because fire extinguishing tanker could be done like this near aircraft and fire extinguishing cooling and often lose valuable escape time after only having passenger plane to stop, passenger plane is that maximum to the air-service personnel decocts in order to empty that fuel tank hovers in the air for a long time aloft, also be the maximum waste to gasoline, successfully also can have produced considerable damage to body even force-land.
The utility model content
The utility model provides a kind of airplane forced landing device, when having solved forced landing in the prior art and the ground problem that the large easily fracture of bump, aircraft and frictional ground force is exploded strongly, fuel tank is delayed and emptied to the enforcement fire extinguishing cooling time aloft.
The utility model provides a kind of airplane forced landing device, mainly formed by landing platform, turbine engine, water tank, hydraulic giant, wheel, inflatable barrier wall, handling device and illumination equipment, wherein turbine engine, water tank, hydraulic giant, handling device, illumination equipment are installed on the landing platform, the inflatable barrier wall is installed in the front end of landing platform, and wheel is connected on the landing platform by bumper.
Preferred scheme is that distress landing platform top is provided with flame-retardant layer, and magnet or rubber suction cups are installed.
Preferred scheme is that distress landing platform is comprised of with the right-angled crossing formula several load-bearing worker section steel beams.
Preferred scheme is that distress landing platform is provided with the noctilucence line of centers.
Preferred scheme is that distress landing platform is provided with the inflatable slide escape.
Preferred scheme is that airplane forced landing device also is provided with brake actuator, and brake actuator one end is connected on the distress landing platform by connection bracket, and an end is connected on the rail.
Preferred scheme is that connection bracket is that separation type connects, and is provided with spring.
Preferred scheme is that turbine engine is three, one of front end, and two of rear ends are separately positioned on wide about 2/3rds places, distress landing platform two ends and 1/2nd places.
Preferred scheme is that bumper is different in size.
Preferred scheme is that illumination equipment is installed in around the distress landing platform, comprises illumination equipment upwards and downward illumination equipment.
The utility model discharges the strong bump of having avoided extension set and ground by using bumper to make the gravity of aircraft be converted into heat energy by bumper, platform and passenger plane be the mobile friction force on aircraft and ground that farthest alleviated simultaneously, use hydraulic giant can aircraft in time to put out a fire and lower the temperature, avoid that the plane is circling about in the sky drains the oil.
Description of drawings
Fig. 1 is construction profile scheme drawing of the present utility model;
Fig. 2 is plan structure scheme drawing of the present utility model.
The specific embodiment
Below in conjunction with the drawings and the specific embodiments; the utility model is described in further detail; but this specific embodiment also is not used in restriction protection domain of the present utility model, and all should be considered as belonging to protection domain of the present utility model with the device of move mode help aircraft landing.
Embodiment 1:
The utility model provides a kind of airplane forced landing device, mainly by landing platform 1, turbine engine 2, water tank 3, hydraulic giant 4, wheel 5, inflatable barrier wall 6, handling device 7 and illumination equipment 8 form, wherein turbine engine 2, water tank 3, hydraulic giant 4, handling device 7, illumination equipment 8 is installed on the landing platform 1, inflatable barrier wall 6 is installed in the front end of landing platform 1, wheel 5 is connected on the landing platform 1 by bumper 9, distress landing platform 1 top is provided with flame-retardant layer, and magnet or rubber suction cups 10 be installed, distress landing platform 1 is comprised of several load-bearing worker section steel beams, distress landing platform 1 is provided with noctilucence line of centers 11, distress landing platform 1 is provided with inflatable slide escape 12, airplane forced landing device also is provided with brake actuator, brake actuator one end is connected on the distress landing platform by connection bracket 13, one end is connected on the rail 14, connection bracket 13 connects for separation type, and be provided with spring, scheme is that turbine engine 2 is three, be separately positioned on wide about 2/3rds places, distress landing platform 1 two ends and 1/2nd places, bumper 9 is different in size, illumination equipment 8 is installed in around the distress landing platform, comprises illumination equipment upwards and downward illumination equipment.
Above content be in conjunction with structure of the present utility model and working process to its further description of doing, can not assert that implementation of the present utility model is confined to these explanations.For the utility model person of an ordinary skill in the technical field, without departing from the concept of the premise utility, can also make some simple deduction or replace, all should be considered as belonging to protection domain of the present utility model.
Claims (10)
1. airplane forced landing device, mainly formed by landing platform, turbine engine, water tank, hydraulic giant, wheel, inflatable barrier wall, handling device and illumination equipment, wherein turbine engine, water tank, hydraulic giant, handling device, illumination equipment are installed on the landing platform, the inflatable barrier wall is installed in the front end of landing platform, and wheel is connected on the landing platform by bumper.
2. airplane forced landing device according to claim 1, it is characterized in that: described distress landing platform top is provided with flame-retardant layer, and magnet or rubber suction cups are installed.
3. airplane forced landing device according to claim 2, it is characterized in that: several load-bearing workers of described distress landing platform section steel beam forms with the right-angled crossing formula.
4. each described airplane forced landing device according to claim 1-3, it is characterized in that: described distress landing platform is provided with the noctilucence line of centers.
5. each described airplane forced landing device according to claim 1-3, it is characterized in that: described distress landing platform is provided with the inflatable slide escape.
6. each described airplane forced landing device according to claim 1-3, it is characterized in that: described airplane forced landing device also is provided with brake actuator, and brake actuator one end is connected on the distress landing platform by connection bracket, and an end is connected on the rail.
7. airplane forced landing device according to claim 6 is characterized in that: described connection bracket is that separation type connects, and is provided with spring.
8. each described airplane forced landing device according to claim 1-3, it is characterized in that: described turbine engine is three, one of front end, two of rear ends are separately positioned on wide about 2/3rds places, distress landing platform two ends and 1/2nd places.
9. each described airplane forced landing device according to claim 1-3, it is characterized in that: described bumper is different in size.
10. each described airplane forced landing device according to claim 1-3, it is characterized in that: described illumination equipment is installed in around the distress landing platform, comprises illumination equipment upwards and downward illumination equipment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220379654 CN202848036U (en) | 2012-08-02 | 2012-08-02 | Aircraft crash-landing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220379654 CN202848036U (en) | 2012-08-02 | 2012-08-02 | Aircraft crash-landing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202848036U true CN202848036U (en) | 2013-04-03 |
Family
ID=47979260
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220379654 Expired - Fee Related CN202848036U (en) | 2012-08-02 | 2012-08-02 | Aircraft crash-landing device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202848036U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105799946A (en) * | 2016-04-27 | 2016-07-27 | 武汉大学 | Airplane safe forced landing assisting system and safe forced landing method |
| CN106256686A (en) * | 2015-06-22 | 2016-12-28 | 古德里奇公司 | Conductive attachment device |
-
2012
- 2012-08-02 CN CN 201220379654 patent/CN202848036U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106256686A (en) * | 2015-06-22 | 2016-12-28 | 古德里奇公司 | Conductive attachment device |
| CN105799946A (en) * | 2016-04-27 | 2016-07-27 | 武汉大学 | Airplane safe forced landing assisting system and safe forced landing method |
| CN105799946B (en) * | 2016-04-27 | 2017-12-15 | 武汉大学 | A kind of aircraft safety forced landing accessory system and safety forced landing method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130403 Termination date: 20150802 |
|
| EXPY | Termination of patent right or utility model |