CN1456479A - Integral lifesaving landing reducer on aircraft - Google Patents
Integral lifesaving landing reducer on aircraft Download PDFInfo
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- CN1456479A CN1456479A CN 02110334 CN02110334A CN1456479A CN 1456479 A CN1456479 A CN 1456479A CN 02110334 CN02110334 CN 02110334 CN 02110334 A CN02110334 A CN 02110334A CN 1456479 A CN1456479 A CN 1456479A
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- aircraft
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- parachute
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Abstract
A deceleration system of aircraft for integral lifesaving or landing is composed of vector-push reaction engine, huge parachute and great buffering air bag.
Description
Patent of the present invention relates to a kind of aircraft that makes can be at et out of order and under may the situation of air crash, effectively realize aerial whole lifesaving and can effectively reduce coasting speed when landing in airplane emergency landing (or normal landing), shorten the system and device of coasting distance, especially be applied to the overall aircraft lifesaving and the landing speed reduction gearing of civil aviation aircraft.
At present, known civil aviation aircraft is because should not be parachuted by the aircraft high speed flight at high altitude and the revenue passenger overwhelming majority is difficult to grasp the puzzlement of problems such as parachute jumping technology, so generally be not equipped with lifesaving appliance such as parachute aboard for the passenger.And realize aerial lifesaving by measures such as parachute are installed for overall aircraft separately, often can't put into practice again because be difficult to be equipped with and install technically enough greatly and be enough to bear the large-scale parachute of aircraft weight.
The purpose of patent of the present invention provides a kind of aircraft that makes can realize the system and device that aerial whole lifesaving and landing are slowed down effectively under the situation of et out of order.This system and device plays the remarkable effect of the sliding running velocity degree of effective reduction, shortening ground run distance when simultaneously, can also land (or normal landing) landing at airplane emergency.
The purpose of patent of the present invention is achieved in that in the airframe both sides near the position of the center of gravity of airplane, two (or some) are installed symmetrically the rotatable vectored thrust recoil of deboost and jet pipe driving engine can be provided, (or a several) large-scale parachute being installed on the top of aircraft simultaneously and in the bottom of airframe and wing several being installed can gas filed automatically large-scale buffer air bag.When aircraft et out of order and can not normal flight and during landing awing, the aviator can close sustainer, main engine immediately, start this aerial whole life saving system device simultaneously, vectored thrust recoil driving engine on the aircraft is started working at this moment, to the powerful high pressure draft of horizontal working direction (or tiltedly) ejection of aircraft, thereby the horizontal flight speed of aircraft is descended rapidly.When the horizontal flight speed of aircraft is reduced to about 0 (km/h), the jet pipe of the vectored thrust recoil driving engine on the aircraft is (or manually control) rotation downwards automatically, to spraying powerful high pressure draft perpendicular to ground-surface direction, thereby the vertical landing speed of aircraft is constantly descended, until reaching the safety falling velocity that is enough to make the landing of aircraft safety.
In order further to increase the safety factor of airplane emergency landing, after aircraft enters the vertical landing state, aircraft (or manually control) is automatically opened the large-scale parachute assembly on aircraft top, large-scale parachute on the aircraft is opened, with vectored thrust recoil driving engine co-operation, further slow down the vertical landing speed of aircraft, thereby aircraft can be landed more safely and reliably.When aircraft is about near ground or sea, recoil driving engine on the aircraft (or manually control) automatically cuts out, the large-scale buffer air bag device of airframe and wing bottom automatic (or manually control) is opened and sufficient unreactable gas simultaneously, large-scale parachute on the aircraft (or manually control) also thereupon automatically breaks away from aircraft, make aircraft steadily and mildly kiss the earth or float on the sea safely wait for rescue, thereby realize the purpose of the aerial general safety lifesaving of aircraft.
This device can also make aircraft when airport forced landing (or normal landing), by the line of travel ejection powerful high pressure draft of the recoil of the vectored thrust on aircraft driving engine to aircraft, play effective reduction coasting speed, shorten the remarkable effect of coasting distance, make the relatively large aircraft can be in the purpose of less airport or shorter runway landing thereby reach.
Owing to adopt such scheme, in the time of can making aircraft may cause the air crash accident at et out of order, can reach the purpose of whole lifesaving and forced landing effectively, thereby not only make numerous passengers' life security obtain guarantee, and avoided the damage of aircraft self to reach the tremendous economic loss that causes owing to air crash.
Below in conjunction with drawings and Examples patent of the present invention is described further.
Fig. 1 is that the recoil driving engine in lifesaving of this overall aircraft and the landing deceleration system device sprays high pressure draft to the horizontal working direction of aircraft, makes the rapid fundamental diagram that descends of horizontal flight (or sliding) speed of aircraft.
Fig. 2 be recoil driving engine in lifesaving of this overall aircraft and the landing deceleration system device to perpendicular to ground-surface direction ejection high pressure draft, the fundamental diagram that the vertical landing speed of aircraft is descended rapidly.
Fig. 3 is the fundamental diagram of the large-scale parachute in lifesaving of this overall aircraft and the landing deceleration system device when opening.
Fig. 4 is the fundamental diagram of the large-scale buffer air bag in aerial whole lifesaving of this aircraft and the landing deceleration system device when opening.
Among the figure 1, sustainer, main engine 2, recoil driving engine 3, parachute storehouse 4, buffer air bag storehouse 5, parachute 6, buffer air bag
In Fig. 1, awing et out of order can not normal flight and landing and when the air crash accident may take place when aircraft, the aviator can close sustainer, main engine (1) immediately, start this aerial whole life saving system device simultaneously, vectored thrust recoil driving engine (2) on the aircraft is started working at this moment, to the powerful high pressure draft of horizontal working direction (or tiltedly) ejection of aircraft, thereby the horizontal flight speed of aircraft is descended rapidly.If aircraft is on less airport or on than the dash road during emergency landing, then the recoil driving engine of the vectored thrust on the aircraft (2) can play the remarkable effect of the sliding running velocity degree of effective reduction, shortening ground run distance to the powerful high pressure draft of the horizontal working direction ejection of aircraft.
In Fig. 2, when the horizontal flight speed of aircraft is reduced to about 0 (km/h), the jet pipe of the vectored thrust recoil driving engine (2) on the aircraft is (or manually control) rotation downwards automatically, to spraying powerful high pressure draft perpendicular to ground-surface direction, thereby the vertical landing speed of aircraft is constantly descended, until reaching the safety falling velocity that is enough to make the landing of aircraft safety.
In Fig. 3, after aircraft entered the vertical landing state, opened in the parachute storehouse (2) on the aircraft (or manually control) automatically, and large-scale parachute (5) ejects and opens, with vectored thrust recoil driving engine (2) co-operation, thereby aircraft can be landed more safely and reliably.
In Fig. 4, when aircraft is about near ground or sea, recoil driving engine on the aircraft (or manually control) automatically cuts out, the buffer air bag storehouse (3) of airframe and wing bottom automatic (or manually controlling) opens simultaneously, large-scale buffer air bag (6) ejects and sufficient unreactable gas, large-scale parachute (5) on the aircraft (or manually control) also thereupon automatically breaks away from aircraft, make aircraft steadily and mildly kiss the earth or float on the sea safely wait for rescue, thereby realize the purpose of overall aircraft safe life-saving.
Claims (3)
1, a kind of whole lifesaving of civil aircraft and landing deceleration system device that is made of recoil driving engine, parachute, buffer air bag is characterized in that: the recoil driving engine that can provide deboost to make the aircraft fall-retarding is installed aboard.
2, whole lifesaving of civil aircraft according to claim 1 and landing deceleration system device is characterized in that: parachute assembly is installed aboard.
3, whole lifesaving of civil aircraft according to claim 1 and landing deceleration system device is characterized in that: the buffer air bag device is installed aboard.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 02110334 CN1456479A (en) | 2002-05-08 | 2002-05-08 | Integral lifesaving landing reducer on aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 02110334 CN1456479A (en) | 2002-05-08 | 2002-05-08 | Integral lifesaving landing reducer on aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1456479A true CN1456479A (en) | 2003-11-19 |
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ID=29410214
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 02110334 Pending CN1456479A (en) | 2002-05-08 | 2002-05-08 | Integral lifesaving landing reducer on aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1456479A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2450956C2 (en) * | 2009-10-26 | 2012-05-20 | Негосударственная образовательная организация высшего профессионального образования Некоммерческое партнерство "Смольный университет" Российской академии образования | Method of salvaging aircraft in in-flight accident |
| CN102582836A (en) * | 2012-03-02 | 2012-07-18 | 浙江金中机电科技有限公司 | Airplane with emergency landing device in fault |
| CN101758928B (en) * | 2010-02-01 | 2013-01-02 | 上海东方久乐汽车安全气囊有限公司 | Air bag protecting device in aircraft landing system |
| CN103171767A (en) * | 2011-12-25 | 2013-06-26 | 山东科技职业学院 | Airplane protective ejection air bag |
| CN104386257A (en) * | 2014-10-15 | 2015-03-04 | 吴祖池 | Protection system used in safe crash landing of aircraft |
| CN104554730A (en) * | 2013-10-11 | 2015-04-29 | 天津得瑞丰凯新材料科技有限公司 | Passenger plane parachute bay collective escape device |
| CN106904266A (en) * | 2017-03-21 | 2017-06-30 | 张宏 | A kind of new fixed wing aircraft |
| CN108163211A (en) * | 2017-12-11 | 2018-06-15 | 孟煊英 | A kind of aircraft security landing-gear |
| CN113443129A (en) * | 2021-08-11 | 2021-09-28 | 长沙医学院 | Aerial flying train with safety protection |
| CN113998106A (en) * | 2021-10-27 | 2022-02-01 | 南京壮大智能科技研究院有限公司 | Overwater forced landing method for unmanned aerial vehicle |
-
2002
- 2002-05-08 CN CN 02110334 patent/CN1456479A/en active Pending
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2450956C2 (en) * | 2009-10-26 | 2012-05-20 | Негосударственная образовательная организация высшего профессионального образования Некоммерческое партнерство "Смольный университет" Российской академии образования | Method of salvaging aircraft in in-flight accident |
| CN101758928B (en) * | 2010-02-01 | 2013-01-02 | 上海东方久乐汽车安全气囊有限公司 | Air bag protecting device in aircraft landing system |
| CN103171767A (en) * | 2011-12-25 | 2013-06-26 | 山东科技职业学院 | Airplane protective ejection air bag |
| CN102582836A (en) * | 2012-03-02 | 2012-07-18 | 浙江金中机电科技有限公司 | Airplane with emergency landing device in fault |
| CN104554730A (en) * | 2013-10-11 | 2015-04-29 | 天津得瑞丰凯新材料科技有限公司 | Passenger plane parachute bay collective escape device |
| CN104386257A (en) * | 2014-10-15 | 2015-03-04 | 吴祖池 | Protection system used in safe crash landing of aircraft |
| CN106904266A (en) * | 2017-03-21 | 2017-06-30 | 张宏 | A kind of new fixed wing aircraft |
| CN108163211A (en) * | 2017-12-11 | 2018-06-15 | 孟煊英 | A kind of aircraft security landing-gear |
| CN113443129A (en) * | 2021-08-11 | 2021-09-28 | 长沙医学院 | Aerial flying train with safety protection |
| CN113998106A (en) * | 2021-10-27 | 2022-02-01 | 南京壮大智能科技研究院有限公司 | Overwater forced landing method for unmanned aerial vehicle |
| CN113998106B (en) * | 2021-10-27 | 2023-12-08 | 南京壮大智能科技研究院有限公司 | Unmanned aerial vehicle water forced landing method |
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| C06 | Publication | ||
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| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |