CN1255448A - Emergency lifesaving system for aircraft - Google Patents
Emergency lifesaving system for aircraft Download PDFInfo
- Publication number
- CN1255448A CN1255448A CN 00100079 CN00100079A CN1255448A CN 1255448 A CN1255448 A CN 1255448A CN 00100079 CN00100079 CN 00100079 CN 00100079 A CN00100079 A CN 00100079A CN 1255448 A CN1255448 A CN 1255448A
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- Prior art keywords
- aircraft
- parachute
- group
- multistage
- emergency lifesaving
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- 239000006096 absorbing agent Substances 0.000 claims description 8
- 230000035939 shock Effects 0.000 claims description 8
- 238000005273 aeration Methods 0.000 claims description 7
- 239000002775 capsule Substances 0.000 claims description 7
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 2
- 206010057071 Rectal tenesmus Diseases 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000010338 mechanical breakdown Methods 0.000 description 1
- 208000012271 tenesmus Diseases 0.000 description 1
- 239000003643 water by type Substances 0.000 description 1
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- Emergency Lowering Means (AREA)
Abstract
An emergency lifesaving system for aircraft is composed of multi-stage parachutes and buffer equipment. After the safe dropping-down speed is chosen, the total area of the parachutes is proportional to the maximal weight of aircraft. When accident occurs, said emergency lifesaving system is started to eject the multi-stage parachutes out, which are sequentially opened. Said buffer equipment which is a number of air bags aerated quickly is used to allow the aircraft to realize soft landing or float on water surface.
Description
The present invention relates to a kind of full machine life saving system that is used for the airplane emergency forced landing, especially a kind of is the main full machine abort escape system of forming of aircraft by multistage parachute.
At present aircraft does not in the world all have the safety device for life-saving of emergency landing, so when aircraft runs into burst contingency or mechanical breakdown in the middle of flight, can not safety carry out emergency landing, consequently cause the generation of fatal crass's aviation accident.In order to address this problem; U.S. cirrus design corporation (Cirrus Design) has developed 4 aviettes of SR20 type in 1999; on fuselage, bundled the large-scale parachute in a top, to reach the purpose that reduces occupant safety forced landing on aircraft lapse rate, the protection machine.Because weight and lapse rate that a top parachute can bear are limited, thereby this design can not be applied to large and medium-sized aircraft.
The purpose of this invention is to provide a kind of large, medium and small type aircraft abort escape system all applicatory.When aircraft is met burst accident awing, uncontrollable, when the situation of tenesmus rapidly occurring, aircraft can be reduced to the safety that descends slowly in the scope of safe deflection ratio from the speed of falling rapidly and land, to reach the purpose of occupant and aircraft on the protection machine.
The objective of the invention is to realize with following technical proposals:
A kind of emergency lifesaving system for aircraft mainly is made up of multistage parachute and shock absorber.Multistage parachute is one group or some groups, and every group is combined by some tops parachute lontitudinal series, and each top parachute is an one-level, and the upper class parachute is the pilot-parachute of next stage parachute.The safe deflection ratio of the gross area of parachute and aircraft and the maximum weight of aircraft are relevant, and the safe deflection ratio of aircraft is meant the distance that aircraft safety each second descends, should be less than 5 meter per seconds.The maximum weight of aircraft then comprises equipment contained on aircraft and the machine, article, personnel's total weight.When the safe deflection ratio of desired aircraft is selected, the gross area of parachute and the maximum weight of aircraft are directly proportional, after the gross area of parachute is determined, rationally determine the group number of multistage parachute according to the gross area of the length of aircraft and umbrella, and the progression of diameter, area and the multistage parachute of the single top umbrella in every group of multistage parachute.One group or some groups of parachutes are built in the fuselage top, and shock absorber then is built in fuselage bottom and wing root.Shock absorber can be several fast aeration capsules, is equipped with linkage on fast aeration capsule and multistage parachute.
Owing to adopt technique scheme, when aircraft chance burst accident causes the air crash situation, start abort escape system of the present invention, make a group of being built in the fuselage top or array multistage parachute successively outside fuselage ejects the storehouse, and the powerful pulling force when relying on the upper class pilot-parachute to launch launches next stage parachute order rapidly, the area of parachute is increased in limited spatial dimension fast, the gross area of the desired parachute of safe deflection ratio that adapts until the maximum weight of aircraft that reaches with hang bob, aircraft is just reduced to from the speed of falling rapidly in the speed range of safe deflection ratio like this, slowly landing.When multistage parachute is opened, also eject and open inflation from fuselage bottom and wing root rapidly with some fast aeration capsules of its interlock, constitute the air bag buffer zone of underbelly, the safe soft landing when realizing forced landing.When if aircraft force-lands in the waters, the fast aeration capsule can make aircraft fly at the water surface, rescues waiting, thereby realizes the purpose of occupant and aircraft on the protection machine.
The present invention is further described below in conjunction with drawings and Examples
Fig. 1 is the job order figure during multistage parachute decline weight in the system of the present invention
Fig. 2 is the structural representation of abort escape system of the present invention
As shown in Figure 1, when weight 5 aloft falls rapidly, pilot-parachute 1 is at first opened, guiding first order umbrella 2 is opened, umbrella 1 and umbrella 2 guide second stage umbrella 3 to open again, umbrella 1, umbrella 2 and umbrella 3 guide second stage umbrella 4 to open again, and weight 5 is landed from fall condition rapidly changes to the state of safe deflection ratio scope slowly.
In abort escape system of the present invention shown in Figure 2, be connected with one group of multistage parachute 6 of forming by 3 top parachutes on top, the fuselage axis girder of aircraft 7, above multistage parachute 6, also be connected with a pilot-parachute 9, constitute the parachute landing system of full machine jointly.At fuselage bottom and wing root by the shock absorber of forming by some fast aeration capsules 8.Shock absorber and parachute landing system are carried out interlock.If multistage parachute not on the fuselage axis, is then answered two limit symmetrical mountings, and opens simultaneously in order to avoid make the aircraft lack of equilibrium.Between parachutes at different levels successively the bonded assembly device be devices such as the hoisting rope that calculates according to the aircraft maximum weight or hook, can not disconnect between umbrella in the aircraft landing process guaranteeing, remain series combination.
According to calculating, when the safety deflection ratio was 1.2, when also being 1.2 meters of every sinkings, per 100 kilograms weight will be realized safe sinking, and for higher safety factor, the area that needs parachute is 30 sq ms.
Be example with 10 business airplanes now, establishing the aircraft maximum take-off weight is 3000 kilograms, and requiring safe deflection ratio is 1.2, and then the gross area of required parachute is 900 sq ms.
Determine the diameter of single top parachute to be no more than 17 meters according to length of aircraft, then rationally determine multistage parachute is divided into 5 grades, the gross area 900 sq ms of umbrella, the area of every top parachute is 180 sq ms, if umbrella is a circular parachute, then its diameter is 15.14 meters.
The shape of the multistage parachute in the abort escape system of the present invention is not limit, and can be circle, square or various geometric figure.
System of the present invention is applicable to the emergency landing lifesaving of large, medium and small type aircraft, and system of the present invention also can be used for the safety air-drop of heavy article.
Claims (5)
1, a kind of emergency lifesaving system for aircraft, it is characterized in that: this system comprises multistage parachute and shock absorber, multistage parachute is one group or some groups, every group is combined by some tops parachute lontitudinal series, the safe deflection ratio of the gross area of parachute and aircraft and the maximum weight of aircraft are relevant, when the safe deflection ratio of desired aircraft was selected, the gross area of parachute and the maximum weight of aircraft were directly proportional; One group or some groups of parachutes are built in the fuselage top, and shock absorber is built in fuselage bottom and wing root.
2, emergency lifesaving system for aircraft according to claim 1 is characterized in that: according to the length of aircraft and the gross area of umbrella, determine the group numbers of many group parachutes, and the diameter of the single top umbrella in every group of multistage parachute, the progression of area and multistage parachute.
3, emergency lifesaving system for aircraft according to claim 1 is characterized in that: described shock absorber is several fast aeration capsules.
4, emergency lifesaving system for aircraft according to claim 1 is characterized in that: one group or some groups of multistage parachutes are built in top, fuselage axis, and are connected with girder on the fuselage axis, constitute the parachute landing system of full machine.
5, emergency lifesaving system for aircraft according to claim 1 is characterized in that: be equipped with linkage on several fast aeration capsules and multistage parachute.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 00100079 CN1255448A (en) | 2000-01-06 | 2000-01-06 | Emergency lifesaving system for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 00100079 CN1255448A (en) | 2000-01-06 | 2000-01-06 | Emergency lifesaving system for aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1255448A true CN1255448A (en) | 2000-06-07 |
Family
ID=4575216
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 00100079 Pending CN1255448A (en) | 2000-01-06 | 2000-01-06 | Emergency lifesaving system for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1255448A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102310946A (en) * | 2011-06-07 | 2012-01-11 | 高尚 | Safe landing method (airbag landing method) of uncontrolled airplane and facility thereof |
| CN104943872A (en) * | 2015-06-10 | 2015-09-30 | 刘亚敏 | Unmanned aircraft and protecting method thereof |
| CN106240823A (en) * | 2016-08-23 | 2016-12-21 | 航宇救生装备有限公司 | It is capable of the aerial delivery system with attitude stabilization that slows down of disembarking |
| CN109383825A (en) * | 2017-08-11 | 2019-02-26 | 菜鸟智能物流控股有限公司 | aircraft |
| CN113955125A (en) * | 2021-11-18 | 2022-01-21 | 杜地 | Safety lifesaving system for airplane |
-
2000
- 2000-01-06 CN CN 00100079 patent/CN1255448A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102310946A (en) * | 2011-06-07 | 2012-01-11 | 高尚 | Safe landing method (airbag landing method) of uncontrolled airplane and facility thereof |
| CN104943872A (en) * | 2015-06-10 | 2015-09-30 | 刘亚敏 | Unmanned aircraft and protecting method thereof |
| CN106240823A (en) * | 2016-08-23 | 2016-12-21 | 航宇救生装备有限公司 | It is capable of the aerial delivery system with attitude stabilization that slows down of disembarking |
| CN109383825A (en) * | 2017-08-11 | 2019-02-26 | 菜鸟智能物流控股有限公司 | aircraft |
| CN113955125A (en) * | 2021-11-18 | 2022-01-21 | 杜地 | Safety lifesaving system for airplane |
| CN113955125B (en) * | 2021-11-18 | 2023-12-19 | 杜同 | Safety lifesaving system for aircraft |
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