CN1036372A - Lifesaving control system of civil aircraft - Google Patents
Lifesaving control system of civil aircraft Download PDFInfo
- Publication number
- CN1036372A CN1036372A CN 88108189 CN88108189A CN1036372A CN 1036372 A CN1036372 A CN 1036372A CN 88108189 CN88108189 CN 88108189 CN 88108189 A CN88108189 A CN 88108189A CN 1036372 A CN1036372 A CN 1036372A
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- umbrella
- control system
- lifesaving
- wing
- cabin
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Abstract
The invention discloses a kind of lifesaving control system of civil aircraft.When various different contingency aloft takes place, chaufeur can pass through center pedestal, computerized control system or manual control system are handled the double insurance lifesaving appliance that is connected in parallel in two systems, this device comprises the high-speed hydraulic pressurized strut that is located in the umbrella cabin and by the wing umbrella that falls, the parachute-opening controller that program control rocket constitutes, high-speed hydraulic pressurized strut in the gas cabin and inflation energy disperser, the directional blasting bolt at umbrella direction controller and two wing root places constitutes.In 6000 meters to 1000 meters flying height, umbrella and pneumatic float can be worked with interior immediately at 15 seconds, thereby kept the people reliably, the machine safe falling.
Description
The present invention relates to finish when a kind of airline carriers of passengers has an accident the control system of lifesaving, specifically, it is the lifesaving appliance of the double insurance of automatic computer and manual control.
For many years, when the accident of accident takes place airline carriers of passengers and occur, cause the fatal crass, study carefully its wrecking cause, it is on fire from explosion suddenly mostly to be driving engine, and fuel tank leaks, alighting gear malfunctioning or hijack a plane due to; Yet technology how to take corresponding rescue action is not seen open report on relevant patent documentation or periodical, magazine so far yet.11, on September in the recent period-1988, the Workers Daily third edition (select from " China Civil Aviation Journal has been published the new design of passenger plane accident escape that the U.S. one inventor proposes; be provided with the main cabin that is fixed on the corner leg in this design; click push button; a string inflation arm can be thrusted away the main cabin, again by landing with main cabin landing and splash automatically with a string air bag that is located at the bottom, cabin that to be expanded into be the main cabin ground-surface mat realization lifesaving hope of landing slowly.By above-mentioned design analysis, the passenger its main cabin in needs just have the chance of escape in the very urgent time, and owing to the lifesaving appliance that only adopts single system also safety inadequately, simultaneously, this scheme is difficult to preserve passenger plane, loses bigger.
The object of the present invention is to provide a kind of double insurance lifesaving appliance, make the accident airline carriers of passengers obtain safe falling in time by computer controlled automatic.
For finishing the foregoing invention task, the present invention proposes following technical scheme, promptly returning apparatus has special-purpose program control disk is set in manual control system and the computer control systems in machine, mutually be connected to center pedestal on parallel form two control system again, simultaneously, it is shared as two systems also to connect lifesaving appliance on two control system again, the lifesaving appliance of the double insurance that constitutes computer controlled automatic and manually control, this device comprises: be contained in high-speed hydraulic pressurized strut and parachute-opening controller in the umbrella cabin, be contained in high-speed hydraulic pressurized strut and inflation energy disperser in the gas cabin, the umbrella direction controller between interior provision room of the machine that is contained in and the after hold and the disconnected wing automatic controller of two wing roots.
The solution of the present invention will be described further in the accompanying drawing of following embodiment.
Fig. 1 is a lifesaving appliance structural representation of the present invention.
Fig. 2 is that system of the present invention connects block diagram.
Fig. 3 is wing umbrella of the present invention and floating drum working state figure.
Fig. 4 is that open and the constitution diagram of program control branch after rocket launching in umbrella of the present invention cabin.
Constitution diagram when Fig. 5 is accident passenger plane landing of the present invention ground.
With reference to Fig. 1,2, computer control system (2) is connected in parallel on the center pedestal (1) with manual control system (3).Manual control system is mechanical servo or electric servo system.Umbrella cabin (13) is located at fuselage (26) top, this chamber is connected and composed by snap close (12) by two the last hatchcovers (11) that are symmetrical set that are hinged on the fuselage, the high-speed hydraulic pressurized strut (10) that is contained in the umbrella cabin is a left side, right uniform setting (six) is connected with fuselage with last hatchcover respectively and joins with two control system 2,3; Indoor parachute-opening controller is made of to rocket (14) wing umbrella and the program control branch that is connected this umbrella lead end, its wing umbrella (with reference to Fig. 3) is made of and the one-tenth turriform the drogue (16) at the shunt umbrella that is located at the top (15) middle part and guiding control umbrella (17) three parts of bottom, its program control branch to rocket (with reference to Fig. 4) be two sub-arrows of a female rocket band form and with two control system 2,3 connect, gas cabin (20) is located at the bottom of fuselage, and this chamber is connected and composed by snap close (12) by two the following hatchcovers (19) that are symmetrical set that are hinged on the fuselage.It is the uniform setting in the left and right sides that six high-speed hydraulic pressurized struts (10) are housed in the gas cabin too, is connected with fuselage with following hatchcover respectively and joins with two control system; Indoor inflation energy disperser is by floating drum (21) and compressed gas cylinder (23) the electromagnetic gas valve switch (22) that is communicated with it formation, and switch is contained on the connecting leg between floating drum and the gas cylinder and with two control system 2,3 and is connected.Avoid high tension cord and other territory jeopardously for making accident passenger plane, control the direction of guiding control umbrella (17) and air-flow and reach the landing direction that changes wing umbrella by the provision room and the umbrella direction controller between the after hold that are located in the fuselage, the umbrella direction controller is made up of the umbrella rope combination (18) and the servo serving combination (18) that are connected on the wing umbrella, its servomechanism is by two hoisting mechanisms and be arranged on rear end, umbrella cabin, one end and umbrella rope are connected, the other end is connected with two control system, the umbrella rope is incorporated into the rare six roots of sensation, every single synthetic by two, the disconnected wing automatic controller that is located at two wing roots is made of the adapter plate (24) of two wing roots and the directional blasting bolt (25) that is connected on the adapter plate, two directional blasting bolts while and control system 2,3 join, high-speed hydraulic pressurized strut in the umbrella cabin and program control branch are to rocket, high-speed hydraulic pressurized strut in the gas cabin and electromagnetic gas valve switch, servo mechanism of twisting rope, the directional blasting bolt is connected on two control system 2 mutually with parallel way, on 3.
Existing accompanying drawings lifesaving control system of civil aircraft working process of the present invention.
When passenger plane has an accident, chaufeur will be according to the different situations that take place in-flight, center pedestal (1) be can pass through and computer control system (2) or operation manual control system (3) opened, start the high-speed hydraulic pressurized strut (10) in the umbrella cabin, Cang Gai (11) is opened, start the program control branch ignition system to rocket (14) simultaneously, one group of female rocket and two sub-arrows divide to (left-right orientation) and fly and open wing umbrella mouth.Make the shunt umbrella (15) of wing umbrella, drogue (16) and guiding umbrella (17) change mode of operation rapidly over to, handle servo mechanism of twisting rope (27) by chaufeur by system (2) or system (3) again and regulate the landing direction, avoid ground high tension cord and other danger zone, make passenger plane along the landing slowly of safe ground direction.In the servo mechanism of twisting rope of operation (27),, hatchcover (19) is opened and inflation in floating drum (21) by high-speed hydraulic pressurized strut (10) and electromagnetic gas valve switch (22) in computer system (2) or manual system (3) the unlatching gas cabin (20).When passenger plane need land across the sea, carry out simultaneously to aeration of float and the wing umbrella of unlatching.When the complete come out of action performance of driving engine is also on fire from explosion, except that being undertaken, also should ignite directional blasting bolt (25) by computer system or manual system immediately, cut off two wings in case fire spreading by said process.
The lifesaving control system that the present invention proposes is provided with the lifesaving appliance of dual fail-safe, on fire from explosion such as sudden engine to what occur in-flight, fuel tank leaks, leap the sea oil plant and exhaust the accident that undercarriage is malfunctioning or the chance ruffian hijacks a plane and causes danger, all can keep in time people, machine safe falling, this device flying height be 8000 meters to 1000 meters with interior the most suitable, through simulated test and calculating, its wing umbrella and camel fully can 10～15 seconds with interior fully change over to duty and the landing ground steady.
Claims (9)
1, a kind of lifesaving control system of civil aircraft, comprise center pedestal (1), computer control systems (2), it is characterized in that also being provided with manual control system (3) and computer control systems (2) and be arranged on that program control disk in the computer system is parallel to that center pedestal (1) is gone up and two control system on shared lifesaving appliance arranged, constitute the lifesaving appliance of double insurance automatic and that manually control, said device is by the high-speed hydraulic pressurized strut (10) and the parachute-opening controller that are contained in the umbrella cabin (13), be contained in high-speed hydraulic pressurized strut (10) and inflation energy disperser in the gas cabin (20), be contained in the umbrella direction controller between provision room and the after hold and the disconnected wing automatic controller of two wing roots and constitute.
2, lifesaving control system according to claim 1 is characterized in that said manual control system (3) is machinery or electrical equipment servomechanism.
3, lifesaving control system according to claim 1 is characterized in that said parachute-opening controller is made of to rocket (14) wing umbrella and the program control branch that is connected umbrella lead-in wire.
4,, it is characterized in that said wing umbrella is turriform and by top shunt umbrella (15), middle part drogue (16) and bottom guiding control umbrella (17) constitute according to claim 1,3 described lifesaving control systems.
5, lifesaving control system according to claim 1 is characterized in that said inflation energy disperser is made of floating drum (21), electromagnetic gas valve switch (22) and compressed gas cylinder (23).
6, lifesaving control system according to claim 1 is characterized in that said umbrella direction controller is made of umbrella rope combination (18) that is connected wing umbrella and servo mechanism of twisting rope (27).
7, lifesaving control system according to claim 6 is characterized in that the combination of umbrella rope constitutes by 6 at least.
8, lifesaving control system according to claim 1 is characterized in that said umbrella cabin (13) and gas cabin (20) are respectively by being hinged on the fuselage top and being hinged on the Cang Gai up and down (11,19) of underbelly and snap close (12) constitutes.
9, lifesaving control system according to claim 1 is characterized in that said disconnected wing automatic controller is made of the adapter plate (24) of two wing roots and the directional blasting bolt (25) that connects onboard.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 88108189 CN1036372A (en) | 1988-11-26 | 1988-11-26 | Lifesaving control system of civil aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 88108189 CN1036372A (en) | 1988-11-26 | 1988-11-26 | Lifesaving control system of civil aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1036372A true CN1036372A (en) | 1989-10-18 |
Family
ID=4834984
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 88108189 Pending CN1036372A (en) | 1988-11-26 | 1988-11-26 | Lifesaving control system of civil aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1036372A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1077063C (en) * | 1998-04-15 | 2002-01-02 | 王俊峰 | Automatic safety escaping danger system for aircraft distress personnel |
| CN103112590A (en) * | 2011-11-16 | 2013-05-22 | 宋学恭 | Airplane capable of landing safely |
| CN108163211A (en) * | 2017-12-11 | 2018-06-15 | 孟煊英 | A kind of aircraft security landing-gear |
| CN110109474A (en) * | 2019-05-13 | 2019-08-09 | 刘钢 | Rotor wing unmanned aerial vehicle complicated landform autobalance landing chassis and control method |
-
1988
- 1988-11-26 CN CN 88108189 patent/CN1036372A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1077063C (en) * | 1998-04-15 | 2002-01-02 | 王俊峰 | Automatic safety escaping danger system for aircraft distress personnel |
| CN103112590A (en) * | 2011-11-16 | 2013-05-22 | 宋学恭 | Airplane capable of landing safely |
| CN103112590B (en) * | 2011-11-16 | 2015-09-23 | 宋学恭 | A kind of safe falling aircraft |
| CN108163211A (en) * | 2017-12-11 | 2018-06-15 | 孟煊英 | A kind of aircraft security landing-gear |
| CN110109474A (en) * | 2019-05-13 | 2019-08-09 | 刘钢 | Rotor wing unmanned aerial vehicle complicated landform autobalance landing chassis and control method |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C01 | Deemed withdrawal of patent application (patent law 1993) | ||
| WD01 | Invention patent application deemed withdrawn after publication |