DE4214609A1 - Emergency parachute to lower complete aircraft - has parachute attached to front of fuselage and rear of fuselage is formed as crumple zone to absorb impact energy - Google Patents

Emergency parachute to lower complete aircraft - has parachute attached to front of fuselage and rear of fuselage is formed as crumple zone to absorb impact energy

Info

Publication number
DE4214609A1
DE4214609A1 DE19924214609 DE4214609A DE4214609A1 DE 4214609 A1 DE4214609 A1 DE 4214609A1 DE 19924214609 DE19924214609 DE 19924214609 DE 4214609 A DE4214609 A DE 4214609A DE 4214609 A1 DE4214609 A1 DE 4214609A1
Authority
DE
Germany
Prior art keywords
fuselage
parachute
emergency landing
landing device
crumple zone
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.)
Withdrawn
Application number
DE19924214609
Other languages
German (de)
Inventor
Joerg Dr Ing Lensing
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Priority to DE19924214609 priority Critical patent/DE4214609A1/en
Publication of DE4214609A1 publication Critical patent/DE4214609A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D25/00—Emergency apparatus or devices, not otherwise provided for
    • B64D25/08—Ejecting or escaping means
    • B64D25/12—Ejectable capsules
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D17/00—Parachutes
    • B64D17/80—Parachutes in association with aircraft, e.g. for braking thereof

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Business, Economics & Management (AREA)
  • Emergency Management (AREA)
  • Emergency Lowering Means (AREA)
  • Toys (AREA)

Abstract

One or several parachutes (1), are attached to the fuselage forward of the centre of gravity (S) so that the fuselage approaches the ground at an angle ( alpha ). The rear of the fuselage may be formed as a crumple zone to absorb energy. Weak points in the wings may be provided to allow them to break off on impact. Rocket or air pressure devices may be used to ensure rapid deployment of the parachute. ADVANTAGE - On impact of aircraft with the ground passengers are pressed into their seats, and energy of impact is absorbed in the crumple zones or wing fractures.

Description

Die Erfindung bezieht sich auf eine Notlandeeinrichtung für Flugzeuge unter Verwendung eines Fallschirmes, wobei der Fall­ schirm in einem Raum , vorteilhaft im vorderen oberen Rumpfbe­ reich, gelagert und während eines nicht mehr kontrollierbaren Fluges ausgestoßen wird.The invention relates to an emergency landing device for Aircraft using a parachute, the case screen in a room, advantageous in the front upper fuselage rich, stored and during a no longer controllable Flight is ejected.

Die Verwendung von Fallschirmen zur Landung beziehungsweise zur Bremsung des Flugzeuges bei der Landung sind in den verschieden­ sten Ausführungsformen bekannt. In erster Linie handelt es sich um Landeverfahren zur senkrechten Landung, wobei der Fallschirm als sogenannter "Flugzeugträger" dient und gewissermaßen das Flugzeug auf den Boden absetzt. Diese Verfahren haben eine Rei­ he von zum Teil erheblichen Nachteilen. Sie erfordern einmal einen sehr großen Schirmdurchmesser, wobei diesem Gebot ver­ schiedentlich dadurch abgeholfen wurde, daß mehrere kleine Schirme zum Einsatz kamen. Ein weiterer Nachteil ist, daß beim Aufsetzen ein hoher Landestoß auftritt, der zu einem enormen Fahrwerksfederungdämpfungssystem führt, was wiederum zu einer wesentlichen Strukturveränderung führt.The use of parachutes for landing or for Braking the aircraft when landing are different in the Most known embodiments. First and foremost about landing procedures for vertical landing, using the parachute serves as a so-called "aircraft carrier" and so to speak Plane drops to the ground. These procedures have a series he of sometimes considerable disadvantages. They require once a very large screen diameter, this requirement ver was remedied by the fact that several small Umbrellas were used. Another disadvantage is that the Landing a high landing thrust occurs, which leads to an enormous Suspension suspension system leads, which in turn leads to a leads to significant structural changes.

Mit keiner der Ausführungsformen nach dem Stand der Technik ist es möglich, eine Notlandung durchzuführen, da die Schirmgröße und Anordnung zu keiner brauchbaren Notlandung des Flugzeuges führt.With none of the prior art embodiments it is possible to make an emergency landing because of the screen size and order for no usable emergency landing of the aircraft leads.

Diese Aufgabe wird durch die in den Ansprüchen niedergelegten Maßnahmen gelöst. In der Beschreibung ist ein Ausführungsbei­ spiel erläutert und in der Zeichnung dargestellt.This task is accomplished by those set out in the claims Measures solved. In the description is an execution example game explained and shown in the drawing.

Es zeigen:Show it:

Fig. 1 eine Ansicht bezüglich der Anlenkung des Fallschirmes am Flugzeug. Fig. 1 is a view regarding the articulation of the parachute on the aircraft.

Das nachfolgend beschriebene Ausführungsbeispiel der Erfindung weist ein oder mehrere Fallschirme 1 auf, deren Auftrieb und Anordnung zum Schwerpunkt S das Flugzeug 2 in eine optimale Sturzlage α bringt. Dabei ist der Winkel α so zu wählen, daß die Knautschzone im Heckbereich voll ausgenutzt werden kann und zusätzlich die Drehenergie gerade so groß werden kann, daß das ausgefahrene Fahrwerk eine Abfederung/dämpfung des Flugzeuges gewährleistet. Außerdem muß die Steifigkeit des Restrumpfes größer sein, als die Steifigkeit der Knautsch­ zone. Unter Umständen kann es günstiger sein, die Flügel 3 mit Hilfe von Sollbruchstellen abknicken zu lassen. Der Fall­ schirm 1 muß mit geeigneten Hilfsmitteln (Rakete, Druckluft, etc.) in kürzester Zeit zur vollen Entfaltung gebracht wer­ den, damit auch bei niedrigeren Flughöhen "sichere" Notlan­ dung gewährleistet ist.The exemplary embodiment of the invention described below has one or more parachutes 1 , the buoyancy and arrangement of which center of gravity S brings the aircraft 2 into an optimal fall position α. The angle α is to be chosen so that the crumple zone in the tail area can be fully utilized and in addition the turning energy can be just so large that the extended landing gear ensures cushioning / damping of the aircraft. In addition, the stiffness of the residual hull must be greater than the stiffness of the crumple zone. Under certain circumstances, it may be cheaper to have the wing 3 snap off with the aid of predetermined breaking points. The case screen 1 must be brought to full development in the shortest possible time with suitable aids (rocket, compressed air, etc.), so that "safe" emergency landing is guaranteed even at lower altitudes.

BerechnungsbeispielCalculation example

Der Einfachheithalber wird angenommen: Die Knautschzone ist so konstruiert, daß in etwa die Stoßkraft F während der Stoßphase nahezu konstant bleibt. Die Sinkge­ schwindigkeit beträgt V=200 km/h und die Verzögerung darf we­ gen der Überlebenschance das 27fache der Erdbeschleunigung g nicht übersteigen.For the sake of simplicity, it is assumed: The crumple zone is designed so that approximately the impact force F remains almost constant during the impact phase. The sinkge speed is V = 200 km / h and the deceleration is allowed 27 times the acceleration due to gravity do not exceed g.

Dann gilt:
Für F≈ konstant ist auch die Verzögerung α≈ konstant. Die Stoß­ zeit ts folgt dann aus:
ts=V/a=0,209 sec
und damit erhält man den Knautschweg s zu:
s=a t₂s/2=5,8 m.Then:
The delay α≈ is also constant for F≈ constant. The impact time t s then follows:
t s = V / a = 0.209 sec
and you get the crumple path s to:
s = a t₂ s / 2 = 5.8 m.

Dies ist durchaus eine realistische Größe. Zusätzliche Reserve ist noch in der Verformung des Bodens, in der Drehenergieauf­ nahme und in der Verformung der Reststruktur enthalten.This is quite a realistic figure. Additional reserve is still in the deformation of the floor, in the turning energy and contained in the deformation of the residual structure.

Die mit der Erfindung erzielten Vorteile bestehen insbeson­ dere darin, daß die Passagiere beim Aufprall in den Sitz ge­ preßt werden. Dabei wird die Fallenergie durch die Knautsch­ zone im Heckbereich, durch die Drehenergie und durch die Ver­ formung des Bodens sowie der Reststruktur aufgenommen.The advantages achieved with the invention are in particular the fact that the passengers on impact ge in the seat be pressed. The fall energy is caused by the crumple zone in the rear area, by the turning energy and by the ver formation of the floor and the rest of the structure.

Claims (5)

1. Notlandevorrichtung für Flugzeuge unter Verwendung ei­ nes Fallschirmes (1), wobei der Fallschirm in einem Raum, vorteilhaft im vorderen oberen Rumpfbereich, gelagert und während einer nicht mehr kontrollierbaren Flugphase ausgestoßen wird, dadurch gekennzeichnet, daß ein oder mehrere Fallschirme (1) zum Einsatz kommen, deren Auftriebs­ kraft das Flugzeug in eine optimale Sturzlage (α) bringt.1. Emergency landing device for airplanes using egg parachute ( 1 ), the parachute being stored in a space, advantageously in the front upper fuselage area and being ejected during a flight phase that can no longer be controlled, characterized in that one or more parachutes ( 1 ) for Use, whose buoyancy force brings the aircraft into an optimal fall position (α). 2. Notlandevorrichtung nach Anspruch 1, dadurch gekennzeich­ net, daß das Rumpfende bis hin zum Passagierraum als Knautschzone ausgebildet wird.2. Emergency landing device according to claim 1, characterized net that the fuselage down to the passenger compartment as Crumple zone is formed. 3. Notlandevorrichtung nach Anspruch 1 und 2, dadurch ge­ kennzeichnet, daß nach Beginn des Aufschlagens der Rest­ rumpf in Drehung versetzt wird und somit zusätzlich Energie aufgenommen wird, die wiederum durchs Erdreich, Fahrwerk und Restrumpfverformung aufzunehmen ist.3. Emergency landing device according to claim 1 and 2, characterized ge indicates that after the start of the service the rest body is rotated and thus additionally Energy is absorbed, which in turn passes through the ground, Chassis and residual hull deformation must be recorded. 4. Notlandevorrichtung nach Anspruch 1, 2 und 3, dadurch ge­ kennzeichnet, daß gegebenenfalls zusätzlich die Flügel (3) mit Hilfe einer Sollbruchstelle abknicken.4. Emergency landing device according to claim 1, 2 and 3, characterized in that optionally additionally bend the wing ( 3 ) with the aid of a predetermined breaking point. 5. Notlandevorrichtung nach Anspruch 1, 2, 3 und 4, dadurch gekennzeichnet, daß der Fallschirm (1) mit geeigneten Hilfsmitteln in kürzester Zeit zur vollen Entfaltung gebracht wird.5. Emergency landing device according to claim 1, 2, 3 and 4, characterized in that the parachute ( 1 ) is brought to full deployment in a very short time with suitable aids.
DE19924214609 1992-05-02 1992-05-02 Emergency parachute to lower complete aircraft - has parachute attached to front of fuselage and rear of fuselage is formed as crumple zone to absorb impact energy Withdrawn DE4214609A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE19924214609 DE4214609A1 (en) 1992-05-02 1992-05-02 Emergency parachute to lower complete aircraft - has parachute attached to front of fuselage and rear of fuselage is formed as crumple zone to absorb impact energy

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19924214609 DE4214609A1 (en) 1992-05-02 1992-05-02 Emergency parachute to lower complete aircraft - has parachute attached to front of fuselage and rear of fuselage is formed as crumple zone to absorb impact energy

Publications (1)

Publication Number Publication Date
DE4214609A1 true DE4214609A1 (en) 1993-11-04

Family

ID=6458059

Family Applications (1)

Application Number Title Priority Date Filing Date
DE19924214609 Withdrawn DE4214609A1 (en) 1992-05-02 1992-05-02 Emergency parachute to lower complete aircraft - has parachute attached to front of fuselage and rear of fuselage is formed as crumple zone to absorb impact energy

Country Status (1)

Country Link
DE (1) DE4214609A1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008048129A1 (en) * 2008-09-20 2010-04-22 Lfk-Lenkflugkörpersysteme Gmbh Missile with at least one brake parachute and fastening device for attaching a brake parachute to a missile
CN104044743A (en) * 2014-07-03 2014-09-17 青岛宏百川金属精密制品有限公司 Tail gas balance system of unmanned helicopter

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008048129A1 (en) * 2008-09-20 2010-04-22 Lfk-Lenkflugkörpersysteme Gmbh Missile with at least one brake parachute and fastening device for attaching a brake parachute to a missile
CN104044743A (en) * 2014-07-03 2014-09-17 青岛宏百川金属精密制品有限公司 Tail gas balance system of unmanned helicopter

Similar Documents

Publication Publication Date Title
DE3827279C2 (en)
EP1283164B1 (en) Supersonic transport device
EP0861780A1 (en) Roll-over preventing method during landing for an air or space vehicle
DE2202411C3 (en) Device for aircraft to break open the cabin roof
DE2852220A1 (en) HORIZONTAL LANDING ARRANGEMENT FOR AIRCRAFT
EP1509448B1 (en) Aircraft comprising a rescue device
DE202015006282U1 (en) Rescue system for aircraft especially Quatrocopter
DE4421139A1 (en) Aircraft with emergency parachute system
DE19847546A1 (en) Airbag system to bring aircraft safely to ground in event of emergency situation
DE4214609A1 (en) Emergency parachute to lower complete aircraft - has parachute attached to front of fuselage and rear of fuselage is formed as crumple zone to absorb impact energy
DE3617294A1 (en) Safety device for rotary-wing aircraft, especially helicopters
DE4208839A1 (en) Aircraft emergency landing parachute - involves parachute released by rocket motor and cable assembly
DE4320470A1 (en) Aircraft airbag
DE10056890B4 (en) Rescue system for an aircraft
EP0599437B1 (en) Escape system for aircraft
DE4124377C1 (en) Aircraft door emergency opening device - has actuator cylinder to swing door outwards and pyrotechnic device may be used
EP0795467B1 (en) Landing method for payloads from air or space missions
DE102017113058B4 (en) space transport aircraft
WO2000034122A1 (en) Method for transporting a payload into outer space
AT410537B (en) Emergency parachute override system for aircraft of any type
DE102019105906B4 (en) aircraft
DE102019118032B4 (en) Seat and aircraft
DE4334567A1 (en) Impact-reducing system for crashing aircraft - uses very large parachutes together with inflated air-bag underneath
DE1101161B (en) Airplane with a separable rescue cabin
DE102005049704B4 (en) Rescue system for victim reduction in helicopter crashes

Legal Events

Date Code Title Description
8122 Nonbinding interest in granting licenses declared
8139 Disposal/non-payment of the annual fee