Aeronautics and astronautics – Aircraft structure – Fuselage and body construction
Patent
1998-02-13
2000-03-28
Poon, Peter M.
Aeronautics and astronautics
Aircraft structure
Fuselage and body construction
B64D 2510
Patent
active
060420545
DESCRIPTION:
BRIEF SUMMARY
FIELD OF THE INVENTION
The invention relates to means for emergency abandonment and can be used to save the crew in the case of aircraft breakdown.
BACKGROUND ART
A method is known for abandonment of an aircraft by using a tractor rocket engine which pulls a crew member out by means of a tractor cable, and then using a parachute.
A method is also known for saving members of a crew using a catapult seat, the method comprising catapulting a member of the crew from the cabin together with the seat, and subsequently opening a parachute located in the seat and separating the crew member from the seat.
These methods have two basic drawbacks. In the first place, the parachute is put into operation with some delay in time after the seat with the pilot has gone a certain distance from the aircraft. In the second place, these methods can only be realized by means of systems having a sufficiently large mass, but this is unacceptable for realizing such methods on light aircraft.
DISCLOSURE OF THE INVENTION
The object of the invention is to create a very light and effective system for the emergency abandonment of an aircraft by a member of the crew, which can be used with aircraft having a flight speed up to 500-600 km/hour.
In order to achieve the indicated object, a method is proposed for the emergency abandonment from an aircraft which comprises catapulting a member of the crew and a rescue parachute. At first, a pack with the parachute is catapulted and then a member of the crew.
Catapulting the member of the crew is carried out behind a suspension-linkage system by means of an ejection mechanism, wherein the force of the latter is directed through the center of gravity of the member of the crew.
Furthermore the catapulting speed and the sequence of operation of the ejection mechanisms are so chosen that at the moment the member of the crew is separated from the aircraft, the free ends and shroud lines of the parachute are stretched to their full length.
In the case of catapulting pairs, in order to ensure safety, the direction of catapulting the parachute pack and member of the crew is at an angle of 15-20.degree. relative to the plane of symmetry of the aircraft, and if necessary the catapulted parachute pack may be used as a means for breaking the transparency of the cockpit canopy of the aircraft.
BRIEF DESCRIPTION OF THE DRAWINGS
The instant invention is explained by the drawings where FIG. 1 shows a schematic diagram of a presupposed device for carrying out the method, FIG. 2 shows the moment of separation of a member of the crew from an aircraft, and FIG. 3 shows a scheme for pair abandonment from an aircraft.
The presupposed invention as shown in FIG. 1 comprises a seat 1, a mechanism 2 for ejecting a member of the crew, a towing bridle 3 and a lock 4, which are connected to the upper part of an internal tube 5 of the mechanism ejecting the member of the crew and a suspension-linkage system of the crew member 9 (FIG. 2).
Two ejection mechanisms are arranged behind the back of the seat: one for catapulting the member of the crew and the other, ejection mechanism 6, for catapulting the parachute pack.
When the catapulting drive is actuated, the telescopic ejection mechanism 6 for the parachute pack 7 (FIG. 1) is put into action. During the first part of the predetermined movement of that mechanism, the telescopic ejection mechanism 2 (FIG. 1) is actuated by means of mechanical coupling, and a member of the crew is catapulted by means of mechanism 2. During further movement of the parachute pack 7 (FIG. 2), the transparency of the cockpit canopy is broken and then the shroud lines are stretched out and the canopy of the parachute 8 is opened (FIG. 2).
At the beginning of the movement of the ejection mechanism 2 (FIG. 1) for the member of the crew, the suspension-linkage system 2 (FIG. 1) is automatically disconnected from the seat 1 (FIG. 1) and, further, the ejection mechanism 2 transmits a speed to the member of the crew which is sufficient to ensure a safe trajectory of his movement in respect of
REFERENCES:
patent: 1906091 (1933-04-01), Pendergast et al.
patent: 2671622 (1954-03-01), Saulnier
patent: 3014678 (1961-12-01), Stencel
patent: 3542319 (1970-11-01), Duncan et al.
patent: 4709885 (1987-12-01), Martin
patent: 5104066 (1992-04-01), Aronne
Otkrytoe Aktsionernoe Obschestvo Nauchno Proizvodstvennoe
Palo Francis T
Poon Peter M.
LandOfFree
Emergency escape method for an aircraft crew does not yet have a rating. At this time, there are no reviews or comments for this patent.
If you have personal experience with Emergency escape method for an aircraft crew, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Emergency escape method for an aircraft crew will most certainly appreciate the feedback.
Profile ID: LFUS-PAI-O-1318823