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Aircraft ejection system
| Details |
Inventors: Martin, John S.;
Assignee: Engineering Patents & Equipment Limited (St. Peter, GB1)
Primary Examiner: Basinger; Sherman D.
Assistant Examiner: Corl; Rodney
Attorney, Agent or Firm: Spencer & Frank
Each of two aircraft ejection seats, initially mounted in a side-by-side arrangement in an aircraft, has a primary rocket motor for accelerating the seat/airman combination on ejection, by producing a thrust vector substantially through the center of gravity of the combination, and having a substantial component along that axis of the seat/airman combination about which the combination is rotationally balanced, which lies closest to parallelism with the vertical center line of the airman. To ensure separation, upon ejection, between the two ejection seats, each has, in addition to its primary rocket motor, a lateral thrust rocket motor arranged to produce a transverse thrust vector which passes through said axis at a position spaced from said center of gravity, so as to produce a rotational moment acting on the combination, whereby the two seats are caused to move in respective arcs diverging from one another, but without spinning about said axis. |
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DETAILED DESCRIPTION I claim: 1.
An ejection system for an aircraft for two airmen, comprising: an ejection seat for each airman; and means for ejecting the ejection seat/airman combinations from the aircraft so that the combinations travel along respective paths divergent from one another, said means including, for each seat/airman combination, a primary rocket motor, a further, lateral thrust rocket motor, means mounting the primary rocket motor for accelerating the combination in a predetermined direction relative to the seat/airman combination by producing a thrust vector extending through or substantially through the centre of gravity of the combination, and having a substantial component along the principal axis of the combination, said principal axis being that axis of the airman/seat combination about which the combination is rotationally balanced and which lies closest to parallelism with the vertical centre line of the airman, said principal axis extending through or substantially through the centre of gravity of the combination but being non-parallel to said thrust vector, and means mounting the further, lateral thrust rocket motor for producing a further thrust vector which extends laterally with respect to the fore and aft axis of the seat in a direction transverse to the direction of the thrust vector produced by the primary motor, but which passes through, or substantially through the principal axis of the seat/airman combination, at a position spaced from said centre of gravity, so as to produce a rotational moment acting on the combination, wherein the lateral thrust motor associated with each ejection seat is arranged to produce a rotational moment acting on the seat in the opposite rotational sense from the rotational moment acting on the other seat.
2.
The ejection system of claim 1 wherein, for each seat/airman combination, said thrust vector of the primary rocket motor lies in the same fore and aft plane, relative to the seat/airman combination, as said principal axis
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