US 4,527,758 AGranted

Deployment sequence mode selection system for aircraft ejection seat

AssigneeThe United States of America as represented by the Secretary of the Navy

InventorsPeter Ayoub, Alan Cantor

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Abstract

An electronic system for selecting the proper mode sequence for deploying a ecovery parachute from an aircraft ejection seat. The system senses altitude, airspeed, and sink rate; and compares these to predetermined reference signals. The system also incorporates logic circuits and time delay circuits. The logic circuits are arranged to select one of four time delays depending on the status of the various parameters relative to the reference signals.

Claims5

Dependent claims

A system for selecting the release time of a parachute after ejection from an aircraft comprising:

sensor means for producing sensor signals indicative of altitude, airspeed and sink rate of the aircraft immediately prior to ejection;
and
processor means responsive to said sensor signals for providing a parachute release signal a predetermined delay time after ejection, the time being selected in accordance with the following criteria:
t.sub.1 to t.sub.2 when S.sub.a <R.sub.a, S.sub.b <R.sub.b, and S.sub.c >Rc, or
t.sub.2 when S.sub.a <R.sub.a, S.sub.b <R.sub.b, and S.sub.c <R.sub.c, or
t.sub.3 when S.sub.a <R.sub.a and S.sub.b >R.sub.b, or
t.sub.4 when S.sub.a >R.sub.a,
where
t.sub.1, t.sub.2, t.sub.3 and t.sub.4 =delay times of respectively increasing durations,
S.sub.a, S.sub.b and S.sub.c =sensor signals indicative of the aircraft altitude, airspeed and sink rate, respectively, and
R.sub.a, R.sub.b and R.sub.c =minimum altitude, airspeed and sink rate, respectively, for optimium recovery envelopes.

8 more elements

A mode selection system for controlling the deployment of a parachute connected to a load ejected from an aircraft, said system comprising:

(A) first sensor means for generating a first sensor signal when the altitude of the aircraft just prior to ejection differs from a first reference signal;
(B) second sensor means for generating a second sensor signal when the airspeed of the aircraft just prior to ejection differs from a second reference signal;
(C) third sensor means for generating a third sensor signal when the sink rate of the aircraft just prior to ejection differs from a third reference signal;
and
(D) processor means responsive to said sensor signals for generating a deployment signal after one of a plurality of predetermined delay times from ejection, said processor means including:
(1) first enabling means for generating a system enable signal when ejection is initiated,
(2) logic means for generating a logic signal in response to the sensor signals and the system enable signal, and said logic means including:
(a) second enabling means responsive to the system enable signal for providing a sequence of delayed enabling signals, said second enabling means including:
(i) gating means responsive to the system enable signal for providing an initiating signal,
(ii) a first pulse generator responsive to the initiating signal for providing a first delayed enabling signal to the control means,
(iii) a second pulse generator responsive to the first delayed enabling signal for providing a second delayed enabling signal to the control means,
(iv) a third pulse generator responsive to the second delayed enabling signal for providing a third delayed enabling signal to the control means, and
(v) a fourth pulse generator responsive to the third delayed enabling signal for providing a fourth delayed enabling signal to the control means,
(b) control means for providing a control signal in response to a preselected combination of one of the sensor signals, the system enable signal, and one of the delayed enabling signals, and
(c) delay means for providing the logic signal in response to the control signal;
and
(3) signal means for providing the deployment signal in response to the logic signal.

14 more elements

A mode selection system for controlling the deployment of a parachute connected to a load ejected from an aircraft, said system comprising:

(A) first sensor means for generating a first sensor signal when the altitude of the aircraft just prior to ejection differs from a first reference signal;
(B) second sensor means for generating a second sensor signal when the airspeed of the aircraft just prior to ejection differs from a second reference signal;
(C) third sensor means for generating a third sensor signal when the sink rate of the aircraft just prior to ejection differs from a third reference signal;
and
(D) processor means responsive to said sensor signals for generating a deployment signal after one of a plurality of predetermined delay times from ejection, said processor means including:
(1) first enabling means for generating a system enable signal when ejection is initiated,
(2) logic means for generating a logic signal in response to the sensor signals and the system enable signal, said logic means including:
(a) second enabling means responsive to the system enable signal for providing a sequence of delayed enabling signals,
(b) control means for providing a control signal in response to a preselected combination of one of the sensor signals, the system enable signal, and one of the delayed enabling signals, said control means including:
(i) first gate means for providing the control signal in response to the first sensor signal, system enable signal, and first delayed enabling signal,
(ii) second gate means for providing the control signal in response to the second sensor signal, system enable signal, and second delayed enabling signal;
(iii) third gate means for providing the control signal in response to the third sensor signal, system enable signal, and third delayed enabling signal,
(iv) fourth gate means for providing the control signal in response to the system enable signal and the fourth delayed enabling signal, and
(v) said second, third, and fourth delayed enabling signals being progressively later than the first delayed enabling signal, and
(c) delay means for providing the logic signal in response to the control signal;
(3) signal means for providing the deployment signal in response to the logic signal;
and
(4) locking means for inhibiting said first enabling means in response to the control signal.

15 more elements

Dependencies are inferred from the claim text.

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Abstract