PROPOSED DESIGN OF AN IMPROVED CAPABILITY ELECTRONIC EJECTION SEQUENCER (ICEES)

Award Information
Agency:
Department of Defense
Branch
Navy
Amount:
$46,083.00
Award Year:
1993
Program:
SBIR
Phase:
Phase I
Contract:
n/a
Award Id:
20752
Agency Tracking Number:
20752
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
31 Highview Avenue, Nanuet, NY, 10954
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
n/a
Principal Investigator:
Paul H. Frisch
(914) 623-7258
Business Contact:
() -
Research Institution:
n/a
Abstract
In multi-place jet aircraft the ejection problems are compounded beyond the head, neck and spinal injuries, windblast exposure and flail injuries, but now also include collision proababilities with other ejectees. The problem actually becomes one of collision avoidance by timing or sequencing the ejection to optimize a clean contact free egress, and controlling the rocket thrust magnitude and/or direction The propsed solution focuses on the monitoring of the multiple ejection seat inertial positions and controlling the sequencing of the seat firing and control of the ejection seat gimbled rocket motors to avoid overlap of the multiple ejection seat envelopes. In order to properly control the gimble or sequence the ejection the seat envelope and relative real time position in 3D space of each seat and the aircraft and possibly the canopy must be known. The control criteria for crash avoidance must be established and finally a detailed knowledge of the ejection platform and projected ejection trajectories will be necessary. It is proposed that each ejection platform, canopy, and aircraft itself be instrumented with a microprosser based acceleration measuring device tracking of each inertial coordinate system as measured relative to the ground. The dosimeters will measure the platform linear and angular accelerations via commercial available sensors, and attitude of each platform. The position information can be compared to the positions of the other monitored platforms and projected ejection envelope or profile. Based on the comparison the ejection sequencing can be altered to maximize impact avoidance, or the rocket thrust vector can be controlled to alter the seat ejection envelope.

* information listed above is at the time of submission.

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