This report presents the design parameters and the concept of an experimental seat system for advanced aerospace vehicles. Design parameters were developed for a seat system which provides: (1) Comfort and support for long periods, up to 4 hours. (2) Compatibility with the 5th through 95th percentile man. (3) Isolation for the crew member from the severe environment of high speed, low altitude flight to a level commensurate with proficiency requirements. (4) Protection in the crew escape capsule ejection environment, and to the degree practical, the vehicle crash environment. A seat system concept is presented embodying a microballoon pad system utilized to achieve universality of fit and a high degree of comfort. A restraint system is presented which enhances mans ability to withstand high acceleration loads and, when not in the full restraint position, permits the same degree of flexibility as available from current Air Force restraint systems. Shock mitigation is provided in the longitudinal and vertical axis to reduce the -Gx and +Gz accelerations to a tolerable level. The seat is isolated in the vertical axis from the rough vibratory environment of high speed, low altitude flight. A presentation of restraint systems previously developed for crew protection in a high acceleration environment, is presented in the Appendix. (Author)


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    Personnel Seating Research for Air Force Aerospace Vehicles

    Peterson, Richard L. | SAE Technical Papers | 1964


    Personnel seating research for air force aerospace vehicles

    Peterson, R.L. | Engineering Index Backfile | 1964


    Crew Escape Criteria for Two Stage Recoverable Aerospace Vehicles

    C. J. Cohan / C. G. Place / H. T. Webster et al. | NTIS | 1964


    SEATING SYSTEM FOR VEHICLES

    BOCCHINO BARTOLOMEO / CAIERO DARIO / CASTIGLIONE MORELLI ALFREDO et al. | Europäisches Patentamt | 2020

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    Aerospace crew station design

    Carr, Gerald P. / Montemerlo, Melvin D. | NTRS | 1984