The sensor is for energizing an electrical circuit at a predetermined time or elevation after re-entry of a space vehicle into the earth's atmosphere. In an embodiment, the heat sensitive element is a predetermined thickness of the ablation material of which the nose is constructed. The ablation material has a rate of disintegration that is very closely predictable so that after a predetermined amount of ablation, a switch within the vehicle nose is actuated to energize the electrical circuit.


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    Titel :

    Space Vehicle Reentry Sensor


    Beteiligte:
    J. M. Perkins (Autor:in) / R. J. Twiford (Autor:in)

    Erscheinungsdatum :

    1965


    Format / Umfang :

    1 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch