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23 records (took 0.015 seconds)

    2.
    发明专利
    未知

    公开(公告)号：DE2055707C1

    公开(公告)日：1987-10-22

    申请号：DE2055707

    申请日：1970-11-12

    Applicant: AEROSPATIALE

    Inventor： STAUFF EMILE ,  GUILLOT JEAN ,  PINEL ANDRE

    IPC: F42B17/00 ,  F42B15/20

    Abstract: The embodiment described comprises a shell (10), an engine compartment (9) comprising a submarine propulsion unit (7) with jet vanes (8) and a nozzle, an electronic guidance box (11), a thermal battery (12), the releasing of the missile being obtained at a moment chosen by an acceleration communicated to a piston (17) towards the missile so that it forces its way through the front 19 of the shell. The invention applies in particular to any sea/land or sea/sea weapon-carrying marine vehicle.

    MISSILE CONTROL SYSTEM BY MEANS OF LATERAL GAS JETS
    4.
    发明专利
    MISSILE CONTROL SYSTEM BY MEANS OF LATERAL GAS JETS 未知

    公开(公告)号：DE3370072D1

    公开(公告)日：1987-04-09

    申请号：DE3370072

    申请日：1983-11-22

    Applicant: AEROSPATIALE

    Inventor： RAYNAUD JACQUES ,  JOLIVET PIERRE ,  DARMOIS JEAN ,  GUILLOT JEAN

    IPC: B64G1/26 ,  B64C15/14 ,  F42B10/60 ,  F42B10/66 ,  F42B15/033

    Abstract: A steering system for a missile provided with aerodynamic surfaces such as fins comprises a gas generator and lateral nozzles through which the gas generated by the gas generator emerges. The nozzles are arranged to lie between adjacent pairs of the aerodynamic surfaces, to project beyond the fuselage of the missile and to have an oblong cross-section, the largest dimension of which lies substantially parallel to the longitudinal axis of the missile. The gas flow through the nozzles is controlled by complete or partial closing of the nozzles. The shape and placement of the nozzles minimizes changes in the aerodynamic characteristics of the missile caused by interaction between the gas jets emerging from the nozzles and the flow of air over the aerodynamic surface of the missile.

    5.
    发明专利
    未知

    公开(公告)号：FR2536720A1

    公开(公告)日：1984-06-01

    申请号：FR8219996

    申请日：1982-11-29

    Applicant: AEROSPATIALE

    Inventor： RAYNAUD JACQUES ,  JOLIVET PIERRE ,  DARMOIS JEAN ,  GUILLOT JEAN

    IPC: B64G1/26 ,  B64C15/14 ,  F42B10/60 ,  F42B10/66 ,  F42B15/18

    Abstract: A steering system for a missile provided with aerodynamic surfaces such as fins comprises a gas generator and lateral nozzles through which the gas generated by the gas generator emerges. The nozzles are arranged to lie between adjacent pairs of the aerodynamic surfaces, to project beyond the fuselage of the missile and to have an oblong cross-section, the largest dimension of which lies substantially parallel to the longitudinal axis of the missile. The gas flow through the nozzles is controlled by complete or partial closing of the nozzles. The shape and placement of the nozzles minimizes changes in the aerodynamic characteristics of the missile caused by interaction between the gas jets emerging from the nozzles and the flow of air over the aerodynamic surface of the missile.

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