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Control propulsion unit, especially for exerting transverse forces on a missile
| Details |
Inventors: Kranz, Walter;
Assignee: Messerschmitt-Bolkow-Blohm GmbH (Munich, DE)
Primary Examiner: Jordan; Charles T.
Assistant Examiner: Lieberman; Rochelle
Attorney, Agent or Firm: Kenyon & Kenyon
A control propulsion unit with a solid propellant (4) and a discharge nozzle, through which the propellant gases emerge into the open air, especially to exert transverse forces on a missile. To be able to precisely, quantitatively regulate the transverse forces, in accordance with the invention, it is proposed to extinguish the propellant in a controlled operation by reducing the clamping of the control propulsion unit, for example, by enlarging the discharge port for the propellant gases. |
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DETAILED DESCRIPTION An object of the present invention is to provide a control propulsion unit of the type discussed having a simple design, which will enable the thrust of the propulsion unit and especially the active duration of the transverse force to be precisely adjusted.
The above and other objects of the invention are achieved by a control propulsion unit having a solid propellant and a discharge nozzle, whereby the propellant gases emerge through the discharge nozzle in the open air, especially to exert transverse forces on a missile, wherein the control propulsion unit includes means which can be controlled after the solid propellant is ignited, for reducing the clamping of the control propulsion unit, said means for reducing the clamping comprising means for reducing the ratio between the combustion surface of the propellant and the narrowest cross-section of the discharge nozzle to such an extent that the propellant extinguishes automatically.
Accordingly, the invention takes a path, which differs from the previous solutions.
In accordance with the invention, the propellant is extinguished by noticeably reducing the clamping of the control propulsion unit.
The clamping of a control propulsion unit is understood to be the ratio between the combustion surface of the propellant and the narrowest cross-section of the discharge nozzle.
If the clamping is reduced five times, for example, it turns out that the propellant is automatically extinguished within 1 to 2 milliseconds.
In this case, the discharge nozzle originally had a smallest diameter of 1.
5 mm, and the diameter of the combustion surface of the propellant amounted to approximately 25 mm.
The propellant is suddenly automatically extinguished, when the diameter of the outlet is enlarged to 3 to 3.
5 mm.
This clamping reduction can be achieved, for example, with a design whereby the discharge nozzle is situated in a piston, which is guided in the missile and is expelled by the propellant gases, for example, after a clamping ring is loosened
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