DE1626080A1 - Solid rocket engine - Google Patents

Description

1628080

DYNAMIT HOBEL AKTIENGESELLSCHAFT Troisdorf, District Cologne

Plague rocket engine

The invention "relates to a solid rocket engine that does not burn from the inside out with a kämmergebunderjßn, i.e. not firmly connected to the combustion chamber, nen, propellant is equipped.

The problem with such solid rocket engines lies in the need for pressure to be applied as simultaneously as possible build inside and outside the propellant charge, with outside the gap-shaped space between the propellant charge outer surface and the combustion chamber wall is meant. Prevents the formation of the engine and / or the arrangement of the engine parts after ignition the at least approximately simultaneous Pressure build-up inside the propellant and in the gap between the propellant and combustion chamber wall, a is created inside the propellant Overpressure, which can cause the propellant body to tear. Such a tear would cause the burning Increase the surface of the propellant charge almost instantly and accordingly, more propellant gas would develop. That in turn would lead to an unwanted and also impermissible increase in pressure lead, which would usually entail the dismantling of the entire engine.

The purpose of the invention is to avoid these disadvantages. According to the invention this is achieved in that on the nozzle side ■ End of the propellant charge a gap between the with an insulating layer provided propellant outer surface and the combustion chamber wall tightly sealing seal is arranged that the Ignition charge is arranged at the nozzle-side end of the propellant charge, that in the clear cross-section of the nozzle a combustion chamber up to the

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reaching a given internal pressure tightly sealing Damming member is arranged, and that at the end opposite the nozzle, the combustion chamber with the gap between the outer surface of the propellant charge and the combustion chamber wall is held in connection.

The result of the ignition and the subsequent burning of the powder ' Propellant gas that is constantly developing on the surface can result the damming of the nozzle cross-section initially not by the Flow through the nozzle, but remains trapped in the combustion chamber. The one initially inside the propellant charge is not heated air is thereby provided via the air provided at the end opposite the nozzle The overflow opening is pressed into the outer gap, which means that the propellant charge inside and the gap are the same on the one hand Pressure sets and by pushing the not yet heated air cushion into the gap, on the other hand, a gentle effect on the outer insulation of the propellant.

Only after the pressure in the combustion chamber has reached the predetermined value has reached, ejecting the dam will open the nozzle opening released and starts the propellant in opposite Direction to flow, with a constant pressure equalization between the propellant interior and the gap.

The invention is shown in the drawing in one embodiment shown and will be explained in the following on the basis of this. It demonstrate

1 shows an engine in an axial section the ignition and

Fig. 2 shows the same engine after ignition outcast damnation.

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The propellant charge provided with insulation 2 on its outer surface 1 of the internal burner type faces the combustion chamber wall open the gap 4, which is attached to the rear end of the combustion chamber wall " Nozzle 5 is by means of the. the ignition 7 carrying damper 6 tightly closed. At the other end of the combustion chamber wall the propellant charge interior 8 is connected to the gap 4 through the overflow opening 9.

When the engine is ignited, the press on the ignition 7 and the burning powder surface, the hot gases developed the unheated air that was present in the tree 8 for so long in the direction of the arrow in front of you and thus out of space 8 over the overflow opening 9 into the gap 4 until such a Pressure is reached that is sufficient for the ejection of the damper. From now on the hot propellant gases start in the through the The direction indicated by the arrow in FIG. 2 is to flow away via the now open nozzle, generating thrust *; ,

109811/0241

Claims (1)

Pat en t a η s ρ r ü c h Pe rocket engine with a non-chamber-bound from the inside to the outside burning propellant charge, characterized in that at the nozzle-side end of the propellant charge a seal which tightly closes the gap between the outer surface of the propellant charge provided with an insulating layer and the combustion chamber wall is arranged Propellant charge is arranged that in the clear cross-section of the nozzle a damming member which tightly closes the Brennrauabis to achieve a predetermined internal pressure is arranged, and that at the end opposite the nozzle the combustion chamber is kept in connection with the gap between the propellant charge outer surface and the combustion chamber wall. ■ '..- ■ 10 9 8-1 1/024 1 GOPY