DE202013100254U1 - Combustion chamber for solid rockets - Google Patents

Abstract

Combustion chamber for solid rockets, comprising at least one container in which takes place by supplying one or more solid fuel (3) and an oxidizer, an exothermic reaction, wherein at the combustion chamber for the introduction of the reactants and for the removal of the gases formed in the reaction more Openings are provided, characterized in that the combustion chamber has at least one segmented shell combustion chamber (2), wherein the shell combustion chamber (2) is designed and aligned such that the forces directed inwardly in the shell combustion chamber (2) in the at least one central combustion chamber ( 1) counteract outwardly directed forces and partially cancel them.

Description

Technical area

The present invention relates to a novel combustion chamber for solid rockets, comprising at least one container in which takes place by supplying one or more solid fuels and an oxidizer (oxidizer) an exothermic reaction, wherein at the combustion chamber for the introduction of the reactants and for the removal of provided in the reaction gases are provided a plurality of openings.

State of the art

A solid rocket is a rocket with a drive set of solid material (fuel). Distinctions are made between front burners and central burners. The entire interior of a solid rocket is also the combustion chamber at the same time. The combustion of the rocket fuel involves high pressures, so the walls must be made of high strength and thick wall steel or carbon fiber reinforced plastics. Since with increasing diameter and increasing length of the solid rocket, the load of the combustion chamber wall at the same combustion chamber pressure increases more and more, the walls must inevitably get thicker wall and therefore heavier. Thus, the empty mass of a solid rocket increases in comparison to the total mass with increasing size more and more, which also leads to a limitation of the maximum mass technically possible with solid rockets.

Presentation of the invention

The present invention is based on the object to provide a combustion chamber configuration for a solid rocket, which optimizes the empty to full mass ratio of the solid rocket.

According to the invention the above object is achieved with the features of claim 1. Advantageous embodiments of the combustion chamber according to the invention are specified in subclaims.

Thereafter, a combustion chamber of the type mentioned is characterized in that the combustion chamber has at least one segmented shell combustion chamber (single or multi-shell), wherein the shell combustion chamber is configured and oriented such that in the shell combustion chamber inwardly directed forces in the at least one central combustion chamber counteract outwardly directed forces and partially cancel them.

The advantage of the segmented shell-type combustor according to the invention is, in particular, that the central combustor wall can be designed to be considerably thinner-walled and therefore significantly lighter in design.

Brief description of the drawings

Other objects, features, advantages and applications of the invention will become apparent from the following description of an embodiment with reference to the drawings.

All described and / or illustrated features, alone or in any combination form the subject matter of the invention, regardless of the summary in individual claims or their dependency.

In the drawing shows

1 the combustion chamber according to the invention.

Embodiment of the invention

How out 1 As can be seen, the combustion chamber has a plurality (for example three) segmented shell combustion chambers 2 on, which by appropriate Segmentwandungen 6 are divided.

Depending on the purpose, the combustion chamber to the outside and / or through other shell combustion chambers 2 be extended. The bowl burning chamber 2 can be divided into three or more segments. This makes it possible to use different solid fuels 3 to use. For example, it is possible in the central combustion chamber 1 a solid fuel 3 with a higher burning rate and a higher temperature, on the other hand in the bowl burning chamber 2 a solid fuel 3 to use at a lower burn rate and a lower temperature.

The combustion chamber according to the invention is not limited in its execution to the above-mentioned preferred embodiments. Rather, a variety of design variations are possible, which make use of the solution shown even with fundamentally different type of execution.

List of reference numbers

LIST OF REFERENCE NUMBERS

1

central combustion chamber

2

bowl combustion chamber

3

Solid fuel

4

Zentralbrennkammerwandung

5

Schalenbrennkammerwandung

6

Segmentwandung

Claims (3)

Combustion chamber for solid rockets, comprising at least one container in which by supplying one or more solid fuels ( 3 ) and an oxidizer takes place an exothermic reaction, wherein a plurality of openings are provided on the combustion chamber for the introduction of the reactants and for the removal of the gases formed during the reaction, characterized in that the combustion chamber at least one segmented shell combustion chamber ( 2 ), wherein the shell combustion chamber ( 2 ) is designed and oriented in such a way that in the shell combustion chamber ( 2 ) inwardly directed forces in the at least one central combustion chamber ( 1 ) counteract outwardly directed forces and partially cancel them. Combustion chamber according to claim 1, characterized in that the combustion chamber to the outside and / or by further shell-burning chambers ( 2 ) is extended. Combustion chamber according to claim 2, characterized in that in the combustion chambers ( 1 . 2 ) different solid fuels ( 3 ) are included.

Images