DE1526837A1 - Solid rocket system - Google Patents

Description

NITROCHEMISTRY. Essen, March 16, 1966

GmbH. Pat / KU / Se

- Case 865 -

Solid rocket system

The invention relates to solid fuel rockets that are equipped with a progressively burning propellant and relates to sin new rocket system with which the difficulties encountered during Ignition of such propellant charges have so far occurred to be overcome.

It is known that in rocket propellants by installing pieces of wire, Metal threads or other shaped metallic bodies to increase the burning rate,

The increase is particularly great when oriented in the focal direction continuous metal wires are incorporated, whereby the different effectiveness of the wires of different metals by the different Thermal conductivity and meltability is conditional.

In principle, the increase in the burning rate is achieved in that When it burns, the metal bodies in the flame zone lead heat into the propellant and become conical around them, for example in the case of metal threads Form depressions in the propellant.

The increase in the burning rate corresponds to the increase in surface area that occurs due to the formation of the conical depression.

One makes of this possibility to increase the burning speed like to use it with stimulators, because with such propellants one shortening burning time is often desired and manufacturing, e.g., pulling-in of metal wires means no difficulty.

BATH ORIGINAL

909851/0731

The combustion chamber nozzle must be designed for dar-like propellants in such a way that that after the occurrence of normal burn-up, i.e. after the final formation a certain chamber pressure is maintained in the conical indentations. Difficulties arose when burning such propellants because the small focal area present at the beginning is not able to deliver as much gas at the given nozzle as for a pressure build-up in the chamber is necessary to ensure a safe burning of the propellant. The surface of a forehead burner is e.g. after training of the conical indentations 3 - 4 times what was originally present at the time of burning. This can be remedied, for example, by using Preforming the conical indentations around the wires or making additional grooves to enlarge the initial focal area, in order to carry out the firing more safely. These measures are cumbersome, time-consuming and in part not desirable or possible in terms of labor.

Similar difficulties arise with other progressively burning propellants, like internal burners.

These difficulties are solved by the solid rocket system according to the invention, that from a main propellant with progressively burning surface and one or more auxiliary clauses and auxiliary clauses exists, eliminated. This propellant combination is characterized in that it also has the following elements individually or in between the nozzle and the main propellant Combination contains,

a) an auxiliary propellant that burns for a period of seconds with decreasing gas evolution,

b) an ignition charge, which is between the main propellant and auxiliary propellant is arranged

c) Damage of the main propellant charge opposite the dead space dar Kammar and dar Nozzle opening, in particular caused by öina appropriate training

the auxiliary or guidance sentence.

8098 S 1/0731 MD onKBN «.

The ignition rate can often be more expedient than on the main propellant rate applied heat-burning firing layer be formed, the the burning of the main fuel makes it easier.

By the aforementioned measures it is achieved that in the dead space of Combustion chamber such a gas pressure cushion is created as it is for a safe burn-up and burn-up of the propellant charge is necessary in the time until the final burning surface is formed.

Since the burning surface of the main propellant charge up to a constant maximum increases, which is obtained during the further burning remains, the gas development of the auxiliary propellant or ignition rate must decrease accordingly.

measures

This can be achieved dunh different /, which can also be combined with each other.

Once, by means of the geometric configuration of the auxiliary propellant or ignition set, the gas delivery to maintain the karamer pressure can be controlled. For this purpose, an embodiment as Star profile or similar configuration advantageous. In addition, through the chemical structure of the auxiliary propellant charge or ignition charge, it can be achieved that the gas formation is necessary Dimension runs degressively.

Those skilled in the art are numerous within the scope of the invention Possibilities for the realization given.

Furthermore, it is proposed according to the invention by a corresponding Construction of the ignition or auxiliary propellant first the burning surface damaging the main propellant against the rest of the dead space in the chamber and the nozzle opening.

909851/0731

This can be done in a technically simple manner by the fact that, for example, the auxiliary relief by appropriate shaping upper a certain burning time a damn to the dead space of the chamber and to the Forms nozzle opening.

Can be particularly advantageous for burning the main propellant it may be that the anfeusrungssatz as a hot-burning layer directly on the main propellant is applied.

The measures a to c listed above can be adapted within the missile system according to the invention in each case by adapting the selected main propellant and its burn-up ratio to the ballistic requirements Adjust requirements.

The missile system according to the invention is shown in the drawings namely show in detail:

Figure 1-3, as well

"7-9 a propellant charge with inlaid metal threads and a Auxiliary propellant in different stages of the burn

"4 a similar main propellant with auxiliary propellant and firing unit

"5 a similar main propellant with a firing layer on the Haupttreibeatz as well as a dam opposite the combustion chamber dead space

^H 6 has an internal burner with a main propellant as well as an auxiliary propellant and a firing unit.

The drawings can be understood without further ado, and specifically denote same numbers same parts:

909851/0731

1 main driver

2 metal thread

3 auxiliary propellant

4 lighting kit

5. Damnation

6 combustion chambers

7 nozzle

8 cheering up

9 main driver (internal burner)

909151 / OTH

Claims (1)

Claims i) Solid rocket system consisting of a main propellant with progressively burning surfaces and one or more auxiliary propulsion seats, characterized, that there are also the following between the nozzle and the main propellant Elements separately or in combination contains: a) an auxiliary propellant that burns for a period of seconds with decreasing gas evolution, b) a firing fuel between the main fuel and Auxiliary propellant is arranged, 2l Solid rocket syate * according to claim 1, can be characterized by the fact that auxiliary or Anfauarungssatz are designed in such a way that they are a dam of the main traction a against the Tatraum form. 3) solid rocket system according to claim 1, characterized in that the Aufauarungaatx ala haiBbrannanda Anfauarungaachicht on the main propellant trained let. 109851 / OtIt bad 4) Faststoffraketensysteni according to claim 1, characterized in that the decreasing gas development of the auxiliary propellant is caused by its geometric design in a manner known per se. 5) solid rocket system according to claim 1, characterized in that the decreasing gas evolution of the auxiliary propellant charge is brought about by the chemical structure in a manner known per se. 6) Solid rocket system according to claim 1, characterized in that the measures of claims 4 and 5 are used in combination. 909861/0731 Blank page