DE1626083A1 - Propellant charge for rocket engines - Google Patents

Description

1626083 Andrejewski & Honke patent attorneys

Physicist

Dr. Walter Andreevsld

"_ -Ο, _{/ TT} graduate engineer

Lawyer files: 2 ₉ 28l / Vg D "-Ing. Manfred Honke

Essen, December 8, 1969 Kettwig ·! · Strass · 36 (th)

Patent application
Les Forges De Zeebrugge SA
145, rue Bellenay
Herstal-Ie z-Lie * ge / Belgium

Propellant charge for rocket engines.

The invention relates to a propellant charge for rocket engines, Consists of two chemically different compositions, coordinated with one another with regard to the desired performance characteristics, e.g. constant thrust Propellant charge containing individual charges and one of these Propellant physically separated ballistic aid.

Such from a two-part propellant and one of them separate ballistic aid existing propellant charges for rocket engines were developed to be as constant as possible to achieve strong thrust.

0098H / 1156

it. / \ nuerurigiigoB. v.

Patent attorneys Dr. W. Andrejewski, Dr. M. Honke, 43 Essen, Kettwiger Strasse

It has already been proposed (US Pat. No. 2,816,418) to embed ammonium nitrate as an auxiliary substance in a rubber-like mass and thus to envelop the propellant, this envelope acting as an inhibitor coating and intended to increase the thrust. However, it cannot be prevented that in the initial phase of the flight an afterburning at the exit of the combustion chamber occurs, which results in a considerable increase in the temperature of the gases. When shot down from the plane revealed This sharp rise in temperature even caused the failure of the reaction motors of the aircraft concerned, but its consequences were not further discussed need to be grounded.

The invention has therefore set itself the task of providing a propellant charge of the aforementioned type in such a way that the exhaust gases are cooled to the extent that the aforementioned Damage cannot occur and, in addition, excessive smoke development is prevented.

For this purpose, the invention proposes that this ballistic Auxiliary at least one oxide of the metals molybdenum, tin, chromium, which is dispersed in a thermoplastic binder, Contains tungsten, zircon, cerium, lanthanum, cobalt, nickel, iron and magnesium. In addition, the ballistic aid contain at least one of the following inorganic salts: potassium sulfate, potassium nitrate, potassium chloride, barium nitrate and potassium perchlorate, and it may also contain silicon dioxide or magnesium silicate.

0098U / 1 156

Potentanwälte Dr. W. Andrajtwski, Dr. M. Honk ·, 43 Essen, Kettwiger Strass «

Such a ballistic additive, which is separate from the actual propellant and burns in the combustion gases of the propellant, has an effect comparable to the admission of secondary air to a boiler and noticeably _{cools the combustion gases as a result of the conversion of CO and CO 2.}

Such propellant charges can be built up in the most varied of ways and can be arranged in the rocket engine, too naturally qualitatively corresponding to the leg length and find quantitatively different compositions. A propellant charge for a rocket with one in the longitudinal axis Axial cavity of the propellant block arranged ballistic Auxiliary material was, for example, in the following composition used and gave excellent results:

1.) = Propellant:

Nitrocellulose (12.6 % H) Nitroglycerin Propyl-di-N-adipate 2-Nitrodiphenylamine Monobasic Cupric Salicylate Monobasic Lead Resorcylate Candelilla Wax

Parts by weight 51 40 - 50 38 - 0, - 0.1 - 3 ' 1 4.5 2 - 3 1 0.3 o, o8-

2.) Ballistic aid:

potassium sulfate ethyl cellulose dibutyl phthalate

67

IC

- 75

- 15.5

- 7th

OQ98 U / 1 156

BATH ORIGINAL Or. W. An4r «|« wtM, Dr. M. "to *", 49 Imm, KtHwIf * punishment Butyl methacrylate 6.5-10.6 Polyglycol dimethacrylate 0.9-1.62

Benzoyl peroxide 0.09 to 0.16

Molybdenum oxide as required.

Some embodiments of the arrangement of the propellant charge and the ballistic aid are explained in detail below with reference to the accompanying drawings; show it:

FIG. 1 shows various possible arrangements in a schematic manner;

Figure 2 and J5 longitudinal sections through rocket drives;

4 and 5 are cross-sections through the arrangements according to FIGS. 2 and 3 with differently shaped ballistic auxiliary material;

FIGS. 6 and 7 are partial longitudinal sections through a rocket drive; and

FIGS. 8, 9 and 10 show three different forms of training and arrangement of the ballistic aid in FIG greatly simplified representation.

In the various figures, the rocket engine is seen as a whole with the reference number 1, the propellant with 2 and the ballistic aid with 3.

009814/115

Patent Attorney Dr. W. Andrejewski, Dr. M. Honk, 43 Estonians, Kettwifjer Straß

-Figure 1 shows the different ways in which the propellant charge and the ballistic aid can be placed in a rocket engine. Which arrangement one chooses, whether one, several or all of the indicated locations are used, depends on the respective conditions of use.

When the hook tenant rubbed according to Figures 2 and 3 is the propellant 2 as a shaped charge and the ballistic aid 3 as coaxial for this purpose arranged molded body used in the drive cylinder 1, which has an end piece 4, nozzles 5 and pivotable around pin 7 Stabilization flassen 6 carries.

The ballistic aid 3 has in the arrangement according to Figure 4 star-shaped cross-section and 1st on a rigid Support member 8 is applied, which sits on a support rod 9. The propellant 2 consists of a »hollow body old ttwa stern« shaped axial cavity, with the internal invading 9 has about a star-shaped cross-section and the upper one second single charge completes this star to a cylinder.

9 ballistic aid according to Figure 5 forms one self load-bearing hollow cylinder 3 with radial openings 10, through which there is an improvement in the effectiveness. In addition to a The ballistic aid can be designed as a hollow cylinder can also be designed as full cylinders with diametrically penetrating bores «

^009814/1156

Patent Attorney Dr. W. Andrejewski, Dr. M. Honk ·, 43 Essrni, JCeftwlgefSlral · 36 In the arrangement of Figure 6 , a second ballistic.

Auxiliary material 3 used in the form of a corrugated disk at the entrance of the drive. In addition, smooth and, Use multi-layer discs, which can also be perforated. Of course, depending on the requirements, i.e. other shapes are conceivable depending on the effective surface that appears to be required in each case.

In FIG. 7, an additional auxiliary material in the form of a ring 3 is inserted in front of the nozzles in the end piece 4, which in the shape shown has a wide variety of cross-sections _.

! «Iron can. ..; ■ ^.

^: Dia itark echimatised help setoffa 3 are in the training! f j dung · »according to Figure 8 and 9 coaxially la propellant 2 inserted and -

j consist · η of shaped bodies with |

(Flg. B) or continuously (Fig. 9} variable diameter, ti * a

din variable displacement in the long direction of the rocket drive

Take into account the course of the combustion conditions 9 ». You virlauf; ■

you strength biiw. the layer thickness of this molding depends on l Naturgimäfl from you Fons and your behavior the turbidity "s used, wich ·! Also other forms of design are «Sinkbai *, ■;

which result in the desired corrective effect.

Case »the ballistic auxiliary material is absolutely necessary in the LMngsaohÜ j. Since the driving act must be arranged, the effective surface ii ^: in the rectilinear molding Jidoeh is not sufficient to achieve the desired effect, if the auxiliary substance is like the a! In

Flg. 10 is shown as a spiral 3 arranged in the longitudinal axis of the propellant charge.

Expectations; 0098U / 1156

BATH ORIGINAL

Claims (1)

Dr. W. An * *) * ***, Pr. M. HmUL; 43 Expectations 1. Propellant charge for rocket propulsion, consisting of a two chemically differently composed, with regard to the desired performance characteristics, e.g. constant thrust, coordinated individual charges having propellant and a physically separate from this propellant ballistic aid, characterized in that this ballistic aid has at least one in oxide of the metals molybdenum dispersed in a thermoplastic binder; Contains tin, chromium, tungsten, zirconium, cerium, lanthanum, cobalt, nickel, iron and magnesium. · 2. Propellant charge according to claim 1, characterized in that that the ballistic auxiliary substance also contains at least one Contains the following inorganic salts: potassium sulfate, potassium nitrate, potassium chloride, barium nitrate and potassium perchlorate. 5. Propellant charge according to claim 1 or 2, characterized in that the ballistic auxiliary also contains silicon dioxide or magnesium silicate. PAe Dr AndreJewski, Dr Honke. 0 0 9 814/1156 BATH