DE1014885B - Missile projectile - Google Patents

Description

Rocket projectile It is known to have several combustion chambers in solid rocket rockets to be arranged, which open into a common Ga.ssaminelraum to which the thrust nozzle connected. It is also known to use the wing of a missile body as fuel chambers to form, which open into a common central chamber which carries the thrust nozzle.

In the violin set to rocket projectiles, which have a briefly burning propellant that generates a high thrust and the projectile quickly to maximum speed accelerated, airplane-like missiles require a slow-burning propellant, that maintains the marching speed over a long period of time.

Slowly burning propellants can be produced. You are proportionate long. In contrast to rockets with high thrust, the solid propellant burns only on the front.

If such a long propellant is in the longitudinal axis of the rocket, it is displaced the center of gravity forwards when it burns, so that the entire missile is top-heavy and thus its flight becomes unstable. The top-heaviness must be through appropriate tax swings be compensated. This means that the rudders lose part of their effective working range for the steering and must be designed accordingly larger.

According to the patent application, the fireplaces are arranged in such a way that that there is no shift in the center of gravity when the propellant charge burns up.

The combustion chambers with the propellant charges are symmetrical across the Missile longitudinal axis arranged and open. in a common gas collector to who carries the nozzle.

Figure 1 shows such an arrangement. The two or pairs of more Combustion chambers a. are closed sideways to the common gas collection room b a, n, who carries the nozzle c at the back.

The gas collecting space b carries devices d for fastening the other parts of the missile (cargo, controls, wings) and is itself a part of the same.

The combustion chambers a can be c can be detachably connected to the gas collector, uin b.

The combustion chambers are located in the tra.gfläcben of the missile or serve even as wing spars and for attaching the wings to the body of the rocket.

Due to the transverse position of the combustion chambers and the simultaneous Abbranid both chambers is achieved that the center of gravity of the missile is not or shifts only insignificantly.

More than two combustion chambers can be used to extend the burning time used in pairs (a.1). It must, for example, by spring-loaded cover closures f it is ensured that only the burning chambers are open while the other chambers are closed until they burn out after the previous one Chambers are ignited or closed again after burning out.

The combustion chambers can also be used with arrow-shaped adjustment of the wings up to a certain angle at an angle to the gas collecting space (Fig 2).

Claims (2)

PATENT CLAIMS 1. Rocket projectile with two or more combustion chambers which open into a common gas collection space provided with the reaction nozzle, characterized in that the two or ineihr combustion chambers with their powder propellants are arranged transversely to the longitudinal axis of the projectile so that the combustion of the powder propellants does not occur Shifting the center of gravity of the bullet causes it to become unstable. 2. Projectile according to claim 1, characterized in that the combustion chambers are housed in wings of the projectile or are designed as wing spars and the common gas collecting space is in a known manner in the projectile body. 3. Geschaß make claim 1 and 2, characterized indicates that "the winged combustion chambers are inextricably linked to the gas milk room or exchangeable, e.g. B. by sleeves, screw connections. 4. Projectile according to claim 1 to 3, characterized in that indicates that several support vane combustion chamber Pairs connected in series to the gas collection room. Documents considered: German Patent No. 734 601; USA. Pat. No. 2,691,495.