DE1130735B - Rocket with a driving and a driven part - Google Patents

Description

The invention relates to a missile with a propelling part, which is one for all missiles Series is the same, consisting of the engine with the propellant charge, and a dragged or driven part.

In rockets with a driving and a driven part, it is known to be between these parts to provide a third middle part, which is to improve the mass distribution, and an explosive charge contains. This middle part remains unchangeable between the driving and driven part, whereby It is also not possible to remove this central part before the missile is deployed, as the detonator does this middle part is assigned. It is also known to provide rockets with a propellant that is divided into several elements in order to influence the range.

Compared to the known is now to be achieved according to the invention that when the same drifting part of a series of missiles changes the firing range of the missile for a given launch angle can be, immediately before the launch or at any other time. This object is achieved according to the invention in that in rockets of the type mentioned above driven part of a rocket of a series is changeable in weight. It remains the driving part always the same for a certain series of missiles, which has a favorable effect in terms of production, while the weight of the driven part by increasing or decreasing weight at any time can be changed, so that the firing range of the rocket at a given launch angle accordingly can be enlarged or reduced according to the respective requirements.

According to a further advantageous embodiment of the invention, one can proceed so that the payload is the same for all rockets in a series and that then a part of the propelled rocket deviating from the payload Partly is changeable in weight. So it remains the driving part as well as the payload for the rockets of a series are always the same, while the weight is changed by an additional part the range is variable.

The invention will now be explained using two exemplary embodiments of the drawing, namely demonstrate

Fig. 1 and 2 two different missile designs according to the invention schematically in side view with axial partial sections, with certain 5 "parts of the rocket being shown exploded in FIG. 2 are.

Rocket with a propelling
and a driven part

Applicant:

Brevets Aero-Mecaniques SA,
Geneva (Switzerland)

Representative: Dr. H. Wilcken, patent attorney,
Lübeck, Breite Str. 52/54

Claimed priority:
Luxembourg of August 24, 1957 (No. 35 409)

It is known that the longitudinal scattering observed when a missile is launched is a Is a function of the angle of incidence of the missile and that this angle of incidence is in turn a function of the Is the angle of elevation at which the missile is launched.

There is now an elevation angle between 0 and 90 ° with a critical value (roughly of the order of magnitude 40 to 45 °), at which the longitudinal scattering is a minimum, so that one is as possible must hold near this angle of elevation. If you want to avoid special devices, have them With rockets you only have a small clearance in the firing range if you want to launch a certain one Missile launch angle is based on that of the angle with the least dispersion in the longitudinal direction differ only a little.

The aim of the invention is to use the angle of elevation or launch angle with the smallest Longitudinal scattering to achieve a considerable game in the range without affecting the driving part of the Missile is regulated at the moment of launch.

Accordingly, each rocket according to the invention consists on the one hand of a propelling part, the always remains the same for all rockets of a series, and from a rocket motor of suitable design, z. B. from a powder-powered rocket motor 1 and on the other hand from a driven one

209 607/52

Part that contains a suitable payload and, for example consists of a projectile head 2 with explosive charge, which is also according to the example is the same for all missiles in a series, but the weight of the propelled part of any one Rocket series can be changed within certain limits.

In this way, assuming a launch angle, it is close to the angle with the smallest Longitudinal scattering possible to change the initial speed and consequently the range of the rocket, an increase in the weight of the driven part by a decrease in the firing range and vice versa.

Albeit by increasing the range of the shot as a result of reducing the weight of the gun being driven Sometimes the rocket flight time is increased, this is less disadvantageous for a rocket than for one classic bullet, which is stabilized by a rapidly decreasing rotation, as the stabilization the rocket takes place aerodynamically, so that this stabilization practically during the whole The missile's flight time remains constant.

One can proceed according to FIG. 1 in such a way that the rocket is placed between the propelling part 1 and the payload 2 provided with one or more compartments 3, which are filled with a material serving as ballast can be, with holes or perforations are provided that open and close and through which these departments are to be filled and emptied. The sections 3 are preferably between the rocket head 2 and the driving part and consist of a tubular element which is divided by transverse walls, so that this tubular element forms part of the missile body.

All or individual departments 3 can now be provided with ballast, and the ballast must be immediate be filled in before launch, since the missile is to be delivered with empty compartments 3. However, it is more advantageous to ballast the compartments beforehand and then to ballast all of them before launching them or to empty part of the compartments 3, which can be carried out easily and quickly, with the ballast made of an inert and cheap material, e.g. B. can consist of water or sand.

In addition to the ballast fillings, an explosive or igniting filler can also be used to reinforce a target effect Product to be used as ballast, e.g. B. explosives, gasoline or naphthalene.

Instead of the embodiment according to FIG. 1, in which the rocket forms a coherent unit from parts 1, 2 and 3, it can also be designed with an independent propelling part 1 and a rocket head 2, as shown in FIG. 2, and connecting elements 4 can then be provided , which are firmly connected to one another one behind the other, one end being connected to the driving part and the other end being connected to the rocket head 2. The driving part 1 and the rocket head 2 as well as the connecting elements 4 have complementary fastening means which enable a coupling with one another and with the connecting elements 4. In order to change the weight of the rocket part that is carried along or driven, the number of connecting elements 4 between the driving part 1 and the rocket head 2 can be changed.

The connecting elements 4 are simple cylinder sections 5 which are provided at one end with a threaded pin 4 α and at the other end with a complementary internal thread 4 b. The driving part 1 has an identical internal thread 1 α and the rocket head 2 has a corresponding threaded pin 2 α. The ballast of the intermediate elements 4 can either be inert or also increase the target effect, in which case the elements 4 in the cylinder part 5 are provided with an explosive or combustible filling.

Claims (6)

PATENT CLAIMS: 1. rocket with a driving part, which is the same for all rockets in a series, consisting of the engine with the propellant charge, and a driven or driven part, characterized in that the driven part (2 to 5) of a rocket Series is changeable in weight. 2. Missile according to claim 1, the driven or entrained part of which contains a payload, which can in particular be a projectile head, characterized in that the payload (2) for all Missile of a series is the same and a part (3 to S) of the propelled one deviating from the payload Part is changeable in weight. 3. Missile according to claim 1, characterized in that the change in the weight of the driven part (2 to 5) is achieved in that the rocket at least one, advantageously several Compartments (3 to 5) which can be filled with a ballast material, with closure bores for filling or emptying the compartments. 4. Missile according to claim 3, characterized in that the compartments (3) between the rocket head (2) and the driving part (1) are, advantageously by transverse partitions of one of the Rocket body forming tube are made and a connecting part (3) between the head (2) and the driving part (1). 5. Missile according to claim 3, characterized in that the ballast material or explosives is an incendiary compound and the like. 6. A missile according to claim 1 with a missile head (2), characterized in that the driving part (1) and the missile head (2) are connected by connecting elements (4 and S) which are firmly coupled to one another at their ends by alternately fitting fastening means and which allow the rocket head (2) to be coupled to the propelling part (1) either by interposing one of the connecting elements (4 and 5) or directly to one another. References considered: British Patent No. 489,876; U.S. Patent No. 2,422,720. 1 sheet of drawings © 203 607/52 5.