DE1078903B - Rocket propelled missile - Google Patents

Description

The invention relates to a missile missile with a launch and a march charge. It is known to arrange launch charges, which have the task of a missile in a short time on his To accelerate top speed while the marching charge, which generates a much smaller thrust acts for a much longer time and maintains the missile's airspeed. It is also known to arrange the thrust of the starting charge to the horizontal so that the Starting force goes through the center of gravity of the entire missile to be accelerated and it is moment-free lifts off the launcher while the marching charge is arranged so that that of it generated thrust goes through the center of resistance. While one large, z. B. unmanned Missile can launch vertically upwards from special substructures and then in the desired course steers, one has missiles that are brought into the target direction before launch and which are equipped with a thrust nozzle inclined to the horizontal, so far from special starting devices fired off. The invention has set itself the goal of each special starting device to make dispensable.

The invention is that in a rocket-propelled missile · with a launch and a March charge the thrust nozzle emitting the combustion gases of the starting charge opposite the direction the missile longitudinal axis by an acute angle of more than 15 ° downwards into at least one approximately through the center of gravity of the missile inclined direction and so arranged is that it has a distance from the ground when the missile is placed on the ground.

Although an angular deviation of the starting thrust from the ideal direction of acceleration is energetic is to be regarded as loss-making, according to the invention this deviation is chosen to be even greater, than was previously the case with the use of starting devices, realizing that the advantage then To be able to do without a starting device at all is more important than the need to having to provide a somewhat larger starting charge for the same work in the direction of acceleration. Because then a very considerable component of the thrust generated by the starting charge acts vertically upwards, the missile is raised at the beginning of the take-off so that at the launch site no preparations need to be made for his good deal off the ground.

In a further embodiment of the invention, the thrust nozzle is the starting charge, optionally together with the cargo container at different angles to the longitudinal rocket propulsion Missile

Applicant:

Bölkow-Developments KG,
Ottobrunn near Munich

Axis adjustable and lockable attached to the missile.

Another feature is that the missile on its rear part has guide ribs, preferably in a cross arrangement, of which at least two are designed so that the missile as if on feet on a base with the Can set up the longitudinal axis at an angle to the direction of a normal on the base, with the focus of the missile lies within the support area of the foot ribs. In the latter case, the front one needs Part of the missile not being supported.

However, if the center of gravity of the missile is not within the support range given by the ribs lies, the front part of the missile could be additionally supported, e.g. B. by one on him attached light support under spring action, which is under spring action at the start to the Missile folds.

With rocket missiles designed according to the invention, especially if they can be remotely steered are trained to carry out the following launch procedure: The missile is essentially in Weft direction on any surface, e.g. B. placed on the ground using the aerodynamic Areas as feet, then the launch charge is ignited and the missile through one because of the Inclination of the starting charge thrust nozzle resulting component of the starting force directed transversely to the base lifted from the base and at the same time by the component of the starting force pointing in the target direction Accelerated in the target direction. The missile performs a so-called jump start.

Further features emerge from the description of an exemplary embodiment.

Fig. 1 is a side view of a rocket propelled missile formed in accordance with the invention; partly in section;

Fig. 2 is a related rear view.

909768/52

The missile fuselage 1 has essentially the shape of a tube which is closed at its front end by a conically pointed body 2. The front part of the fuselage 1 contains a shaped charge. At the rear end of the fuselage, four flight control ribs 3, 4, 5 and 6 are arranged in a cross shape and are preferably glued onto the missile fuselage with feet 7 spread apart. In the direction of the longitudinal axis, the marching charge 8 is housed with a thrust nozzle 8 'in the rear part of the missile fuselage 1, while the thrust nozzle 9 of the launch charge 10 attached to the fuselage 1 in the figures below is bent downwards at an angle α ^> 15 ° to the axial direction is in such a way that its axis passes through the center of gravity S.

The launch charge 10 is attached to the missile fuselage 1 as follows. A front holder 13, the Fuselage 1 is attached, contains a bore 14 into which a projection 15, for. B. an angled pin that Sheath of the starting charge 10 engages so that it can be pulled out backwards. At a rear attached to the fuselage 1 holder 16 is the shell of the starting charge 10 at 17 z. B. with interposition attached to a soldered joint. The connection point is at a point that occurs during combustion the starting charge assumes a temperature above the destruction temperature of the connection. if If the solder melts, the starting charge still remains in its position because its shell is created by the thrust the starting charge is held in contact with the holder 16. If the starting charge is burned out, it works no more such force, and the empty shell of the starting charge is after the air resistance thrown backwards.

In the rear inner parts of the guide ribs 3 to 6 control devices 11 are housed, which make it possible in any known manner to control the missile after take-off, e.g. B. via magnetic Drives that act on adjustable guide surface parts.

As Fig. 2 shows, the missile can be with two of the guide ribs, for. B. with the ribs 3 and 4, on the Set up floor 12 as if using your feet. The two guide ribs form an angle of 90 ° between them and an angle of 45 ° with the floor. This results together with the rectangular one in the example Wing limitation good contact conditions on the ground. For a smooth transition between For take-off and flight conditions, it is important that the flight position of the guide ribs coincides with the take-off position, So that both pairs of guide ribs, as at the start, at 45 ° to the horizontal and vertical in Space and not, as has been the case up to now, horizontally and vertically.

If it is a remotely guided missile, it is also useful for this reason to set the take-off position essentially to be maintained in flight in order to avoid particularly expensive and intricate means for remote control also a z. B. to provide a missile rotating about its longitudinal axis.

The invention, which is preferably applicable to guided missiles, because the aiming accuracy at This does not depend on the position chosen at random during take-off and is not restricted to such missiles. Especially when the angle of inclination of the thruster for the launch charge on the missile is adjustable and if the set angle to the horizontal is measured, it cannot be done with either remotely steerable missiles that are launched from any and any inclined documents, a achieve sufficient accuracy. Measuring ίο the angle can easily be done with outside of the missile to be used or attached to it done spirit levels or pendulums.

Claims (5)

Patent claims: 1. rocket-propelled missile with a launch and a march charge, characterized in that the thrust nozzle (9) of the launch charge with respect to the direction of the missile axis at an acute angle (α) of more than 15 ° downwards into an at least approximately through the center of gravity (S) of the missile going direction is inclined and has a distance from the ground when the missile is placed on the ground. 2. Missile according to claim 1, characterized in that the thrust nozzle (9) of the starting charge Can be set and locked together with the cargo container (10) at different angles to the firing direction is attached to the missile. 3. Missile according to claim 1 or 2, characterized in that the missile on its rear part has guide ribs (3 to 6) preferably in a cross arrangement, of which at least two are designed so that the missile is like on feet on a base substantially Can set up in the firing direction, the center of gravity (S) of the missile lying within the support area of the foot ribs. 4. Missile according to claim 1 or one of the following, characterized in that the starting charge slidable backwards at its front end, e.g. B. by means of an in a recess (14) engaging approach (15) is held while at its rear end z. B. with the interposition of a soldered connection (17) is attached so that the connection point in one During the combustion of the starting charge, the area heated above the destruction temperature of the connection lies. 5. Launching method for rocket-propelled missiles according to claim 1 or one of the following, characterized in that the missile on without a launch device with its tail unit any document, e.g. B. on the ground with the missile longitudinal axis at an angle to the direction a normal placed on the base and when the starting charge is ignited by one of the the combustion of the starting charge generated thrust component of the force diverted from the base is lifted. Considered publications:
German patent specification No. 305 160. 1 sheet of drawings