DE1131559B - Flying body for practice purposes - Google Patents

Description

Missile for training purposes, which for example in place of a warhead against a have this replaceable exercise head, the tip of which is designed as a hollow body, can be detached and contains a parachute are already known. A number of these training missiles are the or the braking parachutes are so unfavorably arranged that the missile when deploying the parachutes does not maintain its normal attitude, but overturns and with that especially against impact the sensitive stern hits the ground first or in a transverse position.

There are also known missiles in which the parachutes or similar braking devices are arranged such that the missile always hits the ground with the tip first, with in a number of applications in the missile tip additional shock absorbers, e.g. B. springs, provided that reduce the kinetic energy and damage the missile on impact to prevent from hitting the ground.

In missiles of the aforementioned type, the braking devices and the shock-absorbing means but so unfavorably arranged and designed that they the aerodynamic behavior of the missile significantly affect and as a result are only significant for missiles that are not subject to any special conditions regarding flight behavior.

The object of the invention is to design a missile for exercise purposes of the type mentioned at the outset in such a way that that while maintaining the highest possible rate of descent of the missile this or at least important parts of the same as a result of the loads occurring upon impact with the ground cannot be destroyed or damaged. In addition, the device required for this should be used for braking of the missile can be arranged in an aerodynamically favorable manner and a simple, uncomplicated and only have a small space-consuming structure, so that they are independent the type and size of the missile ensures a wide range of applications. Also should the braking device must be reusable at all times.

A solution to this problem is achieved according to the invention in that the head of the missile consists of at least two expandable shell-shaped parts, which the braking parachute or parachutes and enclose a landing dome acting in the axial direction of the missile. By one in this way arranged braking device, the disadvantages mentioned of the known devices are avoided.

Missiles for training purposes

Applicant:

Bölkow developments
Limited partnership,
Ottobrunn near Munich

Dipl.-Ing. Fritz Zeyher, Ottobrunn near Munich, has been named as the inventor

An exemplary embodiment of the invention is shown in the figures. Here are the aforementioned and further advantages resulting from the invention as well as expedient configurations of the shock-absorbing Establishment explained in more detail. It shows

Fig. 1 shows a missile for training purposes with a shock absorbing designed according to the invention Device and a braking parachute shortly before the dropping of the missile,

FIG. 2 shows a missile according to FIG. 1 with a fully effective braking device at the moment of impact on the ground,

3 shows a longitudinal section through a missile training head designed according to the invention with landing dome in the interior of the head and two braking parachutes.

The representation of all parts of a missile that are not directly part of the subject matter of the invention has been omitted for reasons of clarity.

In FIGS. 1 and 2, 1 denotes a missile which, in a manner known per se, has a training head 2 (Fig. 3). The latter can be screwed onto the missile by means of a thread 3.

According to the invention, the training head 2 consists of two shell-shaped parts 2 α and 2 b, which can be spread apart around hinges 4. In the interior of the training head 2, a landing dome 5 acting in the axial direction of the missile and two braking parachutes denoted by 6 and 7 are also arranged according to the invention. The parachutes can open automatically in the air flow after the shell-shaped parts 2 α and 2 b have spread , or by suitable means that are not the subject of the invention and are therefore not shown in more detail, inevitably to

209 609/75

Unfold. In order to reduce the kinetic energy with as constant a delay as possible when the missile hits the ground, the elastic articulation of the landing mandrel 5 on the missile is designed as a hydraulic shock absorber, which comprises a piston rod 5 α guided in a sleeve 8 and a cylinder 9 . Premature penetration of the piston 11 into the cylinder interior can be avoided in that

shown in the figures, be rigid and connected to the piston rod 5 a or also made of expandable, when hitting the ground against fixed stops movable parts exist.

Although the landing mandrel is designed as a hydraulic shock absorber in the foregoing, it is However, the invention is by no means restricted to this. Rather, in certain applications, the Landing mandrel in an equally advantageous manner also rigid

the piston rod 5 α in the sleeve 8 can be designed by an abio or as a pneumatic shock absorber shear pin 20 is secured. or a spring as an elastic, shock-absorbing member

As can be seen from the figures, the suspension lines 13 and 14 connected to the missile are the Brake parachutes in a simple way on the rigid cylinder

own.

In a further development of the inventive concept, it is also provided in the exemplary embodiment that the

the 9 of the shock absorber attached. 15 the shell-shaped parts 2a and 2b, the hydraulic

In order to prevent the missile Lischen shock absorbers 5 a and the brake parachutes 6 is rotated 180 ° from its original flight direction when the parachute is deployed and with

stern hits the ground first are in accordance with

and 7 existing braking device comes into effect automatically. This can for example according to the invention happen because the spreading

Another feature of the invention, the suspension lines 20 movement of the shell-shaped parts 2 a and 2 b through 13 and 14 of the parachutes at the tail of the missile, the ignition of a depending on the flame in eyelets 15 out. In this way, the missile also retains the explosive device 17 of the training head which can be triggered at the tip when the parachutes are deployed and which is shown in FIG. 2. Is guided through the unfolded fall. The latter is in the tip 5 b of the Kolschirme, the speed of the flying rod is also arranged and shoots a cap 18, body reduced to a level on which the landing, which the shell-shaped parts 2 a and 2 b is designed during thorn . of the flight when closed. Except,

The mode of operation of the shock absorber is such that the detonation of the detonator is dependent a liquid located in the interior of the cylinder takes place from the burnout of the missile engine amount of kinetic energy is adjusted, which could be 30, the explosive device 17 can also not Missile is to be withdrawn. Appropriate triggering devices shown in more detail, for example The size of the throughflow openings 12 can be determined as a function of the pressure inside a barometer, so that the missile can be ignited in an optimal manner at the same time, is moderately delayed. The retardation force is used as the aforementioned or others to ignite the

via an air cushion due to the pressure of the liquid in facilities serving 35 explosives on a part 10 rigidly arranged cylinder 9 was the invention, is generated on a closer Dar. The reaction force is waived at the position in the cylinder, displaceable piston 11 and over the piston rod to after landing of the missile

5 a supported on the ground. Dragging the same on the ground by the wind

Assuming that the missile is able to prevent fully deployed braking parachutes Unyielding ground hits, the cylinder 9 or the piston rod 5 a finally shows up at the beginning existing missile speed as a piston of the shock absorber or a speed limit in some other way. Landing mandrel formed by bores 12 in the wall is coupled to a device of the cylinder 9, which, as can be seen from Fig. 3, through which the holding lines 13 and 14 of the brake lines If the masking varnish is closed, the screens can be cut off after landing. Because such Liquid located inside the cylinder which is not technically in any way due to the device in its structure the piston 11 is displaced after the difficult features have been blown off, but those of the respective masking lacquer flow away. About the design of the above-mentioned, which is adapted to the previous purpose of the piston The path laid down is the outflow cross-section so that any person skilled in the art is familiar with it changes that the pressure in the cylinder 9 remains constant. 50 a detailed illustration of this development of the The speed of the piston compared to the invention can also be dispensed with. Missile and thus also the speed of the missile, regardless of the type and size of the missile,

Missile itself then inevitably takes on in which the invention is used, intended way. the invention ensures safe braking

By penetrating the tip 5 b into the ground, 55 of the missile when it hits the ground and the amount of delay is weakened even further. The penetration of the shock absorber tip into the ground also offers the advantage that at the same time light missiles with only a short overall length are prevented from tipping over
the. In order to be able to use extremely soft ground, e.g. B. sand, a
To avoid too deep penetration of the piston rod 5 a and thus to make the hydraulic shock absorber device almost ineffective, can at the free
End of the piston rod 5 a at a small distance of 65
the tip 5 b of the same in a known manner a that
Resistance surface 16 preventing penetration into the ground may be formed. As in

Missile. In addition, there is the particular advantage of being technically simple, functionally reliable and compact Construction.

Claims (8)

PATENTAN'S CLAIMS: 1. Missile for training purposes, for example in place of a warhead against a has this exchangeable training head, the tip of which is designed as a hollow body, is detachable and contains a parachute, characterized in that the head (2) of the missile consists of at least two expandable, shell-shaped parts (2 a, 2b) which enclose the braking parachute or parachutes (6, 7) and a landing mandrel (5) acting in the axial direction of the missile. 2. missile for training purposes according to claim 1, characterized in that the elastic articulation of the landing mandrel (5) on the missile designed as a hydraulic shock absorber is. 3. missile for training purposes according to claim 2, characterized in that the outflow cross-section the shock absorber fluid by arranging outflow bores (12) in the cylinder (9) sealed with masking varnish over the Piston travel is reduced so that the deceleration of the missile when braking remains almost constant. 4. missile for training purposes according to any one of the preceding claims, characterized in that that at the free end of the loading mandrel (5) in a known manner a penetration into soft ground preventing resistance surface (16) is formed. 5. missile for training purposes according to claim 1, characterized in that the am Missile attached suspension lines (13, 14) of the parachutes at the tail of the missile (1) out are. 6. missile for training purposes according to claim 1, characterized in that the shell-shaped parts (2 α, 2 b) in the closed state by a cap (18) arranged at the tip of the training head (2) are secured against spreading. 7. missile for training purposes according to claim 6, characterized in that the cap (18) for example by means of a built-in explosive device (17) optionally depending on the Burnout of the missile drive or depending on a baxometer box or by a signal can be blasted off from the ground in a known manner. 8. Shock-absorbing device according to claims 1 to 5, characterized in that the cylinder (9) or the piston rod (5 a) of the landing mandrel (5) with a device for Caps of the suspension lines of the braking parachutes (6, 7) are coupled. Considered publications:
German Patent Nos. 331479, 177 947;
French Patent No. 526120;
U.S. Patent No. 2,887,055;
Cios Report XXIII-10, London, 1945. For this purpose, 1 sheet of drawings © 209 60OT5 6.