DE1254998B - Altitude research rocket - Google Patents

Description

GERMAN yffltlm PATENT OFFICE

German class: 72 d-19/01

EDITORIAL

Number: 1 254 998

File number: D44208Ic / 72d

^ 254 998 filing date: April 20, 1964

Opening day: November 23, 1967

The invention relates to a sounding rocket, so a rocket that in the highest layers of the Earth's atmosphere is shot and its payload consists of measuring devices, etc., with their help in these high and highest strata examinations and measurements, e.g. B. meterological, geophysical or similar. The task of such sounding rockets it implies that they are not only in uninhabited areas but also over populated areas should be used. In addition, it is not just a matter of individual rare missions, but as a result the extensive research on larger series of rocket launches by a corresponding Number of starting places. So far sounding rockets are more or Fired and flying less vertically than missiles with a thrust phase and a subsequent phase unpowered ballistic flight phase to the intended height. There they come as to their vertical speed to rest momentarily, reverse their direction of movement and fall back to earth. The payload, i.e. H. the measuring instruments, etc., are mostly at the apex of the Trajectory or ejected from the actual rocket body in the vicinity of the summit point or otherwise separated from it and then sink, by a parachute or a self-inflating one Balloon slowed down, correspondingly slower through the atmosphere. In this way it is possible to use the to recover the devices contained in the payload undamaged.

Separating or exposing the payload from the missile body presents difficulties. At acquaintances Arrangements is simply the entire tip of the rocket, behind which the sensitive devices lie, repelled. In a known design, the outer skin of the missile consists of two half-shells, which are each connected to one another by a bridge. Fall by blowing up the bridge the two half-shells apart and expose the payload. In another known arrangement should be a sensitive radome hood against impact and rain erosion during the take-off phase and flight etc. are protected. It is a missile tip is provided, which is made of strip-like narrow shells forms a pointed envelope for the payload to be protected. The strips themselves will be held together at the foremost tip by a glued-on cap. To expose the devices is the relatively small cap at the top, which is made of an easily breakable material sounding rocket

Applicant:

Dornier System G. m. B. H., Friedrichshafen

Named as inventor:

Dr. rer. nat. Heinz Busch, Kressbronn (Württ.)

stands, destroyed by a small explosive charge. This causes the ones lying around the missile tip enveloping strips released and spread

¹ pieces open up like flowers on all sides and then fall away. In another known design, the rocket tip is designed as a radome and consists of ceramic. The connection between the ceramic tip and the rest of the rocket body brings with it certain technological difficulties which are avoided in this known arrangement in that the two components are connected to one another by a ring wound from glass fibers. The ring is wound under such tension that unintentional loosening of the two components as a result of this tension is prevented. The two components and the ring are fastened together by bolts. Deliberate separation of the components is not intended.

Since the processes take place at such a height in the earth's atmosphere that none have yet been pronounced Re-entry problems occur, d. H. the parts when they re-enter the earth's atmosphere do not burn up on their own, all parts released from the missile fall back empty to earth. An impact these parts on the surface of the earth represent a risk and a considerable element of danger, since it is not possible to predict this point of impact at the start because of the unknown wind drift. The same problems as with the parts of the covering that have been blown off occur naturally also with the actual missile body, unless special measures are taken against it are. This disadvantage of uncontrolled hitting the ground also applies to multi-level Sounding rockets and naturally especially for the upper levels, which are relatively soar high in the atmosphere.

Various methods have been proposed to render the missile body safe Way to bring it back to the ground. However, these procedures required either for the ascent

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phase and / or the descent phase considerable expenditure on steering means or parachutes, flexible Wings, etc. According to another well-known proposal, the missiles are only in the ascent orbit Made largely independent of the effects of wind by placing rockets with extraordinarily high Start accelerations are developed and used, which is after the start booster burns out a non-propelled body detaches from the rocket, which is self-stabilizing ballistically like a flying arrow continues to fly and is thrown to the desired height. This unpowered missile contains the Payload that is brought back to earth in the known manner. The flight of the start booster does not need to be taken into account here, as the start booster is only slightly removed from the starting position removed and therefore easily monitored and brought to the ground in the security area. For the unpowered missile, however, the above-mentioned disadvantages still apply, namely in the descent phase either great dangers for people or systems on the earth's surface or the rescue with the help of parachutes and the like causes particular difficulties. In addition comes that any use of rescue equipment, such as parachute, self-inflating balloon, deployable Wings, steering devices, etc., not only cause significant costs, but also one Represent an increase in weight that should be avoided if possible.

The invention is based on the object, after the payload has been disconnected during the return of the missile body and, above all, the dangers for residents. Above all, there should be no additional expenditure in terms of costs and weight for special rescue and recovery Steering devices. Starting from a sounding rocket that consists of at least one stage Rocket engine and a driveless mounted on it and the payload or its movement devices and there is devices for releasing the missile containing the payload, the object is achieved according to the invention in that the non-propelled missile is made of glass-like material with extremely high internal stresses, which at the manufacture of the missile are generated artificially, and that a switchable if necessary, the automatic destruction of the missile by utilizing the internal stress initiating device is provided and by the destruction of the missile to harmless individual parts the payload and, if necessary, their recovery facilities are exposed. The device initiating control can be switched on automatically or remotely and generates an additional voltage peak. Advantageously a mechanical device, e.g. B. a firing pin or a small explosive device. Which way the firing pin is triggered is for the essence of the invention is irrelevant. It should only be mentioned here that they are spring-loaded Firing pin or firing pin driven by a propellant charge can act.

So only the payload is recovered in a manner known per se, but the missile itself is that way destroyed so that its individual parts falling on the earth are harmless when hitting the earth's surface are. An essential feature of the

Finding lies in the fact that the energy required for the guaranteed destruction of the missile is in the form is given from the start by residual stresses of the missile. This training indicates the The advantage is that the entire energy required can be stored masslessly and no additional energy for this heavy equipment or weights are required. The small additionally built-in device, which initiates the self-destruction of the missile is of no importance here.

The processes involved in using such a sounding rocket are briefly explained below: The sounding rocket consists essentially of two parts, namely a booster rocket engine with very high thrust and short burn time and one mounted on this engine unpowered missile containing the payload. The missile is of a dart-like style slim shape with low air resistance. It stabilizes itself during its ballistic flight. This missile consists of a material with extremely high internal stresses in this material were artificially produced during its manufacture. The rocket engine used for launch has such a high thrust, but such a short burning time that it is after the burnout and disconnection from the actual missile, possibly through additional generation of resistance, already in such a low altitude is braked that an impact regardless of wind influences with Security still takes place within a certain demarcated area around the starting point. Usual small shooting ranges or airfields, but essentially cordoned off, can be used as the starting area or fenced areas can be used.

The actual missile, which contains the payload, will be like after its separation from the missile mentioned, thrown on ballistic trajectory at heights in the order of magnitude of around 100 km. In the desired height, mostly at the summit or near the summit of the rocket trajectory, The payload is ejected and then in the usual way by devices that provide the resistance increase in free fall, brought back to earth. There is also a device at these heights brought into effect the shattering by generating an additional voltage peak causes the missile into many small individual parts. The missile is destroyed after the well-known effect of the safety glass panes or the glass tears under internal stress. The falling parts are so small that they do not pose a threat when they hit the surface of the earth for residents or systems.

The device, which in turn initiates the automatic destruction of the missile, can be on any known way can be brought into effect. For example, there can be a timer be that triggers a firing pin, or it can also be triggered by a remote control command. It is also possible to take both measures for safety reasons. Furthermore it is possible to destroy the missile not only after the payload has been disconnected, but to make the arrangement so that the payload may be destroyed by destroying the missile is exposed together with their recovery facilities.

Claims (3)

The complete destruction of the missile carrying the payload does not represent a disadvantage, since such missiles themselves are usually lost devices. Compared to the previously known sounding rockets, the invention offers a considerable advantage, since the above-mentioned dangers when hitting the earth's surface are completely avoided and, moreover, the energy necessary for the destruction of the missile is stored masslessly and does not require any additional heavy and expensive equipment. Patent claims: 1. Sounding rocket, consisting of at least a single-stage rocket engine and a non-powered one placed on it and the payload or its recovery facilities and Devices for releasing the missile containing the payload, characterized in that that the driveless missile made of glass-ao-like material with extremely high internal stresses exists, which are artificially produced in the manufacture of the missile, and that a can be switched on as required, the automatic disintegration disruption of the missile provided by utilizing the internal stress initiating device and the destruction of the missile turns the payload into harmless parts and, if necessary, their recovery facilities are exposed. 2. Sounding rocket according to claim 1, characterized in that the destruction introductory device generates an additional voltage peak and is automatically or remotely controlled can be switched on. 3. sounding rocket according to claim 1 or 2, characterized in that the device a mechanical, z. B. a firing pin or a Explosive device, is. Considered publications:
French Patent No. 1318601;
U.S. Patents Nos. 3,111,089, 3,103,887,
985.2 782716;
Hütte I, 28th edition, 1955, p. 1203;
Hut, Taschenbuch der Stoffkunde, 3rd edition,
1961, p. 553. 709 689/128 11.67 @ Bundesdruckerei Berlin