DE1175115B - Electric ignition switch for rockets to be launched one after the other by rocket groups - Google Patents

Description

FEDERAL REPUBLIC OF GERMANY

GERMAN

PATENT OFFICE

EDITORIAL

Boarding school KI .: F 07 d

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German class: 72 c -16/05

1175 115
B61467Ic / 72c
February 28, 1961
July 30, 1964

The invention relates to an electrical ignition circuit for the arrangement of several in series attached to each other, sequentially locking missiles carried by a launcher each rocket has organs that, when the rockets are attached, a continuous, Electrical excitation line that can be connected to a voltage source over the entire row of missiles form, and having an electrical igniter with an input contact, organs provided are through which the excitation line passing through is only connected to the input of an electrical circuit is connected to the first missile to be launched.

It has already been proposed, in the case of the ignition circuits mentioned above, mechanical timing or to provide electromagnetic delay means to stop the ignition of the last Delay missile until this missile has become the last missile in order to avoid early kills to prevent the rockets to be fired one after the other if the ignition pulse lasts too long.

According to another earlier proposal, the procedure for the ignition circuits mentioned is such that instead of a single excitation line running through the entire rocket group, two excitation lines are provided, which refer to the connection contacts of the next missile cross and are connected to the voltage source via a selector switch, the contacts of which alternate operated to connect the two excitation lines to the power source. Also in In this case it is achieved that premature launching of the respective following missile is avoided.

On the one hand to switch off time delay means and on the other hand with only one excitation line get along and only be able to fire the first missile without a. shooting too early the following missile takes place, it is proposed according to the invention that in the case of the aforementioned electrical ignition circuit the ignition of the first missile to be shot over all Excitation line passing through missiles by the second switching pulse of two successive, different switching impulses are triggered.

This solution achieves a simplified circuit without delay means using only one continuous excitation line, the different switching pulses being generated one after the other by generating different voltages by means of a transformer that can be switched on and off or by charging an electric ignition circuit
missiles to be fired from missile groups

Applicant:

Brevets Aero-Mecaniques S. A., Geneva (Switzerland)

Representative:

Dr. H. Wilcken, patent attorney,

Lübeck, Breite Str. 52/54

Claimed priority:
Luxembourg 7 March 1960

and discharging of a capacitor can be caused, as will be explained in more detail below.

The invention is explained below with reference to the drawing with the aid of exemplary embodiments. Fig. 1 shows, on a small scale, a series of three missiles suspended under an aircraft wing, to which the invention can be applied;

F i g. 2 shows schematically these three missiles which, like the aircraft, have one according to a first Embodiment of the invention trained electrical ignition circuit are provided;

F i g. 3 shows a single missile of the type shown in FIG. 2, the various parts of the Ignition circuit carried by the rocket is shown in the transport position of the switching elements, which they take before attaching the missile to their launcher;

F i g. 4 and 5 show in the same representation as FIG. 2 and 3 an arrangement whose electrical Ignition circuit is designed according to a second embodiment of the invention or a single Missile of this arrangement in the transport position of the switching elements.

In the arrangement shown, suspended in a row under the wing 1 of a fighter aircraft Missiles are launched one after the other at the desired times.

The devices for suspending the missile to be fired last on the aircraft and for suspending it the other missiles to each other as well as to transmit an electric current to the first missile to be launched, which flows over the other missiles without affecting them, and finally to prevent any risk of ignition

409 638/35

the detonator of the rocket before it takes its right place in the line can be different Way to be trained.

It is assumed below by way of example that each rocket is attached in a known manner to the part carrying it, ie a rocket or the holder attached to the wing 1 of an aircraft. The missiles then have a body 2 which expires at the rear in an end piece 2 a. This contains the

and then assumes the final rearward position by striking a frustoconical contact surface 2 b , which it maintains during the flight of the missile.

The rockets and their holder 4 are each provided with a flap 5 in a manner known per se, which has such dimensions and such a position that the folded-down flap of an upper wheel

cannot be ignited under any circumstances. For this purpose, the clearly shown in FIG. 2 to 5 visible circuit to be used.

The training described above in broad outline, which in itself is not an object of the invention forms can be replaced by any equivalent arrangements in which one of the Power source 6 supplied electrical current via a single electrical line running through to the Nozzle through which the combustion gases of the propellant can pass the first rocket to be fired, reloading the missile exit. which he flowed over all the other missiles in the series

As shown in Fig. 1, each missile 2 has a is without affecting it.

sliding tail unit 3, with which it was attached to the

corresponding tail unit the electrical current immediately above it the ignition current of the first to be thrown off Missile or, in the case of the last missile, on a landing missile. There was then the risk that a Suspended from the holder 4 attached to the wing 1 are a single impulse the untimely firing of several can. This sliding tail unit 3, takes in front of missiles rather than a single causes. The launch an advanced position in which a single missile then enabled the launch it at the same time as a guide and as a holder for the launch of the rocket immediately above, Missile body is used. When passing during the 20 which was ignited by the pulse, if The initial phase of the launch is taken along and lasted for a correspondingly long time.

The electrical equipment in each rocket is now designed to be used for ignition a rocket at least two successive 25 precisely defined changes to its input contact Requires prevailing voltage, furthermore the overall arrangement with facilities is provided, which give the opportunity to shoot down at the input contact of the first kete II to partially change the voltage present in the path of the propulsion jet of the rocket so that immediately below it is assumed to be ignited - this is ignited.

menen rocket III so that it is caught by the beam.

is pushed away and folded up. The rocket from the ßende by the first voltage change Holder 4 carried flap 5 in turn blocks the only prepared for the launch, which only takes place, Path of the beam of the uppermost rocket I of the bundle, 35 if the voltage changes again accordingly when that top missile I is fired. It is will.

furthermore restraint means, which are also known per se, but since the next missile is not "prepared"

seen which was the * launch of the one to be shot down, it cannot be shot down by itself Allow missile only when the flap 5 of when the tension that caused the launch of the first caused by the 4 ° missile sent out by the missile that was just ignited. To the The gas jet is pushed back and folded up. to shoot the next missile, the ar-

It is also assumed that the successive tension elements occur in the flight endurance game a power source 6 is located, which are repeated by a wrestling.

Contact 7 can be connected to a line 8. B. the training made so that

can. This line is connected to the 45 the ignition of the first missile to be launched by the holder 4, worn flap 5 connected. Furthermore, each d. H. the passage of the ignition current through the Flap 5 of a given missile, if it is behind the igniter of that missile, only by one ignition process Nozzle of the rocket, which can take place immediately in front of it, which inevitably has at least one given rocket is to be launched, the preparatory process must precede which has worked, in this latter rocket a switch consists in that through the only line which ter 9, the one already from the power source 6 over all missiles to the one to be shot down first the parts 7, 8, 5 and 9 produced line to the missile runs through the elek-flap carried by this missile 5 of the missile extended. An electric current is supplied to the apparatus

In this way this line becomes over the individual, which this apparatus in such a rocket up to the flap 5 of the first to be fired 55 offset that the ignition process has the consequence, The rocket is extended, this flap and the rest of the apparatus supplying the next electric current that of all other missiles is designed so that it pushes through the igniter of the missile to be launched sends them when they are folded up as a result of being shot down.

of the preceding missile in the first In a first embodiment of the invention

When the missile completes the line with a contact 10 in 60 (Figs. 2 and 3), the preparatory process exists Connection sets, which of the below explained in that one of the circuits of a transformer electrical Apparatus belongs. mators is fed during the subsequent In such a system, each switching and ignition process can also be interrupted in this supply ter 9 can be used to, if it does not consist of one, this current interruption in the Flap 5 is pushed back (i.e. before attaching 65 another circuit of the transformer to a current movement of the rocket on its holder) in the one in Fig. 3, which causes the ignition, and 5 the two terminals of the This electrical apparatus is e.g. B. following detonator short-circuit, so that this is then formed under measure:

The contact 10 is through a conductor 11 to the input of the primary winding 12 of a transformer connected, and the output of this primary winding is connected to the body by a conductor 13, which is formed here by the entirety of the rocket body and by the body of the launcher will.

One end of the secondary winding 14 of the transformer is also connected to the body while the other end of this secondary winding is connected to one terminal of the igniter 15, whose other clamp has body contact.

This arrangement can easily be designed by any person skilled in the art so that during manufacture of the contact at 7 (preparatory process) for producing a current in the primary circuit 12 of the transformer running line generated in the secondary winding 14 and to the terminals The potential difference applied to the igniter is not sufficient to ignite it, while during interruption of this contact at 7 (ignition process) the sudden power interruption at the terminals of the Igniter generates a greater potential difference, which causes the ignition.

The launch of the first missile to be launched is then only generated by the ignition process, and The next rocket can only be made by a new one that encompasses the two successive processes Work cycle to be shot down.

In the second embodiment (Figs. 4 and 5), the preparatory process consists of charging of a capacitor and the ignition process in the discharge of the capacitor via the igniter, such that that this is ignited.

For this purpose z. B. the contact 10 through a conductor 16 via a rectifier 17 (e.g. a germanium or silicon rectifier) connected to one assignment 18 of a capacitor, the other Occupancy 19 through a conductor 20 has body contact, the rectifier 17 the current passage in the sense going from the occupancy 18 to the contact 10 is prevented.

The assignment 18 is connected by a conductor 21 to one terminal of the igniter 15, the other Terminal is connected to contact 10 by a conductor 22 via a second rectifier 23, which prevents the passage of current in the sense going from the contact 10 to the igniter.

The interacting with the contact 7 switch is designed so that one of the successive Missiles up to contact 10 of the first missile to be launched either can connect to the power source 6 or to a contact 24 which has a body connection.

It can then be carried out through a first process (production of the supply of the line by the power source 6) the charging of the capacitor 18,19 takes place, while the detonator only occurs through the discharge of the capacitor is ignited when the line, i. H. the Contact 10, with which the body is connected.

Here, too, untimely ignition of the second missile to be launched is impossible.

The either only with contact 7 (Figs. 1 and 2) or with contact 24 (Figs. 4 and 5) cooperating switches can of course be manually or automatically in any suitable manner be operated in such a way that any desired type of fire can be achieved, such as the individual launch of the Missiles, volley fire with the desired sequence and number of missiles, etc.

Claims (5)

Patent claims: 1.Electric ignition circuit for the arrangement of several, connected in series, missiles to be launched one after the other, which are carried by a launcher, wherein Each missile has organs that, when attaching the missile, pass through one to a Form a voltage source that can be connected to an electrical excitation line over the entire row of missiles, and an electrical igniter with an input contact, organs being provided through which the excitation line passing through is only connected to the input of an electrical Circuit of the respective first missile to be launched is connected, characterized in that that the ignition of the first rocket to be fired (2) via all the rockets continuous excitation line (8) by the second switching pulse of two successive, different switching impulses are triggered. 2. Arrangement according to claim 1, characterized in that the first switching pulse through Connection of the excitation line (8) to the voltage source (6) is achieved without the igniter (15) to influence while the second switching pulse by disconnecting the excitation line (8) from the Voltage source through the primary winding (12) of a transformer generates a current in the secondary winding (14) induces the transformer, which is able to ignite the on by appropriately dimensioning the two windings to effect this second winding connected detonator (15) of the first missile to be launched. 3. Arrangement according to claim 1 and 2, characterized in that the input contact of the electrical circuit of each missile through a conductor (11) to the input of the primary winding (12) of a transformer is connected, the output of which through a conductor (13) to the Rocket mass is laid (the mass is formed by the mass of all rockets and the launcher), while the secondary winding (14) of the transformer on the one hand also on the rocket mass is and on the other hand is connected to one terminal of the igniter (15) whose other clamp is placed on the rocket mass, and that a switch (7) the continuous excitation line (8) connects or interrupts a voltage source (6) connected to the ground on the other hand. 4. Arrangement according to claim 1, characterized in that the first switching pulse over the excitation line connected to the voltage source (6), on the other hand, connected to ground Capacitor (18,19) charges in a known manner, which is obtained by switching off the excitation line from the voltage source and connecting the same to the rocket mass via the igniter (15) of the first missile to be fired discharges for ignition. 5. Arrangement according to claim 1 and 4, characterized in that the input contact (10) the electrical circuit of each missile through a conductor (16) through a rectifier (17) is connected to one side (18) of the capacitor, the other side (19) of which via a The conductor (20) is connected to the rocket mass, the rectifier (17) supplying the current only to the capacitor (18,19) lets through, and that the capacitor side (18) through a conductor (21) with the one terminal of the igniter (15) is connected, the other terminal of which is connected to the contact (10) through a conductor (22) with the interposition of a second, the current only to the contact (10) conducting rectifier (23) is connected, and that a switch (7, 24) is provided which connects the excitation line to either the output terminal a power source (6) connected to the rocket mass on the other hand or connects it to the Can lay rocket mass. Considered publications: German Patent Specifications No. 1 083 711, 1 056 970, 349 Older patents considered: German patents No. 1,149,640, 1,117,448. 1 sheet of drawings «9 638/35 7.64 © Bundesdruckerei Berlin