DE932348C - Combat equipment equipped with suspended missiles, especially aircraft - Google Patents

Description

Combat equipment equipped with suspended missiles, especially aircraft The invention relates to the earth, sea: or air combat equipment, which with at least a missile are equipped, which in the firing position by a suspension device is held (in contrast to those in such a position by an ejector tube held missiles), where: the expression »equipped with at least one missile Combat equipment «in the following text includes both the actual combat equipment as well as the includes missiles carried or carried by this. The invention relates in particular to but not exclusively, aircraft equipped with suspended missiles, in particular aircraft, with the missiles generally under the wings of the aircraft are arranged.

The invention aims in particular to design devices of this type in such a way that that they correspond better than before to the various requirements of practice, especially with regard to the shooting accuracy, the simplicity of the suspension device and in the case of aircraft with regard to the flight characteristics of the aircraft according to Release the missiles.

For this purpose, according to the invention in such a combat device, which is provided with at least one suspended missile, which is a stabilizing tail unit has, which is to be located on the rear part of the missile body, if the missile moves through its orbit, this tail unit is slidably attached to the body of the missile and in a forward position as part of the rocket suspension system used on the skeleton of the actual device, the rear part of the missile body has axial retaining means, which took the tail unit and in hold the rearward position when this rear part of the missile body after igniting the rocket comes to the height of the tail unit, so that this during the initial phase of launching the rocket also acts as a suspension element and a guide part for the missile body.

The invention is given by way of example with reference to the drawing explained.

Fig. R and 2 show schematically with parts broken away Side view or a front view of an aircraft wing, under which in the invention Way missiles are hung; Fig. 3 shows the mutual position of the various Parts of the system after the missile is launched; Fig. 4 and 5 show a larger Scale certain details of the system for suspending each missile on the Airplane wing; Figs. 6 and 7 show another in side view and front view, respectively method of mounting a plurality of missiles under an aircraft wing according to the invention; Fig. 8 shows, on a larger scale, a detail of the mutual attachment of two successive missiles.

The actual aircraft is in its entirety on any suitable Formed way, but with the exception -the under the wing z to attach the Missile parts to be provided, which are described in more detail below.

The missiles consist essentially of one in the usual way a .generally cylindrical shape having body 2, which is expedient after is extended at the front by a hood 3, which contains the cargo to be transported, z. B. an explosive charge.

As assumed below, the stabilization tail is z. B. formed by a plurality of radially arranged blades 4 (of which e.g. there may be four '), this tail usually, i. `h. if the Missile. Traverses its orbit, are at the rear end of the missile body: 2 target. . According to the invention, the stabilizing tail can now be placed on the missile body 2 slide, for which z. B.. The wings 4 are supported by a sleeve 6, which with Slight friction on the body 2 'can slide, with the adjustment of the sleeve 6 forward through a stop device firmly connected to the missile body 2 is limited, e.g. B. by bolts 7 or better through the rear edge of the hood 3, which then compared to the missile body by approximately the thickness of the sleeve 6 corresponding Protrudes.

When the sliding tail unit on the rocket body 2 is in the extreme forward position, at least one of the flights 14 is used as a part for suspending the rocket under the wing r, each rocket e.g. B., as clearly shown in Fig. 2, can be suspended at the level of the wing underside by two of its wings 4 inclined by 45 '.

On the rear part 2a of the missile body 2 are axial holding means provided, which take the stabilization tail unit and in the rear position (normal operating position) can hold if this rear part2Q after ignition the missile arrives at the height of the stabilization tail unit. 'Such means to hold in the axial direction z. B. be formed in that the rear Tei12Q the shape of a frustoconical bearing surface with a forward facing Pointed and rectilinear or curved generatrix is given, this bearing surface 2a, behind which a retaining bead can be provided, when starting up the missile strikes against the rear edge of the sleeve 6, which then on this bearing surface clamped and taken by, the missile body: 2.

It should be noted that the hanging of the wings 4, in the corresponding, Z borne by the wing parts-must be done so that the wing is under the Effect of when the conical contact surface 2 ″ strikes the sleeve 6 automatically disengage axial forces by a forward movement.

For this purpose, the wings 4 expediently play the role of parts for suspension of the front part of the missile body 2, each wing then in its trailing edge, As shown in Fig. ¢, a rearwardly open groove 8 contains which the front Part of a suspension bolt g comprises half of its circumference, this Bolt z. B. on the wing z by means of a flange seated on the underside of the wing or profiled head zo is attached.

Means for suspending the rear of the missile body must also be: 2 @ are provided. These means are designed to hit the missile body in the direction from back to front any forces acting in the axial direction oppose a resistance which in any case is smaller than the. Thrust of the rocket's propulsion system, but this resistance is sufficient to accidental forward movement and unwanted unhooking of the stabilization tail 4 to prevent the missile from being launched.

The means of suspending the rear part of the missile body .2 can expediently be formed in that the bottom plug r z of the rocket from an arm 12 permanently attached under the wing r.

Furthermore, the arm 12 is expediently indicated so that it can move backwards by a pivoting movement about an axis 13 , so that it will soon be released. This movement is caused by the aercydynar pressure of the surrounding air, by the action of the gases ending up in the rocket or by the action of a return system; sr z. B. a specially provided spring i ¢, is favored :. As already mentioned, the bottom plug ii is connected to the arrn 12 by fastening means. which are so schwaich in the axial direction that they give way when the rocket body 2 is propelled forward by the drive system of the rocket.

Finally, it is expedient to have a circuit along the arm 12 for the electrical ignition of the rocket to: lead, which then through the ground plug i i in the: missile body 2 enters.

The formation of the above suspension system, in particular the system for attaching the bottom plug i i to the arm 12 can be done in various ways take place. Fig. 5 shows a particularly advantageous embodiment of this system.

The bottom plug i i lies in a hole in this end of the arm 12 and is rearwardly through a threaded part protruding behind the arm 12 15 extended.

A blocking nut 16 is screwed onto the threaded part 15, by; the suit of which by the missile body 2 and the tail unit q. formed arrangement backwards, is pulled, whereby the tail unit is attached to the corresponding suspension bolt g is blocked.

A local weakening "a" is provided in front of the threaded part 15, which is designed so that the system for rear attachment of the missile the Axial strength desired, neither too: strong nor too weak, is obtained.

The ignition circuit 17 of the missile enters the missile body 12 through the threaded part 15, which of; your. Body to be isolated and the role of one Intermediate leaders play kainn.

With such an arrangement, which is shown in Fig. I before the launch the rocket is ejected as follows: After the ignition of the; Drive system, The rocket moves the rocket body 2 after breaking the rear attachment forward, and arm 12 folds backward. During this initial phase the start remains the: tail unit ¢ practically due to its inertia in relation to it the wing i immobile. Whom the rear frustoconical part 2 @ of the missile body to the height of this tail unit q. comes, he presses into the sleeve 6 and takes when passing the tail unit with (position shown in Fig. 3), which so in its normal axial position on the missile body 2 is attached.

One in the above way with suspended by means of a sliding, tail unit; A missile-equipped fighter has the following advantages Accuracy of the missiles as a result of the sliding Tail unit resulted in excellent leadership. This sufficiency is done without dali exhaust pipes must be used whose weight and air resistance are a hindrance for the Airplane form.

In the distance jumped under the underside after the missiles were dropped of the wing i only suspension parts with low air resistance (suspension bolts and their owners).

Furthermore, the rocket's suspension system is special, simple and easy has special lifting devices so that the rocket can be attached quickly by: can be carried out by inexperienced personnel.

In the embodiment described above, it was assumed that the Hang rockets next to each other under the part that serves as a holder ( This example wings i), wolb @ ei sliding tail units of rockets were all hung directly from this part.

One can; however, according to an embodiment shown schematically in FIGS. 6 and 7, several rockets A, B, C provided with a sliding, tail unit are staggered according to height, these rockets z. B. form a roughly perpendicular arrangement.

Each missile then hangs with hers. Tail unit on. the one immediately above located. Missile, with only the top missile immediately adjacent to e.g. B. by is attached to the wing i. formed tether.

You then only need to ignite the rockets one after the other by one starts with the lowest one and gradually ascends to the same for each rocket To obtain the dropping process as in the previous embodiment, the The entirety of the rockets lying over the rocket that has just been dropped - the roll this Halters: plays.

The tail units q. then appropriately play the role of the front one, as above Halters while the various missiles are on; their rear end of a, common Arm 12 are held on: which each missile axially z. B. by theirs. Floor plug is attached, as already stated.

Dais tail unit q. each missile is then expediently in the tail unit the rocket immediately above it, so that the rockets from the front; to the rear, and from top to bottom are arranged in stages, then the common arm 12 is inclined in the same direction.

It should be noted that if the arm 12 backwards; or after can be folded down at the front, means are not provided to temporarily hold it in, to lock the above-mentioned inclined position so that it when launching successive missiles; absorb occurring recoil forces, can..

The, hanging one. any tail into the one immediately above it Tail unit is designed in such a way that this: any tail unit through one forward directed movement can be deducted.

For this, z. B., as shown in Fig. 8, each wing q. on his Front b; betw. Rear edge two complementary parts, e.g. B. an intervening and an encompassing part, e.g. B. a pin 18 .on the leading edge and, a sleeve 19 of the same diameter on the trailing edge.

It is then sufficient to hang in one wing q. (I) one. Tail unit a missile on a wing 4 (II) the tail unit of the immediate above and slightly behind rocket, pin 18 of the wing, 4 (II) in insert the sleeve of the. wing 4 (I), this connection the removal this tail unit: to which wing 4 (I) belongs, by a forward-facing one Movement made possible.

Finally, the, of; the missile assembly -during the air resistance resulting from the period preceding the launch, the missile assembly moved into the wing i. be by z. B., as shown in Fig. 7, at a a foot part 2.i pivotable to the axis 2o parallel to the shot axis, eats in which the. Tail unit of the top rocket is attached, with drive means for lifting or lowering of the missile assembly are provided.

A panel can then expediently be parallel to the missile arrangement 22, which restores the continuity of the underside of the wing i, if. the rocket assembly is in the retracted pitch.

Claims (7)

PATENT CLAIMS: i. Combat equipment, in particular aircraft, which; with at least: one suspended rocket is equipped because of a stabilization, guidance system has which. to that. Rear end of the missile body should be located, if; the rocket its orbit: passes through, characterized in that this tail unit on the body of the missile can slide and in a forward position as a; part The system used to suspend the missile on the frame of the actual device is, wherein the rear part of the missile body has axial holding means, which that, take the tail unit with you, and hold it in the rear position if this is rear Part of: missile body. after the firing of the rakeite arrives at the height of the tail unit, so that this during the initial phase of the launch of the rocket at the same time the role of a hanging part and a, guide, fil, flirr serve as the missile body plays. 2. Apparatus according to claim i, characterized in that that sliding tail unit is formed by a plurality of t r, a, dial lying wings (4) which on a sleeve (6) sliding on the missile body (2) with slight friction are. 3. Device me claim 2, characterized in that net, at least. a wing (4) all part for attaching the tail unit is used. 4. Apparatus according to claim 3, characterized in that the: sliding tail unit at an angle of approximately 45 ° on two lying successive wings is suspended. 5. device nasch claim 3, characterized in that the, Verih @ akung the wings (4) with the corresponding, carried by the wing (i): parts; so, that the wings extend through unhook a forward movement under the action of the axial forces which occur when that at the rear end of the missile body. (2) provided axial Reach holding means directly sleeve (6). 6. Apparatus according to claim i, characterized in that geli: ennz: calibrates; that the axial holding means provided at the rear end of the rocket body (2) are bundled by a conical bearing surface (2d) with a forwardly directed tip which, when the rocket is started, rests against the rear edge of the sleeve (6) , which then; is clamped on this support surface and taken along by the missile body (2). 7. Apparatus according to claim 3, characterized in that the rods of suspension parts spielendiem wing (4) belong to a front suspension system of the rocket body (2), wherein the rocket body has rear suspension means which are designed soi that they possibly the Missile bodies propel forward forces in the axial direction oppose a resistance, which on everyone. Case smaller than the thrust of the A.ntri: ebssys @ system. eats the rocket, but this resistance is so great that it prevents accidental forward movement and unwanted detachment of the stabilization tail unit (4) before the rocket fires. B. Apparatus according to claim 7, characterized in that the wings (4) playing the role of suspension parts have in their rear edge a groove (8) which is open to the rear and half of the front part of a suspension bolt (9) its circumference, this bolt to your wing (i), z. B: by means of a flange seated on the underside of the wing, or a profiled head (io). 9 ,. Device according to claim 7, characterized in that the. rear suspension means of the missile body (2) are formed by an arm (12), which remains permanently under the aircraft wing (i) and is attached to a ground plug (ri) firmly connected to the missile body (2). ok Apparatus according to Claim g, characterized in that the arm (12) is pivotable and can be folded back after the rocket has been dropped, this folding back preferably towards the rear. he follows. ii. Apparatus according to Claim 1, characterized in that: it has several rockets (El, B, C) with sliding tail units, which are vertically stable and one substantially. Form a vertical arrangement, each rocket with its tail unit on the rocket immediately above it, s, o that only, the top notch directly on the z. B. hanging by the wing (i) formed tether. . 12. Apparatus nasch claim ii, characterized in that for each missile the tail unit (4) the; The role of the front holder plays the role, whereby the, different missiles, are held towards the back by a common arm (i2). 13. Apparatus according to claim z2, daid @ urch characterized in that the Leitweirk (4) of each rocket is attached to the tail unit of the unmittable rocket, the rockets: from front to back, and from bottom to top stepped down @eit, with the common arm (i2) inclined in the same direction. 14. Apparatus according to claim 13, characterized in that the ketinz @ eichnet that the Flugil (4) of the sliding, I.eitwerke on their front or rear edge have two complementary parts, for. B. an engaging and an encompassing part, e.g. B. a pin (1ä) on your front edge and a sleeve (r9) of the same diameter on the rear edge. 1 5. Device according to claim rr, characterized in that the @ ß by the! The height of the staggered missiles arrangement can be drawn into the interior of the aircraft.