DE959704C - Suspension device for rockets, especially on aircraft - Google Patents

Description

ISSUED MARCH 7, 1957

B 35778 XI / 62 b

The invention relates to oath, sea or air combat equipment, which with at least one suspension device · in the shooting position held missile, where the expression "equipped with at least one missile Combat equipment «below both the actual combat equipment. as well as that of this one Including carried missiles. In terms of combat equipment of this type, the invention relates in particular to if not exclusively, the missile-equipped aircraft, in particular aircraft, the missiles generally being located under the wings of the apparatus are.

The invention aims in particular to train devices of this type so that they are better than before correspond to the various requirements of practice, especially with regard to aerodynamic Resistance of the rocket suspension system and the accuracy of the shooting.

For this purpose, according to the invention, in such, Devices which are equipped with at least one missile which is axially attached to its rear part by a gripping device held in the working position by at least one locking member is held, this locking member carried by a holder, which the action of the beginning of the combustion Propellant charge the rocket is exposed to evolved gases and 'under the action of these gases against the action of a return system from an advanced position in which the Gripping device is locked, can retreat into a rearward position in which the Gripping device is released.

The invention is below in its application to the suspension of missiles the wings of an aircraft explained by way of example with reference to the drawing. ao Fig. ι shows schematically a side view an aircraft wing · under which missiles according to the invention are hung;

Fig. 2 shows the same arrangement after Launch of missiles;

as Fig. 3 shows on a larger scale in a section Side view of a rear suspension device of a missile, which is shown in the working position is, d. 'H. in the position in which the missile is blocked; Fig. 4 and! 5 show the same device in a sectional side view or from the front, the device being shown in the release column.

The plane is formed on the whole in any suitable manner, but with the exception of the ι for suspending the missile under the wing and certain ¹ in more detail below "parts described.

These parts are made in a manner known per se designed so that each rocket was temporarily held in the axial direction by a gripping device is, the training z. B. in the schematically shown in Fig. 1 and 2 only by way of example Way can be taken ·. The Aufliängeteile exist in this training the rocket essentially consists of buckets of frame 2, which is fastened under wing 1 andi one not shown near its front part Device for hanging the tail unit 3 of the suspended rocket 4 carries, wherein the tail unit is slidably mounted on the rocket and so for holding and guiding the Missile is used at the beginning of the launch, whereupon it is due to the action of a rear attachment is taken away by the rocket when the final part of the rocket is level with this tail unit comes.

Furthermore, a (preferably retractable into the frame 2 by a pivoting movement) fastening arm 5 with a in Fig. 1 is schematically at. P shown gripping device is provided, which can carry the rocket 4 in the firing position at the rear and hold it back axially, wherein means are provided for retracting the fastening arm after the rocket has been fired (position shown in FIG. 2). It should be noted that several rockets 4 can be carried by one and the same fastening arm, which are staggered from top, back to front and bottom, each rocket except the top one being attached with its tail unit to the tail unit of the rocket immediately above it. In this case the common fastening arm must have a gripping device for each rocket and thus be provided with two such devices if, as shown in FIG. ¹ , it is intended for the suspension of two rockets one below the other.

Finally, it should be mentioned that the parts in the frame 2 are useful for actuation and locking of the arm 5 and all or part of the auxiliary devices housed which cooperate with the missiles before they are launched, e.g. B. electrical Transformers for charging ignition capacitors.

The above arrangement is now made so that each gripping device is the corresponding Missile automatically under the action of the beginning of the combustion of the propellant charge of the Missile releases evolved gases.

For this purpose, according to the invention, the locking device released by the adjustment of a movable holder, furthermore the dynamic one Pressure of the gases coming out of the rocket is exposed and under the action of this pressure counter to the action of a Return system can withdraw.

This has the effect that the rocket 4 is forcibly retained as long as the locking device do not experience an adjustment in relation to the organs for axial restraint Has. Furthermore, by suitable calibration of the in the direction of return of the locking system in its working position, the RücMiolsystetns work at will be determined in · which the locking device is actually adjusted by the action of the gases.

The entire gripping device can advantageously be designed so that the mutual movement between the locking device and the restraint organs (in the sense of release of these organs) either from an actual adjustment of the locking device under the action of the gases against the 'assumed to be fixed retention organs (normal work) or an adjustment of the restraint organs by the Missile exerted pulling force can result, which generally corresponds to the case that the locking device remains blocked as a result of a fault. Approval takes place under these conditions the rocket at normal. Working through the from the gases to the the locking device controlling moving part exerted dynamic

see pressure and work as a safety device (Blocking of the locking device) a little later under the action of the exerted by the missile on the restraint organs growing train.

For example, the following is a particular embodiment of such a gripping device described with double release option. In this version, the organs exist for

ίο axial retention of the missile from arms 6, which are pivotable about axes 7 in the manner of the legs of a pair of pliers, with z. B '. two diametrically opposing arms are present, each of which has a transverse pin 8 projecting on each side wearing.

The arms 6 are particularly in terms of the shape of their front end and the location of their Pivot axes 7 designed so that they are in their mutual. Approach the diverging

ao terende of the missile capture and so on this one can exert axial restraint.

To keep the arms 6 in this Greifstelliung, a locking device with two Pairs of hooks 9 are provided, which calibrate over

can place the pins 8 when the arms 6 are in the gripping position. The hooks 9 are carried by a part 10 which is arranged in the axis of the missile 4 and opposite the Holding arm 5 can move back against the action of a return spring 11.

The part 10 is given such a shape that its middle part has an end cross-section, which nmr partially the mouth of the nozzle of the Rocket 4 matches.

Furthermore, the design is made such that the part 10 counteracts the action of the spring 11 can be withdrawn and thus release the arms 6, in order to allow the missile to be deployed enable.

The Schwehkachsen 7 of the arms 6 are carried by a sleeve 12 which _{slides in a rigidly connected to the support arm 5 sleeve 5 a} , with a z. B. is arranged by a plate spring stack 13 formed elastic system between a shoulder firmly connected to the arm 5 and a stop 10 firmly connected to the sleeve 12, so that the sleeve is constantly pulled into its rearward position.

It should be noted that the power of the Return system 13 is considerably larger (e.g., of the order of magnitude 200kg) must be than the force of the Return system 11.

The means for voluntarily withdrawing the hooks 9 to release the arms 6 for insertion the rocket 4 are expediently formed by a synchronization control, which z. B. has a pin and a helical cam. These actuating means can; aside from that used to operate the rocket's electrical circuits (in particular of the circuit for firing), such that when the hooks 9 are retracted,

d. H. if the missile is not held axially. these circuits are interrupted.

For this, z. For example, as shown in FIGS. 3 and 4, a tubular rotatable part 15, which can be rotated by an actuating lever 16, can be inserted into the sleeve 12. This tubular part 15 carries a finger 17 which is adjusted during the rotary movement of the tubular part in a helical groove 18 in the wall of the hollow hub of the actuating part 10 of the locking device.

The lever 16 carries a, cam 19, which, when the lever is in the position corresponding to the locking of the arms 6, the Closure of a switch 20 for the electrical connection of the missile causes. A resilient locking latch 21 allows the lever 16 to be temporarily locked in its closed position. This arrangement is expediently completed by a nose 22, which in front of the hub of the Part 10 is and forms a power connection, which with a for this purpose in the nozzle of the rocket 4 Supplementary power connector provided for connecting the various electrical devices the rocket can cooperate, the leading to this multiple power connection 22 Conductors run through the tubular part 15 andl after passing through lateral openings in this tubular part and the one surrounding it Parts lead to a shaking device 23 which is accommodated in the holding arm 5.

There are also guide fingers 24 (e.g. four on either side of the arms 6 in the one shown in FIG. 5 Wise arranged fingers) for guiding the rocket during deployment and launch.

The above arrangement works as follows: After pivoting the lever 16, that the hooks 9 are withdrawn and thus the arms 6 are released, the rear part of the rocket 4 is inserted between the guide fingers 24 and the rocket is pushed back until its inner power connection part 'with the provided in the nose 22 additional connection part in engagement comes, whereupon the arms 6 may capture the final part of the missile. The lever 16 is then in returned to its original position, which allows the part 10 carrying the hooks 9, under the Action of the spring 11 again to assume the position shown in Fig. 3, in which the Hook lock the arms 6 by touching their inner edge with the corresponding pin 8, with these inner edges expediently a little to the front. Since the repatriation of the Lever 16 has closed switch 20 in its initial position, are "the electrical systems the missile is connected to the power sources on board the aircraft, and the Missile is ready to launch. After igniting the rocket's propellant charge, it ejects from the nozzle of the Missile 4 coming beam back the part 10 against the action of the spring 11, and the hook 9 give the pins 8 as well as those bearing these pins Arms 6 free (position shown in Fig. 4). the

Arms can then be placed under that of that. rear diverging · part of the rocket exerted cam movement step back freely, and the missile leaves the gripping device. If the part io from any one Basically works incorrectly or is even completely blocked, the launch of the missile is delayed until the moment in which the tensile force exerted by it on the gripping device is sufficient to move the disc spring stack 13 squeeze. The arrangement formed by the arms 6 and the sleeve 12 then moves forward under the action of this tensile force, with the result that the Advance pins 8 relative to hook 9, thereby releasing arms 6.

Finally, it should be noted that the end part of the missile 4 in particular with regard to its mechanical resistance to the compressive forces acting in the axial direction so ausao must be formed so that it can withstand the forces that occur during the release.

The above device has the following advantages, among others:

i. Blocking the missile without: game; 2. Insensitivity of the rear blocking device of the rocket to longitudinal accelerations, provided, of course, that these accelerations are not a forward force generate the value of which is greater than that of the pulling force required to release it;

3. Release of the rocket during normal work by means of a relatively small force * which of the jet coming out of the nozzle of the rocket immediately at the beginning of the work of the same can be supplied, thereby reducing the pulse loss caused by the time difference between the moment the propellant is ignited and the moment it is released stems from;

4. Possibility of producing a relatively thin rocket nozzle, since the nozzle on this compressive forces exerted by the gripping device are considerably smaller than · the · holding devices with resilient pliers;

S security through the release system by means of the pulling force exerted by the missile on the gripping device.

Claims (10)

PATENT CLAIMS: i. Attacking device at the rear end of a missile for axial restraint of the missile, in particular for suspension on aircraft, which device dl by at least a locking member is held in the working position, characterized in that the Locking member (9) is carried by a holder (10), which the action of the to Beginning] of the combustion of the propellant charge of the rocket is exposed to evolved gases and under the action of these gases against the action of a return system (11) from -einer Position in which the gripping device (6) is locked into a rearward position, in which the gripping device (6) is released, can pass over. 2. Apparatus according to claim 1, characterized in that the organs (6) for the axial Holding back by hooks (9) in the working position blocked by the Backward movement 'this is the dynamic pressure of the gases developed by the rocket exposed movable holder (10) are withdrawn. 3. Apparatus according to claim 1, characterized in that the mutual movement between the locking device and the retaining organs (6) in the sense of Release of these organs either by the backward movement of the holder (10) below the effect of the gases on the retention organs assumed to be fixed (6) (normal work) or from an adjustment of the restraint organs (6) by the the missile exerted tensile force when the holder (10) is blocked by a Malfunction. 4. Apparatus according to claim 2 or 3, characterized in that each organ for axial retention is formed by an arm (6) which is ^{pivotable about an axis (7) and 1} carries at least one transverse pin (8), Over which, when the arm in question is in the gripping position, the hook (9) can be placed, which is carried by the movable part (10) subject to the action of the gases, the design being such that at the backward movement of the movable part (10) under the action of the gases of the hook (9) releases the pin (8) so that the arm (6) in turn can release the missile. 5. Device according to one of claims 1 to 4, characterized in that the end face of this holder (10) is only part of the Muzzle cross-section of the nozzle of the rocket (4) is equivalent to. 6. Apparatus according to claim 3 and 4, characterized in that the pivot axes (7) of the arms (6) are carried by a sleeve (12) which is in one with the düe gripping device holding arm firmly connected sleeve (So) slides, using an elastic system (13) between a firmly connected to the arm (5) Shoulder and a stop (14) fixedly connected to the sleeve (12) is that a force constantly acts on the sleeve, which this into its rear Seeking to lead a position. 7. Apparatus according to claim 6, characterized in that 'd'ass the return system (13) tao exerts a force which is considerably greater (e.g. 200kg in terms of magnitude) than dlie Force (e.g. of the order of magnitude iokg) of the Return systems (11) for the holder (10) is. 8. Apparatus according to claim 1, marked iss characterized by manually operated devices tungera to release the locking device for the insertion of the missile. 9. Apparatus according to claim 4 and 8, characterized in that the manually operable devices cause the backward movement of the holder of the hooks (9). 10. Apparatus according to claim 8 or 9, characterized in that the by hand actuatable devices in their position to release the locking device interrupt electrical circuits feeding the missile. 1 sheet of drawings © 609580/76 8.55 (609 833 2.57)