IL27874A - Bomb braking system - Google Patents

Description

Bomb braking system FORGES DE 26447 This invention relates to a system provided for braking a bomb released at low altitude and at high As is bombs are most efficiently released when flying in skimming the ground at high This method has the advantage of little endangering the attacking plane since i is under radar reach of the The shooting accuracy realizable when attacking in skimming the ground is very high since the bombs may be released at a very small height above the In the bombs may be so released even in disadvantageous atmospheric a normal unbraked bomb released in skimming the ground at high speed endangers the plane So as not to endanger the plane by said the latter should be provided with a braking a braking rocket introduces the following drawbacks in case of light structural the bomb ricochets and is without any in case of bulky structural the bomb will break up by the high speed without having fulfilled its functio Various relatively complicated systems have been said systems being provided to allow releasing bombs in skimming the ground without endangering the plane and the crew A first system brakes the bomb after releasing from the plane by means of a parachute provided at the rear of the In another the braking is provided by a th tion of spacing traps and a Still in another bomb is braked only with spacing These three braking systems are too complicated and very subject to defects when suddenly opening the braking the impact is too In a sudden braking This invention is based upon the new concept of a and flexible braking of the According to the present there is provided an missile comprising a bomb with transverse braking corrugations at the nose a smooth cap for temporarily covering the for removing the cap from the nose and optional retarding for effecting such removal or at a predetermined time after the launching of the In one form of the invention the cap is unitary and connected by at least a filiform element to an adjoining portion of the aircraf carrying the The connection is such that the cap is separated from the bomb after the is In an alternative form of the inventiont the cap is constituted by a plurality of sections releasably connected together in covering relationship to nose cone of the In this form of the sections are hinged to the bomb and held together in covering relationship to the nose cone b suitable means such as a a When the missile is the connection between sections is simultaneously with launching or after a predetermined time subsequent to The preferred way to remove the connection between the sections is by of an explosive charge which may be detonated by moans of a pyrotechnic retarding charge a slow burning powder that is initiated when the missile is When the explosive charge detonates removing the connection holding the sections of the cover the seotions unfold By means of the removable a bomb provided with transverse braking sections at the nose cone can be externally of aircraft without introducing undesirable drag effects on the aircraft during flight to a Only after the missile is launched from the aircraft the braking corrugations effective to increase drag on the For a better understanding of the present and to show how it can be carried out in reference should be made to the accompanying drawings figure 1 shows a plan view of a bomb the front of presents a braking surface 2 shows a half plan view and a half section of a complementary cap temporarily cancellin the braking figure 3 shows a partial plan view and a partial gitudinal section of the application of a cap according to figure 2 on a bomb whose nose cone covered with a sleeve having a corrugated figure 4 shows a partial plan a partial gitudinal section of the application of a cap according to figure 2 on a bomb figure figure 5 is a view similar to that of figure 4 senting another embodiment realizing and mounting the cover according to figure A casing 1 shown in figure 3 according to the invention is generally of a plastic material or any other suitable material under the form of cap capable of correctly contouring the nose cone of bomb 2 at least upon a predetermined length The internal face of said cap will be generally smooth in any it be determined in accordance with the corresponding portion of bomb whereas the external surface of said cap will present successive steps generally outlined by similar or spaced or differently spaced annular grooves in accordance with the braking effect being When applying such casing 1 to a the section of the bomb is increased and due to this increase and the effect of the external profile of said the friction resistance is substantially the falling time of the bomb after releasing is which is sufficient to give a sufficient safety distance to the plane By means of such casing forming a very braking means the same effects as those provided by using complex and expensive bracing means are This braking casing may be fitted to bomb before loading and it may be secured to said suspension rings bomb without any disassembling or mounting operation of any portion of the According to the present the guiding mechanism is kept Integral with the In due to the effect of the longitudinal 8 extending ously as a groove up to the nose of the owing to the back pressure when the bomb has a tendency to thereby bringing it more rapidly and systematically in its vertical position for a normal Of the same braking effect may be obtained by g the bomb as represented by way of example in figure the front portion presenting namely a profile similar to the The successive parallel grooves and ribs 6 are also provided Whatever embodiment may the corrugated surfaces may be advantageously covered with a cap 11 having a smooth external surface when the braking effect is not required during the flight to a target when the missile is carried externally the This cap will be conditioned so that shape and its internal dimensions allow an by leaning upon the outermost generatrices of said stepped ribs As described for the cap having a corrugated external this complementary cap may according to the cases length or any other length consistent with the bomb type and the used separating In one this complementary cap may be connected by at least a filiform element having a good resistance with an adjoining portion of the plane in such manner due to the effect of the speed differences immediately releasing the bomb from the the said cap with a smooth external wall is separated from the projectile the said cap having a smooth external wall could be arranged with being assembled by a means freed when A modification of this embodiment is represented in figure according to which the complementary cap li is provided in four sections three of which are eaoh section being hinged on the bomb body indicated in These four sections are kept in covering position by any suitable means such as fasteners or by weld spots which are broken by firing an explosive charge 1 under the action of the releasing mechanism of the bomb and preferably provided with a retarding the releasing initiates a slow burning powder tho detonates the charge a the miss le is of the said occupy position indicated in dotted lines i figure positio in which they provide each additional surfaces and complementary sur ces For any cap having a smooth or not smooth external there may be used any suitable materia such pressed material bination insufficientOCRQuality

Claims (5)

1. An air-dropped missile comprising a bomb with transverse braking corrugations at the nose cone; a smooth cap for temporarily covering the corrugations; means for removing the cap from the nose cone; and-ajiHuwl retarding means for effecting such removal wpeti, -«r at a predetermined time after the launching of the missile.

2. An air droppable missile according to claim 1 wherein the cap is constituted by a plurality of separate sections releasably oonnected together in covering relationship to the nose cone.

3. An air droppable missile according to claim 2 wherein the sections are hinged to the body of the bomb and are unfolded when the sections are disconnected from each other for providing additional braking means.

4. An air droppable missile according to claim 1 wherein the cap is unitary and the means for removing the cap constitutes a filiform element conneotable to an adjoining portion of an aircraft carrying the missile.

5. An air droppable missile substantially as described above by way of example and with reference to the accompanying drawings· For the Applicants PR. RlfoNHOLI) COM AM) PARTNERS ¾r« (