US3921937A - Projectile or rocket preferably with unfolded tail unit - Google Patents

Projectile or rocket preferably with unfolded tail unit Download PDF

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Publication number
US3921937A
US3921937A US366755A US36675573A US3921937A US 3921937 A US3921937 A US 3921937A US 366755 A US366755 A US 366755A US 36675573 A US36675573 A US 36675573A US 3921937 A US3921937 A US 3921937A
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Prior art keywords
disk
sliding sleeve
projectile
rudder carrier
annular
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Expired - Lifetime
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US366755A
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English (en)
Inventor
Alfred Voss
Manfred Strunk
Heinz Kroschel
Heinz Wilhelm Kreutz
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Dynamit Nobel AG
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Dynamit Nobel AG
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • F42B10/20—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel deployed by combustion gas pressure, or by pneumatic or hydraulic forces

Definitions

  • ABSTRACT A projectile. preferably a rocket with an unfoldable ll; "MI/M 1 11 l Nov. 25, 1975 tail or rudder fin unit with a plurality of guiding fins movable between a storage position extending tangentially along the projectile to a flight position extending radially of the projectile longitudinal axis.
  • a sliding sleeve is arranged in the projectile for engagement with pivot levers on the guiding fins so as to maintain the guiding fins in the storage position until a predetermined instant in the launching of the projectile at which time the sliding sleeve engages the pivot levers to unfold the fins and force them into their flight position
  • the sliding sleeve is maintained in a first arrest ing position for holding the pivot levers and guide this in the storage position by means of a connecting disk abutting the rear end of the sleeve
  • This connecting disk is attached to the projectile in such a manner that ignition of propellant charge means disposed rearwardly of the disk cause a disconnection of the disk with respect to the projectile, with a consequent falling away of the disk after the projectile has left a gun barrel so that a rocket engine disposed forwardly of the disk can operate unimpeded by the disk.
  • the disk is provided with a throttle opening for accommodating transfer of propellant charge gases to ignite the rocket cruising engine and to assist a compression spring in moving the sleeve rearwardly to unfold the guiding fins.
  • Preferred embodiments utilize the disk arrange ment for accommodating the propellant charge initial acceleration and the later operation of the cruising engine with or without the further inclusion of the sliding sleeve for controlling foldable guide fins
  • Other features include a cup spring arrangement for holding a warhead detonator in position between detachably connected parts of the projectile, as well as novel conduit means for transferring the propellant charge gases to an ignition element for the crusing engine.
  • PROJECTILE OR ROCKET PREFERABLY WITH UNFOLDED TAIL UNIT BACKGROUND AND SUMMARY OF THE INVENTION This invention relates to a projectile or rocket of the type with an unfoldable tail or control flap .unit.
  • the fins or wings which serve as control flaps for this type of projectile can be unfolded about axes arranged at right angles to the longitudinal axis of the projectile or rocket, tangentially to the rudder or control flap unit carrier, by providing that a sliding sleeve, which is disposed in the rudder carrier and can be moved rearwardly by gas pressure and/or spring force, presses against pivot levers eccentrically mounted to the fins.
  • the present invention also contemplates improved rocket and projectile features usuable in other kinds of projectiles and rockets.
  • a control flap unit for projec tiles or rockets which can be fired from the barrel of a gun.
  • the rudder carrier has a longitudinal bore wherein a sliding sleeve is disposed which can be moved axially by means of a spring force.
  • This sliding sleeve presses, with its rear end. against pivot or rotary levers eccentrically arranged at the rudders and thus unfolds, after the projectile or rocket has left the gun barrel, the fins about axes extending at right angles to the longitudinal axis of the projectile or the rocket, tangentially to the rudder carrier, into the flying position.
  • the present invention is based in part on solving the problem of avoiding this above-discussed disadvantage by constructing a projectile or rocket with an unfoldable tail unit in such a manner that the fins can unfold only after the firing has actually taken place.
  • This invention contemplates, for a projectile or a rocket with hinged tail unit of the type mentioned in the foregoing, providing the sliding sleeve with an external annular groove in which the pivot levers engage with their free ends; and holding the sliding sleeve in a position wherein it arrests the fins in the folded condition by means of a connection with the rudder carrier which connection can be released at a predetermined instant during firing.
  • the sliding sleeve is held in its arresting position, for example. by means of two shear pins which, radially opposed to each other, are arranged in a bore penetrating the wall of the rudder carrier and the sliding sleeve.
  • the strength of the shear pins is dimensioned so that they are sheared off during the firing of the projectile or rocket during the acceleration phase due to the sliding sleeve which is pressed rearwardly because of its mass moment of inertia and due to a compression spring which is preferably disposed in front thereof.
  • an additional auxiliary means for holding down the fins, and operable by hand is not required. The fins remain folded until the actual firing and can unfold only when the shear pins have been separated due to the accelerative forces and the projectile or rocket has left the gun barrel. This ensures advantageously a rapid and reliable repeated loading and unloading of the projectile or rocket, as well as the possibility of placing the projectile or rocket back into the packaging container.
  • the sliding sleeve of the present invention is arrested within the rudder carrier preferably so that it contacts, with the rear annular surface of its annular groove, more or less uniformly the pivot levers, in order to extensively inhibit the minor pivotal motions of the fins in the folded condition which could otherwise occur because of the axial play of the pivot levers in the annular groove.
  • a suitable embodiment of the present invention provides that the sliding sleeve is extended toward the rear with a preferably annular-cylindrical extension, and rests with the latter on a disk detachably arranged in the zone of the rear end of the rudder carrier.
  • the disk is threadedly connected from the rear in the rudder carrier and is equipped, for example, with an annular predetermined breaking zone, where the disk is severed under the effect of the powder gases of the propellant firing charge. The severed zone of the disk retains its position wherein it supports the sliding sleeve and an optionally provided compression spring until the projectile or rocket has exited from the gun barrel.
  • the powder gases of the propellant firing charge no longer exert a forwardly directed pressure force on the disk.
  • the severed zone of the disk can then be ejected toward the rear, and the sliding sleeve can move toward the rear, thus unfolding the fins of the rudder.
  • the objective is advantageously attained that the sliding sleeve and the possibly provided compression spring are supported in the bottom or base of the projectile or rocket. so that the pivot levers of the fins, furing firing, are not stressed by the inertia forces of the sliding sleeve and the possibly provided compression spring. As was found in prac tice, the target accuracy could thereby be substantially increased.
  • one of the annular flanges is associated with the annular groove of the sliding sleeve so that the rear annular surface of this one annular flange is simultaneously the front lateral face of the annular groove so as to transmit the compressive forces exerted by the sliding sleeve on the pivot levers during the unfolding of the fins in a maximally favorable manner.
  • the throughflow cross sections of these openings are dimensioned in accordance with the conditions of the respective individual case so that erosions due to maximally high flow velocities can be reliably prevented.
  • the annular flanges can also be provided with axial pressure-equalizing apertures, in accordance with another suggestion of the present invention.
  • the detachable connection between the sliding sleeve and the rudder carrier can be a disk. the central portion of which. supporting the sliding sleeve. can be severed by way of an annular predetermined rupturing zone.
  • the disk can also be held by means of shear pins or the like, which release the disk at a predetermined load or stress according to further embodiments contemplated by the present invention.
  • the disk can jam while being flung out of the rear end of the rudder carrier. and thereby exert improper transverse forces on the projectile or rocket. As a consequence thereof. pendulating movements are created which impair the target accuracy and, in case of adverse circumstances. can even be the cause of ricochets.
  • the present invention contemplates further embodiments with the disk inserted in the rear end of the rudder carrier such that it rests in the forward direction against a shoulder formed interiorly at the rudder carrier and is held in this position by means of a tubular member arranged behind the disk.
  • This tubular member contacts with its front edge an annular step of the disk and is firmly joined in its rear area with the rudder carrier. leaving an annular cavity between its front zone and the rudder carrier. which latter is formed with an inside cross section that is enlarged as compared to the cross section of the disk.
  • the front zone of the tubular member which is. for example, of a conical shape.
  • the present invention contemplates use of this type of disk mounting with the tubular member not only when the disk serves for arresting a sliding sleeve. but advantageously also in all those cases wherein movable parts (such as the disk) are to be released upon reaching a certain gas pressure.
  • movable parts such as the disk
  • a certain gas pressure for example. this is the case with a rocket which can be fired from a gun barrel and wherein the propellant powder charge of the cruising engine is ignited by the powder gases of the launching charge disposed behind the rocket.
  • a disk is arranged in the bottom of the rocket.
  • a throttle disk held in this manner can be used, for example, together with a control flap unit, the fins of which are held in the folded condition by means of a ring pushed thereover.
  • this throttle disk simultaneously for the arresting of the fins according to an embodiment of the present invention
  • the disk mounting of this invention is constructed so that the disk, when a certain excess pressure occurs within the tubular member, is uniformly released. In order to obtain uniform results for volume produced rockets, maximally low pressure should be ambient in the annular cavity outside of the tubular member.
  • the disk and the tubular member are to be inserted into the rear end of the rudder carrier so that as long as the tubular member hasnot yet freed the disk practically no powder gases of the propellant firing charge, or at least only a very minor amount, can enter into the outer annular cavity.
  • the rudder carrier is formed with a continuous edge on the inside at the transition from the zone receiving the disk to the zone receiving the tubular member. The tubular member can then be pressed against this edge with the outer surface of its front area.
  • the tubular member can either initially contact this edge, or can be expanded to a minor extent for contacting purposes under the effect of the powder gas pressure of the propellant firing charge and can then be pressed against this edge.
  • an additional seal of the outer cavity is thus attained, in that, during the pressure rise in the tubular member, the latter is pressed against the edge of the rudder carrier and, only after reaching a certain pressure buildup, is pressed toward the outside into the cavity disposed therebehind while sliding with its front zone along this edge.
  • a further improvement of the seal for the cavity can also be obtained, according to this invention, by providing that the disk is supported on the annular shoulder ofthe rudder carrier by means of an annular sealing strip or gasket.
  • the tubular member is fixedly connected with the rudder carrier with its rear zone basically by being inserted therein with a press fit.
  • the tubular member can be glued with its rear zone into the rudder carrier, for example by means of a two component or dual adhesive on the basis of an epoxy resin.
  • tubular member engages, with its rear edge which is beaded on the outside preferably by flanging, into a corresponding annular groove disposed on the inside of the rudder carrier.
  • the projectile or rocket according to this invention is preferably utilized with a hollow-charge warhead. in order to initiate the hollow charge upon impact of the projectile or rocket, it has been contemplated to dispose, in the rear of the projectile or rocket. a piezoelectric percussion or impact detonator or fuzc. According to the present invention, the provision is made, in this connection, to retain the percussion detonator with the interposition of a spring element, preferably including at least one cup spring, between the threadedly connected front and rear portions of the projectile rear or rocket tail.
  • a spring element preferably including at least one cup spring
  • the divided construction of the rear section according to this invention makes it possible to make do without special mounting elements for the impact detonator, such as, for example, screws or synthetic resin housings, while the interposed spring element ensures that the impact detonator, in spite of the usual manufacturing tolerances, is pressed sufficiently firmly against the bottom of the recess which receives the det onator. Consequently, the shock piezoelectric produced during impact of the projectile or rocket in the hollow-charge head is reliably transmitted to the peizoelectric element and produces the ignition voltage at that point.
  • the combustion chamber of the cruising engine of the rocket according to this invention is to be sealed off from outside influences, such as water, for example.
  • This seal must also withstand mechanical stresses, for example due to shocks during transport or ejection from a supply plane.
  • the flawless ignition of the cruising engine by means of the powder gases ofthe propellant firing charge must not be impaired, either, in a temperature range of, for example, 40 C. to +50 C.
  • portions of the seal must not result in clogging of the nozzle.
  • the provision is made, therefore, for this purpose to cover the inside cross section of the nozzle with a thin disk or foil of a metal or a synthetic resin which can be ruptured by the powder gases.
  • This disk or foil is preferably disposed downstream of the narrowest nozzle cross section as seen in the flow direction.
  • the zone of the narrowest nozzle cross section is exposed to strong thermal and mechanical stresses, due to the very rapidly flowing hot powder gases. It has been contemplated to accommodate these stresses by producing the nozzle section having the narrowest cross section as a separate part from a more rugged material, such as, for example, steel or graphite, and then inserting this nozzle section into a special nozzle carrier of aluminum, for example.
  • the disk or foil of the present invention can be advantageously clamped between the nozzle carrier and the nozzle inserted therein.
  • a disk or foil is used made ofa synthetic resin, it is advantageous, with a view toward the required proofness to water vapor or steam-proofness, to deposit on one side thereof a metal, such as aluminum, for example, by vaporization.
  • Rockets which can be fired from a gun barrel are subject, in contrast to the usual rockets, to considerable accelerations which can amount to up to about 7,000 g. s (g. gravity force). If the cruising engine is to be ignited by the powder gases of the propellant firing charge, there is the problem to arrange the ignition charge for the cruising engine so that it will still be reliably ignited by the powder gases of the propellant firing charge at temperatures of, for example 40C., on the one hand, and so that the detonator is not destroyed, on the other hand. due to the very strong acceleration forces during firing or is otherwise impaired in its flawless operation.
  • the ignitor or ignition charge in a housing fixedly disposed on the side of the combustion chamber opposite the nozzle and 7 being perforated like a sieve in the zone of the ignition charge.
  • the housing is suitably provided with a cupshaped indentation wherein the ignition charge. formed in the shape of a pellet. is securely held.
  • a particularly simple and suitable mounting of the housing can be obtained by clamping the housing between the front end wall of the combustion chamber and the flame-inhibiting casing of the solid propellant of the cruising engine.
  • FIG. I is a part sectional side view of a rocket constructed in accordance with the present invention which is inserted in a gun barrel;
  • FIG. 2 is a cross-sectional side view of a part of the rocket of FIG. 1 which illustrates the rear end of the rudder carrier with the sliding sleeve;
  • FIGS. 3 and 4 are views similar to FIG. 2 which show two modifications of the present invention with differently shaped sliding sleeves;
  • FIG. 5 is a schematic partially cross-sectional side view of a part of the rocket of FIG. I which illustrates the rear end of the rudder carrier with unfolded fins;
  • FIG. 6 is an enlarged cross-sectional side view which shows the disk mounting at the rear end of the rudder carrier in accordance with the present invention
  • FIG. 7 is a partial cross-sectional side view of a front part of the rocket of FIG. I which shows the mounting of the impact detonator;
  • FIG. 8 is a partial cross-sectional side view illustrating details of the modified cruising engine constructed in accordance with the present invention.
  • FIG. 9 is a cross-sectional side view of part of the rocket of FIG. I which shows the mounting of the ignition charge.
  • FIG. I0 is an end sectional view which shows the housing for the ignition charge for the rocket of FIG. 1.
  • the rocket inserted according to FIG. I in a gun barrel I from the front and being illustrated partially in section. has a nose 2, a tail or rear 3. a rudder carrier 4, and a propellant firing charge 5.
  • the rudder carrier 4 is provided with a longitudinal bore 6 wherein an axially movable sliding sleeve 7 and a compression spring 8 are housed.
  • fins 9 are attached with kingpins 10. In the FIG. 1 illustration. the fins 9 are folded against the rudder carrier 4.
  • a pivot lever 11 is attached to each fin 9 at a spacing from the kingpins I0.
  • Each of the pivot levers extends through respective circular-arc-shaped slots l2 in the rudder carrier 4 into the bore 6 thereof and. at that point. projects with a free end into annular groove 13 of the sliding sleeve 7.
  • the axial play between the pivot lever II and the annular groove I3 is dimensioned so that the fins 9 are fixed or arrested to the required extent in the folded storage position of the fins.
  • the sliding sleeve 7 is shown on an enlarged scale.
  • the sliding sleeve 7 is guided in the bore 6 of the rudder carrier 4 by means of two narrow annular flanges ZI, 22.
  • the sliding sleeve 7 has an annular-cylindrical extension 23 serving for the centering of the compression spring 8.
  • an annular disk 24 preferably of steel or polytetrafluoroethylcne is disposed. With the rear extension 14, the sliding sleeve 7 rests against the disk I5.
  • annular groove 13 Directly behind the rear annular flange 22 is an annular groove 13; the rearward annular lateral surface 25 of the groove 13 contacts the pivot levers ll of the fins 9, whereas a small gap is provided between the front lateral surface 26 of the annular groove 13 and the pivot levers II.
  • the spacing between the rear lateral surface 25 and the rear end face of the extension 14 is selected so that the fins 9, in the arrested or stored condition. are flawlessly in contact with the rudder carrier 4.
  • Radial pressure-equalizing apertures 27 are provided in the extension 14 of the sliding sleeve 7.
  • the disk 15, provided with a throttle bore 28, is pressed against the shoulder 29 of the rudder carrier 4 by means of tubular member 16.
  • FIG. 3 shows another embodiment which is similar to the FIG. 2 arrangement except that sliding sleeve 7' differs from sleeve 7 by including additional radial pressure-equalizing apertures 27 arranged in the zone between the annular flanges 21, 22, and axial pressureequalization bores 30 provided in the annular flanges 2], 22 proper.
  • FIG. 4 shows another embodiment which is similar to the FIG. 2 arrangement except that sliding sleeve 7" differs from the sliding sleeve 7 in that the sliding sleeve 7" is sealed by means of 0-seals or sealing rings or other sealing elements 31 at the front annular flange 21 and at the annular shoulder 29 of the rudder carrier 4 with respect to the zone of the rudder carrier 4 having the slots I2.
  • the sliding sleeve 7" has no pressureequalizing apertures in this FIG. 4 embodiment.
  • the tubular element 16 releases the disk 15. As long as the rocket is still within the gun barrel 1, the high pressure of the powder gases of the propellant firing charge 5 is effective on the disk 15 from the rear. A small portion of the powder gases flows through the throttle bore 28 into the bore 6 of the rudder carrier 4;
  • the sliding sleeve 7 rests on the disk I5 during the strong acceleration of the rocket and thus does not exert any stress on the pivot levers II of the fins 9.
  • the gas dammed up in the bore 6 of the rudder carrier 4 can. in part. be discharged through the prcssure-equaL izing apertures 27, 30 in the sliding sleeve 7, 7' and through the slots [2 in the rudder carrier 4, or it is accumulated in the bore 6 of the rudder carrier 4 when using the scaled sliding sleeve 7". in which case the throttle bore 28 of the disk 15 can be of a somewhat smaller diameter. After the rocket has left the gun barrel I. the disk I5 falls off toward the rear. due to the powder gases dammed up in the bore 6.
  • FIG. 5 which shows the rear end of the rudder carrier 4 partially in a sectional view. Only two of the fins 9, which can total. for example. six, are illustrated in order to simplify the drawing.
  • FIG. 6 the mounting of the disk according to this invention is shown on an enlarged scale.
  • the disk I5. which serves on the one hand for fixedly holding the sliding sleeve 7 and. on the other hand. for throttling the pressure of the powder gases of the propellant firing charge 5 to the ignition pressure of the cruising engine, rests with a sealing strip 32 at the shoulder 29 of the rudder carrier 4.
  • the disk is held in this position by means of the tubular member 16 which is made of brass. for example.
  • the tubular member 16 is conically tapered in its front zone 33 toward the disk I5 and rests with its front edge on the annular shoulder 34 of the disk 15. With its rear zone 35, the tubular member l6 engages the rudder carrier 4 and locks.
  • the rudder carrier 4 is provided with a continuous edge 38 at the transition from the zone receiving the disk l5 to the zone receiving the tubular member l6.
  • the tubular member 16 contacts this edge 38 with the outer wall ofits front zone 33.
  • the dimensions are chosen so that the front zone of the tubular member 16 is only little removed from the edge 38. Preferably, this spacing is 0.1 to 0.5 mm. Depending on the strength of the tubular member 16 and the value of the pressure of the powder gases of the propellant firing charge 5. other dimensions can. however. also be selected in individual cases.
  • the front zone 33 of the tubular member 16 is pressed against the edge 38 and thus the outer cavity 39 between the tubular member 16 and the wall of the rudder carrier 4 is additionally sealed off.
  • the pressure of the powder gases has risen to a predetermined value.
  • the front zone 33 of the tubular member 16 is pressed into the cavity 39 as shown in FIG. 5 and thus releases the disk IS.
  • a portion ofthe powder gases flows through the throttle bore 28 of the disk 15 into the combustion chamber of the cruising engine and there ignites the propellant charge [9 disposed thcrcat.
  • the disk 15 as described above is ejected toward the rear so that the fins 9 of the tail unit can unfold into the flight posi tion.
  • the projectile or rocket has a hollow-charge warhead with a hollow charge 40. a conical metal lining 41. and a hood 42.
  • the front portion 43 of the tail 3 is connected with its rear portion 44 by means of the threaded connection 45.
  • the piezoelectric impact detonator 46 Between the two portions 43, 44. the piezoelectric impact detonator 46,
  • the rocket is shown with its cruising engine in a longitudinal sectional view.
  • the combustion chamber of the cruising engine with the solid propellant charge [9 disposed therein is sealed off from outside influences by the foil 48 held between the nozzle carrier 49 and the nozzle 50 inserted therein.
  • Nozzle carrier 49 and nozzle 50 correspond to the nozzle 2" of the Flg. l embodiment.
  • the foil 48 is arranged as seen in the flow direction of the propellant gases of the cruising engine as closely as possible behind the narrowest nozzle cross section 5]. so that the free cross section of the foil is correspondingly small and thus the foil 48 is disintegrated only in relatively small fragments during the ignition of the cruising engine.
  • An advantageous foil is a self-adhesive foil or film of polyester of a thickness of 0.05 mm.. which has a coat of aluminum vaporized on both sides.
  • the ignition charge 52 is arranged in the housing 53.
  • the ignition charge 52 fashioned as a pellet. is accommodated in the central cup-shaped indentation of the housing 53, pointing toward the nozzle side. in such a manner that it reliably withstands even greater accelerative forces.
  • the housing 53 is provided with sieve-like perforations 54 in the zone of the cup-shaped indentation. To facilitate the assembly and in view of the stresses during storage and transportation, the ignition charge 52 is held in the housing 53 by means of a paper disk 55 glued thereon.
  • the housing 53 is held at the side of the combustion chamber oppositely to the nozzle by being clamped in between the end wall 56 of this chamber and the flame-inhibiting insulation 57 of the solid propellent charge [9. which insulation is made. for example. of ethylcellulose.
  • the housing 53 serves advantageously at the same time for centering the solid propellant grain I9 within the combustion chamber.
  • the housing furthermore provides the required pressure equalization between the interior of the solid propellant charge l9 and the gap 58 between the cylindrical insulation 57 and the wall of the combustion chamber. in that the housing is supported on the end wall of the combustion chamber by way of four axial extensions (lugs. projections) 59 arranged in a uniform distribution. between which the propellant gases can pass through and enter the gap 58.
  • a projectile comprising:
  • rudder carrier means extending in the direction of a longitudinal axis of the projectile.
  • each of said guiding fin means being movable about a respective fin pivot axis extending substantially perpendicularly to said longitudinal axis between a first storage position extending tangentially along the rudder carrier means and a second-in-flight position extending outwardly of said rudder carrier means.
  • pivot lever means mounted on each of said fin means eccentrically with respect to a respective fin pivot axis
  • sliding sleeve means carried by said rudder carrier means.
  • said sliding sleeve means being provided with annular groove means having a front lat.- eral surface and a rear lateral surface for accommodating a free end of each pivot lever means.
  • said sliding sleeve means being movable from a fin arresting position with said rear lateral surface engaging said pivot lever means to hold said fin means in said first position to positions with said front lateral surface engaging said pivot lever means to move said fin means to said second position.
  • a projectile comprising:
  • rudder carrier means extending in the direction of a longitudinal axis of the projectile.
  • each of said guiding fin means being movable about a respective fin pivot axis extending substantially perpendicularly to said longitudinal axis between a first storage position extending tangentially along the rudder carrier means and a second iii-flight position extending outwardly of said rudder carrier means.
  • pivot lever means mounted on each of said fin means eccentrically with respect to a respective fin pivot axis.
  • said connecting means includes a disk detachably connected adjacent the rear end of the rudder carrier means, and wherein said sliding sleeve means includes an annular rearward extension which rests on said disk when said sliding sleeve means is in said first position.
  • compression spring means are arranged in said projectile with a rear end thereof resting at the most forward of said annular flanges with the interposition of an annular disk constructed on one of steel and polytetrafluorethylene.
  • compression spring means are arranged in said projectile with a rear end thereof resting at the most forward of said annuar flanges with the interposition of an annular disk constructed of one of steel and polytetrafluorethylene.
  • a projectile according to claim I further comprising a piezoelectric impact detonator. wherein said projectile is formed of detachably connected front and rear sections. and wherein said impact detonator is held in position between said front and rear sections by resilient means.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Toys (AREA)
US366755A 1972-06-03 1973-06-04 Projectile or rocket preferably with unfolded tail unit Expired - Lifetime US3921937A (en)

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DE2227104A DE2227104C2 (de) 1972-06-03 1972-06-03 Geschoß oder Rakete mit aufklappbarem Leitwerk

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BE (1) BE800259A (US20050192411A1-20050901-C00001.png)
DE (1) DE2227104C2 (US20050192411A1-20050901-C00001.png)
FR (1) FR2188137B1 (US20050192411A1-20050901-C00001.png)
GB (1) GB1422987A (US20050192411A1-20050901-C00001.png)
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Cited By (11)

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US4296894A (en) * 1979-02-08 1981-10-27 Messerschmitt-Bolkow-Blohm Gmbh Drone-type missile
US4600167A (en) * 1983-08-06 1986-07-15 Diehl Gmbh & Co. Pivoting guidance mechanism for small-calibered projectiles
US5671899A (en) * 1996-02-26 1997-09-30 Lockheed Martin Corporation Airborne vehicle with wing extension and roll control
US6398156B2 (en) * 1999-12-16 2002-06-04 Lfk Lenkflugkoerpersysteme Gmbh Mounting for attaching a rudder to a missile
WO2011127369A2 (en) * 2010-04-09 2011-10-13 Bae Systems Information And Electronic Systems Integration Inc. Torsion spring wing deployment initiator
WO2011126970A2 (en) * 2010-04-07 2011-10-13 Bae Systems Information And Electronic Systems Integration Inc. Compression spring wing deployment initiator
US20140312575A1 (en) * 2010-04-07 2014-10-23 William D. Barry Wing slot seal
CN108801078A (zh) * 2018-08-23 2018-11-13 中国工程物理研究院总体工程研究所 杀爆火箭弹
US20220011082A1 (en) * 2020-07-10 2022-01-13 Pneu-Dart Tail Piece for Remote Delivery Device ( CIP of Application 15/932.942 filed 05/24/2018)
US11340052B2 (en) 2019-08-27 2022-05-24 Bae Systems Information And Electronic Systems Integration Inc. Wing deployment initiator and locking mechanism
US11852211B2 (en) 2020-09-10 2023-12-26 Bae Systems Information And Electronic Systems Integration Inc. Additively manufactured elliptical bifurcating torsion spring

Families Citing this family (5)

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Publication number Priority date Publication date Assignee Title
DE3227766C1 (de) * 1982-07-24 1988-01-21 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Gefechtskopf
DE3507677A1 (de) * 1985-03-05 1986-09-11 Diehl GmbH & Co, 8500 Nürnberg Flugkoerper mit ueberkalibrigem leitwerk
DE10015514B4 (de) * 2000-03-30 2007-10-04 Rheinmetall Waffe Munition Gmbh Flügelstabilisiertes Geschoß
DE202009016713U1 (de) 2009-12-04 2010-04-08 Lehnen, Frank Widerstandsstabilisiertes, flügelloses und angetriebenes Wuchtgeschoss
DE102009057682A1 (de) 2009-12-04 2011-06-09 Frank Lehnen Widerstandsstabilisiertes, flügelloses und angetriebenes Wuchtgeschoss

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US4296894A (en) * 1979-02-08 1981-10-27 Messerschmitt-Bolkow-Blohm Gmbh Drone-type missile
US4600167A (en) * 1983-08-06 1986-07-15 Diehl Gmbh & Co. Pivoting guidance mechanism for small-calibered projectiles
US5671899A (en) * 1996-02-26 1997-09-30 Lockheed Martin Corporation Airborne vehicle with wing extension and roll control
US6398156B2 (en) * 1999-12-16 2002-06-04 Lfk Lenkflugkoerpersysteme Gmbh Mounting for attaching a rudder to a missile
US8895908B2 (en) * 2010-04-07 2014-11-25 Bae Systems Information And Electronic Systems Integration Inc. Wing slot seal
US20140312575A1 (en) * 2010-04-07 2014-10-23 William D. Barry Wing slot seal
WO2011126970A2 (en) * 2010-04-07 2011-10-13 Bae Systems Information And Electronic Systems Integration Inc. Compression spring wing deployment initiator
US20120074256A1 (en) * 2010-04-07 2012-03-29 Amy Pietrzak Compression spring wing deployment initiator
WO2011126970A3 (en) * 2010-04-07 2012-04-19 Bae Systems Information And Electronic Systems Integration Inc. Compression spring wing deployment initiator
US8754352B2 (en) * 2010-04-07 2014-06-17 Bae Systems Information And Electronic Systems Integration Inc. Compression spring wing deployment initiator
US8686329B2 (en) 2010-04-09 2014-04-01 Bae Systems Information And Electronic Systems Integration Inc. Torsion spring wing deployment initiator
WO2011127369A3 (en) * 2010-04-09 2012-02-23 Bae Systems Information And Electronic Systems Integration Inc. Torsion spring wing deployment initiator
WO2011127369A2 (en) * 2010-04-09 2011-10-13 Bae Systems Information And Electronic Systems Integration Inc. Torsion spring wing deployment initiator
CN108801078A (zh) * 2018-08-23 2018-11-13 中国工程物理研究院总体工程研究所 杀爆火箭弹
CN108801078B (zh) * 2018-08-23 2024-02-27 中国工程物理研究院总体工程研究所 杀爆火箭弹
US11340052B2 (en) 2019-08-27 2022-05-24 Bae Systems Information And Electronic Systems Integration Inc. Wing deployment initiator and locking mechanism
US20220011082A1 (en) * 2020-07-10 2022-01-13 Pneu-Dart Tail Piece for Remote Delivery Device ( CIP of Application 15/932.942 filed 05/24/2018)
US11852211B2 (en) 2020-09-10 2023-12-26 Bae Systems Information And Electronic Systems Integration Inc. Additively manufactured elliptical bifurcating torsion spring

Also Published As

Publication number Publication date
DE2227104A1 (de) 1973-12-13
GB1422987A (en) 1976-01-28
FR2188137B1 (US20050192411A1-20050901-C00001.png) 1977-12-30
FR2188137A1 (US20050192411A1-20050901-C00001.png) 1974-01-18
IT985639B (it) 1974-12-10
DE2227104C2 (de) 1982-07-15
BE800259A (fr) 1973-09-17

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