WO1981000908A1 - Projectile,adapted to be given a rotation on firing,which makes the projectile spin-stabilized - Google Patents

Projectile,adapted to be given a rotation on firing,which makes the projectile spin-stabilized Download PDF

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Publication number
WO1981000908A1
WO1981000908A1 PCT/SE1980/000228 SE8000228W WO8100908A1 WO 1981000908 A1 WO1981000908 A1 WO 1981000908A1 SE 8000228 W SE8000228 W SE 8000228W WO 8100908 A1 WO8100908 A1 WO 8100908A1
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WO
WIPO (PCT)
Prior art keywords
projectile
fins
centre
stabilized
rotation
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/SE1980/000228
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French (fr)
Inventor
K Andersson
S Bondesson
N Bartelsson
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Individual
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Individual
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Priority to AT80901895T priority Critical patent/ATE4146T1/en
Priority to DE8080901895T priority patent/DE3064144D1/en
Publication of WO1981000908A1 publication Critical patent/WO1981000908A1/en
Priority to DK230081A priority patent/DK145939C/en
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • 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
    • F42B10/16—Wrap-around fins
    • 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
    • F42B10/26—Stabilising arrangements using spin

Definitions

  • the present invention relates to a projectile adapted to be given a rotation on firing, which makes the projectile spin-stabilized.
  • the invention can be used, in particular, as a terminally guided projectile and in general for projectiles which receive an explosive charge with a hollow-charge effect.
  • a projectile is fired in a ballistic trajectory in conventional manner but at the end of the trajectory a target-seeking member and guidance electronics are activated which can lead the projectile to a hit or near hit on the target.
  • a system with terminally corrected projectiles is less complicated than a robot because continuous guidance is not used.
  • the projectile is more difficult to intercept when it follows a ballistic trajectory for great or greater portion of the flight.
  • the target seeker is complicated and considerable difficulties arise in correcting the course since the roll position of the projectile must be determined when the guiding signal is given. It has been proposed that the roll direction should be determined in relation to a reference direction by means of the so-called rate-gyro and integration. This proposal is not without problems, however, because the gyro is sensitive to acceleration and can drift. With projectiles which are fired with a gun barrel, the sensitivity to acceleration is a particularly serious problem.
  • a projectile which is spin-stabilized is altogether unsuitable for use as a terminally guided projectile or in general if the projectile is to receive for example an explosive charge with a hollow-charge effect where the explosive radiation is adversely affected if the explosive charge rotates.
  • the dispersion easily increases since the projectile is sensitive to disturbances at the beginning of the trajectory, that is to say when the fins are extended, and the extension of the fins easily introduces disturbances.
  • the length of the projectile has greatly exceeded that which applies to conventional projectiles, which imposes new demands on the handling of ammunition particularly where automatic loading systems are concerned.
  • the present invention unites the advantages of the above system while at the same time the disadvantages are reduced to a minimum as a result of the fact that the projectile according to the invention is spin-stabilized when it is fired, after which, at a desired point in the trajectory of the projectile, the rotation is braked so that in the latter part of the projectile's trajectory, the projectile is finstablized.
  • the projectile according to the invention is provided with stabilizing fins of the type which are known per se in fin-stabilized projectiles, wherein the fins are able to be extended from a retracted position on firing to an extended position at a desired point in the trajectory of the projectile and so to brake the rotation of the projectile, and wherein the projectile is so dimensioned that its aerodynamic centre of pressure in said extended position is situated behind the centre of gravity of the projectile, so that during braked rotation, the projectile changes over from being spin-stabilized to being fin stabilized.
  • the projectile is shown with a base bleed unit 1 which gives an increased range of fire in known manner by giving off gas which increases the reduced pressure at the base end of the projectile.
  • the projectile In its back portion, the projectile is provided with four stabilizing fins 6-9 of the type which is known per se in fin-stabilized projectiles.
  • they consist of so-called wrap-around fins, that is to say fins which, in the retracted position, largely follow the outer shell surface of the projectile.
  • the fins 6-9 are held in the retracted position by means of locking members in the form of four conventional covering plates 2-5, which are held in place by the base bleed unit 1 as a result of the fact that this tightly surrounds the back portion of the covering plates.
  • a delay device not shown in the projectile is dimensioned so as to initiate, at a desired point of the trajectory, the throwing off of the base bleed unit 1 so that the covering plates 2-5 are automatically removed and expose the fins 6-9. These are so dimensioned, in known manner, that they extend through a combination of centrifugal forces and aerodynamic forces and afterwards, likewise in know manner, are locked in the extended position.
  • the delay device which can contain a pyrotechnic charge, for example, is of conventional type well known to the expert so that it does not need to be shown or described here.
  • the projectile In its front position, the projectile comprises four nose rudders 10 which can each be extended through its slot 10a, see Figure 3, to guide the projectile in its later, fin-stabilized part of the projectile trajectory.
  • the nose rudders 10 are adapted to be extended through the slots 10a when a predetermined braking of rotation is reached in the projectile.
  • the initiation of the extension of the nose rudders may alternatively be effected by means of a delay device of conventional type, not shown.
  • the guiding of the projectile can alternatively take place by means of pulses from one or more steering nozzles, in which case the nose rudders can be dispensed with entirely.
  • the projectile further comprises four covering plates 11-13 in a nose portion, which are adapted, through initiation by a delay device not shown, to be removed from the projectile after this has become finstabilized and to expose a target tracking optical system of the like, not shown, see Figure 3.
  • the stabilizing fins 6-9 in the manner described above, and on the other hand such a dimensioning of the projectile that its aerodynamic centre of pressure, that is to say the point where the air forces act, are situated behind the centre of gravity of the projectile in the extended position of the fins.
  • the projectile is further so dimensioned that its centre of pressure also lies behind the centre of gravity of the projectile when both the fins 6-9 and the nose rudders 10 are extended.
  • the projectile is so dimensioned that its centre of pressure lies somewhat in front of the centre of gravity of the projectile when the fins 6-9 and the nose rudders 10 are in the retracted position, that is to say in the first part of the trajectory of the projectile, when the projectile is spin-stabilized.
  • the centre of pressure should lie in front of the centre of gravity in this manner, it is nevertheless conceivable, within the scope of the invention, to position the centre of pressure in or behind the centre of gravity of the projectile instead.
  • the mode of operation of the projectile described is as follows: When the projectile is fired from a barrel not shown, it is given a relatively high speed of rotation (of the order of magnitude of 300-2000 rad/sec), for example by means of conventional projectile driving bands. At a predetermined, desired point in the trajectory of the projectile the base bleed unit 1 is thrown away so that the covering plates 2-5 are removed and the fins 6-9 exposed. These are extended and brake the rotation of the projectile. As a result of the above-mentioned dimensioning of the fins and the projectile, the projectile changes over from being spin-stabilized to being finstabilized. The terminal guidance and target-seeking function of the projectile or the triggering of the explosive charge of the projectile with a hollow-charge effect can now take place.

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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)
  • Analogue/Digital Conversion (AREA)
  • Ultra Sonic Daignosis Equipment (AREA)

Abstract

With the object of facilitating the terminal guidance of the projectile or increasing the effect of an explosive charge with a hollow-charge effect carried by the projectile, the projectile is provided with stabilizing fins (6-9) which are extended at a desired point in the trajectory of the projectile and brake the rotation of the projectile. The projectile is so dimensioned that its centre of pressure (C2) is situated behind the centre of gravity (G) of the projectile in the extended position of the fins (Figure 2) and so that the centre of pressure (C1) lies in front of the centre of gravity of the projectile in the retracted position of the fins (Figure 1), so that, with braked rotation, the projectile changes over from being spin-stabilized to being fin-stabilized. The fins (6-9), which can consist of so-called wraparound fins, are held in the retracted position, in an embodiment shown, by means of covering plates (2-5) which are held in place by a so-called base bleed unit (1). A delay device is adapted to be separated from the projectile at said desired point in the trajectory, so that the covering plates (2-5) are removed and expose the fins (6-9), as a result of which these can be extended.

Description

Projectile, adapted to be given a rotation on firing, which makes the projectile spin-stabilized
TECHNICAL FIELD
The present invention relates to a projectile adapted to be given a rotation on firing, which makes the projectile spin-stabilized. The invention can be used, in particular, as a terminally guided projectile and in general for projectiles which receive an explosive charge with a hollow-charge effect.
BACKGROUND ART
The development in the artillery field, both land and sea artillery, has rendered possible projectiles with an increased range of fire, for example by means of a so-called base bleed unit. The increased range of fire is naturally desirable but it leads to increased absolute dispersion of the projectiles. This increased dispersion is very unfavourable, all the more so as a change in the threat picture has become noticeable towards a greater frequency of smaller and harder elementary targets where each elementary target has to be combatted. In order to reduce the dispersion of the projectiles, terminal correction or terminal guidance of the projectiles has been proposed. This means that a projectile is fired in a ballistic trajectory in conventional manner but at the end of the trajectory a target-seeking member and guidance electronics are activated which can lead the projectile to a hit or near hit on the target. Compared with a radical exchange of tube artillery for missiles, a system with terminally corrected projectiles is less complicated than a robot because continuous guidance is not used. Moreover, the projectile is more difficult to intercept when it follows a ballistic trajectory for great or greater portion of the flight.
Different solutions to this problem have been introduced. Conventional artillery ammunition is spin-stabilized over the whole trajectory, that is to say it has i high speed of rotation (of the order of magnitude of 300-2000 rad/sec). Solutions to the problems of terminal guidance of projectiles which are spin-stabilized over the whole trajectory have been put forward. The advantages of such a system are that a completely conventional firing can be effected with ammunition effects which differ little in size and weight from conventional ammunition. The disadvantages are the very complicated guiding and the limited range of control as well as the very uncertain possibilities of realisation.
The target seeker is complicated and considerable difficulties arise in correcting the course since the roll position of the projectile must be determined when the guiding signal is given. It has been proposed that the roll direction should be determined in relation to a reference direction by means of the so-called rate-gyro and integration. This proposal is not without problems, however, because the gyro is sensitive to acceleration and can drift. With projectiles which are fired with a gun barrel, the sensitivity to acceleration is a particularly serious problem.
Thus a projectile which is spin-stabilized is altogether unsuitable for use as a terminally guided projectile or in general if the projectile is to receive for example an explosive charge with a hollow-charge effect where the explosive radiation is adversely affected if the explosive charge rotates.
An attempt to eliminate the disadvantages of a projectile which is spin-stablized by discharging a useful load from the projectile is disclosed in the Swedish Patent Specification 363 892. There a projectile which is spin-stabilized is disclosed which is provided with brake flaps which, at the desired moment in the trajectory, are lowered and brake the rotation of the projectile so that the projectile becomes unstable, after which the useful load of the projectile is thrown away. Since such a projectile thus becomes, unstable as a result of the braking of the rotation, it cannot serve as a terminally guided projectile or be provided with an explosive charge with a hollow-charge effect since that would require that the projectile should be aerodynamically stable. The majority of solutions hitherto put forward for the problem of terminal guidance mean that the projectile is provided with so-called rotating driving bands which means that the projectile has a low speed of rotation (of the order of magnitude 0-200 rad/sec) when it leaves the muzzle. This means that stabilizing fins must be extended immediately outside the muzzle. The advantages of this system with low or no speed of rotation in the trajectory is that target seeking and guiding can be fairly simple. Certain warheads, such as explosive charges with a hollow-charge effect, require a low speed of rotation to give a good result, as mentioned above. The disadvantages of this system are that the range of firing is adversely affected. Moreover, the dispersion easily increases since the projectile is sensitive to disturbances at the beginning of the trajectory, that is to say when the fins are extended, and the extension of the fins easily introduces disturbances. Moreover, with the solutions hitherto proposed, the length of the projectile has greatly exceeded that which applies to conventional projectiles, which imposes new demands on the handling of ammunition particularly where automatic loading systems are concerned.
DISCLOSURE OF INVENTION
The present invention unites the advantages of the above system while at the same time the disadvantages are reduced to a minimum as a result of the fact that the projectile according to the invention is spin-stabilized when it is fired, after which, at a desired point in the trajectory of the projectile, the rotation is braked so that in the latter part of the projectile's trajectory, the projectile is finstablized. This is achieved as a result of the fact that the projectile according to the invention is provided with stabilizing fins of the type which are known per se in fin-stabilized projectiles, wherein the fins are able to be extended from a retracted position on firing to an extended position at a desired point in the trajectory of the projectile and so to brake the rotation of the projectile, and wherein the projectile is so dimensioned that its aerodynamic centre of pressure in said extended position is situated behind the centre of gravity of the projectile, so that during braked rotation, the projectile changes over from being spin-stabilized to being fin stabilized.
BRIEF DESCRIPTION OF DRAWINGS The invention will be described in more detail below with reference to the accompanying drawings which show a preferred form of embodiment of a projectile according to the invention, in which in Figure 1, the projectile, which is provided with a base blow unit, is shown in the introductory phase of its trajectory, in Figure 2 the same projectile is shown when the base flow unit has been discarded and the fins exposed and in Figure 3, the same projectile is shown when the optical system has been exposed and the nose rudder extended.
In the figures, the same parts have been provided with the same reference numerals throughout.
BEST MODE OF CARRYING OUT THE INVENTION
The projectile is shown with a base bleed unit 1 which gives an increased range of fire in known manner by giving off gas which increases the reduced pressure at the base end of the projectile.
The need for end-phase correction increases, as stated earlier, with increased range of fire. It will be seen, however, that the present invention is suitable, to an equally high degree, for all other types of terminally corrected projectiles or for projectiles wich carry an explosive charge with a hollow-charge effect.
In its back portion, the projectile is provided with four stabilizing fins 6-9 of the type which is known per se in fin-stabilized projectiles. In the embodiment shown they consist of so-called wrap-around fins, that is to say fins which, in the retracted position, largely follow the outer shell surface of the projectile. The fins 6-9 are held in the retracted position by means of locking members in the form of four conventional covering plates 2-5, which are held in place by the base bleed unit 1 as a result of the fact that this tightly surrounds the back portion of the covering plates. A delay device, not shown in the projectile is dimensioned so as to initiate, at a desired point of the trajectory, the throwing off of the base bleed unit 1 so that the covering plates 2-5 are automatically removed and expose the fins 6-9. These are so dimensioned, in known manner, that they extend through a combination of centrifugal forces and aerodynamic forces and afterwards, likewise in know manner, are locked in the extended position.
It will be seen that the arrangement of the covering plates 2-5 is not necessary but that these can de dispensed with if necessary.
The delay device which can contain a pyrotechnic charge, for example, is of conventional type well known to the expert so that it does not need to be shown or described here.
Several other methods of extending the fins 6-9 are naturally conceivable within the idea of the invention. Instead of swinging out, for example, they can be extended through gaps formed in the projectile.
In its front position, the projectile comprises four nose rudders 10 which can each be extended through its slot 10a, see Figure 3, to guide the projectile in its later, fin-stabilized part of the projectile trajectory. The nose rudders 10 are adapted to be extended through the slots 10a when a predetermined braking of rotation is reached in the projectile. The initiation of the extension of the nose rudders may alternatively be effected by means of a delay device of conventional type, not shown. The guiding of the projectile can alternatively take place by means of pulses from one or more steering nozzles, in which case the nose rudders can be dispensed with entirely. If the projectile is provided instead with aerodynamic nose rudders, these can be extended during the whole trajectory time and even in the fire tube. This presupposes, however, thet their span is less that the diameter of the barrel. The nose rudders then are so dimensioned that the projectile can fly spin-stabilized. The projectile further comprises four covering plates 11-13 in a nose portion, which are adapted, through initiation by a delay device not shown, to be removed from the projectile after this has become finstabilized and to expose a target tracking optical system of the like, not shown, see Figure 3.
Since neither the guidance system nor the target tracking optical system constitutes any part of the present invention they are not shown or described here in detail but the above summary description of their operation is regarded as sufficient.
In order to achieve fin-stabilization of the spin-stabilized projectile, according to the invention, it requires on the one hand an arrangement of the stabilizing fins 6-9 in the manner described above, and on the other hand such a dimensioning of the projectile that its aerodynamic centre of pressure, that is to say the point where the air forces act, are situated behind the centre of gravity of the projectile in the extended position of the fins. The projectile is further so dimensioned that its centre of pressure also lies behind the centre of gravity of the projectile when both the fins 6-9 and the nose rudders 10 are extended. Finally, the projectile is so dimensioned that its centre of pressure lies somewhat in front of the centre of gravity of the projectile when the fins 6-9 and the nose rudders 10 are in the retracted position, that is to say in the first part of the trajectory of the projectile, when the projectile is spin-stabilized. Although for spin-stabilized projectiles in general, it applies that the centre of pressure should lie in front of the centre of gravity in this manner, it is nevertheless conceivable, within the scope of the invention, to position the centre of pressure in or behind the centre of gravity of the projectile instead.
The positioning of the centre of pressure is shown in Figure 3 where the centre of pressure, in the retracted position of the fins 6-9, is situated at a point C1, which lies somewhat in front of the centre of gravity of the projectile, which is marked by G in Figure 3. In the extended position of the fins 6-9, the centre of pressure is shifted back to a point C2 behind the centre of gravity G. On extension of the nose rudders 10, the centre of pressure is shifted forwards somewhat to a point C3 which nevertheless also lies behind the centre of gravity G.
The mode of operation of the projectile described is as follows: When the projectile is fired from a barrel not shown, it is given a relatively high speed of rotation (of the order of magnitude of 300-2000 rad/sec), for example by means of conventional projectile driving bands. At a predetermined, desired point in the trajectory of the projectile the base bleed unit 1 is thrown away so that the covering plates 2-5 are removed and the fins 6-9 exposed. These are extended and brake the rotation of the projectile. As a result of the above-mentioned dimensioning of the fins and the projectile, the projectile changes over from being spin-stabilized to being finstabilized. The terminal guidance and target-seeking function of the projectile or the triggering of the explosive charge of the projectile with a hollow-charge effect can now take place.
With a view to precision and range, it is usually best to extend the fins after at least half the trajectory has been covered but in certain cases an earlier extension can be advisable so as to obtain a low speed of rotation in time.

Claims

Claims
1. A projectile, adapted to be given a rotation on being fired which makes the projectile spin-stabilized, ch a r a c t e r i s e d in that the projectile is provided with stabilizing fins (6-9) of the type which is known per se in fin-stabilized projectiles, the fins having the capacity to be able to be extended from a retracted position on firing (Figure 1) to an extended position (Figure 2) at a desired point in the trajectory of the projectile and so to brake the rotation of the projectile, and the projectile being so dimensioned that its aerodynamic centre of pressure (C2) in said extended position is situated behind the centre of gravity (G) of the projectile, so that, with braked rotation, the projectile changes over from being spin-stabilized to being fin-stabilized.
2. A projectile as claimed in Claim 1, c h a r a c t e r i s e d in that the aerodynamic centre of pressure (C1) of the projectile lies in front of the centre of gravity (G) of the projectile in the retracted position of the fins (6-9).
3. A projectile as claimed in one of the preceding Claims, ch a r a c t e r i s e d by locking members (1-5) to hold the fins (6-9) in the retracted position, the locking member being separable from the projectile to expose the fins at said desired point in the trajectory.
4. A projectile as claimed in one of the preceding Claims, ch a r a c t e r i s e d in that the fins (6-9) are formed as so-called wrap-around fins.
PCT/SE1980/000228 1979-09-27 1980-09-25 Projectile,adapted to be given a rotation on firing,which makes the projectile spin-stabilized Ceased WO1981000908A1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
AT80901895T ATE4146T1 (en) 1979-09-27 1980-09-25 BULLET THAT IS GIVEN AN IT-STABILIZING SPIN WHEN FIRED.
DE8080901895T DE3064144D1 (en) 1979-09-27 1980-09-25 Projectile, adapted to be given a rotation on firing, which makes the projectile spin-stabilized
DK230081A DK145939C (en) 1979-09-27 1981-05-26 PROJECTLY PROVIDED BY A ROTATION TO RELEASE A ROTATION THAT STABILIZES THE PROJECTILE

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
SE7908002A SE432670B (en) 1979-09-27 1979-09-27 SETTING TO STABILIZE AN ARTILLERY PROJECTILY AND IN THE FINAL PHASE CORRECT ITS COURSE AND ARTILLERY PROJECTILE FOR IMPLEMENTATION OF THE SET
SE7908002 1979-09-27

Publications (1)

Publication Number Publication Date
WO1981000908A1 true WO1981000908A1 (en) 1981-04-02

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/SE1980/000228 Ceased WO1981000908A1 (en) 1979-09-27 1980-09-25 Projectile,adapted to be given a rotation on firing,which makes the projectile spin-stabilized

Country Status (8)

Country Link
US (1) US4546940A (en)
EP (1) EP0039681B2 (en)
JP (1) JPS6136159B2 (en)
DE (1) DE3064144D1 (en)
DK (1) DK145939C (en)
NO (1) NO148347C (en)
SE (1) SE432670B (en)
WO (1) WO1981000908A1 (en)

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US6783095B1 (en) 2003-03-24 2004-08-31 At&T Corp. Deployable flare for aerodynamically stabilizing a projectile
US6691948B1 (en) 2003-04-10 2004-02-17 The United States Of America As Represented By The Secretary Of The Navy High torque rocket nozzle
US7260393B2 (en) * 2003-09-23 2007-08-21 Intel Corporation Systems and methods for reducing communication unit scan time in wireless networks
JP5127284B2 (en) * 2007-04-11 2013-01-23 三菱プレシジョン株式会社 Flying object and apparatus for detecting rotational position of flying object
US7849800B2 (en) 2007-06-24 2010-12-14 Raytheon Company Hybrid spin/fin stabilized projectile
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EP0066715A3 (en) * 1981-06-05 1983-03-30 Dynamit Nobel Aktiengesellschaft Spin-stabilised training projectile
US4533094A (en) * 1982-10-18 1985-08-06 Raytheon Company Mortar system with improved round
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EP0448437A1 (en) * 1990-03-09 1991-09-25 Thomson-Brandt Armements Improvements concerning a system for deploying rail fins
CH685069A5 (en) * 1991-12-18 1995-03-15 Contraves Ag Sub-calibre, fin-stabilised projectile which is fired with spin
EP0884554A1 (en) * 1997-06-13 1998-12-16 Tda Armements S.A.S. Method for controlling the lateral dispersion of projectiles stabilised by means of gyroscopic effect
FR2764689A1 (en) * 1997-06-13 1998-12-18 Tda Armements Sas METHOD FOR CONTROLLING LATERAL DISPERSION OF STABILIZED AMMUNITION BY GYROSCOPIC EFFECT
EP0905473A1 (en) 1997-09-24 1999-03-31 Giat Industries Large-calibre long range projectile for artillery
FR2768809A1 (en) 1997-09-24 1999-03-26 Giat Ind Sa LARGE CALIBER LONG RANGE FIELD ARTILLERY PROJECTILE
US6234082B1 (en) 1997-09-24 2001-05-22 Giat Industries Large-caliber long-range field artillery projectile
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RU2338151C1 (en) * 2007-04-23 2008-11-10 Николай Борисович Болотин Supersonic birotating jet shell
RU2348894C1 (en) * 2007-04-26 2009-03-10 Николай Борисович Болотин Supersonic missile
RU2342628C1 (en) * 2007-05-02 2008-12-27 Николай Борисович Болотин Supersonic jet shell
RU2345315C1 (en) * 2007-05-02 2009-01-27 Николай Борисович Болотин Subsonic jet shell
WO2016070930A1 (en) * 2014-11-07 2016-05-12 Kongsberg Defence & Aerospace As Method and system for protecting folding wings on a missile while in their stowed state
US10852112B2 (en) 2014-11-07 2020-12-01 Kongsberg Defence & Aerospace As Method and system for protecting folding wings on a missile while in their stowed state

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SE7908002L (en) 1981-03-28
NO148347B (en) 1983-06-13
NO148347C (en) 1983-09-21
DK230081A (en) 1981-05-26
EP0039681B1 (en) 1983-07-13
DK145939B (en) 1983-04-18
NO811776L (en) 1981-05-26
JPS6136159B2 (en) 1986-08-16
SE432670B (en) 1984-04-09
US4546940A (en) 1985-10-15
DE3064144D1 (en) 1983-08-18
EP0039681B2 (en) 1986-07-02
JPS56501257A (en) 1981-09-03
DK145939C (en) 1983-09-26
EP0039681A1 (en) 1981-11-18

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