US3434417A - Bomb braking system - Google Patents

Bomb braking system Download PDF

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Publication number
US3434417A
US3434417A US628072A US3434417DA US3434417A US 3434417 A US3434417 A US 3434417A US 628072 A US628072 A US 628072A US 3434417D A US3434417D A US 3434417DA US 3434417 A US3434417 A US 3434417A
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US
United States
Prior art keywords
bomb
braking
cap
casing
smooth
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.)
Expired - Lifetime
Application number
US628072A
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English (en)
Inventor
Fridolin Schroth
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Les Forges de Zeebrugge SA
Original Assignee
Les Forges de Zeebrugge SA
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 Les Forges de Zeebrugge SA filed Critical Les Forges de Zeebrugge SA
Application granted granted Critical
Publication of US3434417A publication Critical patent/US3434417A/en
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
    • F42B10/52—Nose cones

Definitions

  • This invention relates to a system provided for braking a bomb released at low altitude and at high speed.
  • bombs are most etficiently released when flying in skimming the ground at high speed.
  • This method has the advantage of little endangering the attacking plane since it is under radar reach of the enemy.
  • 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 target.
  • the bombs may be so released even in disadvantageous atmospheric conditions.
  • a normal unbraked bomb released in skimming the ground at high speed endangers the plane itself. So as not to endanger the plane by said bomb, the latter should be provided with a braking rocket.
  • a braking rocket introduces at least the following drawbacks:
  • the braking is provided by a combination of spacing traps and a parachute.
  • the bomb is braked only with spacing traps.
  • This invention is based upon the new concept of a simple and flexible braking of the bomb.
  • the invention provides conditioning the bomb body on a longitudinal portion from the front end so as to present a not smooth or not continuous external surface, i.e. a surface having successive steps generally in the form of annular grooves.
  • these grooves will be equally spaced and they may have an essentially variable cross-section in shape as well as in size, the latter being determined and selected in accordance with the desired braking effects as a function of the projectile type being equipped.
  • This special braking surface may be provided either by the corresponding portion of the bomb body itself or by an inserted casing. The latter will be conditioned to be readily disposed upon the bomb without any tool and without any long or critical opera tion and without requiring any modification in the ex- 3,434,417 Patented Mar.
  • thesaid casing will be provided with such a longitudinal cut-out that the said casing will be capable of substantially covering instantaneously the front portion of the bomb by avoiding the obstacle presented by the suspension rings thereof.
  • means are also provided to cancel the braking effects of the so conditioned bomb either when such braking is not required or before releasing.
  • This means comprises covering the said unsmooth surface with a cap having a smooth external surface.
  • this cap will be disposed either directly upon the corresponding front portion of the projectile or concentrically upon the cap having an unsmooth external wall.
  • the said cap having a smooth external wall will be conditioned to be either systematically separable from the projectile or spaced from the said unsmooth external surface of the said projectile when releasing or immediately thereafter.
  • the unsmooth portion will be freed in this manner either by a connection between the said cap having a smooth external Wall with a portion adjoining the plane or by separating the constituting portions of the said cap by means of an explosive charge provided or not provided with a retarding system or by any other means.
  • this invention concerns bombs, the external surface of which is not smooth upon a longitudinal portion from the front end, i.e. bombs having a braking surface, and any cap having an external braking surface conditioned to be secured on the front portion of a bomb, and complementary caps having a smooth external surface to be momentarily secured either directly on the bomb or on the cap covering the front portion of the bomb.
  • FIGURE 1 shows a plan view of a bomb covered with a casing according to the invention
  • FIGURE 2 is an end view according to the arrow F2 of FIGURE 1;
  • FIGURE 3 shows a half vertical section and a half longitudinal section of a casing according to the invention
  • FIGURE 4 is an end view in the direction of arrow F4 of FIGURE 3;
  • FIGURES 5, 6 and 7 show, in cross-section and by way of example, three different profiles of annular grooves characterizing the casing according to the invention
  • FIGURE 8 shows a plan view of a bomb, the front portion of which presents a braking surface
  • FIGURE 9 shows a half plan view and a half longitudinal section of a complementary cap for momentarily cancelling the braking effects
  • FIGURE 10 shows a partial plan view and a partial longitudinal section of the application of a cap according to FIGURE 9 on a bomb covered with a sleeve having an unsmooth surface according to FIGURE 1;
  • FIGURE 11 shows a partial plan view and a partial longitudinal section of the application of a cap according to FIGURE 9 on a bomb according to FIGURE 8;
  • FIGURE 12 is a view similar to that of FIGURE 11 representing another embodiment for realizing and mounting the cap according to FIGURE 9.
  • a casing 1 is generally made of a plastic material or any other suitable material under the form of a cap capable of correctly contouring the front portion of bomb 2 at least upon a predetermined length L.
  • the internal face 3 of said cap will be generally smooth and, in any case, it will be determined in accordance with the corresponding portion of bomb 2, whereas the external surface 4 of said cap will present successive steps generally outlined by similar or different, equally spaced or differently spaced annular grooves 5 in accordance with the braking effect being produced.
  • FIGURES l, 3 and 5 the said external surface 4 will be transversely corrugated so that the said annular grooves 5 and consequently also the annular ribs 6 separating them will be sinusoidally shaped.
  • FIGURE 6 represents an ear shape and FIGURE 7 represents such ear shape slightly modified. Of course, any other suitable shape could be provided.
  • This raised surface portion extends upon a length L of the casing, said length being itself predetermined in accordance with the braking effects being produced.
  • the rear portion 7 of casing 1 may be smooth, respectively continuous or cylindrical.
  • the casing presents a longitudinal cut-out 8 the width E of which is equal or slightly larger than the diameter of the fastening or suspension rings 9 generally provided on bomb 2.
  • this cut-out may be adjusted in accordance with the space occupied by the said fastening elements of the bomb so that the casing may be disposed upon the bomb without any tool nor any disassembling operation.
  • This braking casing may be fitted to any bomb before loading and it may be secured to said suspension rings 9 of the bomb without any disassembling or mounting operation of any portion of the bomb.
  • the guiding mechanism is kept integral with the bomb.
  • the longitudinal cut-out 8 extending advantageously as a groove 10 up to the nose of the bomb, owing to the back pressure when releasing, the bomb has a tendency to nose-drive, thereby bringing it more rapidly and systematically in its vertical position for a normal fall.
  • the same braking effect may be obtained by making the bomb as represented by way of example in FIGURE 8, the front portion presenting a profile similar to the profile 4 of the sleeve described in the preceding example.
  • the same successive parallel grooves 5 and torus-shaped ribs 6 are also provided therein.
  • the said unsmooth surfaces 4 may be advantageously covered with a cap 11 having a smooth external surface.
  • This cap will be conditioned so that its shape and its internal dimensions allow an adjustment by leaning upon the outermost generatrices of said stepped ribs 6.
  • this complementary cap may have, a length L, L or any other length consistent with the bomb type and the used separating means.
  • this complementary cap 11 may be connected e.g. by at least a filiform element having a good resistance with an adjoining portion of the plane in such manner that, due to the effect of the speed differences immediately after releasing the bomb from the plane, 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 shells being kept assembled by a means freed when releasing.
  • FIGURE 12 A modification of this embodiment is represented in FIGURE 12 accorring to which the complementary cap 11 is provided in four sections three of which 12-13-14 are apparent, each section being hinged on the bomb body as indicated in 15.
  • These four sections are kept in covering position by any suitable means such as weld spots which are broken by firing an explosive charge 16 under the action of the releasing mechanism of the bomb and preferably provided with a retarding device. After the explosion of charge 16, the said sections occupy the position indicated in dotted lines in FIGURE 12, a position in Which they provide additional guiding surfaces 17 and complementary braking surfaces 18.
  • any cap having a smooth or unsmooth external wall there may be used any suitable material such as metal, pressed material, fibrous material, plastic material or a combination thereof.
  • An air dropped missile comprising a body having a nose, at least a part of the outer surface of said nose having transverse corrugations, and a separate noseshaped cover adapted to momentarily cover said corrugations and having a smooth outer surface.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)
  • Radar Systems Or Details Thereof (AREA)
  • Valves And Accessory Devices For Braking Systems (AREA)
US628072A 1966-07-26 1967-04-03 Bomb braking system Expired - Lifetime US3434417A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DESC039315 1966-07-26
DESC040023 1966-12-24

Publications (1)

Publication Number Publication Date
US3434417A true US3434417A (en) 1969-03-25

Family

ID=25993396

Family Applications (1)

Application Number Title Priority Date Filing Date
US628072A Expired - Lifetime US3434417A (en) 1966-07-26 1967-04-03 Bomb braking system

Country Status (9)

Country Link
US (1) US3434417A (zh)
BE (1) BE693244A (zh)
DE (2) DE1578227B1 (zh)
ES (1) ES339636A1 (zh)
GB (1) GB1179458A (zh)
IL (1) IL27874A (zh)
LU (1) LU53203A1 (zh)
NO (1) NO122225B (zh)
SE (1) SE323911B (zh)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2447397C2 (ru) * 2010-11-10 2012-04-10 Александр Иванович Голодяев Бомба
US20130214094A1 (en) * 2010-11-02 2013-08-22 Japan Aerospace Exploration Agency Nose for supersonic flying object
RU2723363C1 (ru) * 2019-06-10 2020-06-10 Олег Николаевич Гаршин Противорикошетная насадка
EP3800436A1 (de) * 2019-10-02 2021-04-07 RWM Schweiz AG Geschoss mit verkürzter reichweite

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2547407B1 (fr) * 1983-06-08 1990-09-28 Mecanique Ste Nle Et Projectile d'exercice pour artillerie a freinage de trajectoire et marquage d'impact
NO169308C (no) * 1989-03-03 1992-06-03 Contraves Ag Kortbaneprosjektil med en prosjektilspiss og med midler for aa avkorte prosjektilets flyvebane

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2393274A (en) * 1943-09-04 1946-01-22 Budd Edward G Mfg Co Fragmentation bomb
US3002453A (en) * 1958-12-30 1961-10-03 Joseph V Fedor Anti-ricochet device
US3112906A (en) * 1960-07-01 1963-12-03 Bolkow Entwicklungen Kg Flying body construction
US3185035A (en) * 1961-05-31 1965-05-25 French & Sons Thomas Rocket launchers
US3282216A (en) * 1962-01-30 1966-11-01 Clifford T Calfee Nose cone and tail structures for an air vehicle
US3298312A (en) * 1965-06-14 1967-01-17 Kenneth W Adams High pressure nose for a body in flight

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE713284C (de) * 1938-11-25 1941-11-05 Ver Oberschlesische Huettenwer Bombe zum Abwurf aus einem Flugzeug im Tiefangriff
DE713285C (de) * 1938-11-25 1941-11-05 Ver Oberschlesische Huettenwer Mit Aufschlagzuender versehene Bombe zum Abwurf im Tiefangriff aus einem Flugzeug

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2393274A (en) * 1943-09-04 1946-01-22 Budd Edward G Mfg Co Fragmentation bomb
US3002453A (en) * 1958-12-30 1961-10-03 Joseph V Fedor Anti-ricochet device
US3112906A (en) * 1960-07-01 1963-12-03 Bolkow Entwicklungen Kg Flying body construction
US3185035A (en) * 1961-05-31 1965-05-25 French & Sons Thomas Rocket launchers
US3282216A (en) * 1962-01-30 1966-11-01 Clifford T Calfee Nose cone and tail structures for an air vehicle
US3298312A (en) * 1965-06-14 1967-01-17 Kenneth W Adams High pressure nose for a body in flight

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130214094A1 (en) * 2010-11-02 2013-08-22 Japan Aerospace Exploration Agency Nose for supersonic flying object
US9428264B2 (en) * 2010-11-02 2016-08-30 Japan Aerospace Exploration Agency Nose for supersonic flying object
EP2636594B1 (en) * 2010-11-02 2017-01-11 Japan Aerospace Exploration Agency Nose for supersonic flying object
RU2447397C2 (ru) * 2010-11-10 2012-04-10 Александр Иванович Голодяев Бомба
RU2723363C1 (ru) * 2019-06-10 2020-06-10 Олег Николаевич Гаршин Противорикошетная насадка
EP3800436A1 (de) * 2019-10-02 2021-04-07 RWM Schweiz AG Geschoss mit verkürzter reichweite

Also Published As

Publication number Publication date
DE1578228B1 (de) 1971-08-26
NO122225B (zh) 1971-06-01
LU53203A1 (zh) 1967-05-16
ES339636A1 (es) 1968-05-01
IL27874A (en) 1972-04-27
SE323911B (zh) 1970-05-11
DE1578227B1 (de) 1971-04-01
BE693244A (zh) 1967-07-03
GB1179458A (en) 1970-01-28

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