IL41097A - Rotationally spinning guided projectile and method of making an in-flight correction of its trajectory - Google Patents

Rotationally spinning guided projectile and method of making an in-flight correction of its trajectory

Info

Publication number
IL41097A
IL41097A IL41097A IL4109772A IL41097A IL 41097 A IL41097 A IL 41097A IL 41097 A IL41097 A IL 41097A IL 4109772 A IL4109772 A IL 4109772A IL 41097 A IL41097 A IL 41097A
Authority
IL
Israel
Prior art keywords
projectile
masses
discrete
release
detonation
Prior art date
Application number
IL41097A
Other versions
IL41097A0 (en
Original Assignee
Ship Systems Inc
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 Ship Systems Inc filed Critical Ship Systems Inc
Publication of IL41097A0 publication Critical patent/IL41097A0/en
Publication of IL41097A publication Critical patent/IL41097A/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/24—Beam riding guidance systems
    • F41G7/26—Optical guidance systems
    • F41G7/266—Optical guidance systems for spin-stabilized missiles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/30—Command link guidance systems
    • F41G7/301—Details
    • F41G7/305—Details for spin-stabilized missiles
    • 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
    • F42B10/60—Steering arrangements
    • F42B10/66—Steering by varying intensity or direction of thrust
    • F42B10/661—Steering by varying intensity or direction of thrust using several transversally acting rocket motors, each motor containing an individual propellant charge, e.g. solid charge

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Lasers (AREA)

Claims (13)

C L A I M S
1. A method of making an in-flight correction f the trajectory of a rotationall spinning projectile haying a, plurality of discrete masses releasably mounted in the projectile with the centers of gravity of said masses located in a plane substantially normalp=1-0 the axis of the projectile, and having detonation means associated with each of said discrete masses, said method comprising the steps of transmitting a predetermined signal to said projectile by laser beam means, receiving said signal by said projectile, determining the deviation of the projectile from an optimum trajectory along which the projectile would impact a target by means carried by said projectile, and selectively detonating said detonation means to release at least one of said masses from said projectile in response to receipt of said signal by said projectile in a manner to impart a correctional momentum to said projectile which acts in a plane perpendicular to the axis of the projectile at or very near the center of gravity of the projectile and is sufficient to translate said projectile from the trajectory traveled by the projectile at the time of the correctional momentum toward the said optimum trajectory which substantially improves the probability of the projectile hitting the target.
2. A method as claimed in Claim 1, wherein said projectile includes chemical propellant means cooperative with said discrete masses to effect release of said masses from said projectile upon selective detonation of said chemical propellant means, and wherein said predetermined 41097/2 si.gn.al to said projectile is transmitted and received in a manner to selectively detonate a propellant means and release at least one of said discrete masses to impart said correctional momentum to said projectile.
3. A method as claimed in Claim 1 or Claim 2, wherein said correctional momentum applied to said projectile is imparted in a radial direction relative to the axis of said projectile.
4. A method as claimed in Claim 2, wherein said chemical propellant means comprises high, explosive means cooperative with said masses, to selectively release at least one of said masses from said projectile upon selective detonation of said explosive means, and wherein said step of transmitting said predetermined signal to said projectile and receiving said signal by said projectile are sequenced in a manner to effect said selective detonation and release at least one of said masses to impart said correctional momentum to said projectile.
5. A missile guidance system for guiding a rotationally spinning projectile, said system including discrete mass means mounted in the projectile with the center of gravity of said discrete mass means located in a plane substantially perpendicular to the axis of the projectile and at or very near the center of gravity of said projectile, laser beam means for transmitting a predetermined signal to said projectile, and means within the projectile responsive to receipt of said predetermined signal for determining the deviation of 41097/2 the projectile from, an optimum trajectory along which the projectile would impact a target and for effecting an impulse reaction by selective release of said discrete mass means in a manner to impart a correctional momentum to said projectile and cause said projectile to translate toward said optimum trajectory.
6. A system as claimed in Claim 5, wherein said impulse reaction means includes one or more discrete masses which are releasably mounted in said projectile, and high explosive means cooperative with said discrete masses to effect release of said masses from said projectile upon selected detonation of said high explosive means, and wherein said predetermined signal is effective to selectively detonate said high explosive means and effect release of at least one of said discrete masses.
7. A missile guidance system as claimed in Claim 5, or Claim 6, wherein said means in said projectile responsive to receipt of said predetermined signal includes microcircuit computational element means disposed within said projectile.
8. A projectile for use in a system operative to guide a rotationally spinning projectile between a guidance laser source and a predetermined target substantially along an optimum trajectory, said projectile having discrete mass means mounted thereon and including means capable of being detonated in a manner to effect a net impulse force on the projectile which acts substantially in a plane normal to the projectile axis and passes 41097/3' Substa t ally* through, the center of gravity of the; ' projectile, and means carried by said projectile responsive to a predetermined signal received by said projectile to dete'rmine deviation of th projectile from an optimum trajectory along which the projectile would impact a target and effect detonation of said detonation means to selectively release said discrete mass means to provide a correctional momentum to the projectile to bring it into said optimum trajectory so as to increase the probability of impact of the projectile with the predetermined target.
9. A projectile as claimed in Claim 8, wherein said discrete mass means includes a plurality of discrete guidance masses which are releasably mounted in said projectile substantially in a plane normal to the axis of the projectile and passing substantially through the center of gravity thereof, said detonation means being capable of effecting release of at least one of said masses from said projectile to provide said correctional momentum.
10. A projectile as claimed in Claim 9, wherein said detonation means includes high explosive means selectively detonatable to effect release of at least one of said discrete masses.
11. A method of making an in-flight correction of the trajectory of a high speed spinning projectile substantially as hereinbefore described with reference to the accompanying drawings. 41097/2
12. A missile guidance system substantially as hereinbefore described with reference to and as illustrated in the accompanying drawings.
13. A projectile substantially as hereinbefore described with reference to and as illustrated in the accompanying drawings . _?or the Applicants P
IL41097A 1972-01-03 1972-12-15 Rotationally spinning guided projectile and method of making an in-flight correction of its trajectory IL41097A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US21461972A 1972-01-03 1972-01-03

Publications (2)

Publication Number Publication Date
IL41097A0 IL41097A0 (en) 1973-06-29
IL41097A true IL41097A (en) 1976-08-31

Family

ID=22799788

Family Applications (1)

Application Number Title Priority Date Filing Date
IL41097A IL41097A (en) 1972-01-03 1972-12-15 Rotationally spinning guided projectile and method of making an in-flight correction of its trajectory

Country Status (8)

Country Link
CA (1) CA1009370A (en)
CH (1) CH561893A5 (en)
DE (1) DE2264243C2 (en)
FR (1) FR2167608B1 (en)
GB (1) GB1429941A (en)
IL (1) IL41097A (en)
IT (1) IT976742B (en)
NL (1) NL182911C (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0371007A2 (en) 1985-11-22 1990-05-30 Ship Systems, Inc. Spin-stabilized projectile with pulse receiver and method of use

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2500232C2 (en) * 1972-01-03 1985-01-17 Ship Systems Inc., San Diego, Calif. Improved spin-stabilized missile with correctable trajectory
DE2543606C2 (en) * 1975-09-30 1986-11-06 Deutsch-Französisches Forschungsinstitut Saint-Louis, Saint-Louis Arrangement for correcting the trajectory of a rotating projectile
GB1605301A (en) * 1976-10-08 1988-08-24 Secr Defence Brit Fuzing systems for projectiles
DE2853779C3 (en) * 1978-12-13 1988-02-11 Diehl GmbH & Co, 8500 Nürnberg Rollage knife for spin-stabilized missiles and projectiles
US4347996A (en) * 1980-05-22 1982-09-07 Raytheon Company Spin-stabilized projectile and guidance system therefor
SE430102B (en) * 1981-10-08 1983-10-17 Saab Scania Ab SET AND DEVICE FOR CONTROL OF AN AERODYNAMIC BODY WITH HANDLESS MOLD SUGAR
GB2370342B (en) * 1981-11-05 2002-11-20 Emi Ltd Terminally - corrected sub-munitions
GB2132740B (en) * 1982-07-21 1986-03-12 James Bertram King Weapons system
DE3427227A1 (en) * 1984-07-24 1986-01-30 Diehl GmbH & Co, 8500 Nürnberg END-PHASE-CONTROLLABLE AMMUNITION ITEM AND METHOD FOR ITS TARGET NAVIGATION
FR2612620A1 (en) * 1987-03-20 1988-09-23 Precoul Michel Improvements made to projectiles, in particular for direct firing
DE59004020D1 (en) * 1989-09-19 1994-02-10 Diehl Gmbh & Co Track correctable projectile.
DE4123308C2 (en) * 1991-07-13 1993-12-23 Diehl Gmbh & Co Dirigible projectile against aerial targets
DE4410326C2 (en) * 1994-03-25 1998-07-02 Rheinmetall Ind Ag Projectile with a device for trajectory correction
DE102007059397A1 (en) 2007-12-10 2009-06-18 Diehl Bgt Defence Gmbh & Co. Kg swash detonator
DE102010006528B4 (en) * 2010-02-01 2013-12-12 Rheinmetall Air Defence Ag Method and device for programming a projectile
DE102010006529B4 (en) 2010-02-01 2013-12-12 Rheinmetall Air Defence Ag Method and device for transmitting energy to a projectile

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3374967A (en) * 1949-12-06 1968-03-26 Navy Usa Course-changing gun-launched missile
NL228838A (en) * 1957-06-19
BE683586A (en) * 1966-07-04 1966-12-16

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0371007A2 (en) 1985-11-22 1990-05-30 Ship Systems, Inc. Spin-stabilized projectile with pulse receiver and method of use

Also Published As

Publication number Publication date
IT976742B (en) 1974-09-10
CA1009370A (en) 1977-04-26
DE2264243A1 (en) 1973-07-12
NL182911C (en) 1988-06-01
CH561893A5 (en) 1975-05-15
NL7300067A (en) 1973-07-05
FR2167608B1 (en) 1977-09-02
GB1429941A (en) 1976-03-31
IL41097A0 (en) 1973-06-29
NL182911B (en) 1988-01-04
FR2167608A1 (en) 1973-08-24
DE2264243C2 (en) 1985-01-03

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