IL265993B2 - Method of controlling ejection of a missile form a canister and system therefor - Google Patents

Method of controlling ejection of a missile form a canister and system therefor

Info

Publication number
IL265993B2
IL265993B2 IL265993A IL26599319A IL265993B2 IL 265993 B2 IL265993 B2 IL 265993B2 IL 265993 A IL265993 A IL 265993A IL 26599319 A IL26599319 A IL 26599319A IL 265993 B2 IL265993 B2 IL 265993B2
Authority
IL
Israel
Prior art keywords
canister
measured
missile
data indicative
angle
Prior art date
Application number
IL265993A
Other languages
Hebrew (he)
Other versions
IL265993A (en
Inventor
Shaltiel Rabin
Avishai Ofer
Original Assignee
Israel Aerospace Ind Ltd
Shaltiel Rabin
Avishai Ofer
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 Israel Aerospace Ind Ltd, Shaltiel Rabin, Avishai Ofer filed Critical Israel Aerospace Ind Ltd
Priority to IL265993A priority Critical patent/IL265993B2/en
Priority to EP20788349.7A priority patent/EP3953656A4/en
Priority to US17/602,672 priority patent/US20220178658A1/en
Priority to PCT/IL2020/050324 priority patent/WO2020208625A1/en
Publication of IL265993A publication Critical patent/IL265993A/en
Publication of IL265993B2 publication Critical patent/IL265993B2/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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/007—Preparatory measures taken before the launching of the guided missiles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A27/00—Gun mountings permitting traversing or elevating movement, e.g. gun carriages
    • F41A27/28—Electrically-operated systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A23/00—Gun mountings, e.g. on vehicles; Disposition of guns on vehicles
    • F41A23/34—Gun mountings, e.g. on vehicles; Disposition of guns on vehicles on wheeled or endless-track vehicles
    • F41A23/42—Gun mountings, e.g. on vehicles; Disposition of guns on vehicles on wheeled or endless-track vehicles for rocket throwers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A27/00—Gun mountings permitting traversing or elevating movement, e.g. gun carriages
    • F41A27/30—Stabilisation or compensation systems, e.g. compensating for barrel weight or wind force on the barrel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G3/00—Aiming or laying means
    • F41G3/14—Indirect aiming means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B30/00—Projectiles or missiles, not otherwise provided for, characterised by the ammunition class or type, e.g. by the launching apparatus or weapon used

Landscapes

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

Claims (9)

V3/Amended on 15/12/20 CLAIMS
1. A method for reducing or eliminating "Missile Tip-off Effect" (MTE) of a missile ejected from a canister comprising, by a processor and associated storage: a. receiving data indicative of desired canister state in response to a launch command, the desired canister state includes at least desired canister angle; perform repeatedly until the missile is ejected from the canister: b. receiving, from at least one sensor associated with the canister, data indicative of measured canister state, wherein measured canister state includes at least measure canister angle and measured missile angle; c. processing at least said data indicative of measured canister state and desired canister state for meeting an MTE control criterion, and in response outputting data indicative of a command to at least one actuator associated with the canister for modifying at least the angular position of the canister; thereby reducing or eliminating said (MTE) effect.
2. The method according to Claim 1, wherein said measured canister state includes measured canister angle and wherein desired canister state includes desired canister angle.
3. The method according to Claims 1 or 2, wherein said measured canister state includes measured canister angular rate and wherein desired canister state includes desired canister angular rate.
4. The method according to Claim 3, wherein said processing for outputting data indicative of said command complies with Equation 1: u0001u0002= −u0005 ∙ u0007bttu0002u000bfru000eu000fu0010∙ u0011u0012 ∙ u0013 ∙ u0014u000b∙ u0015u0016 − u0017u0018 u0002u0019u001au001b + u001du0014u000bu0012−u0005u0002u000bfru000eu000fu0010bttu001eu0002u000bfru000eu000fu0010u001f ∙ u0017u0002u000bfru000eu000fu0010− u0017u0002u0019u001a!"# 30 V3/Amended on 15/12/20
5. The method according to any one of the preceding Claims, wherein said measured canister state includes measured missile angle and wherein desired canister state includes desired canister angle.
6. The method according to Claim 3, wherein said measured canister state includes measured missile rate and wherein desired canister state includes desired canister rate.
7. The method according to Claim 6, wherein said processing for outputting data indicative of said command complies with Equation 2: u0001u0002= −u0005u0002u000bfru000eu000fu0010∙ u0011bttu0002u000bfru000eu000fu0010∙ %u0012 ∙ u0013 ∙ u0014u000b∙ u0015&'()*+,-.− u0017u0018 u0002u0019u001au001b + /u0014u000bu0012−u0005u0002u000bfru000eu000fu0010b tt0u0002u000bfru000eu000fu0010∙ u0017u0002u000bfru000eu000fu0010− u0017u0002u0019u001a!2" + −u0005u001afrrf3u000f∙ u0011bttu0002u000bfru000eu000fu0010∙ %u0012 ∙ u0013 ∙ u0014u000b∙ u0015u0016u001afrrf3u000f− u0017u0018 u0002u0019u001au001b + /u0014u000bu0012−u0005 u0002u000bfru000eu000fu0010btt0u0002u000bfru000eu000fu0010∙ u00174*++*5-− u0017u0002u0019u001a!2"
8. The method according to any one of the preceding Claims, wherein the larger the difference between the desired canister state and the measured canister state, the larger is said command.
9. The method according to any one of the preceding Claims, wherein said measured canister state includes data indicate of remaining flight time of the missile in the canister , such that for the same difference in measured angle or rate vs. desired angle or rate, the shorter the remaining flight time, the larger the command. 10.The method according to any one of the preceding Claims, further comprising modifying on-the-fly said data indicative of desired canister state. 11.The method according to any one of the preceding Claims, wherein at least one of said sensors is fitted on the canister. 12.The method according to any one of the preceding Claims, wherein at least one of said sensors is fitted on the missile. 13.The method according to any one of the preceding Claims, further comprising an array of canisters. 14. The method according to Claim 13, wherein said data indicative of measured canister state is obtained by averaging the data indicative of the canister state of each canister of said array. 15.A system for reducing or eliminating "Missile Tip-off Effect" (MTE) of a missile ejected from a canister comprising, a processor and associated storage configured to: V3/Amended on 15/12/20 a. receiving data indicative of desired canister state in response to a launch command, the desired canister state includes at least desired canister angle; perform repeatedly until the missile is ejected from the canister a. receiving, from at least one sensor associated with the canister, data indicative of measured canister state, wherein measured canister state includes at least measure canister angle and measured missile angle; b. processing at least said data indicative of measured canister state and desired canister state for meeting an MTE control criterion, and in response outputting data indicative of a command to at least one actuator associated with the canister for modifying at least the angular position of the canister; thereby reducing or eliminating said (MTE) effect. 16. A non-transitory computer-readable memory tangibly embodying a program of instructions executable by the processor for executing the method of anyone of Claims 1 to 14. 20
IL265993A 2019-04-11 2019-04-11 Method of controlling ejection of a missile form a canister and system therefor IL265993B2 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
IL265993A IL265993B2 (en) 2019-04-11 2019-04-11 Method of controlling ejection of a missile form a canister and system therefor
EP20788349.7A EP3953656A4 (en) 2019-04-11 2020-03-19 Method of controlling ejection of a missile from a canister and system therefor
US17/602,672 US20220178658A1 (en) 2019-04-11 2020-03-19 Method of controlling ejection of a missile from a canister and system therefor
PCT/IL2020/050324 WO2020208625A1 (en) 2019-04-11 2020-03-19 Method of controlling ejection of a missile from a canister and system therefor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
IL265993A IL265993B2 (en) 2019-04-11 2019-04-11 Method of controlling ejection of a missile form a canister and system therefor

Publications (2)

Publication Number Publication Date
IL265993A IL265993A (en) 2020-10-28
IL265993B2 true IL265993B2 (en) 2023-06-01

Family

ID=67874134

Family Applications (1)

Application Number Title Priority Date Filing Date
IL265993A IL265993B2 (en) 2019-04-11 2019-04-11 Method of controlling ejection of a missile form a canister and system therefor

Country Status (4)

Country Link
US (1) US20220178658A1 (en)
EP (1) EP3953656A4 (en)
IL (1) IL265993B2 (en)
WO (1) WO2020208625A1 (en)

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120256038A1 (en) * 2009-06-05 2012-10-11 The Charles Stark Draper Laboratory, Inc. Systems and methods for targeting a projectile payload
RU2659622C1 (en) * 2017-08-29 2018-07-03 Акционерное общество "Конструкторское бюро приборостроения им. академика А.Г. Шипунова" Rotating along the roll angle with direction gyroscope to the target acquisition zone by the homing head rocket outputting method and system for its implementation

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4327624A (en) * 1980-06-23 1982-05-04 General Dynamics, Pomona Division Tip off rate reducer
US5175600A (en) * 1990-06-21 1992-12-29 Frank Jack D Collimator mounting means adapted for attachment to missile launcher
DE4234026C1 (en) * 1992-10-09 1994-02-10 Bodenseewerk Geraetetech Inertial measurement unit for missile or projectile - aligns optical rotation sensor axis with drift axis of two=axis mechanical gyroscope and with axis of high acceleration of launch
JP2000213894A (en) * 1999-01-25 2000-08-02 Mitsubishi Electric Corp Launching device of missile
IL211142A (en) * 2011-02-09 2015-06-30 Yesaiahu Redler System and method for measuring parameters of motion of a projectile as it exits the muzzle of a gun
US9012822B2 (en) * 2012-07-18 2015-04-21 Thales Holdings Uk Plc Missile guidance
US9612085B2 (en) * 2014-01-27 2017-04-04 Sparton Corporation Payload launch system and method
RU2569046C1 (en) * 2014-06-25 2015-11-20 Акционерное общество "Конструкторское бюро приборостроения им. академика А.Г. Шипунова" Method of combined guidance of small-sized missile with separable propulsion system and guidance system for its implementation
CN107044361A (en) * 2017-05-17 2017-08-15 西北工业大学 A kind of pulse detonation rocket engines and control method with combustion-compensating device
CN114001602A (en) * 2021-10-26 2022-02-01 东北大学秦皇岛分校 Rocket gun disturbance detection method based on quaternion Kalman filtering denoising fusion

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120256038A1 (en) * 2009-06-05 2012-10-11 The Charles Stark Draper Laboratory, Inc. Systems and methods for targeting a projectile payload
RU2659622C1 (en) * 2017-08-29 2018-07-03 Акционерное общество "Конструкторское бюро приборостроения им. академика А.Г. Шипунова" Rotating along the roll angle with direction gyroscope to the target acquisition zone by the homing head rocket outputting method and system for its implementation

Also Published As

Publication number Publication date
EP3953656A1 (en) 2022-02-16
WO2020208625A1 (en) 2020-10-15
EP3953656A4 (en) 2023-01-04
US20220178658A1 (en) 2022-06-09
IL265993A (en) 2020-10-28

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