GB1138334A - Directional control device for guided missiles - Google Patents

Directional control device for guided missiles

Info

Publication number
GB1138334A
GB1138334A GB786565A GB786565A GB1138334A GB 1138334 A GB1138334 A GB 1138334A GB 786565 A GB786565 A GB 786565A GB 786565 A GB786565 A GB 786565A GB 1138334 A GB1138334 A GB 1138334A
Authority
GB
United Kingdom
Prior art keywords
missile
gyro
booster
radar
automatic control
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
Application number
GB786565A
Inventor
Thomas William Lake
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.)
SPERRY RAND Co Ltd
Original Assignee
SPERRY RAND Co Ltd
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 SPERRY RAND Co Ltd filed Critical SPERRY RAND Co Ltd
Priority to GB786565A priority Critical patent/GB1138334A/en
Publication of GB1138334A publication Critical patent/GB1138334A/en
Expired legal-status Critical Current

Links

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
    • G01C19/00—Gyroscopes; Turn-sensitive devices using vibrating masses; Turn-sensitive devices without moving masses; Measuring angular rate using gyroscopic effects
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/34—Direction control systems for self-propelled missiles based on predetermined target position data
    • F41G7/36—Direction control systems for self-propelled missiles based on predetermined target position data using inertial references
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
    • G01C21/00—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00
    • G01C21/10—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration
    • G01C21/12—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration executed aboard the object being navigated; Dead reckoning
    • G01C21/16—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration executed aboard the object being navigated; Dead reckoning by integrating acceleration or speed, i.e. inertial navigation
    • G01C21/18—Stabilised platforms, e.g. by gyroscope

Abstract

1,138,334. Automatic control of missiles. SPERRY RAND Ltd. Feb.22, 1966 [Feb.23, 1965], No.7865/65. Heading G3R. An auxiliary automatic control system, utilizing stored information computed before take-off, brings the attitude of a missile within the limited capabilities of another automatic control system which then takes over control of the missile's flight path so that the missile reaches a predetermined target. As described, a two-stage rocket missile which takes off from a vertical position is automatically headed in the general direction of a target by information stored in the booster stage before take-off. After separation of the booster stage, a two-gyro platform and a homing eye radar guide the warhead more accurately towards the target. Until just prior to takeoff , the direction which the missile will require to have at the time of booster separation is continuously computed on the ground from a radar tracker and transmitted through synchronous transmission links to a partly caged line-of - sight gyro and roll gyro in the booster. Just before launch the ground computer is disconnected and the roll gyro uncaged. After launch, when the missile has risen vertically and cleared its container, the gyros are rendered effective to steer the missile by controlling liquid injection into the propulsion jet stream. Automatic control of roll attitude is also effective. To prevent self-locking, the line-of-sight gyro is provided with an extra gimbal ring which is unlocked by operation of an electrical contact on the gyro when the missile turns through a large angle. A predetermined time after initiation of the directional control, signals from the line of sight gyro are applied to move the platform in the warhead to a corresponding position so that, at booster separation, the homing eye radar will be aimed approximately in the required direction. The last mentioned control is disabled just prior to booster separation, after which the warhead is controlled by its own homing eye radar and roll gyro.
GB786565A 1965-02-23 1965-02-23 Directional control device for guided missiles Expired GB1138334A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB786565A GB1138334A (en) 1965-02-23 1965-02-23 Directional control device for guided missiles

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB786565A GB1138334A (en) 1965-02-23 1965-02-23 Directional control device for guided missiles

Publications (1)

Publication Number Publication Date
GB1138334A true GB1138334A (en) 1969-01-01

Family

ID=9841275

Family Applications (1)

Application Number Title Priority Date Filing Date
GB786565A Expired GB1138334A (en) 1965-02-23 1965-02-23 Directional control device for guided missiles

Country Status (1)

Country Link
GB (1) GB1138334A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103543100A (en) * 2013-09-30 2014-01-29 中国人民解放军国防科学技术大学 Pneumatic test electric cable pulling device
CN110414018A (en) * 2018-04-27 2019-11-05 中国航天科工飞航技术研究院（中国航天海鹰机电技术研究院） A kind of virtual reality simulation method and system of Flight Vehicle Stage Separation
CN113218242A (en) * 2021-04-09 2021-08-06 北京航空航天大学 Universal vertical launching turning device

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103543100A (en) * 2013-09-30 2014-01-29 中国人民解放军国防科学技术大学 Pneumatic test electric cable pulling device
CN103543100B (en) * 2013-09-30 2015-11-25 中国人民解放军国防科学技术大学 The pneumatic de-pulling device of a kind of test cable
CN110414018A (en) * 2018-04-27 2019-11-05 中国航天科工飞航技术研究院（中国航天海鹰机电技术研究院） A kind of virtual reality simulation method and system of Flight Vehicle Stage Separation
CN113218242A (en) * 2021-04-09 2021-08-06 北京航空航天大学 Universal vertical launching turning device

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