JPS5518780A - Missile guidance system - Google Patents

Missile guidance system

Info

Publication number
JPS5518780A
JPS5518780A JP9211478A JP9211478A JPS5518780A JP S5518780 A JPS5518780 A JP S5518780A JP 9211478 A JP9211478 A JP 9211478A JP 9211478 A JP9211478 A JP 9211478A JP S5518780 A JPS5518780 A JP S5518780A
Authority
JP
Japan
Prior art keywords
axis
missile
electric
seeker
error angle
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.)
Pending
Application number
JP9211478A
Other languages
Japanese (ja)
Inventor
Kaoru Tanaka
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.)
NEC Corp
Original Assignee
NEC Corp
Nippon Electric 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 NEC Corp, Nippon Electric Co Ltd filed Critical NEC Corp
Priority to JP9211478A priority Critical patent/JPS5518780A/en
Publication of JPS5518780A publication Critical patent/JPS5518780A/en
Pending legal-status Critical Current

Links

Landscapes

  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Abstract

PURPOSE: To make it possible to simplify the structure of an automatic trancking system and also to reduce the agitation of a beam due to a scan, by taking the scan with an electric seeker axis agreeing with a missile axis.
CONSTITUTION: As for the homing guidance system for a missile, error angle detector 1 of K1 in gain detects error angle vector ε between visual-line unit vector T indicating the direction of a target and unit vector S indicating the direction of the electric seeker axis having been scanned agreeing with the axis of the missile, and controller 2 composed of steering unit 4 and rate detector 5 guides the missile by turning around to eliminate ε. If an error angle exists between missile axis vectors KB and SS', the output of rate detector 5 is fed back to the electric seeker axis by electric seeker axis scan control part 3 in proportion to the error angle, thereby controlling the guidance with the electric seeker axis agreeing with the missile axis angle.
COPYRIGHT: (C)1980,JPO&Japio
JP9211478A 1978-07-27 1978-07-27 Missile guidance system Pending JPS5518780A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP9211478A JPS5518780A (en) 1978-07-27 1978-07-27 Missile guidance system

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP9211478A JPS5518780A (en) 1978-07-27 1978-07-27 Missile guidance system

Publications (1)

Publication Number Publication Date
JPS5518780A true JPS5518780A (en) 1980-02-09

Family

ID=14045397

Family Applications (1)

Application Number Title Priority Date Filing Date
JP9211478A Pending JPS5518780A (en) 1978-07-27 1978-07-27 Missile guidance system

Country Status (1)

Country Link
JP (1) JPS5518780A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS57123503U (en) * 1981-01-20 1982-08-02

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS57123503U (en) * 1981-01-20 1982-08-02

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