JPS6446112A - Method for detecting rolling attitude angle of flying object - Google Patents

Method for detecting rolling attitude angle of flying object

Info

Publication number
JPS6446112A
JPS6446112A JP62202506A JP20250687A JPS6446112A JP S6446112 A JPS6446112 A JP S6446112A JP 62202506 A JP62202506 A JP 62202506A JP 20250687 A JP20250687 A JP 20250687A JP S6446112 A JPS6446112 A JP S6446112A
Authority
JP
Japan
Prior art keywords
attitude
computer
control
attitude angle
pitch
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.)
Granted
Application number
JP62202506A
Other languages
Japanese (ja)
Other versions
JP2671310B2 (en
Inventor
Toru Nakano
Mitsuhiko Terajima
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.)
Nissan Motor Co Ltd
Original Assignee
Nissan Motor 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 Nissan Motor Co Ltd filed Critical Nissan Motor Co Ltd
Priority to JP62202506A priority Critical patent/JP2671310B2/en
Publication of JPS6446112A publication Critical patent/JPS6446112A/en
Application granted granted Critical
Publication of JP2671310B2 publication Critical patent/JP2671310B2/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Landscapes

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

Abstract

PURPOSE:To reduce the load of a power supply by flying a flying object tempo rarily in a freely falling state with no control and meanwhile detecting the attitude angle change of at least the pitch via an inertia sensor unit to supply said angle change to an inertia guiding computer. CONSTITUTION:When the attitude control is required for a flying object 1 after launching, an inertia guiding computer 3 actuates an attitude controller 4 of an inertia sensor unit 2 to stop the spin of the object 1. At the same time, only the rolling control is performed for fixture of the rolling angle attitude. Then the object 1 files temporarily in a freely falling state with no control and the unit 2 detects both the yawing and pitch attitude angle changes for a prescribed time and after a prescribed period of time by a command given from the computer 3. These detected yawing and pitch attitude angle changes are supplied to the computer 3 and the computer 3 obtains the rolling attitude angle to the gravity of the axis of the object 1 from the yawing and pitch attitude change values. In such a way, it is required to drive the unit 2 only when needed so that the power supply load is reduced together with reduction of the cost.
JP62202506A 1987-08-13 1987-08-13 Method for detecting roll attitude angle of guided vehicle Expired - Fee Related JP2671310B2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP62202506A JP2671310B2 (en) 1987-08-13 1987-08-13 Method for detecting roll attitude angle of guided vehicle

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP62202506A JP2671310B2 (en) 1987-08-13 1987-08-13 Method for detecting roll attitude angle of guided vehicle

Publications (2)

Publication Number Publication Date
JPS6446112A true JPS6446112A (en) 1989-02-20
JP2671310B2 JP2671310B2 (en) 1997-10-29

Family

ID=16458610

Family Applications (1)

Application Number Title Priority Date Filing Date
JP62202506A Expired - Fee Related JP2671310B2 (en) 1987-08-13 1987-08-13 Method for detecting roll attitude angle of guided vehicle

Country Status (1)

Country Link
JP (1) JP2671310B2 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112284186A (en) * 2020-09-24 2021-01-29 北京航天自动控制研究所 Method for ensuring takeoff safety by reducing rolling angle deviation of carrier rocket

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS59171798A (en) * 1983-03-16 1984-09-28 宇宙開発事業団 Determination system of attitude of artificial satellite

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3249324A (en) 1958-09-19 1966-05-03 William B Coffman Method and system for inertial guidance
US3281094A (en) 1962-04-16 1966-10-25 Trident Engineering Associates Self-contained guidance system
US4044237A (en) 1976-03-16 1977-08-23 The United States Of America As Represented By The Secretary Of The Army Missile maneuver concept

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS59171798A (en) * 1983-03-16 1984-09-28 宇宙開発事業団 Determination system of attitude of artificial satellite

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112284186A (en) * 2020-09-24 2021-01-29 北京航天自动控制研究所 Method for ensuring takeoff safety by reducing rolling angle deviation of carrier rocket

Also Published As

Publication number Publication date
JP2671310B2 (en) 1997-10-29

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