WO1989011632A1 - Ensemble a capteurs inertiels d'axe incline - Google Patents

Ensemble a capteurs inertiels d'axe incline Download PDF

Info

Publication number
WO1989011632A1
WO1989011632A1 PCT/US1989/002221 US8902221W WO8911632A1 WO 1989011632 A1 WO1989011632 A1 WO 1989011632A1 US 8902221 W US8902221 W US 8902221W WO 8911632 A1 WO8911632 A1 WO 8911632A1
Authority
WO
WIPO (PCT)
Prior art keywords
gyros
accelerometers
suspension
plane
base member
Prior art date
Application number
PCT/US1989/002221
Other languages
English (en)
Inventor
Michael A. Knipfer
Kenneth H. Hannah
James S. Paul
Lucien E. Joly
Original Assignee
Honeywell 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 Honeywell Inc. filed Critical Honeywell Inc.
Publication of WO1989011632A1 publication Critical patent/WO1989011632A1/fr

Links

Classifications

    • 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

Definitions

  • the inertial sensor assembly includes six gyros and the six accelerometers mounted to faces of a single sensor base member, preferably composed of a single unitary body.
  • the six gyros are arranged with their respective input axis being mutually exclusive from another and passing through a common centerpoint, and six accelerometers are arranged with their respective input axis being mutually exclusive from another and also passing through the same common centerpoint at which the gyro input axes converge.
  • the inertial sensor assembly in accordance with the present invention includes a base member 10 for providing mounting surfaces for six gyros and six accelerometers (shown on subsequent drawings) .
  • Figure 1 shows a top plan view of base member 10.
  • Base member 10 is shown to be symmetrical about the X-axis, and more particularly about the X-Z plane (the Z-axis being out of the plane of the paper) .
  • the base member 10 is preferably comprised of a block of a selected material, generally to provide high stiffness and light weight, for example Aluminum.
  • Base member 10 includes an upper portion 12a and a lower portion 12b as defined by an imaginary suspension plane SP in parallel with the X-Y plane and passing through the common centerpoint CCP as will be subsequently described.

Landscapes

  • Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Automation & Control Theory (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Gyroscopes (AREA)

Abstract

On monte six gyros (131 à 136) et six accéléromètres (141 à 146) sur les faces d'un seul élément de base (10) à capteurs. Les capteurs sont agencés de sorte que leurs axes d'entrée passent tous par un point central commun (PCC), et que ledit point central commun (PCC) soit le centre de gravité de tout l'ensemble.
PCT/US1989/002221 1988-05-27 1989-05-23 Ensemble a capteurs inertiels d'axe incline WO1989011632A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US19951088A 1988-05-27 1988-05-27
US199,510 1988-05-27

Publications (1)

Publication Number Publication Date
WO1989011632A1 true WO1989011632A1 (fr) 1989-11-30

Family

ID=22737835

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US1989/002221 WO1989011632A1 (fr) 1988-05-27 1989-05-23 Ensemble a capteurs inertiels d'axe incline

Country Status (3)

Country Link
EP (1) EP0381726A4 (fr)
JP (1) JPH03501526A (fr)
WO (1) WO1989011632A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000012269A2 (fr) * 1998-08-26 2000-03-09 Honeywell Inc. Unite de regulation a inertie pour controler l'attitude d'un astronef
WO2006043890A1 (fr) * 2004-10-20 2006-04-27 Imego Ab Dispositif a capteurs
US7121159B2 (en) * 2002-03-01 2006-10-17 Ganid Productions, Llc Apparatus and method for gyroscopic propulsion
US8234943B2 (en) * 2002-03-01 2012-08-07 Ganid Productions, Llc Apparatus and method for gyroscopic propulsion
CN109238280A (zh) * 2018-09-29 2019-01-18 北京航天时代激光导航技术有限责任公司 一种采用50型激光陀螺的航空小型化惯性导航部件

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107588764B (zh) * 2017-08-07 2020-02-11 北京航天时代光电科技有限公司 一种四轴冗余构型电源和电路板冷备份的光纤陀螺组件
CN108267156B (zh) * 2017-12-20 2020-03-24 北京航天时代激光导航技术有限责任公司 激光惯组结构系统陀螺抖动性能确定方法

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3269179A (en) * 1959-05-29 1966-08-30 Honeywell Regulator Co Navigational instruments
US3403874A (en) * 1965-07-20 1968-10-01 Honeywell Inc Control apparatus for aircraft having fail-safe monitoring gyros
US3463909A (en) * 1966-08-15 1969-08-26 Singer General Precision Vector sensing system
US3489004A (en) * 1966-07-21 1970-01-13 Honeywell Inc Navigational reference device
US4020702A (en) * 1974-06-17 1977-05-03 The Bendix Corporation Redundant inertial measurement system configuration
US4125017A (en) * 1977-07-29 1978-11-14 Mcdonnell Douglas Corporation Redundant inertial measurement system
US4179818A (en) * 1976-10-07 1979-12-25 Litton Systems, Inc. Tetrahedral redundant inertial reference unit
US4212443A (en) * 1978-05-18 1980-07-15 Sperry Corporation Strapped down attitude and heading reference system for aircraft employing skewed axis two-degree-of-freedom rate gyros
US4675820A (en) * 1984-06-14 1987-06-23 Sundstrand Data Control, Inc. Inertial reference system
US4711125A (en) * 1985-11-06 1987-12-08 Morrison Melvin M Inertial measurement unit
US4795258A (en) * 1987-04-06 1989-01-03 Litton Systems, Inc. Nonplanar three-axis ring laser gyro with shared mirror faces
US4825716A (en) * 1987-11-13 1989-05-02 Honeywell, Inc. Single gimbal control moment gyroscope skewed array mounting arrangement

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3269179A (en) * 1959-05-29 1966-08-30 Honeywell Regulator Co Navigational instruments
US3403874A (en) * 1965-07-20 1968-10-01 Honeywell Inc Control apparatus for aircraft having fail-safe monitoring gyros
US3489004A (en) * 1966-07-21 1970-01-13 Honeywell Inc Navigational reference device
US3463909A (en) * 1966-08-15 1969-08-26 Singer General Precision Vector sensing system
US4020702A (en) * 1974-06-17 1977-05-03 The Bendix Corporation Redundant inertial measurement system configuration
US4179818A (en) * 1976-10-07 1979-12-25 Litton Systems, Inc. Tetrahedral redundant inertial reference unit
US4125017A (en) * 1977-07-29 1978-11-14 Mcdonnell Douglas Corporation Redundant inertial measurement system
US4212443A (en) * 1978-05-18 1980-07-15 Sperry Corporation Strapped down attitude and heading reference system for aircraft employing skewed axis two-degree-of-freedom rate gyros
US4675820A (en) * 1984-06-14 1987-06-23 Sundstrand Data Control, Inc. Inertial reference system
US4711125A (en) * 1985-11-06 1987-12-08 Morrison Melvin M Inertial measurement unit
US4795258A (en) * 1987-04-06 1989-01-03 Litton Systems, Inc. Nonplanar three-axis ring laser gyro with shared mirror faces
US4825716A (en) * 1987-11-13 1989-05-02 Honeywell, Inc. Single gimbal control moment gyroscope skewed array mounting arrangement

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
Journal of Spacecrafts and Rockets, Vol. 9, No. 1, January 1972, GILMORE et al, "A Redundant Strapdown Inertial Reference Unit (SIRU)" pages 39-47. *
See also references of EP0381726A4 *

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000012269A2 (fr) * 1998-08-26 2000-03-09 Honeywell Inc. Unite de regulation a inertie pour controler l'attitude d'un astronef
WO2000012269A3 (fr) * 1998-08-26 2000-06-02 Honeywell Inc Unite de regulation a inertie pour controler l'attitude d'un astronef
US7121159B2 (en) * 2002-03-01 2006-10-17 Ganid Productions, Llc Apparatus and method for gyroscopic propulsion
US8234943B2 (en) * 2002-03-01 2012-08-07 Ganid Productions, Llc Apparatus and method for gyroscopic propulsion
WO2006043890A1 (fr) * 2004-10-20 2006-04-27 Imego Ab Dispositif a capteurs
US7814791B2 (en) 2004-10-20 2010-10-19 Imego Ab Sensor device
CN109238280A (zh) * 2018-09-29 2019-01-18 北京航天时代激光导航技术有限责任公司 一种采用50型激光陀螺的航空小型化惯性导航部件
CN109238280B (zh) * 2018-09-29 2021-04-13 北京航天时代激光导航技术有限责任公司 一种采用50型激光陀螺的航空小型化惯性导航部件

Also Published As

Publication number Publication date
EP0381726A1 (fr) 1990-08-16
JPH03501526A (ja) 1991-04-04
EP0381726A4 (en) 1992-08-19

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