WO2001009637A1 - Procede pour determiner la position des axes de reference d'un systeme de navigation par inertie que comporte un objet par rapport aux coordonnes de base et modes de realisation correspondants - Google Patents
Procede pour determiner la position des axes de reference d'un systeme de navigation par inertie que comporte un objet par rapport aux coordonnes de base et modes de realisation correspondants Download PDFInfo
- Publication number
- WO2001009637A1 WO2001009637A1 PCT/RU1999/000260 RU9900260W WO0109637A1 WO 2001009637 A1 WO2001009637 A1 WO 2001009637A1 RU 9900260 W RU9900260 W RU 9900260W WO 0109637 A1 WO0109637 A1 WO 0109637A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- οbeκτa
- κοορdinaτ
- ineρtsialnοy
- sisτeme
- τρaeκτορii
- Prior art date
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/38—Determining a navigation solution using signals transmitted by a satellite radio beacon positioning system
- G01S19/39—Determining a navigation solution using signals transmitted by a satellite radio beacon positioning system the satellite radio beacon positioning system transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/53—Determining attitude
Definitions
- the proposed invention is not available for navigation of various devices moving in an inertial area and having an inertial navigation system on board.
- the method is mainly used for the initial delivery of non-stationary systems of a non-mobile land of the earth, as a result of which there is a lot of activity.
- the method cannot be used for moving objects that are experiencing acceleration and angular speed.
- the method is used for the initial delivery of the entire navigation system of fixed systems for known directions, for example, to selected stars, and in the process.
- the direction of the unit is “appliance - Polar star”, other than the base of the calculation and taking into account the non-profit base.
- the parameters are commemorated.
- the account base is an area that includes the directions “apparatus - Polar star” and “apparatus -
- SIGNIFICANT FOX (DR. 26) ⁇ ⁇ 01/09637 2 ⁇ 99 / 00260 a navigation star. " It is characterized by an inertial advantage. The same is true for the rotation of the Polar Star, and the total area of sensibility of the senses of the Earth and the Polar Star is uncoupled. The angle between the area containing the direction “Earth center - Polar star” and “the center of the Earth - polar axis”, and the plane that includes the “center of the Earth - polar star”.
- optical devices For terrestrial and military equipment in the atmosphere that are subject to the effects of environmental conditions, the use of optical devices is prohibited.
- S ⁇ s ⁇ b m ⁇ zhe ⁇ is ⁇ lz ⁇ va ⁇ sya ⁇ l ⁇ in ⁇ e ⁇ sluchaya ⁇
- ⁇ gda apel ⁇ vaya sis ⁇ ema ⁇ dina ⁇
- sis ⁇ ema ⁇ dina ⁇ ⁇ be ⁇ a is ⁇ y ⁇ yvayu ⁇ ⁇ dn ⁇ and ⁇ zhe us ⁇ enie
- ⁇ -es ⁇ n ⁇ si ⁇ el is ⁇ v ⁇ y sis ⁇ emy and ⁇ be ⁇ linked me ⁇ aniches ⁇ i and dvizhu ⁇ sya ⁇ edin ⁇ y ⁇ ae ⁇ ii.
- an airplane objec
- a propellant objec
- the carrier must have a non-profitable state.
- a self-propelled carrier at the time of launching a carrier-rocket, there may be an orientation of the entire base system with a good ten minutes.
- SIGNIFICANT FOX (DR. 26) ⁇ ⁇ 01/09637 ⁇ / ⁇ 99 / 00260
- the objective of the proposed invention is to increase the accuracy and reliability of the distribution of the services of a non-removable, mobile, and non-mobile device.
- This task d ⁇ s ⁇ igae ⁇ sya ⁇ em, ch ⁇ in s ⁇ s ⁇ be ⁇ va ⁇ ian ⁇ u 1 ⁇ edeleniya ⁇ l ⁇ zheniya ⁇ sey ⁇ dina ⁇ ine ⁇ tsialn ⁇ y navigatsi ⁇ nn ⁇ y sis ⁇ emy ⁇ be ⁇ a ⁇ n ⁇ si ⁇ eln ⁇ apel ⁇ , v ⁇ yuschem navigatsi ⁇ nnye izme ⁇ eniya ⁇ be ⁇ a, dvizhuscheg ⁇ sya in ine ⁇ tsialn ⁇ m ⁇ s ⁇ ans ⁇ ve in apel ⁇ v ⁇ y sis ⁇ eme ⁇ dina ⁇ and ine ⁇ tsialn ⁇ y sis ⁇ eme ⁇ dina ⁇ ⁇
- SIGNIFICANT FOX (DR. 26) ⁇ ⁇ 01/09637 ⁇ / ⁇ 99 / 00260
- the components of the matrix share the use of the entire navigation system of the accessory system with a non-essential base.
- SIGNIFICANT FOX 5 systems of the system, including navigational changes of the object, moving in an inertial device, in the base system of the device and in the inert system of the computer
- [,) 1 ... ⁇ , ⁇ ), where ⁇ is the transition matrix from the base system to the in-process system, ⁇ is the quantity of participation in the transport;
- the components of the matrix share the use of the entire navigation system of the accessory system with a non-essential base.
- the essential offer is illustrated on ⁇ . ⁇ , where: 1 - the object;
- SIGNIFICANT FOX (DR. 26) ⁇ ⁇ 01/09637 ⁇ / ⁇ 9 / 00260
- the device will share the use of the in-system navigation system of the 2-in-3 main base; ⁇ -divide the angles of separation between them ⁇ , ⁇ , ⁇ (angles
- SIGNIFICANT FOX (DR. 26) ⁇ ⁇ 01/09637 ⁇ / ⁇ 9 / 00260
- ⁇ is the transition matrix from the base system of the system to the in- tial system of the component, ⁇ is the quantity of participation in the process;
- the components of the matrix share the use of the in-system navigation system 2 of the base system 3.
- the proposed method for option 3 differs in that:
- ⁇ ,) 1 ... ⁇ , ⁇ , where ⁇ is the transition matrix from the base system to the in-process system, ⁇ is the quantity of participation in the vehicle; - In addition, the components of the matrix share the use of the in-system navigation system 2 of the base system 3.
- the method is also distinguished by the fact that when the movement of the object 1 in an inertial
- SIGNIFICANT FOX (DR. 26) 9
- the use of direct linear traffic involves maneuvering, which implements, at the very least, two non-parallel operating paths,
- SIGNIFICANT FOX (DR. 26) ⁇ ⁇ 01/09637 ⁇ / ⁇ 9 / 00260
Description
Claims
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP99952823A EP1207403A4 (en) | 1999-07-29 | 1999-07-29 | METHOD FOR DETERMINING THE POSITION OF THE REFERENCE AXES OF AN INERTIA NAVIGATION SYSTEM THAT AN OBJECT CONTAINS RELATIVE TO BASIC COORDINATES AND CORRESPONDING EMBODIMENTS |
US10/048,176 US6650287B1 (en) | 1999-07-29 | 1999-07-29 | Method for determining the position of reference axes in an inertial navigation system of an object in respect with the basic coordinates and embodiments thereof |
AU64890/99A AU6489099A (en) | 1999-07-29 | 1999-07-29 | Method for determining the position of reference axes in an inertial navigation system of an object in respect with the basic coordinates and embodiments thereof |
UA2002021655A UA59494C2 (ru) | 1999-07-29 | 1999-07-29 | Способ определения положений осей координат системы инерциальной навигации объекта относительно базовой системы координат (варианты) |
PCT/RU1999/000260 WO2001009637A1 (fr) | 1999-07-29 | 1999-07-29 | Procede pour determiner la position des axes de reference d'un systeme de navigation par inertie que comporte un objet par rapport aux coordonnes de base et modes de realisation correspondants |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/RU1999/000260 WO2001009637A1 (fr) | 1999-07-29 | 1999-07-29 | Procede pour determiner la position des axes de reference d'un systeme de navigation par inertie que comporte un objet par rapport aux coordonnes de base et modes de realisation correspondants |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2001009637A1 true WO2001009637A1 (fr) | 2001-02-08 |
Family
ID=20130377
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/RU1999/000260 WO2001009637A1 (fr) | 1999-07-29 | 1999-07-29 | Procede pour determiner la position des axes de reference d'un systeme de navigation par inertie que comporte un objet par rapport aux coordonnes de base et modes de realisation correspondants |
Country Status (5)
Country | Link |
---|---|
US (1) | US6650287B1 (ru) |
EP (1) | EP1207403A4 (ru) |
AU (1) | AU6489099A (ru) |
UA (1) | UA59494C2 (ru) |
WO (1) | WO2001009637A1 (ru) |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7287701B2 (en) * | 2005-02-17 | 2007-10-30 | The Boeing Company | Handheld coordinate reference system |
JP4983132B2 (ja) * | 2006-07-26 | 2012-07-25 | 株式会社デンソー | 車両の方向特定方法,および,車両方向特定装置。 |
CN101846520B (zh) * | 2010-04-20 | 2012-06-06 | 长春理工大学 | 一种用于运动终端间激光通信捕获过程中的动态补偿方法 |
US8963764B1 (en) | 2011-01-14 | 2015-02-24 | Lockheed Martin Corporation | Ship heading and pitch using satellite ephemerides and radar range measurement of satellite |
US9459344B1 (en) * | 2011-01-14 | 2016-10-04 | Lockheed Martin Corporation | Ship position and velocity using satellite ephemerides and radar range measurement of satellite |
CN103411610A (zh) * | 2013-07-29 | 2013-11-27 | 哈尔滨工程大学 | 一种惯性导航系统极区模式横地理纬度初始值的测量方法 |
CN104596503B (zh) * | 2015-01-26 | 2018-04-13 | 中国人民解放军国防科学技术大学 | 基于差分卫星导航测量的跟踪转台定姿与指令补偿方法 |
CN105466477B (zh) * | 2015-12-07 | 2018-05-18 | 中国科学院光电研究院 | 一种面向卫星目标和恒星目标的天基观测模拟系统及方法 |
CN105676865B (zh) * | 2016-04-12 | 2018-11-16 | 北京博瑞云飞科技发展有限公司 | 目标跟踪方法、装置和系统 |
US10262546B2 (en) | 2016-04-13 | 2019-04-16 | Ge Aviation Systems Llc | Aircraft navigation using exponential map |
CN106092096A (zh) * | 2016-06-03 | 2016-11-09 | 上海航天控制技术研究所 | 高精度轨道仿真中基于迭代逼近方法的卫星位置确定方法 |
CN106441297B (zh) * | 2016-08-30 | 2019-11-01 | 北京航空航天大学 | 惯导系统的重力误差矢量获取方法和装置 |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4672382A (en) * | 1984-12-07 | 1987-06-09 | Nissan Motor Co., Ltd. | Position measuring system |
US4898349A (en) * | 1988-12-09 | 1990-02-06 | General Electric Company | Spacecraft approach/separation by use of angular measurement |
US5001647A (en) * | 1989-08-31 | 1991-03-19 | General Electric Company | Inertial transformation matrix generator |
RU2073210C1 (ru) * | 1993-03-10 | 1997-02-10 | Раменское приборостроительное конструкторское бюро | Инерциальноспутниковая система |
US5910789A (en) * | 1994-12-20 | 1999-06-08 | Geco A.S. | Method for integrity monitoring in position determination |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0263894B1 (de) * | 1986-10-16 | 1990-04-25 | LITEF GmbH | Verfahren zur Kursbestimmung in Luftfahrzeugen |
US5406489A (en) * | 1992-07-10 | 1995-04-11 | Unisys Corporation | Instrument for measuring an aircraft's roll, pitch, and heading by matching position changes along two sets of axes |
RU2033949C1 (ru) | 1993-02-09 | 1995-04-30 | Севастиян Дмитриевич Гнатюк | Автономная бортовая система управления космического аппарата "гасад" |
US5614913A (en) | 1995-06-07 | 1997-03-25 | Trimble Navigation | Optimization of survey coordinate transformations |
-
1999
- 1999-07-29 AU AU64890/99A patent/AU6489099A/en not_active Abandoned
- 1999-07-29 US US10/048,176 patent/US6650287B1/en not_active Expired - Fee Related
- 1999-07-29 WO PCT/RU1999/000260 patent/WO2001009637A1/ru not_active Application Discontinuation
- 1999-07-29 UA UA2002021655A patent/UA59494C2/ru unknown
- 1999-07-29 EP EP99952823A patent/EP1207403A4/en not_active Ceased
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4672382A (en) * | 1984-12-07 | 1987-06-09 | Nissan Motor Co., Ltd. | Position measuring system |
US4898349A (en) * | 1988-12-09 | 1990-02-06 | General Electric Company | Spacecraft approach/separation by use of angular measurement |
US5001647A (en) * | 1989-08-31 | 1991-03-19 | General Electric Company | Inertial transformation matrix generator |
RU2073210C1 (ru) * | 1993-03-10 | 1997-02-10 | Раменское приборостроительное конструкторское бюро | Инерциальноспутниковая система |
US5910789A (en) * | 1994-12-20 | 1999-06-08 | Geco A.S. | Method for integrity monitoring in position determination |
Non-Patent Citations (1)
Title |
---|
See also references of EP1207403A4 * |
Also Published As
Publication number | Publication date |
---|---|
EP1207403A1 (en) | 2002-05-22 |
UA59494C2 (ru) | 2003-09-15 |
EP1207403A4 (en) | 2004-05-19 |
US6650287B1 (en) | 2003-11-18 |
AU6489099A (en) | 2001-02-19 |
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