Integrated navigation system of strapdown inertial navigation system (SINS)/central nervous system (CNS)/global navigation satellite system (GNSS) of geostationary earth orbit (GEO) transfer vehicle

An integrated navigation system and orbit transfer technology, applied in the direction of navigation through speed/acceleration measurement, astronomical navigation, navigation calculation tools, etc., can solve the problems that have not yet collected data, no explanation or report has been found, and achieve high reliability, The effect of strong autonomy and high precision
CN103134491AActive Publication Date: 2013-06-05SHANGHAI AEROSPACE SYST ENG INST
2 Cites 32 Cited by

Patent Information

Authority / Receiving Office
CN Β· China
Patent Type
Applications(China)
Current Assignee / Owner
SHANGHAI AEROSPACE SYST ENG INST
Publication Date
2013-06-05

Smart Images

  • Figure 1
    Figure 1
  • Figure 2
    Figure 2
  • Figure 3
    Figure 3
Patent Text Reader

Abstract

The invention provides an integrated navigation system of a strapdown inertial navigation system (SINS) / a central nervous system (CNS) / a global navigation satellite system (GNSS) of a geostationary earth orbit (GEO) transfer vehicle. The SINS serves as a core of the integrated navigation system. Navigation information of the GEO transfer vehicle is calculated and output by the SINS in real time, fault detection and isolation are conducted to data output by a GNSS receiver, a globe sensor and a star sensor by utilizing a residual error chi 2 detecting method improved by a kalman filter. Information fusion is conducted to output information of the globe sensor and the star sensor in a celestial navigation system, pseudorange measuring information output by the GNSS receiver and the navigation information output by the SINS. Navigation errors, inertial device errors, globe sensor errors and GNSS receiver time errors of the GEO transfer vehicle are evaluated in real time, and the navigation errors of the GEO transfer vehicle are corrected through a manner of closed loop feedback correction in real time so that in-orbit self navigation with high precision and high reliability of the GEO transfer vehicle is achieved, and therefore meaningful effects of good subjectivity, high precision, good robustness and high reliability are obtained.
Need to check novelty before this filing date? Find Prior Art

Description

technical field

[0001] The invention relates to the technical field of autonomous navigation of a GEO orbit transfer aircraft, in particular to an information fusion and fault-tolerant design technology applicable to a SINS / CNS / GNSS integrated navigation system of a GEO orbit transfer aircraft. Background technique

[0002] At present, most of the space vehicles operating on the GEO orbit realize the navigation and orbit determination and the corresponding orbit maintenance control through the orbit forecast of the ground measurement and control system. One of the characteristics of the new GEO orbit transfer aircraft is that it can perform autonomous maneuvers in orbit, while the ground measurement and control orbit forecast can only predict the orbit of the aircraft based on the perturbed orbit dynamics. If the aircraft performs orbit change maneuvers during this period, the ground measurement and control The orbit forecast data cannot reflect the real orbit of the aircraf...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More