Error Modeling, Calibration, and Compensation of Inertial Measurement Unit (IMU)

Quan, Wei; Gong, Xiaolin; Fang, Jiancheng; Li, Jianli

doi:10.1007/978-3-662-45159-5_4

Cited by 1 publication

(1 citation statement)

References 38 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…This contribution develops the conceptual mechanics of launching point missions in ballistic missile space orbit and presents results based on navigation strategy considering multiple celestial stars’ gravitational perturbations. 12 –18 The launching point inertial system is described as the long-range missile navigation reference to provide accurate spatial motion parameters and system control. 14,18 To obtain a consistent coordinate calculation of the ballistic missile, the coordinate system of a hypersonic vehicle platform is always parallel with the launching point inertial coordinate frame during the flight.…”

Section: Introductionmentioning

confidence: 99%

Integrated navigation approaches of vehicle aided by the strapdown celestial angles

Chen

Gao

Zhang

2020

International Journal of Advanced Robotic Systems

View full text Add to dashboard Cite

The integrated navigation method based on star sensor celestial angles (altitude angle and azimuth angle) is proposed to serve the need for rapidly responsive, reliable, and precise of a hypersonic vehicle under a sophisticated environment. An integrated navigation algorithm suitable for large azimuth misalignment is established under launching point inertial coordinate and local geographical coordinate system based on altitude angle and azimuth angles. Meanwhile, a Bayesian method for data dropouts aided by the strapdown celestial angles is presented for the rapid variability in the celestial star angle with active galaxies. A nonlinear Bayesian filter is applied to implement the simulation on account of the nonlinear feature of the state and measurement equations. The simulation results showed that the Bayesian method for integrated navigation data dropouts could be accomplished by altitude angle and azimuth angle aiding in both launching point inertial coordinate and local geographical coordinate systems, which converge to 1′ in 10 s. The method indicated that the integrated navigation significant errors derived from initial localization and initial attitude alignment could be modified by the strapdown inertial navigation system (SINS) supported by the star sensor’s celestial angle in the local geographic coordinate system in the early launch stage. For the seconds of the flight phase, the integrated navigation aided by celestial angles in the launching point inertial coordinate system was guaranteed for the feasibility and validity. During the flight, the feasibility and validity of integrated navigation were guaranteed aided by celestial angles in launching point inertial coordinate system.

show abstract