Gravity-model errors in mobile inertial-navigation systems

Kriegsman, B. A.; Mahar, K.

doi:10.2514/3.20108

Cited by 16 publications

(10 citation statements)

References 7 publications

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“…where the δ V is the velocity error of INS; n f is the specific force; Φ represents the misalignment angle of the ' mathematical platform'; n δ g is the gravity disturbance vector Considering that the inertial sensor is error-free, and the gravity disturbances are the only error source, the dynamics of the INS velocity error can be described as (2 ) (2 ) n n n n ie en n n ie en…”

Section: Error Modeling Of the Insmentioning

confidence: 99%

“…The dynamic of the velocity error defined in local level navigation frame(n-frame) is given by (2 ) (2 ) n n n ie en…”

Section: Error Modeling Of the Insmentioning

confidence: 99%

“…A traditional way of DOV compensation is to model the total gravity disturbances as low-order Gauss-Markov processes, and then estimate them online with the aid of GPS measurements [2][3] [5]. This method is considered to be lack of feasibility, because it is unable to decouple the longwavelength components of DOV from attitude errors, and the model parameters are hard to estimate without the prior knowledge of the local gravity disturbances [5].…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

An improved method for gravity disturbances compensation in INS/GPS integrated navigation

Dai

Wang

Zhan

et al. 2014

2014 12th International Conference on Signal Processing (ICSP)

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Though the gravity-induced velocity and position errors can be easily dumped in GPS/INS integrated navigation, the attitude estimation errors are more affected by the gravity disturbance errors. In this paper, an improved gravity disturbance compensation method is performed to reduce the gravity-induced attitude measurement error in inertial navigation system (INS) and global positioning system (GPS) integrated navigation. Specifically, the long and medium wavelength components of the gravity disturbance are compensated by using the EGM2008 global gravity model, and then a derivative second-order Gauss-Markov process is adopted as a statistical model of the short-wavelength components, which are estimated and removed online by a Kalman filter. Simulations results show that the proposed statistical model can decouple the short-wavelength components of gravity disturbances from the attitude errors. Therefore, the attitude errors are reduced effectively when the improved compensation method is applied.

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Section: Error Modeling Of the Insmentioning

confidence: 99%

“…The dynamic of the velocity error defined in local level navigation frame(n-frame) is given by (2 ) (2 ) n n n ie en…”

Section: Error Modeling Of the Insmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

An improved method for gravity disturbances compensation in INS/GPS integrated navigation

Dai

Wang

Zhan

et al. 2014

2014 12th International Conference on Signal Processing (ICSP)

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show abstract

“…A second-order Gauss-Markov process is usually utilized to model DOV disturbances (Kriegsman and Mahar, 1986;Leonard et al, 2013). However, the PSD of the model still has considerable gain in the lowfrequency domain.…”

Section: Dov Estimation Using Ins/gnss Attitude Error Observationmentioning

confidence: 99%

Dynamic measurement of high-frequency deflections of the vertical based on the observation of INS/GNSS integration attitude error

Dai

Wang

Zhan

et al. 2015

Journal of Applied Geophysics

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“…In current engineering applications, ISEs are ordinarily neglected in flight hardware. Conversely, instrument errors [4][5][6] and spatial disturbing gravity [7][8][9] have been extensively considered in many research papers. Vathsal 10 provided an error model of the strapped down inertial navigation system in the state space format.…”

Section: Introductionmentioning

confidence: 99%

Influence of Initial State Errors on Perturbation Guidance Accuracy

Jing

Gao

2019

Def. Sc. Jl.

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The inertial navigation system is aligned and leveled before the launch of a long-range vehicle. However, the initial state errors caused by the non-uniformity of the Earth can influence the parameters in flight dynamics, which will bring about serious uncertainty for the impact point of a long-range vehicle. Firstly, this paper analyses the influence mechanism of initial state errors on nominal trajectory, navigation trajectory and guidance trajectory. Then, a propagation model of engine-cutoff state deviation caused by initial state errors is derived under the condition of without-guidance. On this basis, an accuracy analytical solution of initial state errors on perturbation guidance is finally proposed to obtain the real impact-point of the long-range vehicle. In the simulations, the influence properties of initial state errors on perturbation guidance is analysed, give influence regularities of single initial state error, and obtain the statistical properties of engine-cutoff state deviations and impact-point deviation by Monte Carlo technique. From the simulation results, it seems that the navigation state tracks the nominal state. However, the real impact- point deviation has not been truly eliminated, instead of the almost target-hit deviation calculated by navigation output. The proposed analytical guidance accuracy model can be rapidly computed to provide a compensation for guidance and control system to improve hit accuracy.

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Gravity-model errors in mobile inertial-navigation systems

Cited by 16 publications

References 7 publications

An improved method for gravity disturbances compensation in INS/GPS integrated navigation

An improved method for gravity disturbances compensation in INS/GPS integrated navigation

Dynamic measurement of high-frequency deflections of the vertical based on the observation of INS/GNSS integration attitude error

Influence of Initial State Errors on Perturbation Guidance Accuracy

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