The Effects of Vertical Deflections on Aircraft Inertial Navigation Systems

Bernstein, Uri; Hess, Richard I.

doi:10.2514/3.61479

Cited by 12 publications

(7 citation statements)

References 4 publications

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“…In recent years, the increasing use of sensors connected to a GNSS/INS system has led to deep studies on the impact of the Earth’s actual gravity field [ 1 , 2 , 3 , 4 ].…”

Section: Introductionmentioning

confidence: 99%

Computing the Deflection of the Vertical for Improving Aerial Surveys: A Comparison between EGM2008 and ITALGEO05 Estimates

Barzaghi

Carrión

Pepe

et al. 2016

Sensors

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Recent studies on the influence of the anomalous gravity field in GNSS/INS applications have shown that neglecting the impact of the deflection of vertical in aerial surveys induces horizontal and vertical errors in the measurement of an object that is part of the observed scene; these errors can vary from a few tens of centimetres to over one meter. The works reported in the literature refer to vertical deflection values based on global geopotential model estimates. In this paper we compared this approach with the one based on local gravity data and collocation methods. In particular, denoted by ξ and η, the two mutually-perpendicular components of the deflection of the vertical vector (in the north and east directions, respectively), their values were computed by collocation in the framework of the Remove-Compute-Restore technique, applied to the gravity database used for estimating the ITALGEO05 geoid. Following this approach, these values have been computed at different altitudes that are relevant in aerial surveys. The (ξ, η) values were then also estimated using the high degree EGM2008 global geopotential model and compared with those obtained in the previous computation. The analysis of the differences between the two estimates has shown that the (ξ, η) global geopotential model estimate can be reliably used in aerial navigation applications that require the use of sensors connected to a GNSS/INS system only above a given height (e.g., 3000 m in this paper) that must be defined by simulations.

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“…In recent years, the increasing use of sensors connected to a GNSS/INS system has led to deep studies on the impact of the Earth’s actual gravity field [ 1 , 2 , 3 , 4 ].…”

Section: Introductionmentioning

confidence: 99%

Computing the Deflection of the Vertical for Improving Aerial Surveys: A Comparison between EGM2008 and ITALGEO05 Estimates

Barzaghi

Carrión

Pepe

et al. 2016

Sensors

View full text Add to dashboard Cite

show abstract

“…Because of the instability of INS’s vertical channel, five states are generally used to describe the error propagation of INS, including two horizontal velocity errors, and attitude errors. The state equation of KF is given in [ 22 ]:

where

is the system equation,

is the model noise vector, including measurement noise of accelerometers and measurement noise of gyroscopes.

…”

Section: The Effect Of Dov On Inertial Navigation Systemmentioning

confidence: 99%

“…In this subsection, simulations are used to verify the compensation effect of proposed methods in initial alignment. All inertial sensors exhibit noise from a number of sources [ 22 ] and the accuracy ranges of inertial sensors are set as Table 2 , which is a concise classification of accuracy given in [ 26 ]. Horizontal gravity disturbance has more significant effect on high-precision INS, and gravity disturbance compensation has little improvement on the accuracy of low- and medium-precision INS for the errors of inertial sensors being much larger than the horizontal gravity disturbance.…”

Section: Simulation and Shipborne Inertial Navigation Experimentsmentioning

confidence: 99%

Compensation of Horizontal Gravity Disturbances for High Precision Inertial Navigation

Tie

Cao

et al. 2018

Sensors

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Horizontal gravity disturbances are an important factor that affects the accuracy of inertial navigation systems in long-duration ship navigation. In this paper, from the perspective of the coordinate system and vector calculation, the effects of horizontal gravity disturbance on the initial alignment and navigation calculation are simultaneously analyzed. Horizontal gravity disturbances cause the navigation coordinate frame built in initial alignment to not be consistent with the navigation coordinate frame in which the navigation calculation is implemented. The mismatching of coordinate frame violates the vector calculation law, which will have an adverse effect on the precision of the inertial navigation system. To address this issue, two compensation methods suitable for two different navigation coordinate frames are proposed, one of the methods implements the compensation in velocity calculation, and the other does the compensation in attitude calculation. Finally, simulations and ship navigation experiments confirm the effectiveness of the proposed methods.

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“…At present, the study of ISEs is focused on the influence regularity of engine-cutoff state and impact-point in openloop conditions. Bernstein 12 developed a technique called autocorrelation function of surface gravity anomalies to predict aircraft navigation errors induced by deflection model uncertainties. Wang 13 derived the relationship between target position deviation and vertical deflection.…”

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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The Effects of Vertical Deflections on Aircraft Inertial Navigation Systems

Cited by 12 publications

References 4 publications

Computing the Deflection of the Vertical for Improving Aerial Surveys: A Comparison between EGM2008 and ITALGEO05 Estimates

Computing the Deflection of the Vertical for Improving Aerial Surveys: A Comparison between EGM2008 and ITALGEO05 Estimates

Compensation of Horizontal Gravity Disturbances for High Precision Inertial Navigation

Influence of Initial State Errors on Perturbation Guidance Accuracy

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