Abstract
An issue of improving flight safety during landing with an inertial navigation system (INS) and a failed barometric altimeter is considered. In this paper, we propose a specific algorithm for in-flight calibration of the vertical channel of INS. Accordingly, the baro-inertial integration algorithm using a discrete five-state Kalman filter will be performed during a particular flight maneuver before landing. As a result, it is possible to estimate not only the bias of vertical accelerometer but also its scale factor, which is too small to be defined by a usual in-flight calibration algorithm. After applying the proposed algorithm, the flight management system can provide a safe landing with a standalone INS. The algorithm’s performance is assessed by simulating complete mathematical models of aircraft motion and control systems. The impact of calibrated bias and scale factor of vertical accelerometer on the altitude estimation error is provided through an analysis.
Highlights
Inertial navigation system (INS) is one of the most effective devices that provide an estimation of aircraft state to ensure the accuracy and safety of its motion
We introduce the relative calibration error calculated from the steady-state values of bias and scale factor, which are estimated by Kalman filter, in the form of: δx(%=) x − xtrue ⋅100%, (30)
Validity and performance of the proposed algorithm were assessed by simulations of flight dynamics and aerodynamic models of a passenger aircraft, and baro-inertial integration using Kalman filter and its associated models
Summary
Inertial navigation system (INS) is one of the most effective devices that provide an estimation of aircraft state to ensure the accuracy and safety of its motion. With a topographic map (Bevermeier et al, 2010) is included for compensating the BA bias caused by deviation of sea-level temperature and static pressure from their nominal values used in BA computation This leads to the use of a more complex structure of integration algorithm, which can be avoided by a suitable selection of measurement information from BA output, as done in this work. The main issue of these investigations is to provide a more stable and accurate altitude estimation with BA aiding For this purpose, it is sufficient to define only the accelerometer bias since the rest of its characteristics are quite small (for aviation-grade INS). In the event of BA failure, the altitude estimation is not exact enough to ensure the safety of
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