A new transfer alignment of airborne weapons based on relative navigation

Si, Fan; Zhao, Yan; Lin, Yanghao; Zhang, Xueyan

doi:10.1016/j.measurement.2018.02.064

Cited by 15 publications

(12 citation statements)

References 15 publications

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“…Since the accuracy of gyroscope in the master INS is one or two orders of magnitude higher than that of the gyroscope in the slave INS, the measurement error of gyroscope in the master INS can be ignored (Liu et al., 2014; Si et al., 2018). If the measurement error of the gyroscope in the slave INS is modelled as the constant drift plus random drift, then Equation (24) can be simplified as …”

Section: Scheme and Realisation Of Innovative Transfer Alignmentmentioning

confidence: 99%

“…However, all these online identification methods of empirical model are derived on the premise that the dynamic angular deformation satisfies the Markov process. Since the dynamic angular deformation changes with the structural characteristics of carrier, external random interference and manoeuvre condition, it is difficult to accurately describe the dynamic angular deformation with a simple empirical model (Groves, 2003; Si et al., 2018). Therefore, the estimation method of relative misalignment angle based on the empirical model still reduces the accuracy of transfer alignment due to the model mismatch.…”

Section: Introductionmentioning

confidence: 99%

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A fast and accurate transfer alignment method without relying on the empirical model of angular deformation

Yang

Wang

Ding³

et al. 2022

J. Navigation

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This paper, in allusion to the limitations of traditional transfer alignment methods based on the external measurement equipment or the empirical model of angular deformation, proposes a rapid and accurate transfer alignment method without relying on the empirical angular deformation model. Firstly, the relationship between the actual angular deformation and the angular velocities measured by the gyroscopes in the master and slave inertial navigation systems (INSs) is derived to roughly estimate the angular deformation. Secondly, according to the error characteristics of gyroscopes, the error model of angular deformation is established. Thirdly, expanding the angular deformation error instead of the installation error angle, flexure angle and flexure angle rate into the state vector, a low-order transfer alignment filtering model independent of the empirical angular deformation model is established. The proposed method not only gets rid of the dependence on an empirical angular deformation model, but also realises the rapid and accurate initial alignment of the slave INS without adding any external measurement equipment. The simulations and experiments evidence the validity of the proposed transfer alignment method.

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Section: Scheme and Realisation Of Innovative Transfer Alignmentmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

A fast and accurate transfer alignment method without relying on the empirical model of angular deformation

Yang

Wang

Ding³

et al. 2022

J. Navigation

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“…Different acceleration patterns also correspond to different attenuation ability. Figure 7(d) replaces the sine function of (25) with other functions to show the RARVC and overall error attenuation in ( 26) and ( 27). For the sake of comparison, the maximum acceleration angle is 45 • and the frequency is 1 Hz.…”

Section: Acceleration Modulationmentioning

confidence: 99%

“…The alignment technology is based on the transfer model of carrier(high-precision master INS) to estimate the misalignment angle of load(lowprecision slave INS) under specific maneuver(acceleration or deceleration, s-maneuver, etc). The researches of alignment technology including matching methods [21,22] such as velocity or velocity-attitude matching, transfer errors suppression [23,24] for lever-arm effect and deformation vibration, observability of system state [25]. In curved electronic printing (figure 1), the base(stator) moves horizontally to ensure that the printing nozzle is consistent with the normal direction of substrate on rotor.…”

Section: Introductionmentioning

confidence: 99%

A transfer alignment method for inertial attitude correction of spherical motor on moving base

Dai¹,

Zhang²,

Mao³

et al. 2021

Meas. Sci. Technol.

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Inertial attitude measurement of spherical motor on moving base (SMMB) confronts the problems of unobservable azimuth and acceleration interference. This paper presents a transfer alignment method for inertial attitude correction of SMMB with specific exterior excitation. Because of the low friction torque of the spherical joint in the SMMB, the rotation is not able to be wholly transferred from base to rotor, which is required in the common method of velocity-attitude matching. With an explicit model about the acceleration transfer, the accumulation of unobservable error based on nominal-state is derived. Then the transfer alignment algorithm with innovation-based adaptive filter is proposed. The method brings external acceleration measurement into regular attitude estimation and adopts both estimation of unobservable error and acceleration transfer error into adaptive filter for the balance of azimuth correction and tilt error suppression. The simulation and analysis show that the method can correct the unobservable azimuth angle in high amplitude and frequency excitation as well as better tilt error suppression for transfer error with 20% uncertainty. The method is verified in a prototype platform.

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“…Zhu et al carried out a transfer alignment on a moving base for low-accuracy slave INS in projectiles, which utilized the output information of a high-accuracy master INS in the aircraft [13]. Si et al proposed a new transfer alignment method based on relative navigation [14], in which they solved the problem of a complicated and unknown wing flexure deformation influencing the traditional transfer alignment accuracy for airborne weapons. According to the aforementioned researches, it is obvious that the initial alignment method based on different filtering algorithms can meet the requirement of high accuracy, but it will take a relatively long time for the initial alignment to influence the responsiveness of the projectile’s weapon system.…”

Section: Introductionmentioning

confidence: 99%

Research on In-Flight Alignment for Micro Inertial Navigation System Based on Changing Acceleration using Exponential Function

Yun

Zhou

2018

Micromachines

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In order to guarantee the stable flight of a guided projectile, it is difficult to realize in-flight alignment for the micro inertial navigation system (MINS) during its short flight time. In this paper, a method based on changing acceleration using exponential function is proposed. First, double-vector observations were derived. Then the initial attitude for the guided projectiles was estimated by the regressive quaternion estimation (QUEST) algorithm. Further, the estimated errors were analyzed, and the reason for using the changing acceleration for the in-flight alignment was explained. A simulation and semi-physical experiment was performed to show the effectiveness of the proposed method. The results showed that the initial attitude error for the rolling angle was about 0.35°, the pitch angle was about 0.1° and the heading angle was about 0.6°, in which the initial shooting angle was between 15° and 55°. In future studies, the field experiments will be carried out to test the stability of the proposed in-flight alignment for guided projectiles.

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A new transfer alignment of airborne weapons based on relative navigation

Cited by 15 publications

References 15 publications

A fast and accurate transfer alignment method without relying on the empirical model of angular deformation

A fast and accurate transfer alignment method without relying on the empirical model of angular deformation

A transfer alignment method for inertial attitude correction of spherical motor on moving base

Research on In-Flight Alignment for Micro Inertial Navigation System Based on Changing Acceleration using Exponential Function

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