Integrated inertial network

Kelley, Ronald T.; Carlson, Neal A.; Berning, S.

doi:10.1109/plans.1994.303347

Cited by 20 publications

(7 citation statements)

References 1 publication

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“…Multisensor technology will provide the basis for the future generations of fault-tolerant navigation systems. 8 . In this architecture, inertial sensor systems are mounted at several locations in an aircraft, not only to meet the fault tolerance requirements of navigation systems, but also to provide accurate local inertial vector states for other systems, for example, weapon control systems and imaging sensors and to provide radar stabilization and motion compensation.…”

Section: F a U L T -T O L E R A N T N A V I G A T I O N S Y S T E M Smentioning

confidence: 99%

A Review of Multisensor Fusion Methodologies for Aircraft Navigation Systems

Allerton

Jia

2005

J. Navigation

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This paper reviews currently existing fault-tolerant navigation system architectures and data fusion methods used in the design and development of integrated aircraft navigation systems and also compares their advantages and disadvantages. Four fault-tolerant navigation system architectures are reviewed and the associated Kalman filter architectures and algorithms are discussed. These techniques have been used in most integrated aircraft navigation systems. The aim of this review paper is to provide a guide for navigation system designers to develop future aircraft multisensor navigation systems.

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Section: F a U L T -T O L E R A N T N A V I G A T I O N S Y S T E M Smentioning

confidence: 99%

A Review of Multisensor Fusion Methodologies for Aircraft Navigation Systems

Allerton

Jia

2005

J. Navigation

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“…However, the characteristics of the location error accumulate with time, making it difficult to work independently for a long time. Global Positioning System (GPS) can measure three-dimensional position and velocity accurately, but the disadvantage is susceptible to interference and control [3][4][5]. Therefore, INS and GPS have complementary characteristics.…”

Section: Introductionmentioning

confidence: 99%

A Preferable Airborne Integrated Navigation Method Based on INS and GPS

Zhang

Ning

2018

Journal of Sensors

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An integrated navigation method based on INS and GPS was proposed for airborne navigation. The influence of scale factor error and misalignment error of gyroscope and accelerometer on navigation accuracy was analyzed. Compared with traditional INS/GPS integrated navigation method, scale factor error and misalignment error were added to the state model of the integrated navigation system. The observability of scale factor error and misalignment error was analyzed combined with typical airborne movement. Then the integrated system was optimized, and the new navigation model of the integrated system was obtained. The optimized INS/GPS integrated model was validated by numerical simulation and turntable test. Comparing the proposed model with traditional integrated model (integrated system error states do not include scale factor error and misalignment error), the results showed that the proposed integrated navigation method can improve the accuracy from 8% to 28% of the east, north, and upward positions.

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“…However, since the flexures change depending on the payload, fuel level, speed and altitude of the aircraft, it is necessary to repeat the tests for all values of these parameters, which requires time and increased cost. The third subgroup of studies models the flexures as a linear function of aircraft specific forces (Groves et al, 2002; Kelley et al, 1994; Carlson et al, 1994). Groves et al (2002) related the angular flexures to aircraft specific forces, but they had to insert six additional states into the Kalman Filter (KF) in order to define the angular flexures.…”

Section: Introductionmentioning

confidence: 99%

“…Groves et al (2002) related the angular flexures to aircraft specific forces, but they had to insert six additional states into the Kalman Filter (KF) in order to define the angular flexures. Kelley et al (1994) and Carlson et al (1994) structured their flexure models based on the specific force-dependent flexure angles. They employed stochastic methods to establish flexure-specific force relationships.…”

Section: Introductionmentioning

confidence: 99%

Investigation of Flexure Effect on Transfer Alignment Performance

Pehlivanoğlu

Ercan

2012

J. Navigation

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Transfer Alignment (TA) is the initialisation process of the Inertial Navigation System (INS) of an air-launched weapon before its release by using the data from the aircraft INS. The aim of this paper is to improve the TA performance by taking into account the aircraft flexures deterministically. The developed procedure neither requires captive carry tests for determination of flexures nor increases the size of the problem, and can be used in real-time missions of any type of military aircraft. The procedure is evaluated for the Velocity Match (VM) method as well as the Velocity and Attitude Match (VAM) method, which are applied through a Kalman Filter (KF). Using a short-time Wing-Rock (WR) manoeuvre, the results of both methods are compared to each other for two cases in which either the flexures are taken into account deterministically, or modelled as noise by assuming that they are unknown. Standard deviations of the errors and the Circular Error Probable (CEP) variations have shown that the TA performance of the VAM method can be much improved if aircraft flexures are incorporated deterministically into the method. The improved performance makes possible target of opportunity missions at shorter weapon ranges, and it decreases target strike errors. K E Y WO R D S 1. Transfer Alignment (TA).2. Kalman Filter (KF). 3. Aircraft Flexure.

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Integrated inertial network

Cited by 20 publications

References 1 publication

A Review of Multisensor Fusion Methodologies for Aircraft Navigation Systems

A Review of Multisensor Fusion Methodologies for Aircraft Navigation Systems

A Preferable Airborne Integrated Navigation Method Based on INS and GPS

Investigation of Flexure Effect on Transfer Alignment Performance

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