GPS Based Attitude Determination for the Flying Laptop Satellite

Hauschild, André; Grillmayer, Georg; Montenbruck, Oliver; Markgraf, Markus; Vörsmann, Peter

doi:10.1007/978-1-4020-6943-7_19

Cited by 23 publications

(15 citation statements)

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“…Several of them make use of the popular LAMBDA method, see e.g. Peng et al (1999), Furuno (2003), Lin et al (2004), Monikes et al (2005), Kuylen et al (2006), Hauschild and Montenbruck (2007), Hauschild et al (2008), Wang et al (2009a, b), as this method is known to be efficient and known to maximize the ambiguity success rate (Teunissen 1995(Teunissen , 1999Verhagen and Teunissen 2006). However, the standard LAMBDA method has been developed for unconstrained and/or linearly constrained GNSS models.…”

Section: Introductionmentioning

confidence: 99%

Testing of a new single-frequency GNSS carrier phase attitude determination method: land, ship and aircraft experiments

2010

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Global navigation satellite system (GNSS) ambiguity resolution is the process of resolving the unknown cycle ambiguities of the carrier phase data as integers. The sole purpose of ambiguity resolution is to use the integer ambiguity constraints as a means of improving significantly on the precision of the remaining GNSS model parameters. In this contribution, we consider the problem of ambiguity resolution for GNSS attitude determination. We analyse the performance of a new ambiguity resolution method for GNSS attitude determination. As it will be shown, this method provides a numerically efficient, highly reliable and robust solution of the nonlinearly constrained integer least-squares GNSS compass estimators. The analyses have been done by means of a unique set of extensive experimental tests, using simulated as well as actual GNSS data and using receivers of different manufacturers and type as well as different platforms. The executed field tests cover two static land experiments, one in the Netherlands and one in Australia, and two dynamic experiments, a low-dynamics vessel experiment and high-dynamics aircraft experiment. In our analyses, we focus on stand-alone, unaided, single-frequency, singleepoch attitude determination, as this is the most challenging case of GNSS compass processing.

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Section: Introductionmentioning

confidence: 99%

Testing of a new single-frequency GNSS carrier phase attitude determination method: land, ship and aircraft experiments

2010

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“…They first use the baseline length constraint to obtain an improved float solution and then use the standard LAMBDA method to solve for the integer ambiguities as in (9). Also in Dai et al (2004), Kuylen et al (2005), Hauschild and Montenbruck (2007), and Hauschild et al (2008), the standard LAMBDA method is used. Although good results are reported, the baseline constraints are still not used to their fullest.…”

Section: Other Ambiguity Objective Functionsmentioning

confidence: 99%

“…Several of them make use of the LAMBDA method (see e.g. Furuno 2003; Lin et al 2004;Monikes et al 2005;Kuylen et al 2006;Hauschild et al 2008;Wang et al 2009a). This method is known to be efficient and known to maximize the ambiguity success rate (Teunissen 1995(Teunissen , 1999.…”

Section: Introductionmentioning

confidence: 99%

Integer least-squares theory for the GNSS compass

Teunissen

2010

J Geod

154

134

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Global navigation satellite system (GNSS) carrier phase integer ambiguity resolution is the key to highprecision positioning and attitude determination. In this contribution, we develop new integer least-squares (ILS) theory for the GNSS compass model, together with efficient integer search strategies. It extends current unconstrained ILS theory to the nonlinearly constrained case, an extension that is particularly suited for precise attitude determination. As opposed to current practice, our method does proper justice to the a priori given information. The nonlinear baseline constraint is fully integrated into the ambiguity objective function, thereby receiving a proper weighting in its minimization and providing guidance for the integer search. Different search strategies are developed to compute exact and approximate solutions of the nonlinear constrained ILS problem. Their applicability depends on the strength of the GNSS model and on the length of the baseline. Two of the presented search strategies, a global and a local one, are based on the use of an ellipsoidal search space. This has the advantage that standard methods can be applied. The global ellipsoidal search strategy is applicable to GNSS models of sufficient strength, while the local ellipsoidal search strategy is applicable to models for which the baseline lengths are not too small. We also develop search strategies for the most challenging case, namely when the curvature of the non-ellipsoidal ambiguity search space needs to be taken into account. Two P. J. G. Teunissen Department of Spatial Sciences, Curtin University of Technology, Perth, Australia e-mail: p.teunissen@curtin.edu.au P. J. G. Teunissen (B) Delft Institute for Earth Observation and Space Systems (DEOS), Delft University of Technology, Delft, The Netherlands e-mail: p.j.g.teunissen@tudelft.nl such strategies are presented, an approximate one and a rigorous, somewhat more complex, one. The approximate one is applicable when the fixed baseline variance matrix is close to diagonal. Both methods make use of a search and shrink strategy. The rigorous solution is efficiently obtained by means of a search and shrink strategy that uses nonquadratic, but easy-to-evaluate, bounding functions of the ambiguity objective function. The theory presented is generally valid and it is not restricted to any particular GNSS or combination of GNSSs. Its general applicability also applies to the measurement scenarios (e.g. single-epoch vs. multiepoch, or single-frequency vs. multi-frequency). In particular it is applicable to the most challenging case of unaided, single frequency, single epoch GNSS attitude determination. The success rate performance of the different methods is also illustrated.

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“…In order to direct the sensors to the ground in comparison with sweeping the earth's surface, such earth observation satellites need to improve their agility in large-angle attitude maneuvers. Moreover, methods that enable highly accurate attitude determination by online sensors such as the star tracker (ST) and inertial measurement unit (IMU), as well as global positioning system (GPS) based methods [1,2] have been proposed. Thus, high accuracy of attitude control is also needed using this information.…”

Section: Introductionmentioning

confidence: 99%

Agile Attitude Control and Singularity Avoidance/Escape by the SDRE Method Using a Biased State-Dependent Weighting Matrix

Ozawa

Takahashi

2018

Applied Sciences

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Abstract:In recent years there has been an increasing need to improve satellite attitude control performance in terms of agility and attitude accuracy in large-angle attitude maneuvers. To achieve such control performance, single-gimbal control moment gyros (SGCMGs) should be mounted as modern-type actuators. Conventionally, based on the torque command calculated by the attitude control system of the satellite, SGCMGs were controlled by solving inverse kinematics through a pseudo inverse matrix steering law. However, in such a control system structure, it may be difficult to obtain the desired torque required by the attitude control system because of the singularity problem of SGCMGs. Furthermore, with respect to implementation, since the condition number of the Jacobian matrix of SGCMG becomes extremely large in the singularity, the numerical calculation error of the pseudo inverse matrix increases greatly. Therefore, we propose an overall control system that can solve above-described problems and the state-dependent Riccati equation (SDRE) control system that integrates the satellite and SGCMG system. The proposed optimal control system, which does not solve the pseudo inverse matrix, can realize gimbal angle guidance by gimbal angle feedback and singularity avoidance/escape using the biased weighting matrix. In the numerical simulation, the usefulness of proposed system is shown in comparison with the conventional system.

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GPS Based Attitude Determination for the Flying Laptop Satellite

Cited by 23 publications

References 1 publication

Testing of a new single-frequency GNSS carrier phase attitude determination method: land, ship and aircraft experiments

Testing of a new single-frequency GNSS carrier phase attitude determination method: land, ship and aircraft experiments

Integer least-squares theory for the GNSS compass

Agile Attitude Control and Singularity Avoidance/Escape by the SDRE Method Using a Biased State-Dependent Weighting Matrix

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