In this paper a general approach for modelling structured real-valued parametric perturbations is presented. It based on decomposition of into linear fractional transformations (LFTs), and applicable to rational multi-dimensional (ND) polynomial entries in state-space models. Model reduction used reduce the size uncertainty structure. The procedure will be applied an aircraft model depending altitude velocity (flight envelope).

Polynomial chaos and Gaussian process emulation are methods for surrogate-based uncertainty quantification have been developed independently in their respective communities over the last 25 years. Despite tackling similar problems field, to our knowledge there has yet be a critical comparison of two approaches literature. We begin by providing detailed description polynomial building surrogate model black-box function. The accuracy each method is then tested compared simulators used...

The sizing and capability definitions of reusable launchers during high-speed recovery are very challenging problems. In this paper, a convex optimization guidance algorithm for type system is proposed, based on performance improvements arising from the study coupled flight mechanics, guidance, control problem. To appreciate obtained improvements, tradeoff analyses powered descent landing scenarios presented first using traditional techniques. Subsequently, these results refined by proposed...

ABSTRACT Monte Carlo simulations have long been a widely used method in the industry for control system validation. They provide an accurate probability measure sufficiently frequent phenomena but are often time‐consuming and may fail to detect very rare events. Conversely, deterministic techniques such as or IQC‐based analysis allow fast calculation of worst‐case stability margins performance levels, absence probabilistic framework, be invalidated on basis extremely Probabilistic ‐analysis...

This paper investigates the application of Incremental Nonlinear Dynamic Inversion (INDI) for launch vehicle flight control, addressing limited exploration nonlinear control architectures and their potential benefits in context current “New Space” era. In this context, study aims to bridge gap between launcher’s traditional linear practice methods, focusing on INDI, which offers enhance limits performance while reducing mission preparation (“missionisation”) efforts. INDI commands...

This paper studies the mechanics of reusable retropropelled flight slender low lift-to-drag bodies via integrated guidance and control simulations. To do this, a simulation benchmark focused on coupling between mechanics, guidance, must be developed, as opposed to mission-optimization-oriented ones that simplify (or directly ignore) these couplings. The developed simulator covers vertical takeoff landing first-stage booster for return launch site downrange missions. steer it toward...

Using the structured singular value , an independent control law assessment is presented for Vega launcher thrust vector system. A systematic uncertainty modeling and analysis process illustrated to retrieve structure driving perturbation combinations affecting competing system design requirements. It demonstrated how not only complements generalizes classical frequency-domain stability assessments but also it applies naturally as a performance indicator manage requirements tradeoff space....

Summary This paper deals with the development of a mixed active‐passive microvibration mitigation solution capable attenuating transmitted vibrations generated by reaction wheels to satellite structure. A dedicated simulation environment, provided European Space Agency and Airbus Defence industries, serves as support for testing proposed at level. covers modeling, control system design, worst‐case analysis typical observation mission that requires high pointing stability. Combined novel...

Modern space-observation missions demand stringent pointing requirements that motivated a significant amount of research on the topic microvibration isolation and line-of-sight stabilization systems. While disturbances can be reduced by mounting some noisy equipment various platforms, residual vibrations still propagate through amplified flexible structure spacecraft. In order to alleviate these issues, line sight must also actively controlled at payload level. However, such systems...

Robust tube-based model predictive control (MPC) methods address constraint satisfaction by leveraging an a priori determined tube controller in the prediction to tighten constraints. This paper presents system level tube-MPC (SLTMPC) method derived from parameterization (SLP), which allows optimization over online when solving MPC problem, can significantly reduce conservativeness. We derive SLTMPC establishing equivalence relation between class of robust and SLP. Finally, we show that...

LISA Pathfinder is a technology satellite project that currently in full implementation phase, with launch date scheduled for 2010. One of the key technologies to be tested drag-free control system. It consists two cubic test masses measurement and actuation provisions along all degrees freedom. In total, 15 freedom must controlled such differential free-fall requirement between met. this paper design approach revisited requirements breakdown discussed, based on equation. Then emphasis put...

Linear parameter varying theory has been in the control community for last 15 years but its use space systems limited due to slow transfer of these techniques industry and a lack reliable commercial software tools. This article summarizes some efforts made Europe change situation serves as an assessment on advantages, limitations needs LPV modeling, analysis design systems. A comparative application between LTI, gain scheduling designs representative model re-entry vehicle is used support assessment.

Future safety critical space missions call for increasing levels of embedded spacecraft autonomy. Spacecraft and mission responsiveness will be highly improved via onboard automation autonomy functions, simplifying operations ground control capabilities. Recently developed real-time MPC guidance strategies have a great potential the next generation high performance reusable ESA launch vehicles GNC systems. This paper addresses these technologies covering thrust vectored that could...

Summary This paper presents a systematic robust control framework based on the structured approach to address synthesis of atmospheric ascent‐flight system launch vehicle. To introduce this framework, problem is first formulated recover classically designed baseline rigid‐body controller actual VEGA launcher VV05 mission. legacy recovery builds necessary background for good understanding and increases confidence its transfer Space industry. Subsequently, it shown how systematically augment...

In this paper the application of linear parameter varying (LPV) modeling, design and analysis methods to a re-entry vehicle is presented. The selected atmospheric benchmark includes full nonlinear motion, detailed aerodynamic database (from hypersonic subsonic), relevant actuator sensor models physically-meaningful parametric uncertainty profiles. results show that: (i) LPV controller can solve gain-scheduling problems in very effective manner, (ii) integral quadratic constraint (IQC) be...

An approach to the control of linear parametrically varying systems that takes rate parameter variations intoaccountandalsoguaranteesrobustnessagainstparametricanddynamicuncertaintiesisdiscussed.Toillustrate technique we consider a missile problem has been extensively studied in literature. Nonlinear simulations show proposed method is successful achieving desired performance and robustness goals.