Atmospheric Re-Entry Ndi Control Design for the Hopper RLV Concept

Marcos, Andrés; Peñín, Luis F.; Caramagno, Augusto; Sommer, Josef; Belau, Wolfgang

doi:10.3182/20070625-5-fr-2916.00134

Cited by 9 publications

(13 citation statements)

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“…Full details of the uncertainty sources considered are provided in Ref. 1. They can be summarized as:…”

Section: Fdi Design Problem and Objectivesmentioning

confidence: 99%

“…In the study, a high fidelity nonlinear model of the EADS Astrium Hopper RLV was employed as the vehicle benchmark, with nonlinear dynamic inversion (NDI) control providing a robust vehicle response during unfaulted vehicle operation. 1 In the HMS study faults were considered at several levels within the Hopper RLV and GNC system. This work considers faults acting at the GNC level, with faults active on both the sensors and actuators of the vehicle.…”

Section: Introductionmentioning

confidence: 99%

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Development and Testing of a GNC-FDI Filter for a Reusable Launch Vehicle during Ascent

Kerr¹,

Marcos²,

Peñín³

et al. 2010

AIAA Guidance, Navigation, and Control Conference

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This paper presents the design process and evaluation of a GNC fault detection and isolation (GNC-FDI) filter for the provision of health monitoring capabilities on a reusable launch vehicle (RLV) during ascent. A high fidelity nonlinear model of the Hopper RLV forms the basis of the vehicle benchmark, with NDI control providing a robust vehicle response during unfaulted vehicle operation. Two faults and a variety of fault dynamics are considered; faults in the central engine gimbal actuator and the yaw rate sensor. A robust FDI filter design procedure is developed based on H-infinity FDI theory. Scheduling of designed LTI filters is employed to overcome the variation inherent in the vehicle's dynamical characteristics during ascent. A key feature of the developed design process is that FDI filters are designed in open-loop, despite the vehicle dynamics varying between stable and unstable during the ascent. Monte-Carlo analysis performed using nonlinear simulations demonstrates the robustness and effectiveness of the proposed FDI approach.Nomenclature d = Disturbance f = Generic fault f s = Sensor fault f a = Actuator fault fˆ, res = Fault estimate F = FDI filter F Y ,F U = FDI filter subelements G = Generic vehicle model G u = Vehicle model element accepting plant input G d = Vehicle model element accepting disturbance input G f = Vehicle model element accepting fault input a K , s K = Fault location selectors n = Noise u = Plant input y = Plant output

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“…Full details of the uncertainty sources considered are provided in Ref. 1. They can be summarized as:…”

Section: Fdi Design Problem and Objectivesmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Development and Testing of a GNC-FDI Filter for a Reusable Launch Vehicle during Ascent

Kerr¹,

Marcos²,

Peñín³

et al. 2010

AIAA Guidance, Navigation, and Control Conference

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“…The PID gain sets are scheduled on Mach and dynamic pressure reflecting the varying dynamics of the Hopper vehicle and mission. This component is taken, without modification or gain re-tuning, from the Hopper re-entry control design, see [10] for further details.…”

Section: A Pid-plus-rotational-eom-inversion Componentmentioning

confidence: 99%

“…The first need arises from programmatic time and cost issues, while the second is the result of a desire to have wide fault coverage: from incipient faults (not detectable with very robust/FTC G&C designs [9]) to hard/strong faults (which, without a G&C providing some closed-loop FTC properties, result in almost immediately closed-loop instability impeding FDI assessment and verification). In [10] the re-entry control design for the HMS project is presented, it uses a mixed wind-body formulation for the atmospheric re-entry vehicle but no outer-loop guidance (i.e. trajectory control) yielding acceptable results albeit with some robustness issues (i.e.…”

Section: Introductionmentioning

confidence: 99%

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Guidance and Control Design for the Ascent Phase of the Hopper RLV

Marcos¹,

Peñín²,

Sommer³

et al. 2008

AIAA Guidance, Navigation and Control Conference and Exhibit

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In this article the design of a guidance and control system for the automated ascent of the Hopper reusable launch vehicle is presented. The considered ascent starts at the pull-up maneuver performed immediately after horizontal take off and ends near main-engine-cutoff. The guidance (trajectory control) law is based on the coupled inversion of flight-path-toangle-of-attack and heading-to-bank-angle dynamics. The control (attitude) law uses also nonlinear dynamic inversion to obtain the required aerodynamic surfaces and engine gimbal deflections for robust tracking of the attitude angles from the guidance law. The used NDI attitude law is inherited from a previous design for the Hopper re-entry phase (with only minor modifications apart from the inclusion of thrust vector control) showcasing the reusability of NDI designs for quite different types of configurations. The resulting design has been validated using a Monte Carlo campaign with realistic aerodynamic mismatch, corrupted measurements, parametric uncertainty and high fidelity atmospheric and 6DoF vehicle dynamics models. NomenclatureAngle of attack,

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