Flight Test Results of an Adaptive Guidance System for Reusable Launch Vehicles

Schierman, John D.; Gandhi, Neha; Hull, Jason R.; Ward, Dave

doi:10.2514/6.2004-4771

Cited by 10 publications

(11 citation statements)

References 8 publications

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“…Some of these techniques are computationally expensive and cannot be performed in realtime. A variation is to store optimization results generated by off-line optimization in a polynomial neural network, which can be accessed in real-time [94].…”

Section: Control Reconfigurationmentioning

confidence: 99%

Structural Technology Evaluation and Analysis Program (STEAP). Delivery Order 0037: Prognosis-Based Control Reconfiguration for an Aircraft with Faulty Actuator to Enable Performance in a Degraded State

Mahulkar¹

2010

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Section: Control Reconfigurationmentioning

confidence: 99%

Structural Technology Evaluation and Analysis Program (STEAP). Delivery Order 0037: Prognosis-Based Control Reconfiguration for an Aircraft with Faulty Actuator to Enable Performance in a Degraded State

Mahulkar¹

2010

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“…Recently, Barron associates flight tested an approach for this on the TIFS aircraft, which was being used to simulate an X-40 testbed [84]. The tested approach is shown in Fig.…”

Section: Beyond the Inner Loopmentioning

confidence: 99%

Historical Overview of Research in Reconfigurable Flight Control

Steinberg

2005

Proceedings of the Institution of Mechanical Engineers, Part G:

112

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This article presents a historical overview of research in reconfigurable flight control. For the purpose of this article, the term 'reconfigurable flight control' is used to refer to software algorithms designed specifically to compensate for failures or damage of flight control effectors or lifting surfaces, using the remaining effectors to generate compensating forces and moments. This article will discuss initial research and flight testing of approaches based on explicit fault detection, isolation, and estimation, as well as later approaches based on continuously adaptive and intelligent control algorithms. In addition, approaches for trajectory reshaping of an impaired aircraft with reconfigurable inner loop control laws will be briefly discussed. Finally, there will be some discussion on current implementations of reconfigurable control to improve safety on production and flight test aircraft and remaining challenges to enable broader use of the technology, such as the difficulties of flight certification of these types of approaches.

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“…4. Previous work involving the inner-loop control designs for the X-40A tested two different prefilter structures: implicit [4] and explicit [23]. For this work, an implicit modelfollowing scheme was selected based on its simplicity in regards to having fewer gains that would ultimately need tuning.…”

Section: B Model Following Prefiltersmentioning

confidence: 99%

“…The objective is to find a control law that provides direct control over ω such that For more details on this DI method and the control allocation algorithm see references [3]- [5] and [23]- [25]. A block diagram representation of the dynamic inversion control law is shown in Fig.…”

Section: A Dynamic Inversion and Control Allocationmentioning

confidence: 99%

“…From the optimal trajectory, the α and φ commands are converted into the body-axis angular velocities (P,Q,R) to provide the desired inner-loop commands. The generation of these commands is based on what Schierman defines as a "backstepping" approach whereby the "pseudo-commands" at each loop-closure, using PI-control and DI, drives the next inner-most loop [23]. Common loop closures may consist of an outer-most altitude loop, a FPA loop, and an enclosed inner-most AoA loop.…”

Section: B On-line Optimal Trajectory Generationmentioning

confidence: 99%

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Optimal Guidance Command Generation and Tracking for Reusable Launch Vehicle Reentry

Bollino

Oppenheimer

Doman

2006

AIAA Guidance, Navigation, and Control Conference and Exhibit

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The objective of this work is to develop a robust guidance and control architecture for autonomous reusable launch vehicles that incorporates elements of recent advances in the areas of optimal trajectory generation and reconfigurable control. This work integrates three separately developed methods to form a coherent architecture with the potential to manage control effector failures, vehicle structural/aerodynamic degradation, uncertainty, and external disturbances. Outer-loop guidance commands in the form of body-frame angular rates (roll, pitch, and yaw) are generated from an optimal reference trajectory that is computed off-line with a direct pseudospectral method and then tracked by a reconfigurable inner-loop control law. The appropriate open-loop state histories from the psuedo-four-degree-of-freedom reference trajectory are converted using a modified backstepping approach that complements the inner-loop control law in a six-degree-offreedom simulation. The inner-loop control law is capable of reacting and compensating for off-nominal conditions by employing nonlinear reconfigurable control allocation, dynamic inversion, and model-following/anti-windup prefilters. The results show that the inner-loop control can adequately track the desired optimal guidance commands; thus, confirming the applicability of this control architecture for future development involving on-line, optimal trajectory generation and high-fidelity guidance and control for reentry vehicles.

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Flight Test Results of an Adaptive Guidance System for Reusable Launch Vehicles

Cited by 10 publications

References 8 publications

Structural Technology Evaluation and Analysis Program (STEAP). Delivery Order 0037: Prognosis-Based Control Reconfiguration for an Aircraft with Faulty Actuator to Enable Performance in a Degraded State

Structural Technology Evaluation and Analysis Program (STEAP). Delivery Order 0037: Prognosis-Based Control Reconfiguration for an Aircraft with Faulty Actuator to Enable Performance in a Degraded State

Historical Overview of Research in Reconfigurable Flight Control

Optimal Guidance Command Generation and Tracking for Reusable Launch Vehicle Reentry

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