State Space Representation of the Open Loop Dynamics of the Space Shuttle Main Engine

Duyar, Ahmet; Elden, Vasfi; Merrill, Walter C.; Guo, Ten-Huei

doi:10.23919/acc.1991.4791769

Cited by 4 publications

(6 citation statements)

References 11 publications

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“…The damage mitigation concept is applied, via simulation, to the open loop control of a reusable rocket propulsion engine such as one described by Sutton 22 and Duyar et al 23 The plant model under control is a simplified representation of the dynamic characteristics of a bipropellant rocket engine as shown in Fig. 3.…”

Section: Simulation Results and Discussionmentioning

confidence: 99%

Damage-mitigating control of a reusable rocket engine

Ray

Dai

et al. 1994

Journal of Propulsion and Power

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This article presents a control concept for damage prediction and damage mitigation in reusable rocket engines for enhancement of structural durability. The key idea here is to achieve high performance without overstraining the mechanical structures so that 1) the functional lives of critical components are increased, resulting in enhanced safety, operational reliability, and availability; and 2) the plant (i.e., the rocket engine) can be inexpensively maintained, and safely and efficiently driven under different operating conditions. To this effect, dynamics of fatigue damage have been modeled in the continuous-time setting instead of the conventional cycle-based approach, and an optimal control policy is formulated by constraining the accumulated damage and its time derivative. Efficacy of the proposed damage mitigation concept is evaluated for life extension of the turbine blades of a bipropellant rocket engine via simulation experiments. The simulation results demonstrate the potential of increasing the structural durability of reusable rocket engines with no significant loss of performance.

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Section: Simulation Results and Discussionmentioning

confidence: 99%

Damage-mitigating control of a reusable rocket engine

Ray

Dai

et al. 1994

Journal of Propulsion and Power

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“…This paper is organized as follows: Section II presents the solution setup consisting of two dynamic systems: (1) a simplified linear state space model of the Space Shuttle Main Engine (SSME) 10 and (2) a fluid flow testbed. The state space model is simply used to discuss the traditional implementation of KF-SP-SCST-ARTMAP, whereas the testbed shows its application on a system for which we do not have a current model.…”

Section: Fammentioning

confidence: 99%

“…The state noise matrix, Γ(k) is given by a 4 × 4 identity matrix. In the literature, input and response plots have been provided for this system 10,11 , and here Fig. 1 presents another possible control sequence, with Fig.…”

Section: A Linearized State Space Modelmentioning

confidence: 99%

Predictive Fault Diagnosis System for Intelligent and Robust Health Monitoring

Oonk

Galindo

Figueroa

et al. 2012

Journal of Aerospace Computing, Information, and Communication

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This paper describes work related to the Predictive Fault Diagnosis System for Intelligent and Robust Health Monitoring, which exists as a solution to complete failure detection, identification, and prognostics (FDI&P) in health monitoring applications. Several advanced FDI analytical redundancy techniques have been applied for such a purpose, with the most notable being a compound method comprised of optimal filtering, statistical analysis, and neuro-fuzzy algorithms that is able to detect and diagnose both known and unknown failures. Although this scheme has been proven to be quite successful for systems that can be well described in a state space representation, current research has shown the viability in extending the process to highly complex systems with considerable nonlinearities while still maintaining the FDI capabilities. This paper highlights the utility of these algorithms for determining failures in (1) a known reusable liquid rocket engine model and (2) an unknown input-output relation in a fluid flow testbed. Other research has focused on prognostic capabilities provided by a neural architecture enhanced with fuzzy logic using rule-based knowledge. An example of using data to construct fuzzy rules for determining the remaining useful life of components is provided to give insight into the process.

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“…It is assumed that the system described by equations 3and 4is stable and observable and the C matrix has full row rank. Furthermore, this system is realized in a-canonical form developed in [7] and [12], i.e., the following relations hold:…”

Section: Elmentioning

confidence: 99%

“…This approach was successfully applied to obtain simplified models for control and diagnostics design in other propulsion systems, for example [6]. Linearized dynamic models of the engine at five different operating conditions were obtained by using a multivariable system identification and realization technique [7] with the input and output data generated from the nonlinear simulation described in [1]. The simplified model, covering the whole range of operation of the engine, was then developed by combining the point models.…”

Section: Introductionmentioning

confidence: 99%

A Simplified Dynamic Model of the T700 Turboshaft Engine

Duyar

Litt

1995

j am helicopter soc

Self Cite

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A simplified open-loop dynamic model of the T700 turboshaft engine, valid within the normal operating range of the engine, is developed. This model is obtained by linking linear state space models obtained at different engine operating points. Each linear model is developed from a detailed nonlinear engine simulation using a multivariable system identification and realization method. The simplified model may be used with a model-based real time diagnostic scheme for fault detection and diagnostics, as well as for open loop engine dynamics studies and closed loop control analysis utilizing a user generated control law. Nomenclature Variables 'This work was supported by the U.S. Army under grant number NAG3-1198. 14. SUBJECT TERMS 15. NUMBER OF PAGES Real-time simulator; Helicopter engines; Mathematical models 16. PRICE CODE A03 17. SECURITY CLASSIFICATION 18. SECURITY CLASSIFICATION 19. SECURITY CLASSIFICATION 20. LIMITATION OF ABSTRACT OF REPORT OF THIS PAGE OF ABSTRACT Unclassified Unclassified Unclassified NSN 7540-01-280-5500 Standard Form 298 (Rev. 2-89) Prescribed by ANSI Sid Z39-18 298-102

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State Space Representation of the Open Loop Dynamics of the Space Shuttle Main Engine

Cited by 4 publications

References 11 publications

Damage-mitigating control of a reusable rocket engine

Damage-mitigating control of a reusable rocket engine

Predictive Fault Diagnosis System for Intelligent and Robust Health Monitoring

A Simplified Dynamic Model of the T700 Turboshaft Engine

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