Design of a Near-Isentropic Supersonic Inlet Using Active Control

Ahsun, Umair; Merchant, Ali; Paduano, James D.; Drela, Mark

doi:10.2514/1.7709

Cited by 18 publications

(8 citation statements)

References 9 publications

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“…Note that, the results shown here in Figs. 3 to 10 are produced based on the nominal values of all parameters of the engine computed from CFD data using the relationships given by (10) and (11). The trajectory of the flight vehicle, which is obtained using (33), is shown in Fig.…”

Section: Simulation Resultsmentioning

confidence: 99%

“…7 that the fuel-air-ratio is within the maximum and minimum limits. Figure 8 shows the peak combustion temperature response, which is computed from (11), is within its maximum limit (2200 K). Also, it is shown from this figure that the flight path angle of the vehicle computed by the guidance design attains the desired flight path angle at the cruise phase (0 deg) and remains at the same correspond- ing value.…”

Section: Simulation Resultsmentioning

confidence: 99%

“…where,ṁ f is the fuel flow rate (in kg∕sec) which is another control input of the engine and T pk is the peak combustion temperature (in K). To manipulate the terms and parameters in (10) and (11) and to speed up the simulation runs, the Delaunay triangulation-based interpolation method is used here for acquiring data from the read up table. For the details of this interpolation algorithm and the computation of derivatives of the output terms with respect to the inputs used in this problem as well as the trim value calculation and chocking condition selection, one can refer to Sections II.B and II.C in [5], respectively.…”

Section: Engine Modelmentioning

confidence: 99%

“…Reference [6] has reported to control the shock-position by the variable nozzle against disturbances using the proportional integral (PI) control technique, where the rig-testing has been carried out to acquire the technique for detection of the shock-position with pressure transducers. In [9][10][11], the shock position control and the active control of the inlet using the proportional and proportional integral control techniques are discussed. In [12], the application of linear stochastic optimal control theory for the supersonic air-breathing inlet shock position control has been reported, in the presence of random airflow disturbances.…”

Section: Introductionmentioning

confidence: 99%

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Robust control design of an air‐breathing engine for a supersonic vehicle using backstepping and UKF

Maity

Padhi

2017

Asian Journal of Control

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This paper presents an efficient robust control design approach for an air‐breathing engine for a supersonic vehicle using the Lyapunov stability theory based nonlinear backstepping control, augmented with unscented Kalman filter (UKF). The primary objective of the control design is to ensure that the thrust produced by the engine tracks the commanded thrust by regulating the fuel flow to the combustion chamber. Moreover, as the engine operates in a supersonic range, an important secondary objective is to manage the shock wave location in the intake for maximum pressure recovery with adequate safety margin by varying the throat area of the nozzle simultaneously. To estimate the states and parameters as well as to filter out the process and sensor noises, a UKF has been incorporated for robust output feedback control computation. Furthermore, independent control designs for the actuators have been carried out to assure satisfactory performance of the engine. Additionally, a guidance loop is designed to generate a typical flight trajectory of the representative vehicle using a nonlinear suboptimal input constrained model predictive static programming formulation for testing the performance of the engine. Simulation results clearly indicate quite successful robust performance of the engine during both climb and cruise phases.

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Section: Simulation Resultsmentioning

confidence: 99%

Section: Simulation Resultsmentioning

confidence: 99%

Section: Engine Modelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Robust control design of an air‐breathing engine for a supersonic vehicle using backstepping and UKF

Maity

Padhi

2017

Asian Journal of Control

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“…Ref. [4] has presented the operation of the shock closer to the stability boundary for high inlet pressure recovery. For this operation, using the sensed shock location as feedback, the active control of the inlet computed by the proportional control technique has been applied to drive the shock bleed in order to keep the shock stable in the presence of compressor and atmospheric disturbances.…”

Section: Introductionmentioning

confidence: 99%