Flap configuration and control law

Ganguli, Ranjan and Thakkar, D and Viswamurthy, SR (2016) Flap configuration and control law. Advances in Industrial Control. pp. 81-101. ISSN 14309491

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Official URL: https://link.springer.com/chapter/10.1007%2F978-3-...


Preliminary results obtained in Chap. 3 indicate that multiple trailing-edge flaps have great potential in helicopter vibration control. However, the aerodynamic model used in that chapter did not include the unsteady effects due to the motion of trailing-edge flaps. Also, the effects of the rotor wake were captured using a simple linear inflow model. In this chapter, a two-dimensional unsteady aerodynamic model for a flapped airfoil in compressible, subsonic flow is used to calculate the incremental aerodynamic loads due to flap motion. The free wake model described is utilized to obtain the inflow distribution over the rotor disk. Also, in this chapter, a control algorithm based on optimal control theory is used to determine the flap control input. Sections 4.1 and 4.2 give brief description of the flap inertial and aerodynamic load calculations. The flap control algorithm is explained in Sect. 4.3. Section 4.4 provides a comparison of differential versus uniform weighting method. The effect of trailing-edge flap motion on the blade motion is discussed in Sect. 4.5 and its effect on the optimal location of flaps is examined in Sect. 4.6. In Sect. 4.7, trailing-edge flap actuation power is explained. Section 4.8 explains trailing-edge flap hinge loads. Section 4.9 considers the performance of the multiple-flap system in the event of failure of one or more flaps. Section 4.10 gives the summary of this chapter.

Item Type: Article
Subjects: AERONAUTICS > Aerodynamics
ENGINEERING > Electronics and Electrical Engineering
Depositing User: Mrs SK Pratibha
Date Deposited: 18 May 2022 15:58
Last Modified: 18 May 2022 15:58
URI: http://nal-ir.nal.res.in/id/eprint/12863

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