Name	Dr. Promio Charles F
Designation	Associate Professor
Qualification	Doctor of Philosophy (Aerospace Engineering) from Academy of Scientificand Innovative Research (AcSIR) (CSIR – National Aerospace Laboratories - Campus) M.Tech (Aeronautical Engineering) from Visvesvaraya Technological University – VTU
Area of   Specialization	Aeroelasticity and Structural Dynamics
Work Experience	Research-5.5 years; Industry- 1 year; Teaching- 5 Years
Date of Joining	05-06-2017
Awards & Achievements	University third Rank in M.Tech (VTU)

SUMMARY:

• Technically sophisticated and an innovative thinker with 6 years of research experience in the field of Aeroelasticity.

• Proficient in handling various subjects like Aeroelasticity, Aircraft structure, Finite Element Method, Structural Dynamics, Control Engineering, Aircraft Systems, Aerodynamics etc.

• Handled various software packages like ALTAIR-HYPERMESH, NASTRAN/ PATRAN, ZAERO, ANSYS, MATLAB, SIMULINK, ABAQUS, CATIA.

• Good experience in handling data acquisition software like LMS and dSPACE for full scale aircrafts.

• Involved in GVT based flutter prediction of full scale aircraft with different stores configuration for IAF.

INTERNATIONAL CONFERENCE

1. Charles, P. F., Raja, S. and Mahesh, M., (2014), “Influence of experimental mode shapes on unsteady aerodynamics in flutter prediction”, ICTACEM- 2014", IIT Kharagpur, India.

2. Promio Charles F, Raja Samikkannu, Ashwin Umesh, Niranjan K Sura, “Aerodynamic Force Injection through Smart Actuators”, Eighth ISSS- International Conference on Smart Materials, Structures & Systems, July 5-7, 2017, Indian Institute of Science, INDIA.

3. F. Promio Charles, C. Prakash, B. Venkatesh and G. Gowtham Reddy, "Dynamic Equivalent Load Simulation Using Smart Actuators," 2019 IEEE Aerospace Conference, Big Sky, MT, USA, 2019, pp. 1-7, doi: 10.1109/AERO.2019.8741994.

4. Promio Charles F, Deeksha K, Sathvik K, Rohith V and Manasa H R, Smart Actuators Based Transient Response Analysis, AIAA Scitech 2021 Forum. AIAA 2021-1317. January 2021, doi:10.2514/6.2021-1317

5. Promio Charles F, Pooja Bhat, Sushma V, Varalakshmi T S and Vedavathi G A, “Unsteady aerodynamic force approximation for flutter prediction”, ICTACEM- 2021", IIT Kharagpur, India.

JOURNAL

1. Promio Charles F., Raja Samikkannu, Niranjan K. Sura, Shanwaz Mulla, (2018) "System identification-based aeroelastic modelling for wing flutter", Aircraft Engineering and Aerospace Technology, Vol. 90 Issue: 2, pp.261-269, https://doi.org/10.1108/AEAT-08-2016-0122

RESEARCH AND INDUSTRY EXPERIENCE

• Name of Company: CSIR-National Aerospace Laboratories, Bangalore

• Period: December 2013 to May 2017

• Designation: Senior Project Fellow

• Name of Company: CSIR-National Aerospace Laboratories, Bangalore

• Period: April 2013 to December 2013

• Designation: Project Scientist

• Name of Company: CSIR-National Aerospace Laboratories, Bangalore

• Period: December 2011 – March 2013

• Designation: Project Assistant (Level – III)

• Name of Company: Bharath Earth Movers Limited (BEML), KGF

• Period: September 2008 – September 2009

• Designation: Graduate Engineering Trainee

ROLES AND RESPONSIBILITIES AS A RESEARCHER IN CSIR- NAL

1. Open loop Flutter Analysis using State Space approach

The Aerodynamic influence co-efficient matrix for each Mach number and reduced frequency pairs in modal domain were obtained. To the discrete airloads, Rogers’s rational polynomial approximation was used in transforming the discrete values to continuous form. Both the structural and continuous aerodynamic data was used in building aeroelastic state space system and hence solving open loop flutter analysis using in house MATLAB code. The open loop results were then validated with the NASTRAN results.

2. Gust response studies considering Vertical Gust

The Response of subsonic rectangular plate like aeroelastic wing due to Vertical gust was studied for each mode using MATLAB written code by approximating the unsteady aerodynamic forces extracted from NASTRAN and the gust response results obtained were validated with that of NASTRAN results. The two methods validated with that of NASTRAN values are:

• Transfer Function Approach using Roger’s rational polynomial approximation.

• State Space approach using Roger’s approximation and Hybrid approach.

3. GVT based Flutter prediction for rectangular Wing

The Mass normalized Eigen vectors at the sensor location were obtained from the experiment for each individual mode. The obtained coarse mesh Eigen vectors at sensor location were mapped onto fine-mesh structural data using Thin Plate Spline (TPS) technique and the Eigen vectors at each node and for each mode was obtained. To the splined Eigen vector, mode shape correction was done and the corrected Eigen vectors were used to obtain the flutter analysis in NASTRAN using Direct Matrix Input (DMI).

4. Static Electro Mechanical Analysis

Static electro-mechanical analysis was carried using MFC & PZT actuator on a rectangular cantilevered plate in ANSYS. Numerically an equivalent force model was developed for electro-mechanical coupling. The equivalent force was subsequently used in NASTRAN to validate the response behaviour with ANSYS results.

Ph.D. (Aerospace Engineering)

• AEROSERVOELASTIC SYSTEM MODELLING WITH ACTIVE CONTROL APPLICATIONS USING EXPERIMENTAL AND THEORETICAL METHODS

Location: CSIR- National Aerospace Laboratories

University: Academy of Scientific and Innovative Research

Duration: January 2014 to October 2021

Ground Vibration Testing (GVT) is a system identification technique, which can be used for extracting the structural parameters such as frequencies, mode shapes and damping for unknown aircraft structure. Further, these parameters may be used for predicting the flutter with an appropriate unsteady aerodynamics model. The present study has attempted to use a limited vibration measurements and curve fitting techniques, to build a suitable dynamic model in the numerical flutter analysis platform. As a validation of the approach, a reference FE model of known structure is built and the bending- torsion flutter analysis is performed. The same structure is subsequently fabricated and vibration experiment is conducted to get the mode shapes and frequencies. Thin Plate Spline (TPS) technique is adopted to interpolate the mode shapes from the discrete acceleration measurements, following the orthogonality principle by Modal Assurance Criteria (MAC). The interpolated and corrected mode shapes are subsequently employed to compute the unsteady aerodynamics, to carry out the GVT based flutter analysis in numerical domain. The sensitivity of mode shape amplitude and response measurement locations on flutter is evaluated.

The developed and validated hybrid flutter prediction method, involving GVT, numerical interpolation techniques, laser scanned CAD model and unsteady aerodynamic theories is extended to time domain aeroelastic analysis, exploiting discrete air load approximation technique in state space platform. This has facilitated to incorporate actuator system model and control law to perform the aeroservoelastic analysis. Numerically computed discrete unsteady air loads in frequency domain are transformed as continuous function in time domain by Roger’s rational polynomial and Matrix Polynomial Approximation (MPA). Both open and closed loop flutter analysis can thus be performed, accommodating experimental structural dynamics of unknown airframe in frequency as well as time domain. An interesting study is made to apply computationally obtained unsteady aerodynamic loads as a function of frequencies and velocities on the structure through modal shakers and distributed piezoelectric composite actuators. It is observed that nearing flutter velocity, the structure develops dynamic instability, if there is coupling between two modes. In a simple case study, the bending- torsion flutter of a cantilever plate wing is demonstrated using two modal shakers. Subsequently, this open loop flutter experiment is extended to a complex multibody dynamics system, namely the T-tail structure.

Aerodynamic force to actuator voltage relation is formulated and experimentally applied to inject the unsteady air loads in time domain through distributed Macro Fiber Composite (MFC) actuator, to conduct open loop flutter experiment on the fabricated T-tail structure. The complexity and limitation to use more number of modal shakers have overcome by using smart actuators. Further a novel flight flutter scheme is envisaged by exciting the target modes in a controlled manner using the MFC actuators in a closed loop vibration control environment. For this LQG controlled architecture is adopted in DSP platform and the first two elastic flutter critical modes of the T-tail are actively controlled. From the open loop flutter experiment, the response of the structure by injecting the equivalent aerodynamic loads through smart actuators is validated with respect to the response obtained by injecting the loads through modal shakers. The novelty of replacing the modal shakers with smart actuators have thus avoided the problems arising due to shaker dynamics and positioning multiple shakers. The proposed experimental flutter technique has got lot of promises in flutter certification and load augmentation studies of operational aircrafts during weapon integration programmes. Also this technique may be applied for the flutter qualification of UAV/ HALE/ MALE airframe,

1. On-ground under simulated airloads.

2. In-flight through flight flutter testing under controlled environment.

M.TECH PROJECT:

• FORMULATION AND ANALYSIS FOR GUST LOAD ALLEVIATION OF AEROELASTIC COMPOSITE WING

Location: Dynamics and Adaptive Structures Group, STTD, NAL

Duration: One year (June 2011 to June 2012)

The thesis work focuses on Gust load alleviation for aeroelastic wing represented by laminated composite panel. Numerical gust response studies were carried out using MSC/NASTRAN and state space approach in MATLAB. The generalized unsteady aerodynamic force coefficient matrices (QHH) and unsteady aerodynamic force vector due to gust (PDFX) along with structural matrices were generated using DMAP in NASTRAN. These matrices were taken into MATLAB environment, where the discrete unsteady aerodynamic coefficients of QHH and PDFX are transformed to Laplace domain to form a continuous function through Rational Polynomial Approximation (RPA) in order to build the Aeroservoelastic system. The dynamic analysis for the aeroelastic wing was validated with research literature. The open loop response of aeroelastic wing due to continuous (random) gust in frequency domain and discrete gust in time domain was studied using MSC/NASTRAN and MATLAB written code. The procedure for closed loop Aeroservoelastic system is developed for gust alleviation scheme.

B.E. PROJECT:

• DESIGN OF FUEL SYSTEM FOR AN AERO ENGINE TEST BED

Location: ETBR & DC, Engine Division, HAL

Duration: 4 months

The objective of the project was to design a hydraulic pump capacity based on the pipe dimensions, which supplies the fluid at the required flow rate and pressure at the exit and without altering it. The Fuel system setup for aero engine test bed has a fuel tank, pumping module, metering module and the emergency module. The entire setup has number of pipes, pressure gauges, bent tubes, flow meters etc. Based on the required exit fluid flow parameters, the losses in the entire fuel system setup was calculated for the four-inch pipe used and the Pump capacity to deliver the required output was identified and designed.

PROJECTS GUIDED:

1. Design and Analysis of Fish-Bot using smart actuators to implement motion mechanism for under water surveillance. (2018-2019)

2. Experimental and Numerical Investigation of Gust Response of a wing (2018-2019)

3. Modelling and Analysis of Morphed UAV wing using Smart Actuator (2020 – 2021)

4. Study of Stability parameters for tilt rotor Aircraft using CFD analysis and validation with Theoretical Calculations (2020 – 2021)

5. Unsteady aerodynamic force approximation for flutter prediction (2020 – 2021)

6. Aeroelastic Studies on Aircraft wing for varying store locations (2021 – 2022)

7. Dynamic Aeroelastic Studies of a delta-wing: Closed-loop Flutter Analysis (2021 – 2022)

8. Wind shield design qualification to resist the impact due to bird hit (2021 – 2022)

9. In-house tool development to carry out Modal Analysis and to determine the damping of the system (2021 – 2022)