AE Brown Bag Seminar

 

Friday, April 4

11:00 a.m. - 1:00 p.m.

Guggenheim 442

Pizza Served

 

 

Miral Alabady

Suhanna Bamzai

Tushar Bansal

Anika Chawla

Nicholas Gaug

Patrick Holstine

Matthew Kerner

Brian Gonzalez

 

Miral Alabady

Title:

Learning SysML and Modeling the Space Shuttle

Abstract:

This presentation outlines the learning of Model-Based Systems Engineering (MBSE) and SysML through structured tutorials and applied exercise modules. Key concepts and modeling techniques will be highlighted, culminating in the development of a SysML model for the Space Shuttle, with a particular focus on the Solid Rocket Boosters (SRBs). The model incorporates parametric equations to evaluate critical performance parameters. This presentation demonstrates the application of MBSE methodologies to aerospace system modeling and analysis, showcasing both the learning process and final implementation.

Faculty advisor: 

Dr. Selcuk Cimtalay

Suhanna Bamzai

Title:

Whirl Flutter Prediction

Abstract:

Whirl flutter is an aeroelastic instability that poses significant challenges in the design and operation of tiltrotor aircraft. This project focuses on applying the matrix pencil method—a time-domain system identification technique—to experimental data from a whirl flutter test campaign conducted by the University of Maryland. The work builds on recent efforts to evaluate time history-based approaches for whirl flutter prediction and contributes to ongoing validation of their effectiveness in practical test settings. Specifically, the study involves gaining familiarity with whirl flutter prediction methods and reproducing results from the UMD team using traditional frequency-domain techniques. This work aims to advance the prediction and prevention of whirl flutter in rotorcraft systems.

Faculty advisor: 

Professor Cristina Riso

Tushar Bansal

Title:

Modeling & Simulation Support for a GA Turboprop

Abstract:

Advances in modeling and simulation capabilities in the aerospace industry are forcing startups, even within the general aviation sector, to develop more advanced models to simulate the performance of their vehicles. Centauri Aircraft is one such company, working to develop their aircraft to provide a high-end GA product. This project aims to develop a calibrated model of the Centauri Valkyrie aircraft, replicating its current performance and with the capability of predicting its performance with alternative engines and configurations. Component models have been developed using engine manuals, AVL, and proprietary software to predict aerodynamic and propulsive performance accurately. These are being combined in AVIARY and calibrated to Centauri's flight test data.

Faculty advisor: 

Dr. Christian Perron

Anika Chawla

Title:

Using SysML/MBSE for Streamlined Engine Design and Development

Abstract:

As the demand for cost-effective and rapid space exploration grows, engineers aim to reduce engine development budgets and timelines by half over the next decade. Achieving this goal requires a shift in focus toward the preliminary design phase, where proper requirement development, tracking, and verification play a crucial role. Model-Based Systems Engineering (MBSE) through SysML provides a structured framework for conceptualizing designs, streamlining requirement management, and performing parametric analyses with lower complexity.By leveraging MBSE, engineers can systematically explore the vast design space of rocket engines, including chamber geometry, nozzle characteristics, and injector configurations. This approach enables efficient trade studies, reduces late-stage design failures, and minimizes costly testing iterations. Investing in MBSE-driven preliminary design allows for a more rigorous and optimized development process, ultimately accelerating innovation in space propulsion while reducing costs and development time.

Faculty advisor: 

Dr. Selcuk Cimtalay

Nicholas Gaug

Title:

Modelling the Passive Attitude Dynamics and Orbit Lifetime of Drag Sail Vehicles 

Abstract:

Space debris is an increasing threat to current and future satellites, and has generated interest in active debris removal technologies. Of particular interest is the removal of large, uncontrolled pieces of debris. One concept for active debris removal is a guided net intercept vehicle, which deploys a drag sail to expedite the deorbit process using atmospheric drag. In order to study the orbital lifetime of a given drag sail configuration, higher fidelity orbit lifetime assessment is needed that what can be achieved using a constant drag area assumption. Additionally, knowledge of the drag sail vehicle’s attitude behavior, particularly if it stabilizes in a fixed orientation over time, is desired in order to assess the feasibility of adding propulsive assistance. To analyze passive drag sail behavior in earth orbit, analytical gas surface interaction models were used to model the forces and  moments caused by the rarified flow interacting with the vehicle. 3D geometries were created, and the ray tracing panel method and GSI model were used to create a database of aerodynamic coefficients as a function of orientation, altitude, velocity, temperature, and accommodation coefficient. Then, a framework for integrating this aerodynamic database with an orbit propagation using STK was developed. This framework allows for coupled orbit-attitude simulation over the entire orbit lifetime of dragsail/debris configurations.

Faculty advisor: 

Professor Dimitri Mavris

Patrick Holstine

Title:

Creation of a Manipulated Flow Pattern Measurement System

Abstract:

This experiment investigated the development of a manipulated flow pattern measurement system and evaluated its performance in detecting disturbances. The objective was to create a repeatable and reusable setup capable of identifying and measuring variations in airflow caused by upstream airflow manipulators. Testing was conducted using custom-designed 3D prints to disturb flow within a low-turbulence wind tunnel. Data collected from these tests was analyzed and organized to highlight the flow distortions captured by the system. The report describes the process of manufacturing both the measurement system and manipulator devices, as well as discussing their efficacy in creating and measuring unique flow conditions that otherwise could not be created within a wind tunnel.

Faculty advisor: 

Professor Sedina Tsikata

Matthew Kerner

Title:

Creation of a Manipulated Flow Pattern Measurement System

Abstract:

This experiment investigated the development of a manipulated flow pattern measurement system and evaluated its performance in detecting disturbances. The objective was to create a repeatable and reusable setup capable of identifying and measuring variations in airflow caused by upstream airflow manipulators. Testing was conducted using custom-designed 3D prints to disturb flow within a low-turbulence wind tunnel. Data collected from these tests was analyzed and organized to highlight the flow distortions captured by the system. The report describes the process of manufacturing both the measurement system and manipulator devices, as well as discussing their efficacy in creating and measuring unique flow conditions that otherwise could not be created within a wind tunnel.

Faculty advisor: 

Professor Sedina Tsikata

Brian Gonzalez

Title:

Rocket Propellent Slosh Damping Characterization

Abstract:

The importance of propellant sloshing in the operation of space vehicles has been recognized since the early days of space exploration. Sloshing can induce undesired fluid-structure interactions and affect system dynamics, potentially leading to mission failure. Modeling and mitigating this effect is, therefore, an essential component of launch vehicle design. Both the fundamental and applied aspects of the problem have been studied since the 1960s, and computer programs have been developed to assist in the early phases of design. However, these tools are now often outdated, not readily accessible, or difficult to operate for non-specialized users. SLOSH-ML, an open-source MATLAB graphical user interface that implements and expands upon previously developed axisymmetric tank sloshing algorithms, provides pendulum and spring-mass equivalent mechanical analogies for axisymmetric tanks of arbitrary shape, accommodating variable fill ratios and acceleration levels. One crucial parameter that SLOSH-ML is in the process of fully including is the damping ratio of the system. Although analytical results are available for the modal shapes and frequencies of cylindrical, spherical, and spheroidal tanks, damping ratios are usually obtained with scaled experiments for every specific geometry. As part of the preliminary validation experiments of the damping correlations used for SLOSH-ML, the damping ratios given by the correlations were found not to coincide with the ratios derived from the experiment for smaller tanks. This presentation will go over the preliminary validation findings as well as the current investigation into the discrepancy that arose.

Faculty advisor: 

Professor Álvaro Romero-Calvo