I’m working on a part time basis with the Johns Hopkins University – Applied Physics Lab as part of my masters in Space Systems Engineering. Specializing in the Spacecraft Guidance Navigation and Control with emphasizes on conducting the end to end design that will produce an agile spacecraft. Areas of attitude estimation, attitude control and spacecraft pointing stabilization, and orbital determination, working on simulating 6-DOF for a space mission I’m working on using Matlab/Simulink. In addition, I’m the TT&C (RF Comm) subsystem lead with emphasizes on the design and testing of spacecraft antenna and needed components for a functioning subsystem. Also, studying to a certain depth the rest of the subsystems needed by any spacecraft such as EPS, C&DH, Thermal, Propulsion, Mechanical, FSW, and different types of payloads. Knowing how to design each subsystem by matching and refining the mission requirements and developing design budget to balance cost, schedule, and performance conduct trade studies and risk analysis. After the finish of the end to end conceptual design of the space mission we are designing. We will also, integrate, and test the needed flight hardware. This degree is developing the overall knowledge of a space system giving me the perspective of a systems engineer as well giving me the in-depth knowledge in ADCS and TT&C. In addition, to my JHU-APL work I have seven years of RF Engineering experience with in-depth knowledge in RF Fundamentals, radio propagation modeling and prediction, microwave path analysis, interference analysis, and antenna theory. I also have hands-on experience with RF hardware Integration, testing, and troubleshooting from radios, transmission line, connecters, amplifiers, antennas, and other essential components
MatLab C++ STK-AGI Certified ODTK Space Systems ADCS (GNC) TT&C(RF) Astrodynamics and mission design
Johns Hopkins University – Applied Physics Laboratory, Laurel, MD Aug 2016-Present Space Systems Engineer (TT&C and GN&C Subsystems Lead) Part Time Graduate Student attending remotely
ADCS (GNC) Subsystem Lead:
Calculating Center of pressure for every major area of the spacecraft, after getting center of mass, and spacecraft moment of Inertia from mechanical subsystem lead
Calculating all possible forces acting on the spacecraft such as aero-force (for LEO), solar pressure, gravity gradient, and others. Then, calculating torque acting on the spacecraft and total torque in three dimensions (x,y, and z axis)
Finding out needed torque to overcome outside forces acting on the spacecraft. And thus, sizing reaction wheels to achieve 3-axis stabilized spacecraft
Finding out needed momentum sizing and then selecting appropriate method to dump momentum either using torque rods or thrusters
The use of TRIAD algorithm to find attitude estimation matrix, angle of rotation, and axis of rotation. This is also used as part of 6-DOF analysis (if needed)The selection of two different sensors to give four different vectors
Used Star tracker, Earth horizon sensors: 1st two vectors in body frame. 2nd two vector in inertial frame, those are used to complete 3-degrees of attitude (x,y,z). Also, used sun sensors for safe mode and solar panels pointing.
Used velocity and distance tracking to be used as part of 3-degrees of position (x,y,z)
Attitude estimation will be used as a feedback to perform attitude control using reaction wheels where there Is a wheel perpendicular to each axis (x,y,z)
Also Attitude estimation will be used for position change as part of mission design to fire thrusters during phasing maneuver, and Hohmann transfer to lower orbit
Summary of sensors:
Star tracker: for attitude estimation
Earth Horizon sensor: for attitude estimation (spacecraft must be nadir pointing)
Sun sensors: for safe mode and solar panel pointing
TT&C Subsystem lead:
Perform Link Budget analysis for Space to Ground, Ground to Space, and Space to Space Link, proximity links
Calculate needed cant angle for line of site communication for space to space links
Develop TT&C block diagram
Design needed components to perform as required such asSelection of transponder(s) for two-way accurate tracking:
Velocity (Doppler shift) and Distance tracking
Modulation (using BPSK, QPSK, or others) and Demodulation
Forward Error Correction (FEC), such as Convolutional coding (Turbo Code or others)
Selection of Amplifiers
SSPA (Solid State Power Amplifier): built in transponder or separate depend on needed amplification that will be delivered to the antenna (<15W)
TWTA (Traveling Wave Tube Amplifier): more than 15W usually separate from Transponder
LNA (Low Noise Amplifier): used to amplify received signal given the received signal power is very low and hence very close to noise floor this amplifier is needed to amplify the signal power and minimize the amplification of noise usually NF<2dB
Antennas: selection and design is based on many factors such as
Spacecraft mass and power budget allocation to TT&C subsystem
Spacecraft Link budget allocated to different links
Received signal wavelength (Bands such as S, X, Ka, and Ku)
Needed bandwidth of how many frequencies it could intercept
Required EIRP to deliver minimum signal power to the other end
Diplexer: acts as a filter if same antenna is used for TX/RX
Hybrid Couplers: if equal power division is needed
Switches: if there is a need to turn on/off different antenna or if there is a redundant system
Transmission line: this is where impedance matching with the load (usually antenna) will need to be worked out to deliver as much power to the antenna throughout the transmission line as possible with the least reflected power. Thus, low VSWR.
Johns Hopkins University – Applied Physics Laboratory, Laurel, MD Jan 2016-Present Space Systems Engineering Part Time Graduate Student attending part time via live video conference, 2016-Present
The degree goal is to know how to design a space mission for both Earth orbits and deep space, we must be able to design the space mission by analyzing the mission goals and parameters and getting the mission different parameters and budgets such as Mass and Power budgets, as well conduct end to end design for all spacecraft subsystems.
Working on designing a constellation of 6-10 spacecraft that can detect and report forest fire for NATO countries (The mission is comparable to the FireSatII)
I’m acting as the Telemetry Tracking and Command (TT&C) subsystem lead, and Attitude Determination Control (ADCS) subsystem lead In addition, I’m responsible on Mission trade studies, Mission design summary, mission requirements, and Delta V budget
Studying Spacecraft orbital mechanics and astrodynamics and using that knowledge in designing various missions using STK as well getting their parameters using mathematical equations and lastly the ability to calculate the required Delta V budget through the mission life time
Knowing how to design the spacecraft subsystems and how they can get integrated and tested to operate fully in the environment of space
In addition to the constellation design, there will also be another space mission will involve hardware design (CubeSat)
study critical risk-based decision making required from system concept definition and degree auditing through design, procurement, manufacturing, integration and test, launch, and mission operations
Study and apply mission assurance, ensure mission reliability, and system safety throughout the life cycle of the mission to achieve mission success
Mission assurance such as risk management, system safety, reliability engineering, parts and materials, configuration management, requirements verification and validation, non-conformance, and anomaly tracking and trending.
Mobilitie, Dallas, Texas March 2017-Present
Senior RF System Engineer, 2017-present
Fusion Solutions Contractor, Dallas, Texas Jan 2016-Nov 2016
Sr. RF System Engineer Jan 2016- Dec 2016
Strong Radio Frequency fundamentals, wave propagation, and Antenna theory. A senior DAS and small cells Design Engineer with responsibility on designing & configuring a Varity of custom configured wireless distributed networks with deep knowledge in overall DAS, small cells, antenna systems, and end to end wireless architecture. In addition, assuming full responsibility on the end to end system design. Outdoor small cells design to increase location capacity, and provide superior end customer experience.
ERICSSON, Plano, Texas 2010-2015
RF System Engineer, 2010 – 2015
RF Engineer Subject Matter Expert and solutions architect with in-depth knowledge of the fundamentals of Radio Frequency, wave propagation, antenna theory, transmission line theory, impedance matching, RF link budget analysis, . Worked on building, designing, integrating, testing, and optimizing end to end wireless networks with hands-on experience with Air Interface side and communication tower hardware such as Radios, cables, jumpers, amplifiers, and antennas. RF Technical Leader and a Subject Matter Expert (SME) with responsibility for, developing, building, and leading technical engineering teams in LTE, VOLTE, IMS Planning, Tuning, optimization, DAS, and small cells high profile projects. In addition, wrote technical documents, research & trial parameters & features
EDUCATION / TRAINING
Masters of Science, Space Systems Engineering
Johns Hopkins University, Baltimore, MD - EST 2018 (Current GPA 4.0/4.0)-Administrated by the Applied Physics Laboratory
Bachelors of Science, Electrical Engineering
University of South Alabama, Mobile, AL - 2009
Professional Affiliations: 1. AIAA (American Institute of Aeronautics & Astronautics) 2. IEEE (Institute of Electrical & Electronics Engineers)
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