Jamal Ahmed

• Conducted research, design, development, and testing of attitude control computer electronics (schematic and PCB layout) for space missions.
• Developed FPGA HDL core to acquire sensor data and issue actuator commands.
• Worked on the following projects:
• Design, development, and testing of hardware electronics (schematic and PCB) of Attitude Control Computers for Paktes-1A:
• It is a 100 kg-class satellite, and it is designed for Earth observation and remote sensing applications in order to evaluate the technology in a space environment. In this satellite, the on-board computer and attitude control computer are being controlled by a single DSP processor, and I am involved in the following tasks:
• Design and development of the on-board card in which the DSP processor is interfaced with EDAC and memories for data handling and communication with the telecommand unit. In addition, attitude control electronics are designed on the same card, and all the drivers and application software of the attitude control subsystem are being handled by the same processor. I have used Altium Designer for hardware and PCB designing, and Code Composer Studio and C language for DSP processors.
• Design and develop Sensors-Actuators Emulators (Sun Sensor, Star Sensor, Reaction Wheel, Magneto-torquer, GPS, Magnetometer) for hardware-in-the-loop testing of satellites.
• Design and develop a Zarm sensor-based magnetometer.
• Design, development, and testing of hardware electronics (schematic and PCB) of the Propulsion Control Computer for KHTT PRSS-1:
• Design, development, and testing of telemetry, telecommand, and control electronics cards for the propulsion subsystem. To avoid a single point of failure, a redundant control electronics card is also designed and connected to the primary control card through the backplane PCB.
• Development of control electronics software for the said subsystem.
• Thermal, vibration, and burn-in testing of propulsion control electronics.

• I worked as a researcher on different lab projects in ASCL Lab related to cubesats, deep learning, and computer vision.
• RANDEV - 3U CubeSat
• RANDEV is a 3U CubeSat developed by KAIST for the 5th CubeSat design contest (four CubeSats in total) organized by KARI (Korea Aerospace Research Institute). The RANDEV CubeSat is an Earth-monitoring satellite operating in Low Earth Orbit and providing hyper-spectral images of the Korean Peninsula in case of a natural or industrial disaster.
  Role: I was involved in R&D of CubeSat as a power subsystem lead and a member of the integration and testing team for the flight on the KSLV NURI rocket. During the R&D phase, the power budget is simulated and calculated based on the requirements of all subsystems, considering the orbit and duration of the mission. Accordingly, battery banks, solar panels, and power boards were procured, designed, and tested for engineering and flight models both independently and in an integrated way. EPS space-grade custom electronics and PCB design for solar panels and antenna deployment were developed and tested. Then all subsystems were harnessed, integrated, tested, and the CubeSat was successfully launched into orbit.
• Transformer Network-Aided Relative Pose Estimation for Non-cooperative Spacecraft Using Vision Sensor.
• The objective of the work is to perform monocular vision-based relative 6-DOF pose estimation of the non-cooperative target spacecraft relative to the chaser satellite in rendezvous operations. I am involved in the acquisition and processing of the image using deep learning methods, and I extract useful information that is required to solve the perspective-n-point problem (PnP). The pose estimation pipeline is developed with a learning-based image-processing subsystem, and geometric optimization of the pose solver. In this work, the convolutional neural network (CNN) is replaced by the high-resolution transformer network to predict the feature points of the target satellite. The extracted feature points are then projected onto the 3D model of the known target to calculate pose values.
• Feasibility study for the development of the LUNAR ROVER-ATERIS mission.
• I am involved as a team member in the R&D of the Lunar Rover for the ATERIS mission. The objective is to land the rover on the South Pole and communicate with the satellite. My task is to propose a feasibility study and development plan for the electronics of the Lunar Rover. During the Lunar mission, half of the month is nighttime, and it is required to operate electronic subsystems in such a way that the rover can survive the long nighttime and recharge again during daylight.

Worked on the following projects:

• Design, development, and testing of hardware electronics (schematic and PCB) of Attitude Control Computers for Paktes-1A:
• It is a 100 kg-class satellite, and it is designed for Earth observation and remote sensing applications in order to evaluate the technology in a space environment. In this satellite, the on-board computer and attitude control computer are being controlled by a single DSP processor, and I am involved in the following tasks:
• Design and development of the on-board card in which the DSP processor is interfaced with EDAC and memories for data handling and communication with the telecommand unit. In addition, attitude control electronics are designed on the same card, and all the drivers and application software of the attitude control subsystem are being handled by the same processor. I have used Altium Designer for hardware and PCB designing, and Code Composer Studio and C language for DSP processors.
• Design and develop Sensors-Actuators Emulators (Sun Sensor, Star Sensor, Reaction Wheel, Magneto-torquer, GPS, Magnetometer) for hardware-in-the-loop testing of satellites.
• Design and develop a Zarm sensor-based magnetometer.
• Design, development, and testing of hardware electronics (schematic and PCB) of the Propulsion Control Computer for KHTT PRSS-1:
• Design, development, and testing of telemetry, telecommand, and control electronics cards for the propulsion subsystem. To avoid a single point of failure, a redundant control electronics card is also designed and connected to the primary control card through the backplane PCB.
• Development of control electronics software for the said subsystem.
• Thermal, vibration, and burn-in testing of propulsion control electronics.