Projects
Space Simulator
Explore space ! Fight enemies ! Among the vast emptiness and beauty of interplanetary space.
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Features :
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Developed in Unity (C#)
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Real Orbital Mechanics (N-body).
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1 : 1 scale (Millions or even billions of Km !).
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Ship Construction!
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Endless Exploration
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Missiles , PDC for pew pew !
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Ultra Realistic atmosphere scattering effects.
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Realistic Lighting!
International Space Challenge 2020
Topic : Space Debris Mitigation
As the Team Leader of Team StarFleet Command, along with Shamugham Surya (SSC 2017 Grand prize winner, NUS scholar, LKY Award winner) and Kim Hyun Ji (President SEDS NTU), we overcame the fierce competition of more than 74 local and international teams to win S$10,000 , the grand prize award.
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From the onset, I led the team to approach the problem first from an financial and operational feasibility perspective, drilling down to reusability and <20,000 USD $ cost per debris deorbited. Then I led the team's engineering efforts with a iterative and elimination method to achieve that cost.
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To further differentiate, I pushed the team to minimize assumptions in our engineering and mission design. The prime example being the orbital mechanics, utilizing STK with the advanced J2 propagator which takes into account of all orbital elements and perturbations due to solar flux, non spherical earth and external n body gravitational sources.
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Find Out More :
Mentoring :
Mentor - Team Merlunar from SIT
(ISC 2021 Community choice award winner)
Mentor - Team QUASAR from Cedar Girls
(ISC 2021 Women in Stem award)
Official SSTL Facilitator for ISC 2022
Mentor - SEDS Singapore Rocketry Team
(Hybrid Engine Sub-Team)
Tools Used :
STK
Inventor
Blender
Python
Ansys
100N Igniter Project
Our first Rocket engine , a 100N bi propellent igniter. The purpose of this project is to design and build a small rocket engine that is low cost but demonstrates all the principles of a full scale rocket engine. The engine is made of 304L stainless steel, in 4 sections, Spark plug mount, Injector , chamber and nozzle.
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The injector consumes a fuel rich gaseous oxygen and 95% liquid ethanol mixture at 1.6 O/F Ratio achieving a 78% C* . The pressurization gas is high pressure nitrogen regulated down to about 10 bar. Chamber pressure is 6.4 bar, flow rate is 13g/s and specific impulse is 150 Sec . The injector element is a duplet impinging type injector arranged in 65 deg angle. Fluid analysis was performed using k-Omega SST turbulence model on the injector to determine mixture and atomization characteristics, energy flux , C*/ specific impulse and thrust.
Tools Used :
Inventor
Ansys
Thrust Vectoring Electric Hopper (WIP)
Inspired by the falcon 9 first stage boost back and landing using a gimbled vectoring Merlin D engine , the propose of the project is to learn the principles of rocket GNC system.
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In the thrust vectoring hopper , 2 inline ducted fans was used to simulate a rocket engine and 4 fins were used to deflect the direction of the exhaust, simulating rocket engine gimbaling.
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An AHRS/IMU unit is used that provides readings of orientations in quaternions that eliminate gimbal lock, barometric altitude sensor and GPS. Orientation information is fed into a closed loop PID control system developed in Matlab/Simulink with the help of the aerospace block set.
For indoor navigation, a SVO library is used (RPG SVO Pro) allowing for 3D localization with a single wide angle camera. The library will run on a NVidia jetson Nano. Currently this is Work in Progress.
Tools Used :
Inventor
C++
Python
Matlab / Simulink
1kg/s Ethanol Rocket Turbopump (WIP)
The purpose of this project is to learn the working principles of an electric rocket turbopump. The design goal is to create an ethanol turbopump with max impeller diameter of smaller than 40cm that can achieve 650m head or 50 Bar delta, 1kg/s mass flow or 4.6 m3/hr volumetric flow rate and <15kW power at 50,000 rpm (Based on high end brushless motor used in RC planes).
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The first stage is an inducer consisting of 2 blades and transfers 7% of the total work to the fluid by increasing the intake pressure by 3.5 bar at ~80% hydraulic efficiency. The inducer effectively prevent impeller cavitation and improve efficiency.
The second stage is a shrouded impeller consisting of 8 blades and transfers 93% of the total work to the fluid by increasing the pressure by 46.5 Bar at 64% hydraulic efficiency . The fluid flows from the impeller to a diffuser with leads to the volute which receive high velocity fluid and directs the flow in a spiral channel to the discharge. The volute's spiral geometry is based on the Stepanoff design theory and the cutwater which diverts fluid to the discharge.
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The final design meets the design goals and is a radial two stage mixed flow inducer and shrouded impeller design with a specific speed of 14, e-motor power of 13kW and nominal rotational speed of 50,000 rpm. Overall max efficiency of 68%.
Tools Used :
Inventor
Ansys
CF Turbo
Design of a 10kM Apogee Bi Propellent Rocket
The purpose of this project is investigate the design of a hypothetical 10kM apogee bi propellent blow down nitrous oxide and ethanol rocket at an average of 4.5:1 O/F.
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The rocket consist of 2 aluminum cylinder with welded bulkheads as pressure vessels, the nitrous oxide tank and the ethanol tank. The nitrous oxide tank (Top tank) is a self pressurized 50 Bar, the vapor pressure of nitrous oxide. The ethanol tank (Lower Tank) is a blowdown type tank with 70 Bar initial pressure. Flow control valve of ball type with a geared stepper.
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The rocket engine is a 4kN regen cooled engine with a pintle injector. The Oxidizer flow rate is about 3kg/s while fuel flow rate is about 0.8kg/s on average. Due to the blowdown nature of the fuel tank , the initial 3.5 O/F ratio is the highest efficiency, as the fuel is consumed, the blowdown pressure decreases and O/F shifts to 5:1 at the end of the burn with ~10% propellent residual. The predicted C* 90% at 3.5 O/F and 230 Sec Isp. A pintle injector due to O/F shift and variable flowrate.
The thrust chamber is regen cooled, manufacturing of the chamber using welded spin formed outer and inner steel cylinders. The regen channels are formed with steel strips and its curved geometry maximize heat transfer at the throat which experiences peak flux.
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Tools Used :
Inventor
Ansys
STK
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