Current Research
Quantum Chaos in Presence of Perturbation
[Descriptions to be added]
 [Manuscript in preparation]
Journal Club Presentations

Term Papers

Past Research
Holographic Duality with Random Tensor Network
[Descriptions to be added]
 KITP Symposium Presentation Video
 Presentation Slides
 Senior Thesis
Magnetic Field Insensitive RadioFrequency Dressed Qubits
[Descriptions to be added]
Temperatures of the Galilean Satellites
[Descriptions to be added]
Orbit Determination for NearEarth Asteroid
NearEarth Asteroids (NEA) impose a great threat to Earth due to their destructive impact upon collision, so it is crucial that we study and understand their orbits to appropriately analyze their probability of collision in any foreseeable future. In this research, together with Elisa Zhao and Hernan Valles, under supervision of Dr. Cassandra Fallscheer and Dr. Michael Dubson, we used direct imaging to obtain a series of data across a month, and numerically implemented Gauss's method to compute a preliminary orbit of the asteroid, and then use the least squares methods to obtain corrections and solve iteratively. Our results showed slight updates compared to previous calculation. The results were sent to the Minor Planet Center and were accepted.
Besides the Gauss's method, which utilizes topocentric coordinates, there is also the Laplace's method, which utilizes the geocentric coordinate. Both are good in calculating the preliminary orbit. One good review for such method can be found in this note.
NearEarth Asteroids (NEA) impose a great threat to Earth due to their destructive impact upon collision, so it is crucial that we study and understand their orbits to appropriately analyze their probability of collision in any foreseeable future. In this research, together with Elisa Zhao and Hernan Valles, under supervision of Dr. Cassandra Fallscheer and Dr. Michael Dubson, we used direct imaging to obtain a series of data across a month, and numerically implemented Gauss's method to compute a preliminary orbit of the asteroid, and then use the least squares methods to obtain corrections and solve iteratively. Our results showed slight updates compared to previous calculation. The results were sent to the Minor Planet Center and were accepted.
Besides the Gauss's method, which utilizes topocentric coordinates, there is also the Laplace's method, which utilizes the geocentric coordinate. Both are good in calculating the preliminary orbit. One good review for such method can be found in this note.
Trajectory Optimization for LaserPropelled Spacecraft
In the DESTAR lab, we propose to use phased laser array in LowEarth Orbit(LEO) to apply on the spacecraft for higher speed during the interstellar travel. In our simulation, The idea is to first have both the spacecraft and the laser in the LEO and we turn the laser on and off towards the spacecraft. Sometimes when laser and spacecraft are opposing each other, the laser must be turned off to avoid backfiring. In the end, we realized that energy transfer from the laser to spacecraft is the most efficient when spacecraft and laser reconvene (i.e. meet at the perigee of the spacecraft orbit) as many time as possible before the spacecraft escapes the Earth. So at every close encounter, we integrate forward to maximize the number of future reconvene in response to the amount of time that we left our laser on.
Originally, when we choose to put the initial position of the spacecraft at different point in the LEO, and count the total amount of time for the spacecraft to reach a certain distance from Earth, we would obtain a random behavior. As the initial position, or other parameters such as laser power, differ only slightly, the total time during transit can shoot up and down without clear pattern. After we optimize the algorithm, allowing maximum efficiency in energy transfer, we also manage to stabilize the this random behavior and the time in transit in general follows a downward trend as the laser power goes up. And overall, we reduced the time in transit for the craft to reach a target in space.
Originally, when we choose to put the initial position of the spacecraft at different point in the LEO, and count the total amount of time for the spacecraft to reach a certain distance from Earth, we would obtain a random behavior. As the initial position, or other parameters such as laser power, differ only slightly, the total time during transit can shoot up and down without clear pattern. After we optimize the algorithm, allowing maximum efficiency in energy transfer, we also manage to stabilize the this random behavior and the time in transit in general follows a downward trend as the laser power goes up. And overall, we reduced the time in transit for the craft to reach a target in space.