RadSSC

Final Post

By: Victoria Hatfield Objective 1U:Proof of Concept 3U and 6U:Design Implementation Spacecraft Payload:CREAM Sensor Suite Attitude Control Orbit Trajectory Communication System Command and Data Handling Final Video

3U and 6U: Design Implementation

By: Victoria Hatfield, Project Manager Using what we have learned from manufacturing our own cube, we will then develop a 3U CubeSat that will include our CREAM sensor suite. The 3U CubeSat will contain all necessary components for mission success, however it will not contain a propulsion system. Due to the tethering to ISS, a […]

1U: Proof of Concept

By: Victoria Hatfield, Project Manager The 1U will consist of multiple sensors, within the size constraints, to best represent what our data sensors onboard the 3U will be able to gather. By connecting the 1U to a meteorological balloon, we are able to test the off-the-shelf parts to set basic standards for our measurements. Using […]

Attitude Control

By: Fernando Ayon-Serrato Modes of Operation: RadSSC will need to achieve and sustain control throughout all phases of the mission; [1] Launch/de-tumble Attitude acquisition (initial and recursive) Normal flight operations Delta V Once RadSSC is deployed into orbit, it will experience varying angular velocities and environmental forces. In order for attitude determination to be successful, […]

Orbit Trajectory

By: Fernando Ayon-Serrato A unique factor for RadSSC is after mission success, it will be the first CubeSat to orbit the Moon. Several trajectory methods, both low and high power, have been researched to achieve a successful rendezvous with the Moon. During initial research, we proposed deploying from the ISS and traveling through the Van […]

Communication System

By: Larry Harmon Since the objective of the mission is to send two 6U CubeSats to the L1 and L2 Lunar Lagrange Points, a low-powered (approximately 10W) communications system will not be able to close the link at those distances. To transmit data back to Earth, testing has shown optical communications systems can transmit long-distance […]

Command and Data Handling

By: Muhammad Farooq Telemetry, command, and data handling subsystem is responsible for information exchange between the spacecraft (RadCube) and the ground control station. In case of RadCube, communication relays (TDRSS) could be used for the two-way flow of information. The system is responsible for collecting, storing, and processing the data in system memory and making […]

Spacecraft Payload: CREAM Sensor Suite

By: Victoria Hatfield, Project Manager Using the CREAM sensor suite, we will be able to accurately depict the radiation environment at the Lagrange points. The CREAM sensor suite will utilize a dosimeter for ionizing dose environment measurements, temperature sensor, and UV (or sun-hour) sensors.

RadSSC Objective

By: Victoria Hatfield, Project Manager The objective of the Radiation Solar sail SpaceCraft (RadSSC) initiative is to develop a CubeSat system to measure and map the radiation environment in the vicinity of the first and second Earth-Moon Lagrange points (EM-L1 and -L2). The CubeSat(s) will monitor how cosmic radiation and magnetic fields vary as the […]