Development of mysat (1u cubesat) mission analysis and design
| dc.contributor.author | Ahmad Shaqeer Mohamed Thaheer | |
| dc.date.accessioned | 2021-11-15T00:54:53Z | |
| dc.date.available | 2021-11-15T00:54:53Z | |
| dc.date.issued | 2017-11-01 | |
| dc.description.abstract | A low-cost space platform is needed in measuring the electron-density in the ionosphere to prove the correlation between earth anomalies and the changes of the electron-density. The previous method of measurement is done using traditional satellite, which is very costly and huge. However, satellite development has been a complicated process as the components chosen should be optimized and feasible for the mission. Thus, a preliminary design analysis is done to determine the requirement that suits for the mission and each subsystem. Therefore, this research presents a mission analysis and structure design and analysis of 1U CubeSat named MYSat. MYSat is expected to be deployed using JEM Small Satellite Orbital Deployer (J-SSOD) at the International Space Station (ISS) with a mission of measuring the electron-density in Ionosphere. The research started with mission definition by deriving the objectives and requirements of the mission and subsystems. Then, the orbital analysis is then conducted using Systems Tool Kit (STK) software to estimate the orbital lifetime. The simulation performed is also to determine lighting time and ground track of MYSat. The result from the simulation and operational concept become the input for subsystem’s requirement, and initial subsystem budget is calculated. The structure of MYSat has been designed and structural analysis has been performed using ANSYS software. MYSat is orbiting about 400 km in altitude with the expected lifetime of 1 to 1.3 years. It does not have an attitude control and uses a passive thermal control. The communication link uses Very-High Frequency (VHF) Receiver (144-146 MHz), and Ultra-High Frequency (UHF) Transmitter (435-438 MHz) with limited transmission power of 1.5 W. GaAs (UTJ) solar cell is used for power generation with a Li-ion battery as power storage. All the subsystems including Temperature and Electron-density Probe (TeNeP) science unit are integrated into a 10×10×11.35 cm structure with a maximum mass of 1.30 kg. The results show that the design is feasible and that the mission could efficiently work with the available power and mass. The result of structural analysis also demonstrated that the average stress that MYSat experienced is well below the material’s ultimate strength. Thus, the structure can withstand harsh loading conditions during the mission. It also shows that MYSat ballistic number and natural frequency are following the requirements defined by J-SSOD launch system. The methods used was effective in estimating the preliminary results, but a group of expert teams is recommended for this project as it involves different background fields; hence, a more detail analysis can be done to improve MYSat development for the mission to be successful. Keywords-component; CubeSat; design; electron; MYSat; nanosatellite; power. | en_US |
| dc.identifier.uri | http://hdl.handle.net/123456789/14364 | |
| dc.language.iso | en | en_US |
| dc.title | Development of mysat (1u cubesat) mission analysis and design | en_US |
| dc.type | Thesis | en_US |
Files
License bundle
1 - 1 of 1
Loading...
- Name:
- license.txt
- Size:
- 1.71 KB
- Format:
- Item-specific license agreed upon to submission
- Description: