Abstract
The paper presents the development of the power, propulsion, and thermal systems for a 3U CubeSat orbiting Earth at a radius of 600 km measuring the radiation imbalance using the RAVAN (Radiometer Assessment using Vertically Aligned NanoTubes) payload developed by NASA (National Aeronautics and Space Administration). The propulsion system was selected as a Mars-Space PPTCUP -Pulsed Plasma Thruster for CubeSat Propulsion, micro-pulsed plasma thruster with satisfactory capability to provide enough impulse to overcome the generated force due to drag to maintain an altitude of 600 km and bring the CubeSat down to a graveyard orbit of 513 km. Thermal analysis for hot case found that the integration of a black high-emissivity paint and MLI was required to prevent excessive heating within the structure. Furthermore, the power system analysis successfully defined electrical consumption scenarios for the CubeSat’s 600 km orbit. The analysis concluded that a singular 7 W solar panel mounted on a sun-facing side of the CubeSat using a sun sensor could satisfactorily power the electrical system throughout the hot phase and charge the craft’s battery enough to ensure constant electrical operation during the cold phase, even with the additional integration of an active thermal heater. However, when the inevitable end-of-life degradation of the solar cell was factored into the analysis, an approximate power deficit of 2 kJ was found. This was supplemented by additional solar cell integrated into the antenna housing face.
Highlights
CubeSats are classified as a form of research and commercial spacecraft, originally developed in 1999 as a collaborative project between California Polytechnic state university (CalPoly) and the space program at Stanford University [1]
The current study stands out compared to previous studies, by designing a propulsion system based on pulsed plasma thruster technology and incorporating deployable solar panels with maneuvering capability using a Sun sensor to maximize solar flux collection efficiencies to enhance on-board power in addition to thermal design addressing thermal management and power requirements to carry out the mission to completion by deorbiting the CubeSat to a graveyard orbit
CubeSat powered function include the variety of subsystems such as command and data handling (C&DH), RF communication, Altitude determination and control (ADC) and deployable and components remain dormant during the deployment phase upon release from the P-POD [1]
Summary
CubeSats are classified as a form of research and commercial spacecraft, originally developed in 1999 as a collaborative project between California Polytechnic state university (CalPoly) and the space program at Stanford University [1]. In current CubeSat specifications there is no mention of propulsion systems; the requirements of the design impose limitations such as pyrotechnics are not allowed on board to prevent any leakage that might compromise the primary payload launch mission [12,13]. The current study stands out compared to previous studies, by designing a propulsion system based on pulsed plasma thruster technology and incorporating deployable solar panels with maneuvering capability using a Sun sensor to maximize solar flux collection efficiencies to enhance on-board power in addition to thermal design addressing thermal management and power requirements to carry out the mission to completion by deorbiting the CubeSat to a graveyard orbit. Previous studies were focused on the development and analysis of standalone subsystems such as propulsion system or deployable solar panels system
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
