Thermal Analysis of TRIO-CINEMA Mission

Abstract

Thermal analysis and control design are prerequisite essential to design the satellite. In the space environment, it makes satellite survive from extreme hot and cold conditions. In recent years CubeSat mission is developed for many kinds of purpose. Triplet Ionospheric Observatory (TRIO)-CubeSat for Ion, Neutral, Electron, MAgnetic fields (CINEMA) is required to weigh less than 3 kg and operate on minimal 3 W power. In this paper we describe the thermal analysis and control design for TRIO-CINEMA mission. For this thermal analysis, we made a thermal model of the CubeSat with finite element method and NX6.0 TMG software is used to simulate this analysis model. Based on this result, passive thermal control method has been applied to thermal design of CINEMA. In order to get the better conduction between solar panel and chassis, we choose aluminum 6061-T6 for the material property of standoff. We can increase the average temperature of top and bottom solar panels from -70°C to -40°C and decrease the average temperature of the magnetometer from +93°C to -4°C using black paint on the surface of the chassis, inside of top & bottom solar panels, and magnetometer.

Thermal design and analysis of a nanosatellite in low earth orbit

“…Thermal control techniques may be either passive or active but the former is the most widespread option for small university satellites. References [10][11][12][13][14][15][16] show interesting examples of thermal control systems adopted on-board small platforms. Passive thermal control relies mainly on the definition of the architecture and layout of the satellite, and makes use of materials, coatings or surface finishes, thermal insulation and heat sinks with adequate thermo-optical properties.…”

Thermal Numerical Analysis of the Primary Composite Structure of a CubeSat

“…The temperature for each one of the electronic boards at any instant of time are into the range of their safety operating limits, showing the feasibility to use the composite panels as the primary structure for a CubeSat that perform the selected mission. To compare the thermal behavior between the composite material and an aluminum structure, the simulation was carried out with the properties of the aluminum 5052-H32 sheet with a thickness of 0.080' (2.032 mm) black paint, the thermal properties are listed in Table 2 and the emissivity of this alloy was taken as 0.89 [15]. The average temperature in each panel as function of time is plotted in Figure 9.…”

“…The radiation model S2S from ANSYS assumes the surfaces to be gray and diffuse, then, the emissivity ( ) is equal to the absorptivity (α). In the computational simulations the emissivity for the composite panels was taken as 0.81 [35] and for the PCBs (FR4) equal to 0.6 [15].…”

“…The transient thermal model was implemented in ANSYS 13 software and, minimum and maximum temperatures reached by the CubeSat are presented considering only the aluminum structure and a multi-layer insulation throughout the aluminum structure. A similar but more complete analysis was done by Reference [15] for the TRIO-CINEMA (Triplet Ionospheric Observatory -CubeSat for Ion, Neutral, Electron, MAgnetic fields). The authors took into account the optical properties of the main components of the CubeSat to compute the radiation heat fluxes.…”

Optical Design of a Reflecting Telescope for CubeSat

“…It is launched as a piggyback secondary payload on a large launch vehicle using the Poly-Picosatellite Orbital Deployer (P-POD). There are many kinds of 3U CubeSat missions for scientific research and technical experiments [8,9]. Imaging satellites based on CubeSat have mostly been implemented for Earthobserving missions.…”