• L Aditya Gaikwad
• K Kiran Kumar
• Nitin P Ghodke
• Dattatreya
• Karthik S

This paper constitutes the study good earth imagery from the optical sensors and camera of the satellite in space, good dimensional stable structure is required for supporting the payloads. A small deflection in the support structure of optical payload causes large deviation of focus area from the required target image. To avoid this the selection of material for the structure is important and the material should have a low thermal coefficient of expansion and low density for this we have selected CFRP (Carbon fibre reinforced polymer) as a material, and we have designed a tripod for the supporting structure for the optical payload and sensors. This consumes less space, less material and increased strength as compared to other truss members. This consists of mainly three parts upper deck, pod, and end caps, increasing the strength and stability for the supporting structure. We have assigned and stacked various layers of CFRP with required properties and independent orientation of fibres. The temperature variation in space ranging from -170ºC to +100ºC. The thermal control system will control these temperatures to the working range of +800c to -300c. Due to this temperature variations in the spacecraft structure material gets expanded and contracted. The effect of these temperature variations, on the dimensional stability of the structure thermo-elastic deformation analysis also carried out for extreme temperature ranges. During launching, spacecraft will experience vibration loads at the spacecraft interface to the launch vehicle. These vibration loads are further amplified at the subsystem level within the spacecraft. The low frequency vibration loads added to the steady state acceleration of the launch vehicle impart the combined dynamic and static loads on the spacecraft. This loading is called as Quasi-Static loading and the static analysis is carried out with inertial loading conditions. The stresses and failure indices on the composite materials are calculated for above different analyses types. The change in the orientation of the mounting plane of the optical payload is also estimated for extreme temperature conditions.

CFRP, Optical payload, Tripod Support, Pod, Platform and Tripod

"DESIGN AND ANALYSIS OF STABLE PLATFORM FOR SATELLITE OPTICAL PAYLOAD", International Journal of Emerging Technologies and Innovative Research (www.jetir.org), ISSN:2349-5162, Vol.6, Issue 5, page no.283-288, May-2019, Available :http://www.jetir.org/papers/JETIRBZ06045.pdf

"DESIGN AND ANALYSIS OF STABLE PLATFORM FOR SATELLITE OPTICAL PAYLOAD", International Journal of Emerging Technologies and Innovative Research (www.jetir.org | UGC and issn Approved), ISSN:2349-5162, Vol.6, Issue 5, page no. pp283-288, May-2019, Available at : http://www.jetir.org/papers/JETIRBZ06045.pdf