Miniature Multi-spectral Camera for TWSAT mission

Paper number

IAC-08.B4.6.A12

Author

Mr. Subrahmanyam D, Indian Space Research Organisation (ISRO), SAC, India

Coauthor

Mr. KiranKumar A.S., Indian Space Research Organization (ISRO),SAC, India

Coauthor

Mr. Samudraiah D.R.M, Indian Space Research Organisation (ISRO), India

Coauthor

Mr. Kuriakose Saji . A. , Indian Space Research Organization (ISRO),SAC, India

Coauthor

Mr. Detroja M.P , Indian Space Research Organization (ISRO),SAC, India

Coauthor

Mr. Seth Harish , Indian Space Research Organization (ISRO),SAC, India

Coauthor

Mr. Sarkar S.S., Indian Space Research Organization (ISRO),SAC, India

Coauthor

Mr. Parmar R.M., Indian Space Research Organization (ISRO),SAC, India

Coauthor

Mr. Patel Vishnu , Indian Space Research Organization (ISRO),SAC, India

Coauthor

Mr. Pandya H.B., Indian Space Research Organization (ISRO),SAC, India

Coauthor

Mr. Mathur Neeraj , Indian Space Research Organization (ISRO),SAC, India

Coauthor

Mr. Rao Satish , Indian Space Research Organization (ISRO),SAC, India

Year

2008

Abstract

TWSAT will carry a small size, lightweight Multispectral camera having 36 m resolution from 632km altitude. This is one of the Micro-satellites being developed by ISRO. The imageries from the payload will be used for the purpose of natural resources management like Agriculture, Forest coverage and deforestation, urban infrastructure development, land use as well as disaster management. The other major objective of the mission is also to develop and install low cost user terminals in Indian universities and developing countries to receive the payload data and generate data products. Total weight of TWSAT satellite will be less than 100Kg.

The camera operates in push broom mode, with four bands in the visible and near infra-red (VNIR), Band1 (0.45 to 0.52 micron), Band 2 (0.52 to 0.59 micron), Band 3 (0.62 to 0.68 micron) and Band 4 (0.77 to 0.86 micron), which are identical to the ones used in the previous IRS missions. The TWSAT camera has a modular configuration with each of the four spectral bands having individual optics, detector and associated electronics. All the four bands are nadir viewing with the linear detector array (CCD) being used to image the scene in across track direction of the satellite motion.

The major demands on the optical design were high spatial frequency of operation (70 lp/mm) and the large spectral coverage (0.45 micron to 0.86 micron). The optics has been miniaturized to suit the mission requirements. For miniaturization of camera electronics, state of the art devices like Analog Front End (AFE), FPGA, Low Drop Out (LDO) voltage regulator, Micro-D Connector, Multi layer PCB etc are used along with Surface Mount Technology. The camera electronics provides SNR of more than 1000 with 12 Bit digitization. The camera dynamic ranger covers upto 100

This paper details the development of the payload and the various tests carried out to qualify the payload for space use.

Abstract document

IAC-08.B4.6.A12.pdf

Manuscript document

IAC-08.B4.6.A12.pdf (🔒 authorized access only).

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