Informatics Publishing Limited

A. S. Arya ¹, S. S. Sarkar ¹, A. R. Srinivas ¹, S. Manthira Moorthi ¹, Vishnukumar D. Patel ¹, Rimjhim B. Singh ¹, R. P. Rajasekhar ¹, Sampa Roy ¹, Indranil Misra ¹, Sukamal Kr. Paul ¹, Dhrupesh Shah ², Kamlesh Patel ¹, Rajdeep K. Gambhir ¹, U. S. H. Rao ¹, Amul Patel ¹, Jalshri Desai ¹, Rahul Dev ¹, Ajay K. Prashar ¹, Hiren Rambhia ¹, Ranjan Parnami ¹, Harish Seth ¹, K. R. Murali ¹, Rishi Kaushik ¹, Deepak Patidar ¹, Nilesh Soni ¹, Prakash Chauhan ¹, D. R. M. Samudraiah ¹, A. S. Kiran Kumar ¹

Affiliations
1 Space Applications Centre, Indian Space Research Organisation, Ahmedabad 380 015, IN
2 Space Applications Centre, Indian Space Research Organisation, Ahmedabad 380 015

Abstract

Mars Colour Camera (MCC) on-board Mars Orbiter Mission is considered the ‘eye’ of the mission, taking photographs (imageries) of the surfacial features on Mars, and the cloud and dust around it. MCC is an important contextual camera for other non-imaging sensors like MSM, TIS, LAP, etc. The camera has been designed, characterized, calibrated and qualified at the Space Applications Centre, ISRO, Ahmedabad by a team of professional engineers and scientists. It has been miniaturized, ruggedized and space-qualified to match the weight and power budget of the mission. During Earth orbit phase, the images returned by the camera have been analysed qualitatively and quantitatively. The results show that MCC has been working as expected in terms of radiometry, geometry and application potential to discern various morphological features. The present article discusses these facts in detail.

Keywords

Detector, Earth imaging phase, payload, Mars colour camera.

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Kurian Mathew ¹, S. S. Sarkar ¹, A. R. Srinivas ¹, Moumita Dutta ¹, Minal x Minal Rohit ¹, Harish Seth ¹, Rajiv Kumaran ¹, Kshitij Pandya ¹, Ankush Kumar ¹, Jitendra Sharma ¹, Jalshri Desai ¹, Amul Patel ¹, Vishnu Patel ¹, Piyush Shukla ¹, S. Manthira Moorthi ¹, Aravind K. Singh ¹, Ashutosh Gupta ¹, Jaya Rathi ¹, P. Narayana Babu ¹, Saji A. Kuriakose ¹, D. R. M. Samudraiah ¹, A. S. Kiran Kumar ¹

Affiliations
1 Space Applications Centre, Indian Space Research Organisation, Ahmedabad 380 058, IN

Abstract

Methane Sensor for Mars (MSM), on-board Mars Orbiter Mission is a differential radiometer based on Fabry–Perot Etalon (FPE) filters which measures column density of methane in the Martian atmosphere. It is the first FPE sensor ever flown to space. Spectral, spatial and radiometric performances of the sensor were characterized thoroughly during the pre-launch calibration. Geophysical calibration of the sensor was carried out using the data acquired over Sahara desert during Earth Parking Orbit phase. Retrieval algorithm for MSM, which is based on the linearization of radiative transfer equations, gets simultaneous solutions for CH4 and CO2 concentrations in the Martian atmosphere.

Keywords

Differential radiometer, Fabry–Perot Etalon, geophysical calibration, methane sensor, retrieval algorithm.

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A. Senthil Kumar ¹, V. Keerthi ¹, V. K. Dadhwal ¹, A. S. Kiran Kumar ²

Affiliations
1 Geophysical and Special Products Group, National Remote Sensing Centre (ISRO), Balanagar, Hyderabad 500 037, IN
2 Space Applications Centre (ISRO), Jodhpur Tekra, Ahmedabad 380 015, IN

Abstract

With the inclusion of a hyperspectral imager (HySI) sensor on the Indian Mini Satellite (IMS-1) Earth observation mission and subsequently near identical hyperspectral sensor on the Chandrayaan-1 lunar mission, 64-band hyperspectral data from both these missions have provided the user community rich information to explore new algorithms to exploit sensorspecific parameters and to interpret and/or classify the features in multi-resolution frame. In this article, methods to improve spectral uniqueness present in the HySI by analysing adjacent bands' spectral overlaps, by implementing spectral deconvolution and reconstruction techniques are presented. Similarly, the use of multi-resolution approach for fast searching of standard spectral library end-members for better discrimination of hyperspectral pixel data are also discussed along with applications in Earth and lunar surface hyperspectral image interpretation. These spectral analyses techniques are useful in discriminating subtle differences in spectral signatures that help study the origin of secondary craters and gullies/ landslides on the lunar surface.

Keywords

Lunar Surface, Multi-resolution Approach, Spectral Deconvolution, Spectral Overlap.

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A. S. Arya ¹, A. S. Kiran Kumar ¹

Affiliations
1 Space Applications Centre (ISRO), Ahmedabad 380 015, IN

Abstract

No Abstract.

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A. S. Kiran Kumar ¹, Prakash Chauhan ¹

Affiliations
1 Space Applications Centre (ISRO), Ahmedabad 380 015, IN

Abstract

No Abstract.

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A. S. Kiran Kumar ¹

Affiliations
1 Indian Space Research Organisation, Bengaluru 560 231, IN

Abstract

No Abstract.

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R. P. Singh ¹, Somya S. Sarkar ¹, Manoj Kumar ¹, Anish Saxena ¹, U. S. H. Rao ¹, Arun Bhardwaj ¹, Jalshri Desai ¹, Jitendra Sharma ¹, Amul Patel ¹, Yogesh Shinde ¹, Hemant Arora ¹, A. R. Srinivas ¹, Jaya Rathi ¹, Hitesh Patel ¹, Meenakshi Sarkar ¹, Arpita Gajaria ¹, S. Manthira Moorthi ¹, Mehul R. Pandya ¹, Ashwin Gujrati ¹, Prakash Chauhan ¹, Kuriakose A. Saji ¹, D. R. M. Samudraiah ¹, A. S. Kiran Kumar ²

Affiliations
1 Space Applications Centre, Indian Space Research Organisation, Ahmedabad 380 058, IN
2 Indian Space Research Organisation, Bengaluru 560 231, IN

Abstract

Thermal Infrared Imaging Spectrometer (TIS), which operates in the infrared spectral region (7-13 μm), is one of the five instruments on-board the Mars Orbiting Mission (MOM). TIS was designed to detect emitted thermal infrared radiation from the Martian environment, which would enable the estimation of ground temperature of the surface of Mars and also map its surface composition. TIS instrument is a grating-based spectrometer which has spatial resolution of 258 m at periapsis (372 km). TIS hardware was realized with light-weight miniaturized components (total weight 3.2 kg) with power requirement of 6 W. Observations from TIS instrument were carried out during Earth-bound manoeuvres and cruise phase operations of MOM and the results were found to be in agreement with the laboratory measurements.

Keywords

Aerosol Optical Thickness, Mars Orbiter, Minerals Detection, Thermal Infrared Spectroscopy.

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A. S. Kiran Kumar

Abstract

Bringing down the cost of access to space has been an activity demanding attention of space agencies. Many countries paid attention to realize viable concepts to recover the hardware and reuse the same in multiple missions. One of the strategies is to use Reusable Launch Vehicle (RLV) which is emerging as a possible candidate for recovery of the upper or lower stages. Generally, RLV is a winged body geometry that carries the payload to the specified orbit and returns and lands on a specified location. Hence, unlike the conventional launchers, RLV encounters many technical challenges in terms of aerodynamics, aero-thermo dynamics, control systems, materials, etc. Towards this, Indian Space Research Organisation (ISRO) has been pursuing the RLV technology to achieve two-stage to-orbit (TSTO) launch capability.

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