Refine your search
Collections
Co-Authors
- G. Manju
- Tarun K. Pant
- P. Sreelatha
- P. Pradeep Kumar
- Nirbhay Kumar Upadhyay
- Md. Mosarraf Hossain
- Neha Naik
- Vipin Kumar Yadav
- Rosmy John
- R. Sajeev
- Jothi Ramalingam
- Philip George
- Amarnath Nandi
- N. Mridula
- Aswathy R. P. Janmejay Jaiswal Rana
- Snehil Srivastava
- Satheesh Thampi
- Johns Paul
- Atin Aggarwal
- P. Purushothaman
- M. Premdas
Journals
A B C D E F G H I J K L M N O P Q R S T U V W X Y Z All
Nalluveettil, Santhosh J.
- Lunar Near Surface Plasma Environment from Chandrayaan-2 Lander Platform:RAMBHA-LP payload
Abstract Views :212 |
PDF Views:48
Authors
G. Manju
1,
Tarun K. Pant
1,
P. Sreelatha
1,
Santhosh J. Nalluveettil
1,
P. Pradeep Kumar
1,
Nirbhay Kumar Upadhyay
1,
Md. Mosarraf Hossain
1,
Neha Naik
1,
Vipin Kumar Yadav
1,
Rosmy John
1,
R. Sajeev
1,
Jothi Ramalingam
1,
Philip George
1,
Amarnath Nandi
1,
N. Mridula
1,
Aswathy R. P. Janmejay Jaiswal Rana
1,
Snehil Srivastava
1,
Satheesh Thampi
1
Affiliations
1 Vikram Sarabhai Space Centre, ISRO, Thiruvananthapuram 695 022, IN
1 Vikram Sarabhai Space Centre, ISRO, Thiruvananthapuram 695 022, IN
Source
Current Science, Vol 118, No 3 (2020), Pagination: 383-391Abstract
The near surface lunar plasma environment is modulated by important components like the photoelectron sheath, solar wind, lunar surface potential, etc. In situ measurements of lunar near surface plasma are not available as of now. Previous lunar missions which explored the near surface environment have arrived at estimates of lunar photo electron densities mainly from lunar sample returns. The Chandrayaan-2 lunar mission affords a unique opportunity to explore the near surface lunar plasma environment from the lunar lander platform. A Langmuir probe is developed indigenously for probing the tenuous lunar near surface plasma environment from the top deck of the lunar lander. The probe is designed to cater to a wide dynamic range of 10/cc to 10,000/cc. The probe behaviour is characterized in the ambient room conditions using a current source. The sensitivity of the probe to incoming ionized species is also characterized in a vacuum chamber. The Langmuir probe response is characterized such that the input current to the probe is correctly deciphered during the mission duration. The calibration of the present Langmuir probe is carried out using a standard calibrated Langmuir probe. The details of the theoretical simulations of the expected currents, the characterization and calibration activities are presented and discussed.Keywords
Debye Length, Electron Density, Electron Temperature, Langmuir Probe.Full Text
References
- Freeman Jr, J. W. and Hills, H. U., Positive ions at the Apollo 12 ALSEP site resulting from the Apollo 13 S-IV B Impact. EOS, 1970, 51, 821.
- Freeman Jr, J. W., Energetic ion bursts on the nightside of the Moon. J. Geophys. Res., 1972, 77(1), 239–243.
- O’Brien, B. J. and Reasoner, D. L., Charged particle lunar environment experiment, Apollo 14 Preliminary Science Report, NASA Spec. Publ., 1971, 272, 193.
- Neugebauer, M., Snyder, C. W., Clay, D. R. and Goldstein, B. E., Solar wind observations on the lunar surface with the Apollo-12 Alsep. Planet. Space Sci., 1972, 20, 1577.
- Berg, O. E., Richardson, F. F. and Burton, H., Lunar ejecta an meteorites experiment. In APOLLO 17 Preliminary Science Report, NASA SP-330, 1973, p. 16.
- Berg, O. E., Richardson, F. F., Ree, J. W. and Auer, S., Preliminary results of a cosmic dust experiment on the Moon. Geophys. Res. Lett., 1974, 1(7), 289–290; doi:10.1029/GL001i007p00289.
- Reasoner, D. L. and Burke, W. J., Characteristics of the lunar photoelectron layer in the geomagnetic tail. J. Geophys. Res., 1972, 77, 6671.
- Reasoner, D. L. and Burke, W. J., Direct observations of the lunar photoelectron layer. Proceedings of the Third Lunar Science Conference, Supplement 3, Geochim. Cosmochim. Acta, 1972, 3, 2639.
- Rich, F. J., David, L, Reasoner and William, J. B., Plasma sheet at lunar distance: characteristics and interactions with lunar surface. J. Geophys. Res., 1973, 78, 8097.
- Savich, N. A., Lunar plasma model. Space Res., 1976, 16, 941–943.
- Feuerbacher, B., Anderegg, M., Fitton, B., Laude, L. D. and Willis, R. F., Photoemission from lunar surface fines and the lunar photo electron sheath. Proceedings of the third lunar science conference (Supplement 3, Geochim. Cosmochim. Acta), The MIT Press, 1972, 3, 2655–2663.
- Willis, R. F., Anderegg, M., Feuerbacher, B. and Fitton, B., Photoemission and secondary electron emission from lunar surface material. In Photon and Particle Interactions With Surfaces in Space (eds Grard, R. J. L. and Reidel, D.), Dordrecht, The Netherlands, pp. 389–401.
- Sternovsky, Z., Chamberlin, P., Horanyi, M., Robertson, S. and Wang, X., Variability of the lunar photoelectron sheath and dust mobility due to solar activity. J. Geophys. Res., 2008, 113, A10104; doi:10.1029/2008JA013487.
- Imamura, T. et al., Radio occultation measurement of the electron density near the lunar surface using a subsatellite on the SELENE mission. J. Geophys. Res., 2012, 117, A06303; doi:10.1029/ 2011JA017293.
- Vyshlov, A. S., Preliminary results of circumlunar plasma research by the Luna 22 spacecraft. Space Res., 1976, 16, 945–949.
- Vyshlov, A. S., Savich, N. A., Vasilyev, M. B., Samoznaev, L. N., Sidorenko, A. I. and Shtern, D. Y., Some results of cislunar plasma research. NASA Tech. Rep., 1976, 397, 81–85.
- Stern, S. A., The lunar atmosphere: history, status, current, problems, and context. Rev. Geophys., 1999, 16, 941–943.
- Choudhary, R. K., Ambili, K. M., Choudhury, S., Dhanya, M. B. and Bhardwaj, A., On the origin of the ionosphere at the Moon using results from Chandrayaan-1 S band radio occultation experiment and a photochemical model. Geophys. Res. Lett., 2016, 43, 10025–10033; doi:10.1002/2016GL07061.
- Langmuir, I. and Mott-Smith, H., The theory of collectors in gaseous discharges. Phys. Rev., 1926, 28, 727–763.
- Spencer, N. W., Brace, L. H., Carignan, G. R., Taeusch, D. R. and Niemann, H., Electron and molecular nitrogen temperature and density in the thermosphere. J. Geophys. Res., 1965, 70(11), 2665–2698.
- Prakash and Subbaraya, Langmuir probe for the measurement of electron density and electron temperature in the ionosphere, Rev. Sci. Instrum., 1967, 38(5), 1132–1136.
- Smith, L. G., Small rocket instrumentation techniques (ed. Maeda, K. I.), North Holland Publishing, Amsterdam, 1969, p. 1.
- Stubbs, T. J., Glenar, D. A., Farrell, W. M., Vondrak, R. R., Collier, M. R., Halekas, J. S. and Delory, G. T., On the role of dust in the lunar ionosphere. Planet. Space Sci., 2011, 59, 1659–1664.
- Manju, G. et al., A Novel probe for in situ electron density and neutral wind (ENWi) measurements in the near Earth space. J. Atmos. Sol. Terr. Phys., 2012, 74, 81–86.
- Manju, G., Sridharan, R., Sudha Ravindran, Madhav Haridas, M. K., Pant, T. K., Sreelatha, P. and Mohan Kumar, S. V., Rocket borne in situ electron density and neutral wind measurements in the equatorial ionosphere results from the January 2010 annular solar eclipse campaign from India. J. Atmos. Sol.-Terr. Phys., 2012, 86, 56–64.
- Manju, G., Madhav Haridas, M. K., Ramkumar, G., Pant, T. K., Sridharan, R. and Sreelatha, P., Gravity wave signatures in the dip equatoria ionosphere–thermosphere system during the annular solar eclipse of 15 January 2010. J. Geophys. Res.: Space Phys., 2014, 19, 4929–4937; http://dx.doi.org/10.1002/2014JA019865.
- Design, Development and Flight Performances of Deceleration System
Abstract Views :108 |
PDF Views:54
Authors
Affiliations
1 Aerospace Mechanisms Group, Mechanisms & Vehicle Integration Testing Entity, Vikram Sarabhai Space Centre, Indian Space Research Organisation, Thiruvananthapuram 695 547, IN
1 Aerospace Mechanisms Group, Mechanisms & Vehicle Integration Testing Entity, Vikram Sarabhai Space Centre, Indian Space Research Organisation, Thiruvananthapuram 695 547, IN
Source
Current Science, Vol 120, No 1 (2021), Pagination: 122-128Abstract
Human Spaceflight Programme (HSP) of Indian Space Research Organisation is proposed with the objective of carrying two crew members to low Earth orbit and bring them back safely to a predetermined location on Earth. The deceleration system for the programme has been designed for a 4-tonne class payload and shall cater to the requirements of nominal as well as abort missions. In order to finalize the parachute configurations and deployment sequence, detailed studies and development tests, starting from wind tunnel tests to full-scale air-drop tests were carried out. After successful structural and functional qualification of the parachutes and the various subsystems, the system was used to safely recover the module in the Crew Module Atmospheric Re-entry Experiment, the first unmanned spaceflight of HSP. This article provides details on the system configurations, deployment sequence and numerous tests that have been carried out till now in order to make the system worthy of manned flights in future.Keywords
Abort Missions, Deceleration System, Deployment Sequence Parachutes, Manned Flights.Full Text
References
- Aggarwal, A., Paul, J., Nalluveettil, S. J., Purushothaman, P. and Premdas, M., Crew Module deceleration system integration for CARE mission – development challenges. In National Conference on Recent Trends in Aerospace Systems Integration and Testing, IPRC/ISRO, Mahendragiri, 2015.
- Knacke, T. W., Parachute Recovery Systems Design Manual, Report Number NWC TP 6575, Naval Weapons Center, China Lake, CA, 1991.