scholarly journals Obstacle Detection and Avoidance Method to Achieve a Soft Landing on the Moon and Planets

2002 ◽  
Vol 38 (4) ◽  
pp. 395-403 ◽  
Author(s):  
Ken'ichi NISHIGUCHI
Keyword(s):  
Obstacle Detection ◽  
The Moon ◽  
Soft Landing

scholarly journals Obstacle Detection Method for a Soft Landing on the Moon.

2000 ◽  
Vol 48 (554) ◽  
pp. 55-60 ◽  
Author(s):  
Ken'ichi NISHIGUCHI ◽  
Shoji YOSHIKAWA ◽  
Takahiro KINOSHITA
Keyword(s):  
Detection Method ◽  
Obstacle Detection ◽  
The Moon ◽  
Soft Landing

scholarly journals The Claim for a first insight of Vikram Lander on moon

2020 ◽  
Author(s):  
jagmohan saxena
Keyword(s):  
Surface Composition ◽  
Light Condition ◽  
Space Research ◽  
The Moon ◽  
Lunar Orbiter ◽  
Soft Landing ◽  
Indian Space Research Organisation ◽  
Research Organisation ◽  
Launch Site ◽  
The Impact

The Claim for a First insight of Viram Lander on Moon.CHANDRAYAAN- 2 is the second lunar exploration mission developed by the Indian Space Research Organisation (ISRO), after Chandrayaan-1. As of September 2019, it consists of a lunar orbiter, which included the Vikram lander, andPragyan -the lunar rover. All of which were developed in India. The main scientific objective of this mission was to map and study the variations in lunar surface composition, as well as the location and abundance of lunar water.Chandrayaan-2 Chandrayaan-2 composite (Tecnical Specifications Mission type-Lunar orbiter, Lander and RoverOperator Indian Space Research Organisation (ISRO)COSPAR ID2019-042ASATCAT no.44441Websitewww.isro.gov.in/chandrayaan2-home-0Mission duration-Orbiter: ~ 7 yearsVikram lander: 14 days (planned) ;[1][2]Achieved: 0 days (landing failure)Pragyan rover: 14 days (planned);[2]Achieved: 0 days (landing failure)Spacecraft properties Manufacturer:Indian Space Research Organisation (ISRO)Launch mass Combined (wet) : 3,850 kg(8,490 lb) [3][4][5]Combined (dry): 1,308 kg (2,884 lb)[6]Orbiter (wet): 2,379 kg (5,245 lb)[4][5]Orbiter (dry): 682 kg (1,504 lb)[6]Vikram lander (wet): 1,471 kg (3,243 lb)[4][5]Vikram lander (dry): 626 kg (1,380 lb)[6]Pragyan rover: 27 kg (60 lb)[4] [5] PowerOrbiter: 1 kW (1.3 hp)[7]Vikram lander: 650 W[8]Pragyan rover: 50 W[8] Start of Mission Launch date:22 July 2019, 14:43:12 IST (09:13:12 UTC)[9]Rocket- GSLV Mark III M1[10] [11]Launch site-Satish Dhawan Space Centre (Second Launch Pad )Agency- Indian Space Research Organisation (ISRO)Moon orbiter Orbital insertion: 20 August 2019, - 09:02 IST(03:32UTC)[12[13]Orbital parameters-Pericynthion altitude100 km (62 mi)[14] Apocynthion altitude100 km (62 mi)[14]Moon lander Space craft component Rover Landing date: 7 September 2019, 01:53 IST (failure)(6 September 2019, 20:23 UTC)[13][15]Landing site Lunar south pole (intended)Chandrayaan programme - Scheduled as-← Chandrayaan-1<-- Chandrayaan-2← Chandrayaan-3 (Under Process) The Chandrayaan-2 spacecraft was launched on its mission to the Moon from the second launch pad at the Satish Dhawan Space Centre at Andhra Pradesh on 22 July 2019 at 2.43 p.m. IST (09:13 UTC) by a GSLV Mark III M1. The craft reached the Moon's orbit on 20 August 2019 and began orbital positioning manoeuvres for the Landing of the Vikram lander at Moon Surface. The Lander and the Rover were scheduled to land on the near side of the Moon, in the south polar region at a latitude of about 70° South on 6 September 2019 and conduct scientific experiments for one lunar day, which approximates to two Earth weeks. A successful soft landing of the Lander would have made India the fourth country after the Soviet Union, United States and China to do so.However, the lander deviated from its intended trajectory while attempting to land on 6 September 2019, which caused a 'hard landing. According to a failure analysis report submitted to ISRO, the crash was caused by a software glitch. In the quest to locate the lost Lander, Two subsequent image sequences were acquired on October 14,15 and November 11, 2019 .The LROC team scoured the surrounding area in these new mosaics and found the impact site at 70.8810 degree South, 22.7840 degrees East, 834 m elevation and was supposed with associated debris field. The November 2019 mosaic had the best pixel scale 0.7 meter/ per pixel , With a better light condition . Though, no any claim since been made about the wellness of Vikram Lander. An effort is being made by (me) Mr Jagmohan saxena to find the whereabouts of the (lost ) Vikram Lander and it is supposed that the Pics of Vikram Lander found are exactly on the same Southpole Coordinates (near site) where it was intended to touch down for a soft landing. IT is -70.88087° Latitude and 24.26206° Longitude with a pixel size of 0.50m/px. The final Version of CONFIRMATION of location of Vikram Lander at moon is seek Officially with the launching agency ISRO. JAGMOHAN SAXENA 1 E 19 JNV colony, Bikaner [email protected] Reference- Chandrayaan-2, Wikipedialroc.asu.eduNASASpace.com

scholarly journals Chandrayaan-2: A Memorable Mission Conducted by ISRO

2020 ◽  
pp. 43-57
Author(s):  
Buddhadev Sarkar ◽  
Pabitra Kumar Mani
Keyword(s):  
Scientific Information ◽  
Space Missions ◽  
Dark Side ◽  
Water Molecules ◽  
South Pole ◽  
The Moon ◽  
The South ◽  
Soft Landing ◽  
Lunar Mission ◽  
Satellite Launch Vehicle

Aims: The Chandrayaan-2 aims to wave the Indian flag on the dark side (South Pole) of the Moon that had never been rendered by any country before. The mission had conducted to gather more scientific information about the Moon. There were three main components of the Chandrayann-2 spacecraft- an orbiter, a lander, and a rover, means to collect data for the availability of water in the South Pole of the Moon. Place and Duration of Study: The rover (Pragyan) was designed to operate for one Lunar day that is equivalent to 14 Earth days, whereas the orbiter is assumed to orbit the Moon for seven years instead of the previously planned for just one year. Overview: The Chandrayaan-2 spacecraft launched by India's heavy-lift rocket Geosynchronous Satellite Launch Vehicle-Mark III (GSLV MKIII) from the Satish Dhawan Space Center launch pad located on Sriharikota island of Andhra Prades. Unlike, Chandrayaan-1, this lunar mission aimed to perform a soft-landing on the South Pole of the Lunar surface and do scientific experiments with the help of the rover (Pragyan). Reason: The Chandrayaan-1, the first lunar mission of ISRO that detected water molecules on the Moon. The Chandrayaan-2 was a follow-on mission of Chandrayaan-1 to explore the presence of water molecules on the South Pole of the Moon. Conclusion: Although the orbiter fulfilled all of the command, unfortunately, the lander (Lander) lost its communication at the last moment to touch the Moon’s surface softly. Despite that, India again showed its potential in space missions. Chandrayaan- 2 was the most low budget lunar mission ever conducted by any space organization. The developing or even underdeveloped countries may come forward in their space program as ISRO is showing a convenient way in space missions.

Autonomous soft-landing technique onto the moon in SELENE project

1998 ◽  
Author(s):  
Sumio Hikida ◽  
Haruaki Itagaki
Keyword(s):  
The Moon ◽  
Soft Landing

Soft Landing on the Moon with Mathematica

2012 ◽  
Vol 14 ◽  
Author(s):  
Marian Mureşan
Keyword(s):  
The Moon ◽  
Soft Landing

Topographic and Geomorphological Mapping and Analysis of the Chang'E-4 Landing Site on the Far Side of the Moon

2020 ◽  
Vol 86 (4) ◽  
pp. 247-258 ◽  
Author(s):  
Bo Wu ◽  
Fei Li ◽  
Han Hu ◽  
Yang Zhao ◽  
Yiran Wang ◽  
...  
Keyword(s):  
Landing Site ◽  
Joint Analysis ◽  
The Sun ◽  
The Moon ◽  
Soft Landing ◽  
Geomorphological Mapping ◽  
Von Karman ◽  
Lunar Reconnaissance Orbiter ◽  
Integrated Processing ◽  
Von Kármán

The Chinese lunar probe Chang'E-4 successfully landed in the Von Kármán crater on the far side of the Moon. This paper presents the topographic and geomorphological mapping and their joint analysis for selecting the Chang'E-4 landing site in the Von Kármán crater. A digital topographic model (<small>DTM</small>) of the Von Kármán crater, with a spatial resolution of 30 m, was generated through the integrated processing of Chang'E-2 images (7 m/pixel) and Lunar Reconnaissance Orbiter (<small>LRO</small>) Laser Altimeter (<small>LOLA</small>) data. Slope maps were derived from the <small>DTM</small>. Terrain occlusions to both the Sun and the relay satellite were studied. Craters with diameters ≥ 70 m were detected to generate a crater density map. Rocks with diameters ≥ 2 m were also extracted to generate a rock abundance map using an <small>LRO</small> narrow angle camera (<small>NAC</small>) image mosaic. The joint topographic and geomorphological analysis identified three subregions for landing. One of them, recommended as the highest-priority landing site, was the one in which Chang'E-4 eventually landed. After the successful landing of Chang'E-4, we immediately determined the precise location of the lander by the integrated processing of orbiter, descent and ground images. We also conducted a detailed analysis around the landing location. The results revealed that the Chang'E-4 lander has excellent visibility to the Sun and relay satellite; the lander is on a slope of about 4.5° towards the southwest, and the rock abundance around the landing location is almost 0. The developed methods and results can benefit future soft-landing missions to the Moon and other celestial bodies.

Lidar Technology Role in Future Robotic and Manned Missions to Solar System Bodies

2005 ◽  
Vol 883 ◽  
Author(s):  
Rosemary R. Baize ◽  
Farzin Amzajerdian ◽  
Robert Tolson ◽  
John Davidson ◽  
Richard W. Powell ◽  
...  
Keyword(s):  
Atmospheric Pressure ◽  
The Moon ◽  
Soft Landing ◽  
Landing Zone ◽  
Control Concept ◽  
Solar System Bodies ◽  
Robotic Missions ◽  
And Control ◽  
Terrain Features ◽  
Better Than

AbstractFuture planetary exploration missions will require safe and precision soft-landing to target scientifically interesting sites near hazardous terrain features, such as escarpments, craters, slopes, and rocks. Although the landing accuracy has steadily improved over time to approximately 35 km for the recent Mars Exploration Rovers due to better approach navigation, a drastically different guidance, navigation and control concept is required to meet future mission requirements. For example, future rovers will require better than 6 km landing accuracy for Mars and better than 1 km for the Moon plus 100 m maneuvering capability to avoid hazards. Laser Radar or Lidar technology can be the key to meeting these objectives since it can provide highresolution 3-D maps of the terrain, accurately measure ground proximity and velocity, and determine atmospheric pressure and wind velocity. These lidar capabilities can enable the landers of the future to identify the pre-selected landing zone and hazardous terrain features within it, determine the optimum flight path, having atmospheric pressure and winds data, and accurately navigate using precision ground proximity and velocity data. This paper examines the potential of lidar technology in future human and robotic missions to the Moon, Mars, and other planetary bodies. A guidance and navigation control architecture concept utilizing lidar sensors will be presented and its operation will be described. The performance and physical requirements of the lidar sensors will be also discussed.

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