NDLI: Aerostats/orbiters radiometric measurement based integrated navigation for Mars descent and landing

Content Provider	IEEE Xplore Digital Library
Author	Jiang Xiuqiang Tao Ting Li Shuang
Copyright Year	2015
Description	Author affiliation: Coll. of Astronaut., Nanjing Univ. of Aeronaut. & Astronaut., Nanjing, China (Jiang Xiuqiang; Tao Ting; Li Shuang)
Abstract	Autonomous navigation is considered as a key technology for Mars landing missions. The traditional inertial navigation system (INS) and optical measurement based integrated navigation mode is quite incompetent to provide effective navigation for Mars terminal descent and landing phase with low visibility. As a necessary part of Mars lander, radio equipment can be used to support navigation system by providing beacon measurement(s) without dedicated sensor(s). This paper developed inertial measurement unit (IMU) and orbits/aerostats beacons based integrated navigation scheme for Mars powered descent and landing. The range and Doppler information sensed from orbiter and aerostats beacons and the lander's state information derived from IMU are integrated in extended Kalman filter (EKF) to correct the inertial constant bias and suppress the navigation measurement noise. Simulation results show that the localization precision is better than 10 m and the velocity precision is better than 1 m/s when the trajectories of orbiter and aerostats are set appropriately. So it is a promising and attractive autonomous navigation scheme for Mars lander even if low visibility and sandstorm occur.
Starting Page	5473
Ending Page	5478
File Size	376785
Page Count	6
File Format	PDF
ISBN	9789881563897
ISSN	19341768
DOI	10.1109/ChiCC.2015.7260495
Language	English
Publisher	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Publisher Date	2015-07-28
Publisher Place	China
Access Restriction	Subscribed
Rights Holder	Technical Committee on Control Theory, Chinese Association of Automation
Subject Keyword	Mars Noise orbiter Radio navigation aerostat Extraterrestrial measurements radiometric measurement integrated navigation Noise measurement Mathematical model Mars descent and landing
Content Type	Text
Resource Type	Article

Sl.	Authority	Responsibilities	Communication Details
1	Ministry of Education (GoI), Department of Higher Education	Sanctioning Authority	https://www.education.gov.in/ict-initiatives
2	Indian Institute of Technology Kharagpur	Host Institute of the Project: The host institute of the project is responsible for providing infrastructure support and hosting the project	https://www.iitkgp.ac.in
3	National Digital Library of India Office, Indian Institute of Technology Kharagpur	The administrative and infrastructural headquarters of the project	Dr. B. Sutradhar bsutra@ndl.gov.in
4	Project PI / Joint PI	Principal Investigator and Joint Principal Investigators of the project	Dr. B. Sutradhar bsutra@ndl.gov.in Prof. Saswat Chakrabarti will be added soon
5	Website/Portal (Helpdesk)	Queries regarding NDLI and its services	support@ndl.gov.in
6	Contents and Copyright Issues	Queries related to content curation and copyright issues	content@ndl.gov.in
7	National Digital Library of India Club (NDLI Club)	Queries related to NDLI Club formation, support, user awareness program, seminar/symposium, collaboration, social media, promotion, and outreach	clubsupport@ndl.gov.in
8	Digital Preservation Centre (DPC)	Assistance with digitizing and archiving copyright-free printed books	dpc@ndl.gov.in
9	IDR Setup or Support	Queries related to establishment and support of Institutional Digital Repository (IDR) and IDR workshops	idr@ndl.gov.in

Vision-aided inertial navigation for pin-point landing on Mars

Adaptive points range Square-root Cubature Kalman filter for mars approach navigation

Advanced communications, navigation and technology concepts for a Mars 2018 orbiter

Vision-Aided Inertial Navigation for Spacecraft Entry, Descent, and Landing

Guidance and Control Design for Powered Descent and Landing on Mars

Model study for terrain aided navigation systems

Vision-based spacecraft relative navigation using the sparse Gauss-Hermite quadrature filter

Two-stage robust extended Kalman filter in autonomous navigation for the powered descent phase of Mars EDL

Field Testing of the Mars Exploration Rovers Descent Image Motion Estimation System

Aerostats/orbiters radiometric measurement based integrated navigation for Mars descent and landing

Similar Documents

Vision-aided inertial navigation for pin-point landing on Mars

Adaptive points range Square-root Cubature Kalman filter for mars approach navigation

Advanced communications, navigation and technology concepts for a Mars 2018 orbiter

Vision-Aided Inertial Navigation for Spacecraft Entry, Descent, and Landing

Guidance and Control Design for Powered Descent and Landing on Mars

Model study for terrain aided navigation systems

Vision-based spacecraft relative navigation using the sparse Gauss-Hermite quadrature filter

Two-stage robust extended Kalman filter in autonomous navigation for the powered descent phase of Mars EDL

Field Testing of the Mars Exploration Rovers Descent Image Motion Estimation System

Aerostats/orbiters radiometric measurement based integrated navigation for Mars descent and landing