NASA Logo, External Link
Facebook icon, External Link to NASA STI page on Facebook Twitter icon, External Link to NASA STI on Twitter YouTube icon, External Link to NASA STI Channel on YouTube RSS icon, External Link to New NASA STI RSS Feed AddThis share icon
 

Record Details

Record 9 of 845
Micro Navigator
Author and Affiliation:
Blaes, B. R.(Jet Propulsion Lab., California Inst. of Tech., Pasadena, CA United States)
Kia, T.(Jet Propulsion Lab., California Inst. of Tech., Pasadena, CA United States)
Chau, S. N.(Jet Propulsion Lab., California Inst. of Tech., Pasadena, CA United States)
Abstract: Miniature high-performance low-mass space avionics systems are desired for planned future outer planetary exploration missions (i.e. Europa Orbiter/Lander, Pluto-Kuiper Express). The spacecraft fuel and mass requirements enabling orbit insertion is the driving requirement. The Micro Navigator is an integrated autonomous Guidance, Navigation & Control (GN&C)micro-system that would provide the critical avionics function for navigation, pointing, and precision landing. The Micro Navigator hardware and software allow fusion of data from multiple sensors to provide a single integrated vehicle state vector necessary for six degrees of freedom GN&C. The benefits of this MicroNavigator include: 1) The Micro Navigator employs MEMS devices that promise orders of magnitude reductions in mass power and volume of inertial sensors (accelerometers and gyroscopes), celestial sensing devices (startracker, sun sensor), and computing element; 2) The highly integrated nature of the unit will reduce the cost of flight missions. a) The advanced miniaturization technologies employed by the Micro Navigator lend themselves to mass production, and therefore will reduce production cost of spacecraft. b) The integral approach simplifies interface issues associated with discrete components and reduces cost associated with integration and test of multiple components; and 3) The integration of sensors and processing elements into a single unit will allow the Micro Navigator to encapsulate attitude information and determination functions into a single object. This is particularly beneficial for object-oriented software architectures that are used in advanced spacecraft. Additional information is contained in the original extended abstract.
Publication Date: Jan 01, 2001
Document ID:
20010041208
(Acquired May 18, 2001)
Subject Category: LUNAR AND PLANETARY SCIENCE AND EXPLORATION
Document Type: Conference Paper
Publication Information: Forum on Innovative Approaches to Outer Planetary Exploration 2001-2020; 9; (LPI-Contrib-1084); (SEE 20010041202)
Financial Sponsor: Jet Propulsion Lab., California Inst. of Tech.; Pasadena, CA United States
Organization Source: Jet Propulsion Lab., California Inst. of Tech.; Pasadena, CA United States
Description: In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: AUTONOMOUS NAVIGATION; MINIATURIZATION; MULTISENSOR FUSION; SPACE NAVIGATION; SPACECRAFT GUIDANCE; MICROELECTROMECHANICAL SYSTEMS; ACCELEROMETERS; GYROSCOPES
Availability Notes: Abstract Only; Available from STI Support Services only as part of the entire parent document
› Back to Top
Find Similar Records
NASA Logo, External Link
NASA Official: Gerald Steeman
Site Curator: STI Program
Last Modified: May 08, 2015
Contact Us