Lunar navigation study, sections 1 through 7 Final report, Jun. 1964 - May 1965
Lunar navigation analysis using passive nongyro, inertial navigation, and radio frequency technology
LUNAR LANDING MODULE↗
SEARCH · Search NASA
Results for “Navigation”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
Phase Difference Navigation Satellite Study Interim Scientific Report
Performance analysis and implementation of marine and air navigation and traffic control system using navigation satellite
AIR TRAFFIC CONTROL↗
(abstract) Galileo Navigation: Launch to Jupiter Orbit
The Galileo spacecraft was launched on October 18, 1989. After a 3.7 billion kilometer journey lasting just over six years, the Galileo Orbiter and Probe arrived at Jupiter on December 7, 1995. The atmospheric Probe survived its atmospheric entry and successfully transmitted data to the Orbiter flying overhead. To date, the Orbiter has successfully completed the first three of the ten planned satellite encounters. Navigation for the Galileo Mission has proved to be a unique and challenging task. The challenges and results of navigating Galileo through the interplanetary transfer to Jupiter, delivery of the atmospheric entry Probe, Jupiter orbit insertion, and the orbital tour are presented in this paper.
Galileo Jupiter navigation orbits gravity assists ↗
Dynamic Optimization of Multi-Spacecraft Relative Navigation Configurations in the Earth-Moon System
In this paper, the notion of relative navigation introduced by Hill, Lo and Born is analyzed for a large class of periodic orbits in the Earth-Moon three-body problem, due to its potential in supporting Moon exploration efforts. In particular, a navigation metric is introduced and used as a cost function to optimize over a class of periodic orbits. While the problem could be solve locally as an optimal control problem, a dynamical based approach that allows for a global/systematic view of the problem is proposed. First, the simpler problem of multiple spacecraft placement on a given periodic orbit is solved before the notion of continuation and bifurcation analysis is used to expand the range of solutions thus obtained.
Three Body Problem↗
Optical Navigation Plan and Strategy for the Lunar Lander Altair
This paper reviews the currently planned Altair Optical Navigation (OpNav) system. The discussion includes description of the OpNav camera manifest. The Altair OpNav plan envisions one, OpNav camera assembly, with perhaps a functional backup that includes a wide angle-imager (of 40 deg to 60 deg field of view - FOV), and a narrow angle imager (of 1 to 3 deg FOV) co-mounted on a 2-degree-of-freedom gimbal. Both imagers are assumed to be relatively wide aperture and large dynamic range to provide excellent short-exposure images at mid-latitudes, and adequate images of longer-exposure near the poles. Landmark modeling and tracking methodology is discussed, including the stereophotoclinometry method assumed to be used to obtain high-accuracy terrain maps at lunar landing sites of 1 - 2 m, and 50 - 100 m elsewhere, using the images expected to be obtained from the Lunar Reconnaissance Orbiter (LRO). Characteristics of the OpNav navigation system are discussed and architecture and results from landing simulations presented, showing expected landing accuracies of better than 10m.
TAG↗
ARTSN: Prototype for an Automated Real-Time Spacecraft Navigation System
The Automated Real-Time Spacecraft Navigation system (ARTSN) is a prototype of a new class of software for automated spacecraft navigation and monitoring.
Automated↗
Navigation Application Programming Interface Route Fuel Saving Opportunity Assessment on Large-Scale Real-World Travel Data for Conventional Vehicles and Hybrid Electric Vehicles
The green-routing strategy instructing a vehicle to select a fuel-efficient route benefits the current transportation system with fuel-saving opportunities. This paper introduces a navigation application programming interface (API), route fuel-saving evaluation framework for estimating fuel advantages of alternative API routes based on large-scale, real-world travel data for conventional vehicles (CVs) and hybrid electric vehicles (HEVs). Navigation APIs, such as Google Directions API, integrate traffic conditions and provide feasible alternative routes for origin-destination pairs. This paper develops two link-based fuel-consumption models stratified by link-level speed, road grade, and functional class (local/non-local), one for CVs and the other for HEVs. The link-based fuel-consumption models are built by assigning travel from many global positioning system driving traces to the links in TomTom MultiNet and road grade data from the U.S. Geological Survey elevation data set. Fuel consumption on a link is computed by the proposed model. This paper envisions two kinds of applications: (1) identifying alternate routes that save fuel, and (2) quantifying the potential fuel savings for large amounts of travel. An experiment based on a large-scale California Household Travel Survey global positioning system trajectory data set is conducted. The fuel consumption and savings of CVs and HEVs are investigated. At the same time, the trade-off between fuel saving and travel time due to choosing different routes is also examined for both powertrains.
33 ADVANCED PROPULSION SYSTEMS↗
Problems in space navigation and guidance.
Navigation and guidance problems involving flight path calculations and spacecraft state vector evaluation, using Mars midcourse navigation as example
FLIGHT PATH↗
Laser-Based Relative Navigation and Guidance for Space Shuttle Proximity Operations
American manned spacecraft have used visual piloting techniques in the terminal phase of randezvous during the Gemini, Apollo, Skylab, and Space Shuttle programs. In the last several years, space- shuttle astronauts have used the Rendezvous and Proximity Operations Program (RPOP), running; on a laptop computer, as a guidance and navigation aid during proximity operations. By processing measurements to the target satellite taken by a laser sensor, RPOP provides the shuttle crew with a more accurate relative position and velocity than from any other source. The inclusion of guidance algorithms allows RPOP to determine delta-velocities to fly very efficient, repeatable trajectories. This paper will focus on the guidance and navigation algorithms in RPOP, as well as results from simulation and flight. Although developed for shuttle proximity operations, the RPOP algorithms have potential applicability to an automated vehicle.
Laser sensors↗
Interplanetary navigation overview
For this presentation, we will go over some of the steps needed to navigate a spacecraft from Earth orbit to Mars. We will assume that we have a suitable set of solar system ephemerides. We will come up with a simple travel plan for a trajectory from Earth to Mars. Finally, we will address the role of frequency and timing in navigation.
navigation orbit determination tracking data↗
The Production and Archiving of Navigation and Ancillary Data for the Galileo Mission
The Galileo Mission to Jupiter is using the SPICE formats developed by the Navigation and Ancillary Information Facility, a node of the Planetary Data System, to archive its navigation and ancillary data.
SPICE formats navigation and ancillary data C kern↗
Navigation Demonstration of Precision S/X Ban Ranging with the Ulysses Spacecraft
While Earth orbiting spacecraft navigation has routinely been able to use various sorts of range data at accuracies of 2 meters or better, interplanetary spacecraft navigation using long data arcs has had to artificially deweight range data to 1 kilometer or more, ....
Ulysses modelling range biases interplanetary spac↗
Navigation challenges for the orbit phase of NEAR Shoemaker
This paper will show the unique features of navigation and mission design related to orbiting an asteroid and to designing a robust navigation system for the NEAR spacecraft.
Discovery navigation asteroids NEAR↗
Cassini tour navigation strategy
The Cassini-Huygens spacecraft was launched on October 15, 1997 as a joint NASA/ESA mission to explore Saturn. After a 7 year cruise the spacecraft will enter orbit around Saturn on 1 July 2004 for a 4 year investigation of the Saturnian system. The Cassini Navigation Team is responsible for designing the reference trajectory and conducting operations to realize this design. This paper describes the strategy for achieving project requirements, the characteristics of the Cassini navigation challenge, and the underlying assumptions.
Saturn↗
Navigator program risk management
In this paper, program risk management as applied to the Navigator Program: In Search of New Worlds will be discussed. The Navigator Program's goals are to learn how planetary systems form and to search for those worlds that could or do harbor life.
risk management↗
Interplanetary optical navigation 101
The JPL Navigation and Mission Design Section has two related tasks: Mission Design: calculate a nominal trajectory which meets the diverse needs of the scientists on a particular mission. Locate deterministic maneuvers required to fly the nominal trajectory, while locating statistical maneuvers which correct errors in the actual trajectory. Navigation estimates the flight path of a spacecraft (orbit determination) using three fundamental data sets: ground based astrometric data; radio metric tracking data (Doppler, range).
mission design↗
Mars Exploration Rover - a new standard for interplanetary navigation
The twin Mars Exploration Rovers, Spirit and Opportunity, arrived at Mars for landings respectively at Gusev Crater (on January 4, 2004) and Meridiani Planum (on January 25, 2004). During the development of the mission, the capability of the navigation system to deliver the landers within a particular accuracy played a major role in landing site selection. This process ultimately resulted in commitments to deliver each lander within a specified landing ellipse (about 70 km x 5 km) determined to be safe for landing and also judged to be scientifically interesting. Achieving atmospheric entry delivery accuracies consistent with this landing requirement necessitated significant improvements to the interplanetary navigation system used for MER. These improvements included new processes and software for orbit determination, aggressive, mission-critical use of interferometric ADOR tracking data, propulsive maneuver design, and entry, descent, and landing (EDL) trajectory simulation. Because these advances pressed the state -of -the art, innovative methods to verify the assumptions in the pre-launch covariance analyses were also developed. The actual achieved atmospheric entry accuracies for Spirit and Opportunity significantly bettered the requirements.
navigation↗
Real Time Mars Approach Navigation Aided by the Mars Network
A NASA Mars technology project is described that is building a prototype embedded real time Mars approach navigation capability which can be hosted on the Mars Network's Electra transceiver. The paper motivates the reason for doing real time Mars approach navigation via a set of analyses demonstrating its utility for enabling Mars pin-point landing (< 1-km landing error). The development approach, software design, and test results are discussed. Finally, the way forward towards a flight demonstration on the Mars Science Laboratory is presented.
embedded software↗