Liaison-Supplemented Navigation for Geosynchronous and Lunar L1 Orbiters
No abstract available
lunar libration orbit.↗
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Demonstration of a Precision Data Reduction Technique for Navigation of the Galileo Spacecraft
...This paper presents results from a demonstration of a new sequential filter model and data reduction technique, dubbed the enhanced filter, performed with radio tracking data obtained from the Galileo spacecraft.
Galileo interplanetary spacecraft spacecraft navig↗
Simulated trajectories error analysis program, version 2. Volume 2: Programmer's manual
A series of three computer programs for the mathematical analysis of navigation and guidance of lunar and interplanetary trajectories was developed. All three programs require the integration of n-body trajectories for both interplanetary and lunar missions. The virutal mass technique is used in all three programs. The user's manual contains the information necessary to operate the programs. The input and output quantities of the programs are described. Sample cases are given and discussed.
Vogt, E. D.↗
Impasse-driven tutoring for reactive skill acquisition
We are interested in developing effective performance-oriented training for the operation of systems that are used for monitor and control purposes. We have focused on one such system, the communications Link Monitor and Control (LMC) system used in NASA's Deep Space Network (DSN), which is a worldwide system for navigating, tracking and communicating with unmanned interplanetary spacecraft. The tasks in this domain are procedural in nature and require reactive, goal-oriented skills; we have previously described a cognitive model for problem solving that accounts for both novice and expert levels of behavior as well as how skill is acquired. Our cognitive modeling work in this task domain led us to make a number of predictions about tutoring that have influenced the design of the system described in this paper.
Hill, Randall W., Jr.↗
End-to-end information system concept for the Mars Telecommunications Orbiter
The Mars Telecommunications Orbiter (MTO) was intended to provide high-performance deep space relay links to landers, orbiters, sample-return, missions, and approaching spacecraft in the vicinity of Mars, to demonstrate interplanetary laser communications, to demonstrate autonomous navigation, and to carry out is own science investigations.
EEIS↗
End-to-end information system concept for the Mars Telecommunications Orbiter
The Mars Telecommunications Orbiter (MTO) was intended to provide high-performance deep space relay links to landers, orbiters, sample-return missions, and approaching spacecraft in the vicinity of Mars, to demostrate interplanetary laser communications, to demonstrate autonomous navigation, and to carry out its own science investigations.
MTO↗
Impasse-Driven Tutoring for Reactive Skill Acquisition
We are interested in developing effective performance-oriented training for the operation of systems that are used for monitor and control purposes. We have focused on one such system, the communications Link Monitor and Control (LMC) system used in NASA's Deep Space Network (DSN), which is a worldwide system for navigating, tracking and communicating with unmanned interplanetary spacecraft. The tasks in this domain are procedural in nature and require reactive, goal-oriented skills; we have previously described a cognitive model for problem solving that accounts for both novice and expert levels of behavior as well as how skill is acquired [Hill and Johnson, 1993]. Our cognitive modeling work in this task domain led us to make a number of predictions about tutoring that have influenced the design of the system described in this paper.
Johnson, W. Lewis↗
Mars Exploration Rovers navigation results
The twin Mars Exploration Rovers, Spirit and Opportunity, were launched on June 10, 2003(dagger), and July 8, 2003, from Cape Canaveral, Florida. Spirit and Opportunity were targeted for landings at Gusev Crater (arrival on January 4, 2004) and Meridiani Planum (arrival on January 25, 2004). The primary navigation challenge was to deliver each spacecraft to the desired atmospheric entry interface point with sufficient accuracy such that each lander would touch down within a specified landing ellipse (about 70 km x 5 km) determined to be safe for landing and also judged to be scientifically interesting. In order to achieve landing within the target ellipse, precise control of the inertial entry flight path angle (FPA) at atmospheric entry was required. The maximum allowable errors in FPA following TCM-5 (trajectory correction maneuver #5) at Entry (E) - 2 days were +/-0.12(deg) (3(sigma)) for Spirit and +/-0.14(deg) (3(sigma)) for Opportunity. Achieving these entry delivery accuracies necessitated significant improvements to the interplanetary avigation system used for MER. These improvements included new processes and software for orbit determination, propulsive maneuver design, and entry, descent, and landing (EDL) trajectory simulation. The actual achieved atmospheric entry accuracies for Spirit and Opportunity significantly exceeded the requirements. At the navigation data cutoff for the TCM-5 final design, the orbit determination FPA knowledge error was +/-0.028(deg) (3(sigma) ) for Spirit and +/-0.035(deg) (3(sigma)) for Opportunity. Because of exceptionally accurate navigation performance, TCM-5 (E - 2 days) and TCM-6 (E - 4 hours) were canceled for both Spirit and Opportunity. The actual landing locations (determined from in-situ Doppler tracking between the MER rovers and the Mars Odyssey orbiter) differed from the target landing points by 10.1 km (downtrack) for Spirit and 24.6 km (downtrack) for Opportunity. The majority of the landing position offsets for both landers was primarily caused by variations in atmosphere and spacecraft aerodynamic modeling from what was predicted. The amount of the landing position offset caused by navigation-only errors was only 3.3 km (uptrack) for Spirit and 9.7 km (downtrack) for Opportunity.
Mars Exploration Rover (MER)↗
ICE navigation support
The International Cometary Explorer (ICE) encounter with Comet Giacobini-Zinner took place 7 years after the spacecraft's original launch on 12 August 1978 as the International Sun Earth Explorer 3 (ISEE-3), part of a three-spacecraft project to study the interaction between the solar wind and the Earth's magnetosphere. Transfer to an interplanetary trajectory was performed via a 119-km-altitute, gravity-assist, lunar swingby on December 1983. Navigation support during interplanetary cruise and comet encounter was provided by orbit determination utilizing radio metric data from the DSN 64-meter antennas in Goldstone, California and Madrid, Spain. Orbit solutions yielding predictions of 50-km geocentric delivery accuracy in the target aim plane were achieved during interplanetary cruise and at comet encounter using 6-to-12-week data arcs between periodic attitude-change maneuvers. One-sigma two-way range and range rate residuals were consistently 40 meters and 0.2 mm/s or better, respectively. Non-gravitational forces affected the comet's motion during late August and early September 1985 and caused a 2300-km shift in the orbit of the comet relative to the spacecraft. This necessitated a final ICE orbit trim maneuver 3 days prior to encounter. Near-real-time assessment of two-way 2-GHz (S-band) Doppler pseudo-residuals during the June and July 1985 trajectory change maneuvers aided in calibration of the spacecraft's thrusters in preparation for this final critical maneuver. Post-flight analysis indicates tail centerline passage was achieved within 10 seconds of the predicted time and geocentric position uncertainty at encounter was less than 40 km.
Efron, L.↗
Development of Telecommunications Systems and Ground Support for EM-1 Interplanetary Cubesats Missions: Lunar IceCube and LunaH-Map
CubeSats are now providing an innovative way to explore space: they can be built by smaller teams in academic environments, and they generally require smaller budget than traditional missions. For this reason, a new trend has emerged in the last five years: interplanetary CubeSats. Interplanetary CubeSats take advantage of the CubeSat paradigm and of the availability of commercial components developed for Low Earth Orbit (LEO) missions, but they are specifically designed to explore deep space. As a result, interplanetary CubeSats are essentially very different from Low Earth Orbit CubeSats in at least three technological areas: propulsion, radiation tolerance and telecommunication. This paper is focused on telecommunication issues for interplanetary CubeSats which face harsher environments, longer path distances and have more navigation needs than the LEO CubeSats. For this reason, the design of telecommunication systems for interplanetary missions is extremely challenging and significant development is currently ongoing in the areas of radio design, antenna design and the design of ground support architectures. This presentation focuses on the design of the telecommunication and ground support systems for two of the interplanetary CubeSats missions that will be launched on NASA’s Space Launch System (SLS) Exploration Mission-1 (EM-1): Lunar IceCube and LunaH-Map. Given the commonalities between these missions, an effort is underway at JPL to develop a common set of telecommunication hardware systems to fit the envelope of the two missions’ goals. Additionally, Lunar IceCube and LunaH-Map will also share the use of the Deep Space Network antennas and of the Morehead State University 21 m station, which is currently being upgraded especially for this purpose. This presentation will provide a quick overview of the missions (including goals and telecommunication requirements) and it will also focus on the development of the telecommunication systems design with a particular focus on the current upgrades planned to the Morehead State University ground station.
Babuscia, Alessandra↗
Navigation of the 1982 Jupiter Orbiter Probe mission
A new NASA interplanetary flight project, called Jupiter Orbiter Probe (JOP), has been recently approved by Congress. JOP involves a dual mission intended to explore the planet Jupiter and its environment with an atmospheric probe and a planetary orbiter spacecraft. The probe and orbiter vehicles are to be launched in tandem as a single spacecraft during the time from December 1981 to January 1982. The spacecraft will arrive at Jupiter at the earliest on November 14, 1984. Navigating the JOP spacecraft will be a critical task for the JOP mission. Attention is given to aspects of probe and orbiter delivery, Jupiter orbit insertion and perijove raise, the Satellite Tour, navigation development and the navigation system, the probe delivery, example orbits, velocity perturbation and correction, orbit determination characteristics, orbit determination and control profile, and the correction velocity requirements.
Rourke, K. H.↗
A mission design for the Halley comet rendezvous using Ion Drive
The Ion Drive propulsion system, a derivative of the old Solar Electric Propulsion (SEP) technology is considered adequate to perform all mission objectives of a proposed Halley's comet rendezvous (scheduled for launch in 1982) except one: control of thermal energy from the concentrating solar arrays. This problem can be solved, however, by adding a separable tail probe to the baseline system. The system consists of an Ion Propulsion Module (IPM) and a Mission Module (MM). Scientific objectives include a determination of the structure of the comet nucleus, an evaluation of nucleus evolution, an assay of the comet's atmosphere and ionosphere, and a study of the interaction between the comet and the interplanetary medium. Attention is given to the navigation parameters necessary for heliocentric transfer and post-rendezvous circumnavigation of the comet.
Boain, R. J.↗
The telecommunications and data acquisition
Radio astronomy and radio interferometry at microwave frequencies are discussed. Other topics concerning the Deep Space Network include program planning, planetary and interplanetary mission support, tracking and ground based navigation, communications, and station control and system technology.
Renzetti, N. A.↗
The Venus Radar Mapper (VRM) mission
The Venus Radar Mapper (VRM) mission is sponsored by NASA to put a single spacecraft in orbit around Venus to map the surface of Venus using a synthetic aperture mapping radar. The spacecraft is scheduled to be launched in April 1988 using a Shuttle-Centaur G combination. The spacecraft arrives at Venus in late July 1988 and begins its mapping mission which lasts for one Venus rotation or 243 days. This paper describes the VRM mission at its present state of design. The science objectives and project constraints are described. Key features of the spacecraft system and radar system are discussed. The interplanetary and mapping orbit design are covered. Navigation strategy is explained, including trajectory maneuvers and mapping phase orbit determination. Finally, the mapping sequences to optimize planet coverage are described.
Cutting, E.↗
Architecture and CONOPS of Next-Generation Ground Network for Communications and Tracking of Interplanetary SmallSats
As small spacecraft venture out of Earth orbit, they will encounter challenges not experienced or addressed by the numerous low Earth orbit (LEO) CubeSat and Smallsat missions staged to date. The LEO CubeSats typically use low-cost, proven CubeSat radios, antennas, and university ground stations with small apertures. As more ambitious yet cost-constrained space mission concepts to the Moon and beyond are being developed, CubeSats and smallsats have the potential to provide a more affordable platform for exploring deep space and performing the associated science. Some of the challenges that have, so far, slowed the proliferation of small interplanetary spacecraft are those of communications and navigation.
Cheung, Kar-ming↗
Radio Navigation of Deep Space 1 During Ion Propulsion Usage
One of the main goals of the Deep Space 1 (DS1) project was to demonstrate the use of ion propulsion on an interplanetary spacecraft.
navigation flight mechanics Deep Space 1↗
Matched conic solutions to round trip interplanetary trajectory problems that insure state-vector continuity at all boundaries
Matched conic solutions to round trip interplanetary trajectory problems for use in guidance and navigation simulation
Bond, V. R.↗
Spectral factorization in periodically time-varying systems and application to navigation problems.
Spectral factorization has been used previously to derive the steady-state solution of Kalman filtering equations without iteration for constant coefficient systems. The present work extends the spectral factorization algorithm to time-varying systems having periodic coefficient matrices for cases of both discrete and continuous systems. Time-consuming, expensive iterations of sequential covariance equations are not required to reach the final solution since this is an algebraic algorithm employing existing eigenvalue, eigenvector subroutines. The computer program incorporating the algorithm is suitable for sensitivity studies in formulating navigation and guidance strategies of low-thrust interplanetary missions. The determination of an optimum tracking pattern from an earth station is examined as an example.
Nishimura, T.↗