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Human Landing System Storable Propellant Architectures: Mission Design, Guidance, Navigation, and Control
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In-Situ Radio-Metric Tracking to Support Navigation for Interplanetary Missions with Multiple Spacecraft
Doppler and ranging measurements between spacecraft can be obtained only when the ratio of the total received signal power to noise power density at the receiving spacecraft is sufficiently large that reliable signal detection can be achieved within a reasonable time period.
Navigation and guidance programming for long duration orbital missions Summary report
Navigation and guidance programming for long duration orbital missions
Low-cost inertial navigation for moderate-g missions
A low cost inertial navigation system (INS) concept is described for flight missions characterized by moderate accelerations and limited attitude variations. These missions involve general aviation aircraft, helicopters, or remotely piloted vehicles. The significance of the moderate acceleration and limited attitude is reviewed with respect to platform mechanization and instrumentation. A hybrid mechanization, partially gimballed and partially strapdown, is presented. The INS is implemented by an unbalanced two axis gimbal system and controlled by a two degree of freedom gyro. The INS provides locally level two axis acceleration information along with pitch and roll measurements. Heading information is provided by a second gyro mounted in the inner gimbal. The system error model is equivalent to that of a conventional platform with a tilt error determined by the integral of the gyro drift rate and an equivalent accelerometer type errors are also cancelled. Rapid gyro-compassing, implemented with opened gimbal control loops, and a strapdown procedure provides calibration of gyro drift rate biases.
Independent Optical Navigation Processing for the Osiris-Rex Mission Using the Goddard Image Analysis and Navigation Tool
The OSIRIS-REx mission to the asteroid(101955) Bennu heavily relies on optical navigation to provide relative state information between the asteroid and the spacecraft. These measurements enable determination of the spacecraft's orbit to the tight requirements needed to meet the science goals of the mission. In this document we describe the algorithms and techniques used by the Goddard independent verification and validation navigation effort to extract these measurements from the images taken by the spacecraft during the mission.We also demonstrate the capabilities of the techniques by showing the high accuracy of the results when used in an orbit determination solution.
Navigation of 1975 Mars Viking mission.
This paper describes the Viking mission objectives and overall navigation profile from trans-Mars injection through the post-landing station-keeping phase. Included are interplanetary trajectory corrections, Mars orbit insertion, satellite orbit trims to acquire the landing site, lander separation and deorbit, entry, landing, and, finally, orbiter station keeping with the lander. The broad spectrum of navigation activities has strongly influenced the design of the Viking spacecraft and mission. The paper discusses fuel requirements to account for trajectory dispersions and uncertainties, requirements for navigation hardware and software, expected inflight uncertainties, satellite orbit adjustment for landing site acquisition, lander targeting techniques, lander trajectory reconstruction, and lander position determination.
Validation of a Low-Thrust Mission Design Tool Using Operational Navigation Software
Design of flight trajectories for missions employing solar electric propulsion requires a suitably high-fidelity design tool. In this work, the Evolutionary Mission Trajectory Generator (EMTG) is presented as a medium-high fidelity design tool that is suitable for mission proposals. EMTG is validated against the high-heritage deep-space navigation tool MIRAGE, demonstrating both the accuracy of EMTG's model and an operational mission design and navigation procedure using both tools. The validation is performed using a benchmark mission to the Jupiter Trojans.
Validation of a Low-Thrust Mission Design Tool Using Operational Navigation Software
Design of flight trajectories for missions employing solar electric propulsion requires a suitably high-fidelity design tool. In this work, the Evolutionary Mission Trajectory Generator (EMTG) is presented as a medium-high fidelity design tool that is suitable for mission proposals. EMTG is validated against the high-heritage deep-space navigation tool MIRAGE, demonstrating both the accuracy of EMTG's model and an operational mission design and navigation procedure using both tools. The validation is performed using a benchmark mission to the Jupiter Trojans.
Control, guidance, and navigation for advanced manned missions. Volume 4 - Inertial subsystems Final report
Application and evaluation of strapdown inertial systems for control, guidance, and navigation of advanced manned missions
A Performance-Based Comparison of Deep-Space Navigation using Optical-Communication and Conventional Navigation Techniques: Small Body Missions
Optical communications may be used in future NASA deep-space missions, resulting in much higher data transfer rates. Those optical communication links could also be used for navigation purposes. The performance of deep-space navigation for an asteroid flyby mission using ground-based optical tracking and conventional navigation techniques was investigated in this work. We present the results of variety of asteroid flyby scenarios including low phase and high phase approach angle flybys, one slow flyby in a Trojan tour mission, and also one slow flyby in a Psyche mission. In this task, four different types of observables were simulated, namely ground-based radiometric, spacecraft on-board optical, ground-based optical tracking of spacecraft (astrometry and 2-way range magnitude), and ground-based asteroid astrometry. Different combinations of these four types of observables were compared with currently in-practice ground-based radiometric/on-board optical measurements. The results showed that the ground-based optical tracking is promising and could be a potential candidate for future deep-space navigation. Precise astrometry is not possible for active comets.
A Performance-Based Comparison of Deep-Space Navigation using Optical-Communication and Conventional Navigation Techniques: Small Body Missions
Optical communications may be used in future NASA deep-space missions, resulting in much higher data transfer rates. Those optical communication links could also be used for navigation purposes. The performance of deep-space navigation for an asteroid flyby mission using ground-based optical tracking and conventional navigation techniques was investigated in this work. We present the results of variety of asteroid flyby scenarios including low phase and high phase approach angle flybys, one slow flyby in a Trojan tour mission, and also one slow flyby in a Psyche mission. In this task, four different types of observables were simulated, namely ground-based radiometric, spacecraft on-board optical, ground-based optical tracking of spacecraft (astrometry and 2-way range magnitude), and ground-based asteroid astrometry. Different combinations of these four types of observables were compared with currently in-practice ground-based radiometric/on-board optical measurements. The results showed that the ground-based optical tracking is promising and could be a potential candidate for future deep-space navigation. Precise astrometry is not possible for active comets.
Small optical navigation camera for interplanetary missions
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Control, guidance, and navigation for advanced manned missions. Volume 1 - Systems Final report
Advanced computer, radiation, and inertial subsystem guidance and navigation requirements of interplanetary manned space flight missions