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At least 739 records · Page 41
All sourcesNASA NTRSDOE OSTI
NASA NTRSDate not supplied

Investigating Solar Radiation Pressure Modeling for Operations in Near Rectilinear Halo Orbit

NASA’s Gateway program will build a crew-tended station in an Earth-Moon Near Rectilinear Halo Orbit (NRHO). Deep space operations differ considerably from Low Earth Orbit (LEO) operations in the environmental modeling, orbit geometry, and propagation timespans in operations. The cislunar environment, as opposed to the LEO environment, lacks atmospheric drag and is simultaneously affected by the gravity of both the Earth and the Moon, and solar radiation pressure (SRP) has a significant effect. This paper investigates the impacts of various SRP models on prediction accuracy, attitude control accuracy, orbit determination performance, and computational burden.

Guidance↗
NASA NTRSDate not supplied

Orbit Maintenance Burn Details for Spacecraft in a Near Rectilinear Halo Orbit

The baseline orbit for Gateway is a Near Rectilinear Halo Orbit (NRHO) in a 9:2 resonance with the lunar synodic period. A spacecraft in this slightly unstable NRHO requires orbit maintenance (OM) for long-duration operations. An updated OM algorithm is described, including a discussion of desirable OM burn location along the NRHO and the effects of changing weighting parameters and tolerances. The directions of the OM burns are explored in depth, both in the Earth-Moon rotating frame and from a Sun-relative perspective. A technique to augment the OM algorithm to enable long-term operations in NRHO is outlined, and the effects of constraints on OM attitudes are investigated.

Diane C. Davis↗
NASA NTRS2022

X-Ray Morphology of Cluster-Mass Haloes in Self-Interacting Dark Matter

We perform cosmological zoom-in simulations of 19 relaxed cluster-mass haloes with the inclusion of adiabatic gas in the cold dark matter (CDM) and self-interacting dark matter (SIDM) models. These clusters are selected as dynamically relaxed clusters from a parent simulation with M200(1-3) × 10 15 M. Both the dark matter and the intracluster gas distributions in SIDM appear more spherical than their CDM counterparts. Mock X-ray images are generated based on the simulations and are compared to the real X-ray images of 84 relaxed clusters selected from the Chandra and ROSAT archives. We perform ellipse fitting for the isophotes of mock and real X-ray images and obtain the ellipticities at cluster-centric radii of r0.1–0.2R 200 .The X-ray isophotes in SIDM models with increasing cross-sections are rounder than their CDM counterparts, which manifests as asystematic shift in the distribution function of ellipticities. Unexpectedly, the X-ray morphology of the observed non-cool-coreclusters agrees better with SIDM model swith cross-section (σ/m)=0.5–1cm2g−1 than CDM and SIDM with (σ/m)=0.1cm2g−1. Our statistical analysis indicates that the latter two models are disfavoured at the 68 percent confidence level (as conservative estimates). This conclusion is not altered by shifting the radial range of measurements or applying a temperature selection criterion. However, the primary uncertainty originates from the lack of baryonic physics in the adiabatic model, such as cooling, star formation and feedback effects, which still have the potential to reconcile CDM simulations with observations.

dark matter – cosmology↗
NASA NTRSDate not supplied

Perturbations and Recovery in the Gateway Near Rectilinear Halo Orbit

The Gateway and CAPSTONE spacecraft are planned to orbit the Moon in a Near Rectilinear Halo Orbit (NRHO) that experiences a 9:2 resonance with the lunar synodic period. Disturbances applied to spacecraft in this NRHO must be corrected to achieve a reasonable lifetime in orbit. This investigation explores the variations between a spacecraft operating under nominal orbit maintenance and the baseline NRHO. The effects of perturbations on an unmaintained spacecraft are examined, with a focus on the time to depart the NRHO. Finally, the costs of correcting disturbances of varying magnitudes are computed using a simple but robust orbit maintenance algorithm.

Diane C. Davis↗
NASA NTRSDate not supplied

Maneuver Reconstruction, Tracking Scheduling, and Bias Estimation in the Near Rectilinear Halo Orbit (NRHO)

NASA’s Gateway program will build a crew-tended station in an Earth-Moon Near Rectilinear Halo Orbit (NRHO) to support deep space missions to the lunar surface and heliocentric space. The station in the NRHO will be tracked by the Deep Space Network (DSN) with 2-way radiometric tracking data to produce an estimated state that is utilized to target Orbit Maintenance Maneuvers (OMMs). However, the tracking data is corrupted with measurement noise and range bias, which results in state estimation error and OMM execution error. This paper reports on analysis performed to improve the geometry of the tracking data problem with the inclusion of cross-hemispheric partner sites and explores the performance impact of handovers between partner sites and DSN sites. The OMM execution error is estimated directly using a Batch Least Squares (BLS) process, and the range bias estimation is analyzed among both original DSN sites and a combined DSN + partner sites scenario.

Clark P Newman↗
NASA NTRSDate not supplied

Robust Trajectory Design for Rendezvous in a Near Rectilinear Halo Orbit

Future NASA Artemis missions will require complex docking plans between the Orion capsule and Lunar Gateway that meet predetermined safety constraints while minimizing fuel usage and state uncertainty at rendezvous. In this paper, linear covariance analysis is applied to a first order relative form of Near-Rectilinear Halo Orbit dynamics to determine the nominal trajectories and state dispersions associated with various maneuver profiles in the Sun-referenced Local Vertical Local Horizontal reference frame of the lunar Gateway. These maneuver profiles are optimized using a particle swarm optimizer and direct search algorithm to find trajectories that satisfy approach corridor, free drift, velocity magnitude, under-burn, and maneuver transfer time safety constraints to 3-sigma certainty.

Linear Covariance Analysis↗
NASA NTRSDate not supplied

Linear Covariance Techniques to Analyze a Multi-Vehicle, Multi-GN&C System with Applications to Rendezvous in a Near Rectilinear Halo Orbit

Typically for a rendezvous and docking scenario, only a single vehicle is considered the active vehicle. As a result, the target vehicle’s GN&C system is typically not a factor in the integrated performance analysis as it assumes a passive role. However, for upcoming NASA Artemis missions the active vehicle is both the chaser and target spacecraft. In addition, both vehicles are cooperating with one another, sharing telemetry data, and relying on data extracted from the GN&C system of the other. The process also includes a team of ground support personnel in mission control are tracking and monitoring each spacecraft uplinking state estimates and targeting solutions to support mission operations and enhance the onboard flight system performance. Being able to quickly analyze the impact of both vehicles with two different GN&C systems that also interact with the ground that does its own navigation and targeting uploads is critical. This paper outlines how to perform this rapid analysis using linear covariance techniques and applies them to a rendezvous scenario initiated in low lunar orbit and completed in a Near Rectilinear Halo Orbit (NRHO) representative of the NASA Artemis III mission.

Linear Covariance Analysis↗
NASA NTRSDate not supplied

HaloSat – A CubeSat that Studied the Hot Galactic Halo

HaloSat was the first CubeSat competitively funded by NASA's Astrophysics Division. HaloSat surveyed the sky in the soft (0.4-2 keV) band with the goal of studying diffuse X-ray emission from highly ionized oxygen in the circumgalactic medium (CGM) of the Milky Way (MW). The HaloSat science instrument (shown above ) contained three nominally identical X-ray detectors. The field of view had full response over a 10° diameter, tapering to zero response at 14° diameter. The detectors were sensitive in the 0.4-7 keV band. Typical halo spectra are shown below. The figure of merit for observing diffuse emission, survey grasp, is the product of effective area and solid angle of the field of view, AΩ. HaloSat has a small effective area, but a large field of view, giving it a grasp competitive with major missions. HaloSat’s grasp (17.6 cm 2 deg 2 at 600 eV) was larger than Chandra’s at launch (8.7 cm 2 deg 2 ). HaloSat data are archived at the HEASARC by a collaboration between NASA/MSFC, UI, and GSFC. See poster 104.01 by Jesse Bluem for details. HaloSat was built and operated by the University of Iowa (UI), NASA/GSFC, Johns Hopkins University, the Laboratoire Atmosphères, Observations Spatiales (LATMOS), and Blue Canyon Technologies.

HaloSat↗
NASA NTRSDate not supplied

Baseline Orbit Generation for Near Rectilinear Halo Orbits

A Near Rectilinear Halo Orbit (NRHO) with an eclipse-favorable phase serves as the current baseline orbit for the Gateway mission. The baseline provides a catalog of orbit maintenance targets and serves as a reference path for other types of trajectory analysis. In this investigation, an automated multiple-shooting differential corrections strategy is developed to generate many-revolution, long-duration, ballistic baseline orbits in a higher-fidelity ephemeris force model at the eclipse-avoidant phases and at other alternative phases. Additional geometric considerations for eclipse avoidance in the NRHO are presented and utilized within a long-lead orbit maintenance-based phase shift strategy.

Emily M. Zimovan-Spreen↗
NASA NTRSDate not supplied

Jettison and Disposal From Near Rectilinear Halo Orbits, Part 2: Applications

Objects deployed from a Near Rectilinear Halo Orbit (NRHO) experience simultaneous gravitational forces from the Moon, the Earth, and the Sun, and post-deployment behavior is complex. The current investigation applies the theories explored in Part 1 of the study to examine the dynamics of objects deployed from the Gateway NRHO to heliocentric space. Examples include jettison of cubesats and logistics modules as well as end-of-life options for the Gateway itself. Recontact risk with the Gateway as each object departs the lunar vicinity is explored, and both the immediate destination and the long-term fate of the deployed objects are assessed.

Diane C. Davis↗
NASA NTRSDate not supplied

Jettison and Disposal from Near Rectilinear Halo Orbits, Part 1: Theory

The proposed Gateway spacecraft in a Near Rectilinear Halo Orbit (NRHO) will be a human outpost in cislunar space. The baseline mission may experience the deployment of visiting vehicles, cubesats, and on-orbit debris. Departure from the NRHO and cislunar space is nontrivial due to the complex gravitational environment that persists in and around Gateway. Long-term disposal orbits in heliocentric space offer safe destinations for deployed objects. To mitigate risks associated with conjunctions between Gateway and deployed objects, strategies to identify risk-avoidant paths to heliocentric space are necessary for Gateway mission operations.

Stephen T. Scheuerle↗
NASA NTRSDate not supplied

Perturbation Modeling and Navigation Tuning for a Crewed Station in Near Rectilinear Halo Orbit

NASA's Gateway program will build a crew-tended station in an Earth-Moon Near Rectilinear Halo Orbit (NRHO) to support deep space missions to the lunar surface and heliocentric space. The station in the NRHO will be visited by crewed vehicles including lunar landers that are high mass relative to Gateway. Docking events with large vehicles induce significant thruster plume and docking contact velocity perturbations. Crewed vehicles induce significant venting perturbations that can stress the navigation filter's ability to remain converged about an estimated state. The torques that arise from venting and lunar gravity gradient require reaction control system (RCS) thruster intervention, which themselves induce a velocity perturbation. The best method to model RCS thruster perturbations is currently in development. This paper simulates different RCS perturbation models, schedules, and an increasing magnitude to investigate the navigation sensitivity to different RCS perturbation models. From the RCS perturbation models simulated, a worst-case scenario is chosen for further scrutiny. The navigation filter is further tuned to handle the most disruptive perturbation modeling and the resulting performance is analyzed.

Navigation↗
NASA NTRSDate not supplied

An Orbit Determination Comparison Study and Demonstration for Rendezvous and Docking in a Near Rectilinear Halo Orbit from the Lunar Surface

For the upcoming NASA Artemis III mission and those that follow, both the Human Landing System (HLS) and Orion programs are invested in understanding the impacts of ground tracking performance in supporting rendezvous and docking in a Near Rectilinear Halo Orbit (NRHO). Several critical questions must be answered to ensure mission success and crew safety and an assortment of analysis tools are being incorporated to address them. Two of these tools, LINCOV and MONTE, are currently providing program decision making results through HLS Insight, HLS NASA-collaborations, and Orion/Gateway cross-program analysis. To ensure consistency in the orbit determination performance, a comparison trade-study is performed using a low-lunar orbit to NRHO rendezvous scenario anticipated for the upcoming Artemis missions. An overview of the two analysis tools is provided along with a detailed step-by-step evaluation of the core capabilities and models related to the orbit determination process. This incremental comparison effort reveals both tools produce consistent solutions for the criteria investigated. Given the confidence in the orbit determination process and solutions generated, these results are then applied to demonstrate an integrated, closed-loop system performance where the HLS lander ascends from the lunar surface and successfully inserts into the NRHO relative to the Orion spacecraft in preparation for the final rendezvous and docking phase.

Linear Covariance Analysis↗
NASA NTRS2024

Assessment of Base Loads Generated by an Exercise Device in the HALO Module

The purpose of this document is to prescribe a uniform procedure that can be used to postprocess base loads generated by a crew member and an exercise device in the Gateway Habitation and Logistics Outpost (HALO) module. This memo has three primary sections. First, the exercise loads pass through a Vibration Isolation and Stabilization (VIS) system notionally depicted in Figure 1 for the purpose of preliminary analyses. This is described in Section 2. Next, these loads are processed in frequency domain as explained in Section 3. Finally, the resulting outputs are compared with a Gateway Program Loads and Dynamics (L&D) allocation given to the VIS system. This information is provided in Section 4.

Exercise↗
NASA NTRSDate not supplied

Autonomous Burn Targeting for a Lunar Sortie Staged From a Near-Rectilinear Halo Orbit

NASA is planning manned lunar landings starting in the mid 2020s as part of its Artemis program. These lunar sortie missions will be staged from a Near-Rectilinear Halo Orbit (NRHO), with a requirement for the lander to autonomously determine the timing and targets for multiple burns so that it can navigate its way back to the staging vehicle in the NRHO. The lander mission profile transitions through multiple gravitational regimes, at times influenced equally by 3rd bodies (Earth and Sun) as much as by the Moon, while at other times the lander is primarily influenced by lunar gravitation. These different gravitational regimes pose challenges to guidance and targeting logic. The present work describes options for autonomous logic for each of several major maneuvers of the lunar sortie, including numerical techniques to incorporate the effect of 3rd bodies. Throughout the development there is an emphasis on simplicity and computational efficiency.

NRHO↗
DOE OSTI2021

Faint galaxies and small halos : probes of galaxy formation and dark matter

This thesis addresses the intersection of dark matter and galaxy formation physics by modeling the faintest galaxies in the Universe in a cosmological context. In the first part of this work, I present an empirical model for the connection between faint galaxies and small dark matter halos. Combining this model with tailored cosmological simulations of Milky Way analogs and state-of-the-art satellite galaxy observations yields new insights into dwarf galaxy formation and hierarchical structure formation. Next, I show that these same dwarf galaxy observations place stringent constraints on microphysical dark matter properties including its warmth, self-interactions, Standard Model interactions, minimum particle mass, and formation epoch. Finally, I describe a unified framework that combines dark matter constraints from dwarf galaxies and strong gravitational lensing, paving the way for next-generation surveys of small-scale cosmic structure to deliver unprecedented insights into dark matter physics.

Nadler, Ethan Oliver↗