Download or read book A Comparison of Multiple Techniques for the Reconstruction of Entry Descent and Landing Trajectories and Atmospheres written by Grant Wells and published by . This book was released on 2011 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: The primary importance of trajectory reconstruction is to assess the accuracy of pre-flight predictions of the entry trajectory. While numerous entry systems have flown, often these systems are not adequately instrumented or the flight team not adequately funded to perform the statistical engineering reconstruction required to quantify performance and feed-forward lessons learned into future missions. As such, entry system performance and reliability levels remain unsubstantiated and improvement in aerothermodynamic and flight dynamics modeling remains data poor. The comparison is done in an effort to quantitatively and qualitatively compare Kalman filtering methods of reconstructing trajectories and atmospheric conditions from entry systems flight data. The first Kalman filter used is the extended Kalman filter. Extended Kalman filtering has been used extensively in trajectory reconstruction both for orbiting spacecraft and for planetary probes. The second Kalman filter is the unscented Kalman filter. Additionally, a technique for using collocation to reconstruct trajectories is formulated, and collocation's usefulness for trajectory simulation is demonstrated for entry, descent, and landing trajectories using a method developed here to deterministically find the state variables of the trajectory without nonlinear programming. Such an approach could allow one to utilize the same collocation trajectory design tools for the subsequent reconstruction.

Download or read book Advances in Spacecraft Atmospheric Entry Guidance written by Joel Benito Manrique and published by . This book was released on 2010 with total page 197 pages. Available in PDF, EPUB and Kindle. Book excerpt: In order to advance entry guidance technology two different research areas have been explored with the objective of increasing the reachable landing area and the landing accuracy for future Mars missions. Currently only the northern hemisphere of Mars is available for landing due to its low elevation. Only low elevation landing sites have the necessary atmospheric density to allow landing using current Entry, Descent and Landing (EDL) technology. In order to reach most of the Ancient Highlands, the majority of the southern hemisphere, advanced EDL technology is needed in multiple fields, including entry guidance. The first research area is the definition and applications of reachable and controllable sets for entry. The definition of the reachable and controllable sets provides a framework for the study of the capabilities of an entry vehicle in a given planet. Reachable and controllable sets can be used to comprehensively characterize the envelope of trajectories that a vehicle can fly, the sites it can reach and the entry states that can be accommodated. The sets can also be used for the evaluation of trajectory planning algorithms and to assist in the selection of the entry or landing sites. In essence, the reachable and controllable sets offer a powerful vehicle and trajectory analysis and design framework that allows for better mission design choices. In order to illustrate the use of the sets, they are computed for a representative Mars mission using two different vehicle configurations. The sets characterize the impact of the vehicle configuration on the entry capability. Furthermore, the sets are used to find the best skip-entry trajectory for a return from the Moon mission, highlighting the utility of the sets in atmospheric maneuvers other than entry. The second research area is the development of the components of an entry guidance algorithm that allow high elevation landing and provide as well high landing accuracy. The approach taken follows the acceleration guidance approach successfully used in missions like the Space Shuttle. Based on this approach, a new planner has been developed that is computationally fast and provides trajectories with both high final altitude and high control authority. A new tracking law based on nonlinear predictive control has been developed to track the reference trajectory. The new tracking law accounts for control saturation, which is a common feature of trajectories in the thin Martian atmosphere with a low lift vehicle. Finally, a final position guidance algorithm that aligns the vehicle's heading towards the target and provides altitude and range control, has been developed. The new guidance algorithm provides increased accuracy as well as higher final altitude compared to an entry guidance algorithm representative of the current capabilities.

Download or read book Statistical Entry Descent and Landing Flight Reconstruction with Flush Air Data System Observations Using Inertial Navigation and Monte Carlo Techniques written by Rafael Andres Lugo and published by . This book was released on 2014 with total page 133 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Entry Descent and Landing with Propulsive Deceleration written by Bryan Palaszewski and published by BiblioGov. This book was released on 2013-07 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: The future exploration of the Solar System will require innovations in transportation and the use of entry, descent, and landing (EDL) systems at many planetary landing sites. The cost of space missions has always been prohibitive, and using the natural planetary and planet s moons atmospheres for entry, descent, and landing can reduce the cost, mass, and complexity of these missions. This paper will describe some of the EDL ideas for planetary entry and survey the overall technologies for EDL that may be attractive for future Solar System missions.

Download or read book International Aerospace Abstracts written by and published by . This book was released on 1999 with total page 974 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Statistical Entry Descent and Landing Flight Reconstruction with Flush Air Data System Observations using Inertial Navigation and Monte Carlo Techniques written by Tara Krystyna Shollenberger and published by . This book was released on 2014 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Entry Descent and Landing with Propulsive Deceleration written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2019-01-22 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: The future exploration of the Solar System will require innovations in transportation and the use of entry, descent, and landing (EDL) systems at many planetary landing sites. The cost of space missions has always been prohibitive, and using the natural planetary and planet s moons atmospheres for entry, descent, and landing can reduce the cost, mass, and complexity of these missions. This paper will describe some of the EDL ideas for planetary entry and survey the overall technologies for EDL that may be attractive for future Solar System missions. Palaszewski, Bryan Glenn Research Center NASA/TM-2012-217745, AIAA Paper 2009-521, E-18480

Download or read book Simulation Framework for Rapid Entry Descent and Landing Edl Analysis written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2019-01-15 with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt: The NASA Engineering and Safety Center (NESC) was requested to establish the Simulation Framework for Rapid Entry, Descent, and Landing (EDL) Analysis assessment, which involved development of an enhanced simulation architecture using the Program to Optimize Simulated Trajectories II (POST2) simulation tool. The assessment was requested to enhance the capability of the Agency to provide rapid evaluation of EDL characteristics in systems analysis studies, preliminary design, mission development and execution, and time-critical assessments. Many of the new simulation framework capabilities were developed to support the Agency EDL Systems Analysis (EDL-SA) team, that is conducting studies of the technologies and architectures that are required to enable higher mass robotic and human mission to Mars. The findings of the assessment are contained in this report. Murri, Daniel G. Langley Research Center NASA/TM-2010-216867/VOL1, NESC-RP-09-00530, NF1676L-11761, L-19944

Download or read book Simulation Framework for Rapid Entry Descent and Landing Edl Analysis Phase 2 Results written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-22 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt: The NASA Engineering and Safety Center (NESC) was requested to establish the Simulation Framework for Rapid Entry, Descent, and Landing (EDL) Analysis assessment, which involved development of an enhanced simulation architecture using the Program to Optimize Simulated Trajectories II simulation tool. The assessment was requested to enhance the capability of the Agency to provide rapid evaluation of EDL characteristics in systems analysis studies, preliminary design, mission development and execution, and time-critical assessments. Many of the new simulation framework capabilities were developed to support the Agency EDL-Systems Analysis (SA) team that is conducting studies of the technologies and architectures that are required to enable human and higher mass robotic missions to Mars. The findings, observations, and recommendations from the NESC are provided in this report. Murri, Daniel G. Langley Research Center MARS MISSIONS; LANDING; DESCENT; SUPPORT SYSTEMS; TRAJECTORIES; SYSTEMS ANALYSIS; TIME DEPENDENCE; ROBOTICS; MISSION PLANNING; SIMULATION; SAFETY

Download or read book Cassini Huygens Probe Entry Descent and Landing Edl at Titan Independent Technical Assessment written by National Aeronautics Administration and published by CreateSpace. This book was released on 2014-11-22 with total page 122 pages. Available in PDF, EPUB and Kindle. Book excerpt: Starting in January 2004, the NESC has received several communications from knowledgeable technical experts at NASA expressing shared concerns (mainly at the Langley Research Center (LaRC) and Ames Research Center (ARC)) about Huygens mission success. It was suggested that NASA become more technically involved directly in the analysis of Huygens' entry, descent and landing (EDL) focusing on the following primary concerns: 1. The parachute deployment trigger performance and the resultant effects on the operation of the parachute system, and 2. The determination of the radiative heating environment at Titan by ESA and the corresponding thermal protection system (TPS) response. A NESC Team was formed and tasked to provide an independent assessment of these concerns. Tasks required for this independent assessment included: 1. Development of an aerodynamics database for the entry configuration. 2. Development of an aerodynamic database for the probe under each of the three parachutes. 3. Development of an opening loads model for each of the three parachutes. 4. Development of detailed aerothermal environments. These environments were comprised of the convective (laminar and turbulent) and radiative heat rates and integrated heat loads. 5. Update of the Titan atmosphere model to include the Cassini observation of Titan on November 15, 2004 (Project has denoted this as the "TA" pass). 6. Development of a Monte Carlo trajectory simulation analysis capability. 7. Determination of entry flight path angle that maximizes the mission success probability. 8. Determination of the TPS evaluation trajectories. 9. Determination of applicability and appropriateness of radiative heating models. 10. TPS performance assessment.

Download or read book Trajectory Design and Analysis for Titan Explorer Entry Descent and Landing written by Jody L. Fisher and published by . This book was released on 2005 with total page 224 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Simulation Framework for Rapid Entry Descent and Landing Analysis Phase 2 Results written by Nasa Technical Reports Server (Ntrs) and published by BiblioGov. This book was released on 2013-06 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt: The NASA Engineering and Safety Center (NESC) was requested to establish the Simulation Framework for Rapid Entry, Descent, and Landing (EDL) Analysis assessment, which involved development of an enhanced simulation architecture using the Program to Optimize Simulated Trajectories II simulation tool. The assessment was requested to enhance the capability of the Agency to provide rapid evaluation of EDL characteristics in systems analysis studies, preliminary design, mission development and execution, and time-critical assessments. Many of the new simulation framework capabilities were developed to support the Agency EDL-Systems Analysis (SA) team that is conducting studies of the technologies and architectures that are required to enable human and higher mass robotic missions to Mars. The findings, observations, and recommendations from the NESC are provided in this report.

Download or read book Simulation Framework for Rapid Entry Descent and Landing Analysis written by Nasa Technical Reports Server (Ntrs) and published by BiblioGov. This book was released on 2013-07 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt: The NASA Engineering and Safety Center (NESC) was requested to establish the Simulation Framework for Rapid Entry, Descent, and Landing (EDL) Analysis assessment, which involved development of an enhanced simulation architecture using the Program to Optimize Simulated Trajectories II (POST2) simulation tool. The assessment was requested to enhance the capability of the Agency to provide rapid evaluation of EDL characteristics in systems analysis studies, preliminary design, mission development and execution, and time-critical assessments. Many of the new simulation framework capabilities were developed to support the Agency EDL Systems Analysis (EDL-SA) team, that is conducting studies of the technologies and architectures that are required to enable higher mass robotic and human mission to Mars. The findings of the assessment are contained in this report.

Download or read book Simulation Framework for Rapid Entry Descent and Landing Analysis written by Daniel G. Murri and published by BiblioGov. This book was released on 2013-07 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: The NASA Engineering and Safety Center (NESC) was requested to establish the Simulation Framework for Rapid Entry, Descent, and Landing (EDL) Analysis assessment, which involved development of an enhanced simulation architecture using the Program to Optimize Simulated Trajectories II (POST2) simulation tool. The assessment was requested to enhance the capability of the Agency to provide rapid evaluation of EDL characteristics in systems analysis studies, preliminary design, mission development and execution, and time-critical assessments. Many of the new simulation framework capabilities were developed to support the Agency EDL Systems Analysis (EDL-SA) team, that is conducting studies of the technologies and architectures that are required to enable higher mass robotic and human mission to Mars. The appendices to the original report are contained in this document.

Download or read book Simulation Framework for Rapid Entry Descent and Landing EDL Analysis Phase 2 Results written by Daniel G. Murri and published by . This book was released on 2011 with total page 43 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Entry Descent and Landing Systems Analysis written by Nasa Technical Reports Server (Ntrs) and published by BiblioGov. This book was released on 2013-07 with total page 222 pages. Available in PDF, EPUB and Kindle. Book excerpt: NASA senior management commissioned the Entry, Descent and Landing Systems Analysis (EDL-SA) Study in 2008 to identify and roadmap the Entry, Descent and Landing (EDL) technology investments that the agency needed to successfully land large payloads at Mars for both robotic and human-scale missions. Year 1 of the study focused on technologies required for Exploration-class missions to land payloads of 10 to 50 mt. Inflatable decelerators, rigid aeroshell and supersonic retro-propulsion emerged as the top candidate technologies. In Year 2 of the study, low TRL technologies identified in Year 1, inflatables aeroshells and supersonic retropropulsion, were combined to create a demonstration precursor robotic mission. This part of the EDL-SA Year 2 effort, called Exploration Feed Forward (EFF), took much of the systems analysis simulation and component model development from Year 1 to the next level of detail.

Download or read book Entry Descent and Landing with Propulsive Deceleration Supersonic Retropropulsion Wind Tunnel Testing and Shock Phenomena written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2019-01-14 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: The future exploration of the Solar System will require innovations in transportation and the use of entry, descent, and landing (EDL) systems at many planetary landing sites. The cost of space missions has always been prohibitive, and using the natural planetary and planet's moon atmospheres for entry, and descent can reduce the cost, mass, and complexity of these missions. This paper will describe some of the EDL ideas for planetary entry and survey the overall technologies for EDL that may be attractive for future Solar System missions. Future EDL systems may include an inflatable decelerator for the initial atmospheric entry and an additional supersonic retropropulsion (SRP) rocket system for the final soft landing. A three engine retropropulsion configuration with a 2.5 in. diameter sphere-cone aeroshell model was tested in the NASA Glenn Research Center's 1- by 1-ft (1×1) Supersonic Wind Tunnel (SWT). The testing was conducted to identify potential blockage issues in the tunnel, and visualize the rocket flow and shock interactions during supersonic and hypersonic entry conditions. Earlier experimental testing of a 70deg Viking-like (sphere-cone) aeroshell was conducted as a baseline for testing of a SRP system. This baseline testing defined the flow field around the aeroshell and from this comparative baseline data, retropropulsion options will be assessed. Images and analyses from the SWT testing with 300- and 500-psia rocket engine chamber pressures are presented here. In addition, special topics of electromagnetic interference with retropropulsion induced shock waves and retropropulsion for Earth launched booster recovery are also addressed. Palaszewski, Bryan Glenn Research Center NASA/TM-2014-217891, AIAA Paper 2013-0027, E-18702