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At least 235 records · Page 13
All sourcesNASA NTRSDOE OSTI
NASA NTRS1999

Aeroservoelastic and Flight Dynamics Analysis Using Computational Fluid Dynamics

This document in large part is based on the Masters Thesis of Cole Stephens. The document encompasses a variety of technical and practical issues involved when using the STARS codes for Aeroservoelastic analysis of vehicles. The document covers in great detail a number of technical issues and step-by-step details involved in the simulation of a system where aerodynamics, structures and controls are tightly coupled. Comparisons are made to a benchmark experimental program conducted at NASA Langley. One of the significant advantages of the methodology detailed is that as a result of the technique used to accelerate the CFD-based simulation, a systems model is produced which is very useful for developing the control law strategy, and subsequent high-speed simulations.

Arena, Andrew S., Jr.↗
NASA NTRS2002

Flight Dynamic Model Exchange using XML

The AIAA Modeling and Simulation Technical Committee has worked for several years to develop a standard by which the information needed to develop physics-based models of aircraft can be specified. The purpose of this standard is to provide a well-defined set of information, definitions, data tables and axis systems so that cooperating organizations can transfer a model from one simulation facility to another with maximum efficiency. This paper proposes using an application of the eXtensible Markup Language (XML) to implement the AIAA simulation standard. The motivation and justification for using a standard such as XML is discussed. Necessary data elements to be supported are outlined. An example of an aerodynamic model as an XML file is given. This example includes definition of independent and dependent variables for function tables, definition of key variables used to define the model, and axis systems used. The final steps necessary for implementation of the standard are presented. Software to take an XML-defined model and import/export it to/from a given simulation facility is discussed, but not demonstrated. That would be the next step in final implementation of standards for physics-based aircraft dynamic models.

Jackson, E. Bruce↗
NASA NTRS2005

Application of Piloted Simulation to High-Angle-of-Attack Flight-Dynamics Research for Fighter Aircraft

This paper reviews the use of piloted simulation at Langley Research Center as part of the NASA High-Angle-of-Attack Technology Program (HATP), which was created to provide concepts and methods for the design of advanced fighter aircraft. A major research activity within this program is the development of the design processes required to take advantage of the benefits of advanced control concepts for high-angle-of-attack agility. Fundamental methodologies associated with the effective use of piloted simulation for this research are described, particularly those relating to the test techniques, validation of the test results, and design guideline/criteria development.

Ogburn, Marilyn E.↗
NASA NTRS2008

Low-Speed Flight Dynamic Tests and Analysis of the Orion Crew Module Drogue Parachute System

A test of a dynamically scaled model of the NASA Orion Crew Module (CM) with drogue parachutes was conducted in the NASA-Langley 20-Foot Vertical Spin Tunnel. The primary test objective was to assess the ability of the Orion Crew Module drogue parachute system to adequately stabilize the CM and reduce angular rates at low subsonic Mach numbers. Two attachment locations were tested: the current design nominal and an alternate. Experimental results indicated that the alternate attachment location showed a somewhat greater tendency to attenuate initial roll rate and reduce roll rate oscillations than the nominal location. Comparison of the experimental data to a Program To Optimize Simulated Trajectories (POST II) simulation of the experiment yielded results for the nominal attachment point that indicate differences between the low-speed pitch and yaw damping derivatives in the aerodynamic database and the physical model. Comparisons for the alternate attachment location indicate that riser twist plays a significant role in determining roll rate attenuation characteristics. Reevaluating the impact of the alternate attachment points using a simulation modified to account for these results showed significantly reduced roll rate attenuation tendencies when compared to the original simulation. Based on this modified simulation the alternate attachment point does not appear to offer a significant increase in allowable roll rate over the nominal configuration.

Hahne, David E.↗
NASA NTRS2016

Earth Observation System Flight Dynamics System Covariance Realism

This presentation applies a covariance realism technique to the National Aeronautics and Space Administration (NASA) Earth Observation System (EOS) Aqua and Aura spacecraft based on inferential statistics. The technique consists of three parts: collection calculation of definitive state estimates through orbit determination, calculation of covariance realism test statistics at each covariance propagation point, and proper assessment of those test statistics.

A-Train↗
NASA NTRS2016

Summary of the Second High-Altitude, Supersonic Flight Dynamics Test for the LDSD Project

NASA’s Low-Density Supersonic Decelerator Project is developing and testing the next generation of supersonic aerodynamic decelerators for planetary entry. A key element of that development is the testing of full-scale articles in conditions relevant to their intended use, primarily in the tenuous Mars atmosphere. To achieve this testing, the LDSD project developed a new test architecture for the qualification of their supersonic parachute. A large, helium filled scientific balloon is used to hoist a 4.7 m blunt body test vehicle to an altitude of approximately 32 kilometers. The test vehicle is released from the balloon, spun up for gyroscopic stability, and accelerated to over four times the speed of sound and an altitude of 50 kilometers using a large solid rocket motor. Once at those conditions, the vehicle is despun and the test period begins.

Clark, Ian↗
NASA NTRS2003

Modeling of MARSIS segmented booms and predictions of in-flight dynamics of the Mars Express Spacecraft

In this paper we provide an independent modeling and dynamic analysis of the MARSIS Antenna segmented booms deployed on the Mars Express Spacecraft. The Mars Express Mission is a joint NASA/ESA Cooperative project. The Mars Express Spacecraft being built by ESA will be launched in June 2003 and arrive at Mars in December 2003 to begin a four year study of the planet's atmosphere, surface, and subsurface. The Mars Advanced Radar for Subsurface and Ionospheric Mapping (MARSIS), provided by NASA and managed by JPL, is a key instrument in the search for water on Mars. Our objective was to determine the antenna's dynamic interaction with the spacecraft bus (or central rigid body).

dynamics↗
NASA NTRS2016

DSENDS: multi-mission flight dynamics simulator for NASA missions

Increasingly complex space missions require powerful and flexible simulation environments in order to design, analyze, and operate the missions. NASA’s Jet Propulsion Laboratory has created the DSENDS simulation environment that addresses these needs for a wide range of space missions. In this paper, we describe the DSENDS simulation environment and the key architectural components that make DSENDS a useful simulation and analysis framework. We also overview a variety of NASA missions and flight experiments that are using DSENDS.

Sklyanskiy, Evgeniy↗
NASA NTRS2017

Flight Dynamics of Mars Helicopter

Starting with the first attempted flybys of Mars in the 1960s, human exploration of the Red Planet has evolved through ever-more sophisticated means, with the use of orbiters, stationary landers, and more recently rovers that have traveled over distances of tens of kilometers in search of new knowledge. Yet, despite discussion since the early days of space exploration, no mission has so far attempted to unlock the aerial dimension of Mars exploration through the use of atmospheric flyers. This could be about to change, as NASA is currently considering sending a small helicopter to the Martian surface as part of a future mission, as a technology demonstration to verify the feasibility and utility of using helicopters for future Mars exploration. The use of helicopters promises to bridge a resolution gap in current Mars exploration capabilities—betweeen orbiters providing large-area imagery at low resolution, and rovers that provide detailed imagery limited by line-of-sight from the current rover location. Paired with a rover, a helicopter can act as a forward reconnaisance platform, helping to identify promising science targets or mapping the terrain ahead of the rover. Looking further ahead, helicopters may one day carry their own science payloads to areas that are inaccessible to rovers.

San Martin, Miguel↗