SCIENTIFIC AND TECHNICAL AEROSPACE REPORTS
A Biweekly Publication of the National Aeronautics and Space Administration
VOLUME 44, ISSUE 11 - MAY 30, 2006
18 SPACECRAFT DESIGN, TESTING AND PERFORMANCE
Includes satellites; space platforms; space stations; spacecraft systems and components such as thermal and environmental controls; and spacecraft control and stability characteristics.
For life support systems see 54 Man/System Technology and Life Support.
For related information see also 05 Aircraft Design, Testing and Performance; 39 Structural Mechanics; and 16 Space Transportation and Safety.
20060013197 NASA Goddard Space Flight Center, Greenbelt, MD, USA
An Empirical Comparison between Two Recursive Filters for Attitude and Rate Estimation of Spinning Spacecraft
Harman, Richard R.; January 2006; 2 pp.; In English; No Copyright; Avail.: Other Sources; Abstract Only
The advantages of inducing a constant spin rate on a spacecraft are well known. A variety of science missions have used this technique as a relatively low cost method for conducting science. Starting in the late 1970s, NASA focused on building spacecraft using 3-axis control as opposed to the single-axis control mentioned above. Considerable effort was expended toward sensor and control system development, as well as the development of ground systems to independently process the data. As a result, spinning spacecraft development and their resulting ground system development stagnated. In the 1990s, shrinking budgets made spinning spacecraft an attractive option for science. The attitude requirements for recent spinning spacecraft are more stringent and the ground systems must be enhanced in order to provide the necessary attitude estimation accuracy. Since spinning spacecraft (SC) typically have no gyroscopes for measuring attitude rate, any new estimator would need to rely on the spacecraft dynamics equations. One estimation technique that utilized the SC dynamics and has been used successfully in 3-axis gyro-less spacecraft ground systems is the pseudo-linear Kalman filter algorithm. Consequently, a pseudo-linear Kalman filter has been developed which directly estimates the spacecraft attitude quaternion and rate for a spinning SC. Recently, a filter using Markley variables was developed specifically for spinning spacecraft. The pseudo-linear Kalman filter has the advantage of being easier to implement but estimates the quaternion which, due to the relatively high spinning rate, changes rapidly for a spinning spacecraft. The Markley variable filter is more complicated to implement but, being based on the SC angular momentum, estimates parameters which vary slowly. This paper presents a comparison of the performance of these two filters. Monte-Carlo simulation runs will be presented which demonstrate the advantages and disadvantages of both filters. Author
Attitude (Inclination); Estimates; Angular Momentum; Kalman Filters; Linear Filters; Spacecraft Design; Systems Engineering; Gyroscopes
20060013198 NASA Goddard Space Flight Center, Greenbelt, MD, USA
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Rigid Body Rate Inference from Attitude Variation
Bar-Itzhack, I. Y.; Harman, Richard R.; Thienel, Julie K.; [2006]; 30 pp.; In English; Original contains black and white illustrations; Copyright; Avail.: CASI: A03, Hardcopy
In this paper we research the extraction of the angular rate vector from attitude information without differentiation, in particular from quaternion measurements. We show that instead of using a Kalman filter of some kind, it is possible to obtain good rate estimates, suitable for spacecraft attitude control loop damping, using simple feedback loops, thereby eliminating the need for recurrent covariance computation performed when a Kalman filter is used. This considerably simplifies the computations required for rate estimation in gyro-less spacecraft. Some interesting qualities of the Kalman filter gain are explored, proven and utilized. We examine two kinds of feedback loops, one with varying gain that is proportional to the well known Q matrix, which is computed using the measured quaternion, and the other type of feedback loop is one with constant coefficients. The latter type includes two kinds; namely, a proportional feedback loop, and a proportional-integral feedback loop. The various schemes are examined through simulations and their performance is compared. It is shown that all schemes are adequate for extracting the angular velocity at an accuracy suitable for control loop damping. Author
Attitude Control; Angular Velocity; Kalman Filters; Quaternions; Rigid Structures; Spacecraft Control; Damping; Estimates; Loops
20060013403 NASA Kennedy Space Center, Cocoa Beach, FL, USA
Debris/Ice/TPS Assessment and Integrated Photographic Analysis of Shuttle Mission STS-105
Oliu, Armando; February 2005; 99 pp.; In English; Original contains color and black and white illustrations Report No.(s): NASA/TM-2005-211537; No Copyright; Avail.: CASI: A05, Hardcopy
The Debris Team has developed and implemented measures to control damage from debris in the Shuttle operational environment and to make the control measures a part of routine launch flows. These measures include engineering surveillance during vehicle processing and closeout operations, facility and flight hardware inspections before and after launch, and photographic analysis of mission events. Photographic analyses of mission imagery from launch, on-orbit, and landing provide significant data in verifying proper operation of systems and evaluating anomalies. In addition to the Kennedy Space Center Photo/Video Analysis, reports from Johnson Space Center and Marshall Space Flight Center are also included in this document to provide an integrated assessment of the mission. Derived from text
Space Shuttle Missions; Debris; Anomalies; Ice; Inspection; Space Transportation System; Aerospace Environments; Damage
20060013404 NASA Kennedy Space Center, Cocoa Beach, FL, USA
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Debris/Ice/TPS Assessment and Integrated Photographic Analysis of Shuttle Mission STS-108
Oliu, Armando; March 2005; 136 pp.; In English; Original contains color and black and white illustrations Report No.(s): NASA/TM-2005-212556; No Copyright; Avail.: CASI: A07, Hardcopy
The Debris Team has developed and implemented measures to control damage from debris in the Shuttle operational environment and to make the control measures a part of routine launch flows.
These measures include engineering surveillance during vehicle processing and closeout operations, facility and flight hardware inspections before and after launch, and photographic analysis of mission events.
Photographic analyses of mission imagery from launch, on-orbit, and landing provide significant data in verifying proper operation of systems and evaluating anomalies.
In addition to the Kennedy Space Center Photo/Video Analysis, reports from Johnson Space Center and Marshall Space Flight Center are also included in this document to provide an integrated assessment of the mission. Derived from text
Aerospace Environments; Space Shuttle Missions; Launching; Ice; Debris; Damage; Anomalies; Inspection
20060013405 NASA Kennedy Space Center, Cocoa Beach, FL, USA
Debris/Ice/TPS Assessment and Integrated Photographic Analysis of Shuttle Mission STS-109
Oliu, Armando; March 2005; 103 pp.; In English; Original contains color and black and white illustrations Report No.(s): NASA/TM-2005-212557; No Copyright; Avail.: CASI: A06, Hardcopy
The Debris Team has developed and implemented measures to control damage from debris in the Shuttle operational environment and to make the control measures a part of routine launch flows. These measures include engineering surveillance during vehicle processing and closeout operations, facility and flight hardware inspections before and after launch, and photographic analysis of mission events. Photographic analyses of mission imagery from launch, on-orbit, and landing provide significant data in verifying proper operation of systems and evaluating anomalies. In addition to the Kennedy Space Center Photo/Video Analysis, reports from Johnson Space Center and Marshall Space Flight Center are also included in this document to provide an integrated assessment of the mission. Derived from text
Space Shuttle Missions; Launching; Inspection; Anomalies; Aerospace Environments; Debris; Ice; Damage
20060013406 NASA Kennedy Space Center, Cocoa Beach, FL, USA
Debris/Ice/TPS Assessment and Integrated Photographic Analysis of Shuttle Mission STS-110
Oliu, Armando; March 2005; 114 pp.; In English; Original contains color and black and white illustrations Report No.(s): NASA/TM-212558; No Copyright; Avail.: CASI: A06, Hardcopy
The Debris Team has developed and implemented measures to control damage from debris in the Shuttle operational environment and to make the control measures a part of routine launch flows. These measures include engineering surveillance during vehicle processing and closeout operations, facility and flight hardware inspections before and after launch, and photographic analysis of mission events. Photographic analyses of mission imagery from launch, on-orbit, and landing provide significant data in verifying proper operation of systems and evaluating anomalies. In addition to the Kennedy Space Center Photo/Video Analysis, reports from Johnson Space Center and Marshall Space Flight Center are also included in this document to provide an integrated assessment of the mission. Derived from text
Space Shuttle Missions; Launching; Inspection; Anomalies; Debris; Damage; Ice; Aerospace Environments
20060013429 NASA Kennedy Space Center, Cocoa Beach, FL, USA
Debris/Ice/TPS Assessment and Integrated Photographic Analysis of Shuttle Mission STS-112
Oliu, Armando; Oct. 7, 2002; 126 pp.; In English; Original contains black and white illustrations Report No.(s): NASA/TM-2005-212560; No Copyright; Avail.: CASI: A07, Hardcopy
A debris/ice/thermal protection system assessment and integrated photographic analysis was conducted for Shuttle mission STS-112. Debris inspections of the flight elements and launch pad were performed before and after launch. Icing conditions on the External Tank were assessed by the use of computer programs and infrared scanned data during cryogenic loading of the vehicle, followed by on-pad visual inspection. High speed photography of the launch was analyzed to identify ice/debris sources and evaluate potential vehicle damage and/or in-flight anomalies. The report documents the debris/ice/thermal protection system conditions and integrated photographic analysis of Space Shuttle mission STS-112 and the resulting effect of the Space Shuttle Program. Author
Space Shuttle Missions; Debris; Ice Formation; Thermal Protection; Space Transportation System; Infrared Radiation; Inspection; Cryogenics; Launching
20060013482 NASA Johnson Space Center, Houston, TX, USA
Design and Certification of the Extravehicular Activity Mobility Unit (EMU) Water Processing Jumper
Peterson, Laurie J.; Neumeyer, Derek J.; Lewis, John F.; [2006]; 6 pp.; In English; International Conference of Environmental Systems, 17-20 Jul. 2006, Norfolk, VA, USA; Original contains color illustrations Contract(s)/Grant(s): 769.06.01.01.01 Report No.(s): 06ICES-169; Copyright; Avail.: Other Sources
The Extravehicular Mobility Units (EMUs) onboard the International Space Station (ISS) experienced a failure due to cooling water contamination from biomass and corrosion byproducts forming solids around the EMU pump rotor. The coolant had no biocide and a low pH which induced biofilm growth and corrosion precipitates, respectively. NASA JSC was tasked with building hardware to clean the ionic, organic, and particulate load from the EMU coolant loop before and after Extravehicular Activity (EVAs). Based on a return sample of the EMU coolant loop, the chemical load was well understood, but there was not sufficient volume of the returned sample to analyze particulates. Through work with EMU specialists, chemists, (EVA) Mission Operations Directorate (MOD) representation, safety and mission assurance, astronaut crew, and team engineers, requirements were developed for the EMU Water Processing hardware (sometimes referred to as the Airlock Coolant Loop Recovery [A/L CLR] system). Those requirements ranged from the operable level of ionic, organic, and particulate load, interfaces to the EMU, maximum cycle time, operating pressure drop, flow rate, and temperature, leakage rates, and biocide levels for storage. Design work began in February 2005 and certification was completed in April 2005 to support a return to flight launch date of May 12, 2005. This paper will discuss the details of the design and certification of the EMU Water Processing hardware and its components Author
Contamination; Coolants; Extravehicular Mobility Units; Corrosion; Biomass; By-Products; Rotors; International Space Station
20060013503 NASA Langley Research Center, Hampton, VA, USA
Planetary Airplane Extraction System Development and Subscale Testing
Teter, John E., Jr.; [2006]; 14 pp.; In English; 38th Aerospace Mechanisms Symposium, 17-19 May 2006, Williamsburg, VA, USA; Original contains color illustrations Contract(s)/Grant(s): 581.02.08.07; No Copyright; Avail.: CASI: A03, Hardcopy
The Aerial Regional-scale Environmental Survey (ARES) project employs an airplane as the science platform from which to collect science data in the previously inaccessible, thin atmosphere of Mars. In order for the airplane to arrive safely in the Martian atmosphere a number of sequences must occur. A critical element in the entry sequence at Mars is an extraction maneuver to separate the airplane quickly (in less than a second) from its protective backshell to reduce the possibility of re-contact, potentially leading to mission failure. This paper describes the development, testing, and lessons learned from building a 1/3 scale model of this airplane extraction system. This design, based on the successful Mars Exploration Rover (MER) extraction mechanism, employs a series of trucks rolling along tracks located on the surface of the central parachute can. Numerous tests using high speed video were conducted at the Langley Research Center (LaRC) to validate this concept. One area of concern was that that although the airplane released cleanly, a pitching moment could be introduced. While targeted for a Mars mission, this concept will enable environmental surveys by aircraft in other planetary bodies with a sensible atmosphere such as Venus or Saturn s moon, Titan. Author
Extraction; Scale Models; Mars Atmosphere; Mars Missions; Systems Engineering; Mars Exploration
20060013504 NASA Langley Research Center, Hampton, VA, USA
Structural Analysis and Testing of the Inflatable Re-entry Vehicle Experiment (IRVE)
Lindell, Michael C.; Hughes, Stephen J.; Dixon, Megan; Wiley, Cliff E.; [2006]; 19 pp.; In English; 47th AIAA/ASME/ ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 1-4 May 2006, Newport, RI, USA; Original contains color illustrations Contract(s)/Grant(s): 23-614-10-04-13 Report No.(s): AIAA Paper 2006-1699; Copyright; Avail.: CASI: A03, Hardcopy
The Inflatable Re-entry Vehicle Experiment (IRVE) is a 3.0 meter, 60 degree half-angle sphere cone, inflatable aeroshell experiment designed to demonstrate various aspects of inflatable technology during Earth re-entry. IRVE will be launched on a Terrier-Improved Orion sounding rocket from NASA s Wallops Flight Facility in the fall of 2006 to an altitude of approximately 164 kilometers and re-enter the Earth s atmosphere. The experiment will demonstrate exo-atmospheric inflation, inflatable structure leak performance throughout the flight regime, structural integrity under aerodynamic pressure and associated deceleration loads, thermal protection system performance, and aerodynamic stability. Structural integrity and dynamic response of the inflatable will be monitored with photogrammetric measurements of the leeward side of the aeroshell during flight. Aerodynamic stability and drag performance will be verified with on-board inertial measurements and radar tracking from multiple ground radar stations. In addition to demonstrating inflatable technology, IRVE will help validate structural, aerothermal, and trajectory modeling and analysis techniques for the inflatable aeroshell system. This paper discusses the structural analysis and testing of the IRVE inflatable structure. Equations are presented for calculating fabric loads in sphere cone aeroshells, and finite element results are presented which validate the equations. Fabric material properties and testing are discussed along with aeroshell fabrication techniques. Stiffness and dynamics tests conducted on a small-scale development unit and a full-scale prototype unit are presented along with correlated finite element models to predict the in-flight fundamental mod Author
Reentry Vehicles; Inflatable Structures; Aeroshells; Aerodynamic Stability; Structural Analysis; Aerothermodynamics; Sounding Rockets
Source: NASA
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