SCIENTIFIC AND TECHNICAL AEROSPACE REPORTS
A Biweekly Publication of the National Aeronautics and Space Administration
VOLUME 44, ISSUE 12 - JUNE 20, 2006
15 LAUNCH VEHICLES AND LAUNCH OPERATIONS
Includes all classes of launch vehicles, launch/space vehicle systems, and boosters; and launch operations.
For related information see also 18 Spacecraft Design, Testing and Performance; and 20 Spacecraft Propulsion and Power.
20060014285 Air Force Research Lab., Edwards AFB, CA USA
Computer Programs for Solar Concentrator Focus Control (Preprint)
Beasley, Joseph N; Holmes, Michael R; Dec 5, 2005; 33 pp.; In English Contract(s)/Grant(s): Proj-1011 Report No.(s): AD-A441725; AFRL-PR-ED-VG-2005-416; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA441725; Avail.: CASI: A03, Hardcopy
This presentation describes two methods for imaging an absorber used as a new sensor in determining the location of the focal spot for a solar concentrator. The absorber is used as a sensor in both methods, but in slightly different ways. The first method developed is an optimization method inspired by Shack-Hartmann wave front sensing. This optimization utilizes masking and a correlation calculation to determine the error from the current image of the focal spot and the ideal or designed position of the focal spot. The second method still uses the absorber as a sensor but calculates area moments of the reflected sunlight on the tubing to calculate the current location of the focal spot. DTIC
Computer Programs; Solar Collectors
20060014449 Naval Postgraduate School, Monterey, CA USA
| |
| Tools for Aviation/Aerospace |
| IHS sells products and services designed to meet the needs of today's engineers. To learn more, and for a free quote, please complete the form below. |
|
Analysis of Performance Characteristics of the MWR-05XP Mobile Weather Radar
Knorr, Jeffrey B; Dec 31, 2005; 51 pp.; In English; Original contains color illustrations Contract(s)/Grant(s): N6227103WER0026; Proj-NCRADA-NPS-03-0052 Report No.(s): AD-A442203; NPS-EC-05-005; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA442203; Avail.: CASI: A04, Hardcopy
In 1998, the Naval Postgraduate School (NPS) Center for Interdisciplinary Remotely Piloted Aircraft Studies (CIRPAS) and the NPS Department of Electrical and Computer Engineering (ECE Dept.) collaborated on the acquisition of a mobile radar, the AN/MPQ-64 (Sentinel). This is a modern X-band, pulse Doppler radar used by the Army for forward area air defense. An SBIR project funded by the Office of Naval Research resulted in a contract to ProSensing, Inc., Amherst, MA to retrofit this radar with a weather processor. The intent is to provide a military capability to assess battlespace weather in real time. This capability will be developed using the NPS radar as a testbed. When the weather capability has been fully implemented on the NPS radar, it will also have application as a scientific instrument for severe storm research because of its mobility and cutting edge capabilities. The modified radar has been designated the MWR-05XP (Mobile Weather Radar, 2005, X-band, Phased Array).
This report presents the results of an analysis of numerous aspects of the radar's erformance as a weather sensor. The ability of the MWR-05XP radar to detect rain with different levels of reflectivity, the ability of the radar to detect clear air turbulence with different structure parameters and echoes from birds and insects has been examined. Curves are provided to determine correlation and decorrelation times for weather signals with varying rms velocity spread. MWR-05XP post detection integration improvement has been computed for a Rayleigh weather target with varying pulse-to-pulse correlation and curves are provided to determine the improvement in terms of the number of pulses integrated. Lastly, scan strategy is discussed with emphasis on obtaining weather signal parameter estimates with small variance while at the same time achieving a rapid volumetric update rate. Electronic scan is the feature that enables the radar to achieve a rapid volumetric update rate. DTIC
Clear Air Turbulence; Doppler Radar; Meteorological Radar; Phased Arrays
20060014547 National War Coll., Washington, DC USA
The High Ground
Huybrechts, Steven M; Jan 2004; 12 pp.; In English Report No.(s): AD-A441607; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA441607; Avail.: CASI: A03, Hardcopy
35,880 km above the Earth's surface, it is dark, lonely and cold the universe looks black and empty. Far away, the Earth is just a small bright disc; the Middle East, Indian Sub-Continent, and South-East Asia frame the deep blue Indian Ocean below. Always in view of these highly troubled regions, Milstar 5 is relentlessly busy. The $1.268B spacecraft's movement is imperceptible as large reaction wheels balance torque to keep the spacecraft from tumbling while precision antennas slew to track incoming data streams from Air Force Global Hawk aircraft and Army Special Operations units deployed all around, and now inside, the Iraqi nation. Orbiting 15,000 km below, all 27 satellites of the Global Positioning System (GPS) are in view as they circle the Earth. From Milstar 5's geosynchronous vantage point, the GPS satellites occasionally appear to pass through the highly classified spy satellites of many nations America, Russia, China, Israel, France, Japan, and others as they survey targets, assess damage, and search for hostile activity. The view along the communication satellite's daunting 15m length looks deep out into cold, black space; occasionally in view is an aging Cold-War-era infrared missile warning spacecraft built with 35 year old technology intently scanning its side of the Earth for any sign of a dreaded chemical-weapon-tipped Scud missile launch onburst of high-energy radio energy from Milstar 5 retargets a salvo of Tomahawk cruise missiles just launched from the USS Donald Cook in the Red Sea the missiles are skimming along the Earth's surface far, far below. The Tomahawks' guidance systems look out into space for LBand transmissions broadcast from the four GPS satellites not blocked from their view by the Earth, autonomously charting a course to a recently discovered Iraqi leadership bunker. DTIC
Artificial Satellites; Global Positioning System; Missiles; Targets
20060014914 Space and Naval Warfare Systems Command, San Diego, CA USA
| |
| Aerospace Engineering Design |
| ESDU packages provide validated design data, methods and software, offering a valuable toolset to aerospace engineers. To learn more, and for a free quote, please complete the form below. |
|
Enabling Technologies for Unmanned Protection Systems
Carroll, Daniel M; Harbour, Jerry L; Bauer, Scott G; Bruemmer, David J; Pacis, Estrellina B; Mullens, Kathenne D; Everett, H R; Jan 2005; 9 pp.; In English; Original contains color illustrations Report No.(s): AD-A442881; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA442881; Avail.: CASI: A02, Hardcopy
Unmanned vehicles perform critical mission functions. Today, fielded unmanned vehicles have restricted operations as a single asset controlled by a single operator. In the future, however, it is envisioned that multiple unmanned air , ground, surface and underwater vehicles will be deployed in an integrated unmanned (and 'manned') team fashion in order to more effectively execute complex mission scenarios. To successfully facilitate this transition from single platforms to an integrated unmanned system concept, it is essential to first develop the required base technologies for multi-vehicle mission requirements, as well as test and evaluate such technologies in tightly controlled field experiments. Under such conditions, advances in unmanned technologies and associated system configurations can be empirically evaluated and quantitatively measured against relevant performance metrics. DTIC
Protection; Underwater Vehicles
20060015039 National War Coll., Washington, DC USA
Integrated Battlefeld Management Begins in Space
Branco, Jr, Allen G; Mar 18, 1997; 12 pp.; In English Report No.(s): AD-A442715; NDU/NWC-ASE-97-11; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA442715; Avail.: CASI: A03, Hardcopy
On July 3, 1863, 'Lee's stubborn pugnacity still pushed the attack forward, until three divisions totaling about 15,000 men suffered wreckage beyond recovery in the failure of Pickett's Charge.' Sadly, Robert E. Lee stands out for miscalculating the impact of an ongoing revolution in military affairs. He was knowledgeable in the new weapon systems he faced, yet was unwilling to adapt his strategy and tactics to the new realities of war. At the close of the 20th century, military leaders face a similar dilemma. Today, a highly volatile technological environment is reshaping the battlefield. The challenge is to understand and adapt, for if the USA fails to shape the new technologies, they will shape it with potentially disastrous results. The Joint Chiefs of Staff (JCS), through Joint Publication 6-0, established a benchmark for future C4. The nation must build a future in which an effective C4I structure is able to support virtually any type of joint operation. This future vision is captured in the concept of real-time battlespace information. The JCS describes the system's objective as follows: 'The warrior needs a fused, real-time, true picture of the battlespace and the ability to order, respond and coordinate vertically and horizontally to the degree necessary to prosecute the mission in the battlespace.' To understand the issue of battlefield management, this paper addresses the following key questions: (1) Is this concept part of a revolution in military affairs, (2) What is a reasonable vision for an integrated battlespace goal, (3) What are the acquisition issues associated with the concept, and (4) What is the best method for converting this concept into a strategy to guide U.S. efforts? These questions are central to the concept of battlefield dominance and U.S. success in reaching this goal in the next century. DTIC
Aerospace Engineering; Communication Networks; Information Systems; Military Operations; Strategy; Systems Integration
20060015043 National War Coll., Washington, DC USA
Deploying an Operational Anti-Satellite Capability: Filling a Vulnerable Point in U.S. Defense
Dillman, Robert D; Jan 1996; 12 pp.; In English Report No.(s): AD-A442382; NDU-NWC-ASE-96-7; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA442382; Avail.: CASI: A03, Hardcopy
In 1989, Secretary of Defense Carlucci asserted to Congress that the lack of a U.S. ASAT [Anti-Satellite system was the single most vulnerable point in the country's defense. Since then, the Iron Curtain has fallen, Germany has reunified, the Soviet Union has disintegrated, Russia and Eastern European countries are delving into democratic and free market institutionalization, as is much of the rest of the world, and the UNITED States stands as the remaining super power in the post-cold war world. Indeed, on the face of it, now would seem an odd time for the U.S. to add an operational ASAT capability to its military instrument of national power After all, the Communist threat has dramatically receded, the economic and political instruments of national power seem to have taken precedence over the military instrument, and, accordingly, the U.S military is undergoing reductions of historical proportions. But this is the time the U.S. should deploy an operational ASAT capability. What's more, that capability should be open to venfication and known to the world. This paper expounds upon the reasons why deploying an operational ASAT capability would be a prudent step for the U.S at this time. DTIC
Deployment
20060015372 Defense Advanced Research Projects Agency, Arlington, VA USA
Coulomb Thrusting Application Study
Schaub, Hanspeter; Parker, Gordon G; King, Lyon B; Jan 20, 2006; 120 pp.; In English Contract(s)/Grant(s): HR0011-05-C-0026; DARPA ORDER-U122/01 Report No.(s): AD-A443162; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA443162; Avail.: CASI: A06, Hardcopy
This report discusses the results of an 8-month inter-disciplinary research project between Virginia Polytechnic Institute and State University and Aerophysics Inc. The research task objectives are to study how Coulomb propulsion can be used to create reconfigurable distributed spacecraft formation concepts. Both formation maintenance and deployment charge and voltage levels are of interest, as well as the required reconfiguration times to change the formation size. A further task is to study the space plasma environment at low to high Earth orbit altitudes. Associated to this task is the study of the expected differential disturbance levels that Coulomb spacecraft will experience at a range of orbit altitudes. Using the results of the plasma environment study, expected spacecraft voltages are to be computed to compensate for conservative orbital perturbation estimates. Another objective is to study mechanisms to both measure the local plasma charge level, and control the spacecraft charge relative to this plasma charge level. The final task is to perform a comparison study of the Coulomb propulsion concept to other high-efficiency propulsion concepts. DTIC
Electric Propulsion; Formation Flying; Propulsion
20060015403 Aerospace Corp., El Segundo, CA USA
Dilution of Disposal Orbit Collision Risk for the Medium Earth Orbit Constellations
Jenkin, A B; Gick, R A; May 13, 2005; 39 pp.; In English; Original contains color illustrations Contract(s)/Grant(s): FA8802-04-C-0001 Report No.(s): AD-A443232; TR-2005(8506)-2; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA443232; Avail.: CASI: A03, Hardcopy
Previous studies have shown that disposal orbits for the medium Earth orbit constellations can be unstable and undergo significant long-term eccentricity growth. This can lead to repenetration of the constellations by disposed vehicles, thereby posing a collision risk. The study presented here investigated the possibility of diluting disposal orbit collision risk by exploiting long-term eccentricity growth. The Galileo constellation was selected as an example. Various disposal strategies were considered. It was found that high eccentricity growth strategies can reduce the combined constellation and intra-graveyard collision risk relative to a minimum eccentricity growth strategy. High eccentricity growth strategies also offer the option of significantly increasing the percentage of disposed vehicles that will re-enter the atmosphere within 200 years after disposal rather than remain on orbit for thousands of years. High eccentricity growth strategies thereby offer an effective and potentially inexpensive option for medium Earth orbit debris mitigation. DTIC
Collisions; Constellations; Debris; Dilution; Earth Orbits; Eccentricity; Galileo Spacecraft; Global Positioning System; Navigation Satellites; Risk
20060015736 CSA Engineering, Inc., Albuquerque, NM USA
EELV Secondary Payload Adapter (ESPA) Static Qualification Tests
Sanford, Gregory E; Welsh, Jeffry S; Aug 2004; 26 pp.; In English; Original contains color illustrations Report No.(s): AD-A443362; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA443362; Avail.: CASI: A03, Hardcopy
The USA Air Force Research Lab is currently examining options to launch small satellites (\h200 kg e.g., 440 lb) more economically and efficiently. This class of satellite is quickly becoming a government and industry mainstay due to their ability to inexpensively demonstrate new technology, test prototype operational hardware, as well as perform space experimentation. Most of existing launch options include foreign sources, such as the Ariane launch vehicle, that are not available to Department of Defense (DoD) launches. Through the efforts of team members from the Air Force Research Lab$Space Vehicles Directorate (AFRL/VS), DoD Space Test Program (STP), TRW, and CSA Engineering, a secondary payload adapter has been developed to allow small satellites to be launched with the primary payload. This is to be accomplished by using an adapter on the upcoming Evolved Expendable Launch Vehicles (EELV), DoD medium lift vehicles, more specifically, the Boeing Co. Delta IV and the Lockheed Martin Atlas V launch vehicles. This adapter, known as the EELV Secondary Payload Adapter (ESPA) will take advantage of the primary payload's unused volume and mass margins. DTIC
Adapters; Artificial Satellites; Launch Vehicles; Payloads; Performance Tests; Static Tests
20060015839 Army Medical Research Inst. of Chemical Defense, Aberdeen Proving Ground, MD USA
Effects of Prednisolone Acetate on Ocular Sulfur Mustard Injury in a Rabbit Model
Bossone, C; Newkirk, K; Schulz, S; Railer, R; Gazaway, M; Shutz, M; Clarkson, E; Estep, S; Subramarian, P; Castro, A; Clinkscales, J; Lukey, B; Dec 2003; 22 pp.; In English Report No.(s): AD-A443564; USAMRICD-TR-03-08; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA443564; Avail.: CASI: A03, Hardcopy
Eye injury from HD (sulfur mustard) exposure continues to remain a threat to soldiers in the battlefield. This study was designed to explore the effects of Pred-Forte (prednisolone) in treating ocular HD injury. Sixteen female New Zealand White rabbits were exposed to 0.51 mg of undiluted HD as a liquid droplet. One group (n=8) received 2 drops of Pred-Forte into the eye every 10 minutes for the first 30 minutes postexposure, then every 30 minutes for 2 hours, after which treatments were given three times daily (tid). The control group of animals (n=7) received 2 drops of Artificial Tears. Eyes of rabbits were evaluated and scored weekly for 56 weeks, then at 12, 13 and 16 weeks. Measurements included slit lamp evaluation, corneal thickness (Pachymetry), and modified ocular severity score (MOSS). Lesions or ulcers resulting in corneal perforations developed within the first 34 weeks in 9 out of 15 rabbits. Treatments were discontinued at 3 weeks; however, observations continued to 16 weeks. Adverse reactions were attributed to treatment effect, inexperienced operators (HD) and/or both. The use of different applications of HD to the eye should also be considered to eliminate variability seen with the droplet method. DTIC
Acetates; Cornea; Eye (Anatomy); Injuries; Rabbits; Sulfur
20060016086 CSA Engineering, Inc., Mountain View, CA USA
CASPAR: Low-Cost, Dual-Manifest Payload Adapter for Minotaur IV
Maly, Joseph R; Pendleton, Scott C; Buckley, Steven J; Higgins, John E; Walsh, Eric J; Hevner, Ryan A; Schoneman, Scott R; Emmer, William A; Jan 2005; 12 pp.; In English; Original contains color illustrations Report No.(s): AD-A443936; No Copyright; Avail.: CASI: A03, Hardcopy
The Minotaur IV Launch Vehicle is being developed by the Air Force Rocket Systems Launch Program (RSLP) to utilize excess Peacekeeper missile motors and provide low-cost launches for Government payloads to Low Earth Orbit (LEO). This vehicle uses three Peacekeeper stages, an Orion 38 motor, and avionics from the heritage Minotaur I vehicle. Nominal capability for Minotaur IV is almost 4000 lbm to LEO. The fly-away cost is just over $20 million. The Composite Adapter for Shared PAyload Rides (CASPAR) Multi-Payload Adapter (MPA) will enable a Minotaur IV to launch two large satellites (1000-2000 lbm) for about $10 million each. The CASPAR MPA is being designed for projected Minotaur IV launch load environments, with design objectives of light weight, integrated vibration isolation, low shock, and modularity. An innovative composite design, including co-cured composite stiffening, provides a lightweight structure with optional access doors. Low-shock separation systems are integrated for MPA and satellite separation events. Vibration isolation systems protect the payloads from the dynamic environment of the Peacekeeper motor stack, and isolation tuning will enable a range of payloads and facilitate modular designs. Qualification testing of a full-scale adapter is planned for early 2006. Design variations are being considered for existing and new launch vehicles. DTIC
Adapters; Launch Vehicles; Low Cost; Payloads
20060016329 Naval Postgraduate School, Monterey, CA USA
Strain-Based Displacement Estimation For Precision Spacecraft Structures
Coleman, Craig S; Dec 2005; 49 pp.; In English; Original contains color illustrations Report No.(s): AD-A443429; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA443429; Avail.: Defense Technical Information Center (DTIC)
For precision spacecraft structures used for antennas and reflectors of telescopes, determination of in-orbit structural displacement and its control is very important. While this kind of measurement is relatively easy to carry out in a laboratory setting, it can be problematic in a real world environment. A procedure for the real-time determination of displacements at any point of a vibrating body can be utilized by measuring strain that is present. The procedure could employ measurement devices like Fiber Bragg Gratings, which are capable of very fine strain measurements. This thesis presents the finite element analysis of a truss similar to the NPS Space truss to observe the behavior of the strain relative to the displacement. DTIC
Displacement; Finite Element Method; Spacecraft Components; Spacecraft Structures; Strain Gages; Structural Design
20060016331 National War Coll., Washington, DC USA
Space Launch Vehicle Export Policy and The Struggle between National Security Policy & Foreign Policy
Shearer, Thomas D; Jan 1997; 15 pp.; In English Report No.(s): AD-A443806; NDU/NWC-97-E-33; No Copyright; Avail.: CASI: A03, Hardcopy
In the spring of 1992 several U S commercial aerospace contractors informed the U S Department of State (DOS) that Italy, Spain, and Australia were independently initiating small space launch vehicle (SLV) programs Furthermore, that these countries wanted the assistance of U S aerospace contractors to build these SLVs Thus, the contractors desired U S government approval to assist these countries build then unrelated indigenous SLV programs Over the period from April to December 1992 U S contractors followed up their inquiries by filing 14 specific export license requests with the DOS, Defense Trade Center (DTC) These export license requests were for the sale of hardware, technology, and services, to support the SLV programs in these countries U S contractors submitted these license requests with the knowledge that existing U S national security and foreign policy prohibited U S firms from supporting the development of foreign SLV programs In accordance with standard procedures, the DTC referred these SLV export requests to a formal interagency working group established to approve or deny all rocket related exports from the USA. DTIC
Foreign Policy; International Trade; Launch Vehicles; Policies; Security; Spacecraft Launching
Source: NASA
|
IHS sells products and services designed to meet the needs of today's aviation & aerospace engineers, including:
- Quick access to FAA, JAA, ICAO and UK-CAA information and regulations.
- Validated engineering methods, data, principles, worked examples, programs and related equations on over 1340 specific aerospace, process, structural and mechanical engineering topics.
- The IHS Fasteners eCatalog, providing decision support for the identification, specification and sourcing of aerospace & defense standard fasteners/hardware such as bolts, screws, nuts, washers, rivets, studs, etc.
- Standards documents and collections from the top aerospace & aviation standards development organizations, including SAE International, AIAA, AIA, FAA and NASA.
|