SCIENTIFIC AND TECHNICAL AEROSPACE REPORTS
A Biweekly Publication of the National Aeronautics and Space Administration
VOLUME 43, ISSUE 16 - AUGUST 12, 2005
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.
20050188586 Army Missile Command, Redstone Arsenal, AL USA
LOKI Antiaircraft Free-Flight Rocket System: Historical Summary, December 1947 - November 1955
Cagle, Mary T.; Bjork, Carold F.; Lewis, Richard M.; Newman, Paul; Apr. 1957; 72 pp.; In English Report No.(s): AD-A434200; ORDGX-6; No Copyright; Avail: CASI; A04, Hardcopy
This special historical monograph on the LOKI Anti-Aircraft Free-Flight Rocket System was compiled for the Office, Chief of Ordnance, in compliance with letter, ORDGX 00/700 4072, subject: ‘Historical Monograph on LOKI,’ dated 5 February 1957. The material contained herein was furnished in draft form by Mr. Ernest K. Charlton, Chief of the Commodity Coordination Branch, Plans Coordination Office. In connection with this history of the LOKI Rocket System, the reader’s attention is invited to the special study entitled ‘Design, Development and Production of Rockets and Rocket Launchers,’ dated 1 July 1954, which was also prepared for the Office, Chief of Ordnance. DTIC
Ammunition; Free Flight; Histories; Loki Rocket Vehicle; Sounding Rockets
20050188611 Joint Chiefs of Staff, Washington, DC USA
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Joint Doctrine for Space Operations
Aug. 2002; 88 pp.; In English; Original contains color illustrations Report No.(s): AD-A434234; JCS-PUB-3-14; No Copyright; Avail: CASI; A05, Hardcopy
This publication provides guidelines for planning and conducting joint space operations. It provides space doctrine fundamentals for all warfighters -air, land, sea, space, and special operations forces; describes the military operational principles associated with support from and through space, and operating in space; explains US Space Command relationships and responsibilities; and establishes a framework for the employment of space forces and space capabilities. This publication has been prepared under the direction of the Chairman of the Joint Chiefs of Staff. It sets forth doctrine to govern the joint activities and performance of the Armed Forces of the USA in joint operations and provides the doctrinal basis for US military involvement in multinational and interagency operations. It provides military guidance for the exercise of authority by combatant commanders and other joint force commanders (JFCs) and prescribes doctrine for joint operations and training. It provides military guidance for use by the Armed Forces in preparing their appropriate plans. It is not the intent of this publication to restrict the authority of the JFC from organizing the force and executing the mission in a manner the JFC deems most appropriate to ensure unity of effort in the accomplishment of the overall mission. DTIC
Military Operations; Space Missions
20050188660 Air Force Inst. of Tech., Wright-Patterson AFB, OH USA
Maneuver Estimation Model for Relative Orbit Determination
Storch, Tara R.; Mar. 2005; 77 pp.; In English; Original contains color illustrations Report No.(s): AD-A434307; AFIT/GA/ENY/05-M011; XC-AFRL/DET-15; No Copyright; Avail: Defense Technical Information Center (DTIC)
While the use of relative orbit determination has reduced the difficulties inherent in tracking geosynchronous satellites that are in close proximity, the problem is often compounded by stationkeeping operations or unexpected maneuvers. If a maneuver occurs, observations will no longer fit predicted data, increasing the risk of misidentification and cross-tagging. The goal of this research was to develop a model that will estimate the magnitude, direction, and time of a suspected maneuver performed by a collocated satellite in geosynchronous orbit. Relative motion was modelled using Hill’s equations, and least squares estimation was employed to create both a linear non-maneuver model and non-linear maneuver model. Two sets of data (DirecTV 4S and AMC-4) for an actual satellite collocation were obtained from the Air Force Maui Optical and Supercomputing (AMOS) site, consisting of differential right ascension and declination. Studies conducted with these observations, along with simulation studies, indicate that it is possible to perform maneuver estimation. It was found, however, that the amount of data required for successful convergence is much greater than that typically obtained for tracking purposes. DTIC
Earth Orbits; Estimates; Maneuvers; Mathematical Models; Orbit Determination; Synchronous Satellites
20050188670 Air Force Inst. of Tech., Wright-Patterson AFB, OH USA
Performance Study of Staging Variables on Two-Stage-to-Orbit Reusable Launch Vehicles
Nilsen, James K.; Mar. 2005; 65 pp.; In English; Original contains color illustrations Report No.(s): AD-A434320; AFIT/GA/ENY/05-M08; No Copyright; Avail: CASI; A04, Hardcopy
The purpose of this research is to investigate the effects of staging variables on Two-Stage-To-Orbit reusable launch vehicles, specifically, the question of what measurable factors play important roles in staging performance. Three different configurations (Rocket-Rocket, Turbojet-Rocket and Turbine Based Combined Cycle-Rocket) were considered. The software, Program to Optimize Simulated Trajectories (POST), was used to analyze these configurations. Vehicle coasting time, staging dynamic pressure and staging Mach number were all varied to determine their influence on the final payload. DTIC
Launch Vehicles; Reusable Launch Vehicles
20050194721 NASA Lewis
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Launch Collision Probability Model Developed and Analyzed Research and Technology
1998; April 1999; 2 pp.; In English; Original contains black and white illustrations; No Copyright; Avail: CASI; A01, Hardcopy
There are nearly 10,000 tracked objects orbiting the earth. These objects encompass manned objects, active and decommissioned satellites, spent rocket bodies, and debris. They range from a few centimeters across to the size of the MIR space station. Anytime a new satellite is launched, the launch vehicle with its payload attached passes through an area of space in which these objects orbit. Although the population density of these objects is low, there always is a small but finite probability of collision between the launch vehicle and one or more of these space objects.
Even though the probability of collision is very low, for some payloads even this small risk is unacceptable. To mitigate the small risk of collision associated with launching at an arbitrary time within the daily launch window, NASA performs a prelaunch mission assurance Collision Avoidance Analysis (or COLA).
For the COLA of the Cassini spacecraft, the NASA Lewis Research Center conducted an in-house development and analysis of a model for launch collision probability. The model allows a minimum clearance criteria to be used with the COLA analysis to ensure an acceptably low probability of collision. If, for any given liftoff time, the nominal launch vehicle trajectory would pass a space object with less than the minimum required clearance, launch would not be attempted at that time.
The model assumes that the nominal positions of the orbiting objects and of the launch vehicle can be predicted as a function of time, and therefore, that any tracked object that comes within close proximity of the launch vehicle can be identified. For any such pair, these nominal positions can be used to calculate a nominal miss distance. The actual miss distances may differ substantially from the nominal miss distance, due, in part, to the statistical uncertainty of the knowledge of the objects positions.
The model further assumes that these position uncertainties can be described with position covariance matrices. With these, and some additional simplifying assumptions, a closed-form solution for the probability of collision is obtained. This solution provides clear insights into how each of the independent parameters affects the probability of collision. It shows that for a given maximum probability of collision and prior knowledge of the objects position uncertainties and sizes, only knowledge of the nominal closest approach distance is required to make the launch/no launch decision.
The model was completed and used for the mission assurance COLA analysis for the Cassini spacecraft, which was launched on a Titan IV/Centaur rocket on October 15, 1997. Although the model was specifically developed for the Cassini mission, it is clearly applicable for other launches as well. The effect of COLA closures on the launch window is shown. The bar represents the entire 140-min launch window on October 15, 1997; the blackened areas represent the loss of launch opportunities due to the potential for a collision with an orbiting object. Author
Collision Avoidance; Launch Vehicles; Models; Probability Theory; NASA Space Programs
20050196058 Air Force Inst. of Tech., Wright-Patterson AFB, OH USA
Weight Analysis of Two-Stage-To-Orbit Reusable Launch Vehicles for Military Applications
Caldwell, Richard A.; Mar. 2005; 119 pp.; In English; Original contains color illustrations Report No.(s): AD-A434888; AFIT/GA/ENY/05-M02; No Copyright; Avail: Defense Technical Information Center (DTIC)
In response to Department of Defense (DoD) requirements for responsive and low-cost space access, this design study provides an objective empty weight analysis of potential reusable launch vehicle (RLV) configurations. Each two-stage-toorbit (TSTO) RLV has a fixed payload requirement of 20,000 lbf to low Earth orbit. The propulsion systems considered in this study include pure rocket, pure turbine, rocket-based-combined-cycle (RBCC), and turbine-based-combined-cycle (TBCC). The hydrocarbon dual-mode scramjet (DMSJ) engines used in the RBCC and TBCC propulsion systems represent possible applications of the current research being performed in the U.S. Air Force HyTech program. Two sensitivity analyses were then performed on areas of interest directly affecting the propulsion systems in this study, including the effects of orbiter fuel selection, as well as the effects of increasing the turbine installed thrust to weight ratios for the RLVs utilizing afterburning turbine engines. The vertical-takeoff-horizontal-landing (VTHL) RLVs have an empty weight advantage over the horizontaltakeoff-horizontal-landing (HTHL) RLVs. The orbiter propellant switch has either negligible or no empty weight savings for the VTHL RLVs, while it leads to substantial empty weight savings for the HTHL RLVs. For the HTHL RLVs, increasing the turbine installed thrust to weight ratio causes a significant decrease in empty weight. DTIC
Launch Vehicles; Military Technology; Reusable Launch Vehicles; Weight Analysis
20050196065 Cornell Univ., Ithaca, NY USA
Mission Support for the Communication/Navigation Outage Forecast System
Hysell, D. L.; Dec. 2004; 9 pp.; In English Contract(s)/Grant(s): F19628-03-C-0067; Proj-1010 Report No.(s): AD-A434897; AFRL-VS-HA-TR-2005-1013; No Copyright; Avail: CASI; A02, Hardcopy
This project provides mission support for the Communication/Navigation Outage Forecast System (C/NOFS) under BAA VS-03-01 during its first 4 years of operation. Cornell is required to support the mission with ground-based radar observations of background ionospheric parameters and of equatorial spread F events from the Jicamarca Radio Observatory near Lima, Peru. In the pre-launch period for C/NOFS, Cornell and Jicamarca contributed to the project by measuring plasma density, drift, temperature, and composition profiles during eight campaign periods. The data were processed and made available to AFRL for model validation and also for the Defense Meteorological Satellite Program (DMSP) CalVal operations. Cornell also developed an extensive collection of codes for processing incoherent scatter data from the Altair radar, which also will provide support for the C/NOFS mission. Finally, Cornell undertook a new theoretical formulation of the ionospheric stability problem that stresses the role of shear instabilities in preconditioning the post-sunset ionosphere. The work led to the production of two manuscripts (published or in press) and to a number of presentations. DTIC
Forecasting; Incoherent Scattering; Ionospheric Disturbances; Meteorological Radar; Meteorological Satellites; Navigation; Transmission Loss
20050196076 Space and Missile Systems Organization, Los Angeles AFB, CA USA
Environmental Impact Analysis Process. Final Environmental Assessment U.S. Air Force Advanced Extremely High Frequency Satellite Program (AEHF)
Behrens, Paul; Brown, Karen; Davis, Anthony; Latimer, J. D.; Martin, John C.; Peten, Rachey; Roy, Paula; Wooten, R. C.; Feb. 2001; 53 pp.; In English; Original contains color illustrations Report No.(s): AD-A434921; No Copyright; Avail: Defense Technical Information Center (DTIC)
The USA Air Force (USAF) currently operates the Milstar satellite system to provide Military Satellite Communication Systems (MILSATCOM) to compliment the Air Force’s Satellite Communication System, Navy’s Fleet Satellite Communication System, and the Defense Satellite Communication System. Milstar utilizes integrated defense communications controlled from a small, continental USA based force structure. The Milstar I system was designed as an advanced communications network consisting of three primary elements: a constellation of six satellites, a satellite ground control systems, and individual user terminals. Initially conceived in 1983, this system was designed to meet the joint service requirements to simultaneously provide: (1) the tactical forces with critical command and control communications, (2) the National Command Authorities (NCA) with Single Integrated Operation Plan (SIOP) execution and (3) the Strategic Forces with direction and report back capability. To meet user requirements, the satellite and terminal communication elements of the Miltar system were designed with a Low Data Rate (LDR) capability. DTIC
Communication Satellites; Environmental Surveys; Extremely High Frequencies; Military Spacecraft
20050196135 Air Force Academy, CO USA
‘All Our Tomorrows’: A Long-Range Forecast of Global Trends Affecting Arms Control Technology
Smith, James M.; Larsen, Jeffrey A.; Jun. 2002; 59 pp.; In English; Original contains color illustrations Report No.(s): AD-A435012; INSS-OP-44; No Copyright; Avail: Defense Technical Information Center (DTIC)
This is the 44th volume in the Occasional Paper series of the USA Air Force Institute for National Security Studies (INSS). This report summarizes a three-phase research project undertaken by the USAF Institute for National Security Studies on behalf of the Defense Threat Reduction Agency to forecast long-range global trends affecting arms control technologies. The report projects the international political, economic, and scientific environments to the year 2015. It posits economic and technological drivers as shaping the system, including its military and political dimensions. The result will be a two-tiered system, with great danger arising from significant proliferation in the second tier and the transition zone between tiers. The report next draws conclusions from this likely future for the scope, value, and practice of arms control. Arms control will be focused less on limitation and reduction of existing weapons, although the endgame between the USA and Russia will remain a significant effort. The focus will shift to the less well-defined realm of counterproliferation, and to marginal, failing, and failed states as well as nontraditional and non-state actors. New dimensions will be added, including control efforts toward small arms, advanced conventional weapons, military space, and information operations. The report then extrapolates from this future to assess the likely arms control technology requirements in cooperative, noncooperative, intrusive, and nonintrusive regimes. The projection here is continuing requirements for each of these specialized sets of technologies, with particular emphasis on multiple-use technologies for remote arms control compliance and verification monitoring as well as for intelligence detection and collection. DTIC
Forecasting; International Relations; Trend Analysis; Trends; United States
20050196202 Air Force Research Lab., Edwards AFB, CA USA
AFRL MicroPPT Development for Small Spacecraft Propulsion
Spanjers, Gregory G.; Bromaghim, Daron R.; Lake, James; White, David; Schilling, John H.; Bushman, Stewart; Antonsen, Erik L.; Burton, Rodney L.; Keidar, Michael; Boyd, Iain D.; Jul. 2002; 13 pp.; In English Contract(s)/Grant(s): Proj-1011 Report No.(s): AD-A435108; AIAA-2002-3974; No Copyright; Avail: Defense Technical Information Center (DTIC)
A class of miniaturized pulsed plasma thrusters (PPT), known as MicroPPTs, is currently in development at the Air Force Research Laboratory, Edwards Research Site, California. The MicroPPTs use a surface discharge across solid Teflon propellant to provide precise impulse bits in the 10 micro-newton-per-second range. In the near term, these thrusters can provide propulsive attitude control on 150-kg-class spacecraft using one-fifth the dry mass of conventional torque rods and reaction wheels. Eventually these thrusters are designed for primary and attitude control propulsion on future 25-kg class spacecraft. Efforts to characterize MicroPPT performance and the thruster plume are underway. To this end, a modified torsional thrust stand has been developed for the purpose of accurately measuring the low-level thrust generated by the MicroPPT. A Herriott Cell interferometer is introduced to establish the electron and neutral densities in the thruster plume. Comparison of the measured electron density with modeling predictions shows close agreement. Additionally, a Pockels cell has been developed to provide a zero-impedance MicroPPT breakdown voltage measurement, and an intensified CCD array has been used to characterize the divergence of both the thruster plume and the particulate emission. A synopsis is also presented of the status of the thruster development, including lifetime, thermal, and environmental testing. DTIC
Miniaturization; Propulsion System Configurations; Propulsion System Performance; Pulsed Plasma Thrusters; Spacecraft Propulsion; Unmanned Spacecraft
20050196268 Air Force Inst. of Tech., Wright-Patterson AFB, OH USA
Orbit Estimation Algorithms for a Microsatellite Rendezvous With a Non-Cooperative Target
Heslin, John P.; Mar. 2005; 184 pp.; In English; Original contains color illustrations Report No.(s): AD-A435238; AFIT/GSS/ENY/05-M02; No Copyright; Avail: Defense Technical Information Center (DTIC)
This study investigated the minimum requirements to establish a satellite tracking system architecture for a microsatellite to rendezvous with a non-cooperative target satellite. A prototype optical tracking system was reviewed with emphasis on a proposed tactical employment that could be used by technologically unsophisticated state or non-state adversaries. With the tracking system architecture selected, simulated tracking data was processed with a Non-Linear Least Squares batch orbit estimation algorithm and a Bayes sequential orbit determination filter to update the target satellite’s state vector. DTIC
Algorithms; Artificial Satellites; Microsatellites; Optical Tracking; Satellite Tracking; Targets
20050196546 Aerospace Corp., El Segundo, CA USA
SMC Orbital/Sub-Orbital Debris Mitigation User’s Handbook, Version 1.0
Campbell, W. S.; Nerio, D. M.; Jul. 2002; 70 pp.; In English; Original contains color illustrations Report No.(s): AD-A435172; No Copyright; Avail: Defense Technical Information Center (DTIC)
The purpose of this handbook is to provide Space and Missile Systems Center (SMC) space system developers a reference for use in satisfying DoD and National Space Policy regarding the Mitigation and Control of space debris. Meeting policy objectives involves mitigation of the effects of the debris environment on military space systems as well as mitigation of the effects of military space systems on other users of space. This handbook is intended to be a source of information to assist space system developers, planners, and operators in mitigating the effects of debris to assure minimal impact on their systems and on other users of space through proper design and operations. In addition, this handbook acquaints SMC space system developers with the various types of space hazards as well as current debris mitigation practices of SMC space programs. Metrics for determining the cost effectiveness of mitigation measures will be developed for inclusion in later versions of the handbook. DTIC
Aerospace Systems; Debris; Handbooks; Manuals; Orbits; Space Debris
Source: NASA.
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