Orbiting Frog Otolith /OFO/ - Press kit
Scheduled double launch of Orbiting Frog Otolith and Radiation Meteor spacecraft by single Scout launch vehicle - press kit
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Results for “SCOUT LAUNCH VEHICLE”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Acoustic data from the launch of Scout S-172C /ESRO 1-B/ and Scout S-169 /GRS-A/
Acoustic data obtained during launch of ESRO 1-B satellite and GRS-A satellite by Scout launch vehicles
Nagy, J. A.↗
Large Diameter Shuttle Launched-AEM (LDSL-AEM) study
A technical description of a Large Diameter Shuttle Launched-AEM (LDSL-AEM), an AEM base module adapted to carry 5 ft diameter payloads in the shuttle with propulsion for carrying payloads to higher altitude orbits from a 150 NM shuttle orbit, is described. The AEM is designed for launch on the scout launch vehicle. Onboard equipment provides capability to despin, acquire the earth, and control the vehicle in an earth pointing mode using reaction wheels for torque with magnets for all attitude acquisition, wheel desaturation, and nutation damping. Earth sensors in the wheels provide pitch and roll attitude. This system provides autonomous control capability to 1 degree in pitch and roll and 2 degrees in yaw. The attitude can be determined to .5 degrees in pitch and roll and 2 degrees in yaw.
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SCOUT Nozzle Data Book
Available analyses and material property information are summarized relevant to the design of four rocket motor nozzles currently incorporated in the four solid propellant rocket stages of the NASA SCOUT launch vehicle. The nozzles discussed include those for the following motors: (1) first stage - Algol IIIA; (2) second stage - Castor IIA; (3) third stage - Antares IIA; and (4) fourth stage - Altair IIIA. Separate sections for each nozzle provide complete data packages. Information on the Antares IIB motor which had limited usage as an alternate motor for the third stage is included.
Shieds, S.↗
Attitude motion of a non-attitude-controlled cylindrical satellite
In 1985, two non-attitude-controlled satellites were each placed in a low earth orbit by the Scout Launch Vehicle. The satellites were cylindrical in shape and contained reservoirs of hydrazine fuel. Three-axis magnetometer measurements, telemetered in real time, were used to derive the attitude motion of each satellite. Algorithms are generated to deduce possible orientations (and magnitudes) of each vehicle's angular momentum for each telemetry contact. To resolve ambiguities at each contact, a force model was derived to simulate the significant long-term effects of magnetic, gravity gradient, and aerodynamic torques on the angular momentum of the vehicles. The histories of the orientation and magnitude of the angular momentum are illustrated.
Wilkinson, C. K.↗
Nasa Langley Research Center seventy-fifth anniversary publications, 1992
The following are presented: The National Advisory Committee for Aeronautics Charter; Exploring NASA's Roots, the History of NASA Langley Research Center; NASA Langley's National Historic Landmarks; The Mustang Story: Recollections of the XP-51; Testing the First Supersonic Aircraft: Memoirs of NACA Pilot Bob Champine; NASA Langley's Contributions to Spaceflight; The Rendezvous that was Almost Missed: Lunar Orbit Rendezvous and the Apollo Program; NASA Langley's Contributions to the Apollo Program; Scout Launch Vehicle Program; NASA Langley's Contributions to the Space Shuttle; 69 Months in Space: A History of the First LDEF; NACA TR No. 460: The Characteristics of 78 Related Airfoil Sections from Tests in the Variable-Density Wind Tunnel; NACA TR No. 755: Requirements for Satisfactory Flying Qualities of Airplanes; 'Happy Birthday Langley' NASA Magazine Summer 1992 Issue.
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San Marco C-2 Explorer
The San Marco C-2 spacecraft will be launched no earlier than 18 February 1974 from the San Marco Range located off the coast of Kenya, Africa, by a Scout launch vehicle. The launch will be conducted by an Italian crew. The San Marco C-2 is the fourth cooperative satellite project between Italy and the United States. The purpose of the mission is to obtain measurements of the diurnal variations of the equatorial neutral atmosphere density, composition, and temperature and to use these data for correlation with AE-C (Explorer 51) data for studies of the physics and dynamics of the thermosphere. The San Marco C-2 project is a joint undertaking of the National Aeronautics and Space Administration (NASA) and the Italian Space Commission officially initiated with a Memorandum of Understanding in August of 1973. Project management responsibility for the Italian portion of the project has been assigned to the Centro Ricerche Aerospaziali (CRA) while the Goddard Space Flight Center (GSFC) has responsibility for the United States portion.
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Feasibility study of storage concepts for Scout and other NASA solid propellant launch vehicles
Feasibility study of long term storing of Scout and other solid propellant launch vehicles in assembled, flightworthy configuration and facility requirements
STORAGE↗
NASA to launch 5th Scout reentry heat experiment
Scout vehicle flight experiment to determine performance of phenolic nylon spacecraft heat shield material under reentry conditions
ABLATING MATERIAL↗
Satellite Telemetry and Data Recovery Systems
Satellite telemetry and data recovery systems
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Measured Response to Wind-Induced Dynamic Loads of a Full-Scale Scout Vehicle Mounted Vertically on a Launching Tower
Winds blowing over a vehicle mounted in the launch position may induce dynamic loads which are large enough to cause structural damage. In an attempt to prevent the formation of excessive wind-induced loads on the Scout vehicle, spoiler strips of the type used on the.Vanguard vehicle were to be mounted along the upper two stages of the Scout. These spoilers were designed to blow off shortly after launch and might hit and damage the fins at the base of the Scout. In order to determine whether the spoilers planned for installation on the Scout were needed, measurements of the response to dynamic loads imposed by winds at average velocities up to approximately 33 mph were made on a full-scale Scout vehicle mounted vertically on the launching tower at the NASA Wallops Station. From these measurements, it has been concluded that the deflections and bending moments measured in response t o wind-induced dynamic loads were small and should present no structural problems to the vehicle. No significant difference exists between the responses measured with and without spoilers of the type used on the Vanguard vehicle.
Jones, George W., Jr.↗
AN ANALYSIS OF THE CONING MOTIONS OF THE FINAL STAGES OF THREE NASA SCOUT DEVELOPMENT VEHICLES
Coning motions of the final stages of three nasa scout development vehicles
SCOUT LAUNCH VEHICLE↗
HEAT-TRANSFER AND PRESSURE DISTRIBUTIONS AT MACH NUMBERS OF 6.0 AND 9.6 OVER TWO REENTRY CONFIGURATIONS FOR THE FIVE-STAGE SCOUT VEHICLE
Heat transfer and pressure distribution over reentry configuration for five-stage scout vehicle
SCOUT LAUNCH VEHICLE↗
Electrostatic measurement experiment, Scout Vehicle 131-R /S.E.V./
Scout vehicle electrostatic sensor performance
SCOUT LAUNCH VEHICLE↗
United States launch vehicle systems
United States policy for national space launch capability provides for a balanced mix of launches, utilizing the Space Shuttle and Expendable Launch Vehicles (ELVs). The current mixed fleet includes the Space Shuttle and four expendable launch vehicles - Titan, Atlas, Delta, and Scout. New small class launch vehicles, including Pegasus, are in development. In addition, studies are underway to assure that the United States has cost-effective, reliable access to space, heavy-lift launch capability, and a new manned spacecraft after the current Space Shuttle reaches the end of its operational life. This paper highlights the current capabilities of the mixed fleet and summarizes the plans for new or modified United States launch vehicles through the first decade of the next century.
Krause, Robert B.↗
A feasibility study for Scout polar launches from NASA Wallops Flight Center
The feasibility of launching the Scout vehicle into a polar orbit from Wallops Flight Center is discussed. The impact of proposed flights on vehicle hardware and range safety are defined. The launch and flight modes are described.
Myler, T. R.↗
FIN LOADS AND TIP-CONTROL HINGE MOMENTS ON A 1 8-SCALE MODEL SIMULATING THE FIRST STAGE OF THE SCOUT RESEARCH VEHICLE AT A MACH NUMBER OF 2.01
Supersonic wind tunnel testing - scout vehicle fin load and tip control hinge moments
TIP CONTROL↗
Free-Flight Tests of Fifth-Stage Scout Entry Vehicle at Mach Numbers of 5 and 17
Measurements have been made in air at two Mach numbers of the static stability, normal force, and drag of a version of the fifth-stage Scout entry vehicle. The most significant result was that the design center of gravity led to a condition of static instability at small angles of attack at Mach number 17. At this Mach number, the static stability was a highly nonlinear function of the angle of attack. A useful method for analyzing free-flight data having this nonlinear behavior is included in this report. Comparisons were made between the measured aerodynamic coefficients and those estimated by Newtonian impact theory and by a method developed by Seiff and Whiting. The latter method gave good estimates of the normal-force-curve slope at both Mach numbers and of the moment-curve slope at the lower Mach number. It resulted in an overestimation of the static stability at Mach number 17, although it gave results decidedly closer to the experimental value than did Newtonian impact theory.
FREE FLIGHT↗