A Review of ETM-03 (A Five Segment Shuttle RSRM Configuration) Ballistic Performance

NASA Technical Reports Server (NTRS)

McMillin, J. E.; Furfaro, J. A.

2004-01-01

Marshall Space Flight Center and ATK Thiokol Propulsion worked together on the engineering design of a five-segment Engineering Test Motor (ETM-03), the world's largest segmented solid rocket motor. The data from ETM-03's static test have helped to provide a better understanding of the Reusable Solid Rocket Motor's (RSRM's) margins and the techniques and models used to simulate solid rocket motor performance. The enhanced performance of ETM-03 was achieved primarily by the addition of a RSRM center segment. Added motor performance was also achieved with a nozzle throat diameter increase and the incorporation of an Extended Aft Exit Cone (EAEC). Performance parameters such as web time, action time, head-end pressure, web time average pressure, maximum thrust, mass flow rate, centerline Mach number, pressure and thrust integrals were all increased over RSRM. In some cases, the performance increases were substantial. Overall, the measured data were exceptionally close to the pretest predictions.

KENNEDY SPACE CENTER, FLA. - On Launch Complex 17-B, Cape Canaveral Air Force Station, a solid rocket booster (SRB) is lifted into the mobile service tower, joining two others. They are three of nine 46-inch-diameter, stretched SRBs that are being attached to the Delta II Heavy rocket that will launch the Space Infrared Telescope Facility (SIRTF). Consisting of three cryogenically cooled science instruments and an 0.85-meter telescope, SIRTF is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

NASA Image and Video Library

2003-07-22

KENNEDY SPACE CENTER, FLA. - On Launch Complex 17-B, Cape Canaveral Air Force Station, a solid rocket booster (SRB) is lifted into the mobile service tower, joining two others. They are three of nine 46-inch-diameter, stretched SRBs that are being attached to the Delta II Heavy rocket that will launch the Space Infrared Telescope Facility (SIRTF). Consisting of three cryogenically cooled science instruments and an 0.85-meter telescope, SIRTF is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

KENNEDY SPACE CENTER, FLA. - Workers on Launch Complex 17-B, Cape Canaveral Air Force Station, help steady a solid rocket booster (SRB) being lifted into the mobile service tower. It is one of nine 46-inch-diameter, stretched SRBs that are being attached to the Delta II Heavy rocket that will launch the Space Infrared Telescope Facility (SIRTF). Consisting of three cryogenically cooled science instruments and an 0.85-meter telescope, SIRTF is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

NASA Image and Video Library

2003-07-22

KENNEDY SPACE CENTER, FLA. - Workers on Launch Complex 17-B, Cape Canaveral Air Force Station, help steady a solid rocket booster (SRB) being lifted into the mobile service tower. It is one of nine 46-inch-diameter, stretched SRBs that are being attached to the Delta II Heavy rocket that will launch the Space Infrared Telescope Facility (SIRTF). Consisting of three cryogenically cooled science instruments and an 0.85-meter telescope, SIRTF is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

KENNEDY SPACE CENTER, FLA. - On Launch Complex 17-B, Cape Canaveral Air Force Station, another solid rocket booster (SRB) is being raised from its transporter to lift it to vertical. It is one of nine 46-inch-diameter, stretched SRBs that are being attached to the Delta II Heavy rocket that will launch the Space Infrared Telescope Facility (SIRTF). Consisting of three cryogenically cooled science instruments and an 0.85-meter telescope, SIRTF is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

NASA Image and Video Library

2003-07-22

KENNEDY SPACE CENTER, FLA. - On Launch Complex 17-B, Cape Canaveral Air Force Station, another solid rocket booster (SRB) is being raised from its transporter to lift it to vertical. It is one of nine 46-inch-diameter, stretched SRBs that are being attached to the Delta II Heavy rocket that will launch the Space Infrared Telescope Facility (SIRTF). Consisting of three cryogenically cooled science instruments and an 0.85-meter telescope, SIRTF is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

KENNEDY SPACE CENTER, FLA. - A solid rocket booster (SRB) for the Delta II Heavy rocket that will launch the Space Infrared Telescope Facility (SIRTF) is lifted off its transporter on Launch Complex 17-B, Cape Canaveral Air Force Station. The SRB will be added to the launch vehicle in the background. The Delta II Heavy features nine 46-inch-diameter, stretched SRBs. SIRTF, consisting of three cryogenically cooled science instruments and an 0.85-meter telescope, is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

NASA Image and Video Library

2003-07-22

KENNEDY SPACE CENTER, FLA. - A solid rocket booster (SRB) for the Delta II Heavy rocket that will launch the Space Infrared Telescope Facility (SIRTF) is lifted off its transporter on Launch Complex 17-B, Cape Canaveral Air Force Station. The SRB will be added to the launch vehicle in the background. The Delta II Heavy features nine 46-inch-diameter, stretched SRBs. SIRTF, consisting of three cryogenically cooled science instruments and an 0.85-meter telescope, is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

Space Shuttle Projects

NASA Image and Video Library

1978-11-01

The structural test article to be used in the solid rocket booster (SRB) structural and load verification tests is being assembled in a high bay building of the Marshall Space Flight Center (MSFC). The Shuttle's two SRB's are the largest solids ever built and the first designed for refurbishment and reuse. Standing nearly 150-feet high, the twin boosters provide the majority of thrust for the first two minutes of flight, about 5.8 million pounds, augmenting the Shuttle's main propulsion system during liftoff. The major design drivers for the solid rocket motors (SRM's) were high thrust and reuse. The desired thrust was achieved by using state-of-the-art solid propellant and by using a long cylindrical motor with a specific core design that allows the propellant to burn in a carefully controlled marner. At burnout, the boosters separate from the external tank and drop by parachute to the ocean for recovery and subsequent refurbishment.

Ozone depletion caused by NO and H2O emissions from hydrazine-fueled rockets

NASA Astrophysics Data System (ADS)

Ross, M. N.; Danilin, M. Y.; Weisenstein, D. K.; Ko, M. K. W.

2004-11-01

Rockets using unsymmetrical dimethyl hydrazine (N(CH3)2NH2) and dinitrogen tetroxide (N2O4) propellants account for about one third of all stratospheric rocket engine emissions, comparable to the solid-fueled rocket emissions. We use plume and global atmosphere models to provide the first estimate of the local and global ozone depletion caused by NO and H2O emissions from the Proton rocket, the largest hydrazine-fueled launcher in use. NO and H2O emission indices are assumed to be 20 and 350 g/kg (propellant), respectively. Predicted maximum ozone loss in the plume of the Proton rocket is 21% at 44 km altitude. Plume ozone loss at 20 km equals 8% just after launch and steadily declines to 2% by model sunset. Predicted steady state global ozone loss from ten Proton launches annually is 1.2 × 10-4%, with nearly all of the loss due to the NO component of the emission. Normalized by stratospheric propellant consumption, the global ozone depletion efficiency of the Proton is approximately 66-90 times less than that of solid-fueled rockets. In situ Proton plume measurements are required to validate assumed emission indices and to assess the role of rocket emissions not considered in these calculations. Such future studies would help to establish a formalism to evaluate the relative ozone depletion caused by different rocket engines using different propellants.

History of Solid Rockets

NASA Technical Reports Server (NTRS)

Green, Rebecca

2017-01-01

Solid rockets are of interest to the space program because they are commonly used as boosters that provide the additional thrust needed for the space launch vehicle to escape the gravitational pull of the Earth. Larger, more advanced solid rockets allow for space launch vehicles with larger payload capacities, enabling mankind to reach new depths of space. This presentation will discuss, in detail, the history of solid rockets. The history begins with the invention and origin of the solid rocket, and then goes into the early uses and design of the solid rocket. The evolution of solid rockets is depicted by a description of how solid rockets changed and improved and how they were used throughout the 16th, 17th, 18th, and 19th centuries. Modern uses of the solid rocket include the Solid Rocket Boosters (SRBs) on the Space Shuttle and the solid rockets used on current space launch vehicles. The functions and design of the SRB and the advancements in solid rocket technology since the use of the SRB are discussed as well. Common failure modes and design difficulties are discussed as well.

KSC-97PC1725

NASA Image and Video Library

1997-11-21

KENNEDY SPACE CENTER, FLA. -- Seen carrying a spent solid rocket booster (SRB) from the STS-87 launch on Nov. 19 is the solid rocket booster recovery ship Liberty Star as it reenters the Hangar AF area at Cape Canaveral Air Station. Hangar AF is a building originally used for Project Mercury, the first U.S. manned space program. The SRBs are the largest solid propellant motors ever flown and the first designed for reuse. After a Shuttle is launched, the SRBs are jettisoned at two minutes, seven seconds into the flight. At six minutes and 44 seconds after liftoff, the spent SRBs, weighing about 165,000 lb., have slowed their descent speed to about 62 mph and splashdown takes place in a predetermined area. They are retrieved from the Atlantic Ocean by special recovery vessels and returned for refurbishment and eventual reuse on future Shuttle flights. Once at Hangar AF, the SRBs are unloaded onto a hoisting slip and mobile gantry cranes lift them onto tracked dollies where they are safed and undergo their first washing

KSC-97PC1727

NASA Image and Video Library

1997-11-21

KENNEDY SPACE CENTER, FLA. -- Seen carrying a spent solid rocket booster (SRB) from the STS-87 launch on Nov. 19 is the solid rocket booster recovery ship Liberty Star as it reenters the Hangar AF area at Cape Canaveral Air Station. Hangar AF is a building originally used for Project Mercury, the first U.S. manned space program. The SRBs are the largest solid propellant motors ever flown and the first designed for reuse. After a Shuttle is launched, the SRBs are jettisoned at two minutes, seven seconds into the flight. At six minutes and 44 seconds after liftoff, the spent SRBs, weighing about 165,000 lb., have slowed their descent speed to about 62 mph and splashdown takes place in a predetermined area. They are retrieved from the Atlantic Ocean by special recovery vessels and returned for refurbishment and eventual reuse on future Shuttle flights. Once at Hangar AF, the SRBs are unloaded onto a hoisting slip and mobile gantry cranes lift them onto tracked dollies where they are safed and undergo their first washing

Space Shuttle Projects

NASA Image and Video Library

1976-01-01

This image illustrates the solid rocket motor (SRM)/solid rocket booster (SRB) configuration. The Shuttle's two SRB's are the largest solids ever built and the first designed for refurbishment and reuse. Standing nearly 150-feet high, the twin boosters provide the majority of thrust for the first two minutes of flight, about 5.8 million pounds, augmenting the Shuttle's main propulsion system during liftoff. The major design drivers for the SRM's were high thrust and reuse. The desired thrust was achieved by using state-of-the-art solid propellant and by using a long cylindrical motor with a specific core design that allows the propellant to burn in a carefully controlled marner. At burnout, the boosters separate from the external tank and drop by parachute to the ocean for recovery and subsequent refurbishment. The boosters are designed to survive water impact at almost 60 miles per hour, maintain flotation with minimal damage, and preclude corrosion of the hardware exposed to the harsh seawater environment. Under the project management of the Marshall Space Flight Center, the SRB's are assembled and refurbished by the United Space Boosters. The SRM's are provided by the Morton Thiokol Corporation.

Reusable Solid Rocket Motor - Accomplishment, Lessons, and a Culture of Success

NASA Technical Reports Server (NTRS)

Moore, D. R.; Phelps, W. J.

2011-01-01

The Reusable Solid Rocket Motor (RSRM) represents the largest solid rocket motor (SRM) ever flown and the only human-rated solid motor. High reliability of the RSRM has been the result of challenges addressed and lessons learned. Advancements have resulted by applying attention to process control, testing, and postflight through timely and thorough communication in dealing with all issues. A structured and disciplined approach was taken to identify and disposition all concerns. Careful consideration and application of alternate opinions was embraced. Focus was placed on process control, ground test programs, and postflight assessment. Process control is mandatory for an SRM, because an acceptance test of the delivered product is not feasible. The RSRM maintained both full-scale and subscale test articles, which enabled continuous improvement of design and evaluation of process control and material behavior. Additionally RSRM reliability was achieved through attention to detail in post flight assessment to observe any shift in performance. The postflight analysis and inspections provided invaluable reliability data as it enables observation of actual flight performance, most of which would not be available if the motors were not recovered. RSRM reusability offered unique opportunities to learn about the hardware. NASA is moving forward with the Space Launch System that incorporates propulsion systems that takes advantage of the heritage Shuttle and Ares solid motor programs. These unique challenges, features of the RSRM, materials and manufacturing issues, and design improvements will be discussed in the paper.

Reusable Solid Rocket Motor - Accomplishments, Lessons, and a Culture of Success

NASA Technical Reports Server (NTRS)

Moore, Dennis R.; Phelps, Willie J.

2011-01-01

The Reusable Solid Rocket Motor represents the largest solid rocket motor ever flown and the only human rated solid motor. Each Reusable Solid Rocket Motor (RSRM) provides approximately 3-million lb of thrust to lift the integrated Space Shuttle vehicle from the launch pad. The motors burn out approximately 2 minutes later, separate from the vehicle and are recovered and refurbished. The size of the motor and the need for high reliability were challenges. Thrust shaping, via shaping of the propellant grain, was needed to limit structural loads during ascent. The motor design evolved through several block upgrades to increase performance and to increase safety and reliability. A major redesign occurred after STS-51L with the Redesigned Solid Rocket Motor. Significant improvements in the joint sealing systems were added. Design improvements continued throughout the Program via block changes with a number of innovations including development of low temperature o-ring materials and incorporation of a unique carbon fiber rope thermal barrier material. Recovery of the motors and post flight inspection improved understanding of hardware performance, and led to key design improvements. Because of the multidecade program duration material obsolescence was addressed, and requalification of materials and vendors was sometimes needed. Thermal protection systems and ablatives were used to protect the motor cases and nozzle structures. Significant understanding of design and manufacturing features of the ablatives was developed during the program resulting in optimization of design features and processing parameters. The project advanced technology in eliminating ozone-depleting materials in manufacturing processes and the development of an asbestos-free case insulation. Manufacturing processes for the large motor components were unique and safety in the manufacturing environment was a special concern. Transportation and handling approaches were also needed for the large hardware segments. The reusable solid rocket motor achieved significant reliability via process control, ground test programs, and postflight assessment. Process control is mandatory for a solid rocket motor as an acceptance test of the delivered product is not feasible. Process control included process failure modes and effects analysis, statistical process control, witness panels, and process product integrity audits. Material controls and inspections were maintained throughout the sub tier vendors. Material fingerprinting was employed to assess any drift in delivered material properties. The RSRM maintained both full scale and sub-scale test articles. These enabled continuous improvement of design and evaluation of process control and material behavior. Additionally RSRM reliability was achieved through attention to detail in post flight assessment to observe any shift in performance. The postflight analysis and inspections provided invaluable reliability data as it enables observation of actual flight performance, most of which would not be available if the motors were not recovered. These unique challenges, features of the reusable solid rocket motor, materials and manufacturing issues, and design improvements will be discussed in the paper.

History of Solid Rockets

NASA Technical Reports Server (NTRS)

Green, Becky; Hales, Christy

2017-01-01

Solid rockets were created by accident and their design and uses have evolved over time. Solid rockets are more simple and reliable than liquid rockets, but they have reduced performance capability. All solid rockets have a similar set of failure modes.

Evaluation of the Effect of Exhausts from Liquid and Solid Rockets on Ozone Layer

NASA Astrophysics Data System (ADS)

Yamagiwa, Yoshiki; Ishimaki, Tetsuya

This paper reports the analytical results of the influences of solid rocket and liquid rocket exhausts on ozone layer. It is worried about that the exhausts from solid propellant rockets cause the ozone depletion in the ozone layer. Some researchers try to develop the analytical model of ozone depletion by rocket exhausts to understand its physical phenomena and to find the effective design of rocket to minimize its effect. However, these models do not include the exhausts from liquid rocket although there are many cases to use solid rocket boosters with a liquid rocket at the same time in practical situations. We constructed combined analytical model include the solid rocket exhausts and liquid rocket exhausts to analyze their effects. From the analytical results, we find that the exhausts from liquid rocket suppress the ozone depletion by solid rocket exhausts.

Space Shuttle Projects

NASA Image and Video Library

1977-01-01

This illustration is a cutaway of the solid rocket booster (SRB) sections with callouts. The Shuttle's two SRB's are the largest solids ever built and the first designed for refurbishment and reuse. Standing nearly 150-feet high, the twin boosters provide the majority of thrust for the first two minutes of flight, about 5.8 million pounds, augmenting the Shuttle's main propulsion system during liftoff. The major design drivers for the solid rocket motors (SRM's) were high thrust and reuse. The desired thrust was achieved by using state-of-the-art solid propellant and by using a long cylindrical motor with a specific core design that allows the propellant to burn in a carefully controlled marner. At burnout, the boosters separate from the external tank and drop by parachute to the ocean for recovery and subsequent refurbishment. The boosters are designed to survive water impact at almost 60 miles per hour, maintain flotation with minimal damage, and preclude corrosion of the hardware exposed to the harsh seawater environment. Under the project management of the Marshall Space Flight Center, the SRB's are assembled and refurbished by the United Space Boosters. The SRM's are provided by the Morton Thiokol Corporation.

General view of the Solid Rocket Booster's (SRB) Solid Rocket ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

General view of the Solid Rocket Booster's (SRB) Solid Rocket Motor Segments in the Surge Building of the Rotation Processing and Surge Facility at Kennedy Space Center awaiting transfer to the Vehicle Assembly Building and subsequent mounting and assembly on the Mobile Launch Platform. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Study of solid rocket motor for space shuttle booster, volume 2, book 1

NASA Technical Reports Server (NTRS)

1972-01-01

The technical requirements for the solid propellant rocket engine to be used with the space shuttle orbiter are presented. The subjects discussed are: (1) propulsion system definition, (2) solid rocket engine stage design, (3) solid rocket engine stage recovery, (4) environmental effects, (5) manrating of the solid rocket engine stage, (6) system safety analysis, and (7) ground support equipment.

KSC-07pd1511

NASA Image and Video Library

2007-06-15

KENNEDY SPACE CENTER, FLA. -- The second stage of the Delta II launch vehicle for the Dawn spacecraft is lifted alongside the mobile service tower on Launch Pad 17-B at Cape Canaveral Air Force Station. At right can be seen the solid rocket boosters surrounding Delta's first stage. The second stage will be mated with the first stage. The Delta II-Heavy, manufactured by the United Launch Alliance, is scheduled to launch the Dawn spacecraft on its 4-year flight to the asteroid belt. The Delta II-Heavy is the strongest rocket in the Delta II class. It will use three stages and nine solid-fueled booster rockets to propel Dawn on its way. A 9.5-foot payload fairing will protect the spacecraft from the heat and stresses of launch. Dawn's goal is to characterize the conditions and processes of the solar system's earliest epoch by investigating in detail the largest protoplanets that have remained intact since their formations: asteroid Vesta and the dwarf planet Ceres. They reside in the extensive zone between Mars and Jupiter together with many other smaller bodies, called the asteroid belt. Dawn is scheduled to launch July 7. Photo credit: NASA/Jack Pfaller

KSC-07pd0411

NASA Image and Video Library

2007-02-16

KENNEDY SPACE CENTER, FLA. -- At Launch Pad 17-B at Cape Canaveral Air Force Station, an unusual view of the Delta II rocket with the THEMIS spacecraft atop gives the solid rocket boosters a "larger than life" appearance as the mobile service tower moves away. THEMIS, an acronym for Time History of Events and Macroscale Interactions during Substorms, consists of five identical probes that will track violent, colorful eruptions near the North Pole. This will be the largest number of scientific satellites NASA has ever launched into orbit aboard a single rocket. The THEMIS mission aims to unravel the mystery behind auroral substorms, an avalanche of magnetic energy powered by the solar wind that intensifies the northern and southern lights. The mission will investigate what causes auroras in the Earth’s atmosphere to dramatically change from slowly shimmering waves of light to wildly shifting streaks of bright color. Launch is scheduled for 6:05 p.m. Photo credit: NASA/Kim Shiflett

Space Shuttle Projects

NASA Image and Video Library

1978-09-29

This photo depicts the installation of an External Tank (ET) into the Marshall Space Flight Center Dynamic Test Stand, building 4550. It is being mated to the Solid Rocket Boosters (SRB's) for a Mated Vertical Ground Vibration Test (MVGVT). At 154-feet long and more than 27-feet in diameter, the ET is the largest component of the Space Shuttle, the structural backbone of the entire Shuttle system, and is the only part of the vehicle that is not reusable.

Aerodynamic characteristics of a 142-inch diameter solid rocket booster, configuration 139 (SA2FA/SA2FB)

NASA Technical Reports Server (NTRS)

Radford, W. D.; Johnson, J. D.

1974-01-01

Tests of a 2.112 percent scale model of the space shuttle solid rocket booster model were conducted in a transonic pressure tunnel. Tests were conducted at Mach numbers ranging from 0.4 to 1.2, angles of attack from minus one degree to plus 181 degrees, and Reynolds numbers from 0.6 million to 6.1 million per foot. The model configurations investigated were as follows: (1) solid rocket booster without external protuberances, (2) solid rocket booster with an electrical tunnel and a solid rocket booster/external tank thrust attachment structure, and (3) solid rocket booster with two body strakes.

Analysis of quasi-hybrid solid rocket booster concepts for advanced earth-to-orbit vehicles

NASA Technical Reports Server (NTRS)

Zurawski, Robert L.; Rapp, Douglas C.

1987-01-01

A study was conducted to assess the feasibility of quasi-hybrid solid rocket boosters for advanced Earth-to-orbit vehicles. Thermochemical calculations were conducted to determine the effect of liquid hydrogen addition, solids composition change plus liquid hydrogen addition, and the addition of an aluminum/liquid hydrogen slurry on the theoretical performance of a PBAN solid propellant rocket. The space shuttle solid rocket booster was used as a reference point. All three quasi-hybrid systems theoretically offer higher specific impulse when compared with the space shuttle solid rocket boosters. However, based on operational and safety considerations, the quasi-hybrid rocket is not a practical choice for near-term Earth-to-orbit booster applications. Safety and technology issues pertinent to quasi-hybrid rocket systems are discussed.

Acoustic Measurements for Small Solid Rocket Motors

NASA Technical Reports Server (NTRS)

Vargas, Magda B.; Kenny, R. Jeremy

2010-01-01

Models have been developed to predict large solid rocket motor acoustic loads based on the scaling of small solid rocket motors. MSFC has measured several small solid rocket motors in horizontal and launch configurations to anchor these models. Solid Rocket Test Motor (SRTM) has ballistics similar to the Reusable Solid Rocket Motor (RSRM) therefore a good choice for acoustic scaling. Acoustic measurements were collected during the test firing of the Insulation Configuration Extended Length (ICXL) 7,6, and 8 (in firing order) in order to compare to RSRM horizontal firing data. The scope of this presentation includes: Acoustic test procedures and instrumentation implemented during the three SRTM firings and Data analysis method and general trends observed in the data.

Experimental investigation of solid rocket motors for small sounding rockets

NASA Astrophysics Data System (ADS)

Suksila, Thada

2018-01-01

Experimentation and research of solid rocket motors are important subjects for aerospace engineering students. However, many institutes in Thailand rarely include experiments on solid rocket motors in research projects of aerospace engineering students, mainly because of the complexity of mixing the explosive propellants. This paper focuses on the design and construction of a solid rocket motor for total impulse in the class I-J that can be utilised as a small sounding rocket by researchers in the near future. Initially, the test stands intended for measuring the pressure in the combustion chamber and the thrust of the solid rocket motor were designed and constructed. The basic design of the propellant configuration was evaluated. Several formulas and ratios of solid propellants were compared for achieving the maximum thrust. The convenience of manufacturing and casting of the fabricated solid rocket motors were a critical consideration. The motor structural analysis such as the combustion chamber wall thickness was also discussed. Several types of nozzles were compared and evaluated for ensuring the maximum thrust of the solid rocket motors during the experiments. The theory of heat transfer analysis in the combustion chamber was discussed and compared with the experimental data.

The effects of solid rocket motor effluents on selected surfaces and solid particle size, distribution, and composition for simulated shuttle booster separation motors

NASA Technical Reports Server (NTRS)

Jex, D. W.; Linton, R. C.; Russell, W. M.; Trenkle, J. J.; Wilkes, D. R.

1976-01-01

A series of three tests was conducted using solid rocket propellants to determine the effects a solid rocket plume would have on thermal protective surfaces (TPS). The surfaces tested were those which are baselined for the shuttle vehicle. The propellants used were to simulate the separation solid rocket motors (SSRM) that separate the solid rocket boosters (SRB) from the shuttle launch vehicle. Data cover: (1) the optical effects of the plume environment on spacecraft related surfaces, and (2) the solid particle size, distribution, and composition at TPS sample locations.

On the history of the development of solid-propellant rockets in the Soviet Union

NASA Technical Reports Server (NTRS)

Pobedonostsev, Y. A.

1977-01-01

Pre-World War II Soviet solid-propellant rocket technology is reviewed. Research and development regarding solid composite preparations of pyroxyline TNT powder is described, as well as early work on rocket loading calculations, problems of flight stability, and aircraft rocket launching and ground rocket launching capabilities.

Study of solid rocket motor for space shuttle booster, volume 2, book 2

NASA Technical Reports Server (NTRS)

1972-01-01

A technical analysis of the solid propellant rocket engines for use with the space shuttle is presented. The subjects discussed are: (1) solid rocket motor stage recovery, (2) environmental effects, (3) man rating of the solid propellant rocket engines, (4) system safety analysis, (5) ground support equipment, and (6) transportation, assembly, and checkout.

Fluidized-Solid-Fuel Injection Process

NASA Technical Reports Server (NTRS)

Taylor, William

1992-01-01

Report proposes development of rocket engines burning small grains of solid fuel entrained in gas streams. Main technical discussion in report divided into three parts: established fluidization technology; variety of rockets and rocket engines used by nations around the world; and rocket-engine equation. Discusses significance of specific impulse and ratio between initial and final masses of rocket. Concludes by stating three important reasons to proceed with new development: proposed engines safer; fluidized-solid-fuel injection process increases variety of solid-fuel formulations used; and development of fluidized-solid-fuel injection process provides base of engineering knowledge.

Application of X-ray television image system to observation in solid rocket motor

NASA Astrophysics Data System (ADS)

Fujiwara, T.; Ito, K.; Tanemura, T.; Shimizu, M.; Godai, T.

The X-ray television image system is used to observe the solid propellant burning surface during rocket motor operation as well as to inspect defects in solid rocket motors in a real time manner. This system can test 200 mm diameter dummy propellant rocket motors with under 2 percent discriminative capacity. Viewing of a 50 mm diameter internal-burning rocket motor, propellant burning surface time transition and propellant burning process of the surroundings of artificial defects were satisfactorily observed. The system was demonstrated to be effective for nondestructive testing and combustion research of solid rocket motors.

Closeup view of the Solid Rocket Booster (SRB) Forward Skirt ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Close-up view of the Solid Rocket Booster (SRB) Forward Skirt sitting on ground support equipment in the Solid Rocket Booster Assembly and Refurbishment Facility at Kennedy Space Center while being prepared for mating with the Frustum-Nose Cap Assembly and the Forward Rocket Motor Segment. The prominent feature in this view is the electrical, data, telemetry and safety systems terminal which connects to the Aft Skirt Assembly systems via the Systems Tunnel that runs the length of the Rocket Motor. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

General view in the transfer aisle of the Vehicle Assembly ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

General view in the transfer aisle of the Vehicle Assembly Building at Kennedy Space Center looking at one of a pair of Aft Center Segments of the Solid Rocket Motor of the Solid Rocket Booster awaiting hoisting and mating to the Solid Rocket Booster's Aft Segment on the Mobile Launch Platform. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

General view in the transfer aisle of the Vehicle Assembly ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

General view in the transfer aisle of the Vehicle Assembly Building at Kennedy Space Center looking at one of a pair of Forward Segments of the Solid Rocket Motor of the Solid Rocket Booster awaiting hoisting and mating to the Solid Rocket Booster assembly on the Mobile Launch Platform. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

General view in the transfer aisle of the Vehicle Assembly ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

General view in the transfer aisle of the Vehicle Assembly Building at Kennedy Space Center looking at one of a pair of Forward Center Segments of the Solid Rocket Motor of the Solid Rocket Booster awaiting hoisting and mating to the Solid Rocket Booster assembly on the Mobile Launch Platform. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Solid Rocket Booster (SRB) Flight System Integration at Its Best

NASA Technical Reports Server (NTRS)

Wood, T. David; Kanner, Howard S.; Freeland, Donna M.; Olson, Derek T.

2011-01-01

The Solid Rocket Booster (SRB) element integrates all the subsystems needed for ascent flight, entry, and recovery of the combined Booster and Motor system. These include the structures, avionics, thrust vector control, pyrotechnic, range safety, deceleration, thermal protection, and retrieval systems. This represents the only human-rated, recoverable and refurbishable solid rocket ever developed and flown. Challenges included subsystem integration, thermal environments and severe loads (including water impact), sometimes resulting in hardware attrition. Several of the subsystems evolved during the program through design changes. These included the thermal protection system, range safety system, parachute/recovery system, and others. Because the system was recovered, the SRB was ideal for data and imagery acquisition, which proved essential for understanding loads, environments and system response. The three main parachutes that lower the SRBs to the ocean are the largest parachutes ever designed, and the SRBs are the largest structures ever to be lowered by parachutes. SRB recovery from the ocean was a unique process and represented a significant operational challenge; requiring personnel, facilities, transportation, and ground support equipment. The SRB element achieved reliability via extensive system testing and checkout, redundancy management, and a thorough postflight assessment process. However, the in-flight data and postflight assessment process revealed the hardware was affected much more strongly than originally anticipated. Assembly and integration of the booster subsystems required acceptance testing of reused hardware components for each build. Extensive testing was done to assure hardware functionality at each level of stage integration. Because the booster element is recoverable, subsystems were available for inspection and testing postflight, unique to the Shuttle launch vehicle. Problems were noted and corrective actions were implemented as needed. The postflight assessment process was quite detailed and a significant portion of flight operations. The SRBs provided fully redundant critical systems including thrust vector control, mission critical pyrotechnics, avionics, and parachute recovery system. The design intent was to lift off with full redundancy. On occasion, the redundancy management scheme was needed during flight operations. This paper describes some of the design challenges and technical issues, how the design evolved with time, and key areas where hardware reusability contributed to improved system level understanding.

Solid Rocket Booster (SRB) - Evolution and Lessons Learned During the Shuttle Program

NASA Technical Reports Server (NTRS)

Kanner, Howard S.; Freeland, Donna M.; Olson, Derek T.; Wood, T. David; Vaccaro, Mark V.

2011-01-01

The Solid Rocket Booster (SRB) element integrates all the subsystems needed for ascent flight, entry, and recovery of the combined Booster and Motor system. These include the structures, avionics, thrust vector control, pyrotechnic, range safety, deceleration, thermal protection, and retrieval systems. This represents the only human-rated, recoverable and refurbishable solid rocket ever developed and flown. Challenges included subsystem integration, thermal environments and severe loads (including water impact), sometimes resulting in hardware attrition. Several of the subsystems evolved during the program through design changes. These included the thermal protection system, range safety system, parachute/recovery system, and others. Obsolescence issues occasionally required component recertification. Because the system was recovered, the SRB was ideal for data and imagery acquisition, which proved essential for understanding loads and system response. The three main parachutes that lower the SRBs to the ocean are the largest parachutes ever designed, and the SRBs are the largest structures ever to be lowered by parachutes. SRB recovery from the ocean was a unique process and represented a significant operational challenge; requiring personnel, facilities, transportation, and ground support equipment. The SRB element achieved reliability via extensive system testing and checkout, redundancy management, and a thorough postflight assessment process. Assembly and integration of the booster subsystems was a unique process and acceptance testing of reused hardware components was required for each build. Extensive testing was done to assure hardware functionality at each level of stage integration. Because the booster element is recoverable, subsystems were available for inspection and testing postflight, unique to the Shuttle launch vehicle. Problems were noted and corrective actions were implemented as needed. The postflight assessment process was quite detailed and a significant portion of flight operations. The SRBs provided fully redundant critical systems including thrust vector control, mission critical pyrotechnics, avionics, and parachute recovery system. The design intent was to lift off with full redundancy. On occasion, the redundancy management scheme was needed during flight operations. This paper describes some of the design challenges, how the design evolved with time, and key areas where hardware reusability contributed to improved system level understanding.

Acoustic Measurements of Small Solid Rocket Motor

NASA Technical Reports Server (NTRS)

Vargas, Magda B.; Kenny, R. Jeremy

2010-01-01

Rocket acoustic noise can induce loads and vibration on the vehicle as well as the surrounding structures. Models have been developed to predict these acoustic loads based on scaling existing solid rocket motor data. The NASA Marshall Space Flight Center acoustics team has measured several small solid rocket motors (thrust below 150,000 lbf) to anchor prediction models. This data will provide NASA the capability to predict the acoustic environments and consequent vibro-acoustic response of larger rockets (thrust above 1,000,000 lbf) such as those planned for the NASA Constellation program. This paper presents the methods used to measure acoustic data during the static firing of small solid rocket motors and the trends found in the data.

Closeup view of the Solid Rocket Booster (SRB) Forward Skirt, ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Close-up view of the Solid Rocket Booster (SRB) Forward Skirt, Frustum and Nose Cap mated assembly undergoing final preparations in the Solid Rocket Booster Assembly and Refurbishment Facility at Kennedy Space Center. In this view the access panel on the Forward Skirt is removed and you can see a small portion of the interior of the Forward Skirt. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Closeup view of the Solid Rocket Booster Frustum and Nose ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Close-up view of the Solid Rocket Booster Frustum and Nose Cap assembly undergoing preparations and close-out procedures in the Solid Rocket Booster Assembly and Refurbishment Facility at Kennedy Space Center. The Nose Cap contains the Pilot and Drogue Chutes and the Frustum contains the three Main Parachutes, Altitude Switches and forward booster Separation Motors. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Experimental investigation of a solid rocket combustion simulator

NASA Technical Reports Server (NTRS)

Frederick, Robert A., Jr.

1991-01-01

The response of solid rocket motor materials to high-temperature corrosive gases is usually accomplished by testing the materials in a subscale solid rocket motor. While this imposes the proper thermal and chemical environment, a solid rocket motor does not provide practical features that would enhance systematic evaluations such as: the ability to throttle for margin testing, on/off capability, low test cost, and a low-hazards test article. Solid Rocket Combustion Simulators (SRCS) are being evaluated by NASA to test solid rocket nozzle materials and incorporate these essential practical features into the testing of rocket materials. The SRCS is designed to generate the thermochemical environment of a solid rocket. It uses hybrid rocket motor technology in which gaseous oxygen (Gox) is injected into a chamber containing a solid fuel grain. Specific chemicals are injected in the aft mixing chamber so that the gases entering the test section match the temperature and a non-dimensional erosion factor B' to insure similarity with a solid motor. Because the oxygen flow can be controlled, this approach allows margin testing, the ability to throttle, and an on/off capability. The fuel grains are inert which makes the test article very safe to handle. The objective of this work was to establish the baseline operating characteristics of a Labscale Solid Rocket Combustion Simulator (LSRCS). This included establishing the baseline burning rates of plexiglass fuels and the evaluation of a combustion instability for hydroxy-terminated polybutadyene (HTPB) propellants. The scope of the project included: (1) activation of MSFC Labscale Hybrid Combustion Simulator; (2) testing of plexiglass fuel at Gox ranges from 0.025 to 0.200 lb/s; (3) burning HTPB fuels at a Gox rate of 0.200 lb/s using four different mixing chamber configurations; and (4) evaluating the fuel regression and chamber pressure responses of each firing.

Hybrid Rocket Motor Test

NASA Technical Reports Server (NTRS)

1994-01-01

A 10,000-pound thrust hybrid rocket motor is tested at Stennis Space Center's E-1 test facility. A hybrid rocket motor is a cross between a solid rocket and a liquid-fueled engine. It uses environmentally safe solid fuel and liquid oxygen.

Development of a new generation solid rocket motor ignition computer code

NASA Technical Reports Server (NTRS)

Foster, Winfred A., Jr.; Jenkins, Rhonald M.; Ciucci, Alessandro; Johnson, Shelby D.

1994-01-01

This report presents the results of experimental and numerical investigations of the flow field in the head-end star grain slots of the Space Shuttle Solid Rocket Motor. This work provided the basis for the development of an improved solid rocket motor ignition transient code which is also described in this report. The correlation between the experimental and numerical results is excellent and provides a firm basis for the development of a fully three-dimensional solid rocket motor ignition transient computer code.

GOES-R Atlas V Solid Rocket Motor (SRM) Lift and Mate

NASA Image and Video Library

2016-10-27

A United Launch Alliance (ULA) technician inspects the solid rocket motor for the ULA Atlas V rocket on its transporter near the Vertical Integration Facility at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. The solid rocket motor will be lifted and mated to the rocket in preparation for the launch of NOAA's Geostationary Operational Environmental Satellite (GOES-R) this month. GOES-R is the first satellite in a series of next-generation NOAA GOES Satellites.

General view of a fully assembled Solid Rocket Booster sitting ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

General view of a fully assembled Solid Rocket Booster sitting atop the Mobile Launch Platform in the Vehicle Assembly Building at Kennedy Space Center - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Closeup view of the Solid Rocket Booster (SRB) Forward Skirt ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Close-up view of the Solid Rocket Booster (SRB) Forward Skirt sitting on ground support equipment in the Solid Rocket Booster Assembly and Refurbishment Facility at Kennedy Space Center while being prepared for mating with the Frustum-Nose Cap Assembly and the Forward Rocket Motor Segment. The prominent feature in this view is the Forward Thrust Attach Fitting which mates up with the Forward Thrust Attach Fitting of the External Tank (ET) at the ends of the SRB Beam that runs through the ET's Inter Tank Assembly. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Space Shuttle Projects

NASA Image and Video Library

1975-01-01

As early as September 1972, the Marshall Space Flight Center arnounced plans for a series of 20 water-entry simulation tests with a solid-fueled rocket casing assembly. The tests would provide valuable data for assessment of solid rocket booster parachute water recovery and aid in preliminary solid rocket motor design.

KSC-07pd1487

NASA Image and Video Library

2007-06-11

KENNEDY SPACE CENTER, FLA. -- Three solid rocket boosters are suspended in the mobile service tower on Launch Pad 17-B at Cape Canaveral Air Force Station for mating to the Delta II first stage for launch of the Dawn spacecraft. Dawn's goal is to characterize the conditions and processes of the solar system's earliest epoch 4.5 billion years ago by investigating in detail two of the largest asteroids, Ceres and Vesta. They reside between Mars and Jupiter in the asteroid belt. Launch is targeted for July 7. Photo credit: NASA/Jim Grossmann

KSC-07pd1477

NASA Image and Video Library

2007-06-11

KENNEDY SPACE CENTER, FLA. -- This closeup shows four of the nine solid rocket boosters being mated to the Delta II first stage on Launch Pad 17-B at Cape Canaveral Air Force Station for launch of the Dawn spacecraft. Dawn's goal is to characterize the conditions and processes of the solar system's earliest epoch 4.5 billion years ago by investigating in detail two of the largest asteroids, Ceres and Vesta. They reside between Mars and Jupiter in the asteroid belt. Launch is targeted for July 7. Photo credit: NASA/Jim Grossmann

KSC-07pd1483

NASA Image and Video Library

2007-06-11

KENNEDY SPACE CENTER, FLA. -- A solid rocket booster is lifted into the mobile service tower on Launch Pad 17-B at Cape Canaveral Air Force Station. The booster will be mated to the Delta II first stage for launch of the Dawn spacecraft. Dawn's goal is to characterize the conditions and processes of the solar system's earliest epoch 4.5 billion years ago by investigating in detail two of the largest asteroids, Ceres and Vesta. They reside between Mars and Jupiter in the asteroid belt. Launch is targeted for July 7. Photo credit: NASA/Jim Grossmann

KSC-07pd1479

NASA Image and Video Library

2007-06-11

KENNEDY SPACE CENTER, FLA. -- Another solid rocket booster arrives on Launch Pad 17-B at Cape Canaveral Air Force Station to be mated to the Delta II first stage. The Delta is the launch vehicle for the Dawn spacecraft. Dawn's goal is to characterize the conditions and processes of the solar system's earliest epoch 4.5 billion years ago by investigating in detail two of the largest asteroids, Ceres and Vesta. They reside between Mars and Jupiter in the asteroid belt. Launch is targeted for July 7. Photo credit: NASA/Jim Grossmann

Ignition transient analysis of solid rocket motor

NASA Technical Reports Server (NTRS)

Han, Samuel S.

1990-01-01

To predict pressure-time and thrust-time behavior of solid rocket motors, a one-dimensional numerical model is developed. The ignition phase of solid rocket motors (time less than 0.4 sec) depends critically on complex interactions among many elements, such as rocket geometry, heat and mass transfer, flow development, and chemical reactions. The present model solves the mass, momentum, and energy equations governing the transfer processes in the rocket chamber as well as the attached converging-diverging nozzle. A qualitative agreement with the SRM test data in terms of head-end pressure gradient and the total thrust build-up is obtained. Numerical results show that the burning rate in the star-segmented head-end section and the erosive burning are two important parameters in the ignition transient of the solid rocket motor (SRM).

Study of solid rocket motors for a space shuttle booster. Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

1972-01-01

An analysis of the solid propellant rocket engines for use with the space shuttle booster was conducted. A definition of the specific solid propellant rocket engine stage designs, development program requirements, production requirements, launch requirements, and cost data for each program phase were developed.

General view of a Solid Rocket Motor Forward Segment in ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

General view of a Solid Rocket Motor Forward Segment in the process of being offloaded from it's railcar inside the Rotation Processing and Surge Facility at Kennedy Space Center. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Study of solid rocket motor for a space shuttle booster

NASA Technical Reports Server (NTRS)

1972-01-01

The study of solid rocket motors for a space shuttle booster was directed toward definition of a parallel-burn shuttle booster using two 156-in.-dia solid rocket motors. The study effort was organized into the following major task areas: system studies, preliminary design, program planning, and program costing.

Dynamic characterization of solid rockets

NASA Technical Reports Server (NTRS)

1973-01-01

The structural dynamics of solid rockets in-general was studied. A review is given of the modes of vibration and bending that can exist for a solid propellant rocket, and a NASTRAN computer model is included. Also studied were the dynamic properties of a solid propellant, polybutadiene-acrylic acid-acrylonitrile terpolymer, which may be used in the space shuttle rocket booster. The theory of viscoelastic materials (i.e, Poisson's ratio) was employed in describing the dynamic properties of the propellant. These studies were performed for an eventual booster stage development program for the space shuttle.

KENNEDY SPACE CENTER, FLA. - Seen from below and through a solid rocket booster segment mockup, Jeff Thon, an SRB mechanic with United Space Alliance, tests the feasibility of a vertical solid rocket booster propellant grain inspection technique. The inspection of segments is required as part of safety analysis.

NASA Image and Video Library

2003-09-11

KENNEDY SPACE CENTER, FLA. - Seen from below and through a solid rocket booster segment mockup, Jeff Thon, an SRB mechanic with United Space Alliance, tests the feasibility of a vertical solid rocket booster propellant grain inspection technique. The inspection of segments is required as part of safety analysis.

General view of a Solid Rocket Motor Nozzle in the ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

General view of a Solid Rocket Motor Nozzle in the Solid Rocket Booster (SRB) Assembly and Refurbishment Facility at Kennedy Space Center, being prepared to be mated with the Aft Skirt. In this view you can see the attach brackets where the Thrust Vector Control System actuators connect to the nozzle which can swivel the nozzle up to 3.5 degrees to redirect the thrust to steer and maintain the Shuttle's programmed trajectory. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Closeup view of the Solid Rocket Booster (SRB) Forward Skirt, ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Close-up view of the Solid Rocket Booster (SRB) Forward Skirt, Frustum and Nose Cap mated assembly undergoing final preparations in the Solid Rocket Booster Assembly and Refurbishment Facility at Kennedy Space Center. The prominent feature in this view is the Forward Thrust Attach Fitting which mates up with the Forward Thrust Attach Fitting of the External Tank (ET) at the ends of the SRB Beam that runs through the ET's Inter Tank Assembly. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Closeup view of the Solid Rocket Booster (SRB) Nose Caps ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Close-up view of the Solid Rocket Booster (SRB) Nose Caps mounted on ground support equipment in the Solid Rocket Booster Assembly and Refurbishment Facility at Kennedy Space Center as they are being prepared for attachment to the SRB Frustum. The Nose Cap contains the Pilot and Drogue Chutes that are deployed prior to the main chutes as the SRBs descend to a splashdown in the Atlantic Ocean where they are recovered refurbished and reused. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

KSC-06pd2287

NASA Image and Video Library

2006-10-12

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, the external tank is transferred from the checkout cell for attaching to its twin solid rocket boosters on the mobile launch platform in highbay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6-feet wide and 154-feet tall. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6-feet wide and 154-feet tall. STS-116 will be mission no. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

Space Shuttle with rail system and aft thrust structure securing solid rocket boosters to external tank

NASA Technical Reports Server (NTRS)

Vonpragenau, G. L. (Inventor)

1984-01-01

The configuration and relationship of the external propellant tank and solid rocket boosters of space transportation systems such as the space shuttle are described. The space shuttle system with the improved propellant tank is shown. The external tank has a forward pressure vessel for liquid hydrogen and an aft pressure vessel for liquid oxygen. The solid rocket boosters are joined together by a thrust frame which extends across and behind the external tank. The thrust of the orbiter's main rocket engines are transmitted to the aft portion of the external tank and the thrust of the solid rocket boosters are transmitted to the aft end of the external tank.

Design of a Six Degree of Freedom Thrust Sensor for a Hybrid Rocket

NASA Astrophysics Data System (ADS)

McGehee, Tripp

2005-03-01

A hybrid rocket is composed of a solid fuel and a separate liquid or gaseous oxidizer. These rockets may be throttled like liquid rockets, are safer than solid rockets, and are much less complex than liquid rockets. However, hybrid rockets produce thrust oscillations that are not practical for large scale use. A lab scale hybrid rocket at the University of Arkansas at Little Rock (UALR) Hybrid Rocket Facility is used to develop sensors to measure physical properties of hybrid rockets. Research is currently being conducted to design a six degree of freedom force sensor to measure the thrust and torque in all three spatial dimensions. The current design mounts the rocket in a rigid cage and connects the cage to a solid table by six sensor legs. The legs utilize strain gauges and a Wheatstone bridge to produce a voltage proportional to the force on the leg. A detailed description of the cage design and the design process will be given.

Probabilistic failure assessment with application to solid rocket motors

NASA Technical Reports Server (NTRS)

Jan, Darrell L.; Davidson, Barry D.; Moore, Nicholas R.

1990-01-01

A quantitative methodology is being developed for assessment of risk of failure of solid rocket motors. This probabilistic methodology employs best available engineering models and available information in a stochastic framework. The framework accounts for incomplete knowledge of governing parameters, intrinsic variability, and failure model specification error. Earlier case studies have been conducted on several failure modes of the Space Shuttle Main Engine. Work in progress on application of this probabilistic approach to large solid rocket boosters such as the Advanced Solid Rocket Motor for the Space Shuttle is described. Failure due to debonding has been selected as the first case study for large solid rocket motors (SRMs) since it accounts for a significant number of historical SRM failures. Impact of incomplete knowledge of governing parameters and failure model specification errors is expected to be important.

Rocket Engines Displayed for 1966 Inspection at Lewis Research Center

NASA Image and Video Library

1966-10-21

An array of rocket engines displayed in the Propulsion Systems Laboratory for the 1966 Inspection held at the National Aeronautics and Space Administration (NASA) Lewis Research Center. Lewis engineers had been working on chemical, nuclear, and solid rocket engines throughout the 1960s. The engines on display are from left to right: two scale models of the Aerojet M-1, a Rocketdyne J-2, a Pratt and Whitney RL-10, and a Rocketdyne throttleable engine. Also on display are several ejector plates and nozzles. The Chemical Rocket Division resolved issues such as combustion instability and screech, and improved operation of cooling systems and turbopumps. The 1.5-million pound thrust M-1 engine was the largest hydrogen-fueled rocket engine ever created. It was a joint project between NASA Lewis and Aerojet-General. Although much larger in size, the M-1 used technology developed for the RL-10 and J-2. The M-1 program was cancelled in late 1965 due to budget cuts and the lack of a post-Apollo mission. The October 1966 Inspection was the culmination of almost a year of events held to mark the centers’ 25th anniversary. The three‐day Inspection, Lewis’ first since 1957, drew 2000 business, industry, and government executives and included an employee open house. The visitors witnessed presentations at the major facilities and viewed the Gemini VII spacecraft, a Centaur rocket, and other displays in the hangar. In addition, Lewis’ newest facility, the Zero Gravity Facility, was shown off for the first time.

Delta II JPSS-1 Solid Rocket Motor Hoist and Mate

NASA Image and Video Library

2016-07-19

The United Launch Alliance/Orbital ATK Delta II solid rocket motor arrives at Space Launch Complex 2 at Vandenberg Air Force Base in California. Technicians and engineers lift and mate the solid rocket motor to a Delta II rocket in preparation for launch of the Joint Polar Satellite System-1 (JPSS-1) later this year. JPSS, a next-generation environmental satellite system, is a collaborative program between the National Oceanic and Atmospheric Administration (NOAA) and NASA.

Delta II JPSS-1 Solid Rocket Motor (SRM) Installation

NASA Image and Video Library

2017-04-04

The United Launch Alliance/Orbital ATK Delta II solid rocket motor arrives at Space Launch Complex 2 at Vandenberg Air Force Base in California. Technicians and engineers lift and mate the solid rocket motor to a Delta II rocket in preparation for launch of the Joint Polar Satellite System-1 (JPSS-1) later this year. JPSS, a next-generation environmental satellite system, is a collaborative program between the National Oceanic and Atmospheric Administration (NOAA) and NASA.

Closeup view of the Solid Rocket Booster Frustum and Nose ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Close-up view of the Solid Rocket Booster Frustum and Nose Cap assembly undergoing preparations and assembly procedures in the Solid Rocket Booster Assembly and Refurbishment Facility at Kennedy Space Center. The Nose Cap contains the Pilot and Drogue Chutes and the Frustum contains the three Main Parachutes, Altitude Switches and forward booster Separation Motors. In this view the assembly is rotated so that the four Separation Motors are in view and aligned with the approximate centerline of the image. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Assessment of tbe Performance of Ablative Insulators Under Realistic Solid Rocket Motor Operating Conditions (a Doctoral Dissertation)

NASA Technical Reports Server (NTRS)

Martin, Heath Thomas

2013-01-01

Ablative insulators are used in the interior surfaces of solid rocket motors to prevent the mechanical structure of the rocket from failing due to intense heating by the high-temperature solid-propellant combustion products. The complexity of the ablation process underscores the need for ablative material response data procured from a realistic solid rocket motor environment, where all of the potential contributions to material degradation are present and in their appropriate proportions. For this purpose, the present study examines ablative material behavior in a laboratory-scale solid rocket motor. The test apparatus includes a planar, two-dimensional flow channel in which flat ablative material samples are installed downstream of an aluminized solid propellant grain and imaged via real-time X-ray radiography. In this way, the in-situ transient thermal response of an ablator to all of the thermal, chemical, and mechanical erosion mechanisms present in a solid rocket environment can be observed and recorded. The ablative material is instrumented with multiple micro-thermocouples, so that in-depth temperature histories are known. Both total heat flux and thermal radiation flux gauges have been designed, fabricated, and tested to characterize the thermal environment to which the ablative material samples are exposed. These tests not only allow different ablative materials to be compared in a realistic solid rocket motor environment but also improve the understanding of the mechanisms that influence the erosion behavior of a given ablative material.

Complex Burn Region Module (CBRM) update

NASA Technical Reports Server (NTRS)

Adams, Carl L.; Jenkins, Billy

1991-01-01

Presented here is a Complex Burn Region Module (CBRM) update for the Solid Rocket Internal Ballistics Module (SRIBM) Program for the Advanced Solid Rocket Motor (ASRM) design/performance assessments. The goal was to develop an improved version of the solid rocket internal ballistics module program that contains a diversified complex region model for motor grain design, performance prediction, and evaluation.

Solid rocket motor certification to meet space shuttle requirements from challenge to achievement

NASA Technical Reports Server (NTRS)

Miller, J. Q.; Kilminster, J. C.

1985-01-01

Three solid rocket motor (SRM) design requirements for the Space Shuttle were discussed. No existing solid rocket motor experience was available for the requirement for a thrust-time trace, twenty uses for the principle hardware, and a moveable nozzle with an 8 deg. omnivaxial vectoring capability. The solutions to these problems are presented.

Solid rocket booster internal flow analysis by highly accurate adaptive computational methods

NASA Technical Reports Server (NTRS)

Huang, C. Y.; Tworzydlo, W.; Oden, J. T.; Bass, J. M.; Cullen, C.; Vadaketh, S.

1991-01-01

The primary objective of this project was to develop an adaptive finite element flow solver for simulating internal flows in the solid rocket booster. Described here is a unique flow simulator code for analyzing highly complex flow phenomena in the solid rocket booster. New methodologies and features incorporated into this analysis tool are described.

The aerodynamic challenges of SRB recovery

NASA Technical Reports Server (NTRS)

Bacchus, D. L.; Kross, D. A.; Moog, R. D.

1985-01-01

Recovery and reuse of the Space Shuttle solid rocket boosters was baselined to support the primary goal to develop a low cost space transportation system. The recovery system required for the 170,000-lb boosters was for the largest and heaviest object yet to be retrieved from exoatmospheric conditions. State-of-the-art design procedures were ground-ruled and development testing minimized to produce both a reliable and cost effective system. The ability to utilize the inherent drag of the boosters during the initial phase of reentry was a key factor in minimizing the parachute loads, size and weight. A wind tunnel test program was devised to enable the accurate prediction of booster aerodynamic characteristics. Concurrently, wind tunnel, rocket sled and air drop tests were performed to develop and verify the performance of the parachute decelerator subsystem. Aerodynamic problems encountered during the overall recovery system development and the respective solutions are emphasized.

Space Shuttle Reusable Solid Rocket Motor Program Overview and Lessons Learned

NASA Technical Reports Server (NTRS)

Graves, Stan R.; McCool, Alex (Technical Monitor)

2001-01-01

An overview of the Space Shuttle Reusable Solid Rocket Motor (RSRM) program is provided with a summary of lessons learned since the first test firing in 1977. Fifteen different lessons learned are discussed that fundamentally changed the motor's design, processing, and RSRM program risk management systems. The evolution of the rocket motor design is presented including the baseline or High Performance Solid Rocket Motor (HPM), the Filament Wound Case (FWC), the RSRM, and the proposed Five-Segment Booster (FSB).

A system level model for preliminary design of a space propulsion solid rocket motor

NASA Astrophysics Data System (ADS)

Schumacher, Daniel M.

Preliminary design of space propulsion solid rocket motors entails a combination of components and subsystems. Expert design tools exist to find near optimal performance of subsystems and components. Conversely, there is no system level preliminary design process for space propulsion solid rocket motors that is capable of synthesizing customer requirements into a high utility design for the customer. The preliminary design process for space propulsion solid rocket motors typically builds on existing designs and pursues feasible rather than the most favorable design. Classical optimization is an extremely challenging method when dealing with the complex behavior of an integrated system. The complexity and combinations of system configurations make the number of the design parameters that are traded off unreasonable when manual techniques are used. Existing multi-disciplinary optimization approaches generally address estimating ratios and correlations rather than utilizing mathematical models. The developed system level model utilizes the Genetic Algorithm to perform the necessary population searches to efficiently replace the human iterations required during a typical solid rocket motor preliminary design. This research augments, automates, and increases the fidelity of the existing preliminary design process for space propulsion solid rocket motors. The system level aspect of this preliminary design process, and the ability to synthesize space propulsion solid rocket motor requirements into a near optimal design, is achievable. The process of developing the motor performance estimate and the system level model of a space propulsion solid rocket motor is described in detail. The results of this research indicate that the model is valid for use and able to manage a very large number of variable inputs and constraints towards the pursuit of the best possible design.

Past and Present Large Solid Rocket Motor Test Capabilities

NASA Technical Reports Server (NTRS)

Kowalski, Robert R.; Owen, David B., II

2011-01-01

A study was performed to identify the current and historical trends in the capability of solid rocket motor testing in the United States. The study focused on test positions capable of testing solid rocket motors of at least 10,000 lbf thrust. Top-level information was collected for two distinct data points plus/minus a few years: 2000 (Y2K) and 2010 (Present). Data was combined from many sources, but primarily focused on data from the Chemical Propulsion Information Analysis Center s Rocket Propulsion Test Facilities Database, and heritage Chemical Propulsion Information Agency/M8 Solid Rocket Motor Static Test Facilities Manual. Data for the Rocket Propulsion Test Facilities Database and heritage M8 Solid Rocket Motor Static Test Facilities Manual is provided to the Chemical Propulsion Information Analysis Center directly from the test facilities. Information for each test cell for each time period was compiled and plotted to produce a graphical display of the changes for the nation, NASA, Department of Defense, and commercial organizations during the past ten years. Major groups of plots include test facility by geographic location, test cells by status/utilization, and test cells by maximum thrust capability. The results are discussed.

Infrared Imagery of Solid Rocket Exhaust Plumes

NASA Technical Reports Server (NTRS)

Moran, Robert P.; Houston, Janice D.

2011-01-01

The Ares I Scale Model Acoustic Test program consisted of a series of 18 solid rocket motor static firings, simulating the liftoff conditions of the Ares I five-segment Reusable Solid Rocket Motor Vehicle. Primary test objectives included acquiring acoustic and pressure data which will be used to validate analytical models for the prediction of Ares 1 liftoff acoustics and ignition overpressure environments. The test article consisted of a 5% scale Ares I vehicle and launch tower mounted on the Mobile Launch Pad. The testing also incorporated several Water Sound Suppression Systems. Infrared imagery was employed during the solid rocket testing to support the validation or improvement of analytical models, and identify corollaries between rocket plume size or shape and the accompanying measured level of noise suppression obtained by water sound suppression systems.

Integration of Flex Nozzle System and Electro Hydraulic Actuators to Solid Rocket Motors

NASA Astrophysics Data System (ADS)

Nayani, Kishore Nath; Bajaj, Dinesh Kumar

2017-10-01

A rocket motor assembly comprised of solid rocket motor and flex nozzle system. Integration of flex nozzle system and hydraulic actuators to the solid rocket motors are done after transportation to the required place where integration occurred. The flex nozzle system is integrated to the rocket motor in horizontal condition and the electro hydraulic actuators are assembled to the flex nozzle systems. The electro hydraulic actuators are connected to the hydraulic power pack to operate the actuators. The nozzle-motor critical interface are insulation diametrical compression, inhibition resin-28, insulation facial compression, shaft seal `O' ring compression and face seal `O' ring compression.

The Alabama Space and Rocket Center: The Second Decade.

ERIC Educational Resources Information Center

Buckbee, Edward O.

1983-01-01

The Alabama Space and Rocket Center in Huntsville, the world's largest rocket and space museum, includes displays illustrating American rocket history, exhibits and demonstrations on rocketry principles and experiences, and simulations of space travel. A new project includes an integrated recreational-educational complex, described in the three…

KSC-06pd2292

NASA Image and Video Library

2006-10-13

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, the external tank is mated to its twin solid rocket boosters on the mobile launch platform in high bay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6 feet wide and 154 feet tall. STS-116 will be mission No. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

KSC-06pd2291

NASA Image and Video Library

2006-10-13

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, the external tank is mated to its twin solid rocket boosters on the mobile launch platform in high bay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6 feet wide and 154 feet tall. STS-116 will be mission No. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

KSC-06pd2289

NASA Image and Video Library

2006-10-13

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, the external tank is mated to its twin solid rocket boosters on the mobile launch platform in high bay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6-feet wide and 154-feet tall. STS-116 will be mission No. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

KSC-06pd2290

NASA Image and Video Library

2006-10-13

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, the external tank is mated to its twin solid rocket boosters on the mobile launch platform in high bay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the space shuttle system at 27.6 feet wide and 154 feet tall. STS-116 will be mission No. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

KSC-06pd2293

NASA Image and Video Library

2006-10-13

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, the external tank is mated to its twin solid rocket boosters on the mobile launch platform in high bay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6 feet wide and 154 feet tall. STS-116 will be mission No. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

Hybrid rockets - Combining the best of liquids and solids

NASA Technical Reports Server (NTRS)

Cook, Jerry R.; Goldberg, Ben E.; Estey, Paul N.; Wiley, Dan R.

1992-01-01

Hybrid rockets employing liquid oxidizer and solid fuel grain answers to cost, safety, reliability, and environmental impact concerns that have become as prominent as performance in recent years. The oxidizer-free grain has limited sensitivity to grain anomalies, such as bond-line separations, which can cause catastrophic failures in solid rocket motors. An account is presently given of the development effort associated with the AMROC commercial hybrid booster and component testing efforts at NASA-Marshall. These hybrid rockets can be fired, terminated, inspected, evaluated, and restarted for additional testing.

Space shuttle propulsion systems

NASA Technical Reports Server (NTRS)

Bardos, Russell

1991-01-01

This is a presentation of view graphs. The design parameters are given for the redesigned solid rocket motor (RSRM), the Advanced Solid Rocket Motor (ASRM), Space Shuttle Main Engine (SSME), Solid Rocket Booster (SRB) separation motor, Orbit Maneuvering System (OMS), and the Reaction Control System (RCS) primary and Vernier thrusters. Space shuttle propulsion issues are outlined along with ASA program definition, ASA program selection methodology, its priorities, candidates, and categories.

General view of the Aft Skirt Assembly and the Aft ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

General view of the Aft Skirt Assembly and the Aft Solid Rocket Motor Segment mated together in the Vehicle Assembly Building at Kennedy Space Center and being prepared for mounting onto the Mobile Launch Platform and mating with the other Solid Rocket Booster segments. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Analyses of Noise from Reusable Solid Rocket Motor (RSRM) Firings

NASA Technical Reports Server (NTRS)

Gee, Kent L.; Kenny, R. Jeremy; Jerome, Trevor W.; Neilsen, Tracianne B.; Hobbs, Christopher M.; James, Michael M.

2012-01-01

NASA s Space Launch Vehicle (SLS) program has chosen the Reusable Solid Rocket Motor V (RSRMV) as the booster system for initial flights. Lift off acoustics continue to be a consideration in overall vehicle vibroacoustic evaluations and launch pad modifications. Work started with the Ares program to understand solid rocket noise mechanisms is continuing through SLS program in conjunction with BYU/Blue Ridge Research Consulting.

Tight Fits for Americas Next Moon Rocket, Ares V

NASA Technical Reports Server (NTRS)

Jaap, John; Fisher, Wyatt; Richardson, Lea

2010-01-01

America has begun the development of a new heavy lift rocket which will enable humans to return to the moon and reach even farther destinations. Five decades ago, the National Aeronautics and Space Administration designed a system (called Saturn/Apollo) to carry men to the moon and back; the rocket which boosted them to the moon was the Saturn V. Saturn V was huge relative to contemporary rockets and is still the largest rocket ever launched. The new moon rocket is called Ares V. It will insert 40% more payload into low earth orbit than Saturn V; and after docking with the crew spacecraft, it will insert 50% more payload onto the translunar trajectory than Saturn V. The current design of Ares V calls for two liquid-fueled stages and 2 "strap-on" solid rockets. The solid rockets are extended-length versions of the solid rockets used on the Shuttle. The diameter of the liquid stages is at least as large as the first stage of the Saturn V; the height of the lower liquid stage (called the core stage) is longer than the external tank of the Shuttle. Huge rockets require huge infrastructure and, during the Saturn/Apollo era, America invested significantly in manufacturing, assembly and launch facilities which are still in use today. Since the Saturn/Apollo era, America has invested in additional infrastructure for the Shuttle program. Ares V must utilize this existing infrastructure, with reasonable modifications. Building a rocket with 50% more capability in the same buildings, testing it in the same test stands, shipping on the same canals under the same bridges, assembling it in the same building, rolling it to the pad on the same crawler, and launching it from the same launch pad is an engineering and logistics challenge which goes hand-in-hand with designing the structure, tanks, turbines, engines, software, etc. necessary to carry such a large payload to earth orbit and to the moon. This paper quantitatively discusses the significant "tight fits" that are constraining Ares V. The engineers designing and building the infrastructure for the Saturn/Apollo program usually added margins and growth capability; sometimes the size of existing facilities (such as the width of a draw bridge) was not a constraint. Ares V may utilize the "extra" space in the existing facilities and expand other tight fits. Some of the tight fits cannot be overcome without great expense; raising the roof on the Vertical Assembly Building for example. Other tight fits are easily overcome; the transporter at the manufacturing facility for the core stage can pass under low ceilings and later over a dike (without dragging the middle) by retracting or extending the struts which support the stage. Tight fits discussed in this paper include manufacturing (jigs, widths, heights, and local transportation), testing (test stand sizes and crane capability), transportation to the test stands and the launch site (barge, waterway, and rail), assembly (VAB internal dimensions and door size), roll-out limits, and launch pad size.

On the nature of the fragment environment created by the range destruction or random failure of solid rocket motor casings

NASA Technical Reports Server (NTRS)

Eck, M.; Mukunda, M.

1988-01-01

Given here are predictions of fragment velocities and azimuths resulting from the Space Transportation System Solid Rocket Motor range destruct, or random failure occurring at any time during the 120 seconds of Solid Rocket Motor burn. Results obtained using the analytical methods described showed good agreement between predictions and observations for two specific events. It was shown that these methods have good potential for use in predicting the fragmentation process of a number of generically similar casing systems. It was concluded that coupled Eulerian-Lagrangian calculational methods of the type described here provide a powerful tool for predicting Solid Rocket Motor response.

Controllable Solid Propulsion Combustion and Acoustic Knowledge Base Improvements

NASA Technical Reports Server (NTRS)

McCauley, Rachel; Fischbach, Sean; Fredrick, Robert

2012-01-01

Controllable solid propulsion systems have distinctive combustion and acoustic environments that require enhanced testing and analysis techniques to progress this new technology from development to production. In a hot gas valve actuating system, the movement of the pintle through the hot gas exhibits complex acoustic disturbances and flow characteristics that can amplify induced pressure loads that can damage or detonate the rocket motor. The geometry of a controllable solid propulsion gas chamber can set up unique unsteady flow which can feed acoustic oscillations patterns that require characterization. Research in this area aids in the understanding of how best to design, test, and analyze future controllable solid rocket motors using the lessons learned from past government programs as well as university research and testing. This survey paper will give the reader a better understanding of the potentially amplifying affects propagated by a controllable solid rocket motor system and the knowledge of the tools current available to address these acoustic disturbances in a preliminary design. Finally the paper will supply lessons learned from past experiences which will allow the reader to come away with understanding of what steps need to be taken when developing a controllable solid rocket propulsion system. The focus of this survey will be on testing and analysis work published by solid rocket programs and from combustion and acoustic books, conference papers, journal articles, and additionally from subject matter experts dealing currently with controllable solid rocket acoustic analysis.

General view of the Aft Solid Rocket Motor Segment mated ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

General view of the Aft Solid Rocket Motor Segment mated with the Aft Skirt Assembly and External Tank Attach Ring in the Rotation Processing and Surge Facility at Kennedy Space Center and awaiting transfer to the Vehicle Assembly Building where it will be mounted onto the Mobile Launch Platform. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Design and Fabrication of a 200N Thrust Rocket Motor Based on NH4ClO4+Al+HTPB as Solid Propellant

NASA Astrophysics Data System (ADS)

Wahid, Mastura Ab; Ali, Wan Khairuddin Wan

2010-06-01

The development of rocket motor using potassium nitrate, carbon and sulphur mixture has successfully been developed by researchers and students from UTM and recently a new combination for solid propellant is being created. The new solid propellant will combine a composition of Ammonium perchlorate, NH4ClO4 with aluminium, Al and Hydroxyl Terminated Polybutadiene, HTPB as the binder. It is the aim of this research to design and fabricate a new rocket motor that will produce a thrust of 200N by using this new solid propellant. A static test is done to obtain the thrust produced by the rocket motor and analyses by observation and also calculation will be done. The experiment for the rocket motor is successful but the thrust did not achieve its required thrust.

Analysis of the measured effects of the principal exhaust effluents from solid rocket motors

NASA Technical Reports Server (NTRS)

Dawbarn, R.; Kinslow, M.; Watson, D. J.

1980-01-01

The feasibility of conducting environmental chamber tests using a small rocket motor to study the physical processes which occur when the exhaust products from solid motors mix with the ambient atmosphere was investigated. Of particular interest was the interaction between hydrogen chloride, aluminum oxide, and water vapor. Several types of instruments for measuring HCl concentrations were evaluated. Under some conditions it was noted that acid aerosols were formed in the ground cloud. These droplets condensed on Al2O3 nuclei and were associated with the rocket exhaust cooling during the period of plume rise to stabilization. Outdoor firings of the solid rocket motors of a 6.4 percent scaled model of the space shuttle were monitored to study the interaction of the exhaust effluents with vegetation downwind of the test site. Data concerning aluminum oxide particles produced by solid rocket motors were evaluated.

Space Shuttle Projects

NASA Image and Video Library

1989-06-03

The Marshall Space Flight Center (MSFC) engineers test fired a 26-foot long, 100,000-pound-thrust solid rocket motor for 30 seconds at the MSFC east test area, the first test firing of the Modified NASA Motor (M-NASA Motor). The M-NASA Motor was fired in a newly constructed stand. The motor is 48-inches in diameter and was loaded with two propellant cartridges weighing a total of approximately 12,000 pounds. The purpose of the test was to learn more about solid rocket motor insulation and nozzle materials and to provide young engineers additional hands-on expertise in solid rocket motor technology. The test is a part of NASA's Solid Propulsion Integrity Program, that is to provide NASA engineers with the techniques, engineering tools, and computer programs to be able to better design, build, and verify solid rocket motors.

Comparisons Between Stability Prediction and Measurements for the Reusable Solid Rocket Motor

NASA Technical Reports Server (NTRS)

Fischbach, Sean R.; Kenny, R. Jeremy

2010-01-01

The Space Transportation System has used the solid rocket boosters for lift-off and ascent propulsion over the history of the program. Part of the structural loads assessment of the assembled vehicle is the contribution due to solid rocket booster thrust oscillations. These thrust oscillations are a consequence of internal motor pressure oscillations active during operation. Understanding of these pressure oscillations is key to predicting the subsequent thrust oscillations and vehicle loading. The pressure oscillation characteristics of the Reusable Solid Rocket Motor (RSRM) design are reviewed in this work. Dynamic pressure data from the static test and flight history are shown, with emphasis on amplitude, frequency, and timing of the oscillations. Physical mechanisms that cause these oscillations are described by comparing data observations to predictions made by the Solid Stability Prediction (SSP) code.

Model of lidar range-Doppler signatures of solid rocket fuel plumes

NASA Astrophysics Data System (ADS)

Bankman, Isaac N.; Giles, John W.; Chan, Stephen C.; Reed, Robert A.

2004-09-01

The analysis of particles produced by solid rocket motor fuels relates to two types of studies: the effect of these particles on the Earth's ozone layer, and the dynamic flight behavior of solid fuel boosters used by the NASA Space Shuttle. Since laser backscatter depends on the particle size and concentration, a lidar system can be used to analyze the particle distributions inside a solid rocket plume in flight. We present an analytical model that simulates the lidar returns from solid rocket plumes including effects of beam profile, spot size, polarization and sensing geometry. The backscatter and extinction coefficients of alumina particles are computed with the T-matrix method that can address non-spherical particles. The outputs of the model include time-resolved return pulses and range-Doppler signatures. Presented examples illustrate the effects of sensing geometry.

Repeated Failures: What We Haven’t Learned About Complex Systems

DTIC Science & Technology

2010-11-01

Computer (OBC) ordered full nozzle deflection for both solid rocket motors and the Vulcain at approximately T +39 seconds. This was based on data...Workmanship/QC: .. Deficiencies in CM design, workmanship and quality control UNCLASSIFIED What h8PPIIDIItl: • Failure of Solid Rocket Motor ...SAM) field joint allowed hot gases to impinge on External Tank (ET) and lower struts ( aft attach points between ET and Solid Rocket Booster (SRB

Closeup view of the Solid Rocket Booster (SRB) Frustum mounted ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Close-up view of the Solid Rocket Booster (SRB) Frustum mounted on ground support equipment in the Solid Rocket Booster Assembly and Refurbishment Facility at Kennedy Space Center as it is being prepared to be mated with the Nose Cap and Forward Skirt. The Frustum contains the three Main Parachutes, Altitude Switches and forward booster Separation Motors. The Separation Motors burn for one second to ensure the SRBs drift away from the External Tank and Orbiter at separation. The three main parachutes are deployed to reduce speed as the SRBs descend to a splashdown in the Atlantic Ocean where they are recovered refurbished and reused. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

GOES-R Atlas V Solid Rocket Motor (SRM) Lift and Mate

NASA Image and Video Library

2016-10-27

Inside the Vertical Integration Facility at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida, the solid rocket motor is mated to the United Launch Alliance Atlas V rocket for its upcoming launch. NOAA's Geostationary Operational Environmental Satellite (GOES-R) will launch aboard the Atlas V rocket this month. GOES-R is the first satellite in a series of next-generation NOAA GOES Satellites.

GOES-R Atlas V Solid Rocket Motor (SRM) Lift and Mate

NASA Image and Video Library

2016-10-27

Inside the Vertical Integration Facility at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida, the solid rocket motor is being mated to the United Launch Alliance Atlas V rocket for its upcoming launch. NOAA's Geostationary Operational Environmental Satellite (GOES-R) will launch aboard the Atlas V rocket this month. GOES-R is the first satellite in a series of next-generation NOAA GOES Satellites.

GOES-R Atlas V Solid Rocket Motor (SRM) Lift and Mate

NASA Image and Video Library

2016-10-27

The solid rocket motor is lifted on its transporter for mating to the United Launch Alliance Atlas V rocket in the Vertical Integration Facility at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. NOAA's Geostationary Operational Environmental Satellite (GOES-R) will launch aboard the Atlas V rocket this month. GOES-R is the first satellite in a series of next-generation NOAA GOES Satellites.

Variable Thrust, Multiple Start Hybrid Motor Solutions for Missile and Space Applications

DTIC Science & Technology

2010-06-01

considered: I. Boost/Sustain/Boost. Simulating a tactical solid rocket motor profile with another boost at the end to demonstrate a "throttle up", this...of tactical solid rocket motors were tested with 75%, 50%, and lower sustain-to- boost chamber pressure ratios with rapid throttle-up achieved... solid rocket motors were tested with 75%, 50%, and lower sustain-to-boost chamber pressure ratios with rapid throttle-up achieved following the sustain

Solid Propellant Nonlinear Constitutive Theory Extension

DTIC Science & Technology

1984-01-01

Force Rocket Propulsion Laboratory, June 1979. Farris, R. J., Hermann , I. R., Hutchinson, J. R., and Schapery, R. A., "Development of a Solid Rocket...Effect of Stretching on the Properties of Rubber," J. Rub. Res., 16, 275-289, 1947. 28. Oberth , A. E., and Brenner, R. S., "Tear Phenomena Around...34Development of a Solid Rocket Propellant Nonlinear Viscoelastic Constitutive Theory," AFRPL-TR-73-50, June 1973. 30. Hermann , L. R., and Peterson, F. E., "A

Development of CT and 3D-CT Using Flat Panel Detector Based Real-Time Digital Radiography System

NASA Astrophysics Data System (ADS)

Ravindran, V. R.; Sreelakshmi, C.; Vibin, Vibin

2008-09-01

The application of Digital Radiography in the Nondestructive Evaluation (NDE) of space vehicle components is a recent development in India. A Real-time DR system based on amorphous silicon Flat Panel Detector has been developed for the NDE of solid rocket motors at Rocket Propellant Plant of VSSC in a few years back. The technique has been successfully established for the nondestructive evaluation of solid rocket motors. The DR images recorded for a few solid rocket specimens are presented in the paper. The Real-time DR system is capable of generating sufficient digital X-ray image data with object rotation for the CT image reconstruction. In this paper the indigenous development of CT imaging based on the Realtime DR system for solid rocket motor is presented. Studies are also carried out to generate 3D-CT image from a set of adjacent CT images of the rocket motor. The capability of revealing the spatial location and characterisation of defect is demonstrated by the CT and 3D-CT images generated.

Development of CT and 3D-CT Using Flat Panel Detector Based Real-Time Digital Radiography System

DOE Office of Scientific and Technical Information (OSTI.GOV)

Ravindran, V. R.; Sreelakshmi, C.; Vibin

2008-09-26

The application of Digital Radiography in the Nondestructive Evaluation (NDE) of space vehicle components is a recent development in India. A Real-time DR system based on amorphous silicon Flat Panel Detector has been developed for the NDE of solid rocket motors at Rocket Propellant Plant of VSSC in a few years back. The technique has been successfully established for the nondestructive evaluation of solid rocket motors. The DR images recorded for a few solid rocket specimens are presented in the paper. The Real-time DR system is capable of generating sufficient digital X-ray image data with object rotation for the CTmore » image reconstruction. In this paper the indigenous development of CT imaging based on the Realtime DR system for solid rocket motor is presented. Studies are also carried out to generate 3D-CT image from a set of adjacent CT images of the rocket motor. The capability of revealing the spatial location and characterisation of defect is demonstrated by the CT and 3D-CT images generated.« less

GOES-R Atlas V Solid Rocket Motor (SRM) Lift and Mate

NASA Image and Video Library

2016-10-27

The solid rocket motor has been lifted to the vertical position and moved into the Vertical Integration Facility at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida for mating to the United Launch Alliance Atlas V rocket. NOAA's Geostationary Operational Environmental Satellite (GOES-R) will launch aboard the Atlas V rocket this month. GOES-R is the first satellite in a series of next-generation NOAA GOES Satellites.

GOES-R Atlas V Solid Rocket Motor (SRM) Lift and Mate

NASA Image and Video Library

2016-10-27

Preparations are underway to lift the solid rocket motor up from its transporter for mating to the United Launch Alliance Atlas V rocket in the Vertical Integration Facility at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. NOAA's Geostationary Operational Environmental Satellite (GOES-R) will launch aboard the Atlas V rocket this month. GOES-R is the first satellite in a series of next-generation NOAA GOES Satellites.

GOES-R Atlas V Solid Rocket Motor (SRM) Lift and Mate

NASA Image and Video Library

2016-10-27

The solid rocket motor has been lifted to the vertical position for mating to the United Launch Alliance Atlas V rocket in the Vertical Integration Facility at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. NOAA's Geostationary Operational Environmental Satellite (GOES-R) will launch aboard the Atlas V rocket this month. GOES-R is the first satellite in a series of next-generation NOAA GOES Satellites.

GOES-R Atlas V Solid Rocket Motor (SRM) Lift and Mate

NASA Image and Video Library

2016-10-27

Technicians with United Launch Alliance (ULA) assist as the solid rocket motor is mated to the ULA Atlas V rocket in the Vertical Integration Facility at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. NOAA's Geostationary Operational Environmental Satellite (GOES-R) will launch aboard the Atlas V rocket this month. GOES-R is the first satellite in a series of next-generation NOAA GOES Satellites.

GOES-R Atlas V Solid Rocket Motor (SRM) Lift and Mate

NASA Image and Video Library

2016-10-27

Technicians with United Launch Alliance (ULA) monitor the progress as the solid rocket motor is mated to the ULA Atlas V rocket in the Vertical Integration Facility at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. NOAA's Geostationary Operational Environmental Satellite (GOES-R) will launch aboard the Atlas V rocket this month. GOES-R is the first satellite in a series of next-generation NOAA GOES Satellites.

A rocket-borne energy spectrometer using multiple solid-state detectors for particle identification

NASA Technical Reports Server (NTRS)

Fries, K. L.; Smith, L. G.; Voss, H. D.

1979-01-01

A rocket-borne experiment using energy spectrometers that allows particle identification by the use of multiple solid-state detectors is described. The instrumentation provides information regarding the energy spectrum, pitch-angle distribution, and the type of energetic particles present in the ionosphere. Particle identification was accomplished by considering detector loss mechanisms and their effects on various types of particles. Solid state detectors with gold and aluminum surfaces of several thicknesses were used. The ratios of measured energies for the various detectors were compared against known relationships during ground-based analysis. Pitch-angle information was obtained by using detectors with small geometrical factors mounted with several look angles. Particle flux was recorded as a function of rocket azimuth angle. By considering the rocket azimuth, the rocket precession, and the location of the detectors on the rocket, the pitched angle of the incident particles was derived.

Space shuttle with common fuel tank for liquid rocket booster and main engines (supertanker space shuttle)

NASA Technical Reports Server (NTRS)

Thorpe, Douglas G.

1991-01-01

An operation and schedule enhancement is shown that replaces the four-body cluster (Space Shuttle Orbiter (SSO), external tank, and two solid rocket boosters) with a simpler two-body cluster (SSO and liquid rocket booster/external tank). At staging velocity, the booster unit (liquid-fueled booster engines and vehicle support structure) is jettisoned while the remaining SSO and supertank continues on to orbit. The simpler two-bodied cluster reduces the processing and stack time until SSO mate from 57 days (for the solid rocket booster) to 20 days (for the liquid rocket booster). The areas in which liquid booster systems are superior to solid rocket boosters are discussed. Alternative and future generation vehicles are reviewed to reveal greater performance and operations enhancements with more modifications to the current methods of propulsion design philosophy, e.g., combined cycle engines, and concentric propellant tanks.

Hybrid propulsion technology program: Phase 1, volume 4

NASA Technical Reports Server (NTRS)

Claflin, S. E.; Beckman, A. W.

1989-01-01

The use of a liquid oxidizer-solid fuel hybrid propellant combination in booster rocket motors appears extremely attractive due to the integration of the best features of liquid and solid propulsion systems. The hybrid rocket combines the high performance, clean exhaust, and safety of liquid propellant engines with the low cost and simplicity of solid propellant motors. Additionally, the hybrid rocket has unique advantages such as an inert fuel grain and a relative insensitivity to fuel grain and oxidizer injection anomalies. The advantages mark the hybrid rocket as a potential replacement or alternative for current and future solid propellant booster systems. The issues are addressed and recommendations are made concerning oxidizer feed systems, injectors, and ignition systems as related to hybrid rocket propulsion. Early in the program a baseline hybrid configuration was established in which liquid oxygen would be injected through ports in a solid fuel whose composition is based on hydroxyl terminated polybutadiene (HTPB). Liquid oxygen remained the recommended oxidizer and thus all of the injector concepts which were evaluated assumed only liquid would be used as the oxidizer.

Technical report analysis and design: Study of solid rocket motors for a space shuttle booster, volume 2, book 1, supplement 1

NASA Technical Reports Server (NTRS)

1972-01-01

An analysis and design effort was conducted as part of the study of solid rocket motor for a space shuttle booster. The 156-inch-diameter, parallel burn solid rocket motor was selected as its baseline because it is transportable and is the most cost-effective, reliable system that has been developed and demonstrated. The basic approach was to concentrate on the selected baseline design, and to draw from the baseline sufficient data to describe the alternate approaches also studied. The following conclusions were reached with respect to technical feasibility of the use of solid rocket booster motors for the space shuttle vehicle: (1) The 156-inch, parallel-burn baseline SRM design meets NASA's study requirements while incorporating conservative safety factors. (2) The solid rocket motor booster represents a cost-effective approach. (3) Baseline costs are conservative and are based on a demonstrated design. (4) Recovery and reuse are feasible and offer substantial cost savings. (5) Abort can be accomplished successfully. (6) Ecological effects are acceptable.

On use of hybrid rocket propulsion for suborbital vehicles

NASA Astrophysics Data System (ADS)

Okninski, Adam

2018-04-01

While the majority of operating suborbital rockets use solid rocket propulsion, recent advancements in the field of hybrid rocket motors lead to renewed interest in their use in sounding rockets. This paper presents results of optimisation of sounding rockets using hybrid propulsion. An overview of vehicles under development during the last decade, as well as heritage systems is provided. Different propellant combinations are discussed and their performance assessment is given. While Liquid Oxygen, Nitrous Oxide and Nitric Acid have been widely tested with various solid fuels in flight, Hydrogen Peroxide remains an oxidiser with very limited sounding rocket applications. The benefits of hybrid propulsion for sounding rockets are given. In case of hybrid rocket motors the thrust curve can be optimised for each flight, using a flow regulator, depending on the payload and mission. Results of studies concerning the optimal burn duration and nozzle selection are given. Specific considerations are provided for the Polish ILR-33 "Amber" sounding rocket. Low regression rates, which up to date were viewed as a drawback of hybrid propulsion may be used to the benefit of maximising rocket performance if small solid rocket boosters are used during the initial flight period. While increased interest in hybrid propulsion is present, no up-to-date reference concerning use of hybrid rocket propulsion for sounding rockets is available. The ultimate goal of the paper is to provide insight into the sensitivity of different design parameters on performance of hybrid sounding rockets and delve into the potential and challenges of using hybrid rocket technology for expendable suborbital applications.

Cape Canaveral Air Force Station, Launch Complex 39, Solid Rocket ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Cape Canaveral Air Force Station, Launch Complex 39, Solid Rocket Booster Disassembly & Refurbishment Complex, Thrust Vector Control Deservicing Facility, Hangar Road, Cape Canaveral, Brevard County, FL

The space shuttle advanced solid rocket motor: Quality control and testing

NASA Technical Reports Server (NTRS)

1991-01-01

The Congressional committees that authorize the activities of NASA requested that the National Research Council (NRC) review the testing and quality assurance programs for the Advanced Solid Rocket Motor (ASRM) program. The proposed ASRM design incorporates numerous features that are significant departures from the Redesigned Solid Rocket Motor (RSRM). The NRC review concentrated mainly on these features. Primary among these are the steel case material, welding rather than pinning of case factory joints, a bolted field joint designed to close upon firing the rocket, continuous mixing and casting of the solid propellant in place of the current batch processes, use of asbestos-free insulation, and a lightweight nozzle. The committee's assessment of these and other features of the ASRM are presented in terms of their potential impact on flight safety.

KSC-06pd2284

NASA Image and Video Library

2006-10-12

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, workers prepare to transfer the external tank from the checkout cell for attaching to its twin solid rocket boosters on the mobile launch platform in highbay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6-feet wide and 154-feet tall. STS-116 will be mission no. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

KSC-06pd2286

NASA Image and Video Library

2006-10-12

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, the external tank is transferred from the checkout cell for attaching to its twin solid rocket boosters on the mobile launch platform in highbay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6-feet wide and 154-feet tall. STS-116 will be mission no. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

KSC-06pd2283

NASA Image and Video Library

2006-10-12

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, workers prepare to transfer the external tank from the checkout cell for attaching to its twin solid rocket boosters on the mobile launch platform in highbay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6-feet wide and 154-feet tall. STS-116 will be mission no. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

KSC-06pd2288

NASA Image and Video Library

2006-10-12

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, the external tank is transferred from the checkout cell for attaching to its twin solid rocket boosters on the mobile launch platform in highbay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6-feet wide and 154-feet tall. STS-116 will be mission no. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

KSC-06pd2285

NASA Image and Video Library

2006-10-12

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, workers prepare to transfer the external tank from the checkout cell for attaching to its twin solid rocket boosters on the mobile launch platform in highbay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6-feet wide and 154-feet tall. STS-116 will be mission no. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

28. HISTORIC VIEW OF A3 ROCKET IN TEST STAND NO. ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

28. HISTORIC VIEW OF A-3 ROCKET IN TEST STAND NO. 3 AT KUMMERSDORF (THE LARGEST TEST STAND AT KUMMERSDORF). THE STAND WAS MOBILE, SINCE IT MOVED ALONG RAILS. - Marshall Space Flight Center, Redstone Rocket (Missile) Test Stand, Dodd Road, Huntsville, Madison County, AL

Fluid-solid coupled simulation of the ignition transient of solid rocket motor

NASA Astrophysics Data System (ADS)

Li, Qiang; Liu, Peijin; He, Guoqiang

2015-05-01

The first period of the solid rocket motor operation is the ignition transient, which involves complex processes and, according to chronological sequence, can be divided into several stages, namely, igniter jet injection, propellant heating and ignition, flame spreading, chamber pressurization and solid propellant deformation. The ignition transient should be comprehensively analyzed because it significantly influences the overall performance of the solid rocket motor. A numerical approach is presented in this paper for simulating the fluid-solid interaction problems in the ignition transient of the solid rocket motor. In the proposed procedure, the time-dependent numerical solutions of the governing equations of internal compressible fluid flow are loosely coupled with those of the geometrical nonlinearity problems to determine the propellant mechanical response and deformation. The well-known Zeldovich-Novozhilov model was employed to model propellant ignition and combustion. The fluid-solid coupling interface data interpolation scheme and coupling instance for different computational agents were also reported. Finally, numerical validation was performed, and the proposed approach was applied to the ignition transient of one laboratory-scale solid rocket motor. For the application, the internal ballistics were obtained from the ground hot firing test, and comparisons were made. Results show that the integrated framework allows us to perform coupled simulations of the propellant ignition, strong unsteady internal fluid flow, and propellant mechanical response in SRMs with satisfactory stability and efficiency and presents a reliable and accurate solution to complex multi-physics problems.

Space shuttle solid rocket booster recovery system definition, volume 1

NASA Technical Reports Server (NTRS)

1973-01-01

The performance requirements, preliminary designs, and development program plans for an airborne recovery system for the space shuttle solid rocket booster are discussed. The analyses performed during the study phase of the program are presented. The basic considerations which established the system configuration are defined. A Monte Carlo statistical technique using random sampling of the probability distribution for the critical water impact parameters was used to determine the failure probability of each solid rocket booster component as functions of impact velocity and component strength capability.

KSC-07pd1509

NASA Image and Video Library

2007-06-15

KENNEDY SPACE CENTER, FLA. -- The second stage of the Delta II launch vehicle for the Dawn spacecraft arrives on Launch Pad 17-B at Cape Canaveral Air Force Station where it will be mated with the first stage. The Delta II-Heavy, manufactured by the United Launch Alliance, is scheduled to launch the Dawn spacecraft on its 4-year flight to the asteroid belt. The Delta II-Heavy is the strongest rocket in the Delta II class. It will use three stages and nine solid-fueled booster rockets to propel Dawn on its way. A 9.5-foot payload fairing will protect the spacecraft from the heat and stresses of launch. Dawn's goal is to characterize the conditions and processes of the solar system's earliest epoch by investigating in detail the largest protoplanets that have remained intact since their formations: asteroid Vesta and the dwarf planet Ceres. They reside in the extensive zone between Mars and Jupiter together with many other smaller bodies, called the asteroid belt. Dawn is scheduled to launch July 7. Photo credit: NASA/Jack Pfaller

KSC-07pd1515

NASA Image and Video Library

2007-06-15

KENNEDY SPACE CENTER, FLA. -- On Launch Pad 17-B at Cape Canaveral Air Force Station, workers maneuver the second stage of the Delta II launch vehicle onto the first stage for mating. The Delta II-Heavy, manufactured by the United Launch Alliance, is scheduled to launch the Dawn spacecraft on its 4-year flight to the asteroid belt. The Delta II-Heavy is the strongest rocket in the Delta II class. It will use three stages and nine solid-fueled booster rockets to propel Dawn on its way. A 9.5-foot payload fairing will protect the spacecraft from the heat and stresses of launch. Dawn's goal is to characterize the conditions and processes of the solar system's earliest epoch by investigating in detail the largest protoplanets that have remained intact since their formations: asteroid Vesta and the dwarf planet Ceres. They reside in the extensive zone between Mars and Jupiter together with many other smaller bodies, called the asteroid belt. Dawn is scheduled to launch July 7. Photo credit: NASA/Jack Pfaller

GOES-R Atlas V Solid Rocket Motor (SRM) Lift and Mate

NASA Image and Video Library

2016-10-27

The solid rocket motor has been lifted to the vertical position on its transporter for mating to the United Launch Alliance Atlas V rocket in the Vertical Integration Facility at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. NOAA's Geostationary Operational Environmental Satellite (GOES-R) will launch aboard the Atlas V rocket this month. GOES-R is the first satellite in a series of next-generation NOAA GOES Satellites.

Solid rocket motor witness test

NASA Technical Reports Server (NTRS)

Welch, Christopher S.

1991-01-01

The Solid Rocket Motor Witness Test was undertaken to examine the potential for using thermal infrared imagery as a tool for monitoring static tests of solid rocket motors. The project consisted of several parts: data acquisition, data analysis, and interpretation. For data acquisition, thermal infrared data were obtained of the DM-9 test of the Space Shuttle Solid Rocket Motor on December 23, 1987, at Thiokol, Inc. test facility near Brigham City, Utah. The data analysis portion consisted of processing the video tapes of the test to produce values of temperature at representative test points on the rocket motor surface as the motor cooled down following the test. Interpretation included formulation of a numerical model and evaluation of some of the conditions of the motor which could be extracted from the data. These parameters included estimates of the insulation remaining following the tests and the thickness of the charred layer of insulation at the end of the test. Also visible was a temperature signature of the star grain pattern in the forward motor segment.

Hydrodynamic Stability Analysis of Particle-Laden Solid Rocket Motors

NASA Astrophysics Data System (ADS)

Elliott, T. S.; Majdalani, J.

2014-11-01

Fluid-wall interactions within solid rocket motors can result in parietal vortex shedding giving rise to hydrodynamic instabilities, or unsteady waves, that translate into pressure oscillations. The oscillations can result in vibrations observed by the rocket, rocket subsystems, or payload, which can lead to changes in flight characteristics, design failure, or other undesirable effects. For many years particles have been embedded in solid rocket propellants with the understanding that their presence increases specific impulse and suppresses fluctuations in the flowfield. This study utilizes a two dimensional framework to understand and quantify the aforementioned two-phase flowfield inside a motor case with a cylindrical grain perforation. This is accomplished through the use of linearized Navier-Stokes equations with the Stokes drag equation and application of the biglobal ansatz. Obtaining the biglobal equations for analysis requires quantification of the mean flowfield within the solid rocket motor. To that end, the extended Taylor-Culick form will be utilized to represent the gaseous phase of the mean flowfield while the self-similar form will be employed for the particle phase. Advancing the mean flowfield by quantifying the particle mass concentration with a semi-analytical solution the finalized mean flowfield is combined with the biglobal equations resulting in a system of eight partial differential equations. This system is solved using an eigensolver within the framework yielding the entire spectrum of eigenvalues, frequency and growth rate components, at once. This work will detail the parametric analysis performed to demonstrate the stabilizing and destabilizing effects of particles within solid rocket combustion.

The development of H-II rocket solid rocket booster thrust vector control system

NASA Astrophysics Data System (ADS)

Nagai, Hirokazu; Fukushima, Yukio; Kazama, Hiroo; Asai, Tatsuro; Okaya, Shunichi; Watanabe, Yasushi; Muramatsu, Shoji

The development of the thrust-vector-control (TVC) system for the two solid rocket boosters (SRBs) of the H-II rocket, which was started in 1984 and completed in 1989, is described. Special attention is given to the system's design, the trade-off studies, and the evaluation of the SRB-TVC system performance, as well as to problems that occurred in the course of the system's development and to the countermeasures that were taken. Schematic diagrams are presented for the H-II rocket, the SRB, and the SRB-TVC system configurations.

Space Shuttle Project

NASA Image and Video Library

1978-01-18

Pictured is an early testing of the Solid Rocket Motor (SRM) at the Thiokol facility in Utah. The SRMs later became known as Solid Rocket Boosters (SRBs) as they were more frequently used on the Space Shuttles.

Space Shuttle Project

NASA Image and Video Library

1977-11-18

This photograph shows Solid Rocket Booster segments undergoing stacking operations in Marshall Space Flight Center's Building 4707. The Solid Rocket Boosters were designed in-house at the Marshall Center with the Thiokol Corporation as the prime contractor.

Performance evaluation of Space Shuttle SRB parachutes from air drop and scaled model wind tunnel tests. [Solid Rocket Booster recovery system

NASA Technical Reports Server (NTRS)

Moog, R. D.; Bacchus, D. L.; Utreja, L. R.

1979-01-01

The aerodynamic performance characteristics have been determined for the Space Shuttle Solid Rocket Booster drogue, main, and pilot parachutes. The performance evaluation on the 20-degree conical ribbon parachutes is based primarily on air drop tests of full scale prototype parachutes. In addition, parametric wind tunnel tests were performed and used in parachute configuration development and preliminary performance assessments. The wind tunnel test data are compared to the drop test results and both sets of data are used to determine the predicted performance of the Solid Rocket Booster flight parachutes. Data from other drop tests of large ribbon parachutes are also compared with the Solid Rocket Booster parachute performance characteristics. Parameters assessed include full open terminal drag coefficients, reefed drag area, opening characteristics, clustering effects, and forebody interference.

Engineers demonstrate the pocket rocket

NASA Technical Reports Server (NTRS)

1996-01-01

Part of Stennis Space Center's mission with its traveling exhibits is to educate the younger generation on how propulsion systems work. A popular tool is the 'pocket rocket,' which demonstrates how a hybrid rocket works. A hybrid rocket is a cross breed between a solid fuel rocket and a liquid fuel rocket.

Solid rocket motor internal insulation

NASA Technical Reports Server (NTRS)

Twichell, S. E. (Editor); Keller, R. B., Jr.

1976-01-01

Internal insulation in a solid rocket motor is defined as a layer of heat barrier material placed between the internal surface of the case propellant. The primary purpose is to prevent the case from reaching temperatures that endanger its structural integrity. Secondary functions of the insulation are listed and guidelines for avoiding critical problems in the development of internal insulation for rocket motors are presented.

Viscoelastic propellant effects on Space Shuttle Dynamics

NASA Technical Reports Server (NTRS)

Bugg, F.

1981-01-01

The program of solid propellant research performed in support of the space shuttle dynamics modeling effort is described. Stiffness, damping, and compressibility of the propellant and the effects of many variables on these properties are discussed. The relationship between the propellant and solid rocket booster dynamics during liftoff and boost flight conditions and the effects of booster vibration and propellant stiffness on free free solid rocket booster modes are described. Coupled modes of the shuttle system and the effect of propellant stiffness on the interfaces of the booster and the external tank are described. A finite shell model of the solid rocket booster was developed.

Hybrid rocket motor testing at Nammo Raufoss A/S

NASA Astrophysics Data System (ADS)

Rønningen, Jan-Erik; Kubberud, Nils

2005-08-01

Hybrid rocket motor technology and the use of hybrid rockets have gained increased interest in recent years in many countries. A typical hybrid rocket consists of a tank containing the oxidizer in either liquid or gaseous state connected to the combustion chamber containing an injector, inert solid fuel grain and nozzle. Nammo Raufoss A/S has for almost 40 years designed and produced high-performance solid propellant rocket motors for many military missile systems as well as solid propellant rocket motors for civil space use. In 2003 an in-house technology program was initiated to investigate and study hybrid rocket technology. On 23 September 2004 the first in-house designed hybrid test rocket motor was static test fired at Nammo Raufoss Test Center. The oxidizer was gaseous oxygen contained in a tank pressurized to 10MPa, flow controlled through a sonic orifice into the combustion chamber containing a multi port radial injector and six bore cartridge-loaded fuel grain containing a modified HTPB fuel composition. The motor was ignited using a non-explosive heated wire. This paper will present what has been achieved at Nammo Raufoss since the start of the program.

Hybrids - Best of both worlds. [liquid and solid propellants mated for safe reliable and low cost launch vehicles

NASA Technical Reports Server (NTRS)

Goldberg, Ben E.; Wiley, Dan R.

1991-01-01

An overview is presented of hybrid rocket propulsion systems whereby combining solids and liquids for launch vehicles could produce a safe, reliable, and low-cost product. The primary subsystems of a hybrid system consist of the oxidizer tank and feed system, an injector system, a solid fuel grain enclosed in a pressure vessel case, a mixing chamber, and a nozzle. The hybrid rocket has an inert grain, which reduces costs of development, transportation, manufacturing, and launch by avoiding many safety measures that must be taken when operating with solids. Other than their use in launch vehicles, hybrids are excellent for simulating the exhaust of solid rocket motors for material development.

Advanced Solid Rocket Motor case design status

NASA Technical Reports Server (NTRS)

Palmer, G. L.; Cash, S. F.; Beck, J. P.

1993-01-01

The Advanced Solid Rocket Motor (ASRM) case design aimed at achieving a safer and more reliable solid rocket motor for the Space Shuttle system is considered. The ASRM case has a 150.0 inch diameter, three equal length segment, and 9Ni-4CO-0.3C steel alloy. The major design features include bolted casebolted case joints which close during pressurization, plasma arc welded factory joints, integral stiffener for splash down and recovery, and integral External Tank attachment rings. Each mechanical joint has redundant and verifiable o-ring seals.

Analytical investigation of solid rocket nozzle failure

NASA Technical Reports Server (NTRS)

Mccoy, K. E.; Hester, J.

1985-01-01

On April 5, 1983, an Inertial Upper Stage (IUS) spacecraft experienced loss of control during the burn of the second of two solid rocket motors. The anomaly investigation showed the cause to be a malfunction of the solid rocket motor. This paper presents a description of the IUS system, a failure analysis summary, an account of the thermal testing and computer modeling done at Marshall Space Flight Center, a comparison of analysis results with thermal data obtained from motor static tests, and describes some of the design enhancement incorporated to prevent recurrence of the anomaly.

Solid rocket motors for the Space Shuttle booster.

NASA Technical Reports Server (NTRS)

Odom, J. B.

1972-01-01

The evolution of the space shuttle booster system is reviewed from its initial concepts based on liquid-propellant reusable boosters to the final selection of recoverable, solid-fuel rocket motors. The rationale associated with each of the several major decisions in the evolution process is discussed. It is shown that the external tank orbiter configuration emerging from the latest studies takes maximum advantage of the solid rocket motor development experience and promises to be the optimum configuration for fulfilling the paramount shuttle program requirements of minimum total development risk within acceptable costs.

50 Years of Testing

NASA Image and Video Library

2016-04-23

A 15-second test of a Saturn V rocket stage on the A-2 Test Stand at Stennis Space Center ushered in the Space Age for south Mississippi. Fifty years later, Stennis has grown into the nation’s largest rocket engine test site, continuing to test rocket engines and stages that power the nation’s space program.

Solid Rocket Motor Test

NASA Technical Reports Server (NTRS)

2008-01-01

Shown is a test of the TEM-13 solid rocket motor at the ATK test facility in Utah in support of the Ares/CLV first stage. This image is extracted from high definition video and is the highest resolution available.

Solid Rocket Motor Test

NASA Technical Reports Server (NTRS)

2008-01-01

Shown is a test of the TEM-13 Solid Rocket Motor in support of the Ares/CLV first stage at ATK, Utah . Constellaton/Ares project. This image is extracted from a high definition video file and is the highest resolution available.

Solid Rocket Motor Test

NASA Technical Reports Server (NTRS)

2008-01-01

Shown is a test of the TEM-13 Solid Rocket Motor in support of the Ares/CLV first stage at ATK, Utah . Constellation/Ares project. This image is extracted from a high definition video file and is the highest resolution available.

Solid rocket booster performance evaluation model. Volume 4: Program listing

NASA Technical Reports Server (NTRS)

1974-01-01

All subprograms or routines associated with the solid rocket booster performance evaluation model are indexed in this computer listing. An alphanumeric list of each routine in the index is provided in a table of contents.

Closeup view of the Solid Rocket Booster (SRB) Frustum mounted ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Close-up view of the Solid Rocket Booster (SRB) Frustum mounted on ground support equipment in the Solid Rocket Booster Assembly and Refurbishment Facility at Kennedy Space Center as it is being prepared to be mated with the Nose Cap and Forward Skirt. The Frustum contains the three Main Parachutes, Altitude Switches and forward booster Separation Motors. The Separation Motors burn for one second to ensure the SRBs drift away from the External Tank and Orbiter at separation. The three main parachutes are deployed to reduce speed as the SRBs descend to a splashdown in the Atlantic Ocean where they are recovered refurbished and reused. In this view the assembly is rotated so that the four Separation Motors are in view and aligned with the approximate centerline of the image. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Impact and mitigation of stratospheric ozone depletion by chemical rockets

DOE Office of Scientific and Technical Information (OSTI.GOV)

Mcdonald, A.J.

1992-03-01

The American Institute of Aeronautics and Astronautics (AIAA) conducted a workshop in conjunction with the 1991 AIAA Joint Propulsion Conference in Sacramento, California, to assess the impact of chemical rocket propulsion on the environment. The workshop included recognized experts from the fields of atmospheric physics and chemistry, solid rocket propulsion, liquid rocket propulsion, government, and environmental agencies, and representatives from several responsible environmental organizations. The conclusion from this workshop relative to stratospheric ozone depletion was that neither solid nor liquid rocket launchers have a significant impact on stratospheric ozone depletion, and that there is no real significant difference between themore » two.« less

Technology for low cost solid rocket boosters.

NASA Technical Reports Server (NTRS)

Ciepluch, C.

1971-01-01

A review of low cost large solid rocket motors developed at the Lewis Research Center is given. An estimate is made of the total cost reduction obtainable by incorporating this new technology package into the rocket motor design. The propellant, case material, insulation, nozzle ablatives, and thrust vector control are discussed. The effect of the new technology on motor cost is calculated for a typical expandable 260-in. booster application. Included in the cost analysis is the influence of motor performance variations due to specific impulse and weight changes. It is found for this application that motor costs may be reduced by up to 30% and that the economic attractiveness of future large solid rocket motors will be improved when the new technology is implemented.

Space Shuttle Projects

NASA Image and Video Library

1989-01-20

This photograph shows a static firing test of the Solid Rocket Qualification Motor-8 (QM-8) at the Morton Thiokol Test Site in Wasatch, Utah. The twin solid rocket boosters provide the majority of thrust for the first two minutes of flight, about 5.8 million pounds, augmenting the Shuttle's main propulsion system during liftoff. The major design drivers for the solid rocket motors (SRM's) were high thrust and reuse. The desired thrust was achieved by using state-of-the-art solid propellant and by using a long cylindrical motor with a specific core design that allows the propellant to burn in a carefully controlled marner. Under the direction of the Marshall Space Flight Center, the SRM's are provided by the Morton Thiokol Corporation.

PHOTOGRAPHER: KSC The first solid rocket booster solid motor segemnts to arrive at KSC, the left and

NASA Technical Reports Server (NTRS)

1980-01-01

PHOTOGRAPHER: KSC The first solid rocket booster solid motor segemnts to arrive at KSC, the left and right hand aft segments are off-loaded into High Bay 4 in the Vehicle Assembly Building and mated to their respective SRB aft skirts. The two aft assemblies will support the entire 150 foot tall solid boosters, in turn supporting the external tank and Orbiter Columbia on the Mobile Launcher Platform, for the first orbital flight test of the Space Shuttle.

Photographer: KSC The first solid rocket booster solid motor segemnts to arrive at KSC, the left and

NASA Technical Reports Server (NTRS)

1980-01-01

Photographer: KSC The first solid rocket booster solid motor segemnts to arrive at KSC, the left and right hand aft segments are off-loaded into High Bay 4 in the Vehicle Assembly Building and mated to their respective SRB aft skirts. The two aft assemblies will support the entire 150 foot tall solid boosters, in turn supporting the external tank and Orbiter Columbia on the Mobile Launcher Platform, for the first orbital flight test of the Space Shuttle.

Delta II JPSS-1 Solid Rocket Motor (SRM) Hoist and Mate

NASA Image and Video Library

2016-07-19

At Vandenberg Air Force Base in California, a solid rocket motor is attached to a United Launch Alliance Delta II rocket at Space Launch Complex 2. Preparations are continuing for launch of the Joint Polar Satellite System (JPSS-1) spacecraft on March 27, 2017. JPSS-1 is part of the next-generation environmental satellite system, a collaborative program between the National Oceanic and Atmospheric Administration (NOAA) and NASA.

Combustion of metal agglomerates in a solid rocket core flow

NASA Astrophysics Data System (ADS)

Maggi, Filippo; Dossi, Stefano; DeLuca, Luigi T.

2013-12-01

The need for access to space may require the use of solid propellants. High thrust and density are appealing features for different applications, spanning from boosting phase to other service applications (separation, de-orbiting, orbit insertion). Aluminum is widely used as a fuel in composite solid rocket motors because metal oxidation increases enthalpy release in combustion chamber and grants higher specific impulse. Combustion process of metal particles is complex and involves aggregation, agglomeration and evolution of reacting particulate inside the core flow of the rocket. It is always stated that residence time should be enough in order to grant complete metal oxidation but agglomerate initial size, rocket grain geometry, burning rate, and other factors have to be reconsidered. New space missions may not require large rocket systems and metal combustion efficiency becomes potentially a key issue to understand whether solid propulsion embodies a viable solution or liquid/hybrid systems are better. A simple model for metal combustion is set up in this paper. Metal particles are represented as single drops trailed by the core flow and reacted according to Beckstead's model. The fluid dynamics is inviscid, incompressible, 1D. The paper presents parametric computations on ideal single-size particles as well as on experimental agglomerate populations as a function of operating rocket conditions and geometries.

KSC-2009-3214

NASA Image and Video Library

2008-10-09

CAPE CANAVERAL, Fla. – This is the radome beneath which is the NASA Debris Radar. It is located at a remote site on North Merritt Island in Florida. One of the largest of its kind in the world, the C-band radar provided critical support to pinpoint debris during the launch of space shuttle Atlantis on the STS-125 mission. The need for this radar was identified after the Columbia tragedy. It worked together with smaller X-band radars placed on the solid rocket booster ship Liberty Star and the U.S. Army landing craft utility ship Brandy Station. Together they provided extremely high resolution images of any debris that created by Atlantis during launch. Photo credit: NASA/Troy Cryder

KSC-2009-3209

NASA Image and Video Library

2008-10-09

CAPE CANAVERAL, Fla. – This is the radome beneath which is the NASA Debris Radar. It is located at a remote site on North Merritt Island in Florida. One of the largest of its kind in the world, the C-band radar provided critical support to pinpoint debris during the launch of space shuttle Atlantis on the STS-125 mission. The need for this radar was identified after the Columbia tragedy. It worked together with smaller X-band radars placed on the solid rocket booster ship Liberty Star and the U.S. Army landing craft utility ship Brandy Station. Together they provided extremely high resolution images of any debris that created by Atlantis during launch. Photo credit: NASA/Troy Cryder

KSC-2009-3215

NASA Image and Video Library

2008-10-09

CAPE CANAVERAL, Fla. – This is the radome beneath which is the NASA Debris Radar. It is located at a remote site on North Merritt Island in Florida. One of the largest of its kind in the world, the C-band radar provided critical support to pinpoint debris during the launch of space shuttle Atlantis on the STS-125 mission. The need for this radar was identified after the Columbia tragedy. It worked together with smaller X-band radars placed on the solid rocket booster ship Liberty Star and the U.S. Army landing craft utility ship Brandy Station. Together they provided extremely high resolution images of any debris that created by Atlantis during launch. Photo credit: NASA/Troy Cryder

KSC-2009-3210

NASA Image and Video Library

2008-10-09

CAPE CANAVERAL, Fla. – This is the radome beneath which is the NASA Debris Radar. It is located at a remote site on North Merritt Island in Florida. One of the largest of its kind in the world, the C-band radar provided critical support to pinpoint debris during the launch of space shuttle Atlantis on the STS-125 mission. The need for this radar was identified after the Columbia tragedy. It worked together with smaller X-band radars placed on the solid rocket booster ship Liberty Star and the U.S. Army landing craft utility ship Brandy Station. Together they provided extremely high resolution images of any debris that created by Atlantis during launch. Photo credit: NASA/Troy Cryder

The Peak of Rocket Production: The Designer of Ballistic Missiles V.F. Utkin (1923-2000)

NASA Astrophysics Data System (ADS)

Prisniakov, V.; Sitnikova, N.

2002-01-01

The main landmarks of the biography of the general designer of the most power missiles Vladimira Fe- dorovicha Utkina are stated. Formation of character of outstanding scientist of 20 century as the son of the Soviet epoch is shown. He belongs to that generation which had many difficulties and afflictions - hungry time, the heavy years of the second world war, post-war disruption, but also many happy days - the Victory above fascism, restoration of the country, pride of successes in conquest of Space. In June, 1941 Vladimir has finished school with honours certificate and since October, 1941 up to the end of the second world war was on various fronts. After the ending of Leningrad military-mechanical insti- tute the young engineer came in Southern engineering works in Dnipropetrovsk (Yugmach). Here for 40 years there was a dizzy ascent of the beginner-designer over a ladder of space-rocket's Olympus up to the chief designer and the general director of the biggest in the world of rocket concern (9000 high quality engineers of Design office Yugnoe (DOYu) and 60 thousand workers Yugmach). After death in 1971 to year of main designer M. Jangele V. F. Utkin has headed Design office Yugnoe. Under ma- nual of V. Utkin four strategic rocket complexes of new generation SS-17, SS-18 (three updatings with divided head parts with weight of 8 tons), SS-24 (railway and shaft basing) were developed and han- ded over on arms. Among development of academician V. Utkin there is a rocket-carrier "Zenit" which delivers to an orbit over 12 tons of a payload. This rocket is also a basis of the first stage of reusable transport space system "Energia-Buran". Under manual of V. Utkin were developed and used the con- version carrier-rockets "Ziclon" and "Kosmos", as well the effective satellites of a defensive, scientific and economic direction, among which family of satellites "Kosmos", the satellite "Ocean", equipped by a locator of the side observation too. Largest scientific achievements V. Utkin and his pupils are crea- tion unique "mortar" launching of a heavy liquid rocket from shaft, the decision of a complex of prob- lems on maintenance ready for military action (continuous attendance) of liquid rockets in the filled condi-tion for many years, maintenance of stability of rockets at action on them of striking factors of nuclear explosion. With personal participation of academician IAA V. Utkin the following large scien- tific and technical results were received: (a) a military railway rocket complex with intercontinental solid-propellant rocket with starting weight of 105 tons and with 10 warheads; (b) a method of war manage-ment with the help of command rockets; (c) a method of definition of characteristics of means of overcoming of antimissile defense; (d) war intercontinental rockets with the increased accuracy, with the survivability, with the availability for action; (e) a commanding rocket. Design' decisions not ha- ving the analogues in world: (a) managements of flight solid-propellant an intercontinental ballistic missiles by means of a deviating head part; (b) managements solid-propellant rocket by method of inje- ction of gas in supercritical part of nozzle; (c) industrial introduction of the newest materials etc.V. Ut- kin is the active participant of works in the field of the international cooperation in research and deve- lopment of a space. In 1990 V. Utkin hold a high post of the director of ZSNIIMACH which is leading organization of a space-rocket industry of Russia. Under manual V. Utkin the Federal space program of Russia was developed. V. Utkin had huge authority as the chairman of Advice of the Main designers of the USSR. He was the co-chairman combined commission of experts V. Utkin - T. Stafford" on problems of maintenance joint manned flights. He was the chairman of Coordination advice under the program of researches on manned space complexes. V. Utkin dreamed to be the active participant of a new stage of the outer space exploration, connected with commissioning ISS. He believed, that Human mind and integration of efforts of all world community will be prevailed over the world.

Block 2 Solid Rocket Motor (SRM) conceptual design study. Volume 1: Appendices

NASA Technical Reports Server (NTRS)

1986-01-01

The design studies task implements the primary objective of developing a Block II Solid Rocket Motor (SRM) design offering improved flight safety and reliability. The SRM literature was reviewed. The Preliminary Development and Validation Plan is presented.

STS-55 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Fricke, Robert W., Jr.

1993-01-01

A summary of the Space Shuttle Payloads, Orbiter, External Tank, Solid Rocket Booster, Redesigned Solid Rocket Motor, and the Main Engine subsystems performance during the 55th flight of the Space Shuttle Program and the 14th flight of Columbia is presented.

A study of performance and cost improvement potential of the 120 inch (3.05 m) diameter solid rocket motor. Volume 1: Summary report

NASA Technical Reports Server (NTRS)

Backlund, S. J.; Rossen, J. N.

1971-01-01

A parametric study of ballistic modifications to the 120 inch diameter solid propellant rocket engine which forms part of the Air Force Titan 3 system is presented. 576 separate designs were defined and 24 were selected for detailed analysis. Detailed design descriptions, ballistic performance, and mass property data were prepared for each design. It was determined that a relatively simple change in design parameters could provide a wide range of solid propellant rocket engine ballistic characteristics for future launch vehicle applications.

Development and evaluation of an ablative closeout material for solid rocket booster thermal protection system

NASA Technical Reports Server (NTRS)

Patterson, W. J.

1979-01-01

A trowellable closeout/repair material designated as MTA-2 was developed and evaluated for use on the Solid Rocket Booster. This material is composed of an epoxy-polysulfide binder and is highly filled with phenolic microballoons for density control and ablative performance. Mechanical property testing and thermal testing were performed in a wind tunnel to simulate the combined Solid Rocket Booster trajectory aeroshear and heating environments. The material is characterized by excellent thermal performance and was used extensively on the Space Shuttle STS-1 and STS-2 flight hardware.

Study of solid rocket motors for a space shuttle booster. Appendix E: Environmental impact statement, solid rocket motor, space shuttle booster

NASA Technical Reports Server (NTRS)

1972-01-01

An analysis of the combustion products resulting from the solid propellant rocket engines of the space shuttle booster is presented. Calculation of the degree of pollution indicates that the only potentially harmful pollutants, carbon monoxide and hydrochloric acid, will be too diluted to constitute a hazard. The mass of products ejected during a launch within the troposphere is insignificant in terms of similar materials that enter the atmosphere from other sources. Noise pollution will not exceed that obtained from the Saturn 5 launch vehicle.

SRB Environment Evaluation and Analysis. Volume 3: ASRB Plume Induced Environments

NASA Technical Reports Server (NTRS)

Bender, R. L.; Brown, J. R.; Reardon, J. E.; Everson, J.; Coons, L. W.; Stuckey, C. I.; Fulton, M. S.

1991-01-01

Contract NAS8-37891 was expanded in late 1989 to initiate analysis of Shuttle plume induced environments as a result of the substitution of the Advanced Solid Rocket Booster (ASRB) for the Redesigned Solid Rocket Booster (RSRB). To support this analysis, REMTECH became involved in subscale and full-scale solid rocket motor test programs which further expanded the scope of work. Later contract modifications included additional tasks to produce initial design cycle environments and to specify development flight instrumentation. Volume 3 of the final report describes these analyses and contains a summary of reports resulting from various studies.

Study of Required Thrust Profile Determination of a Three Stages Small Launch Vehicle

NASA Astrophysics Data System (ADS)

Fariz, A.; Sasongko, R. A.; Poetro, R. E.

2018-04-01

The effect of solid rocket motor specifications, i.e. specific impulse and mass flow rate, and coast time on the thrust profile of three stages small launch vehicle is studied. Solid rocket motor specifications are collected from various small launch vehicle that had ever been in operation phase, and also from previous study. Comparison of orbital parameters shows that the radius of apocenter targeted can be approached using one combination of solid rocket motor specifications and appropriate coast time. However, the launch vehicle designed is failed to achieve the targeted orbit nor injecting the satellite to any orbit.

Rocket propulsion elements - An introduction to the engineering of rockets (6th revised and enlarged edition)

NASA Astrophysics Data System (ADS)

Sutton, George P.

The subject of rocket propulsion is treated with emphasis on the basic technology, performance, and design rationale. Attention is given to definitions and fundamentals, nozzle theory and thermodynamic relations, heat transfer, flight performance, chemical rocket propellant performance analysis, and liquid propellant rocket engine fundamentals. The discussion also covers solid propellant rocket fundamentals, hybrid propellant rockets, thrust vector control, selection of rocket propulsion systems, electric propulsion, and rocket testing.

Block 2 Solid Rocket Motor (SRM) conceptual design study, volume 1

NASA Technical Reports Server (NTRS)

1986-01-01

Segmented and monolithic Solid Rocket Motor (SRM) design concepts were evaluated with emphasis on joints and seals. Particular attention was directed to eliminating deficiencies in the SRM High Performance Motor (HPM). The selected conceptual design is described and discussed.

Space Shuttle Project

NASA Image and Video Library

1998-03-24

The roman candle effect as seen in this picture represents the testing of a solid rocket booster (SRB) for unexplained corrosion conditions (EUCC) which have occurred on the nozzles of redesigned solid rocket motors (RSRM). The motor being tested in this photo is a 48 M-NASA motor.

Advanced Concept

NASA Image and Video Library

2008-03-15

Shown is an illustration of the Ares I concept. The first stage will be a single, five-segment solid rocket booster derived from the space shuttle programs reusable solid rocket motor. The first stage is managed by NASA's Marshall Space Flight Center in Huntsville, Alabama for NASA's Constellation program.

76 FR 51459 - Office of Commercial Space Transportation (AST); Notice of Availability of the Finding of No...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-08-18

... five solid-propellant strap-on rocket motors to the Atlas V launch vehicle and larger solid- propellant strap-on rocket motors on the Delta IV vehicle. The FAA participated as a cooperating agency in...

Design of Force Sensor Leg for a Rocket Thrust Detector

NASA Astrophysics Data System (ADS)

Woten, Douglas; McGehee, Tripp; Wright, Anne

2005-03-01

A hybrid rocket is composed of a solid fuel and a separate liquid or gaseous oxidizer. These rockets may be throttled like liquid rockets, are safer than solid rockets, and are much less complex than liquid rockets. However, hybrid rockets produce thrust oscillations that are not practical for large scale use. A lab scale hybrid rocket at the University of Arkansas at Little Rock (UALR) Hybrid Rocket Facility is used to develop sensors to measure physical properties of hybrid rockets. Research is currently being conducted to design a six degree of freedom force sensor to measure the thrust and torque in all three spacial dimensions. The detector design uses six force sensor legs. Each leg utilizes strain gauges and a Wheatstone bridge to produce a voltage propotional to the force on the leg. The leg was designed using the CAD software ProEngineer and ProMechanica. Computer models of the strains on the single leg will be presented. A prototype leg was built and was tested in an INSTRON and results will be presented.

Delta II JPSS-1 Solid Rocket Motor (SRM) Hoist and Mate

NASA Image and Video Library

2016-07-19

At Vandenberg Air Force Base in California, a solid rocket motor is lifted at Space Launch Complex 2 to be attached to a United Launch Alliance Delta II rocket. Preparations are continuing for launch of the Joint Polar Satellite System (JPSS-1) spacecraft on March 27, 2017. JPSS-1 is part of the next-generation environmental satellite system, a collaborative program between the National Oceanic and Atmospheric Administration (NOAA) and NASA.

Delta II JPSS-1 Solid Rocket Motor (SRM) Hoist and Mate

NASA Image and Video Library

2016-07-19

At Vandenberg Air Force Base in California, technicians inspect a solid rocket motor at Space Launch Complex 2 as it is attached to a United Launch Alliance Delta II rocket. Preparations are continuing for launch of the Joint Polar Satellite System (JPSS-1) spacecraft on March 27, 2017. JPSS-1 is part of the next-generation environmental satellite system, a collaborative program between the National Oceanic and Atmospheric Administration (NOAA) and NASA.

Space Shuttle Five-Segment Booster (Short Course)

NASA Technical Reports Server (NTRS)

Graves, Stanley R.; Rudolphi, Michael (Technical Monitor)

2002-01-01

NASA is considering upgrading the Space Shuttle by adding a fifth segment (FSB) to the current four-segment solid rocket booster. Course materials cover design and engineering issues related to the Reusable Solid Rocket Motor (RSRM) raised by the addition of a fifth segment to the rocket booster. Topics cover include: four segment vs. five segment booster, abort modes, FSB grain design, erosive burning, enhanced propellant burn rate, FSB erosive burning model development and hardware configuration.

KSC-2013-4438

NASA Image and Video Library

2013-12-19

VANDENBERG AIR FORCE BASE, Calif. -- A solid rocket rocket motor is maneuvered toward the open high bay door of the Solid Rocket Motor Processing Facility at Vandenberg Air Force Base in California. The motor will be attached to the United Launch Alliance Delta II rocket slated to launch NASA's Orbiting Carbon Observatory-2, or OCO-2, spacecraft in July 2014. OCO-2 will collect precise global measurements of carbon dioxide in the Earth's atmosphere. Scientists will analyze this data to improve our understanding of the natural processes and human activities that regulate the abundance and distribution of this important atmospheric gas. Photo credit: NASA/Randy Beaudoin

Measurement and Characterization of Space Shuttle Solid Rocket Motor Plume Acoustics

NASA Technical Reports Server (NTRS)

Kenny, Jeremy; Hobbs, Chris; Plotkin, Ken; Pilkey, Debbie

2009-01-01

Lift-off acoustic environments generated by the future Ares I launch vehicle are assessed by the NASA Marshall Space Flight Center (MSFC) acoustics team using several prediction tools. This acoustic environment is directly caused by the Ares I First Stage booster, powered by the five-segment Reusable Solid Rocket Motor (RSRMV). The RSRMV is a larger-thrust derivative design from the currently used Space Shuttle solid rocket motor, the Reusable Solid Rocket Motor (RSRM). Lift-off acoustics is an integral part of the composite launch vibration environment affecting the Ares launch vehicle and must be assessed to help generate hardware qualification levels and ensure structural integrity of the vehicle during launch and lift-off. Available prediction tools that use free field noise source spectrums as a starting point for generation of lift-off acoustic environments are described in the monograph NASA SP-8072: "Acoustic Loads Generated by the Propulsion System." This monograph uses a reference database for free field noise source spectrums which consist of subscale rocket motor firings, oriented in horizontal static configurations. The phrase "subscale" is appropriate, since the thrust levels of rockets in the reference database are orders of magnitude lower than the current design thrust for the Ares launch family. Thus, extrapolation is needed to extend the various reference curves to match Ares-scale acoustic levels. This extrapolation process yields a subsequent amount of uncertainty added upon the acoustic environment predictions. As the Ares launch vehicle design schedule progresses, it is important to take every opportunity to lower prediction uncertainty and subsequently increase prediction accuracy. Never before in NASA s history has plume acoustics been measured for large scale solid rocket motors. Approximately twice a year, the RSRM prime vendor, ATK Launch Systems, static fires an assembled RSRM motor in a horizontal configuration at their test facility in Utah. The remaining RSRM static firings will take place on elevated terrain, with the nozzle exit plume being mostly undeflected and the landscape allowing placement of microphones within direct line of sight to the exhaust plume. These measurements will help assess the current extrapolation process by direct comparison between subscale and full scale solid rocket motor data.

Shuttle Boosters stacked in the VAB

NASA Image and Video Library

2007-01-04

Workers continue stacking the solid rocket boosters in highbay 1 inside Kennedy Space Center's Vehicle Assembly Building. The solid rocket boosters are being prepared for NASA's next Space Shuttle launch, mission STS-117. The mission is scheduled to launch aboard Atlantis no earlier than March 16, 2007.

Results of Small-scale Solid Rocket Combustion Simulator testing at Marshall Space Flight Center

NASA Technical Reports Server (NTRS)

Goldberg, Benjamin E.; Cook, Jerry

1993-01-01

The Small-scale Solid Rocket Combustion Simulator (SSRCS) program was established at the Marshall Space Flight Center (MSFC), and used a government/industry team consisting of Hercules Aerospace Corporation, Aerotherm Corporation, United Technology Chemical Systems Division, Thiokol Corporation and MSFC personnel to study the feasibility of simulating the combustion species, temperatures and flow fields of a conventional solid rocket motor (SRM) with a versatile simulator system. The SSRCS design is based on hybrid rocket motor principles. The simulator uses a solid fuel and a gaseous oxidizer. Verification of the feasibility of a SSRCS system as a test bed was completed using flow field and system analyses, as well as empirical test data. A total of 27 hot firings of a subscale SSRCS motor were conducted at MSFC. Testing of the Small-scale SSRCS program was completed in October 1992. This paper, a compilation of reports from the above team members and additional analysis of the instrumentation results, will discuss the final results of the analyses and test programs.

Combustion diagnosis for analysis of solid propellant rocket abort hazards: Role of spectroscopy

NASA Astrophysics Data System (ADS)

Gill, W.; Cruz-Cabrera, A. A.; Donaldson, A. B.; Lim, J.; Sivathanu, Y.; Bystrom, E.; Haug, A.; Sharp, L.; Surmick, D. M.

2014-11-01

Solid rocket propellant plume temperatures have been measured using spectroscopic methods as part of an ongoing effort to specify the thermal-chemical-physical environment in and around a burning fragment of an exploded solid rocket at atmospheric pressures. Such specification is needed for launch safety studies where hazardous payloads become involved with large fragments of burning propellant. The propellant burns in an off-design condition producing a hot gas flame loaded with burning metal droplets. Each component of the flame (soot, droplets and gas) has a characteristic temperature, and it is only through the use of spectroscopy that their temperature can be independently identified.

Measuring Fluctuating Pressure Levels and Vibration Response in a Jet Plume

NASA Technical Reports Server (NTRS)

Osterholt, Douglas J.; Knox, Douglas M.

2011-01-01

The characterization of loads due to solid rocket motor plume impingement allows for moreaccurate analyses of components subjected to such an environment. Typically, test verification of predicted loads due to these conditions is widely overlooked or unsuccessful. ATA Engineering, Inc., performed testing during a solid rocket motor firing to obtain acceleration and pressure responses in the hydrodynamic field surrounding the jet plume. The test environment necessitated a robust design to facilitate measurements being made in close proximity to the jet plume. This paper presents the process of designing a test fixture and an instrumentation package that could withstand the solid rocket plume environment and protect the required instrumentation.

Measuring the Internal Environment of Solid Rocket Motors During Ignition

NASA Technical Reports Server (NTRS)

Weisenberg, Brent; Smith, Doug; Speas, Kyle; Corliss, Adam

2003-01-01

A new instrumentation system has been developed to measure the internal environment of solid rocket test motors during motor ignition. The system leverages conventional, analog gages with custom designed, electronics modules to provide safe, accurate, high speed data acquisition capability. To date, the instrumentation system has been demonstrated in a laboratory environment and on subscale static fire test motors ranging in size from 5-inches to 24-inches in diameter. Ultimately, this system is intended to be installed on a full-scale Reusable Solid Rocket Motor. This paper explains the need for the data, the components and capabilities of the system, and the test results.

Reduced hazard chemicals for solid rocket motor production

NASA Technical Reports Server (NTRS)

Caddy, Larry A.; Bowman, Ross; Richards, Rex A.

1995-01-01

During the last three years. the NASA/Thiokol/industry team has developed and started implementation of an environmentally sound manufacturing plan for the continued production of solid rocket motors. NASA Marshall Space Flight Center (MSFC) and Thiokol Corporation have worked with other industry representatives and the U.S. Environmental Protection Agency (EPA) to prepare a comprehensive plan to eliminate all ozone depleting chemicals from manufacturing processes and reduce the use of other hazardous materials used to produce the space shuttle reusable solid rocket motors. The team used a classical approach for problem-solving combined with a creative synthesis of new approaches to attack this challenge.

Orion EM-1 Forward Skirt Move from Hangar AF to BFF

NASA Image and Video Library

2017-08-30

The Exploration Mission-1 (EM-1) left-hand forward skirt for NASA's Space Launch System (SLS) solid rocket boosters arrives inside the high bay at the Booster Fabrication Facility (BFF) at NASA's Kennedy Space Center in Florida. In the BFF, the forward skirt will be inspected and prepared for use on the left-hand solid rocket booster for EM-1. NASA's Orion spacecraft will fly atop the SLS rocket on its first uncrewed flight test.

KSC-07pd1514

NASA Image and Video Library

2007-06-15

KENNEDY SPACE CENTER, FLA. -- On Launch Pad 17-B at Cape Canaveral Air Force Station, the second stage of the Delta II launch vehicle for the Dawn spacecraft is lowered into the hole toward the Delta first stage below. The two stages will be mated. The Delta II-Heavy, manufactured by the United Launch Alliance, is scheduled to launch the Dawn spacecraft on its 4-year flight to the asteroid belt. The Delta II-Heavy is the strongest rocket in the Delta II class. It will use three stages and nine solid-fueled booster rockets to propel Dawn on its way. A 9.5-foot payload fairing will protect the spacecraft from the heat and stresses of launch. Dawn's goal is to characterize the conditions and processes of the solar system's earliest epoch by investigating in detail the largest protoplanets that have remained intact since their formations: asteroid Vesta and the dwarf planet Ceres. They reside in the extensive zone between Mars and Jupiter together with many other smaller bodies, called the asteroid belt. Dawn is scheduled to launch July 7. Photo credit: NASA/Jack Pfaller

KSC-07pd1512

NASA Image and Video Library

2007-06-15

KENNEDY SPACE CENTER, FLA. -- The second stage of the Delta II launch vehicle for the Dawn spacecraft is lifted alongside the mobile service tower on Launch Pad 17-B at Cape Canaveral Air Force Station. It will be mated with the first stage already in the tower. The Delta II-Heavy, manufactured by the United Launch Alliance, is scheduled to launch the Dawn spacecraft on its 4-year flight to the asteroid belt. The Delta II-Heavy is the strongest rocket in the Delta II class. It will use three stages and nine solid-fueled booster rockets to propel Dawn on its way. A 9.5-foot payload fairing will protect the spacecraft from the heat and stresses of launch. Dawn's goal is to characterize the conditions and processes of the solar system's earliest epoch by investigating in detail the largest protoplanets that have remained intact since their formations: asteroid Vesta and the dwarf planet Ceres. They reside in the extensive zone between Mars and Jupiter together with many other smaller bodies, called the asteroid belt. Dawn is scheduled to launch July 7. Photo credit: NASA/Jack Pfaller

KSC-07pd1510

NASA Image and Video Library

2007-06-15

KENNEDY SPACE CENTER, FLA. -- The second stage of the Delta II launch vehicle for the Dawn spacecraft is lifted alongside the mobile service tower on Launch Pad 17-B at Cape Canaveral Air Force Station. It will be mated with the first stage already in the tower. The Delta II-Heavy, manufactured by the United Launch Alliance, is scheduled to launch the Dawn spacecraft on its 4-year flight to the asteroid belt. The Delta II-Heavy is the strongest rocket in the Delta II class. It will use three stages and nine solid-fueled booster rockets to propel Dawn on its way. A 9.5-foot payload fairing will protect the spacecraft from the heat and stresses of launch. Dawn's goal is to characterize the conditions and processes of the solar system's earliest epoch by investigating in detail the largest protoplanets that have remained intact since their formations: asteroid Vesta and the dwarf planet Ceres. They reside in the extensive zone between Mars and Jupiter together with many other smaller bodies, called the asteroid belt. Dawn is scheduled to launch July 7. Photo credit: NASA/Jack Pfaller

SRB-3D Solid Rocket Booster performance prediction program. Volume 3: Programmer's manual

NASA Technical Reports Server (NTRS)

Winkler, J. C.

1976-01-01

The programmer's manual for the Modified Solid Rocket Booster Performance Prediction Program (SRB-3D) describes the major control routines of SRB-3D, followed by a super index listing of the program and a cross-reference of the program variables.

Space Shuttle Propulsion System Reliability

NASA Technical Reports Server (NTRS)

Welzyn, Ken; VanHooser, Katherine; Moore, Dennis; Wood, David

2011-01-01

This session includes the following sessions: (1) External Tank (ET) System Reliability and Lessons, (2) Space Shuttle Main Engine (SSME), Reliability Validated by a Million Seconds of Testing, (3) Reusable Solid Rocket Motor (RSRM) Reliability via Process Control, and (4) Solid Rocket Booster (SRB) Reliability via Acceptance and Testing.

Shuttle Boosters stacked in the VAB

NASA Image and Video Library

2007-01-04

Workers continue stacking the twin solid rocket boosters in highbay 1 inside Kennedy Space Center's Vehicle Assembly Building. The solid rocket boosters are being prepared for NASA's next Space Shuttle launch, mission STS-117. The mission is scheduled to launch aboard Atlantis no earlier than March 16, 2007.

76 FR 51459 - Office of Commercial Space Transportation (AST); Notice of Availability of the Record of Decision...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-08-18

... impacts of up to five solid-propellant strap-on rocket motors (SRMs) on the Atlas V medium lift vehicle... Proposed Action in the 2000 SEIS, up to five solid- propellant strap-on rocket motors (SRMs) would be added...

Shuttle Propulsion Overview - The Design Challenges

NASA Technical Reports Server (NTRS)

Owen, James W.

2011-01-01

The major elements of the Space Shuttle Main Propulsion System include two reusable solid rocket motors integrated into recoverable solid rocket boosters, an expendable external fuel and oxidizer tank, and three reusable Space Shuttle Main Engines. Both the solid rocket motors and space shuttle main engines ignite prior to liftoff, with the solid rocket boosters separating about two minutes into flight. The external tank separates, about eight and a half minutes into the flight, after main engine shutdown and is safely expended in the ocean. The SSME's, integrated into the Space Shuttle Orbiter aft structure, are reused after post landing inspections. The configuration is called a stage and a half as all the propulsion elements are active during the boost phase, with only the SSME s continuing operation to achieve orbital velocity. Design and performance challenges were numerous, beginning with development work in the 1970's. The solid rocket motors were large, and this technology had never been used for human space flight. The SSME s were both reusable and very high performance staged combustion cycle engines, also unique to the Space Shuttle. The multi body side mount configuration was unique and posed numerous integration and interface challenges across the elements. Operation of the system was complex and time consuming. This paper describes the design challenges and key areas where the design evolved during the program.

Introduction to the problem

NASA Technical Reports Server (NTRS)

Ramohalli, Kumar

1989-01-01

Solid propellant rockets were used extensively in space missions ranging from large boosters to orbit-raising upper stages. The smaller motors find exclusive use in various earth-based applications. The advantage of the solids include simplicity, readiness, volumetric efficiency, and storability. Important recent progress in related fields (combustion, rheology, micro-instrumentation/diagnostics, and chaos theory) can be applied to solid rockets to derive maximum advantage and avoid waste. Main objectives of research in solid propellants include: to identify critical parameters, to establish specification rules, and to develop quantitative criteria.

Nitrous Oxide/Paraffin Hybrid Rocket Engines

NASA Technical Reports Server (NTRS)

Zubrin, Robert; Snyder, Gary

2010-01-01

Nitrous oxide/paraffin (N2OP) hybrid rocket engines have been invented as alternatives to other rocket engines especially those that burn granular, rubbery solid fuels consisting largely of hydroxyl- terminated polybutadiene (HTPB). Originally intended for use in launching spacecraft, these engines would also be suitable for terrestrial use in rocket-assisted takeoff of small airplanes. The main novel features of these engines are (1) the use of reinforced paraffin as the fuel and (2) the use of nitrous oxide as the oxidizer. Hybrid (solid-fuel/fluid-oxidizer) rocket engines offer advantages of safety and simplicity over fluid-bipropellant (fluid-fuel/fluid-oxidizer) rocket en - gines, but the thrusts of HTPB-based hybrid rocket engines are limited by the low regression rates of the fuel grains. Paraffin used as a solid fuel has a regression rate about 4 times that of HTPB, but pure paraffin fuel grains soften when heated; hence, paraffin fuel grains can, potentially, slump during firing. In a hybrid engine of the present type, the paraffin is molded into a 3-volume-percent graphite sponge or similar carbon matrix, which supports the paraffin against slumping during firing. In addition, because the carbon matrix material burns along with the paraffin, engine performance is not appreciably degraded by use of the matrix.

Solid rocket technology advancements for space tug and IUS applications

NASA Technical Reports Server (NTRS)

Ascher, W.; Bailey, R. L.; Behm, J. W.; Gin, W.

1975-01-01

In order for the shuttle tug or interim upper stage (IUS) to capture all the missions in the current mission model for the tug and the IUS, an auxiliary or kick stage, using a solid propellant rocket motor, is required. Two solid propellant rocket motor technology concepts are described. One concept, called the 'advanced propulsion module' motor, is an 1800-kg, high-mass-fraction motor, which is single-burn and contains Class 2 propellent. The other concept, called the high energy upper stage restartable solid, is a two-burn (stop-restartable on command) motor which at present contains 1400 kg of Class 7 propellant. The details and status of the motor design and component and motor test results to date are presented, along with the schedule for future work.

Coal-Fired Rocket Engine

NASA Technical Reports Server (NTRS)

Anderson, Floyd A.

1987-01-01

Brief report describes concept for coal-burning hybrid rocket engine. Proposed engine carries larger payload, burns more cleanly, and safer to manufacture and handle than conventional solid-propellant rockets. Thrust changeable in flight, and stops and starts on demand.

7. Credit BG. View looking west into small solid rocket ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

7. Credit BG. View looking west into small solid rocket motor testing bay of Test Stand 'E' (Building 4259/E-60). Motors are mounted on steel table and fired horizontally toward the east. - Jet Propulsion Laboratory Edwards Facility, Test Stand E, Edwards Air Force Base, Boron, Kern County, CA

Study of solid rocket motors for a space shuttle booster. Volume 4: Mass properties report

NASA Technical Reports Server (NTRS)

Vonderesch, A. H.

1972-01-01

Mass properties data for the 156 inch diameter, parallel burn, solid propellant rocket engine for the space shuttle booster are presented. Design ground rules and assumptions applicable to generation of the mass properties data are described, together with pertinent data sources.

Solid rocket booster thermal radiation model. Volume 2: User's manual

NASA Technical Reports Server (NTRS)

Lee, A. L.

1976-01-01

A user's manual was prepared for the computer program of a solid rocket booster (SRB) thermal radiation model. The following information was included: (1) structure of the program, (2) input information required, (3) examples of input cards and output printout, (4) program characteristics, and (5) program listing.

Study of solid rocket motors for a space shuttle booster. Appendix B: Prime item development specification

NASA Technical Reports Server (NTRS)

1972-01-01

The specifications for the performance, design, development, and test requirements of the P2-156, S3-156, and S6-120 space shuttle booster solid rocket motors are presented. The applicable documents which form a part of the specifications are listed.

Solid rocket booster thermal protection system materials development. [space shuttle boosters

NASA Technical Reports Server (NTRS)

Dean, W. G.

1978-01-01

A complete run log of all tests conducted in the NASA-MSFC hot gas test facility during the development of materials for the space shuttle solid rocket booster thermal protection system are presented. Lists of technical reports and drawings generated under the contract are included.

SRB-3D Solid Rocket Booster performance prediction program. Volume 2: Sample case

NASA Technical Reports Server (NTRS)

Winkler, J. C.

1976-01-01

The sample case presented in this volume is an asymmetrical eight sector thermal gradient performance prediction for the solid rocket motor. This motor is the TC-227A-75 grain design and the initial grain geometry is assumed to be symmetrical about the motors longitudinal axis.

ADAPTATION OF A TECHNIQUE FOR PREDICTING LARGE SOLID ROCKET MOTOR SPECIFIC IMPULSE FROM DATA OBTAINED IN MICROMOTORS.

DTIC Science & Technology

Laboratory. The purpose of this technique is to predict specific impulse in large solid rocket motors based on data obtained in micromotors . As little as 2...concerning performance of a propellant in a large solid motor. Predictions, based on data obtained in micromotors , were within 0.6% of the delivered impulse in 6-pound motors and 70-pound BATES motors. (Author)

KSC-2013-4437

NASA Image and Video Library

2013-12-19

VANDENBERG AIR FORCE BASE, Calif. -- A solid rocket rocket motor is hauled away from its delivery truck and toward the open high bay door of the Solid Rocket Motor Processing Facility at Vandenberg Air Force Base in California. The motor will be attached to the United Launch Alliance Delta II rocket slated to launch NASA's Orbiting Carbon Observatory-2, or OCO-2, spacecraft in July 2014. OCO-2 will collect precise global measurements of carbon dioxide in the Earth's atmosphere. Scientists will analyze this data to improve our understanding of the natural processes and human activities that regulate the abundance and distribution of this important atmospheric gas. Photo credit: NASA/Randy Beaudoin

EELV Booster Assist Options for CEV

NASA Technical Reports Server (NTRS)

McNeal, Curtis, Jr.

2005-01-01

Medium lift EELVs may still play a role in manned space flight. To be considered for manned flight, medium lift EELVs must address the short comings in their current boost assist motors. Two options exist: redesign and requalify the solid rocket motors. Replace solid rocket motors (SRMs) with hybrid rocket motors. Hybrid rocket motors are an attractive alternative. They are safer than SRMs. The TRL's Lockheed Martin Small Launch Vehicle booster development substantially lowers the development risk, cost risk, and the schedule risk for developing hybrid boost assist for EELVs. Hybrid boosters testability offsets SRMs higher inherent reliability.Hybrid booster development and recurring costs are lower than SRMs. Performance gains are readily achieved.

Improving of Hybrid Rocket Engine on the Basis of Optimizing Design Fuel Grain

NASA Astrophysics Data System (ADS)

Oriekov, K. M.; Ushkin, M. P.

2015-09-01

This article examines the processes intrachamber in hybrid rocket engine (HRE) and the comparative assessment of the use of solid rocket motors (SRM) and HRE for meteorological rockets with a mass of payload of the 364 kg. Results of the research showed the possibility of a significant increase in the ballistic effectiveness of meteorological rocket.

Draft environmental impact statement: Space Shuttle Advanced Solid Rocket Motor Program

NASA Technical Reports Server (NTRS)

1988-01-01

The proposed action is design, development, testing, and evaluation of Advanced Solid Rocket Motors (ASRM) to replace the motors currently used to launch the Space Shuttle. The proposed action includes design, construction, and operation of new government-owned, contractor-operated facilities for manufacturing and testing the ASRM's. The proposed action also includes transport of propellant-filled rocket motor segments from the manufacturing facility to the testing and launch sites and the return of used and/or refurbished segments to the manufacturing site.

Orion EM-1 Forward Skirt Move from Hangar AF to BFF

NASA Image and Video Library

2017-08-30

The Exploration Mission-1 (EM-1) left-hand forward skirt for NASA's Space Launch System (SLS) solid rocket boosters arrives at the entrance to the high bay at the Booster Fabrication Facility (BFF) at NASA's Kennedy Space Center in Florida. In the BFF, the forward skirt will be inspected and prepared for use on the left-hand solid rocket booster for EM-1. NASA's Orion spacecraft will fly atop the SLS rocket on its first uncrewed flight test.

Orion EM-1 Forward Skirt Move from Hangar AF to BFF

NASA Image and Video Library

2017-08-30

The Exploration Mission-1 (EM-1) left-hand forward skirt for NASA's Space Launch System (SLS) solid rocket boosters arrives at the Booster Fabrication Facility (BFF) at NASA's Kennedy Space Center in Florida from Hangar AE at Cape Canaveral Air Force Station. In the BFF, the forward skirt will be inspected and prepared for use on the left-hand solid rocket booster for EM-1. NASA's Orion spacecraft will fly atop the SLS rocket on its first uncrewed flight test.

Orion EM-1 Forward Skirt Transport from Hangar AF to BFF

NASA Image and Video Library

2017-08-30

The Exploration Mission-1 (EM-1) left-hand forward skirt for NASA's Space Launch System (SLS) solid rocket boosters is transported by truck to the Booster Fabrication Facility (BFF) at NASA's Kennedy Space Center in Florida from Hangar AE at Cape Canaveral Air Force Station. In the BFF, the forward skirt will be inspected and prepared for use on the left-hand solid rocket booster for EM-1. NASA's Orion spacecraft will fly atop the SLS rocket on its first uncrewed flight test.

Ionic Fluorine Chemistry.

DTIC Science & Technology

SOLID ROCKET OXIDIZERS, *LIQUID ROCKET OXIDIZERS, CHLORATES, FLUORIDES, ACETONES, CHLORINE COMPOUNDS, NITROSO COMPOUNDS, *HALOGEN COMPOUNDS, ADDITION REACTIONS, CESIUM COMPOUNDS, CHLORIDES, COMPLEX COMPOUNDS

Around Marshall

NASA Image and Video Library

2002-10-01

This is a ground level view of Test Stand 300 at the east test area of the Marshall Space Flight Center. Test Stand 300 was constructed in 1964 as a gas generator and heat exchanger test facility to support the Saturn/Apollo Program. Deep-space simulation was provided by a 1960 modification that added a 20-ft thermal vacuum chamber and a 1981 modification that added a 12-ft vacuum chamber. The facility was again modified in 1989 when 3-ft and 15-ft diameter chambers were added to support Space Station and technology programs. This multiposition test stand is used to test a wide range of rocket engine components, systems, and subsystems. It has the capability to simulate launch thermal and pressure profiles. Test Stand 300 was designed for testing solid rocket booster (SRB) insulation panels and components, super-insulated tanks, external tank (ET) insulation panels and components, Space Shuttle components, solid rocket motor materials, and advanced solid rocket motor materials.

MEMS-Based Solid Propellant Rocket Array Thruster

NASA Astrophysics Data System (ADS)

Tanaka, Shuji; Hosokawa, Ryuichiro; Tokudome, Shin-Ichiro; Hori, Keiichi; Saito, Hirobumi; Watanabe, Masashi; Esashi, Masayoshi

The prototype of a solid propellant rocket array thruster for simple attitude control of a 10 kg class micro-spacecraft was completed and tested. The prototype has 10×10 φ0.8 mm solid propellant micro-rockets arrayed at a pitch of 1.2 mm on a 20×22 mm substrate. To realize such a dense array of micro-rockets, each ignition heater is powered from the backside of the thruster through an electrical feedthrough which passes along a propellant cylinder wall. Boron/potassium nitrate propellant (NAB) is used with/without lead rhodanide/potassium chlorate/nitrocellulose ignition aid (RK). Impulse thrust was measured by a pendulum method in air. Ignition required electric power of at least 3 4 W with RK and 4 6 W without RK. Measured impulse thrusts were from 2×10-5 Ns to 3×10-4 Ns after the calculation of compensation for air dumping.

KSC-2010-4812

NASA Image and Video Library

2010-09-22

LOUISIANA -- In Gulfport, La., workers connect the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122, to Freedom Star, NASA's solid rocket booster retrieval ship. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett

KSC-07pd2838

NASA Image and Video Library

2007-10-11

KENNEDY SPACE CENTER, FLA. -- In the Vehicle Assembly Building at NASA's Kennedy Space Center, the frustum is lifted from a transporter to be moved onto a stand. The solid rocket booster segment will be added to the stack for space shuttle Atlantis, launch vehicle for mission STS-122 targeted for a December launch. Atlantis will be carrying the Columbus Laboratory, Europe’s largest contribution to the construction of the International Space Station. It will support scientific and technological research in a microgravity environment. Columbus, a program of ESA, is a multifunctional, pressurized laboratory that will be permanently attached to Node 2 of the space station to carry out experiments in materials science, fluid physics and biosciences, as well as to perform a number of technological applications. Photo credit: NASA/Jack Pfaller

KSC-07pd2837

NASA Image and Video Library

2007-10-11

KENNEDY SPACE CENTER, FLA. -- In the Vehicle Assembly Building at NASA's Kennedy Space Center, the frustum is lifted from a transporter to be moved onto a stand. The solid rocket booster segment will be added to the stack for space shuttle Atlantis, launch vehicle for mission STS-122 targeted for a December launch. Atlantis will be carrying the Columbus Laboratory, Europe’s largest contribution to the construction of the International Space Station. It will support scientific and technological research in a microgravity environment. Columbus, a program of ESA, is a multifunctional, pressurized laboratory that will be permanently attached to Node 2 of the space station to carry out experiments in materials science, fluid physics and biosciences, as well as to perform a number of technological applications. Photo credit: NASA/Jack Pfaller

Spacecraft boost and abort guidance and control systems requirement study, boost dynamics and control analysis study. Exhibit A: Boost dynamics and control anlaysis

NASA Technical Reports Server (NTRS)

Williams, F. E.; Price, J. B.; Lemon, R. S.

1972-01-01

The simulation developments for use in dynamics and control analysis during boost from liftoff to orbit insertion are reported. Also included are wind response studies of the NR-GD 161B/B9T delta wing booster/delta wing orbiter configuration, the MSC 036B/280 inch solid rocket motor configuration, the MSC 040A/L0X-propane liquid injection TVC configuration, the MSC 040C/dual solid rocket motor configuration, and the MSC 049/solid rocket motor configuration. All of the latest math models (rigid and flexible body) developed for the MSC/GD Space Shuttle Functional Simulator, are included.

KSC-2011-1806

NASA Image and Video Library

2011-02-24

CAPE CANAVERAL, Fla. -- A worker on Freedom Star, one of NASA's solid rocket booster retrieval ships, manipulates a crane to recover the left solid rocket booster from the Atlantic Ocean after space shuttle Discovery's STS-133 launch. The shuttle’s two solid rocket booster casings and associated flight hardware are recovered in the Atlantic Ocean after every launch by Liberty Star and Freedom Star. The boosters impact the Atlantic about seven minutes after liftoff and the retrieval ships are stationed about 10 miles from the impact area at the time of splashdown. After the spent segments are processed, they will be transported to Utah, where they will be refurbished and stored, if needed. Photo credit: NASA/Ben Smegelsky

KSC-97PC1729

NASA Image and Video Library

1997-11-21

KENNEDY SPACE CENTER, FLA. -- The frustum of a forward skirt assembly of a spent solid rocket booster (SRB) from the STS-87 launch on Nov. 19 is transported into the Hangar AF area at Cape Canaveral Air Station. Hangar AF is a building originally used for Project Mercury, the first U.S. manned space program. The SRBs are the largest solid propellant motors ever flown and the first designed for reuse. After a Shuttle is launched, the SRBs are jettisoned at two minutes, seven seconds into the flight. At six minutes and 44 seconds after liftoff, the spent SRBs, weighing about 165,000 lb., have slowed their descent speed to about 62 mph and splashdown takes place in a predetermined area. They are retrieved from the Atlantic Ocean by special recovery vessels and returned for refurbishment and eventual reuse on future Shuttle flights. Once at Hangar AF, the SRBs are unloaded onto a hoisting slip and mobile gantry cranes lift them onto tracked dollies where they are safed and undergo their first washing

KSC-97PC1726

NASA Image and Video Library

1997-11-21

A spent solid rocket booster (SRB) from the STS-87 launch on Nov. 19 is lifted in a hoisting slip in the Hangar AF area at Cape Canaveral Air Station. Hangar AF is a building originally used for Project Mercury, the first U.S. manned space program. The SRBs are the largest solid propellant motors ever flown and the first designed for reuse. After a Shuttle is launched, the SRBs are jettisoned at two minutes, seven seconds into the flight. At six minutes and 44 seconds after liftoff, the spent SRBs, weighing about 165,000 lb., have slowed their descent speed to about 62 mph and splashdown takes place in a predetermined area. They are retrieved from the Atlantic Ocean by special recovery vessels and returned for refurbishment and eventual reuse on future Shuttle flights. Once at Hangar AF, the SRBs are unloaded onto a hoisting slip and mobile gantry cranes lift them onto tracked dollies where they are safed and undergo their first washing

KSC-97PC1728

NASA Image and Video Library

1997-11-21

A spent solid rocket booster (SRB) from the STS-87 launch on Nov. 19 is lifted in a hoisting slip in the Hangar AF area at Cape Canaveral Air Station. Hangar AF is a building originally used for Project Mercury, the first U.S. manned space program. The SRBs are the largest solid propellant motors ever flown and the first designed for reuse. After a Shuttle is launched, the SRBs are jettisoned at two minutes, seven seconds into the flight. At six minutes and 44 seconds after liftoff, the spent SRBs, weighing about 165,000 lb., have slowed their descent speed to about 62 mph and splashdown takes place in a predetermined area. They are retrieved from the Atlantic Ocean by special recovery vessels and returned for refurbishment and eventual reuse on future Shuttle flights. Once at Hangar AF, the SRBs are unloaded onto a hoisting slip and mobile gantry cranes lift them onto tracked dollies where they are safed and undergo their first washing

n/a

NASA Image and Video Library

1975-10-10

This diagram illustrates the Space Shuttle mission sequence. The Space Shuttle was approved as a national program in 1972 and developed through the 1970s. Part spacecraft and part aircraft, the Space Shuttle orbiter, the brain and the heart of the Space Transportation System (STS), required several technological advances, including thousands of insulating tiles able to stand the heat of reentry over the course of many missions, as well as sophisticated engines that could be used again and again without being thrown away. The airplane-like orbiter has three main engines, that burn liquid hydrogen and oxygen stored in the large external tank, the single largest structure in the Shuttle. Attached to the tank are two solid rocket boosters that provide the vehecile with most of the thrust needed for liftoff. Two minutes into the flight, the spent solids drop into the ocean to be recovered and refurbished for reuse, while the orbiter engines continue burning until approximately 8 minutes into the flight. After the mission is completed, the orbiter lands on a runway like an airplane.

Hazard Studies for Solid Propellant Rocket Motors (Etude des Risque pour les Moteurs-Fusees a Propergols Solides)

DTIC Science & Technology

1990-09-01

RESEARCH AND DEVELOPMENT (ORGANISATION DU TRAITE DE LATIANTIOUF NORD) AGARDograph No.3 16 Hazard Studies for Solid Propellant Rocket Motors (Etudes de...member nations to use their research and development capabilities for the common benefit of the NATO community; - Providing scientific and technical...advice and assistance to the Military Committee in the field of aerospace research and development (with particular regard to its military application

High-speed schlieren imaging of rocket exhaust plumes

NASA Astrophysics Data System (ADS)

Coultas-McKenney, Caralyn; Winter, Kyle; Hargather, Michael

2016-11-01

Experiments are conducted to examine the exhaust of a variety of rocket engines. The rocket engines are mounted in a schlieren system to allow high-speed imaging of the engine exhaust during startup, steady state, and shutdown. A variety of rocket engines are explored including a research-scale liquid rocket engine, consumer/amateur solid rocket motors, and water bottle rockets. Comparisons of the exhaust characteristics, thrust and cost for this range of rockets is presented. The variety of nozzle designs, target functions, and propellant type provides unique variations in the schlieren imaging.

6. Credit WCT. Photographic copy of photograph, Advanced Solid Rocket ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

6. Credit WCT. Photographic copy of photograph, Advanced Solid Rocket Motor (ASRM) test in progress at Test Stand 'E.' It was a JPL/Marshall Space Flight Center project. (JPL negative no. 344-4816 19 February 1982) - Jet Propulsion Laboratory Edwards Facility, Test Stand E, Edwards Air Force Base, Boron, Kern County, CA

Study of solid rocket motors for a space shuttle booster. Volume 2, book 3: Cost estimating data

NASA Technical Reports Server (NTRS)

Vanderesch, A. H.

1972-01-01

Cost estimating data for the 156 inch diameter, parallel burn solid rocket propellant engine selected for the space shuttle booster are presented. The costing aspects on the baseline motor are initially considered. From the baseline, sufficient data is obtained to provide cost estimates of alternate approaches.

Development of high temperature materials for solid propellant rocket nozzle applications

NASA Technical Reports Server (NTRS)

Manning, C. R., Jr.; Lineback, L. D.

1974-01-01

Aspects of the development and characteristics of thermal shock resistant hafnia ceramic material for use in solid propellant rocket nozzles are presented. The investigation of thermal shock resistance factors for hafnia based composites, and the preparation and analysis of a model of elastic materials containing more than one crack are reported.

Control techniques to improve Space Shuttle solid rocket booster separation

NASA Technical Reports Server (NTRS)

Tomlin, D. D.

1983-01-01

The present Space Shuttle's control system does not prevent the Orbiter's main engines from being in gimbal positions that are adverse to solid rocket booster separation. By eliminating the attitude error and attitude rate feedback just prior to solid rocket booster separation, the detrimental effects of the Orbiter's main engines can be reduced. In addition, if angular acceleration feedback is applied, the gimbal torques produced by the Orbiter's engines can reduce the detrimental effects of the aerodynamic torques. This paper develops these control techniques and compares the separation capability of the developed control systems. Currently with the worst case initial conditions and each Shuttle system dispersion aligned in the worst direction (which is more conservative than will be experienced in flight), the solid rocket booster has an interference with the Shuttle's external tank of 30 in. Elimination of the attitude error and attitude rate feedback reduces that interference to 19 in. Substitution of angular acceleration feedback reduces the interference to 6 in. The two latter interferences can be eliminated by atess conservative analysis techniques, that is, by using a root sum square of the system dispersions.

Electrets used to measure exhaust cloud effluents from Solid Rocket Motor (SRM) during demonstration model (DM-2) static test firing

NASA Technical Reports Server (NTRS)

Susko, M.

1978-01-01

Electrets were compared with fixed flow samplers during static test firing. The measurement of the rocket exhaust effluents by samplers and electrets indicated that the Solid Rocket Motor had no significant effect on the air quality in the area sampled. The results show that the electrets (a passive device which needs no power) can be used effectively alongside existing measuring devices (which need power). By placing electrets in areas where no power is available, measurements may be obtained. Consequently, it is a valuable complementary instrument in measuring rocket exhaust effluents in areas where other measuring devices may not be able to assess the contaminants.

SRB Processing Facilities Media Event

NASA Image and Video Library

2016-03-01

Inside the Booster Fabrication Facility (BFF) at NASA’s Kennedy Space Center in Florida, members of the news media view a forward skirt that will be used on a solid rocket booster for NASA’s Space Launch System (SLS) rocket. Orbital ATK is a contractor for NASA’s Marshall Space Flight Center in Alabama, and operates the BFF to prepare aft booster segments and hardware for the SLS solid rocket boosters. Rick Serfozo, Orbital ATK Florida site director, talks to the media. The SLS rocket and Orion spacecraft will launch on Exploration Mission-1 in 2018. The Ground Systems Development and Operations Program is preparing the infrastructure to process and launch spacecraft for deep-space missions and the journey to Mars.

Critical Review of the Navy Space Cadre

DTIC Science & Technology

2014-06-01

SPACE PROGRAM Following World War II, Army and Navy researchers divided captured German V-2 rocket components to rebuild V-2 rockets and eventually...develop the first American rockets .19 The Navy began launching space probes on V-2 rockets in 1946, including from the deck of USS Midway (CVB-41) in...1947.20 But the dwindling supply of V-2 rockets motivated the Navy to develop its own rockets . The Aerobee and Viking, would form a solid foundation

KSC-2013-4439

NASA Image and Video Library

2013-12-19

VANDENBERG AIR FORCE BASE, Calif. -- A solid rocket motor is rolled into the Solid Rocket Motor Processing Facility at Vandenberg Air Force Base in California. The motor will be attached to the United Launch Alliance Delta II rocket slated to launch NASA's Orbiting Carbon Observatory-2, or OCO-2, spacecraft in July 2014. OCO-2 will collect precise global measurements of carbon dioxide in the Earth's atmosphere. Scientists will analyze this data to improve our understanding of the natural processes and human activities that regulate the abundance and distribution of this important atmospheric gas. Photo credit: NASA/Randy Beaudoin

Hybrid boosters for future launch vehicles

NASA Astrophysics Data System (ADS)

Dargies, E.; Lo, R. E.

1987-10-01

Hybrid rocket propulsion systems furnish the advantages of much higher safety levels, due both to shut-down capability in case of ignition failure to one unit and the potential choice of nontoxic propellant combinations, such as LOX/polyethylene; they nevertheless yield performance levels comparable or superior to those of solid rocket boosters. Attention is presently given to the results of DFVLR analytical model studies of hybrid propulsion systems, with attention to solid fuel grain geometrical design and propellant grain surface ablation rate. The safety of hybrid rockets recommends them for use by manned spacecraft.

Experimental research and design planning in the field of liquid-propellant rocket engines conducted between 1934 - 1944 by the followers of F. A. Tsander

NASA Technical Reports Server (NTRS)

Dushkin, L. S.

1977-01-01

The development of the following Liquid-Propellant Rocket Engines (LPRE) is reviewed: (1) an alcohol-oxygen single-firing LPRE for use in wingless and winged rockets, (2) a similar multifiring LPRE for use in rocket gliders, (3) a combined solid-liquid propellant rocket engine, and (4) an aircraft LPRE operating on nitric acid and kerosene.

Potential Climate and Ozone Impacts From Hybrid Rocket Engine Emissions

NASA Astrophysics Data System (ADS)

Ross, M.

2009-12-01

Hybrid rocket engines that use N2O as an oxidizer and a solid hydrocarbon (such as rubber) as a fuel are relatively new. Little is known about the composition of such hybrid engine emissions. General principles and visual inspection of hybrid plumes suggest significant soot and possibly NO emissions. Understanding hybrid rocket emissions is important because of the possibility that a fleet of hybrid powered suborbital rockets will be flying on the order of 1000 flights per year by 2020. The annual stratospheric emission for these rockets would be about 10 kilotons, equal to present day solid rocket motor (SRM) emissions. We present a preliminary analysis of the magnitude of (1) the radiative forcing from soot emissions and (2) the ozone depletion from soot and NO emissions associated with such a fleet of suborbital hybrid rockets. Because the details of the composition of hybrid emissions are unknown, it is not clear if the ozone depletion caused by these hybrid rockets would be more or less than the ozone depletion from SRMs. We also consider the climate implications associated with the N2O production and use requirements for hybrid rockets. Finally, we identify the most important data collection and modeling needs that are required to reliably assess the complete range of environmental impacts of a fleet of hybrid rockets.

SOLID PROPELLANT COMBUSTION MECHANISM STUDIES.

DTIC Science & Technology

SOLID ROCKET PROPELLANTS, BURNING RATE), LOW PRESSURE, COMBUSTION PRODUCTS, QUENCHING, THERMAL CONDUCTIVITY, KINETIC THEORY, SURFACE PROPERTIES, PHASE STUDIES, SOLIDS, GASES, PYROLYSIS, MATHEMATICAL ANALYSIS.

Electrets used in measuring rocket exhaust effluents from the space shuttle's solid rocket booster during static test firing, DM-3

NASA Technical Reports Server (NTRS)

Susko, M.

1979-01-01

The purpose of this experimental research was to compare Marshall Space Flight Center's electrets with Thiokol's fixed flow air samplers during the Space Shuttle Solid Rocket Booster Demonstration Model-3 static test firing on October 19, 1978. The measurement of rocket exhaust effluents by Thiokol's samplers and MSFC's electrets indicated that the firing of the Solid Rocket Booster had no significant effect on the quality of the air sampled. The highest measurement by Thiokol's samplers was obtained at Plant 3 (site 11) approximately 8 km at a 113 degree heading from the static test stand. At sites 11, 12, and 5, Thiokol's fixed flow air samplers measured 0.0048, 0.00016, and 0.00012 mg/m3 of CI. Alongside the fixed flow measurements, the electret counts from X-ray spectroscopy were 685, 894, and 719 counts. After background corrections, the counts were 334, 543, and 368, or an average of 415 counts. An additional electred, E20, which was the only measurement device at a site approximately 20 km northeast from the test site where no power was available, obtained 901 counts. After background correction, the count was 550. Again this data indicate there was no measurement of significant rocket exhaust effluents at the test site.

An Acoustical Comparison of Sub-Scale and Full-Scale Far-Field Measurements for the Reusable Solid Rocket Motor

NASA Technical Reports Server (NTRS)

Haynes, Jared; Kenny, R. Jeremy

2010-01-01

Recently, members of the Marshall Space Flight Center (MSFC) Fluid Dynamics Branch and Wyle Labs measured far-field acoustic data during a series of three Reusable Solid Rocket Motor (RSRM) horizontal static tests conducted in Promontory, Utah. The test motors included the Technical Evaluation Motor 13 (TEM-13), Flight Verification Motor 2 (FVM-2), and the Flight Simulation Motor 15 (FSM-15). Similar far-field data were collected during horizontal static tests of sub-scale solid rocket motors at MSFC. Far-field acoustical measurements were taken at multiple angles within a circular array centered about the nozzle exit plane, each positioned at a radial distance of 80 nozzle-exit-diameters from the nozzle. This type of measurement configuration is useful for calculating rocket noise characteristics such as those outlined in the NASA SP-8072 "Acoustic Loads Generated by the Propulsion System." Acoustical scaling comparisons are made between the test motors, with particular interest in the Overall Sound Power, Acoustic Efficiency, Non-dimensional Relative Sound Power Spectrum, and Directivity. Since most empirical data in the NASA SP-8072 methodology is derived from small rockets, this investigation provides an opportunity to check the data collapse between a sub-scale and full-scale rocket motor.

Shuttle Boosters stacked in the VAB

NASA Image and Video Library

2007-01-04

Lighting inside Kennedy Space Center's Vehicle Assembly Building seems to bathe the highbay 1 area in a golden hue as workers continue stacking the twin solid rocket boosters. The solid rocket boosters are being prepared for NASA's next Space Shuttle launch, mission STS-117. The mission is scheduled to launch aboard Atlantis no earlier than March 16, 2007.

Solid rocket booster performance evaluation model. Volume 2: Users manual

NASA Technical Reports Server (NTRS)

1974-01-01

This users manual for the solid rocket booster performance evaluation model (SRB-II) contains descriptions of the model, the program options, the required program inputs, the program output format and the program error messages. SRB-II is written in FORTRAN and is operational on both the IBM 370/155 and the MSFC UNIVAC 1108 computers.

Study of solid rocket motor for a space shuttle booster. Appendix A: SRM water entry loads

NASA Technical Reports Server (NTRS)

1972-01-01

An analysis of the water entry loads imposed on the reusable solid propellant rocket engine of the space shuttle following parachute descent is presented. The cases discussed are vertical motion, horizontal motion, and motion after penetration. Mathematical models, diagrams, and charts are included to support the theoretical considerations.

Study of solid rocket motors for a space shuttle booster. Volume 3: Program acquisition planning

NASA Technical Reports Server (NTRS)

Vonderesch, A. H.

1972-01-01

Plans for conducting Phase C/D for a solid rocket motor booster vehicle are presented. Methods for conducting this program with details of scheduling, testing, and program management and control are included. The requirements of the space shuttle program to deliver a minimum cost/maximum reliability booster vehicle are examined.

KSC00pp1913

NASA Image and Video Library

2000-12-14

A KSC solid rocket booster worker inspects the reusable cables and connectors located inside the external tank attachment ring on the STS-98 left-hand solid rocket booster. Inspection and X-ray analysis of the ordnance-related cable connectors is required as part of an evaluation of their flight readiness before Space Shuttle Atlantis can rollout to Launch Pad 39A

KSC-00pp1913

NASA Image and Video Library

2000-12-14

A KSC solid rocket booster worker inspects the reusable cables and connectors located inside the external tank attachment ring on the STS-98 left-hand solid rocket booster. Inspection and X-ray analysis of the ordnance-related cable connectors is required as part of an evaluation of their flight readiness before Space Shuttle Atlantis can rollout to Launch Pad 39A

Five-Segment Reusable Solid Rocket Booster Upgrade

NASA Technical Reports Server (NTRS)

Sauvageau, Don

1999-01-01

The Five Segment Reusable Solid Rocket Booster (RSRB) feasibility status is presented in viewgraph form. The Five Segment Booster (FSB) objective is to provide a low cost, low risk approach to increase reliability and safety of the Shuttle system. Topics include: booster upgrade requirements; design summary; reliability issues; booster trajectories; launch site assessment; and enhanced abort modes.

Thiokol Solid Rocket Motors

NASA Technical Reports Server (NTRS)

Graves, S. R.

2000-01-01

This paper presents viewgraphs on thiokol solid rocket motors. The topics include: 1) Communications; 2) Military and government intelligence; 3) Positioning satellites; 4) Remote sensing; 5) Space burial; 6) Science; 7) Space manufacturing; 8) Advertising; 9) Space rescue space debris management; 10) Space tourism; 11) Space settlements; 12) Hazardous waste disposal; 13) Extraterrestrial resources; 14) Fast package delivery; and 15) Space utilities.

Study of solid rocket motor for space shuttle booster. Volume 4: Cost

NASA Technical Reports Server (NTRS)

1972-01-01

The cost data for solid propellant rocket engines for use with the space shuttle are presented. The data are based on the selected 156 inch parallel and series burn configurations. Summary cost data are provided for the production of the 120 inch and 260 inch configurations. Graphs depicting parametric cost estimating relationships are included.

Development of improved ablative materials for ASRM. [Advanced Solid Rocket Motor

NASA Technical Reports Server (NTRS)

Canfield, A.; Armour, W.; Clinton, R.

1991-01-01

A program to improve ablative materials for the Advanced Solid Rocket Motor (ASRM) is briefly discussed. The main concerns with the baseline material are summarized along with the measures being undertaken to obtain improvements. The materials involved in the program, all of which have been manufactured and are now being evaluated, are mentioned.

Study of solid rocket motor for space shuttle booster, Volume 3: Program acquisition planning

NASA Technical Reports Server (NTRS)

1972-01-01

The program planning acquisition functions for the development of the solid propellant rocket engine for the space shuttle booster is presented. The subjects discussed are: (1) program management, (2) contracts administration, (3) systems engineering, (4) configuration management, and (5) maintenance engineering. The plans for manufacturing, testing, and operations support are included.

Solid rocket motors

NASA Technical Reports Server (NTRS)

Carpenter, Ronn L.

1993-01-01

Structural requirements, materials and, especially, processing are critical issues that will pace the introduction of new types of solid rocket motors. Designers must recognize and understand the drivers associated with each of the following considerations: (1) cost; (2) energy density; (3) long term storage with use on demand; (4) reliability; (5) safety of processing and handling; (6) operability; and (7) environmental acceptance.

Vibration, acoustic, and shock design and test criteria for components on the Solid Rocket Boosters (SRB), Lightweight External Tank (LWT), and Space Shuttle Main Engines (SSME)

NASA Technical Reports Server (NTRS)

1984-01-01

The vibration, acoustics, and shock design and test criteria for components and subassemblies on the space shuttle solid rocket booster (SRB), lightweight tank (LWT), and main engines (SSME) are presented. Specifications for transportation, handling, and acceptance testing are also provided.

A computer simulation of the afterburning processes occurring within solid rocket motor plumes in the troposphere

NASA Technical Reports Server (NTRS)

Gomberg, R. I.; Stewart, R. B.

1976-01-01

As part of a continuing study of the environmental effects of solid rocket motor (SRM) operations in the troposphere, a numerical model was used to simulate the afterburning processes occurring in solid rocket motor plumes and to predict the quantities of potentially harmful chemical species which are created. The calculations include the effects of finite-rate chemistry and turbulent mixing. It is found that the amount of NO produced is much less than the amount of HCl present in the plume, that chlorine will appear predominantly in the form of HCl although some molecular chlorine is present, and that combustion is complete as is evident from the predominance of carbon dioxide over carbon monoxide.

Introduction of laser initiation for the 48-inch Advanced Solid Rocket Motor (ASRM) test motors at Marshall Space Flight Center (MSFC)

NASA Technical Reports Server (NTRS)

Zimmerman, Chris J.; Litzinger, Gerald E.

1993-01-01

The Advanced Solid Rocket Motor is a new design for the Space Shuttle Solid Rocket Booster. The new design will provide more thrust and more payload capability, as well as incorporating many design improvements in all facets of the design and manufacturing process. A 48-inch (diameter) test motor program is part of the ASRM development program. This program has multiple purposes for testing of propellent, insulation, nozzle characteristics, etc. An overview of the evolution of the 48-inch ASRM test motor ignition system which culminated with the implementation of a laser ignition system is presented. The laser system requirements, development, and operation configuration are reviewed in detail.

Results of wind tunnel tests of an ASRM configured 0.03 scale Space Shuttle integrated vehicle model (47-OTS) in the AEDC 16-foot transonic wind tunnel, volume 2

NASA Technical Reports Server (NTRS)

Marroquin, J.; Lemoine, P.

1992-01-01

An experimental Aerodynamic and Aero-Acoustic loads data base was obtained at transonic Mach numbers for the Space Shuttle Launch Vehicle configured with the ASRM Solid Rocket Boosters as an increment to the current flight configuration (RSRB). These data were obtained during transonic wind tunnel tests (IA 613A) conducted in the Arnold Engineering Development Center 16-Foot transonic propulsion wind tunnel from March 27, 1991 through April 12, 1991. This test is the first of a series of two tests covering the Mach range from 0.6 to 3.5. Steady state surface static and fluctuating pressure distributions over the Orbiter, External Tank and Solid Rocket Boosters of the Shuttle Integrated Vehicle were measured. Total Orbiter forces, Wing forces and Elevon hinge moments were directly measured as well from force balances. Two configurations of Solid Rocket Boosters were tested, the Redesigned Solid Rocket Booster (RSRB) and the Advanced Solid Rocket Motor (ASRM). The effects of the position (i.e., top, bottom, top and bottom) of the Integrated Electronics Assembly (IEA) box, mounted on the SRB attach ring, were obtained on the ASRM configured model. These data were obtained with and without Solid Plume Simulators which, when used, matched as close as possible the flight derived pressures on the Orbiter and External Tank base. Data were obtained at Mach numbers ranging from 0.6 to 1.55 at a Unit Reynolds Number of 2.5 million per foot through model angles of attack from -8 to +4 degrees at sideslip angles of 0, +4 and -4 degrees.

Results of wind tunnel tests of an ASRM configured 0.03 scale Space Shuttle integrated vehicle model (47-OTS) in the AEDC 16-foot Transonic wind tunnel (IA613A), volume 1

NASA Technical Reports Server (NTRS)

Marroquin, J.; Lemoine, P.

1992-01-01

An experimental Aerodynamic and Aero-Acoustic loads data base was obtained at transonic Mach numbers for the Space Shuttle Launch Vehicle configured with the ASRM Solid Rocket Boosters as an increment to the current flight configuration (RSRB). These data were obtained during transonic wind tunnel tests (IA 613A) conducted in the Arnold Engineering Development Center 16-Foot transonic propulsion wind tunnel from March 27, 1991 through April 12, 1991. This test is the first of a series of two tests covering the Mach range from 0.6 to 3.5. Steady state surface static and fluctuating pressure distributions over the Orbiter, External Tank and Solid Rocket Boosters of the Shuttle Integrated Vehicle were measured. Total Orbiter forces, Wing forces and Elevon hinge moments were directly measured as well from force balances. Two configurations of Solid Rocket Boosters were tested, the Redesigned Solid Rocket Booster (RSRB) and the Advanced Solid Rocket Motor (ASRM). The effects of the position (i.e. top, bottom, top and bottom) of the Integrated Electronics Assembly (IEA) box, mounted on the SRB attach ring, were obtained on the ASRM configured model. These data were obtained with and without Solid Plume Simulators which, when used, matched as close as possible the flight derived pressures on the Orbiter and External Tank base. Data were obtained at Mach numbers ranging from 0.6 to 1.55 at a Unit Reynolds Number of 2.5 million per foot through model angles of attack from -8 to +4 degrees at sideslip angles of 0, +4 and -4 degrees.

Vibration characteristics of 1/8-scale dynamic models of the space-shuttle solid-rocket boosters

NASA Technical Reports Server (NTRS)

Leadbetter, S. A.; Stephens, W.; Sewall, J. L.; Majka, J. W.; Barret, J. R.

1976-01-01

Vibration tests and analyses of six 1/8 scale models of the space shuttle solid rocket boosters are reported. Natural vibration frequencies and mode shapes were obtained for these aluminum shell models having internal solid fuel configurations corresponding to launch, midburn (maximum dynamic pressure), and near endburn (burnout) flight conditions. Test results for longitudinal, torsional, bending, and shell vibration frequencies are compared with analytical predictions derived from thin shell theory and from finite element plate and beam theory. The lowest analytical longitudinal, torsional, bending, and shell vibration frequencies were within + or - 10 percent of experimental values. The effects of damping and asymmetric end skirts on natural vibration frequency were also considered. The analytical frequencies of an idealized full scale space shuttle solid rocket boosted structure are computed with and without internal pressure and are compared with the 1/8 scale model results.

Development of Mechanics in Support of Rocket Technology in Ukraine

NASA Astrophysics Data System (ADS)

Prisnyakov, Vladimir

2003-06-01

The paper analyzes the advances of mechanics made in Ukraine in resolving various problems of space and rocket technology such as dynamics and strength of rockets and rocket engines, rockets of different purpose, electric rocket engines, and nonstationary processes in various systems of rockets accompanied by phase transitions of working media. Achievements in research on the effect of vibrations and gravitational fields on the behavior of space-rocket systems are also addressed. Results obtained in investigating the reliability and structural strength durability conditions for nuclear installations, solid- and liquid-propellant engines, and heat pipes are presented

Multiple-wavelength transmission measurements in rocket motor plumes

NASA Astrophysics Data System (ADS)

Kim, Hong-On

1991-09-01

Multiple-wavelength light transmission measurements were used to measure the mean particle size (d(sub 32)), index of refraction (m), and standard deviation of the small particles in the edge of the plume of a small solid propellant rocket motor. The results have shown that the multiple-wavelength light transmission measurement technique can be used to obtain these variables. The technique was shown to be more sensitive to changes in d(sub 32) and standard deviation (sigma) than to m. A GAP/AP/4.7 percent aluminum propellant burned at 25 atm produced particles with d32 = 0.150 +/- 0.006 microns, standard deviation = 1.50 +/- 0.04 and m = 1.63 +/- 0.13. The good correlation of the data indicated that only submicron particles were present in the edge of the plume. In today's budget conscious industry, the solid propellant rocket motor is an ideal propulsion system due to its low cost and simplicity. The major obstacle for solid rocket motors, however, is their limited specific impulse compared to airbreathing motors. One way to help overcome this limitation is to utilize metal fuel additives. Solid propellant rocket motors can achieve high specific impulse with metal fuel additives such as aluminum. Aluminum propellants also increase propellant densities and suppress transverse modes of combustion oscillations by damping the oscillations with the aluminum agglomerates in the combustion chamber.

Lessons Learned in Solid Rocket Combustion Instability

DTIC Science & Technology

2006-11-14

Gary Flandro . Also I wish to thank James Crump and H.B. Mathes who provided guidance during my first ten years at China Lake. VIII. References 1 L...It is also a form of analysis to examine the acoustic boundary with flow normal to the surface. It is sometimes known as the " Flandro boundary layer...Tso, "Flow Turning Losses in Solid Rocket Motors," AFAL-TR-87-095, March 1988. 30 G.A. Flandro , "Solid Propellant Acoustic Admittance Corrections

SRB Processing Facilities Media Event

NASA Image and Video Library

2016-03-01

Inside the Booster Fabrication Facility (BFF) at NASA’s Kennedy Space Center in Florida, members of the news media view the right-hand aft skirt that will be used on a solid rocket booster for NASA’s Space Launch System (SLS) rocket. Orbital ATK is contractor for NASA’s Marshall Space Flight Center in Alabama, and operates the BFF to prepare aft booster segments and hardware for the SLS solid rocket boosters. At far right, in the royal blue shirt, Rick Serfozo, Orbital ATK Florida site director, talks to the media. The SLS rocket and Orion spacecraft will launch on Exploration Mission-1 in 2018. The Ground Systems Development and Operations Program is preparing the infrastructure to process and launch spacecraft for deep-space missions and the journey to Mars.

KENNEDY SPACE CENTER, FLA. - On Launch Complex 17-B, Cape Canaveral Air Force Station, the first stage of a Delta II rocket is lifted up the mobile service tower. Below the rocket is the flame trench, and in the foreground is the overflow pool. The rocket is being erected to launch the Space InfraRed Telescope Facility (SIRTF). Consisting of an 0.85-meter telescope and three cryogenically cooled science instruments, SIRTF is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

NASA Image and Video Library

2003-07-18

KENNEDY SPACE CENTER, FLA. - On Launch Complex 17-B, Cape Canaveral Air Force Station, the first stage of a Delta II rocket is lifted up the mobile service tower. Below the rocket is the flame trench, and in the foreground is the overflow pool. The rocket is being erected to launch the Space InfraRed Telescope Facility (SIRTF). Consisting of an 0.85-meter telescope and three cryogenically cooled science instruments, SIRTF is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

KSC-07pd0011

NASA Image and Video Library

2007-01-05

KENNEDY SPACE CENTER, FLA. -- Lighting inside Kennedy Space Center's Vehicle Assembly Building seems to bathe the highbay 1 area in a golden hue as workers continue stacking the twin solid rocket boosters. The solid rocket boosters are being prepared for NASA's next Space Shuttle launch, mission STS-117. The mission is scheduled to launch aboard Atlantis no earlier than March 16, 2007. Photo credit: NASA/George Shelton

Space Shuttle Project

NASA Image and Video Library

1988-01-01

Marshall Space Flight Center workers install Structural Test Article Number Three (STA-3) into a Center test facility. From December 1987 to April 1988, STA-3 (a test model of the Redesigned Solid Rocket Motor) underwent a series of six tests at the Marshall Center designed to demonstrate the structural strength of the Space Shuttle's Solid Rocket Booster, redesigned after the January 1986 Challenger accident.

KENNEDY SPACE CENTER, FLA. - Jeff Thon, an SRB mechanic with United Space Alliance, tests a technique for vertical solid rocket booster propellant grain inspection. The inspection of segments is required as part of safety analysis.

NASA Image and Video Library

2003-09-11

KENNEDY SPACE CENTER, FLA. - Jeff Thon, an SRB mechanic with United Space Alliance, tests a technique for vertical solid rocket booster propellant grain inspection. The inspection of segments is required as part of safety analysis.

Closeup view of the External Tank and Solid Rocket Boosters ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Close-up view of the External Tank and Solid Rocket Boosters at the Launch Pad at Kennedy Space Center. Note the Hydrogen Vent Arm extending out from the Fixed Service Structure at attached to the Intertank segment of the External Tank. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

The 17th JANNAF Combustion Meeting, Volume 1

NASA Technical Reports Server (NTRS)

Eggleston, D. S. (Editor)

1980-01-01

The combustion of solid rocket propellants and combustion in ramjets is addressed. Subjects discussed include metal burning, steady-state combustion of composite propellants, velocity coupling and nonlinear instability, vortex shedding and flow effects on combustion instability, combustion instability in solid rocket motors, combustion diagnostics, subsonic and supersonic ramjet combustion, characterization of ramburner flowfields, and injection and combustion of ramjet fuels.

Scaled Rocket Testing in Hypersonic Flow

NASA Technical Reports Server (NTRS)

Dufrene, Aaron; MacLean, Matthew; Carr, Zakary; Parker, Ron; Holden, Michael; Mehta, Manish

2015-01-01

NASA's Space Launch System (SLS) uses four clustered liquid rocket engines along with two solid rocket boosters. The interaction between all six rocket exhaust plumes will produce a complex and severe thermal environment in the base of the vehicle. This work focuses on a recent 2% scale, hot-fire SLS base heating test. These base heating tests are short-duration tests executed with chamber pressures near the full-scale values with gaseous hydrogen/oxygen engines and RSRMV analogous solid propellant motors. The LENS II shock tunnel/Ludwieg tube tunnel was used at or near flight duplicated conditions up to Mach 5. Model development was strongly based on the Space Shuttle base heating tests with several improvements including doubling of the maximum chamber pressures and duplication of freestream conditions. Detailed base heating results are outside of the scope of the current work, rather test methodology and techniques are presented along with broader applicability toward scaled rocket testing in supersonic and hypersonic flow.

KSC-2010-4813

NASA Image and Video Library

2010-09-22

GULFPORT, La. -- At Gulfport, La., Michael Nicholas, captain M/V Freedom Star, guides NASA's solid rocket booster retrieval ship out of port pulling the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett

KSC-2010-4819

NASA Image and Video Library

2010-09-25

CAPE CANAVERAL, Fla. -- This sunrise view from the stern of Freedom Star, one of NASA's solid rocket booster retrieval ships, shows the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett

KSC-2010-4826

NASA Image and Video Library

2010-09-26

CAPE CANAVERAL, Fla. -- Deckhands on Freedom Star, one of NASA's solid rocket booster retrieval ships, keep the ship in good repair as it pulls the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett

KSC-2010-4824

NASA Image and Video Library

2010-09-26

CAPE CANAVERAL, Fla. -- This view is from the deck of Freedom Star, one of NASA's solid rocket booster retrieval ships, as it pulls the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett

KSC-2010-4816

NASA Image and Video Library

2010-09-22

CAPE CANAVERAL, Fla. -- This view from Freedom Star, one NASA's solid rocket booster retrieval ships, shows the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122, as it is transported to NASA's Kennedy Space Center in Florida. The tank will travel 900 miles by sea before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett

KSC-2010-4827

NASA Image and Video Library

2010-09-26

CAPE CANAVERAL, Fla. -- This view from the stern of Freedom Star, one of NASA's solid rocket booster retrieval ships, shows the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett

KSC-2010-4823

NASA Image and Video Library

2010-09-26

CAPE CANAVERAL, Fla. -- Deckhands on Freedom Star, one of NASA's solid rocket booster retrieval ships, keep the ship in good repair as it pulls the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett

KSC-2010-4815

NASA Image and Video Library

2010-09-22

CAPE CANAVERAL, Fla. -- This view from the stern of Freedom Star, one of NASA's solid rocket booster retrieval ships, shows the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122, as it is transported to NASA's Kennedy Space Center in Florida. The tank will travel 900 miles by sea, offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett

KSC-2010-4820

NASA Image and Video Library

2010-09-25

CAPE CANAVERAL, Fla. -- This view from the stern of Freedom Star, one of NASA's solid rocket booster retrieval ships, shows the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett

KSC-2010-4822

NASA Image and Video Library

2010-09-26

CAPE CANAVERAL, Fla. -- A deckhand on Freedom Star, one of NASA's solid rocket booster retrieval ships, keeps the ship in good repair as it pulls the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett

KSC-2010-4821

NASA Image and Video Library

2010-09-26

CAPE CANAVERAL, Fla. -- Deckhands on Freedom Star, one of NASA's solid rocket booster retrieval ships, keep the ship in good repair as it pulls the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett

KSC-07pd2836

NASA Image and Video Library

2007-10-11

KENNEDY SPACE CENTER, FLA. -- In the Vehicle Assembly Building at NASA's Kennedy Space Center, the frustum is ready to be lifted from a transporter to move onto a stand. The solid rocket booster segment will be added to the stack for space shuttle Atlantis, launch vehicle for mission STS-122 targeted for a December launch. Atlantis will be carrying the Columbus Laboratory, Europe’s largest contribution to the construction of the International Space Station. It will support scientific and technological research in a microgravity environment. Columbus, a program of ESA, is a multifunctional, pressurized laboratory that will be permanently attached to Node 2 of the space station to carry out experiments in materials science, fluid physics and biosciences, as well as to perform a number of technological applications. Photo credit: NASA/Jack Pfaller

Contamination Control Changes to the Reusable Solid Rocket Motor Program: A Ten Year Review

NASA Technical Reports Server (NTRS)

Bushman, David M.

1998-01-01

During the post Challenger period, the National Aeronautics and Space Administration and Thiokol implemented changes to the Reusable Solid Rocket Motor (RSRM) contract to include provisions for contamination control to enhance the production environment. During the ten years since those agreements for contamination controls were made, many changes have taken place in the production facilities at Thiokol. These changes have led to the production of much higher quality shuttle solid rocket motors and improved cleanliness and safety of operations in the production facilities. The experience in contamination control over this past decade highlights the value these changes have brought to the RSRM program, and how the system can be improved to meet the challenges the program will face in the next ten years.

Space Shuttle SRM development. [Solid Rocket Motors

NASA Technical Reports Server (NTRS)

Brinton, B. C.; Kilminster, J. C.

1979-01-01

The successful static test of the fourth Development Space Shuttle Solid Rocket Motor (SRM) in February 1979 concluded the development testing phase of the SRM Project. Qualification and flight motors are currently being fabricated, with the first qualification motor to be static tested. Delivered thrust-time traces on all development motors were very close to predicted values, and both specific and total impulse exceeded specification requirements. 'All-up' static tests conducted with a solid rocket booster equipment on development motors achieved all test objectives. Transportation and support equipment concepts have been proven, baselining is complete, and component reusability has been demonstrated. Evolution of the SRM transportation support equipment, and special test equipment designs are reviewed, and development activities discussed. Handling and processing aspects of large, heavy components are described.

Extension of a simplified computer program for analysis of solid-propellant rocket motors

NASA Technical Reports Server (NTRS)

Sforzini, R. H.

1973-01-01

A research project to develop a computer program for the preliminary design and performance analysis of solid propellant rocket engines is discussed. The following capabilities are included as computer program options: (1) treatment of wagon wheel cross sectional propellant configurations alone or in combination with circular perforated grains, (2) calculation of ignition transients with the igniter treated as a small rocket engine, (3) representation of spherical circular perforated grain ends as an alternative to the conical end surface approximation used in the original program, and (4) graphical presentation of program results using a digital plotter.

KSC-2013-4453

NASA Image and Video Library

2013-12-19

VANDENBERG AIR FORCE BASE, Calif. -- A solid rocket motor sits on a transporter inside the Solid Rocket Motor Processing Facility at Vandenberg Air Force Base in California. The motor will be attached to the United Launch Alliance Delta II rocket slated to launch NASA's Orbiting Carbon Observatory-2, or OCO-2, spacecraft in July 2014. OCO-2 will collect precise global measurements of carbon dioxide in the Earth's atmosphere. Scientists will analyze this data to improve our understanding of the natural processes and human activities that regulate the abundance and distribution of this important atmospheric gas. Photo credit: NASA/Randy Beaudoin

KSC-2013-4442

NASA Image and Video Library

2013-12-19

VANDENBERG AIR FORCE BASE, Calif. -- A solid rocket motor is secured to a transporter inside the Solid Rocket Motor Processing Facility at Vandenberg Air Force Base in California. The motor will be attached to the United Launch Alliance Delta II rocket slated to launch NASA's Orbiting Carbon Observatory-2, or OCO-2, spacecraft in July 2014. OCO-2 will collect precise global measurements of carbon dioxide in the Earth's atmosphere. Scientists will analyze this data to improve our understanding of the natural processes and human activities that regulate the abundance and distribution of this important atmospheric gas. Photo credit: NASA/Randy Beaudoin

KSC-2013-4459

NASA Image and Video Library

2013-12-19

VANDENBERG AIR FORCE BASE, Calif. -- A solid rocket motor is moved on a transporter to the Solid Rocket Motor Processing Facility at Vandenberg Air Force Base in California. The motor will be attached to the United Launch Alliance Delta II rocket slated to launch NASA's Orbiting Carbon Observatory-2, or OCO-2, spacecraft in July 2014. OCO-2 will collect precise global measurements of carbon dioxide in the Earth's atmosphere. Scientists will analyze this data to improve our understanding of the natural processes and human activities that regulate the abundance and distribution of this important atmospheric gas. Photo credit: NASA/Randy Beaudoin

KSC-2013-4461

NASA Image and Video Library

2013-12-19

VANDENBERG AIR FORCE BASE, Calif. – Technicians prepare to move a solid rocket motor to a different transporter inside the Solid Rocket Motor Processing Facility at Vandenberg Air Force Base in California. The motor will be attached to the United Launch Alliance Delta II rocket slated to launch NASA's Orbiting Carbon Observatory-2, or OCO-2, spacecraft in July 2014. OCO-2 will collect precise global measurements of carbon dioxide in the Earth's atmosphere. Scientists will analyze this data to improve our understanding of the natural processes and human activities that regulate the abundance and distribution of this important atmospheric gas. Photo credit: NASA/Randy Beaudoin

KSC-2013-4456

NASA Image and Video Library

2013-12-19

VANDENBERG AIR FORCE BASE, Calif. -- A solid rocket motor is moved on a transporter to the Solid Rocket Motor Processing Facility at Vandenberg Air Force Base in California. The motor will be attached to the United Launch Alliance Delta II rocket slated to launch NASA's Orbiting Carbon Observatory-2, or OCO-2, spacecraft in July 2014. OCO-2 will collect precise global measurements of carbon dioxide in the Earth's atmosphere. Scientists will analyze this data to improve our understanding of the natural processes and human activities that regulate the abundance and distribution of this important atmospheric gas. Photo credit: NASA/Randy Beaudoin

KSC-2013-4441

NASA Image and Video Library

2013-12-19

VANDENBERG AIR FORCE BASE, Calif. -- An overhead crane moves a solid rocket motor onto a transporter inside the Solid Rocket Motor Processing Facility at Vandenberg Air Force Base in California. The motor will be attached to the United Launch Alliance Delta II rocket slated to launch NASA's Orbiting Carbon Observatory-2, or OCO-2, spacecraft in July 2014. OCO-2 will collect precise global measurements of carbon dioxide in the Earth's atmosphere. Scientists will analyze this data to improve our understanding of the natural processes and human activities that regulate the abundance and distribution of this important atmospheric gas. Photo credit: NASA/Randy Beaudoin

KSC-2013-4460

NASA Image and Video Library

2013-12-19

VANDENBERG AIR FORCE BASE, Calif. -- A solid rocket motor is moved on a transporter to the Solid Rocket Motor Processing Facility at Vandenberg Air Force Base in California. The motor will be attached to the United Launch Alliance Delta II rocket slated to launch NASA's Orbiting Carbon Observatory-2, or OCO-2, spacecraft in July 2014. OCO-2 will collect precise global measurements of carbon dioxide in the Earth's atmosphere. Scientists will analyze this data to improve our understanding of the natural processes and human activities that regulate the abundance and distribution of this important atmospheric gas. Photo credit: NASA/Randy Beaudoin

KSC-2013-4464

NASA Image and Video Library

2013-12-19

VANDENBERG AIR FORCE BASE, Calif. – A pair of solid rocket motors on transporters inside the Solid Rocket Motor Processing Facility at Vandenberg Air Force Base in California. The motors will be attached to the United Launch Alliance Delta II rocket slated to launch NASA's Orbiting Carbon Observatory-2, or OCO-2, spacecraft in July 2014. OCO-2 will collect precise global measurements of carbon dioxide in the Earth's atmosphere. Scientists will analyze this data to improve our understanding of the natural processes and human activities that regulate the abundance and distribution of this important atmospheric gas. Photo credit: NASA/Randy Beaudoin

KSC-2013-4457

NASA Image and Video Library

2013-12-19

VANDENBERG AIR FORCE BASE, Calif. -- A solid rocket motor is moved on a transporter to the Solid Rocket Motor Processing Facility at Vandenberg Air Force Base in California. The motor will be attached to the United Launch Alliance Delta II rocket slated to launch NASA's Orbiting Carbon Observatory-2, or OCO-2, spacecraft in July 2014. OCO-2 will collect precise global measurements of carbon dioxide in the Earth's atmosphere. Scientists will analyze this data to improve our understanding of the natural processes and human activities that regulate the abundance and distribution of this important atmospheric gas. Photo credit: NASA/Randy Beaudoin

KSC-2013-4458

NASA Image and Video Library

2013-12-19

VANDENBERG AIR FORCE BASE, Calif. – A pair of solid rocket motors on transporters inside the Solid Rocket Motor Processing Facility at Vandenberg Air Force Base in California. The motors will be attached to the United Launch Alliance Delta II rocket slated to launch NASA's Orbiting Carbon Observatory-2, or OCO-2, spacecraft in July 2014. OCO-2 will collect precise global measurements of carbon dioxide in the Earth's atmosphere. Scientists will analyze this data to improve our understanding of the natural processes and human activities that regulate the abundance and distribution of this important atmospheric gas. Photo credit: NASA/Randy Beaudoin

KSC-2013-4440

NASA Image and Video Library

2013-12-19

VANDENBERG AIR FORCE BASE, Calif. -- An overhead crane is moved into position above a solid rocket motor inside the Solid Rocket Motor Processing Facility at Vandenberg Air Force Base in California. The motor will be attached to the United Launch Alliance Delta II rocket slated to launch NASA's Orbiting Carbon Observatory-2, or OCO-2, spacecraft in July 2014. OCO-2 will collect precise global measurements of carbon dioxide in the Earth's atmosphere. Scientists will analyze this data to improve our understanding of the natural processes and human activities that regulate the abundance and distribution of this important atmospheric gas. Photo credit: NASA/Randy Beaudoin

KSC-2013-4463

NASA Image and Video Library

2013-12-19

VANDENBERG AIR FORCE BASE, Calif. – Technicians move a solid rocket motor to a different transporter inside the Solid Rocket Motor Processing Facility at Vandenberg Air Force Base in California. The motor will be attached to the United Launch Alliance Delta II rocket slated to launch NASA's Orbiting Carbon Observatory-2, or OCO-2, spacecraft in July 2014. OCO-2 will collect precise global measurements of carbon dioxide in the Earth's atmosphere. Scientists will analyze this data to improve our understanding of the natural processes and human activities that regulate the abundance and distribution of this important atmospheric gas. Photo credit: NASA/Randy Beaudoin

KSC-2013-4462

NASA Image and Video Library

2013-12-19

VANDENBERG AIR FORCE BASE, Calif. – Technicians move a solid rocket motor to a different transporter inside the Solid Rocket Motor Processing Facility at Vandenberg Air Force Base in California. The motor will be attached to the United Launch Alliance Delta II rocket slated to launch NASA's Orbiting Carbon Observatory-2, or OCO-2, spacecraft in July 2014. OCO-2 will collect precise global measurements of carbon dioxide in the Earth's atmosphere. Scientists will analyze this data to improve our understanding of the natural processes and human activities that regulate the abundance and distribution of this important atmospheric gas. Photo credit: NASA/Randy Beaudoin

KSC-2013-4454

NASA Image and Video Library

2013-12-19

VANDENBERG AIR FORCE BASE, Calif. -- A solid rocket motor is moved on a transporter to the Solid Rocket Motor Processing Facility at Vandenberg Air Force Base in California. The motor will be attached to the United Launch Alliance Delta II rocket slated to launch NASA's Orbiting Carbon Observatory-2, or OCO-2, spacecraft in July 2014. OCO-2 will collect precise global measurements of carbon dioxide in the Earth's atmosphere. Scientists will analyze this data to improve our understanding of the natural processes and human activities that regulate the abundance and distribution of this important atmospheric gas. Photo credit: NASA/Randy Beaudoin

KSC-08pd1093

NASA Image and Video Library

2008-05-01

CAPE CANAVERAL, Fla. -- In Firing Room No. 1 in the Launch Control Center at NASA's Kennedy Space Center, a worker maneuvers a panel to build another cabinet to hold equipment that will support the future Ares rocket launches as part of the Constellation Program. Future astronauts will ride to orbit on Ares I, which uses a single five-segment solid rocket booster, a derivative of the space shuttle's solid rocket booster, for the first stage. Ares will be launched from Pad 39B, which is being reconfigured from supporting space shuttle launches. The Launch Control Center firing rooms face the launch pads. Photo credit: NASA/Kim Shiflett

KSC-08pd1096

NASA Image and Video Library

2008-05-01

CAPE CANAVERAL, Fla. -- In Firing Room No. 1 in the Launch Control Center at NASA's Kennedy Space Center, workers line up the new equipment cabinets. The firing room will support the future Ares rocket launches as part of the Constellation Program. Future astronauts will ride to orbit on Ares I, which uses a single five-segment solid rocket booster, a derivative of the space shuttle's solid rocket booster, for the first stage. Ares will be launched from Pad 39B, which is being reconfigured from supporting space shuttle launches. The Launch Control Center firing rooms face the launch pads. Photo credit: NASA/Kim Shiflett

KSC-08pd1090

NASA Image and Video Library

2008-05-01

CAPE CANAVERAL, Fla. -- In Firing Room No. 1 in the Launch Control Center at NASA's Kennedy Space Center, cabinets are being erected to hold equipment that will support the future Ares rocket launches as part of the Constellation Program. Future astronauts will ride to orbit on Ares I, which uses a single five-segment solid rocket booster, a derivative of the space shuttle's solid rocket booster, for the first stage. Ares will be launched from Pad 39B, which is being reconfigured from supporting space shuttle launches. The Launch Control Center firing rooms face the launch pads. Photo credit: NASA/Kim Shiflett

KSC-08pd1094

NASA Image and Video Library

2008-05-01

CAPE CANAVERAL, Fla. -- In Firing Room No. 1 in the Launch Control Center at NASA's Kennedy Space Center, workers put together another cabinet to hold equipment that will support the future Ares rocket launches as part of the Constellation Program. Future astronauts will ride to orbit on Ares I, which uses a single five-segment solid rocket booster, a derivative of the space shuttle's solid rocket booster, for the first stage. Ares will be launched from Pad 39B, which is being reconfigured from supporting space shuttle launches. The Launch Control Center firing rooms face the launch pads. Photo credit: NASA/Kim Shiflett

KSC-08pd1091

NASA Image and Video Library

2008-05-01

CAPE CANAVERAL, Fla. -- In Firing Room No. 1 in the Launch Control Center at NASA's Kennedy Space Center, workers put together another cabinet to hold equipment that will support the future Ares rocket launches as part of the Constellation Program. Future astronauts will ride to orbit on Ares I, which uses a single five-segment solid rocket booster, a derivative of the space shuttle's solid rocket booster, for the first stage. Ares will be launched from Pad 39B, which is being reconfigured from supporting space shuttle launches. The Launch Control Center firing rooms face the launch pads. Photo credit: NASA/Kim Shiflett

Flight Investigation of the Performance of a Two-stage Solid-propellant Nike-deacon (DAN) Meteorological Sounding Rocket

NASA Technical Reports Server (NTRS)

Heitkotter, Robert H

1956-01-01

A flight investigation of two Nike-Deacon (DAN) two-stage solid-propellant rocket vehicles indicated satisfactory performance may be expected from the DAN meteorological sounding rocket. Peak altitudes of 356,000 and 350,000 feet, respectively, were recorded for the two flight tests when both vehicles were launched from sea level at an elevation angle of 75 degrees. Performance calculations based on flight-test results show that altitudes between 358,000 feet and 487,000 feet may be attained with payloads varying between 60 pounds and 10 pounds.

Seismic Yield Estimates of UTTR Surface Explosions

NASA Astrophysics Data System (ADS)

Hayward, C.; Park, J.; Stump, B. W.

2016-12-01

Since 2007 the Utah Test and Training Range (UTTR) has used explosive demolition as a method to destroy excess solid rocket motors ranging in size from 19 tons to less than 2 tons. From 2007 to 2014, 20 high quality seismic stations within 180 km recorded most of the more than 200 demolitions. This provides an interesting dataset to examine seismic source scaling for surface explosions. Based upon observer records, shots were of 4 sizes, corresponding to the size of the rocket motors. Instrument corrections for the stations were quality controlled by examining the P-wave amplitudes of all magnitude 6.5-8 earthquakes from 30 to 90 degrees away. For each station recording, the instrument corrected RMS seismic amplitude in the first 10 seconds after the P-onset was calculated. Waveforms at any given station for all the observed explosions are nearly identical. The observed RMS amplitudes were fit to a model including a term for combined distance and station correction, a term for observed RMS amplitude, and an error term for the actual demolition size. The observed seismic yield relationship is RMS=k*Weight2/3 . Estimated yields for the largest shots vary by about 50% from the stated weights, with a nearly normal distribution.

KSC-07pd1513

NASA Image and Video Library

2007-06-15

KENNEDY SPACE CENTER, FLA. -- On Launch Pad 17-B at Cape Canaveral Air Force Station, the second stage of the Delta II launch vehicle for the Dawn spacecraft arrives at the upper level of the mobile service tower. It will be moved inside the tower and mated with the first stage already in the tower. The Delta II-Heavy, manufactured by the United Launch Alliance, is scheduled to launch the Dawn spacecraft on its 4-year flight to the asteroid belt. The Delta II-Heavy is the strongest rocket in the Delta II class. It will use three stages and nine solid-fueled booster rockets to propel Dawn on its way. A 9.5-foot payload fairing will protect the spacecraft from the heat and stresses of launch. Dawn's goal is to characterize the conditions and processes of the solar system's earliest epoch by investigating in detail the largest protoplanets that have remained intact since their formations: asteroid Vesta and the dwarf planet Ceres. They reside in the extensive zone between Mars and Jupiter together with many other smaller bodies, called the asteroid belt. Dawn is scheduled to launch July 7. Photo credit: NASA/Jack Pfaller

Photoignition Torch Applied to Cryogenic H2/O2 Coaxial Jet

DTIC Science & Technology

2016-12-06

suitable for certain thrusters and liquid rocket engines. This ignition system is scalable for applications in different combustion chambers such as gas ...turbines, gas generators, liquid rocket engines, and multi grain solid rocket motors. photoignition, fuel spray ignition, high pressure ignition...thrusters and liquid rocket engines. This ignition system is scalable for applications in different combustion chambers such as gas turbines, gas

The Future of the U.S. Intercontinental Ballistic Missile Force

DTIC Science & Technology

2014-01-01

42 3.7. Nevada Test Range and Surrounding Areas . . . . . . . . . . . . . . . . . . . . . 44 4.1. Solid Rocket ... Rocket Mass Ratio . . . 62 4.6. Range of an ICBM from Current Missile Bases . . . . . . . . . . . . . . . . 64 4.7. Range of an ICBM from Expanded...38 4.1. Specific Impulse of Various Rocket Propellants

Tenth Workshop for Computational Fluid Dynamic Applications in Rocket Propulsion, part 1

NASA Technical Reports Server (NTRS)

Williams, R. W. (Compiler)

1992-01-01

Experimental and computational fluid dynamic activities in rocket propulsion were discussed. The workshop was an open meeting of government, industry, and academia. A broad number of topics were discussed including computational fluid dynamic methodology, liquid and solid rocket propulsion, turbomachinery, combustion, heat transfer, and grid generation.

Nonlinear Acoustic Processes in a Solid Rocket Engine

DTIC Science & Technology

1994-03-29

conceptual framwork for the study number (M), weakly viscous internal flow sustained of solid rocket engine chamber flow dynamics which by mass...same magnitude. The formulation and results provide a conceptual framwork for the study of injected cylinder flow dynamics which supplements traditional...towards the axial direction. Until recently, conceptual understanding of this flow turning process has been based largely on the viscous properties of the

Lithium cell tests at Marshall Space Flight Center. [batteries for range safety and frustrum location aid in the shuttle solid rocket booster

NASA Technical Reports Server (NTRS)

Paschal, L. E.

1977-01-01

Three 18 AH Li-CF batteries with a polypropylene separator and using dimethyl sulfite in Li as F6 for the electrolyte will be placed in each shuttle solid rocket booster for range safety and frustrum location aid. Mechanical vibration, acceleration, random and design vibration, and discharge evaluation tests are discussed.

Thermophysical Property Testing Using Transient Techniques.

DTIC Science & Technology

1984-06-29

WORDS (Continue on reverse side if necessary and identify by block number) Specific heat HMX carbon/carbon Diffusivity RDX solid propellants Conductivity...energetic materials (AP, " HMX , RDX and HTPB) used in solid rocket fuel to carbon/carbon materials used as rocket nozzles. Studies on AP included single...32 4.1b HMX and RDX ............................35 a 4.2 Carbon/Carbon Materials ...................... 36 5.0 SUMMARY

IUS solid rocket motor contamination prediction methods

NASA Technical Reports Server (NTRS)

Mullen, C. R.; Kearnes, J. H.

1980-01-01

A series of computer codes were developed to predict solid rocket motor produced contamination to spacecraft sensitive surfaces. Subscale and flight test data have confirmed some of the analytical results. Application of the analysis tools to a typical spacecraft has provided early identification of potential spacecraft contamination problems and provided insight into their solution; e.g., flight plan modifications, plume or outgassing shields and/or contamination covers.

Water absorption and desorption in shuttle ablator and insulation materials

NASA Technical Reports Server (NTRS)

Whitaker, A. F.; Smith, C. F.; Wooden, V. A.; Cothren, B. E.; Gregory, H.

1982-01-01

Shuttle systems ablator and insulation materials underwent water soak with subsequent water desorption in vacuum. Water accumulation in these materials after a soak for 24 hours ranged from +1.1% for orbiter tile to +161% for solid rocket booster MSA-1. After 1 minute in vacuum, water retention ranged from none in the orbiter tile to +70% for solid rocket booster cork.

Thermal design of the space shuttle solid rocket booster

NASA Technical Reports Server (NTRS)

Fisher, R. R.; Vaniman, J. L.; Patterson, W. J.

1985-01-01

The thermal protection systems (TPS) to meet the quick turnaround and low cost required for reuse of the solid rocket booster (SRB) hardware. The TPS development considered the ease of application, changing ascent/reentry environments, and the problem of cleaning the residual insulation upon recovery. A sprayable ablator TPS material was developed. The challenges involved in design and development of this thermal system are discussed.

Closeup view of an Aft Skirt being prepared for mating ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Close-up view of an Aft Skirt being prepared for mating with sub assemblies in the Solid Rocket Booster Assembly and Refurbishment Facility at Kennedy Space Center. The most prominent feature in this view are the six Thrust Vector Control System access ports, three per hydraulic actuator. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

STS-80 Space Shuttle Mission Report

NASA Technical Reports Server (NTRS)

Fricke, Robert W., Jr.

1997-01-01

The STS-80 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Reusable Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the eightieth flight of the Space Shuttle Program, the fifty-fifth flight since the return-to-flight, and the twenty-first flight of the Orbiter Columbia (OV-102).

Study of organic ablative thermal-protection coating for solid rocket motor

NASA Astrophysics Data System (ADS)

Hua, Zenggong

1992-06-01

A study is conducted to find a new interior thermal-protection material that possesses good thermal-protection performance and simple manufacturing possibilities. Quartz powder and Cr2O3 are investigated using epoxy resin as a binder and Al2O3 as the burning inhibitor. Results indicate that the developed thermal-protection coating is suitable as ablative insulation material for solid rocket motors.

Study of solid rocket motor for space shuttle booster, volume 2, book 3, appendix A

NASA Technical Reports Server (NTRS)

1972-01-01

A systems requirements analysis for the solid propellant rocket engine to be used with the space shuttle was conducted. The systems analysis was developed to define the physical and functional requirements for the systems and subsystems. The operations analysis was performed to identify the requirements of the various launch operations, mission operations, ground operations, and logistic and flight support concepts.

A Preliminary Investigation on the Destruction of Solid-Propellant Rocket Motors by Impact from Small Particles

NASA Technical Reports Server (NTRS)

Carter, David J., Jr.

1960-01-01

An investigation was conducted to determine whether solid-propellant rocket motors could be ignited and destroyed by small-particle impacts at particle velocities up to a approximately 10,940 feet per second. Spheres ranging from 1/16 to 7/32 inch in diameter were fired into simulated rocket motors containing T-22 propellant over a range of ambient pressures from sea level to 0.12 inch of mercury absolute. Simulated cases of stainless steel, aluminum alloy, and laminated Fiberglas varied in thickness from 1/50 to 1/8 inch. Within the scope of this investigation, it was found that ignition and explosive destruction of simulated steel-case rocket motors could result from impacts by steel spheres at the lowest attainable pressure.

KENNEDY SPACE CENTER, FLA. - The Delta II rocket on Launch Complex 17-A, Cape Canaveral Air Force Station, is having solid rocket boosters (SRBs) installed that will help launch Mars Exploration Rover 2 (MER-2) on June 5. In the center are three more solid rocket boosters that will be added to the Delta, which will carry nine in all. NASA’s twin Mars Exploration Rovers are designed to study the history of water on Mars. These robotic geologists are equipped with a robotic arm, a drilling tool, three spectrometers, and four pairs of cameras that allow them to have a human-like, 3D view of the terrain. Each rover could travel as far as 100 meters in one day to act as Mars scientists' eyes and hands, exploring an environment where humans can’t yet go. MER-2 is scheduled to launch as MER-A. MER-1 (MER-B) will launch June 25.

NASA Image and Video Library

2003-05-15

KENNEDY SPACE CENTER, FLA. - The Delta II rocket on Launch Complex 17-A, Cape Canaveral Air Force Station, is having solid rocket boosters (SRBs) installed that will help launch Mars Exploration Rover 2 (MER-2) on June 5. In the center are three more solid rocket boosters that will be added to the Delta, which will carry nine in all. NASA’s twin Mars Exploration Rovers are designed to study the history of water on Mars. These robotic geologists are equipped with a robotic arm, a drilling tool, three spectrometers, and four pairs of cameras that allow them to have a human-like, 3D view of the terrain. Each rover could travel as far as 100 meters in one day to act as Mars scientists' eyes and hands, exploring an environment where humans can’t yet go. MER-2 is scheduled to launch as MER-A. MER-1 (MER-B) will launch June 25.

A hybrid rocket engine design for simple low cost sounding rocket use

NASA Astrophysics Data System (ADS)

Grubelich, Mark; Rowland, John; Reese, Larry

1993-06-01

Preliminary test results on a nitrous oxide/HTPB hybrid rocket engine suitable for powering a small sounding rocket to altitudes of 50-100 K/ft are presented. It is concluded that the advantage of the N2O hybrid engine over conventional solid propellant rocket motors is the ability to obtain long burn times with core burning geometries due to the low regression rate of the fuel. Long burn times make it possible to reduce terminal velocity to minimize air drag losses.

Optical Measurements on Solid Specimens of Solid Rocket Motor Exhaust and Solid Rocket Motor Slag

NASA Technical Reports Server (NTRS)

Roberts, F. E., III

1991-01-01

Samples of aluminum slag were investigated to aid the Earth Science and Applications Division at the Marshall Space Flight Center (MSFC). Alumina from space motor propellant exhaust and space motor propellant slag was examined as a component of space refuse. Thermal emittance and solar absorptivity measurements were taken to support their comparison with reflectance measurements derived from actual debris. To determine the similarity between the samples and space motor exhaust or space motor slag, emittance and absorbance results were correlated with an examination of specimen morphology.

Space Shuttle solid rocket motor exposure monitoring

NASA Technical Reports Server (NTRS)

Brown, S. W.

1993-01-01

During the processing of the Space Shuttle Solid Rocket Booster (SRB), segments at the Kennedy Space Center, an odor was detected around the solid propellant. An Industrial Hygiene survey was conducted to determine the chemical identity of the SRB offgassing constituents. Air samples were collected inside a forward SRB segment and analyzed to determine chemical composition. Specific chemical analysis for suspected offgassing constituents of the propellant indicated ammonia to be present. A gas chromatograph mass spectroscopy (GC/MS) analysis of the air samples detected numerous high molecular weight hydrocarbons.

Three-dimensional finite element analysis of acoustic instability of solid propellant rocket motors

NASA Technical Reports Server (NTRS)

Hackett, R. M.; Juruf, R. S.

1976-01-01

A three dimensional finite element solution of the acoustic vibration problem in a solid propellant rocket motor is presented. The solution yields the natural circular frequencies of vibration and the corresponding acoustic pressure mode shapes, considering the coupled response of the propellant grain to the acoustic oscillations occurring in the motor cavity. The near incompressibility of the solid propellant is taken into account in the formulation. A relatively simple example problem is solved in order to illustrate the applicability of the analysis and the developed computer code.

Safety Practices Followed in ISRO Launch Complex- An Overview

NASA Astrophysics Data System (ADS)

Krishnamurty, V.; Srivastava, V. K.; Ramesh, M.

2005-12-01

The spaceport of India, Satish Dhawan Space Centre (SDSC) SHAR of Indian Space Research Organisation (ISRO), is located at Sriharikota, a spindle shaped island on the east coast of southern India.SDSC SHAR has a unique combination of facilities, such as a solid propellant production plant, a rocket motor static test facility, launch complexes for different types of rockets, telemetry, telecommand, tracking, data acquisition and processing facilities and other support services.The Solid Propellant Space Booster Plant (SPROB) located at SDSC SHAR produces composite solid propellant for rocket motors of ISRO. The main ingredients of the propellant produced here are ammonium perchlorate (oxidizer), fine aluminium powder (fuel) and hydroxyl terminated polybutadiene (binder).SDSC SHAR has facilities for testing solid rocket motors, both at ambient conditions and at simulated high altitude conditions. Other test facilities for the environmental testing of rocket motors and their subsystems include Vibration, Shock, Constant Acceleration and Thermal / Humidity.SDSC SHAR has the necessary infrastructure for launching satellites into low earth orbit, polar orbit and geo-stationary transfer orbit. The launch complexes provide complete support for vehicle assembly, fuelling with both earth storable and cryogenic propellants, checkout and launch operations. Apart from these, it has facilities for launching sounding rockets for studying the Earth's upper atmosphere and for controlled reentry and recovery of ISRO's space capsule reentry missions.Safety plays a major role at SDSC SHAR right from the mission / facility design phase to post launch operations. This paper presents briefly the infrastructure available at SDSC SHAR of ISRO for launching sounding rockets, satellite launch vehicles, controlled reentry missions and the built in safety systems. The range safety methodology followed as a part of the real time mission monitoring is presented. The built in safety systems provided onboard the launch vehicle are automatic shut off the propulsion system based on real time mission performance and a passivation system incorporated in the orbit insertion stage are highlighted.

Space Shuttle Solid Rocket Booster Lightweight Recovery System

NASA Technical Reports Server (NTRS)

Wolf, Dean; Runkle, Roy E.

1995-01-01

The cancellation of the Advanced Solid Rocket Booster Project and the earth-to-orbit payload requirements for the Space Station dictated that the National Aeronautics and Space Administration (NASA) look at performance enhancements from all Space Transportation System (STS) elements (Orbiter Project, Space Shuttle Main Engine Project, External Tank Project, Solid Rocket Motor Project, & Solid Rocket Booster Project). The manifest for launching of Space Station components indicated that an additional 12-13000 pound lift capability was required on 10 missions and 15-20,000 pound additional lift capability is required on two missions. Trade studies conducted by all STS elements indicate that by deleting the parachute Recovery System (and associated hardware) from the Solid Rocket Boosters (SRBS) and going to a lightweight External Tank (ET) the 20,000 pound additional lift capability can be realized for the two missions. The deletion of the parachute Recovery System means the loss of four SRBs and this option is two expensive (loss of reusable hardware) to be used on the other 10 Space Station missions. Accordingly, each STS element looked at potential methods of weight savings, increased performance, etc. As the SRB and ET projects are non-propulsive (i.e. does not have launch thrust elements) their only contribution to overall payload enhancement can be achieved by the saving of weight while maintaining adequate safety factors and margins. The enhancement factor for the SRB project is 1:10. That is for each 10 pounds saved on the two SRBS; approximately 1 additional pound of payload in the orbiter bay can be placed into orbit. The SRB project decided early that the SRB recovery system was a prime candidate for weight reduction as it was designed in the early 1970s and weight optimization had never been a primary criteria.

Hybrid rocket engine, theoretical model and experiment

NASA Astrophysics Data System (ADS)

Chelaru, Teodor-Viorel; Mingireanu, Florin

2011-06-01

The purpose of this paper is to build a theoretical model for the hybrid rocket engine/motor and to validate it using experimental results. The work approaches the main problems of the hybrid motor: the scalability, the stability/controllability of the operating parameters and the increasing of the solid fuel regression rate. At first, we focus on theoretical models for hybrid rocket motor and compare the results with already available experimental data from various research groups. A primary computation model is presented together with results from a numerical algorithm based on a computational model. We present theoretical predictions for several commercial hybrid rocket motors, having different scales and compare them with experimental measurements of those hybrid rocket motors. Next the paper focuses on tribrid rocket motor concept, which by supplementary liquid fuel injection can improve the thrust controllability. A complementary computation model is also presented to estimate regression rate increase of solid fuel doped with oxidizer. Finally, the stability of the hybrid rocket motor is investigated using Liapunov theory. Stability coefficients obtained are dependent on burning parameters while the stability and command matrixes are identified. The paper presents thoroughly the input data of the model, which ensures the reproducibility of the numerical results by independent researchers.

Fundamental phenomena on fuel decomposition and boundary layer combustion processes with applications to hybrid rocket motors

NASA Technical Reports Server (NTRS)

Kuo, Kenneth K.; Lu, Y. C.; Chiaverini, Martin J.; Harting, George C.

1994-01-01

An experimental study on the fundamental processes involved in fuel decomposition and boundary layer combustion in hybrid rocket motors is being conducted at the High Pressure Combustion Laboratory of the Pennsylvania State University. This research should provide an engineering technology base for development of large scale hybrid rocket motors as well as a fundamental understanding of the complex processes involved in hybrid propulsion. A high pressure slab motor has been designed for conducting experimental investigations. Oxidizer (LOX or GOX) is injected through the head-end over a solid fuel (HTPB) surface. Experiments using fuels supplied by NASA designated industrial companies will also be conducted. The study focuses on the following areas: measurement and observation of solid fuel burning with LOX or GOX, correlation of solid fuel regression rate with operating conditions, measurement of flame temperature and radical species concentrations, determination of the solid fuel subsurface temperature profile, and utilization of experimental data for validation of a companion theoretical study also being conducted at PSU.

Effect of the Thruster Configurations on a Laser Ignition Microthruster

NASA Astrophysics Data System (ADS)

Koizumi, Hiroyuki; Hamasaki, Kyoichi; Kondo, Ryo; Okada, Keisuke; Nakano, Masakatsu; Arakawa, Yoshihiro

Research and development of small spacecraft have advanced extensively throughout the world and propulsion devices suitable for the small spacecraft, microthruster, is eagerly anticipated. The authors proposed a microthruster using 1—10-mm-size solid propellant. Small pellets of solid propellant are installed in small combustion chambers and ignited by the irradiation of diode laser beam. This thruster is referred as to a laser ignition microthruster. Solid propellant enables large thrust capability and compact propulsion system. To date theories of a solid-propellant rocket have been well established. However, those theories are for a large-size solid propellant and there are a few theories and experiments for a micro-solid rocket of 1—10mm class. This causes the difficulty of the optimum design of a micro-solid rocket. In this study, we have experimentally investigated the effect of thruster configurations on a laser ignition microthruster. The examined parameters are aperture ratio of the nozzle, length of the combustion chamber, area of the nozzle throat, and divergence angle of the nozzle. Specific impulse dependences on those parameters were evaluated. It was found that large fraction of the uncombusted propellant was the main cause of the degrading performance. Decreasing the orifice diameter in the nozzle with a constant open aperture ratio was an effective method to improve this degradation.

ASRM case insulation design and development

NASA Astrophysics Data System (ADS)

Bell, Matthew S.; Tam, William F. S.

1992-10-01

This paper describes the achievements made on the Advanced Solid Rocket Motor (ASRM) case insulation design and development program. The ASRM case insulation system described herein protects the metal case and joints from direct radiation and hot gas impingement. Critical failure of solid rocket systems is often traceable to failure of the insulation design. The wide ranging accomplishments included the development of a nonasbestos insulation material for ASRM that replaced the existing Redesigned Solid Rocket Motor (RSRM) asbestos-filled nitrile butadiene rubber (NBR) along with a performance gain of 300 pounds, and improved reliability of all the insulation joint designs, i.e., segmented case joint, case-to-nozzle and case-to-igniter joint. The insulation process development program included the internal stripwinding process. This process advancement allowed Aerojet to match to exceed the capability of other propulsion companies.

Characterization of welded HP 9-4-30 steel for the advanced solid rocket motor

NASA Technical Reports Server (NTRS)

Watt, George William

1990-01-01

Solid rocket motor case materials must be high-strength, high-toughness, weldable alloys. The Advanced Solid Rocket Motor (ASRM) cases currently being developed will be made from a 9Ni-4Co quench and temper steel called HP 9-4-30. These ultra high-strength steels must be carefully processed to give a very clean material and a fine grained microstructure, which insures excellent ductility and toughness. The HP 9-4-30 steels are vacuum arc remelted and carbon deoxidized to give the cleanliness required. The ASRM case material will be formed into rings and then welded together to form the case segments. Welding is the desired joining technique because it results in a lower weight than other joining techniques. The mechanical and corrosion properties of the weld region material were fully studied.

Expendable solid rocket motor upper stages for the Space Shuttle

NASA Technical Reports Server (NTRS)

Davis, H. P.; Jones, C. M.

1974-01-01

A family of expendable solid rocket motor upper stages has been conceptually defined to provide the payloads for the Space Shuttle with performance capability beyond the low earth operational range of the Shuttle Orbiter. In this concept-feasibility assessment, three new solid rocket motors of fixed impulse are defined for use with payloads requiring levels of higher energy. The conceptual design of these motors is constrained to limit thrusting loads into the payloads and to conserve payload bay length. These motors are combined in various vehicle configurations with stage components derived from other programs for the performance of a broad range of upper-stage missions from spin-stabilized, single-stage transfers to three-axis stabilized, multistage insertions. Estimated payload delivery performance and combined payload mission loading configurations are provided for the upper-stage configurations.

Space Shuttle solid rocket booster

NASA Technical Reports Server (NTRS)

Hardy, G. B.

1979-01-01

Details of the design, operation, testing and recovery procedures of the reusable solid rocket boosters (SRB) are given. Using a composite PBAN propellant, they will provide the primary thrust (six million pounds maximum at 20 s after ignition) within a 3 g acceleration constraint, as well as thrust vector control for the Space Shuttle. The drogues were tested to a load of 305,000 pounds, and the main parachutes to 205,000. Insulation in the solid rocket motor (SRM) will be provided by asbestos-silica dioxide filled acrylonitrile butadiene rubber ('asbestos filled NBR') except in high erosion areas (principally in the aft dome), where a carbon-filled ethylene propylene diene monomer-neopreme rubber will be utilized. Furthermore, twenty uses for the SRM nozzle will be allowed by its ablative materials, which are principally carbon cloth and silica cloth phenolics.

ASRM case insulation design and development

NASA Technical Reports Server (NTRS)

Bell, Matthew S.; Tam, William F. S.

1992-01-01

This paper describes the achievements made on the Advanced Solid Rocket Motor (ASRM) case insulation design and development program. The ASRM case insulation system described herein protects the metal case and joints from direct radiation and hot gas impingement. Critical failure of solid rocket systems is often traceable to failure of the insulation design. The wide ranging accomplishments included the development of a nonasbestos insulation material for ASRM that replaced the existing Redesigned Solid Rocket Motor (RSRM) asbestos-filled nitrile butadiene rubber (NBR) along with a performance gain of 300 pounds, and improved reliability of all the insulation joint designs, i.e., segmented case joint, case-to-nozzle and case-to-igniter joint. The insulation process development program included the internal stripwinding process. This process advancement allowed Aerojet to match to exceed the capability of other propulsion companies.

Space shuttle SRM plume expansion sensitivity analysis. [flow characteristics of exhaust gases from solid propellant rocket engines

NASA Technical Reports Server (NTRS)

Smith, S. D.; Tevepaugh, J. A.; Penny, M. M.

1975-01-01

The exhaust plumes of the space shuttle solid rocket motors can have a significant effect on the base pressure and base drag of the shuttle vehicle. A parametric analysis was conducted to assess the sensitivity of the initial plume expansion angle of analytical solid rocket motor flow fields to various analytical input parameters and operating conditions. The results of the analysis are presented and conclusions reached regarding the sensitivity of the initial plume expansion angle to each parameter investigated. Operating conditions parametrically varied were chamber pressure, nozzle inlet angle, nozzle throat radius of curvature ratio and propellant particle loading. Empirical particle parameters investigated were mean size, local drag coefficient and local heat transfer coefficient. Sensitivity of the initial plume expansion angle to gas thermochemistry model and local drag coefficient model assumptions were determined.

KSC-08pd0872

NASA Image and Video Library

2008-03-27

CAPE CANAVERAL, Fla. --- On Pad 17-B on Cape Canaveral Air Force Station, the mobile service tower at left approaches the Delta II rocket at right. The solid rocket boosters in the tower will be mated with the rocket, which will launch NASA's Gamma-ray Large Area Space Telescope, or GLAST, spacecraft. A series of nine strap-on solid rocket motors will be mated with the rocket to help power the first stage. Because the Delta rocket is configured as a Delta II 7920 Heavy, the boosters are larger than those used on the standard configuration. The GLAST is a powerful space observatory that will explore the Universe's ultimate frontier, where nature harnesses forces and energies far beyond anything possible on Earth; probe some of science's deepest questions, such as what our Universe is made of, and search for new laws of physics; explain how black holes accelerate jets of material to nearly light speed; and help crack the mystery of stupendously powerful explosions known as gamma-ray bursts. Launch is currently planned for May 16 from Pad 17-B. Photo credit: NASA/Jim Grossmann

KSC-08pd0873

NASA Image and Video Library

2008-03-27

CAPE CANAVERAL, Fla. --- On Pad 17-B on Cape Canaveral Air Force Station, the mobile service tower at left approaches the Delta II rocket at right. The solid rocket boosters in the tower will be mated with the rocket, which will launch NASA's Gamma-ray Large Area Space Telescope, or GLAST, spacecraft. A series of nine strap-on solid rocket motors will be mated with the rocket to help power the first stage. Because the Delta rocket is configured as a Delta II 7920 Heavy, the boosters are larger than those used on the standard configuration. The GLAST is a powerful space observatory that will explore the Universe's ultimate frontier, where nature harnesses forces and energies far beyond anything possible on Earth; probe some of science's deepest questions, such as what our Universe is made of, and search for new laws of physics; explain how black holes accelerate jets of material to nearly light speed; and help crack the mystery of stupendously powerful explosions known as gamma-ray bursts. Launch is currently planned for May 16 from Pad 17-B. Photo credit: NASA/Jim Grossmann

SRB Processing Facilities Media Event

NASA Image and Video Library

2016-03-01

Inside the Booster Fabrication Facility (BFF) at NASA’s Kennedy Space Center in Florida, members of the news media photograph a frustrum that will be stacked atop a forward skirt for one of NASA’s Space Launch System (SLS) solid rocket boosters. Orbital ATK is a contractor for NASA’s Marshall Space Flight Center in Alabama, and operates the BFF to prepare aft booster segments and hardware for the SLS solid rocket boosters. The SLS rocket and Orion spacecraft will launch on Exploration Mission-1 in 2018. The Ground Systems Development and Operations Program is preparing the infrastructure to process and launch spacecraft on deep-space missions and the journey to Mars.

KSC-08pd1095

NASA Image and Video Library

2008-05-01

CAPE CANAVERAL, Fla. -- In Firing Room No. 1 in the Launch Control Center at NASA's Kennedy Space Center, the number of new equipment cabinets increases as workers put the elements together. The firing room will support the future Ares rocket launches as part of the Constellation Program. Future astronauts will ride to orbit on Ares I, which uses a single five-segment solid rocket booster, a derivative of the space shuttle's solid rocket booster, for the first stage. Ares will be launched from Pad 39B, which is being reconfigured from supporting space shuttle launches. The Launch Control Center firing rooms face the launch pads. Photo credit: NASA/Kim Shiflett

KSC-08pd1088

NASA Image and Video Library

2008-05-01

CAPE CANAVERAL, Fla. -- A near-empty Firing Room No. 1 in the Launch Control Center at NASA's Kennedy Space Center is ready for the installation of racks of equipment. The firing room will support the future Ares rocket launches as part of the Constellation Program. Future astronauts will ride to orbit on Ares I, which uses a single five-segment solid rocket booster, a derivative of the space shuttle's solid rocket booster, for the first stage. Ares will be launched from Pad 39B, which is being reconfigured from supporting space shuttle launches. The Launch Control Center firing rooms face the launch pads. Photo credit: NASA/Kim Shiflett

KSC-08pd1092

NASA Image and Video Library

2008-05-01

CAPE CANAVERAL, Fla. -- In Firing Room No. 1 in the Launch Control Center at NASA's Kennedy Space Center, a worker holds on to a cabinet being put together to hold equipment that will support the future Ares rocket launches as part of the Constellation Program. Future astronauts will ride to orbit on Ares I, which uses a single five-segment solid rocket booster, a derivative of the space shuttle's solid rocket booster, for the first stage. Ares will be launched from Pad 39B, which is being reconfigured from supporting space shuttle launches. The Launch Control Center firing rooms face the launch pads. Photo credit: NASA/Kim Shiflett

KSC-08pd1089

NASA Image and Video Library

2008-05-01

CAPE CANAVERAL, Fla. -- In Firing Room No. 1 in the Launch Control Center at NASA's Kennedy Space Center, panels stretch across the floor in preparation for erecting equipment racks. The firing room will support the future Ares rocket launches as part of the Constellation Program. Future astronauts will ride to orbit on Ares I, which uses a single five-segment solid rocket booster, a derivative of the space shuttle's solid rocket booster, for the first stage. Ares will be launched from Pad 39B, which is being reconfigured from supporting space shuttle launches. The Launch Control Center firing rooms face the launch pads. Photo credit: NASA/Kim Shiflett

Space shuttle redesigned solid rocket motor Certificate of Qualification (COQ) data report

NASA Technical Reports Server (NTRS)

Duersch, Fred, Jr.

1990-01-01

The Space Shuttle Redesigned Solid Rocket Motor (RSRM) Certification Program provides confidence that the RSRM and its components/subsystems meet or exceed Mission Oriented Requirements when manufactured per design requirements and specified/approved processes. Certification is based on documented results of tests, analyses, inspections, similarity, and demonstrations. Evidencing information is provided to certify that each RSRM component/subsystem satisfies design, mission related requirements and objectives.

Experimental and Numerical Characterization of Polymer Nanocomposites for Solid Rocket Motor Internal Insulation

DTIC Science & Technology

2009-09-30

combustion chamber. Kevlar®-filled ethylene-propylene-diene rubber ( EPDM ) is the baseline insulation material for solid rocket motor cases. A novel...filled EPDM is the industry standard for this application. Since the elastic modulus of rubbers is low, they also act as absorbers during...Santoprene® thermoplastic rubber is already demonstrating their performance capability to replace EPDM in automotive weather seal applications [18]. An

KENNEDY SPACE CENTER, FLA. - The external tank in the Vehicle Assembly Building (VAB) is destacked from the solid rocket boosters. The tank and SRBs were configured for Atlantis and mission STS-114. The tank will remain in the VAB.

NASA Image and Video Library

2003-05-20

KENNEDY SPACE CENTER, FLA. - The external tank in the Vehicle Assembly Building (VAB) is destacked from the solid rocket boosters. The tank and SRBs were configured for Atlantis and mission STS-114. The tank will remain in the VAB.

SRB-3D Solid Rocket Booster performance prediction program. Volume 1: Engineering description/users information manual

NASA Technical Reports Server (NTRS)

Winkler, J. C.

1976-01-01

The modified Solid Rocket Booster Performance Evaluation Model (SRB-3D) was developed as an extension to the internal ballistics module of the SRB-2 performance program. This manual contains the engineering description of SRB-3D which describes the approach used to develop the 3D concept and an explanation of the modifications which were necessary to implement these concepts.

Evolution of solid rocket booster component testing

NASA Technical Reports Server (NTRS)

Lessey, Joseph A.

1989-01-01

The evolution of one of the new generation of test sets developed for the Solid Rocket Booster of the U.S. Space Transportation System. Requirements leading to factory checkout of the test set are explained, including the evolution from manual to semiautomated toward fully automated status. Individual improvements in the built-in test equipment, self-calibration, and software flexibility are addressed, and the insertion of fault detection to improve reliability is discussed.

The Use of Ion Vapor Deposited Aluminum (IVD) for the Space Shuttle Solid Rocket Booster (SRB)

NASA Technical Reports Server (NTRS)

Novak, Howard L.

2003-01-01

This viewgraph representation provides an overview of the use of ion vapor deposited aluminum (IVD) for use in the Space Shuttle Solid Rocket Booster (SRB). Topics considered include: schematics of ion vapor deposition system, production of ion vapor deposition system, IVD vs. cadmium coated drogue ratchets, corrosion exposure facilities and tests, seawater immersion facilities and tests and continued research and development issues.

Space shuttle solid rocket booster sting interference wind tunnel test analysis

NASA Technical Reports Server (NTRS)

Conine, B.; Boyle, W.

1981-01-01

Wind tunnel test results from shuttle solid rocket booster (SRB) sting interference tests were evaluated, yielding the general influence of the sting on the normal force and pitching moment coefficients and the side force and yawing moment coefficients. The procedures developed to determine the sting interference, the development of the corrected aerodynamic data, and the development of a new SRB aerodynamic mathematical model are documented.

Measurements of Particulates in Solid Propellant Rocket Motors

DTIC Science & Technology

1987-10-01

gradients created during a firing, however, could be a problem. Finally, a torch was placed in the motor to study temperature effects. The nitrogen...techniques available for studying particulate behavior in solid propellant rocket motors is holography. For the exposed scene a hologram provides both...is underway to study the effects of addition of aluminum and other metallic particles on the magnitude of the performance losses in propellant motors

Some problems of nonlinear waves in solid propellant rocket motors

NASA Technical Reports Server (NTRS)

Culick, F. E. C.

1979-01-01

An approximate technique for analyzing nonlinear waves in solid propellant rocket motors is presented which inexpensively provides accurate results up to amplitudes of ten percent. The connection with linear stability analysis is shown. The method is extended to third order in the amplitude of wave motion in order to study nonlinear stability, or triggering. Application of the approximate method to the behavior of pulses is described.

Characterization of the non axial thrust generated by large solid propellant rocket motors in three axis stabilized ascent

NASA Technical Reports Server (NTRS)

Kosmann, W. J.; Dionne, E. R.; Klemetson, R. W.

1978-01-01

Nonaxial thrusts produced by solid rocket motors during three-axis stabilized attitude control have been determined from ascent experience on twenty three Burner II, Burner IIA and Block 5D-1 upper stage vehicles. A data base representing four different rocket motor designs (three spherical and one extended spherical) totaling twenty five three-axis stabilized firings is generated. Solid rocket motor time-varying resultant and lateral side force vector magnitudes, directions and total impulses, and roll torque couple magnitudes, directions, and total impulses are tabulated in the appendix. Population means and three sigma deviations are plotted. Existing applicable ground test side force and roll torque magnitudes and total impulses are evaluated and compared to the above experience data base. Within the spherical motor population, the selected AEDC ground test data consistently underestimated experienced motor side forces, roll torques and total impulses. Within the extended spherical motor population, the selected AEDC test data predicted experienced motor side forces, roll torques, and total impulses, with surprising accuracy considering the very small size of the test and experience populations.

Development of a miniature solid propellant rocket motor for use in plume simulation studies

NASA Technical Reports Server (NTRS)

Baran, W. J.

1974-01-01

A miniature solid propellant rocket motor has been developed to be used in a program to determine those parameters which must be duplicated in a cold gas flow to produce aerodynamic effects on an experimental model similar to those produced by hot, particle-laden exhaust plumes. Phenomena encountered during the testing of the miniature solid propellant motors included erosive propellant burning caused by high flow velocities parallel to the propellant surface, regressive propellant burning as a result of exposed propellant edges, the deposition of aluminum oxide on the nozzle surfaces sufficient to cause aerodynamic nozzle throat geometry changes, and thermal erosion of the nozzle throat at high chamber pressures. A series of tests was conducted to establish the stability of the rocket chamber pressure and the repeatibility of test conditions. Data are presented which define the tests selected to represent the final test matrix. Qualitative observations are also presented concerning the phenomena experienced based on the results of a large number or rocket tests not directly applicable to the final test matrix.

Air Force Research Laboratory (AFRL) research highlights, September--October 1998

DOE Office of Scientific and Technical Information (OSTI.GOV)

NONE

New AFOSR-sponsored research shows that exhausts from solid-fueled rocket motors have very limited impact on stratospheric ozone. The research provides the Air Force with hard data to support continued access to space using the existing fleet of rockets and rocket technology. This basic research data allows the Air Force to maintain a strongly proactive environmental stance, and to meet federal guidelines regarding environmental impacts. Long-standing conjecture within the international rocket community suggests that chlorine compounds and alumina particulates produced in solid rocket motor (SRM) exhausts could create localized, temporary ozone toss in rocket plumes following launches. The extent of amore » local depletion of ozone and its environmental impact depends on details of the composition and chemistry in these plumes. Yet direct measurements of plume composition and plume chemistry in the stratosphere had never been made. Uncertainty about these details left the Air Force and commercial space launch capability potentially vulnerable to questions about the environmental impact of rocket launches. In 1995, APOSR and the Space and Missiles Systems Center Launch Programs Office (SMC/CL) jointly began the Rocket Impacts on Stratospheric Ozone (RISO) program to make the first-ever detailed measurements of rocket exhaust plumes. These measurements were aimed at understanding how the exhaust from large rocket motors effect the Earth`s stratospheric ozone layer. The studies determined: the size distribution of alumina particles in these exhausts, the amount of reactive chlorine in SRM exhaust, and the size and duration of localized ozone toss in the rocket plumes.« less

U.S. Strategic Nuclear Forces: Background, Developments, and Issues

DTIC Science & Technology

2016-09-27

meet the terms of the New START Treaty. The Air Force is also modernizing the Minuteman missiles, replacing and upgrading their rocket motors...began in 1998 and has been replacing the propellant, the solid rocket fuel, in the Minuteman motors to extend the life of the rocket motors. A...complete the program. It has not requested additional funding in subsequent years. Propulsion System Rocket Engine Program (PSRE) According to the Air

Atmospheric scavenging of solid rocket exhaust effluents

NASA Technical Reports Server (NTRS)

Fenton, D. L.; Purcell, R. Y.

1978-01-01

Solid propellant rocket exhaust was directly utilized to ascertain raindrop scavenging rates for hydrogen chloride. Two chambers were used to conduct the experiments; a large, rigid walled, spherical chamber stored the exhaust constituents, while the smaller chamber housing all the experiments was charged as required with rocket exhaust HCl. Surface uptake experiments demonstrated an HCl concentration dependence for distilled water. Sea water and brackish water HCl uptake was below the detection limit of the chlorine-ion analysis technique used. Plant life HCl uptake experiments were limited to corn and soybeans. Plant age effectively correlated the HCl uptake data. Metallic corrosion was not significant for single 20 minute exposures to the exhaust HCl under varying relative humidity. Characterization of the aluminum oxide particles substantiated the similarity between the constituents of the small scale rocket and the full size vehicles.

General view of the Aft Rocket Motor mated with the ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

General view of the Aft Rocket Motor mated with the External Tank Attach Ring and Aft Skirt Assembly in the process of being mounted onto the Mobile Launch Platform in the Vehicle Assembly Building at Kennedy Space Center. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

General view of the Aft Rocket Motor mated with the ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

General view of the Aft Rocket Motor mated with the External Tank Attach Ring and Aft Skirt Assembly being transported from the Rotation Processing and Surge Facility to the Vehicle Assembly Building at Kennedy Space Center. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Liquid rocket booster study. Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

1989-01-01

The purpose of this study was to determine the feasibility of Liquid Rocket Boosters (LRBs) replacing Solid Rocket Boosters on the Space Shuttle program. The major findings are given. The most significant conclusion is that LRBs offer significantly safety and performance advantages over the SRBs currently used by the STS without major impact to the ongoing program.

KENNEDY SPACE CENTER, FLA. - Workers on Launch Complex 17-B, Cape Canaveral Air Force Station, prepare the first stage of a Delta II rocket for its lift up the mobile service tower. The rocket is being erected to launch the Space InfraRed Telescope Facility (SIRTF). Consisting of an 0.85-meter telescope and three cryogenically cooled science instruments, SIRTF is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

NASA Image and Video Library

2003-07-18

KENNEDY SPACE CENTER, FLA. - Workers on Launch Complex 17-B, Cape Canaveral Air Force Station, prepare the first stage of a Delta II rocket for its lift up the mobile service tower. The rocket is being erected to launch the Space InfraRed Telescope Facility (SIRTF). Consisting of an 0.85-meter telescope and three cryogenically cooled science instruments, SIRTF is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

KENNEDY SPACE CENTER, FLA. - On Launch Complex 17-B, Cape Canaveral Air Force Station, the first stage of a Delta II rocket arrives at the pad. The rocket is being erected to launch the Space InfraRed Telescope Facility (SIRTF). Consisting of an 0.85-meter telescope and three cryogenically cooled science instruments, SIRTF is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

NASA Image and Video Library

2003-07-18

KENNEDY SPACE CENTER, FLA. - On Launch Complex 17-B, Cape Canaveral Air Force Station, the first stage of a Delta II rocket arrives at the pad. The rocket is being erected to launch the Space InfraRed Telescope Facility (SIRTF). Consisting of an 0.85-meter telescope and three cryogenically cooled science instruments, SIRTF is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

KENNEDY SPACE CENTER, FLA. - On Launch Complex 17-B, Cape Canaveral Air Force Station, the first stage of a Delta II rocket is moved into the mobile service tower. The rocket is being erected to launch the Space InfraRed Telescope Facility (SIRTF). Consisting of an 0.85-meter telescope and three cryogenically cooled science instruments, SIRTF is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

NASA Image and Video Library

2003-07-18

KENNEDY SPACE CENTER, FLA. - On Launch Complex 17-B, Cape Canaveral Air Force Station, the first stage of a Delta II rocket is moved into the mobile service tower. The rocket is being erected to launch the Space InfraRed Telescope Facility (SIRTF). Consisting of an 0.85-meter telescope and three cryogenically cooled science instruments, SIRTF is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

KENNEDY SPACE CENTER, FLA. - On Launch Complex 17-B, Cape Canaveral Air Force Station, the first stage of a Delta II rocket is nearly erect for its move into the mobile service tower. The rocket is being erected to launch the Space InfraRed Telescope Facility (SIRTF). Consisting of an 0.85-meter telescope and three cryogenically cooled science instruments, SIRTF is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

NASA Image and Video Library

2003-07-18

KENNEDY SPACE CENTER, FLA. - On Launch Complex 17-B, Cape Canaveral Air Force Station, the first stage of a Delta II rocket is nearly erect for its move into the mobile service tower. The rocket is being erected to launch the Space InfraRed Telescope Facility (SIRTF). Consisting of an 0.85-meter telescope and three cryogenically cooled science instruments, SIRTF is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

KENNEDY SPACE CENTER, FLA. - On Launch Complex 17-B, Cape Canaveral Air Force Station, the first stage of a Delta II rocket waits to be lifted up into the mobile service tower. The rocket is being erected to launch the Space InfraRed Telescope Facility (SIRTF). Consisting of an 0.85-meter telescope and three cryogenically cooled science instruments, SIRTF is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

NASA Image and Video Library

2003-07-18

KENNEDY SPACE CENTER, FLA. - On Launch Complex 17-B, Cape Canaveral Air Force Station, the first stage of a Delta II rocket waits to be lifted up into the mobile service tower. The rocket is being erected to launch the Space InfraRed Telescope Facility (SIRTF). Consisting of an 0.85-meter telescope and three cryogenically cooled science instruments, SIRTF is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

Animation: What makes up the Space Launch System’s massive core stage

NASA Image and Video Library

2017-04-24

NASA’s new rocket, the Space Launch System, will be the most powerful rocket ever built for deep-space missions. The 212-foot core stage is the largest rocket stage ever built and will fuel four RS-25 engines that will help launch SLS. This animation depicts the parts that make up the core stage and how these parts will be joined to form the entire stage. The five major parts include: the engine section, the hydrogen tank, the intertank, the liquid oxygen tank and the forward skirt.

KSC-2010-4843

NASA Image and Video Library

2010-09-27

CAPE CANAVERAL, Fla. -- Freedom Star, one of NASA's solid rocket booster retrieval ships, pulls the Space Shuttle Program's last external fuel tank, ET-122, toward NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. After reaching the Turn Basin at Kennedy, the tank will be offloaded and moved to the Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Jack Pfaller

KSC-2010-4850

NASA Image and Video Library

2010-09-27

CAPE CANAVERAL, Fla. -- Freedom Star, one of NASA's solid rocket booster retrieval ships, pulls the Space Shuttle Program's last external fuel tank, ET-122, toward NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. After reaching the Turn Basin at Kennedy, the tank will be offloaded and moved to the Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Kim Shiflett

KSC-2010-4846

NASA Image and Video Library

2010-09-27

CAPE CANAVERAL, Fla. -- Freedom Star, one of NASA's solid rocket booster retrieval ships, pulls the Space Shuttle Program's last external fuel tank, ET-122, toward NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. After reaching the Turn Basin at Kennedy, the tank will be offloaded and moved to the Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Jack Pfaller

KSC-2010-4830

NASA Image and Video Library

2010-09-27

CAPE CANAVERAL, Fla. -- Freedom Star, one of NASA's solid rocket booster retrieval ships, ushers the Space Shuttle Program's last external fuel tank, ET-122, toward NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. After reaching the Turn Basin at Kennedy, the tank will be offloaded and moved to the Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Frankie Martin

KSC-2010-4853

NASA Image and Video Library

2010-09-27

CAPE CANAVERAL, Fla. -- Freedom Star, one of NASA's solid rocket booster retrieval ships, pulls the Space Shuttle Program's last external fuel tank, ET-122, toward NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. After reaching the Turn Basin at Kennedy, the tank will be offloaded and moved to the Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Kim Shiflett

KSC-2010-4817

NASA Image and Video Library

2010-09-22

CAPE CANAVERAL, Fla. -- This view at dusk from the stern of Freedom Star, one of NASA's solid rocket booster retrieval ships, shows the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122, as it is transported to NASA's Kennedy Space Center in Florida. The tank will travel 900 miles by sea before being offloaded and moved to Kennedy's Vehicle Assembly Building where it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett

KSC-2010-4829

NASA Image and Video Library

2010-09-27

CAPE CANAVERAL, Fla. -- Freedom Star, one of NASA's solid rocket booster retrieval ships, ushers the Space Shuttle Program's last external fuel tank, ET-122, toward NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. After reaching the Turn Basin at Kennedy, the tank will be offloaded and moved to the Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Frankie Martin

KSC-2010-4814

NASA Image and Video Library

2010-09-22

GULFPORT, La. -- This view from the captain's deck of Freedom Star, one of NASA's solid rocket booster retrieval ships, shows the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122, as it is escorted from Gulfport, La., to NASA's Kennedy Space Center in Florida. The tank will travel 900 miles by sea before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett

KSC-2010-4845

NASA Image and Video Library

2010-09-27

CAPE CANAVERAL, Fla. -- Freedom Star, one of NASA's solid rocket booster retrieval ships, pulls the Space Shuttle Program's last external fuel tank, ET-122, toward NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. After reaching the Turn Basin at Kennedy, the tank will be offloaded and moved to the Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Jack Pfaller

EPDM rocket motor insulation

NASA Technical Reports Server (NTRS)

Guillot, David G. (Inventor); Harvey, Albert R. (Inventor)

2003-01-01

A novel and improved EPDM formulation for a solid propellant rocket motor is described wherein hexadiene EPDM monomer components are replaced by alkylidene norbornene components and with appropriate adjustment of curing and other additives functionally-required rheological and physical characteristics are achieved with the desired compatibility with any one of a plurality of solid filler materials, e.g. powder silica, carbon fibers or aramid fibers, and with appropriate adhesion and extended storage or shelf life characteristics.

EPDM rocket motor insulation

NASA Technical Reports Server (NTRS)

Guillot, David G. (Inventor); Harvey, Albert R. (Inventor)

2008-01-01

A novel and improved EPDM formulation for a solid propellant rocket motor is described wherein hexadiene EPDM monomer components are replaced by alkylidene norbornene components, and, with appropriate adjustment of curing and other additives, functionally required rheological and physical characteristics are achieved with the desired compatibility with any one of a plurality of solid filler materials, e.g., powder silica, carbon fibers or aramid fibers, and with appropriate adhesion and extended storage or shelf-life characteristics.

EPDM rocket motor insulation

NASA Technical Reports Server (NTRS)

Guillot, David G. (Inventor); Harvey, Albert R. (Inventor)

2004-01-01

A novel and improved EPDM formulation for a solid propellant rocket motor is described wherein hexadiene EPDM monomer components are replaced by alkylidene norbornene components, and, with appropriate adjustment of curing and other additives, functionally required rheological and physical characteristics are achieved with the desired compatibility with any one of a plurality of solid filler materials, e.g., powder silica, carbon fibers or aramid fibers, and with appropriate adhesion and extended storage or shelf-life characteristics.

Solid Rocket Testing at AFRL (Briefing Charts)

DTIC Science & Technology

2016-10-21

Force Research Laboratory (AFMC) AFRL /RQRO 8 Draco Drive Edwards AFB, CA 93524-7135 Air Force Research Laboratory (AFMC) AFRL /RQR 5 Pollux Drive...19b. TELEPHONE NUMBER (Include area code) 10/21/2016 Briefing Charts 01 October 2016 - 31 October 2016 Solid Rocket Testing at AFRL Robert Antypas Air ...Space Dominance MOJAVE BORONHWY 58 LANCASTER H IG H W A Y 14 RESERVATION BOUNDARY 0 5 10SCALE IN MILES HWY 395 EDWARDS

Water impact test of aft skirt end ring, and mid ring segments of the Space Shuttle Solid Rocket Booster

NASA Technical Reports Server (NTRS)

1983-01-01

The results of water impact loads tests using aft skirt end ring, and mid ring segments of the Space Shuttle Solid Rocket Booster (SRB) are examined. Dynamic structural response data is developed and an evaluation of the model in various configurations is presented. Impact velocities are determined for the SRB with the larger main chute system. Various failure modes are also investigated.

Response of selected plant and insect species to simulated solid rocket exhaust mixtures and to exhaust components from solid rocket fuels

NASA Technical Reports Server (NTRS)

Heck, W. W.; Knott, W. M.; Stahel, E. P.; Ambrose, J. T.; Mccrimmon, J. N.; Engle, M.; Romanow, L. A.; Sawyer, A. G.; Tyson, J. D.

1980-01-01

The effects of solid rocket fuel (SRF) exhaust on selected plant and and insect species in the Merritt Island, Florida area was investigated in order to determine if the exhaust clouds generated by shuttle launches would adversely affect the native, plants of the Merritt Island Wildlife Refuge, the citrus production, or the beekeeping industry of the island. Conditions were simulated in greenhouse exposure chambers and field chambers constructed to model the ideal continuous stirred tank reactor. A plant exposure system was developed for dispensing and monitoring the two major chemicals in SRF exhaust, HCl and Al203, and for dispensing and monitoring SRF exhaust (controlled fuel burns). Plants native to Merritt Island, Florida were grown and used as test species. Dose-response relationships were determined for short term exposure of selected plant species to HCl, Al203, and mixtures of the two to SRF exhaust.

Lightning tests and analyses of tunnel bond straps and shielded cables on the Space Shuttle solid rocket booster

NASA Technical Reports Server (NTRS)

Druen, William M.

1993-01-01

The purposes of the tests and analyses described in this report are as follows: (1) determine the lightning current survivability of five alternative changed designs of the bond straps which electrically bond the solid rocket booster (SRB) systems tunnel to the solid rocket motor (SRM) case; (2) determine the amount of reduction in induced voltages on operational flight (OF) tunnel cables obtained by a modified design of tunnel bond straps (both tunnel cover-to-cover and cover-to-motor case); (3) determine the contribution of coupling to the OF tunnel cables by ground electrical and instrumentation (GEI) cables which enter the systems tunnel from unshielded areas on the surfaces of the motor case; and (4) develop a model (based on test data) and calculate the voltage levels at electronic 'black boxes' connected to the OF cables that run in the systems tunnel.

KSC-2012-4455

NASA Image and Video Library

2012-08-14

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, a crane is used to load the aft skirt for a space shuttle solid rocket booster on a truck. A twin set of space shuttle solid rocket boosters and an external fuel tank are being prepared for transport to separate museums. The solid rocket boosters, or SRBs, will be displayed at the California Science Center in Los Angeles. The external tank soon will be transported for display at the Wings of Dreams Aviation Museum at Keystone Heights Airport between Gainesville and Jacksonville, Fla. The 149-foot SRBs together provided six million pounds of thrust. The external fuel tank contained over 500,000 gallons of liquid hydrogen and liquid oxygen propellant for the shuttle orbiters' three main engines. The work is part of Transition and Retirement of the space shuttle. For more information, visit http://www.nasa.gov/transition Photo credit: NASA/ Dimitri Gerondidakis

KSC-07pd1044

NASA Image and Video Library

2007-05-02

KENNEDY SPACE CENTER, FLA. -- A train carrying space shuttle reusable solid rocket motor segments from the ATK Launch Systems manufacturing site in Brigham City,Utah, to NASA’s Kennedy Space Center in Florida was derailed May 2. At the site of the train mishap involving eight NASA solid rocket booster segment cars, a handling fixture has been attached to a box car being used as a spacer between the segment cars so that it can be removed from the rails. The solid rocket booster cars can be seen behind it. The train was traveling over the Meridian & Bigbee railroad near Pennington, Ala., at the time of the mishap.. The hardware was intended for use on shuttle Discovery's STS-120 mission in October and shuttle Atlantis's STS-122 mission in December. These segments are interchangeable, and ATK Launch Systems has replacement units that could be used for the shuttle flights, if necessary.

Star 48 solid rocket motor nozzle analyses and instrumented firings

NASA Technical Reports Server (NTRS)

Porter, R. L.

1986-01-01

The analyses and testing performed by NASA in support of an expanded and improved nozzle design data base for use by the U.S. solid rocket motor industry is presented. A production nozzle with a history of one ground failure and two flight failures was selected for analyses and testing. The stress analysis was performed with the Champion computer code developed by the U.S. Navy. Several improvements were made to the code. Strain predictions were made and compared to test data. Two short duration motor firings were conducted with highly instrumented nozzles. The first nozzle had 58 thermocouples, 66 strain gages, and 8 bondline pressure measurements. The second nozzle had 59 thermocouples, 68 strain measurements, and 8 bondline pressure measurements. Most of this instrumentation was on the nonmetallic parts, and provided significantly more thermal and strain data on the nonmetallic components of a nozzle than has been accumulated in a solid rocket motor test to date.

An improved heat transfer configuration for a solid-core nuclear thermal rocket engine

NASA Technical Reports Server (NTRS)

Clark, John S.; Walton, James T.; Mcguire, Melissa L.

1992-01-01

Interrupted flow, impingement cooling, and axial power distribution are employed to enhance the heat-transfer configuration of a solid-core nuclear thermal rocket engine. Impingement cooling is introduced to increase the local heat-transfer coefficients between the reactor material and the coolants. Increased fuel loading is used at the inlet end of the reactor to enhance heat-transfer capability where the temperature differences are the greatest. A thermal-hydraulics computer program for an unfueled NERVA reactor core is employed to analyze the proposed configuration with attention given to uniform fuel loading, number of channels through the impingement wafers, fuel-element length, mass-flow rate, and wafer gap. The impingement wafer concept (IWC) is shown to have heat-transfer characteristics that are better than those of the NERVA-derived reactor at 2500 K. The IWC concept is argued to be an effective heat-transfer configuration for solid-core nuclear thermal rocket engines.

Tailoff thrust and impulse imbalance between pairs of Space Shuttle solid rocket motors

NASA Technical Reports Server (NTRS)

Jacobs, E. P.; Yeager, J. M.

1975-01-01

The tailoff thrust and impulse imbalance between pairs of solid rocket motors is of particular interest for the Space Shuttle Vehicle because of the potential control problems that exist with this asymmetric configuration. Although a similar arrangement of solid rocket motors was utilized for the Titan Program, they produced less than one-half the thrust level of the Space Shuttle at web action time, and the overall vehicle was symmetric. Since the Titan Program does provide the most applicable actual test data, 23 flight pairs were analyzed to determine the actual tailoff thrust and impulse imbalance experienced. The results were scaled up using the predicted web action time thrust and tailoff time to arrive at values for the Space Shuttle. These values were then statistically treated to obtain a prediction of the maximum imbalance one could expect to experience during the Shuttle Program.

Effects of entrained water and strong turbulence on afterburning within solid rocket motor plumes

NASA Technical Reports Server (NTRS)

Gomberg, R. I.; Wilmoth, R. G.

1978-01-01

During the first few seconds of the space shuttle trajectory, the solid rocket boosters will be in the proximity of the launch pad. Because of the launch pad structures and the surface of the earth, the turbulent mixing experienced by the exhaust gases will be greatly increased over that for the free flight situation. In addition, a system will be present, designed to protect the lifting vehicle from launch structure vibrations, which will inject quantities of liquid water into the hot plume. The effects of these two phenomena on the temperatures, chemical composition, and flow field present in the afterburning solid rocket motor exhaust plumes of the space shuttle were studied. Results are included from both a computational model of the afterburning and supporting measurements from Titan 3 exhaust plumes taken at Kennedy Space Center with infrared scanned radiometers.

Aerodynamic stability and drag characteristics of a parallel burn/SRM ascent configuration at Mach numbers from 0.6 to 4.96

NASA Technical Reports Server (NTRS)

Sims, J. F.; Hamilton, T.

1972-01-01

Experimental aerodynamic investigations were conducted in the NASA/MSFC 14-inch trisonic wind tunnel during March 1972 on a .003366 scale model of a solid rocket motor version of the space shuttle ascent configuration. The configuration consisted of a parallel burn solid rocket motor booster on an external H-O centerline tank orbiter. Six component aerodynamic force and moment date were recorded over an angle of attack range from -10 to 10 deg at zero degrees sideslip and over a sideslip range from -10 to 10 deg at 0, +6, and -6 deg angle of attack. Mach number ranged from 0.6 to 4.96. The performance and stability characteristics of the complete ascent configuration and build-up, and the effects of variations in tank diameter, orbiter incidence, fairings and positioning of the solid rocket motors and tank fins were determined.

Failure mode and effects analysis (FMEA) for the Space Shuttle solid rocket motor

NASA Technical Reports Server (NTRS)

Russell, D. L.; Blacklock, K.; Langhenry, M. T.

1988-01-01

The recertification of the Space Shuttle Solid Rocket Booster (SRB) and Solid Rocket Motor (SRM) has included an extensive rewriting of the Failure Mode and Effects Analysis (FMEA) and Critical Items List (CIL). The evolution of the groundrules and methodology used in the analysis is discussed and compared to standard FMEA techniques. Especially highlighted are aspects of the FMEA/CIL which are unique to the analysis of an SRM. The criticality category definitions are presented and the rationale for assigning criticality is presented. The various data required by the CIL and contribution of this data to the retention rationale is also presented. As an example, the FMEA and CIL for the SRM nozzle assembly is discussed in detail. This highlights some of the difficulties associated with the analysis of a system with the unique mission requirements of the Space Shuttle.

Development of Thermal Barriers for Solid Rocket Motor Nozzle Joints

NASA Technical Reports Server (NTRS)

Steinetz, Bruce M.; Dunlap, Patrick H., Jr.

1999-01-01

The Space Shuttle solid rocket motor case assembly joints are sealed using conventional 0-ring seals. The 5500+F combustion gases are kept a safe distance away from the seals by thick layers of insulation. Special joint-fill compounds are used to fill the joints in the insulation to prevent a direct flowpath to the seals. On a number of occasions. NASA has observed in several of the rocket nozzle assembly joints hot gas penetration through defects in the joint- fill compound. The current nozzle-to-case joint design incorporates primary, secondary and wiper (inner-most) 0-rings and polysulfide joint-fill compound. In the current design, 1 out of 7 motors experience hot gas to the wiper 0-ring. Though the condition does not threaten motor safety, evidence of hot gas to the wiper 0-ring results in extensive reviews before resuming flight. NASA and solid rocket motor manufacturer Thiokol are working to improve the nozzle-to-case joint design by implementing a more reliable J-leg design and a thermal barrier, This paper presents burn-resistance, temperature drop, flow and resiliency test results for several types of NASA braided carbon-fiber thermal barriers. Burn tests were performed to determine the time to burn through each of the thermal barriers when exposed to the flame of an oxy-acetylene torch (5500 F), representative of the 5500 F solid rocket motor combustion temperatures. Thermal barriers braided out of carbon fibers endured the flame for over 6 minutes, three times longer than solid rocket motor burn time. Tests were performed on two thermal barrier braid architectures, denoted Carbon-3 and Carbon-6, to measure the temperature drop across and along the barrier in a compressed state when subjected to the flame of an oxyacetylene torch. Carbon-3 and Carbon-6 thermal barriers were excellent insulators causing temperature drops through their diameter of up to a 2800 and 2560 F. respectively. Gas temperature 1/4" downstream of the thermal barrier were within the downstream Viton 0-ring temperature limit of 600 F. Carbon-6 performed extremely well in subscale rocket "char" motor tests when subjected to hot gas at 3200 F for an 11 second rocket firing, simulating the maximum downstream joint cavity fill time. The thermal barrier reduced the incoming hot gas temperature by 2200 F in an intentionally oversized gap defect, spread the incoming jet flow, and blocked hot slag, thereby offering protection to the downstream 0-rings.

KSC-2013-4455

NASA Image and Video Library

2013-12-19

VANDENBERG AIR FORCE BASE, Calif. -- A solid rocket motor is moved on a transporter to the Solid Rocket Motor Processing Facility at Vandenberg Air Force Base in California. The motor will be attached to the United Launch Alliance Delta II rocket slated to launch NASA's Orbiting Carbon Observatory-2, or OCO-2, spacecraft in July 2014. Space Launch Complex-2, where the mission will launch from, can be seen in the background. OCO-2 will collect precise global measurements of carbon dioxide in the Earth's atmosphere. Scientists will analyze this data to improve our understanding of the natural processes and human activities that regulate the abundance and distribution of this important atmospheric gas. Photo credit: NASA/Randy Beaudoin

Modeling of vortex generated sound in solid propellant rocket motors

NASA Technical Reports Server (NTRS)

Flandro, G. A.

1980-01-01

There is considerable evidence based on both full scale firings and cold flow simulations that hydrodynamically unstable shear flows in solid propellant rocket motors can lead to acoustic pressure fluctuations of significant amplitude. Although a comprehensive theoretical understanding of this problem does not yet exist, procedures were explored for generating useful analytical models describing the vortex shedding phenomenon and the mechanisms of coupling to the acoustic field in a rocket combustion chamber. Since combustion stability prediction procedures cannot be successful without incorporation of all acoustic gains and losses, it is clear that a vortex driving model comparable in quality to the analytical models currently employed to represent linear combustion instability must be formulated.

Reentry static stability characteristics of a (Model 471) .005479-scale 146-inch solid rocket booster tested in the NASA/MSFC 14 by 14 inch TWT (SA8F)

NASA Technical Reports Server (NTRS)

Johnson, J. D.; Braddock, W. F.; Praharaj, S. C.

1975-01-01

A force test of a scale model of the Space Shuttle Solid Rocket Booster was conducted in a trisonic wind tunnel. The model was tested with such protuberances as a camera capsule, electrical tunnel, attach rings, aft separation rockets, ET attachment structure, and hold-down struts. The model was also tested with the nozzle at gimbal angles of 0, 2.5, and 5 degrees. The influence of a unique heat shield configuration was also determined. Some photographs of model installations in the tunnel were taken and are included. Schlieren photography was utilized for several angles of attack.

Boron epoxy rocket motor case program

NASA Technical Reports Server (NTRS)

Stang, D. A.

1971-01-01

Three 28-inch-diameter solid rocket motor cases were fabricated using 1/8 inch wide boron/epoxy tape. The cases had unequal end closures (4-1/8-inch-diameter forward flanges and 13-inch-diameter aft flanges) and metal attachment skirts. The flanges and skirts were titanium 6Al-4V alloy. The original design for the first case was patterned after the requirements of the Applications Technology Satellite apogee kick motor. The second and third cases were designed and fabricated to approximate the requirements of a small Applications Technology Satellite apogee kick motor. The program demonstrated the feasibility of designing and fabricating large-scale filament-wound solid propellant rocket motor cases with boron/epoxy tape.

Mechanical and Combustion Performance of Multi-Walled Carbon Nanotubes as an Additive to Paraffin-Based Solid Fuels for Hybrid Rockets

NASA Technical Reports Server (NTRS)

Larson, Daniel B.; Boyer, Eric; Wachs, Trevor; Kuo, Kenneth, K.; Koo, Joseph H.; Story, George

2012-01-01

Paraffin-based solid fuels for hybrid rocket motor applications are recognized as a fastburning alternative to other fuel binders such as HTPB, but efforts to further improve the burning rate and mechanical properties of paraffin are still necessary. One approach that is considered in this study is to use multi-walled carbon nanotubes (MWNT) as an additive to paraffin wax. Carbon nanotubes provide increased electrical and thermal conductivity to the solid-fuel grains to which they are added, which can improve the mass burning rate. Furthermore, the addition of ultra-fine aluminum particles to the paraffin/MWNT fuel grains can enhance regression rate of the solid fuel and the density impulse of the hybrid rocket. The multi-walled carbon nanotubes also present the possibility of greatly improving the mechanical properties (e.g., tensile strength) of the paraffin-based solid-fuel grains. For casting these solid-fuel grains, various percentages of MWNT and aluminum particles will be added to the paraffin wax. Previous work has been published about the dispersion and mixing of carbon nanotubes.1 Another manufacturing method has been used for mixing the MWNT with a phenolic resin for ablative applications, and the manufacturing and mixing processes are well-documented in the literature.2 The cost of MWNT is a small fraction of single-walled nanotubes. This is a scale-up advantage as future applications and projects will require low cost additives to maintain cost effectiveness. Testing of the solid-fuel grains will be conducted in several steps. Dog bone samples will be cast and prepared for tensile testing. The fuel samples will also be analyzed using thermogravimetric analysis and a high-resolution scanning electron microscope (SEM). The SEM will allow for examination of the solid fuel grain for uniformity and consistency. The paraffin-based fuel grains will also be tested using two hybrid rocket test motors located at the Pennsylvania State University s High Pressure Combustion Lab.

Replacement of chemical rocket launchers by beamed energy propulsion.

PubMed

Fukunari, Masafumi; Arnault, Anthony; Yamaguchi, Toshikazu; Komurasaki, Kimiya

2014-11-01

Microwave Rocket is a beamed energy propulsion system that is expected to reach space at drastically lower cost. This cost reduction is estimated by replacing the first-stage engine and solid rocket boosters of the Japanese H-IIB rocket with Microwave Rocket, using a recently developed thrust model in which thrust is generated through repetitively pulsed microwave detonation with a reed-valve air-breathing system. Results show that Microwave Rocket trajectory, in terms of velocity versus altitude, can be designed similarly to the current H-IIB first stage trajectory. Moreover, the payload ratio can be increased by 450%, resulting in launch-cost reduction of 74%.

Flame-spreading phenomena in the fin-slot region of a solid rocket motor

NASA Astrophysics Data System (ADS)

Kuo, K. K.; Kokal, R. A.; Paulauskas, M.; Alaksin, P.; Lee, L. S.

1993-06-01

Flame-spreading processes in the fin-slot regions of solid-propellant motor grains have the potential to influence the behavior of the overall ignition transient. The work being done on this project is aimed at obtaining a better understanding of the flame-spreading processes in rocket motors with aft-end fin slots. Non-intrusive optical diagnostic methods were employed to acquire flame-spreading measurements in the fin-slot region of a subscale rocket motor. Highly non-uniform flame-spreading processes were observed in both the deep and shallow fin regions of the test rig. The average flame-spreading rates in the fin-slot region were found to be two orders of magnitude less than those in the circular port region of a typical rocket motor. The flame-spreading interval was found to correlate well with the local pressurization rates. A higher pressurization rate produces a shorter flame-spreading time interval.

KSC-07pd2167

NASA Image and Video Library

2007-08-03

KENNEDY SPACE CENTER, FLA. -- The solid rocket boosters on the Delta II 7925 rocket are revealed following the retraction of the mobile service tower, or gantry, on Launch Pad 17A at Cape Canaveral Air Force Station. Equipped with three stages and nine strap-on solid rocket motors, the Delta II rocket packs plenty of punch for sending the Phoenix spacecraft on its way toward Mars. Launch is targeted for Aug. 4 during one of two opportunities for liftoff: 5:26 or 6:02 a.m. EDT. Phoenix will land in icy soils near the north polar, permanent ice cap of Mars and explore the history of the water in these soils and any associated rocks, while monitoring polar climate. Landing on Mars is planned in May 2008 on arctic ground where a mission currently in orbit, Mars Odyssey, has detected high concentrations of ice just beneath the top layer of soil. Photo credit: NASA/Jim Grossmann

Thirteenth Workshop for Computational Fluid Dynamic Applications in Rocket Propulsion and Launch Vehicle Technology. Volume 1

NASA Technical Reports Server (NTRS)

Williams, R. W. (Compiler)

1996-01-01

The purpose of the workshop was to discuss experimental and computational fluid dynamic activities in rocket propulsion and launch vehicles. The workshop was an open meeting for government, industry, and academia. A broad number of topics were discussed including computational fluid dynamic methodology, liquid and solid rocket propulsion, turbomachinery, combustion, heat transfer, and grid generation.

A review of liquid rocket propulsion programs in Japan

NASA Technical Reports Server (NTRS)

Merkle, Charles L.

1991-01-01

An assessment of Japan's current capabilities in the areas of space and transatmospheric propulsion is presented. The primary focus is upon Japan's programs in liquid rocket propulsion and in space plane and related transatmospheric areas. Brief reference is also made to their solid rocket programs, as well as to their supersonic air breathing propulsion efforts that are just getting underway.

Applications of High-speed motion analysis system on Solid Rocket Motor (SRM)

NASA Astrophysics Data System (ADS)

Liu, Yang; He, Guo-qiang; Li, Jiang; Liu, Pei-jin; Chen, Jian

2007-01-01

High-speed motion analysis system could record images up to 12,000fps and analyzed with the image processing system. The system stored data and images directly in electronic memory convenient for managing and analyzing. The high-speed motion analysis system and the X-ray radiography system were established the high-speed real-time X-ray radiography system, which could diagnose and measure the dynamic and high-speed process in opaque. The image processing software was developed for improve quality of the original image for acquiring more precise information. The typical applications of high-speed motion analysis system on solid rocket motor (SRM) were introduced in the paper. The research of anomalous combustion of solid propellant grain with defects, real-time measurement experiment of insulator eroding, explosion incision process of motor, structure and wave character of plume during the process of ignition and flameout, measurement of end burning of solid propellant, measurement of flame front and compatibility between airplane and missile during the missile launching were carried out using high-speed motion analysis system. The significative results were achieved through the research. Aim at application of high-speed motion analysis system on solid rocket motor, the key problem, such as motor vibrancy, electrical source instability, geometry aberrance, and yawp disturbance, which damaged the image quality, was solved. The image processing software was developed which improved the capability of measuring the characteristic of image. The experimental results showed that the system was a powerful facility to study instantaneous and high-speed process in solid rocket motor. With the development of the image processing technique, the capability of high-speed motion analysis system was enhanced.

Overall Control on Solid Rocket Motor Hazard Zone: Example of VEGA an Innovative Solution at System Level

NASA Astrophysics Data System (ADS)

Vertueux, M.

2013-09-01

The arrival of additional Space launch vehicles Soyouz and Vega in Guiana Space Center facilities faced a new ground range safety major question: The technical hazards assessment and management related to the preparation of these three launchers simultaneously with the same high level of safety. The objective of this publication is to highlight the new safety solutions that are applied in CSG to reduce the risk of self-propulsion of the stages of VEGA launcher. During all the preparation campaign of VEGA launch vehicle, the explosive risk due to the use of solid propellant is permanent. Uncontrolled propulsion of a solid rocket motor is capable of destruction of other important installations with catastrophic effects. This event could cause loss of human lives and great damages to the CSG launch site structures. Early in the space program development phases of VEGA, the risk of self- propulsion of solid rocket motors and the solutions to avoid the "domino effects" on neighboring facilities have been issued as one of the major concern in term of safety.

KSC-08pd0736

NASA Image and Video Library

2008-03-12

KENNEDY SPACE CENTER, FLA. -- The Freedom Star, one of NASA's solid rocket booster retrieval ships, motors through Port Canaveral with a solid rocket booster alongside. The booster is from space shuttle Endeavour, which launched the STS-123 mission on March 11. The space shuttle’s solid rocket booster casings and associated flight hardware are recovered at sea. The boosters impact the Atlantic Ocean approximately seven minutes after liftoff. The splashdown area is a square of about 6 by 9 nautical miles located about 140 nautical miles downrange from the launch pad. The retrieval ships are stationed approximately 8 to 10 nautical miles from the impact area at the time of splashdown. As soon as the boosters enter the water, the ships accelerate to a speed of 15 knots and quickly close on the boosters, which they tow back to port. After transfer to a position alongside the ship, the booster will be towed to Hangar AF at Cape Canaveral Air Force Station. There, the expended boosters are disassembled, refurbished and reloaded with solid propellant for reuse. Photo credit: NASA/Jack Pfaller

KSC-08pd0741

NASA Image and Video Library

2008-03-12

KENNEDY SPACE CENTER, FLA. -- The Freedom Star, one of NASA's solid rocket booster retrieval ships, nears Hangar AF at Cape Canaveral Air Force Station with a solid rocket booster alongside. The booster is from space shuttle Endeavour, which launched the STS-123 mission on March 11. The space shuttle’s solid rocket booster casings and associated flight hardware are recovered at sea. The boosters impact the Atlantic Ocean approximately seven minutes after liftoff. The splashdown area is a square of about 6 by 9 nautical miles located about 140 nautical miles downrange from the launch pad. The retrieval ships are stationed approximately 8 to 10 nautical miles from the impact area at the time of splashdown. As soon as the boosters enter the water, the ships accelerate to a speed of 15 knots and quickly close on the boosters, which they tow back to port. After transfer to a position alongside the ship, the booster will be towed to Hangar AF at Cape Canaveral Air Force Station. There, the expended boosters are disassembled, refurbished and reloaded with solid propellant for reuse. Photo credit: NASA/Jack Pfaller

KSC-08pd0738

NASA Image and Video Library

2008-03-12

KENNEDY SPACE CENTER, FLA. -- The Freedom Star, one of NASA's solid rocket booster retrieval ships, crosses through the drawbridge over the Haulover Canal into the Banana River. The ship is towing a solid rocket booster alongside. The booster is from space shuttle Endeavour, which launched the STS-123 mission on March 11. The space shuttle’s solid rocket booster casings and associated flight hardware are recovered at sea. The boosters impact the Atlantic Ocean approximately seven minutes after liftoff. The splashdown area is a square of about 6 by 9 nautical miles located about 140 nautical miles downrange from the launch pad. The retrieval ships are stationed approximately 8 to 10 nautical miles from the impact area at the time of splashdown. As soon as the boosters enter the water, the ships accelerate to a speed of 15 knots and quickly close on the boosters, which they tow back to port. After transfer to a position alongside the ship, the booster will be towed to Hangar AF at Cape Canaveral Air Force Station. There, the expended boosters are disassembled, refurbished and reloaded with solid propellant for reuse. Photo credit: NASA/Jack Pfaller

KSC-08pd0740

NASA Image and Video Library

2008-03-12

KENNEDY SPACE CENTER, FLA. -- The Freedom Star, one of NASA's solid rocket booster retrieval ships, tows a solid rocket booster alongside, heading for Hangar AF at Cape Canaveral Air Force Station. The booster is from space shuttle Endeavour, which launched the STS-123 mission on March 11. The space shuttle’s solid rocket booster casings and associated flight hardware are recovered at sea. The boosters impact the Atlantic Ocean approximately seven minutes after liftoff. The splashdown area is a square of about 6 by 9 nautical miles located about 140 nautical miles downrange from the launch pad. The retrieval ships are stationed approximately 8 to 10 nautical miles from the impact area at the time of splashdown. As soon as the boosters enter the water, the ships accelerate to a speed of 15 knots and quickly close on the boosters, which they tow back to port. After transfer to a position alongside the ship, the booster will be towed to Hangar AF at Cape Canaveral Air Force Station. There, the expended boosters are disassembled, refurbished and reloaded with solid propellant for reuse. Photo credit: NASA/Jack Pfaller

KSC-08pd0737

NASA Image and Video Library

2008-03-12

KENNEDY SPACE CENTER, FLA. -- The Freedom Star, one of NASA's solid rocket booster retrieval ships, motors through Port Canaveral with a solid rocket booster alongside. The booster is from space shuttle Endeavour, which launched the STS-123 mission on March 11. The space shuttle’s solid rocket booster casings and associated flight hardware are recovered at sea. The boosters impact the Atlantic Ocean approximately seven minutes after liftoff. The splashdown area is a square of about 6 by 9 nautical miles located about 140 nautical miles downrange from the launch pad. The retrieval ships are stationed approximately 8 to 10 nautical miles from the impact area at the time of splashdown. As soon as the boosters enter the water, the ships accelerate to a speed of 15 knots and quickly close on the boosters, which they tow back to port. After transfer to a position alongside the ship, the booster will be towed to Hangar AF at Cape Canaveral Air Force Station. There, the expended boosters are disassembled, refurbished and reloaded with solid propellant for reuse. Photo credit: NASA/Jack Pfaller

Study of solid rocket motors for a space shuttle booster. Volume 2, book 1: Analysis and design

NASA Technical Reports Server (NTRS)

1972-01-01

An analysis of the factors which determined the selection of the solid rocket propellant engines for the space shuttle booster is presented. The 156 inch diameter, parallel burn engine was selected because of its transportability, cost effectiveness, and reliability. Other factors which caused favorable consideration are: (1) recovery and reuse are feasible and offer substantial cost savings, (2) abort can be easily accomplished. and (3) ecological effects are acceptable.

Proceedings of Shuttle Environmental Effects Program Review. [conferences

NASA Technical Reports Server (NTRS)

Potter, A. E. (Editor)

1980-01-01

Measurements of Titan exhaust cloud effluents are documented and compared, mesoscale and microphysical acid rain models are described, and a submesoscale model is proposed. Various instruments and facilities for measuring ice nuclei and other constituents of solid rocket motor exhaust effluents are discussed. Regional air quality monitoring and rain collection systems are described, and the ecological impact of solid rocket motor exhaust effluents is examined. The potential effect of space shuttle launches is estimated where data are adequate.

Detail view of an Aft Skirt being prepared for mating ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Detail view of an Aft Skirt being prepared for mating with sub assemblies in the Solid Rocket Booster (SRB) Assembly and Refurbishment Facility at Kennedy Space Center. This detail is showing the four Aft Booster Separation Motors. The Separation Motors burn for one second to ensure the SRBs drift away from the External Tank and Orbiter at separation. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

KSC-97PC870

NASA Image and Video Library

1997-05-30

A Titan IVB core vehicle and its twin Solid Rocket Motor Upgrades (SRMUs) depart from the Solid Rocket Motor Assembly and Readiness Facility (SMARF), Cape Canaveral Air Station (CCAS), en route to Launch Complex 40. At the pad, the Centaur upper stage will be added and, eventually, the prime payload, the Cassini spacecraft. Cassini will explore the Saturnian system, including the planet’s rings and moon, Titan. Launch of the Cassini mission to Saturn is scheduled for Oct. 6 from Pad 40, CCAS

Experimental and Numerical Characterization of Polymer Nanocomposites for Solid Rocket Motor Internal Insulation

DTIC Science & Technology

2006-09-30

Nanophase, Thermoplastic Elastomer, EPDM Rubber , Surface Modified MMT Clay, Carbon Nanofibers 16. SECURITY CLASSIFICATION OF: a. REPORT u b. ABSTRACT U...diene rubber ( EPDM ) is the baseline insulation material for solid rocket motor cases. A novel class of insulation materials was developed by the Air...Figure 1. Upon analysis of the control sample, it was observed that the EPDM rubber was totally burned forming a small amount of char, which was easily

KENNEDY SPACE CENTER, FLA. - At the Rotation, Processing and Surge Facility stand a mockup of two segments of a solid rocket booster (SRB) being used to test the feasibility of a vertical SRB propellant grain inspection, required as part of safety analysis.

NASA Image and Video Library

2003-09-11

KENNEDY SPACE CENTER, FLA. - At the Rotation, Processing and Surge Facility stand a mockup of two segments of a solid rocket booster (SRB) being used to test the feasibility of a vertical SRB propellant grain inspection, required as part of safety analysis.

Palynological Investigation of Post-Flight Solid Rocket Booster Foreign Material

NASA Technical Reports Server (NTRS)

Nelson, Linda; Jarzen, David

2008-01-01

Investigations of foreign material in a drain tube, from the Solid Rocket Booster (SRB) of a recent Space Shuttle mission, was identified as pollen. The source of the pollen is from deposits made by bees, collecting pollen from plants found at the Kennedy Space Center, Cape Canaveral, Florida. The pollen is determined to have been present in the frustum drain tubes before the shuttle flight. During the flight the pollen did not undergo thermal maturation.

Environmental Impact Statement Space Shuttle Advanced Solid Rocket Motor Program

DTIC Science & Technology

1989-03-01

Space Shuttle solid rocket boosters are currently retrieved from the Atlantic Ocean after a launch and disassembled at KSC. It is assumed that the...testing is not anticipated to impact aquatic resources. The exhaust plume will be directed over the ocean , which has a high buffering capacity and mixing...approximately 30 miles. After being slowed by parachutes, the spent motors will fall into the ocean where they will be recovered and towed to a dock at

STS-26 solid rocket booster post flight structural assessment

NASA Technical Reports Server (NTRS)

Herda, David A.; Finnegan, Charles J.

1988-01-01

A post flight assessment of the Space Shuttle's Solid Rocket Boosters was conducted at the John F. Kennedy Space Center in Florida after the launch of STS-26. The two boosters were inspected for structural damage and the results of this inspection are presented. Overall, the boosters were in good condition. However, there was some minor damage attributed to splash down. Some of this damage is a recurring problem. Explanations of these problems are provided.

KSC-07pd1206

NASA Image and Video Library

2007-05-15

KENNEDY SPACE CENTER, FLA. -- The locomotive and rail cars carrying solid rocket booster motor segments and two aft exit cone segments roll to the Rotation, Processing and Surge Facility in Kennedy Space Center's Launch Complex 39 Area. The main facility is used for solid rocket motor receiving, rotation and inspection, and supports aft booster buildup. When live solid rocket motor segments arrive at the processing facility, they are positioned under one of the cranes. Handling slings are then attached to and remove the railcar cover. The segment is inspected while it remains horizontal. The two overhead cranes hoist the segment, rotate it to a vertical position and place it on a fixed stand. The aft handling ring is then removed. The segment is hoisted again and lowered onto a transportation and storage pallet, and the forward handling ring is removed to allow inspections. It is then transported to one of the surge buildings and temporarily stored until it is needed for booster stacking in the VAB. While enroute, solid rocket motor segments were involved in a derailment in Alabama. The rail cars carrying these segments remained upright and were undamaged. An inspection determined these segment cars could continue on to Florida. The segments themselves will undergo further evaluation at Kennedy before they are cleared for flight. Other segments involved in the derailment will be returned to a plant in Utah for further evaluation. Photo credit: NASA/George Shelton

KSC-07pd1211

NASA Image and Video Library

2007-05-15

KENNEDY SPACE CENTER, FLA. -- The final rail car carrying solid rocket booster motor segments moves its cargo into the Rotation, Processing and Surge Facility (RPSF) in Kennedy Space Center's Launch Complex 39 Area. The RPSF is used for solid rocket motor receiving, rotation and inspection, and supports aft booster buildup. When live solid rocket motor segments arrive at the processing facility, they are positioned under one of the cranes. Handling slings are then attached to and remove the railcar cover. The segment is inspected while it remains horizontal. The two overhead cranes hoist the segment, rotate it to a vertical position and place it on a fixed stand. The aft handling ring is then removed. The segment is hoisted again and lowered onto a transportation and storage pallet, and the forward handling ring is removed to allow inspections. It is then transported to one of the surge buildings and temporarily stored until it is needed for booster stacking in the VAB. While enroute, solid rocket motor segments were involved in a derailment in Alabama. The rail cars carrying these segments remained upright and were undamaged. An inspection determined these segment cars could continue on to Florida. The segments themselves will undergo further evaluation at Kennedy before they are cleared for flight. Other segments involved in the derailment will be returned to a plant in Utah for further evaluation. Photo credit: NASA/George Shelton

KSC-07pd1210

NASA Image and Video Library

2007-05-15

KENNEDY SPACE CENTER, FLA. -- The locomotive and rail cars carrying solid rocket booster motor segments and two aft exit cone segments deliver their cargo to the Rotation, Processing and Surge Facility (RPSF) in Kennedy Space Center's Launch Complex 39 Area. The RPSF is used for solid rocket motor receiving, rotation and inspection, and supports aft booster buildup. When live solid rocket motor segments arrive at the processing facility, they are positioned under one of the cranes. Handling slings are then attached to and remove the railcar cover. The segment is inspected while it remains horizontal. The two overhead cranes hoist the segment, rotate it to a vertical position and place it on a fixed stand. The aft handling ring is then removed. The segment is hoisted again and lowered onto a transportation and storage pallet, and the forward handling ring is removed to allow inspections. It is then transported to one of the surge buildings and temporarily stored until it is needed for booster stacking in the VAB. While enroute, solid rocket motor segments were involved in a derailment in Alabama. The rail cars carrying these segments remained upright and were undamaged. An inspection determined these segment cars could continue on to Florida. The segments themselves will undergo further evaluation at Kennedy before they are cleared for flight. Other segments involved in the derailment will be returned to a plant in Utah for further evaluation. Photo credit: NASA/George Shelton

KSC-07pd1208

NASA Image and Video Library

2007-05-15

KENNEDY SPACE CENTER, FLA. -- The locomotive and rail cars carrying solid rocket booster motor segments and two aft exit cone segments roll past the Vehicle Assembly Building to the Rotation, Processing and Surge Facility (RPSF) in Kennedy Space Center's Launch Complex 39 Area. The RPSF is used for solid rocket motor receiving, rotation and inspection, and supports aft booster buildup. When live solid rocket motor segments arrive at the processing facility, they are positioned under one of the cranes. Handling slings are then attached to and remove the railcar cover. The segment is inspected while it remains horizontal. The two overhead cranes hoist the segment, rotate it to a vertical position and place it on a fixed stand. The aft handling ring is then removed. The segment is hoisted again and lowered onto a transportation and storage pallet, and the forward handling ring is removed to allow inspections. It is then transported to one of the surge buildings and temporarily stored until it is needed for booster stacking in the VAB. While enroute, solid rocket motor segments were involved in a derailment in Alabama. The rail cars carrying these segments remained upright and were undamaged. An inspection determined these segment cars could continue on to Florida. The segments themselves will undergo further evaluation at Kennedy before they are cleared for flight. Other segments involved in the derailment will be returned to a plant in Utah for further evaluation. Photo credit: NASA/George Shelton

KSC-2009-2144

NASA Image and Video Library

2009-03-18

CAPE CANAVERAL, Fla. – The Solid Rocket Booster Retrieval Ship Liberty Star tows a booster to the dock at Hangar AF at Cape Canaveral Air Force Station in Florida. The booster was used during space shuttle Discovery's launch from NASA's Kennedy Space Center in Florida March 15 on mission STS-119. The space shuttle’s solid rocket booster casings and associated flight hardware are recovered at sea after a launch. The spent rockets were recovered by NASA's Solid Rocket Booster Retrieval Ships Freedom Star and Liberty Star. The boosters impact the Atlantic Ocean approximately seven minutes after liftoff. The splashdown area is a square of about six by nine nautical miles located about 140 nautical miles downrange from the launch pad. The retrieval ships are stationed approximately 8 to 10 nautical miles from the impact area at the time of splashdown. As soon as the boosters enter the water, the ships accelerate to a speed of 15 knots and quickly close on the boosters. The pilot chutes and main parachutes are the first items to be brought on board. With the chutes and frustum recovered, attention turns to the boosters. The ship’s tow line is connected and the booster is returned to the Port and, after transfer to a position alongside the ship, to Hangar AF. There, the expended boosters are disassembled, refurbished and reloaded with solid propellant for reuse. Photo credit: NASA/Jack Pfaller

KSC-2009-2142

NASA Image and Video Library

2009-03-18

CAPE CANAVERAL, Fla. – At the dock at Hangar AF at Cape Canaveral Air Force Station in Florida, the solid rocket booster is lifted out of the water by the straddle crane. The booster, used during space shuttle Discovery's launch from NASA's Kennedy Space Center in Florida March 15 on mission STS-119, will be placed on a transporter. The space shuttle’s solid rocket booster casings and associated flight hardware are recovered at sea after a launch. The spent rockets were recovered by NASA's Solid Rocket Booster Retrieval Ships Freedom Star and Liberty Star. The boosters impact the Atlantic Ocean approximately seven minutes after liftoff. The splashdown area is a square of about six by nine nautical miles located about 140 nautical miles downrange from the launch pad. The retrieval ships are stationed approximately 8 to 10 nautical miles from the impact area at the time of splashdown. As soon as the boosters enter the water, the ships accelerate to a speed of 15 knots and quickly close on the boosters. The pilot chutes and main parachutes are the first items to be brought on board. With the chutes and frustum recovered, attention turns to the boosters. The ship’s tow line is connected and the booster is returned to the Port and, after transfer to a position alongside the ship, to Hangar AF. There, the expended boosters are disassembled, refurbished and reloaded with solid propellant for reuse. Photo credit: NASA/Jack Pfaller

KSC-2009-2143

NASA Image and Video Library

2009-03-18

CAPE CANAVERAL, Fla. – At the dock at Hangar AF at Cape Canaveral Air Force Station in Florida, the straddle crane lowers a solid rocket booster onto a transporter. The booster was used during space shuttle Discovery's launch from NASA's Kennedy Space Center in Florida March 15 on mission STS-119. The space shuttle’s solid rocket booster casings and associated flight hardware are recovered at sea after a launch. The spent rockets were recovered by NASA's Solid Rocket Booster Retrieval Ships Freedom Star and Liberty Star. The boosters impact the Atlantic Ocean approximately seven minutes after liftoff. The splashdown area is a square of about six by nine nautical miles located about 140 nautical miles downrange from the launch pad. The retrieval ships are stationed approximately 8 to 10 nautical miles from the impact area at the time of splashdown. As soon as the boosters enter the water, the ships accelerate to a speed of 15 knots and quickly close on the boosters. The pilot chutes and main parachutes are the first items to be brought on board. With the chutes and frustum recovered, attention turns to the boosters. The ship’s tow line is connected and the booster is returned to the Port and, after transfer to a position alongside the ship, to Hangar AF. There, the expended boosters are disassembled, refurbished and reloaded with solid propellant for reuse. Photo credit: NASA/Jack Pfaller

KSC-2009-2141

NASA Image and Video Library

2009-03-18

CAPE CANAVERAL, Fla. – The Solid Rocket Booster Retrieval Ship Liberty Star tows a booster to the dock at Hangar AF at Cape Canaveral Air Force Station in Florida. The booster was used during space shuttle Discovery's launch from NASA's Kennedy Space Center in Florida March 15 on mission STS-119. The space shuttle’s solid rocket booster casings and associated flight hardware are recovered at sea after a launch. The spent rockets were recovered by NASA's Solid Rocket Booster Retrieval Ships Freedom Star and Liberty Star. The boosters impact the Atlantic Ocean approximately seven minutes after liftoff. The splashdown area is a square of about six by nine nautical miles located about 140 nautical miles downrange from the launch pad. The retrieval ships are stationed approximately 8 to 10 nautical miles from the impact area at the time of splashdown. As soon as the boosters enter the water, the ships accelerate to a speed of 15 knots and quickly close on the boosters. The pilot chutes and main parachutes are the first items to be brought on board. With the chutes and frustum recovered, attention turns to the boosters. The ship’s tow line is connected and the booster is returned to the Port and, after transfer to a position alongside the ship, to Hangar AF. There, the expended boosters are disassembled, refurbished and reloaded with solid propellant for reuse. Photo credit: NASA/Jack Pfaller

KSC-2009-2139

NASA Image and Video Library

2009-03-18

CAPE CANAVERAL, Fla. – At the dock at Hangar AF at Cape Canaveral Air Force Station in Florida, one of the solid rocket boosters used during space shuttle Discovery's launch March 15 on mission STS-119 is moved to an area beneath the straddle crane that will lift it out of the water. The space shuttle’s solid rocket booster casings and associated flight hardware are recovered at sea after a launch. The spent rockets were recovered by NASA's Solid Rocket Booster Retrieval Ships Freedom Star and Liberty Star. The boosters impact the Atlantic Ocean approximately seven minutes after liftoff. The splashdown area is a square of about six by nine nautical miles located about 140 nautical miles downrange from the launch pad. The retrieval ships are stationed approximately 8 to 10 nautical miles from the impact area at the time of splashdown. As soon as the boosters enter the water, the ships accelerate to a speed of 15 knots and quickly close on the boosters. The pilot chutes and main parachutes are the first items to be brought on board. With the chutes and frustum recovered, attention turns to the boosters. The ship’s tow line is connected and the booster is returned to the Port and, after transfer to a position alongside the ship, to Hangar AF. There, the expended boosters are disassembled, refurbished and reloaded with solid propellant for reuse. Photo credit: NASA/Jack Pfaller

KSC-2009-2145

NASA Image and Video Library

2009-03-18

CAPE CANAVERAL, Fla. – At the dock at Hangar AF at Cape Canaveral Air Force Station in Florida, a solid rocket boosters used during space shuttle Discovery's launch from NASA's Kennedy Space Center in Florida March 15 on mission STS-119 waits in an area beneath the straddle crane that will lift it out of the water. The space shuttle’s solid rocket booster casings and associated flight hardware are recovered at sea after a launch. The spent rockets were recovered by NASA's Solid Rocket Booster Retrieval Ships Freedom Star and Liberty Star. The boosters impact the Atlantic Ocean approximately seven minutes after liftoff. The splashdown area is a square of about six by nine nautical miles located about 140 nautical miles downrange from the launch pad. The retrieval ships are stationed approximately 8 to 10 nautical miles from the impact area at the time of splashdown. As soon as the boosters enter the water, the ships accelerate to a speed of 15 knots and quickly close on the boosters. The pilot chutes and main parachutes are the first items to be brought on board. With the chutes and frustum recovered, attention turns to the boosters. The ship’s tow line is connected and the booster is returned to the Port and, after transfer to a position alongside the ship, to Hangar AF. There, the expended boosters are disassembled, refurbished and reloaded with solid propellant for reuse. Photo credit: NASA/Jack Pfaller

KSC-2009-2140

NASA Image and Video Library

2009-03-18

CAPE CANAVERAL, Fla. – At the dock at Hangar AF at Cape Canaveral Air Force Station in Florida, the frustum of a solid rocket booster is moved onto a transporter. The booster was used during space shuttle Discovery's launch on mission STS-119 from NASA's Kennedy Space Center in Florida March 15. The space shuttle’s solid rocket booster casings and associated flight hardware are recovered at sea after a launch. The spent rockets were recovered by NASA's Solid Rocket Booster Retrieval Ships Freedom Star and Liberty Star. The boosters impact the Atlantic Ocean approximately seven minutes after liftoff. The splashdown area is a square of about six by nine nautical miles located about 140 nautical miles downrange from the launch pad. The retrieval ships are stationed approximately 8 to 10 nautical miles from the impact area at the time of splashdown. As soon as the boosters enter the water, the ships accelerate to a speed of 15 knots and quickly close on the boosters. The pilot chutes and main parachutes are the first items to be brought on board. With the chutes and frustum recovered, attention turns to the boosters. The ship’s tow line is connected and the booster is returned to the Port and, after transfer to a position alongside the ship, to Hangar AF. There, the expended boosters are disassembled, refurbished and reloaded with solid propellant for reuse. Photo credit: NASA/Jack Pfaller

KSC-08pd3733

NASA Image and Video Library

2008-11-19

CAPE CANAVERAL, Fla. – At the dock at Hangar AF at Cape Canaveral Air Force Station in Florida, workers move the spent solid rocket booster to an area beneath the straddle crane that will lift it out of the water. The booster is from space shuttle Endeavour, which launched Nov. 14 on the STS-126 mission. The space shuttle’s solid rocket booster casings and associated flight hardware are recovered at sea. The spent rocket was recovered by NASA's Solid Rocket Booster Retrieval Ship Freedom Star. The boosters impact the Atlantic Ocean approximately seven minutes after liftoff. The splashdown area is a square of about six by nine nautical miles located about 140 nautical miles downrange from the launch pad. The retrieval ships are stationed approximately 8 to 10 nautical miles from the impact area at the time of splashdown. As soon as the boosters enter the water, the ships accelerate to a speed of 15 knots and quickly close on the boosters. The pilot chutes and main parachutes are the first items to be brought on board. With the chutes and frustum recovered, attention turns to the boosters. The ship’s tow line is connected and the booster is returned to the Port and, after transfer to a position alongside the ship, to Hangar AF. There, the expended boosters are disassembled, refurbished and reloaded with solid propellant for reuse. Photo credit: NASA/Kim Shiflett

KSC-08pd3732

NASA Image and Video Library

2008-11-19

CAPE CANAVERAL, Fla. – At the dock at Hangar AF at Cape Canaveral Air Force Station in Florida, the spent solid rocket booster from space shuttle Endeavour's launch Nov. 14 on mission STS-126 is moved to an area beneath the straddle crane that will lift it out of the water. The space shuttle’s solid rocket booster casings and associated flight hardware are recovered at sea. The spent rocket was recovered by NASA's Solid Rocket Booster Retrieval Ship Freedom Star. The boosters impact the Atlantic Ocean approximately seven minutes after liftoff. The splashdown area is a square of about six by nine nautical miles located about 140 nautical miles downrange from the launch pad. The retrieval ships are stationed approximately 8 to 10 nautical miles from the impact area at the time of splashdown. As soon as the boosters enter the water, the ships accelerate to a speed of 15 knots and quickly close on the boosters. The pilot chutes and main parachutes are the first items to be brought on board. With the chutes and frustum recovered, attention turns to the boosters. The ship’s tow line is connected and the booster is returned to the Port and, after transfer to a position alongside the ship, to Hangar AF. There, the expended boosters are disassembled, refurbished and reloaded with solid propellant for reuse. Photo credit: NASA/Kim Shiflett

KSC-08pd3734

NASA Image and Video Library

2008-11-19

CAPE CANAVERAL, Fla. – At the dock at Hangar AF at Cape Canaveral Air Force Station in Florida, the straddle crane lifts a spent solid rocket booster to allow saltwater contamination to be rinsed off. The booster is from space shuttle Endeavour, which launched Nov. 14 on the STS-126 mission. The space shuttle’s solid rocket booster casings and associated flight hardware are recovered at sea. The spent rocket was recovered by NASA's Solid Rocket Booster Retrieval Ship Freedom Star. The boosters impact the Atlantic Ocean approximately seven minutes after liftoff. The splashdown area is a square of about six by nine nautical miles located about 140 nautical miles downrange from the launch pad. The retrieval ships are stationed approximately 8 to 10 nautical miles from the impact area at the time of splashdown. As soon as the boosters enter the water, the ships accelerate to a speed of 15 knots and quickly close on the boosters. The pilot chutes and main parachutes are the first items to be brought on board. With the chutes and frustum recovered, attention turns to the boosters. The ship’s tow line is connected and the booster is returned to the Port and, after transfer to a position alongside the ship, to Hangar AF. There, the expended boosters are disassembled, refurbished and reloaded with solid propellant for reuse. Photo credit: NASA/Kim Shiflett

High Energy Density Additives for Hybrid Fuel Rockets to Improve Performance and Enhance Safety

NASA Technical Reports Server (NTRS)

Jaffe, Richard L.

2014-01-01

We propose a conceptual study of prototype strained hydrocarbon molecules as high energy density additives for hybrid rocket fuels to boost the performance of these rockets without compromising safety and reliability. Use of these additives could extend the range of applications for which hybrid rockets become an attractive alternative to conventional solid or liquid fuel rockets. The objectives of the study were to confirm and quantify the high enthalpy of these strained molecules and to assess improvement in rocket performance that would be expected if these additives were blended with conventional fuels. We confirmed the chemical properties (including enthalpy) of these additives. However, the predicted improvement in rocket performance was too small to make this a useful strategy for boosting hybrid rocket performance.

Thermal Barriers Developed for Solid Rocket Motor Nozzle Joints

NASA Technical Reports Server (NTRS)

Steinetz, Bruce M.; Dunlap, Patrick H., Jr.

2000-01-01

Space shuttle solid rocket motor case assembly joints are sealed with conventional O-ring seals that are shielded from 5500 F combustion gases by thick layers of insulation and by special joint-fill compounds that fill assembly splitlines in the insulation. On a number of occasions, NASA has observed hot gas penetration through defects in the joint-fill compound of several of the rocket nozzle assembly joints. In the current nozzle-to-case joint, NASA has observed penetration of hot combustion gases through the joint-fill compound to the inboard wiper O-ring in one out of seven motors. Although this condition does not threaten motor safety, evidence of hot gas penetration to the wiper O-ring results in extensive reviews before resuming flight. The solid rocket motor manufacturer (Thiokol) approached the NASA Glenn Research Center at Lewis Field about the possibility of applying Glenn's braided fiber preform seal as a thermal barrier to protect the O-ring seals. Glenn and Thiokol are working to improve the nozzle-to-case joint design by implementing a more reliable J-leg design and by using a braided carbon fiber thermal barrier that would resist any hot gases that the J-leg does not block.

Feasibility Assessment of Thermal Barrier Seals for Extreme Transient Temperatures

NASA Technical Reports Server (NTRS)

Steinetz, Bruce M.; Dunlap, Patrick H., Jr.

1998-01-01

The assembly joints of modem solid rocket motor cases are generally sealed using conventional O-ring type seals. The 5500+ F combustion gases produced by rocket motors are kept a safe distance away from the seals by thick layers of phenolic insulation. Special compounds are used to fill insulation gaps leading up to the seals to prevent a direct flowpath to them. Design criteria require that the seals should not experience torching or charring during operation, or their sealing ability would be compromised. On limited occasions, NASA has observed charring of the primary O-rings of the Space Shuttle solid rocket nozzle assembly joints due to parasitic leakage paths opening up in the gap-fill compounds during rocket operation. NASA is investigating different approaches for preventing torching or charring of the primary O-rings. One approach is to implement a braided rope seal upstream of the primary O-ring to serve as a thermal barrier that prevents the hot gases from impinging on the O-ring seals. This paper presents flow, resiliency, and thermal resistance for several types of NASA rope seals braided out of carbon fibers. Burn tests were performed to determine the time to burn through each of the seals when exposed to the flame of an oxyacetylene torch (5500 F), representative of the 5500 F solid rocket motor combustion temperatures. Rope seals braided out of carbon fibers endured the flame for over six minutes, three times longer than solid rocket motor burn time. Room and high temperature flow tests are presented for the carbon seals for different amounts of linear compression. Room temperature compression tests were performed to assess seal resiliency and unit preloads as a function of compression. The thermal barrier seal was tested in a subscale "char" motor test in which the seal sealed an intentional defect in the gap insulation. Temperature measurements indicated that the seal blocked 2500 F combustion gases on the upstream side with very little temperature rise on the downstream side.

Academician V.F. Utkin, General Designer of Space Launch Systems

NASA Astrophysics Data System (ADS)

Konyukhov, S.; Novykov, O.

2002-01-01

Academician Vladimir Fedorovich Utkin was an outstanding scientist and designer of rocket and space machinery, Doctor of Technical Science, Professor, Twice Hero of Socialist Labor, Lenin Prize and USSR State Prize winner, bearer of six Orders of Lenin and many other government awards. For 19 years, 1971 - 1990, V. F. Utkin held a position of General Designer in Yuzhnoye SDO having inherited this post from Academician Mikhail Kuzmich Yangel - Yuhnoye's founder. From 1990 till 2000 V. F. Utkin headed Central Scientific Research Institute of Machinery of Russia (TsNIIMash) as its General Designer. Under leadership of V. F. Utkin Yuzhnoye SDO designed several generations of unique strategic missile systems that laid the foundation for Rocket Strategic Forces of the Soviet Union and Russia, subsequently, developed one of the largest high-performance liquid- propellant ICBM SS-18 (Satan), solid-propellant ICBM SS-24 designed for both silo and rail- road deployment, environment friendly Zenit launch vehicle, delivered more than three hundred military, scientific and environmental satellites with tasks. A series of complicated scientific and technical problems has been resolved, a number of unique designing and technological solutions has been implemented in course of development, e.g. separating and orbital warheads, pop-up launch of heavy missiles from a container, continuous and persistent combat duty of liquid-propellant missiles, missile tolerance to nuclear explosion damage, liberation of vessels from ice captivity in the Arctic Ocean using Cosmos-1500 satellite - ancestor of the Ocean satellite constellation designed for accomplishment of seafaring tasks. The existing Russian Program for Rocket and Space Machinery development was designed under leadership of V.F. Utkin.

Progress on Ares First Stage Propulsion

NASA Technical Reports Server (NTRS)

Priskos, Alex S.; Tiller, Bruce

2008-01-01

The mission of the National Aeronautics and Space Administration (NASA) is not simply to maintain its current position with the International Space Station and other space exploration endeavors, but to build a permanent outpost on the Moon and then travel on to explore ever more distant terrains. The Constellation Program will oversee the development of the crew capsule, launch vehicles, and other systems needed to achieve this mission. From this initiative will come two new launch vehicles: the Ares I and Ares V. The Ares I will be a human-rated vehicle, which will be used for crew transport; the Ares V, a cargo transport vehicle, will be the largest launch vehicle ever built. The Ares Projects team at Marshall Space Flight Center (MSFC) in Huntsville, Alabama is assigned with developing these two new vehicles. The Ares I vehicle will have an in-line, two-stage rocket configuration. The first stage will provide the thrust or propulsion component for the Ares rocket systems through the first two minutes of the mission. The First Stage Team is tasked with developing the propulsion system necessary to liftoff from the Earth and loft the entire Ares vehicle stack toward low-Earth orbit. Building on the legacy of the Space Shuttle and other NASA space exploration initiatives, the propulsion for the Ares I First Stage will be a Shuttle-derived reusable solid rocket motor. Progress to date by the First Stage Team has been robust and on schedule. This paper provides an update on the design and development of the Ares First Stage Propulsion system.

Hybrid rocket propellants from lunar material

NASA Astrophysics Data System (ADS)

Sparks, Douglas R.

This paper examines the use of lunar material for hybrid rocket propellants. Liquid oxygen is identified as the primary oxidizer and metals such as aluminum, magnesium, calcium, titanium and silicon are compared as possible fuels. Due to the reduced transportation costs, the use of lunar materials for both oxidizer and fuel will dramatically reduce the cost of a sustained space program. The advantage of hybrid rocket systems over liquid and solid rockets is discussed. It is pointed out that this type of hybrid rocket propellant could also be obtained from asteroidal and planetary soils, thereby facilitating the exploration and industrialization of the inner solar system.

5. Credit BG. View looking northwest at eastern facade of ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

5. Credit BG. View looking northwest at eastern facade of Test Stand 'E' (Building 4259/E-60), solid rocket motor test facility. Central bay (high concrete walls) was used for testing large solid motors in a vertical position. A second smaller bay to the north fired smaller motors horizontally. Just south of the large bay is an equipment room with access to the tunnel system; entrance is by small single door on east side. The large double doors lead to a third bay used for X-raying solid rocket motors before testing. - Jet Propulsion Laboratory Edwards Facility, Test Stand E, Edwards Air Force Base, Boron, Kern County, CA

Launch Architecture Impact on Ascent Abort and Crew Survival

NASA Technical Reports Server (NTRS)

Mathias, Donovan L.; Lawrence, Scott L.

2006-01-01

A study was performed to assess the effect of booster configuration on the ascent abort process. A generic abort event sequence was created and booster related risk drivers were identified. Three model boosters were considered in light of the risk drivers: a solid rocket motor configuration, a side mount combination solid and liquid configuration, and a stacked liquid configuration. The primary risk drivers included explosive fireball, overpressure, and fragment effects and booster-crew module re-contact. Risk drivers that were not specifically booster dependent were not addressed. The solid rocket configuration had the most benign influence on an abort while the side mount architecture provided the most challenging abort environment.

Computational fluid dynamics and frequency-dependent finite-difference time-domain method coupling for the interaction between microwaves and plasma in rocket plumes

NASA Astrophysics Data System (ADS)

Kinefuchi, K.; Funaki, I.; Shimada, T.; Abe, T.

2012-10-01

Under certain conditions during rocket flights, ionized exhaust plumes from solid rocket motors may interfere with radio frequency transmissions. To understand the relevant physical processes involved in this phenomenon and establish a prediction process for in-flight attenuation levels, we attempted to measure microwave attenuation caused by rocket exhaust plumes in a sea-level static firing test for a full-scale solid propellant rocket motor. The microwave attenuation level was calculated by a coupling simulation of the inviscid-frozen-flow computational fluid dynamics of an exhaust plume and detailed analysis of microwave transmissions by applying a frequency-dependent finite-difference time-domain method with the Drude dispersion model. The calculated microwave attenuation level agreed well with the experimental results, except in the case of interference downstream the Mach disk in the exhaust plume. It was concluded that the coupling estimation method based on the physics of the frozen plasma flow with Drude dispersion would be suitable for actual flight conditions, although the mixing and afterburning in the plume should be considered depending on the flow condition.

Post-impact behavior of composite solid rocket motor cases

NASA Technical Reports Server (NTRS)

Highsmith, Alton L.

1992-01-01

In recent years, composite materials have seen increasing use in advanced structural applications because of the significant weight savings they offer when compared to more traditional engineering materials. The higher cost of composites must be offset by the increased performance that results from reduced structural weight if these new materials are to be used effectively. At present, there is considerable interest in fabricating solid rocket motor cases out of composite materials, and capitalizing on the reduced structural weight to increase rocket performance. However, one of the difficulties that arises when composite materials are used is that composites can develop significant amounts of internal damage during low velocity impacts. Such low velocity impacts may be encountered in routine handling of a structural component like a rocket motor case. The ability to assess the reduction in structural integrity of composite motor cases that experience accidental impacts is essential if composite rocket motor cases are to be certified for manned flight. The study described herein was an initial investigation of damage development and reduction of tensile strength in an idealized composite subjected to low velocity impacts.

Numerical Modelling of Staged Combustion Aft-Injected Hybrid Rocket Motors

NASA Astrophysics Data System (ADS)

Nijsse, Jeff

The staged combustion aft-injected hybrid (SCAIH) rocket motor is a promising design for the future of hybrid rocket propulsion. Advances in computational fluid dynamics and scientific computing have made computational modelling an effective tool in hybrid rocket motor design and development. The focus of this thesis is the numerical modelling of the SCAIH rocket motor in a turbulent combustion, high-speed, reactive flow framework accounting for solid soot transport and radiative heat transfer. The SCAIH motor is modelled with a shear coaxial injector with liquid oxygen injected in the center at sub-critical conditions: 150 K and 150 m/s (Mach ≈ 0.9), and a gas-generator gas-solid mixture of one-third carbon soot by mass injected in the annual opening at 1175 K and 460 m/s (Mach ≈ 0.6). Flow conditions in the near injector region and the flame anchoring mechanism are of particular interest. Overall, the flow is shown to exhibit instabilities and the flame is shown to anchor directly on the injector faceplate with temperatures in excess of 2700 K.

Monitoring Direct Effects of Delta, Atlas, and Titan Launches from Cape Canaveral Air Station

NASA Technical Reports Server (NTRS)

Schmalzer, Paul A.; Boyle, Shannon R.; Hall, Patrice; Oddy, Donna M.; Hensley, Melissa A.; Stolen, Eric D.; Duncan, Brean W.

1998-01-01

Launches of Delta, Atlas, and Titan rockets from Cape Canaveral Air Station (CCAS) have potential environmental effects that could arise from direct impacts of the launch exhaust (e.g., blast, heat), deposition of exhaust products of the solid rocket motors (hydrogen chloride, aluminum oxide), or other effects such as noise. Here we: 1) review previous reports, environmental assessments, and environmental impact statements for Delta, Atlas, and Titan vehicles and pad areas to clarity the magnitude of potential impacts; 2) summarize observed effects of 15 Delta, 22 Atlas, and 8 Titan launches; and 3) develop a spatial database of the distribution of effects from individual launches and cumulative effects of launches. The review of previous studies indicated that impacts from these launches can occur from the launch exhaust heat, deposition of exhaust products from the solid rocket motors, and noise. The principal effluents from solid rocket motors are hydrogen chloride (HCl), aluminum oxide (Al2O3), water (H2O), hydrogen (H2), carbon monoxide (CO), and carbon dioxide (CO2). The exhaust plume interacts with the launch complex structure and water deluge system to generate a launch cloud. Fall out or rain out of material from this cloud can produce localized effects from acid or particulate deposition. Delta, Atlas, and Titan launch vehicles differ in the number and size of solid rocket boosters and in the amount of deluge water used. All are smaller and use less water than the Space Shuttle. Acid deposition can cause damage to plants and animals exposed to it, acidify surface water and soil, and cause long-term changes to community composition and structure from repeated exposure. The magnitude of these effects depends on the intensity and frequency of acid deposition.

KSC-07pd1321

NASA Image and Video Library

2007-05-29

KENNEDY SPACE CENTER, FLA. -- On Launch Pad 17-B at Cape Canaveral Air Force Station, the 1st stage of the Delta II rocket awaits solid rocket booster attachment. The rocket is the launch vehicle for the Dawn spacecraft, scheduled to launch June 30. Dawn's mission is to explore two of the asteroid belt's most intriguing and dissimilar occupants: asteroid Vesta and the dwarf planet Ceres. Photo credit: NASA/Jim Grossmann

blessing ceremony for the rocket

NASA Image and Video Library

2014-02-27

The H-IIA No. 23 rocket that will carry the GPM Core Observatory into space arrived at Tanegashima Space Center on Jan. 20, 2014. The rocket has two stages, an lower first stage that, with the help of two solid rocket boosters gets them off the ground, and an upper second stage that lights up a few minutes after launch to boost the satellite the rest of the way to orbit. The launch services provider, Mitsubishi Heavy Industries (MHI), immediately began assembling the rocket. On Jan. 22, the GPM team in Tanegashima was invited to participate in a blessing ceremony for the rocket. Lynette Marbley, the Instruments Chief Safety and Mission Assurance Officer for GPM, represented the NASA team.

The Development of the Wall Momentum Erosive Burning Scaling Law and Macro Scale Erosive Burning Model

DTIC Science & Technology

2010-05-01

burn rate in excess of 2 in/sec at 1000 psi, and Mach numbers that reach 1.0 at the aft end at ignition . Typically, motors with high burning rate...37 VI I. INTRODUCTION Interior ballistics of solid propellant rocket motors continues to be an engineering discipline that is...and one open source paper published between 2005 and 2009 [2, 3, 13]. II. BACKGROUND Erosive burning is a term used in the solid rocket motor

Engineering design manual of parachute decelerator characteristics for space shuttle solid rocket booster recovery

NASA Technical Reports Server (NTRS)

Mansfield, D. L.

1973-01-01

The design criteria and characteristics of parachutes for recovery of the solid rocket boosters used with the space shuttle launch are presented. A computer program for analyzing the requirements of the parachute decelerators is described. The computer inputs for both the drogue and main parachute decelerators are; (1) parachute size, (2) deployment conditions, (3) inflation times, (4) reefing times, (5) mass properties, (6) spring properties, and (7) aerodynamic coefficients. Graphs of the parachute performance are included.

UTC LIBERTY AND FREEDOM RETURN - SOLID ROCKET BOOSTER (SRB) - PORT CANAVERAL, FL

NASA Image and Video Library

1981-04-14

S81-31319 (14 April 1981) --- One of the STS-1 solid rocket boosters (SRB) is towed back to shore after landing in the Atlantic Ocean following the jettisoning of both of Columbia?s SRB en route to her Earth-orbital mission. The UTC Freedom and Liberty (pictured) were involved in the recovery of the reusable boosters. Astronauts John W. Young, commander, and Robert L. Crippen, pilot, are orbiting Earth for approximately two and a third days aboard Columbia. Photo credit: NASA

Explicit Finite Element Techniques Used to Characterize Splashdown of the Space Shuttle Solid Rocket Booster Aft Skirt

NASA Technical Reports Server (NTRS)

Melis, Matthew E.

2003-01-01

NASA Glenn Research Center s Structural Mechanics Branch has years of expertise in using explicit finite element methods to predict the outcome of ballistic impact events. Shuttle engineers from the NASA Marshall Space Flight Center and NASA Kennedy Space Flight Center required assistance in assessing the structural loads that a newly proposed thrust vector control system for the space shuttle solid rocket booster (SRB) aft skirt would expect to see during its recovery splashdown.

KENNEDY SPACE CENTER, FLA. - On Launch Complex 17-B, Cape Canaveral Air Force Station, the first stage of a Delta II rocket is raised off the transporter before lifting and moving it into the mobile service tower. The rocket is being erected to launch the Space InfraRed Telescope Facility (SIRTF). Consisting of an 0.85-meter telescope and three cryogenically cooled science instruments, SIRTF is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

NASA Image and Video Library

2003-07-18

KENNEDY SPACE CENTER, FLA. - On Launch Complex 17-B, Cape Canaveral Air Force Station, the first stage of a Delta II rocket is raised off the transporter before lifting and moving it into the mobile service tower. The rocket is being erected to launch the Space InfraRed Telescope Facility (SIRTF). Consisting of an 0.85-meter telescope and three cryogenically cooled science instruments, SIRTF is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

KENNEDY SPACE CENTER, FLA. - On Launch Complex 17-B, Cape Canaveral Air Force Station, the first stage of a Delta II rocket is raised off the transporter before lifting it up and moved into the mobile service tower. The rocket is being erected to launch the Space InfraRed Telescope Facility (SIRTF). Consisting of an 0.85-meter telescope and three cryogenically cooled science instruments, SIRTF is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

NASA Image and Video Library

2003-07-18

KENNEDY SPACE CENTER, FLA. - On Launch Complex 17-B, Cape Canaveral Air Force Station, the first stage of a Delta II rocket is raised off the transporter before lifting it up and moved into the mobile service tower. The rocket is being erected to launch the Space InfraRed Telescope Facility (SIRTF). Consisting of an 0.85-meter telescope and three cryogenically cooled science instruments, SIRTF is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

KENNEDY SPACE CENTER, FLA. - On Launch Complex 17-B, Cape Canaveral Air Force Station, the first stage of a Delta II rocket waits to be lifted up and moved into the mobile service tower. The rocket is being erected to launch the Space InfraRed Telescope Facility (SIRTF). Consisting of an 0.85-meter telescope and three cryogenically cooled science instruments, SIRTF is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

NASA Image and Video Library

2003-07-18

KENNEDY SPACE CENTER, FLA. - On Launch Complex 17-B, Cape Canaveral Air Force Station, the first stage of a Delta II rocket waits to be lifted up and moved into the mobile service tower. The rocket is being erected to launch the Space InfraRed Telescope Facility (SIRTF). Consisting of an 0.85-meter telescope and three cryogenically cooled science instruments, SIRTF is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

KENNEDY SPACE CENTER, FLA. - On Launch Complex 17-B, Cape Canaveral Air Force Station, the first stage of a Delta II rocket is lifted up the mobile service tower. In the background is pad 17-A. The rocket is being erected to launch the Space InfraRed Telescope Facility (SIRTF). Consisting of an 0.85-meter telescope and three cryogenically cooled science instruments, SIRTF is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

NASA Image and Video Library

2003-07-18

KENNEDY SPACE CENTER, FLA. - On Launch Complex 17-B, Cape Canaveral Air Force Station, the first stage of a Delta II rocket is lifted up the mobile service tower. In the background is pad 17-A. The rocket is being erected to launch the Space InfraRed Telescope Facility (SIRTF). Consisting of an 0.85-meter telescope and three cryogenically cooled science instruments, SIRTF is one of NASA's largest infrared telescopes to be launched. SIRTF will obtain images and spectra by detecting the infrared energy, or heat, radiated by objects in space. Most of this infrared radiation is blocked by the Earth's atmosphere and cannot be observed from the ground.

Solid rocket booster performance evaluation model. Volume 1: Engineering description

NASA Technical Reports Server (NTRS)

1974-01-01

The space shuttle solid rocket booster performance evaluation model (SRB-II) is made up of analytical and functional simulation techniques linked together so that a single pass through the model will predict the performance of the propulsion elements of a space shuttle solid rocket booster. The available options allow the user to predict static test performance, predict nominal and off nominal flight performance, and reconstruct actual flight and static test performance. Options selected by the user are dependent on the data available. These can include data derived from theoretical analysis, small scale motor test data, large motor test data and motor configuration data. The user has several options for output format that include print, cards, tape and plots. Output includes all major performance parameters (Isp, thrust, flowrate, mass accounting and operating pressures) as a function of time as well as calculated single point performance data. The engineering description of SRB-II discusses the engineering and programming fundamentals used, the function of each module, and the limitations of each module.

Flexible Inhibitor Fluid-Structure Interaction Simulation in RSRM.

NASA Astrophysics Data System (ADS)

Wasistho, Bono

2005-11-01

We employ our tightly coupled fluid/structure/combustion simulation code 'Rocstar-3' for solid propellant rocket motors to study 3D flows past rigid and flexible inhibitors in the Reusable Solid Rocket Motor (RSRM). We perform high resolution simulations of a section of the rocket near the center joint slot at 100 seconds after ignition, using inflow conditions based on less detailed 3D simulations of the full RSRM. Our simulations include both inviscid and turbulent flows (using LES dynamic subgrid-scale model), and explore the interaction between the inhibitor and the resulting fluid flow. The response of the solid components is computed by an implicit finite element solver. The internal mesh motion scheme in our block-structured fluid solver enables our code to handle significant changes in geometry. We compute turbulent statistics and determine the compound instabilities originated from the natural hydrodynamic instabilities and the inhibitor motion. The ultimate goal is to studdy the effect of inhibitor flexing on the turbulent field.

The Repair and Return to Flight of Solid Rocket Booster Forward Skirt Serial Number 20022

NASA Technical Reports Server (NTRS)

Malone, T. W.; Jones, C. S.; Honeycutt, J. H., Sr.

2008-01-01

On April 5, 1991, a solid rocket booster (SRB) forward skirt serial number (S/N) 20022 sustained buckling damage during water impact after the launch of Space Transportation System Flight 37 (STS-37). As of that date, five forward skirts had been lost during water impact. Repair attempts began with the least damaged skirt available (S/N 20022). Sp ecial hydraulic tooling was used to remove buckled areas of the skirt. Afterwards, its aft clevis pinholes were found to be out of alignment with the redesigned solid rocket motor (RSRM) check gauge, but weld passes were used to correct this condition. Meanwhile, USA Analytics generated mechanical property data for buckled and subsequently debuckled material. Their analysis suggested that structural integrity might be improved by adding stringer reinforcements, stiffeners, to the aft bay section of the skirt. This improvement was recommended as a fleet modification to be implemented on a case-by-case basis.

Modified computation of the nozzle damping coefficient in solid rocket motors

NASA Astrophysics Data System (ADS)

Liu, Peijin; Wang, Muxin; Yang, Wenjing; Gupta, Vikrant; Guan, Yu; Li, Larry K. B.

2018-02-01

In solid rocket motors, the bulk advection of acoustic energy out of the nozzle constitutes a significant source of damping and can thus influence the thermoacoustic stability of the system. In this paper, we propose and test a modified version of a historically accepted method of calculating the nozzle damping coefficient. Building on previous work, we separate the nozzle from the combustor, but compute the acoustic admittance at the nozzle entry using the linearized Euler equations (LEEs) rather than with short nozzle theory. We compute the combustor's acoustic modes also with the LEEs, taking the nozzle admittance as the boundary condition at the combustor exit while accounting for the mean flow field in the combustor using an analytical solution to Taylor-Culick flow. We then compute the nozzle damping coefficient via a balance of the unsteady energy flux through the nozzle. Compared with established methods, the proposed method offers competitive accuracy at reduced computational costs, helping to improve predictions of thermoacoustic instability in solid rocket motors.

Aerodynamic stability and drag characteristics of a parallel burn/SRM ascent configuration (M equals 0.6 to 4.96)

NASA Technical Reports Server (NTRS)

Sims, F.

1972-01-01

Experimental aerodynamic investigations were conducted in the NASA/MSFC 14-inch trisonic wind tunnel during April 1972 on a 0.004-scale model of a solid rocket motor version of the space shuttle ascent configuration. The configuration consisted of a parallel burn solid rocket motor booster on an external HO centerline tank orbiter. Six component aerodynamic force and moment data were recorded over an angle of attack range from -10 deg to +10 deg at zero degrees sideslip and over a sideslip range from -10 deg to +10 deg at zero degrees angle of attack. Mach numbers ranged from 0.6 to 4.96. The purpose of the test was to determine the performance and stability characteristics of the complete ascent configuration and buildup, and to determine the effects of variations in HO tank and SRM nose shaping, orbiter incidence and position, and position of the solid rocket motors.

Preliminary 2-D shell analysis of the space shuttle solid rocket boosters

NASA Technical Reports Server (NTRS)

Knight, Norman F., Jr.; Gillian, Ronnie E.; Nemeth, Michael P.

1987-01-01

A two-dimensional shell model of an entire solid rocket booster (SRB) has been developed using the STAGSC-1 computer code and executed on the Ames CRAY computer. The purpose of these analyses is to calculate the overall deflection and stress distributions for the SRB when subjected to mechanical loads corresponding to critical times during the launch sequence. The mechanical loading conditions for the full SRB arise from the external tank (ET) attachment points, the solid rocket motor (SRM) pressure load, and the SRB hold down posts. The ET strut loads vary with time after the Space Shuttle main engine (SSME) ignition. The SRM internal pressure varies axially by approximately 100 psi. Static analyses of the full SRB are performed using a snapshot picture of the loads. The field and factory joints are modeled by using equivalent stiffness joints instead of detailed models of the joint. As such, local joint behavior cannot be obtained from this global model.

KSC-2010-4809

NASA Image and Video Library

2010-09-22

LOUISIANA -- A tug boat pulls the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122, from NASA's Michoud Assembly Facility in New Orleans toward a dock in Gulfport, La. The barge will meet up with Freedom Star, NASA's solid rocket booster retrieval ship, which will escort it to NASA's Kennedy Space Center in Florida. The tank will travel 900 miles by sea before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett

KSC-2010-4808

NASA Image and Video Library

2010-09-22

LOUISIANA -- A tug boat pulls the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122, from NASA's Michoud Assembly Facility in New Orleans toward Gulfport, La. The barge will meet up with Freedom Star, NASA's solid rocket booster retrieval ship, which will escort it to NASA's Kennedy Space Center in Florida. The tank will travel 900 miles by sea before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett

KSC-98pc1238

NASA Image and Video Library

1998-09-21

KENNEDY SPACE CENTER, FLA. -- Looking eastward, the Vehicle Assembly Building (VAB) in the Launch Complex 39 area can be seen with its new coat of paint, along with newly painted American flag and NASA logo. The improved look was finished in time to honor NASA's 40th anniversary on Oct. 1. In order to do the job, workers were suspended on platforms from the top of the 525-foot-high VAB. One of the world's largest buildings by volume, the VAB is the last stop for the Shuttle before rollout to the launch pad. Integration and stacking of the complete Space Shuttle vehicle (orbiter, two solid rocket boosters and the external tank) takes place in High Bays 1 or 3. Stretching from the side of the VAB, on the right, is the crawlerway, used to transport the Space Shuttle to the launch pad. Beyond the VAB is Banana Creek

76 FR 57103 - Office of Commercial Space Transportation (AST); Notice of Availability of the Supplemental...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-09-15

..., consisting of a two-stage Castor 120 solid-propellant rocket motor with the addition of up to six Castor IVA or Castor IVXL rocket motors strapped to the first stage. The 1995 EA analyzed the potential...

New instrumentation technologies for testing the bonding of sensors to solid materials

NASA Technical Reports Server (NTRS)

Hashemian, H. M.; Shell, C. S.; Jones, C. N.

1996-01-01

This report presents the results of a comprehensive research and development project that was conducted over a three-year period to develop new technologies for testing the attachment of sensors to solid materials for the following NASA applications: (1) testing the performance of composites that are used for the lining of solid rocket motor nozzles, (2) testing the bonding of surface-mounted platinum resistance thermometers that are used on fuel and oxidizer lines of the space shuttle to detect valve leaks by monitoring temperature, (3) testing the attachment of strain gages that are used in testing the performance of space shuttle main engines, and (4) testing the thermocouples that are used for determining the performance of blast tube liner material in solid rocket boosters.

State and prospects of solid propellant rocket development

NASA Astrophysics Data System (ADS)

Kukushkin, V. Kh.

1992-07-01

An overview is presented of aspects of solid-propellant rocket engine (SPRE) development with individual treatment given to sustainer and spacecraft SPRE technologies. The paper focuses on low-modulus fuels of composite solid propellant, requirements for adhesion stability, and enhancement of the power characteristics of solid propellants. R&D activities are described that relate to the use of SPREs with extending nozzles and to the design of ultradimensional nozzles for upper-stage engines. Other developments for the SPREs include engines with separate loading and pasty fuel applications, and progress is reported in the direction of detonation SPREs. The SPREs using pasty propellants provide good control over thrust characteristics and fuel qualities. A device is incorporated that assures fuel burning in the combustion region and reliable ignition during restarting of these engines.

Tenth Workshop for Computational Fluid Dynamic Applications in Rocket Propulsion, part 2

NASA Technical Reports Server (NTRS)

Williams, R. W. (Compiler)

1992-01-01

Presented here are 59 abstracts and presentations and three invited presentations given at the Tenth Workshop for Computational Fluid Dynamic Applications in Rocket Propulsion held at the George C. Marshall Space Flight Center, April 28-30, 1992. The purpose of the workshop is to discuss experimental and computational fluid dynamic activities in rocket propulsion. The workshop is an open meeting for government, industry, and academia. A broad number of topics are discussed, including a computational fluid dynamic methodology, liquid and solid rocket propulsion, turbomachinery, combustion, heat transfer, and grid generation.

Eleventh Workshop for Computational Fluid Dynamic Applications in Rocket Propulsion

NASA Technical Reports Server (NTRS)

Williams, R. W. (Compiler)

1993-01-01

Conference publication includes 79 abstracts and presentations and 3 invited presentations given at the Eleventh Workshop for Computational Fluid Dynamic Applications in Rocket Propulsion held at George C. Marshall Space Flight Center, April 20-22, 1993. The purpose of the workshop is to discuss experimental and computational fluid dynamic activities in rocket propulsion. The workshop is an open meeting for government, industry, and academia. A broad number of topics are discussed including computational fluid dynamic methodology, liquid and solid rocket propulsion, turbomachinery, combustion, heat transfer, and grid generation.

Eleventh Workshop for Computational Fluid Dynamic Applications in Rocket Propulsion, Part 1

NASA Technical Reports Server (NTRS)

Williams, Robert W. (Compiler)

1993-01-01

Conference publication includes 79 abstracts and presentations given at the Eleventh Workshop for Computational Fluid Dynamic Applications in Rocket Propulsion held at the George C. Marshall Space Flight Center, April 20-22, 1993. The purpose of this workshop is to discuss experimental and computational fluid dynamic activities in rocket propulsion. The workshop is an open meeting for government, industry, and academia. A broad number of topics are discussed including computational fluid dynamic methodology, liquid and solid rocket propulsion, turbomachinery, combustion, heat transfer, and grid generation.

Modeling and testing of a tube-in-tube separation mechanism of bodies in space

NASA Astrophysics Data System (ADS)

Michaels, Dan; Gany, Alon

2016-12-01

A tube-in-tube concept for separation of bodies in space was investigated theoretically and experimentally. The separation system is based on generation of high pressure gas by combustion of solid propellant and restricting the expansion of the gas only by ejecting the two bodies in opposite directions, in such a fashion that maximizes generated impulse. An interior ballistics model was developed in order to investigate the potential benefits of the separation system for a large range of space body masses and for different design parameters such as geometry and propellant. The model takes into account solid propellant combustion, heat losses, and gas phase chemical reactions. The model shows that for large bodies (above 100 kg) and typical separation velocities of 5 m/s, the proposed separation mechanism may be characterized by a specific impulse of 25,000 s, two order of magnitude larger than that of conventional solid rockets. It means that the proposed separation system requires only 1% of the propellant mass that would be needed for a conventional rocket for the same mission. Since many existing launch vehicles obtain such separation velocities by using conventional solid rocket motors (retro-rockets), the implementation of the new separation system design can reduce dramatically the mass of the separation system and increase safety. A dedicated experimental setup was built in order to demonstrate the concept and validate the model. The experimental results revealed specific impulse values of up to 27,000 s and showed good correspondence with the model.

KSC-07pd1207

NASA Image and Video Library

2007-05-15

KENNEDY SPACE CENTER, FLA. -- The locomotive and rail cars carrying solid rocket booster motor segments and two aft exit cone segments roll to the Rotation, Processing and Surge Facility (RPSF) in Kennedy Space Center's Launch Complex 39 Area. In the background, at left, is the Vehicle Assembly Building. The RPSF is used for solid rocket motor receiving, rotation and inspection, and supports aft booster buildup. When live solid rocket motor segments arrive at the processing facility, they are positioned under one of the cranes. Handling slings are then attached to and remove the railcar cover. The segment is inspected while it remains horizontal. The two overhead cranes hoist the segment, rotate it to a vertical position and place it on a fixed stand. The aft handling ring is then removed. The segment is hoisted again and lowered onto a transportation and storage pallet, and the forward handling ring is removed to allow inspections. It is then transported to one of the surge buildings and temporarily stored until it is needed for booster stacking in the VAB. While enroute, solid rocket motor segments were involved in a derailment in Alabama. The rail cars carrying these segments remained upright and were undamaged. An inspection determined these segment cars could continue on to Florida. The segments themselves will undergo further evaluation at Kennedy before they are cleared for flight. Other segments involved in the derailment will be returned to a plant in Utah for further evaluation. Photo credit: NASA/George Shelton

Generic system components of the Thiokol ultrasonic RSRM case-to-insulation bondline inspection system

NASA Technical Reports Server (NTRS)

Cook, M.

1989-01-01

Qualification testing of the Ultrasonic Redesigned Solid Rocket Motor Bondline Inspection Systems (URBIS) was conducted at the Thiokol Nondestructive Evaluation Test Facility M337A and at the Rotation Process Storage Facility at Kennedy Space Center. The test was performed on portions of the URBIS that are generic to redesigned solid rocket motor case-to-insulation bondline inspections. Testing began on Feb. 13, 1989 and was completed on May 26, 1989. The main purpose of the test was to verify that each URBIS performed to the manufacturer's specifications in the same manner and to make any procedural changes necessary for specific redesigned solid rocket motor inspections. All five URBISs passed every stage of the qualification test. Each URBIS is now qualified for use on redesigned solid rocket motors. Verifying the fact that each URBIS obtains and analyzes data in a similar fashion has eliminated concerns about variations in data between the five systems. The following recommendations were made as a result of this test: (1) each URBIS should be located within a stable environment; (2) an electronic preventative maintenance program should be established for each URBIS; (3) when the URBIS is being utilized to perform transducer analysis, the URBIS equipment setting should match the equipment setting noted on the manufacturer-supplied transducer certification sheet; and (4) optimum scan velocities for each inspection technique (clevis, capture feature, pinhole and membrane) should be determined through further testing.

Investigation of flame driving and flow turning in axial solid rocket instabilities

NASA Astrophysics Data System (ADS)

Zinn, Ben T.; Daniel, Brady R.; Matta, Lawrence M.

1993-08-01

An understanding of the processes responsible for driving and damping acoustic oscillations in solid rocket motors is necessary for developing practical design methods that eliminate or reduce the occurrence combustion instabilities. While state of the art solid rocket stability prediction methods generally account for the flow turning loss, the magnitude and characteristics of this loss have never been fully investigated. Results of an investigation of the role of the flow turning loss in the stability of solid rockets and its dependence upon motor design and operating parameters are described. A one dimensional acoustic stability equation that verifies that the flow turning loss term is appropriately included in the one dimensional stability formulation was derived for a chamber with a constant mean temperature and pressure by an approach independent from that of Culick. This study was extended providing the background and expressions needed to guide an experimental study of the flow turning loss in the presence of mean temperature and density gradients. This allows the study of combustion systems in which mean temperature gradients and heat losses are significant. The relevant conservation equations were solved numerically for the experimental configuration in order to predict the behavior of the flow turning loss and to assist in the analysis of experimental results. Experiments performed, with and without combustion, showed that the flow turning loss strongly depends upon the propellant burning rate and the location of the flow turning region relative to the standing pressure wave.

Rocket Sled Propelled Testing of a Supersonic Inflatable Aerodynamic Decelerator

NASA Technical Reports Server (NTRS)

Meacham, Michael B.; Kennett, Andrew; Townsend, Derik J.; Marti, Benjamin

2013-01-01

Decelerators (IADs) have traditionally been tested in wind tunnels. As the limitations of these test facilities are reached, other avenues must be pursued. The IAD being tested is a Supersonic IAD (SIAD), which attaches just aft of the heatshield around the perimeter of an entry body. This 'attached torus' SIAD is meant to improve the accuracy of landing for robotic class missions to Mars and allow for potentially increased payloads. The SIAD Design Verification (SDV) test aims to qualify the SIAD by applying a targeted aerodynamic load to the vehicle. While many test architectures were researched, a rocket sled track was ultimately chosen to be the most cost effective way to achieve the desired dynamic pressures. The Supersonic Naval Ordnance Research Track (SNORT) at the Naval Air Warfare Center Weapons Division (NAWCWD) China Lake is a four mile test track, traditionally used for warhead and ejection seat testing. Prior to SDV, inflatable drag bodies have been tested on this particular track. Teams at Jet Propulsion Laboratory (JPL) and NAWCWD collaborate together to design and fabricate one of the largest sleds ever built. The SDV sled is comprised of three individual sleds: a Pusher Sled which holds the solid booster rockets, an Item Sled which supports the test vehicle, and a Camera Sled that is pushed in front for in-situ footage and measurements. The JPL-designed Test Vehicle has a full-scale heatshield shape and contains all instrumentation and inflation systems necessary to inflate and test a SIAD. The first campaign that is run at SNORT tested all hardware and instrumentation before the SIAD was ready to be tested. For each of the three tests in this campaign, the number of rockets and top speed was increased and the data analyzed to ensure the hardware is safe at the necessary accelerations and aerodynamic loads.

Computational study on nitronium and nitrosonium oxalate: potential oxidizers for solid rocket propulsion?

PubMed

Gökçinar, Elif; Klapötke, Thomas M; Kramer, Michael P

2010-08-26

The enthalpies of formation for solid ionic nitrosonium oxalate, [NO](2)[O(2)C-CO(2)], nitronium oxalate, [NO(2)](2)[O(2)C-CO(2)], as well as covalent bis(nitroso)oxalic acid, ON-O(2)C-CO(2)-NO, and oxalic acid dinitrate ester, O(2)N-O(2)C-CO(2)-NO(2), were calculated using the complete basis set (CBS-4M) method of Petersson and coworkers to obtain very accurate energies. For the nitrosonium species, the ionic form ([NO](2)[O(2)C-CO(2)]) was identified as the more stable isomer, whereas for the nitrosonium compound, the covalently bound dinitrate ester (O(2)N-O(2)C-CO(2)-NO(2)) was found to be more stable. The combustion parameters with respect to possible use as ingredients in solid rocket motors for both stable species were calculated using the EXPLO5 and the ICT code. The performance of an aluminized formulation with covalently bound dinitrate ester (O(2)N-O(2)C-CO(2)-NO(2)) was shown to be comparable to that of ammonium perchlorate/aluminum. This makes oxalic acid dinitrate ester a potentially interesting perchlorate-free and environmentally benign oxidizer for solid rocket propulsion.

KSC-08pd0739

NASA Image and Video Library

2008-03-12

KENNEDY SPACE CENTER, FLA. -- The Freedom Star, one of NASA's solid rocket booster retrieval ships, tows a solid rocket booster alongside, heading for Hangar AF at Cape Canaveral Air Force Station. Barely visible in the background at right is the Vehicle Assembly Building at NASA's Kennedy Space Center. The booster is from space shuttle Endeavour, which launched the STS-123 mission on March 11. The space shuttle’s solid rocket booster casings and associated flight hardware are recovered at sea. The boosters impact the Atlantic Ocean approximately seven minutes after liftoff. The splashdown area is a square of about 6 by 9 nautical miles located about 140 nautical miles downrange from the launch pad. The retrieval ships are stationed approximately 8 to 10 nautical miles from the impact area at the time of splashdown. As soon as the boosters enter the water, the ships accelerate to a speed of 15 knots and quickly close on the boosters, which they tow back to port. After transfer to a position alongside the ship, the booster will be towed to Hangar AF at Cape Canaveral Air Force Station. There, the expended boosters are disassembled, refurbished and reloaded with solid propellant for reuse. Photo credit: NASA/Jack Pfaller

Demonstration of a sterilizable solid rocket motor system

NASA Technical Reports Server (NTRS)

Mastrolia, E. J.; Santerre, G. M.; Lambert, W. L.

1975-01-01

A solid propellant rocket motor containing 60.9 Kg (134-lb) of propellant was successfully static fired after being subjected to eight heat sterilization cycles (three 54-hour cycles plus five 40-hour cycles) at 125 C (257 F). The test motor, a modified SVM-3 chamber, incorporated a flexible grain retention system of EPR rubber to relieve thermal shrinkage stresses. The propellant used in the motor was ANB-3438, and 84 wt% solids system (18 wt% aluminum) containing 66 wt% stabilized ammonium perchlorate oxidizer and a saturated hydroxylterminated polybutadiene binder. Bonding of the propellant to the EPR insulation (GenGard V-4030) was provided by the use of SD-886, an epoxy urethane restriction.

Space shuttle system program definition. Volume 4: Cost and schedule report

NASA Technical Reports Server (NTRS)

1972-01-01

The supporting cost and schedule data for the second half of the Space Shuttle System Phase B Extension Study is summarized. The major objective for this period was to address the cost/schedule differences affecting final selection of the HO orbiter space shuttle system. The contending options under study included the following booster launch configurations: (1) series burn ballistic recoverable booster (BRB), (2) parallel burn ballistic recoverable booster (BRB), (3) series burn solid rocket motors (SRM's), and (4) parallel burn solid rocket motors (SRM's). The implications of varying payload bay sizes for the orbiter, engine type for the ballistics recoverable booster, and SRM motors for the solid booster were examined.

Flight demonstration of flight termination system and solid rocket motor ignition using semiconductor laser initiated ordnance

NASA Astrophysics Data System (ADS)

Schulze, Norman R.; Maxfield, B.; Boucher, C.

1995-01-01

Solid State Laser Initiated Ordnance (LIO) offers new technology having potential for enhanced safety, reduced costs, and improved operational efficiency. Concerns over the absence of programmatic applications of the technology, which has prevented acceptance by flight programs, should be abated since LIO has now been operationally implemented by the Laser Initiated Ordnance Sounding Rocket Demonstration (LOSRD) Program. The first launch of solid state laser diode LIO at the NASA Wallops Flight Facility (WFF) occurred on March 15, 1995 with all mission objectives accomplished. This project, Phase 3 of a series of three NASA Headquarters LIO demonstration initiatives, accomplished its objective by the flight of a dedicated, all-LIO sounding rocket mission using a two-stage Nike-Orion launch vehicle. LIO flight hardware, made by The Ensign-Bickford Company under NASA's first Cooperative Agreement with Profit Making Organizations, safely initiated three demanding pyrotechnic sequence events, namely, solid rocket motor ignition from the ground and in flight, and flight termination, i.e., as a Flight Termination System (FTS). A flight LIO system was designed, built, tested, and flown to support the objectives of quickly and inexpensively putting LIO through ground and flight operational paces. The hardware was fully qualified for this mission, including component testing as well as a full-scale system test. The launch accomplished all mission objectives in less than 11 months from proposal receipt. This paper concentrates on accomplishments of the ordnance aspects of the program and on the program's implementation and results. While this program does not generically qualify LIO for all applications, it demonstrated the safety, technical, and operational feasibility of those two most demanding applications, using an all solid state safe and arm system in critical flight applications.

Rocket engine exhaust plume diagnostics and health monitoring/management during ground testing

NASA Technical Reports Server (NTRS)

Chenevert, D. J.; Meeks, G. R.; Woods, E. G.; Huseonica, H. F.

1992-01-01

The current status of a rocket exhaust plume diagnostics program sponsored by NASA is reviewed. The near-term objective of the program is to enhance test operation efficiency and to provide for safe cutoff of rocket engines prior to incipient failure, thereby avoiding the destruction of the engine and the test complex and preventing delays in the national space program. NASA programs that will benefit from the nonintrusive remote sensed rocket plume diagnostics and related vehicle health management and nonintrusive measurement program are Space Shuttle Main Engine, National Launch System, National Aero-Space Plane, Space Exploration Initiative, Advanced Solid Rocket Motor, and Space Station Freedom. The role of emission spectrometry and other types of remote sensing in rocket plume diagnostics is discussed.

Composite Solid Propellant Predictability and Quality Assurance

NASA Technical Reports Server (NTRS)

Ramohalli, Kumar

1989-01-01

Reports are presented at the meeting at the University of Arizona on the study of predictable and reliable solid rocket motors. The following subject areas were covered: present state and trends in the research of solid propellants; the University of Arizona program in solid propellants, particularly in mixing (experimental and analytical results are presented).

KSC-03pd2211

NASA Image and Video Library

2003-07-23

KENNEDY SPACE CENTER, FLA. - An aerial view of the KSC Visitor Complex shows the Shuttle Plaza at left, with the solid rocket boosters and external tank and a model of an orbiter; the Astronaut Memorial Mirror in the center alongside the lake; and the Rocket Garden at right, center.