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Journal articles on the topic 'Space shuttle boosters'

Author: Grafiati

Published: 4 June 2021

Last updated: 27 July 2025

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1

Foster, Winfred A., Richard H. Sforzini, and P. H. Shu. "Flight thrust imbalance of Space Shuttle SRM boosters." Journal of Propulsion and Power 5, no. 2 (1989): 254–56. http://dx.doi.org/10.2514/3.23144.

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2

Mohammad Gharouni, S., Hamid M. Panahiha, and Jafar Eskandari Jam. "Space shuttle SRM field joint: Review paper." Metallurgical and Materials Engineering 20, no. 3 (2014): 155–64. http://dx.doi.org/10.5937/metmateng1403155g.

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Due to Challenger space shuttle accident in 1986, significant research has been done concerning structural behavior of field joints in solid rocket boosters (SRB). The structural deformations between the clevis inner leg and the tang (male-to-female parts of joint), the sealing of the O-ring to prevent the hot gas in joints, has been neglected causing the failure of the vehicle. Redesigning the field joint in SRB engine by accurate analysis of dynamic and thermal loads and by design of insulator and good O-ring, the leakiness of combustion hot gases was eliminated. Some parts of field joint su

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3

Martz, H. F., and W. J. Zimmer. "The Risk of Catastrophic Failure of the Solid Rocket Boosters on the Space Shuttle." American Statistician 46, no. 1 (1992): 42. http://dx.doi.org/10.2307/2684410.

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4

Martz, H. F., and W. J. Zimmer. "The Risk of Catastrophic Failure of the Solid Rocket Boosters on the Space Shuttle." American Statistician 46, no. 1 (1992): 42–47. http://dx.doi.org/10.1080/00031305.1992.10475846.

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5

Ramezani, Mohammad Ali, Shahram Yousefi, and Noorbakhsh Fouladi. "An experimental and numerical investigation of the effect of geometric parameters on the flexible joint nonlinear behavior for thrust vector control." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 8 (2018): 2772–82. http://dx.doi.org/10.1177/0954410018785988.

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Solid-propellant motors are used in a variety of space systems. This type of motor requires a guidance system, and a thrust vector control to function properly. One of the most effective methods for thrust vector control can be achieved by utilizing a flexible joint system. The flexible joint is the most widely used device in advanced nozzle system, such as space shuttle boosters, Vega, and Ariane 5. This setup includes multiple layers of elastomers to provide the flexibility, and a few metallic or composite rings as the scaffold of the system. In this study, a nonlinear simulation of the flex

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6

Tolasa, Diriba. "From Earth to Orbit: The Evolution of Launchers and Their Impact on Satellite Deployment." American Journal of Aerospace Engineering 10, no. 1 (2025): 11–23. https://doi.org/10.11648/j.ajae.20231001.12.

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The advancement of launch vehicles has been pivotal in shaping the landscape of space exploration and satellite deployment. This abstract examines the historical evolution of launchers, from early ballistic rockets to contemporary reusable systems, and their profound impact on the deployment and operational capabilities of satellites. The development of launch technology has paralleled the increasing complexity and functionality of satellites, enabling a diverse array of applications ranging from telecommunications and Earth observation to scientific research and interplanetary exploration. In

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7

SELTZER, RICHARD. "U.S. SPACE SHUTTLE: Booster problem delays June launch." Chemical & Engineering News 66, no. 2 (1988): 4. http://dx.doi.org/10.1021/cen-v066n002.p004.

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8

Lamb, Thomas, Alex M. Loudon, and Robert J. Van Slyke. "The Lockheed Space Shuttle Rocket Retrieval Ship." Marine Technology and SNAME News 23, no. 02 (1986): 109–22. http://dx.doi.org/10.5957/mt1.1986.23.2.109.

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This paper describes the design and construction of a 200-ft rocket retrieval ship for West Coast space shuttle operations. The ship, MV Independence, is designed to retrieve the reusable solid rocket booster casings from each launch of the space shuttle. Construction design and technical management of the project are outlined and a typical rocket retrieval mission is described. Updated information on builder's trials and mission performance is appended.

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9

Benton, Mark G. "Reusable, flyback liquid rocket booster for the Space Shuttle." Journal of Spacecraft and Rockets 26, no. 4 (1989): 252–58. http://dx.doi.org/10.2514/3.26063.

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10

Stern, S. A., and F. I. Tallentire. "Payload piggybacking aboard Shuttle solid rocket booster." Journal of Spacecraft and Rockets 22, no. 6 (1985): 668–70. http://dx.doi.org/10.2514/3.25790.

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11

Young, Richard D., Michael P. Nemeth, Timothy J. Collins, and James H. Starnes. "Nonlinear Behavior of Space Shuttle Superlightweight Tank Under Booster Ascent Loads." Journal of Spacecraft and Rockets 36, no. 6 (1999): 820–27. http://dx.doi.org/10.2514/2.3520.

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12

Barthelemy, Jean-Frangois M., Kwan J. Chang, and James L. Rogers. "Shuttle solid rocket booster bolted field joint shape optimization." Journal of Spacecraft and Rockets 25, no. 2 (1988): 117–24. http://dx.doi.org/10.2514/3.25959.

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13

Call, Vicki B., and Donald R. Mason. "Space Shuttle redesigned solid rocket booster structural dynamic liftoff predictions and correlations." Journal of Propulsion and Power 8, no. 2 (1992): 297–302. http://dx.doi.org/10.2514/3.23477.

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14

Nemeth, Michael P., and Melvin S. Anderson. "Axisymmetric shell analysis of the Space Shuttle solid rocket booster field joint." Journal of Spacecraft and Rockets 27, no. 1 (1990): 85–92. http://dx.doi.org/10.2514/3.26111.

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15

Spanos, P. D., T. T. Cao, D. A. R. Nelson, and D. A. Hamilton. "Efficient Loads Analyses of Shuttle-Payloads Using Dynamic Models With Linear Or Nonlinear Interfaces." Journal of Vibration and Acoustics 112, no. 3 (1990): 366–73. http://dx.doi.org/10.1115/1.2930517.

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A technique is presented for conducting efficient loads analyses of Shuttle-payloads systems with linear or nonlinear attachment interfaces. The technique relies on representing the Space Shuttle and the payloads with physical and modal coordinates. Further, by invoking a standard algorithm of numerical integration of equations of motion, the kinematics of the interface degrees of freedom at a given time are determined without calculating the modes of the combined system involving the Space Shuttle and the payload. If the Shuttle-payloads interface coupling induces a linear dynamic model for t

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16

Jenab, Kouroush, Josh Herrin, Saeid Moslehpour, and Sam Khoury. "System Hazard Platform: Case Study NASA Field Joint Failure." Mechanical Engineering Research 5, no. 2 (2015): 9. http://dx.doi.org/10.5539/mer.v5n2p9.

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<p class="1Body">NASA became overconfident with consecutive successful flights with no major failures leading up to Flight 25 of the Space Shuttle Challenger and failed to correctly apply quality assurance to reanalyze the possibilities of failure when extreme cold weather was present for what would become the last Challenger launch. System Hazard Analysis applied correctly to analyze the failure rate patterns of the NASA Space Shuttle Challenger Solid Rocket Booster field joints may have prevented the launch of the tragic Flight 25, where there was a total loss of aircraft and seven ast

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17

Adams, Thomas S. "Sound power level and directivity pattern determination of a space shuttle solid rocket booster." Journal of the Acoustical Society of America 85, S1 (1989): S23. http://dx.doi.org/10.1121/1.2026873.

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18

Cline, Michael C., and Richard G. Wilmoth. "Computation of the Shuttle solid booster nozzle start-up transient flow." Journal of Propulsion and Power 1, no. 5 (1985): 321–28. http://dx.doi.org/10.2514/3.22804.

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19

Mathew, Sony, Diganta Das, Michael Osterman, Michael Pecht, Robin Ferebee, and Joseph Clayton. "Virtual Remaining Life Assessment of Electronic Hardware Subjected to Shock and Random Vibration Life Cycle Loads." Journal of the IEST 50, no. 1 (2007): 86–97. http://dx.doi.org/10.17764/jiet.50.1.l5721m6160258l22.

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This study presents a physics-of-failure-based virtual remaining life assessment method for assessing the remaining life of an electronic circuit card. The approach is then demonstrated through a case study of a circuit card assembly in the Space Shuttle solid rocket booster. Using thermal and mechanical stress damage models, the accumulated damage in the circuit card due to the life cycle environment loads on the card was calculated. Based on the amount of damage accumulated, the remaining life of the circuit card was estimated.

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20

Gyekenyesi, John P. "Potential Composite Structures for NASA Future Launch Vehicles and Crew Spacecraft." Advanced Materials Research 410 (November 2011): 17. http://dx.doi.org/10.4028/www.scientific.net/amr.410.17.

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Because of their well known specific strength, stiffness and excellent durability properties, advanced composites are being considered for primary structures in launch vehicles, crew modules and various components for increased performance and cost reduction. Therefore, it is prudent and beneficial to review the engineering practices and lessons learned in connection with their use in related aeronautic and energy applications, where they are already replacing formerly used metallic materials. Examples of composite components will be shown for the reusable space shuttle orbiter where a number

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21

Meeroff, Jamie G., Derek J. Dalle, Stuart E. Rogers, Aaron C. Burkhead, Daniel G. Schauerhamer, and Joshua F. Diaz. "Advances in Space Launch System Booster Separation Computational Fluid Dynamics." Journal of Spacecraft and Rockets, February 23, 2024, 1–13. http://dx.doi.org/10.2514/1.a35807.

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The Space Launch System (SLS) employs two Space Shuttle–derived solid rocket boosters, which separate from the SLS core while still experiencing appreciable aerodynamic loads. Creating an aerodynamic database for this phase of flight can be challenging due to the large number of independent variables needed to fully constrain the problem and the complex flow induced by exhaust plumes of the booster separation motors and core main engines impinging on other parts of the vehicle. This paper details recent efforts in generating aerodynamic data used to create databases for the SLS during the boos

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22

Stappert, Sven, Ingrid Dietlein, Jascha Wilken, Leonid Bussler, and Martin Sippel. "Options for future European reusable booster stages: evaluation and comparison of VTHL and VTVL return methods." CEAS Space Journal, November 4, 2024. http://dx.doi.org/10.1007/s12567-024-00571-x.

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AbstractIn the past, the majority of system studies on reusable space transportation performed within Europe focused on concepts relying on lift-generating wings for recovery. Recently, vertically landing concepts similar to those deployed successfully by SpaceX have moved to the center of technical attention. Both recovery and landing strategies have their pros and cons and it is not obvious what would be a sound choice for Europe. Therefore, the German Aerospace Center DLR initiated a parametric system study, named ENTRAIN, that evaluates the impact of different return options on the launche

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