Browse Topic: Expendable launch vehicles

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A Satellite to Detect Short Gamma-Ray Burst Emissions25AERP06_096/1/2025
Physicists at the Naval Research Laboratory are collaborating with several universities throughout the U.S. to develop a small satellite that will detect the emission of short gamma-ray bursts. U.S. Naval Research Laboratory, Washington D.C. The U.S. Naval Research Laboratory (NRL), in partnership with NASA's Marshall Space Flight Center (MSFC), has developed StarBurst, a small satellite (SmallSat) instrument for NASA's StarBurst Multimessenger Pioneer mission, which will detect the emission of short gamma-ray bursts (GRBs), a key electromagnetic (EM) signature that will contribute to the understanding of neutron star (NS) mergers. NRL transferred the instrument to NASA on March 4 for the next phase, environmental testing. From there, the instrument will be integrated onto the spacecraft bus, followed by launch into Low Earth Orbit in 2027. StarBurst will be installed as a secondary payload via the Evolved Expendable Launch Vehicle Secondary Payload Adapter Grande interface with a mission duration of one year, with the option of extension.
Rockets re-engineered-a step further into the cosmos17MEIP12_0112/1/2017
The 20th-Century nuclear arms race led to pioneering efforts in space technology, primarily driven by nations' desire to surpass one another for supremacy in spaceflight capability. Despite the largely deplorable motivations that drove the so-called “space race,” it resulted in a massive surge in aerospace engineering efforts that eventually led to the development of artificial satellites orbiting the earth, space probes that have explored the moon and other planets and the most challenging accomplishment: human spaceflight. After the first human spaceflight in 1961 by Yuri Gagarin of the USSR, and later the U.S.'s Alan Shepard, respectively the first-ever “cosmonaut” and “astronaut,” engineering efforts were dedicated mainly towards landing a man on the moon.
Vented Launch Vehicle Adapter for a Manned Spacecraft With “Pusher” Launch Abort SystemTBMG-2768610/1/2017
A Launch Vehicle Adapter (LVA) was developed that provides a structural interface between a Commercial Crew Vehicle (CCV) Crew Module/Service Module Spacecraft (CM/SM) and an expendable launch vehicle. It also provides a means to control the exhaust plume from a pusher type launch abort system integrated into the Service Module.
Glossary of Terms, Acronyms, and DefinitionsCMB7_4A (Current)10/1/2014
This Bulletin provides a comprehensive list of Terms and Definitions used in or related to TechAmerica prepared standards/documents. The information in these listings was extracted from standards and documents prepared by the Systems Engineering (G47), Configuration Management (G33), Life Cycle Logistics Supportability and Enterprise Information Management Interoperability Committees along with other pertinent international, industry and government standards. It is intended that this bulletin be used as a resource to help with harmonization of terms and definitions across standards. One should be cognizant of the release date of this Bulletin and understand that updates to the included standards and handbooks after this Bulletin was released may affect its accuracy.
G-47 Systems Engineering
The Next Generation of Systems Engineering: A Report by the GEIA G-47 Systems Engineering PanelGEIASE0001 (Current)10/1/2014
Systems Management Council
Filling the Space13AERD0603_016/3/2013
A look at the changing face of manned spaceflight and the commercialization of orbital access. Persuading politicians to fund big-scale space projects is more difficult today than ever, as witnessed by the scores of advanced spaceplane and expendable launcher projects that have fallen by the wayside over the last 30 years. But access to space is still vital as satellites keep the global economy moving and enable seamless real-time financial trading and communication at a level of reliability and accuracy that was unthinkable three decades ago, and plenty of nations still want to do it. Apart from the established major space players in the U.S., Europe, and Russia, China, Japan, and India also have ambitious national space programs.
Gardner, Richard
Low-Cost Phased Array Antenna for Sounding Rockets, Missiles, and Expendable Launch VehiclesTBMG-1509911/1/2012
A low-cost beamformer phased array antenna has been developed for expendable launch vehicles, rockets, and missiles. It utilizes a conformal array antenna of ring or individual radiators (design varies depending on application) that is designed to be fed by the recently developed hybrid electrical/ mechanical (vendor-supplied) phased array beamformer. The combination of these new array antennas and the hybrid beamformer results in a conformal phased array antenna that has significantly higher gain than traditional “omni” antennas, and costs an order of magnitude or more less than traditional phased array designs.
Applications of Probabilistic MethodsAIR5109 (Current)5/8/2012
This SAE Aerospace Information Report (AIR) addresses the following: 1 Captures previous experience and lessons learned in the application of PM. 2 Tabulates public-domain applications, and several representative examples discussed in detail. 3 Notes relative merits and barriers to implementation. The document does not contain technical details of probabilistic methods, benchmarking of specific approaches or legal aspects. These subjects are covered in other AIRs, referenced in Section 2 and prepared by the Probabilistic Methods Committee of the G-11 Reliability, Maintainability, Supportability and Logistics (RMSL) Division of SAE.
G-11 Probabilistic Methods and Uncertainty Quantification
The Future of Space PropulsionTBMG-489410/1/2008
Significant challenges and advances in space propulsion have occurred over the past ten years. The end of the Cold War had significant impacts, both positive and negative. Operational systems now have to operate well beyond their design life. Parts and technology obsolescence are having a significant impact, as are an aging workforce and limited opportunities to develop new systems. The advent of asymmetric warfare is fully upon us. The military has to pro - ject power anywhere on the globe. In addition, there is concern that U.S. space assets are vulnerable in this new world. Furthermore, changes in acquisition policy driven by incredible cost and schedule overruns on nearly every space acquisition program will have significant impacts on the future of propulsion.
Simulating Operations at a SpaceportTBMG-23879/1/2007
SPACESIM is a computer program for detailed simulation of operations at a spaceport. SPACESIM is being developed to greatly improve existing spaceports and to aid in designing, building, and operating future spaceports, given that there is a worldwide trend in spaceport operations from very expensive, research-oriented launches to more frequent commercial launches. From an operational perspective, future spaceports are expected to resemble current airports and seaports, for which it is necessary to resolve issues of safety, security, efficient movement of machinery and people, cost effectiveness, timeliness, and maximizing effectiveness in utilization of resources.
Generic Environment for Simulating Launch OperationsTBMG-17162/1/2006
GEM-FLO (A Generic Simulation Environment for Modeling Future Launch Operations) is a computer program that facilitates creation of discrete event simulation models of ground processes in which reusable or expendable launch vehicles (RLVs) are prepared for flight. GEM-FLO includes a component, developed in Visual Basic, that generates a graphical user interface (GUI) and a component, developed in the Arena simulation language, that creates a generic discrete-event simulation model. Through the GUI, GEM-FLO elicits RLV design information from the user. The design information can include information on flight hardware elements, resources, and ground processes. GEMFLO translates the user's responses into mathematical variables and expressions that populate the generic simulation model. The variables and expressions can represent processing times, resource capacities, status variables, and other process parameters needed to configure a simulation model that reflects the ground processing flow and requirements of a specific RLV. Upon execution of the model, GEM-FLO puts out data on many measures of performance, including the flight rate, turnaround time, and utilization of resources. This information can serve as the basis for determining whether design goals can be met, and for comparing characteristics of competing RLV designs.
TOP technologies for 2005AERONOV05_0311/1/2005
A look back at some of the most significant technological innovations in the news during the past year, as deemed by readers and editors. MIT researchers have developed and tested an aircraft-guidance system that allows a pilot in one plane to guide another, separate UAV by speaking commands in English. The system allows the pilot to interface with the UAV at a high level, not just “turn right, turn left” but “fly to this region and perform this task,” according to Boeing. The pilot essentially treats the UAV as a wingman.
NASA goes deepAEROJUN04_026/1/2004
The agency's new long-term space exploration program starts with a return to the moon and will ultimately enable future exploration of Mars and other solar system destinations. In early April, National Aeronautics and Space Administration (NASA) Administrator Sean O'Keefe testified before the U.S. Senate Subcommittee on Science, Technology and the Space Committee on Commerce, Science and Transportation regarding NASA's FY 2005 budget request. The occasion provided the first initial glimpse of how President Bush's vision for U.S. space exploration will be implemented by the agency. Input from members of Congress and others, as well as the findings of the Columbia Accident Investigation Board, have emphasized the importance of setting clear, long-term goals for the nation's human space flight program, with the deliberations forming the basis for the President's FY 2005 budget request for NASA, said O'Keefe. The FY 2005 NASA budget request is a little over $16.2 billion, a 5.6% increase over FY 2004, with approximately 5% growth per year over the following two years and about 1% for each of the following two years. The budget strategy supporting the vision for sustainable exploration will not require large balloon payments by future Congresses and Administrations, said O'Keefe. Unlike previous major civil space initiatives, this approach is intentionally flexible, with investments in sustainable exploration approaches to maintain affordability. After FY 2009, budgeters project that the exploration vision can be implemented within a NASA budget that keeps pace with inflation.
Jost, Kevin
NASA's Space Launch IntiativeAEROJUN03_036/1/2003
The agency's revised plan spells out roles for two programs involving Next Generation Launch Technology (NGLT) and an Orbital Space Plane (OSP) aimed at providing safe, affordable access to the International Space Station (ISS). In April NASA announced that about $135 million would be awarded to three competing contractor teams in support of NASA's ongoing OSP program under the Space Launch Initiative (SLI) to provide crew rescue and transfer capabilities to the ISS. The awards are a part of a contract modification of a Cycle 1 SLI solicitation originally awarded in May 2001 (see Table), extending existing contracts through July 2004. The three system design contractor teams-The Boeing Co. of Seal Beach, CA; Lockheed Martin Corp. of Denver; and a team of Orbital Sciences Corp. of Dulles, VA, and Northrop Grumman of El Segundo, CA-will each receive about $45 million to design potential candidates for OSP vehicles, ground operations, and supporting technologies needed to conduct missions to and from the ISS. The contract modifications include work to develop specifications, including systems analysis, trade studies, and concept feasibility, in preparation for an OSP program systems-requirements review in October.
Jost, Kevin
PREPARE for launchAEROJAN01_021/1/2001
Lockheed Martin and its suppliers are gearing up activities to launch the first Atlas V launch vehicle before the end of the year. Lockheed Martin and its suppliers have recently completed major components for the Atlas V launch vehicle, such as the Centaur upper stage. The company also has plans for future upgrades to the system, such as new fault-tolerant inertial navigation units. The Atlas V program was started to meet the needs of the U.S. Air Force for its Evolved Expendable Launch Vehicle program and the growing needs of International Launch Services for its commercial and government satellite customers worldwide. The company recently awarded Honeywell Space Systems a $52 million contract to produce fault-tolerant inertial navigation units for the Atlas V. The navigation units are the latest in an established line of high-performance guidance, navigation, and control products for launch vehicles.
Bokulich, Frank
Assembly Techniques for Space Vehicles2000-01-30289/19/2000
Assembly techniques for the majority of expendable and reusable launch vehicles have not changed much over the last thirty years. Some progress has been made, specifically on new programs, however, improvements on existing expendable launch vehicle production lines can be difficult to justify; even more so for one or two reusable vehicles. This presentation will focus on techniques and systems used for manual and automated assembly of expendable and reusable launch vehicle primary structures. Today's assembly is characterized by manual operations involving fixtures and templates, and all tasks are carried out primarily with single function hand tools. Typical assembly approaches used for metallic and composite primary structures will be discussed. Potential opportunities for process improvements utilizing advanced hand tools, mechanized and/or automated equipment will be addressed.
Sarh, Branko
Improved Covered-Louver Thermal Performance9321597/1/1993
Variable emittance vane type louvers are flight proven, lightweight assemblies for temperature control of spacecraft equipment and structures. Applications have included both exposed and covered configurations, depending upon spacecraft performance requirements. One of the most recent applications of a new covered configuration is the louver assembly flying on the Extreme Ultraviolet Explorer (EUVE), which was successfully launched on a Delta II expendable launch vehicle (ELV) from Cape Canaveral Air Force Station (CCAFS) on June 7, 1992 into a 528 kilometer circular orbit. Because EUVE was designed for on-orbit exchange of payload and bus equipment, a new louver-cover design was required which provided protection of the astronauts and louvers during on-orbit servicing in the Space Transportation System (STS). Described in this paper are features of the louver-cover design which were implemented to provide equal or better thermal control compared to that of the traditional louver-sunshield assembly. Data from thermal vacuum performance testing are included and results are compared to those for a traditional louver-sunshield assembly. The comparisons indicate better than expected performance was achieved for the new louver-cover design. The enhanced thermal performance and increased durability of the improved louver-cover design make it an ideal application for future missions where on-orbit servicing or extreme micrometeorite environments are encountered.
Krein, S., Ducas, W., Ousley, W.
An Electromechanical Actuation System for an Expendable Launch Vehicle9291128/3/1992
A major effort at the NASA Lewis Research Center in recent years has been to develop electromechanical actuators (EMA's) to replace the hydraulic systems used for thrust vector control (TVC) on launch vehicles. This is an attempt to overcome the inherent inefficiencies and costs associated with the existing hydraulic structures. General Dynamics Space Systems Division, under contract to NASA Lewis, is developing 18.6 kW (25 hp), 29.8 kW (40 hp), and 52.2 kW (70 hp) peak EMA systems to meet the power demands for TVC on a family of vehicles developed for the National Launch System. These systems utilize a pulse population modulated converter and field-oriented control scheme to obtain independent control of both the voltage and frequency. These techniques allow an induction motor to be operated at its maximum torque at all times. At NASA Lewis, we are building on this technology to develop our own in-house system capable of meeting the peak power requirements for an expendable launch vehicle (ELV) such as the Atlas. Our EMA will be capable of delivering 22.4 kW (30 hp) peak power with a nominal of 6.0 kW (8 hp). This system differs from the previous ones in two areas: 1) the use of advanced control methods, and 2) the incorporation of built-in-test. The advanced controls are essential for minimizing the controller size, while the built-in-test is necessary to enhance the system reliability and vehicle health monitoring. The ultimate goal of this program is to demonstrate an EMA which will be capable of self-test and easy integration into other projects. This paper will describe the effort underway at NASA Lewis to develop an EMA for an Atlas class ELV. An explanation will be given for each major technology block, and the status of the overall program will be reported.
Burrows, Linda M., Roth, Mary Ellen
APPROACHES TO REDUCED LAUNCH OPERATIONS COSTS9018779/1/1990
Current US expendable launch vehicles evolved from ICBMs (Thor, Atlas, Titan) which were primarily performance (payload to orbit) driven. They are expensive and, although originally highly responsive, have been modified so extensively that they now have relatively poor operability characteristics (responsiveness, flexibility, robustness, resiliency, etc.). This paper examines past/existing systems to derive lessons learned and operations drivers which need to be mitigated on new systems. It surveys requirements of several new/proposed systems and suggests approaches for low cost operations for these and any other new systems. Strategies include trading weight for dollars, system simplification, selective automation, modernization (hardware and software, ground and vehicle system), and application of (military) aircraft operations and design concepts. The paper concludes that operability in launch systems is achievable. It requires 1) attention to design early in development, with follow through of some up front dollars, 2) modest technology development, and 3) a new mind set in performing launch operations.
Hopkins, Jerry L.
ALS Turbomachinery Technology9018829/1/1990
Advanced Development Programs are being pursued by Rocketdyne, Aerojet, and Pratt & Whitney to define and validate design approaches toward producing low-cost, reliable liquid-hydrogen and liquid-oxygen turbopumps for a 2580 kN (580 klb) thrust Advanced Launch System. The generic approach, which is evolving after 18 months of trade studies and conceptual and preliminary design efforts, is explained. In addition, the preliminary liquid-hydrogen turbopump designs produced in parallel tasks by Rocketdyne and Aerojet and the liquid-oxygen turbopump design produced by Pratt & Whitney are described, and technology features and issues are discussed.
Csomor, A., Faulkner, C., Ferlita, F.
Design and Development of Composite Fairing Structures for Space Launch Vehicles9018369/1/1990
Current space transportation systems such as expendable launch vehicles (ELVs) and the reusable Space Transportation System (space shuttle) are very expensive. In some instances they are based on 10 to 20 year old technologies. Newer, lower cost technologies must be applied to designing and manufacturing the next generation of vehicles. Competing effectively in the launch vehicle industry requires an order-of-magnitude reduction in the cost per pound of payloads delivered to orbit. Payload fairings are critical structural elements in all ELV systems. In addition to carrying and transmitting vehicle loads, they also protect payloads from severe launch and in-flight environments. Developing improved fairing hardware and the associated structural, thermal, acoustic, and separation subsystems is a major undertaking. It requires extensive design, analysis, testing, and systems integration activity. To maintain a competitive posture in the launch service industry, three years ago McDonnell Douglas Space System Company (MDSSC) initiated a research and development program on composite fairings. The program investigated and refined design and analysis, process techniques, and fabrication methods for large diameter composite fairings (1,2).* Substantial progress was achieved in composite fairing material selection, design and analysis, and manufacturing methods characterization. Eight composite fairing configurations with different constructions, and five aerodynamic forebody shapes with improved performance characteristics, were evaluated and studied. A final fairing configuration was selected for further study and the fabrication of a demonstration/test article is underway. This paper presents the composite fairing structural alternatives investigated and summarizes the results of the major trade studies undertaken.
Shen, Frank, Pope, Dennis
Alternate Transportation System88149610/1/1988
The need for gaining alternate access into space can undoubtedly enhance the Space Shuttle System to produce a strong and well balanced U.S. space program. Balance, because the use of Expendable Launch Vehicles (ELVs) with the Space Shuttle program provide reliability and flexibility in providing an alternate manned access into space. This paper focuses on an Alternate Transportation System (ATS) study conducted by NASA and more specifically the technical feasibility for providing alternate manned access into space. This is accomplished by using combinations of booster vehicles, crew modules and service modules to achieve manned access into space should the Space Shuttle be unavailable to support the Space Station. The Space Shuttle manifest could also be relieved for those dedicated Space Shuttle missions which support the Space Station directly. The three missions identified for the Alternate Transportation System (ATS) are (1) manned launch, specifically for rotating Space Station crewmembers every 90 days, (2) launch of a logistics module which will re-supply the Space Station every 180 days, and (3) launch of both crew and logistics to the Space Station. The Titan IV/NUS and Shuttle-C are discussed as booster candidates as are the Apollo and a glider assessed as crew modules. The flight elements and their associated mission profiles are defined to help visualize the configurations and understand the operational complexities. A vehicle performance assessment summarizes the different capabilities, and the results of the ATS are discussed in closing. Before entering into discussion about the ATS study, a parallel is drawn for the sake of emphasizing the need for alternate manned access into space.
Zertuche, Tony, McKinnie, James
Shuttle and ELV Flight Planning Using the Flight Design System87190810/1/1987
THE FLIGHT DESIGN SYSTEM (FDS) is an interactive software simulation tool used by the National Aeronautics and Space Administration (NASA), the Department of Defense (DOD), and aerospace contractors for a wide range of spacecraft conceptual mission planning and realtime mission support, in the past, the FDS has been used exclusively for the Space Shuttle, but the software flexibility allows the system to also be used for expendable launch vehicles (ELVs). The FDS consists of approximately 100 high-fidelity computer programs called “processors” which can be organized in any desired sequence to simulate a complete spacecraft mission from ascent to final orbit. Examples of simulation capabilities are booster ascent, trajectory propagation, on-orbit impulsive or finite burns, precision attitude and pointing, relative motion, rendezvous, and launch window analysis. FDS also has excellent graphical support processors for generating ancillary products such as groundtracks, celestial maps, instrument camera views, and timelines.
Friedlander, Melvin M., Hare, James A.
AMROC Industrial Launch Vehicle: A Low Cost Launch Vehicle8713367/1/1987
American Rocket Company is engaged in design and development of an expendable launch vehicle to be used for placing moderate size payloads in low Earth orbit. The primary drivers in the design are reliability and low cost. High production rates of relatively few components, maximum use of existing designs and avoiding the normal drive for maximum performance are among the concepts used in attempting this task.
French, J. R.
Commercial US Transfer Vehicle Overview86176410/1/1986
With the introduction of the Payload Assist Module (PAM) the McDonnell Douglas Astronautics Company pioneered the development of the first commercial US orbital transfer vehicle. The PAM program was initiated in 1976 to provide spacecraft developers with an orderly transition from the Delta expendable launch vehicle to the space shuttle. With the PAM system, medium-sized payloads designed to be placed in orbit from the Delta vehicle could, without any redesign, be launched from the space shuttle when it became operational. During the late 1970s and early 1980s, an evolutionary increase in the weight of spacecraft to be launched and the introduction of the operational space shuttle system produced a need for new, economical transfer vehicle systems. To meet this need, and also take advantage of the larger payload volume available in the shuttle orbiter, several companies initiated the commercial development of additional upper-stage systems. This paper provides an overview of upper-stage systems that are currently operational, under development, or in the planning stages. Each system is described, performance comparisons are made, the operational status is identified, and a discussion of what might be anticipated for commercial transfer vehicles in the early 1990s is provided.
Winchell, J. W., Huss, R. L.
The Space Transportation System Mixed Fleet Economics8213702/1/1982
A conservative projection of future space missions indicates that in 1985 the United States will place at least 55 payloads in orbit, and that subsequent growth in launch support needs will increase at 8 percent or more per year. As our dependence on space systems grows, so will the launch support system performance requirements grow in throw-weight capability, frequency of launch, and mission success probability. The newly developed, recoverable space transportation system (STS) has demonstrated its feasibility and reusability. STS marks the next generation of space mission support capability with greater launch performance, manned on-orbit support capability, and increased mission success probability. From an economic standpoint, the cost to place comparable weight payloads in orbit is shown to be less when using the STS as compared to currently operational expendable launch vehicles (ELV's). A national commitment has been made to fully utilize the STS capabilities to support the expanding national space mission requirements. This commitment to STS will result in substantial mission support savings for all users.
Beilock, Milton M.
NEAR-TERM LOW-COST EXPENDABLE BOOSTERS6907162/1/1969
Although currently available booster technology could allow a major decrease in space-booster costs, hardware already built in the Saturn system has precluded any development efforts in this direction. However, as such hardware is programmed for launches during the next several years, decisions concerning such low-cost approaches become more imminent. This paper reviews the available alternatives and describes the characteristics and capabilities of a low-cost booster system which is both desirable and practically feasible for missions beginning as early as 1973. Space program plans project needs for (1) Space-Station deployment, (2) Space-Station logistics supply, (3) unmanned scientific planetary probes, (4) further lunar exploration, and (5) large synchronous-orbit satellite deployment. These missions are interrelated in the paper with regard to booster and spacecraft capabilities. It is shown that a low-cost booster based largely on current expendable booster technology can meet these interrelated requirements. In the low-cost expendable rocket technology area, three booster approaches are feasible: (1) 260-in. diam solid rockets, (2) pressure-fed liquid rockets, and (3) 156-in. diam solid rockets. This document reviews the status of these and their relative amenability to the projected requirements.
SIEGFRIED, W. H., GOLDIN, R. W.
Effect on Structures of Rapidly Changing Environmental Conditions - Launch to Orbit to Entry6606802/1/1966
ABSTRACT The influence of the integrated, rapidly changing environmental conditions, from launch through orbit to entry and recovery, on the structure and thermal protection systems of advanced space vehicle systems is defined. Two vehicle systems are considered: a space exploration system employing a vertical takeoff expendable launch vehicle, ballistic entry vehicle, and vertical landing; and an orbital operations system employing reusable stages with horizontal takeoff and landing capability. Data are presented on the mission requirements, design criteria, structural characteristics, and pacing technology problems for each system.
Bernstein, Allen I., Price, Melvin A.
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