Dynamic stability of space vehicles. Structural dynamics model testing
Dimensional analysis, and similitude and scaling laws for structural dynamics model testing of spacecraft dynamic stability
Wissmann, J. W.↗
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Analysis of space vehicle structures using the transfer-function concept
Analysis of large complex systems is accomplished by dividing it into suitable subsystems and determining the individual dynamical and vibrational responses. Frequency transfer functions then determine the vibrational response of the whole system.
Heer, E.↗
Space shuttle structural design criteria development
NASA structural design criteria development and specific problem areas requiring more study
Vosteen, L. F.↗
Optimization of space antenna structures
Spacecraft antenna concepts, structural types, and materials
Heer, E.↗
Establishment of design criteria for acceptable failure modes and fail safe considerations for the space shuttle structural system
The application of general design approaches for preventing failures due to repeated load cycles is briefly discussed. Program objective, mission requirements, and structural design criteria are summarized. Discrete structural elements and associated sections were selected for detailed strength, fatigue, and fracture mechanics investigations.
Westrup, R. W.↗
Composite systems utilization for space shuttle structures
Research and development of composite material systems to show applicability of these materials to shuttle structures and to demonstrate availability through a hardware development program is reported. The various configurations studied and potential areas of composite structures use are described and an outline of ongoing composite programs, complementing the indicated feasible applications, including a typical cost study, is shown. The following composite systems are investigated: Boron filaments with epoxy, polyimide, or aluminum matrix, and graphite filaments with epoxy or polyimide matrix.
Engler, E. E.↗
Development of methods for fracture control of space shuttle structures
The technology with respect to fracture control requirements of the shuttle is considered. The current state-of-the-art does permit an approach based on linear elastic fracture mechanics concepts. Development and implementation of a fracture control plan should recognize deficiencies and provide adequate resources for the extensive empirical test data which are required. With respect to the cost impact of such tests, recent experiences involving advanced aircraft systems have seen unit cost increases of from 200 to 500 percent.
Smith, G. T.↗
A study of space shuttle structural integrity test and assessment. Part 2: Appendices
For abstract, see .
Anderson, R. E.↗
Design, fracture control, fabrication, and testing of pressurized space-vehicle structures
The relationship between analysis, design, fabrication, and testing of thin shells is illustrated by Saturn S-IVB, Thor, Delta, and other single-use and reusable large-size cryogenic aluminum tankage. The analyses and design to meet the design requirements are reviewed and include consideration of fracture control, general instability, and other failure modes. The effect of research and development testing on the structure is indicated. It is shown how fabrication and nondestructive and acceptance testing constrain the design. Finally, qualification testing is reviewed to illustrate the extent of testing used to develop the Saturn S-IVB.
Babel, H. W.↗
Space-time structure in high energy interactions
Explore the source record for details and available documents.
Finkelstein, D.↗
The application of thermally stable graphite composites to a space telescope structure
An optical bench and associated mirror support structural components were designed and fabricated for the HEAO-B satellite. Stringent dimensional stability criteria dictated the use of a graphite/epoxy composite as the basic structural material. Design, analysis, and fabrication aspects are discussed for the resulting structures, which pioneer the use of advanced composite materials for significant applications to orbital flight hardware.
Prunty, J.↗
Structural/thermal considerations for design of large space platform structures
A method is described for placing a large, STS-compatible platform on orbit utilizing a construction method employing both deployable and erectable structures. A multifunctional mechanism is used for deployable structures and an on-orbit assembly is used for erectable structures. Also analyses are discussed which assess the thermal distortion of a simple open truss and a more complex truss.
Barclay, D. L.↗
Control-structure interaction in a free beam
A simple energy approach to study the problem of control structure interactions in large space structures is presented. For the illustrative case of a free-free beam, the vibrational energy imparted during operation of constant, step, and pulsed thrusters is found in a nondimensional closed form. Then based on a parametric study, suggestions are made on the choice of parameters to minimize the control structure interactions. The study of this simple system provides physical insight and understanding for more complex systems.
Shrivastava, S. K.↗
The dynamics and control of large flexible space structures-IV
The effects of solar radiation pressure as the main environmental disturbance torque were incorporated into the model of the rigid orbiting shallow shell and computer simulation results indicate that within the linear range the rigid modal amplitudes are excited in proportion to the area to mass ratio. The effect of higher order terms in the gravity-gradient torque expressions previously neglected was evaluated and found to be negligible for the size structures under consideration. A graph theory approach was employed for calculating the eigenvalues of a large flexible system by reducing the system (stiffness) matrix to lower ordered submatrices. The related reachability matrix and term rank concepts are used to verify controllability and can be more effective than the alternate numerical rank tests. Control laws were developed for the shape and orientation control of the orbiting flexible shallow shell and numerical results presented.
Bainum, P. M.↗
Cost reduction in space operations - Structuring a planetary program to minimize the annual funding requirement as opposed to minimizing the program runout cost
An approach is proposed for the structuring of a planetary mission set wherein the peak annual funding is minimized to meet the annual budget restraint. One aspect of the approach is to have a transportation capability that can launch a mission in any planetary opportunity; such capability can be provided by solar electric propulsion. Another cost reduction technique is to structure a mission test in a time sequenced fashion that could utilize essentially the same spacecraft for the implementation of several missions. A third technique would be to fulfill a scientific objective in several sequential missions rather than attempt to accomplish all of the objectives with one mission. The application of the approach is illustrated by an example involving the Solar Orbiter Dual Probe mission.
Herman, D. H.↗
The dynamics and control of large flexible space structures-V
A general survey of the progress made in the areas of mathematical modelling of the system dynamics, structural analysis, development of control algorithms, and simulation of environmental disturbances is presented. The use of graph theory techniques is employed to examine the effects of inherent damping associated with LSST systems on the number and locations of the required control actuators. A mathematical model of the forces and moments induced on a flexible orbiting beam due to solar radiation pressure is developed and typical steady state open loop responses obtained for the case when rotations and vibrations are limited to occur within the orbit plane. A preliminary controls analysis based on a truncated (13 mode) finite element model of the 122m. Hoop/Column antenna indicates that a minimum of six appropriately placed actuators is required for controllability. An algorithm to evaluate the coefficients which describe coupling between the rigid rotational and flexible modes and also intramodal coupling was developed and numerical evaluation based on the finite element model of Hoop/Column system is currently in progress.
Bainum, P. M.↗
NASA/USAF research in structural dynamics
Research in the structural dynamics of large space structures is discussed. The problems of structural response are emphasized. Dynamic modeling, structural members, finite element techniques, axial loads, and vibration tests are among the topics discussed.
Pinson, L. D.↗
Mapping magnetized geologic structures from space: The effect of orbital and body parameters
When comparing previous satellite magnetometer missions (such as MAGSAT) with proposed new programs (for example, Geopotential Research Mission, GRM) it is important to quantify the difference in scientific information obtained. The ability to resolve separate magnetic blocks (simulating geological units) is used as a parameter for evaluating the expected geologic information from each mission. The effect of satellite orbital altitude on the ability to resolve two magnetic blocks with varying separations is evaluated and quantified. A systematic, nonlinear, relationship exists between resolution and distance between magnetic blocks as a function of orbital altitude. The proposed GRM would provide an order-of-magnitude greater anomaly resolution than the earlier MAGSAT mission for widely separated bodies. The resolution achieved at any particular altitude varies depending on the location of the bodies and orientation.
Schnetzler, C. C.↗