Reduction of control system design effort
Reliable control systems with satisfactory dynamic response for launch vehicles
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Reliable control systems with satisfactory dynamic response for launch vehicles
Launch vehicle flight control system and relation to stability requirements and dynamic responses
Dynamic responses of cylindrical shells under axisymmetric surface tractions, solving free vibration problem
Axisymmetric dynamic response of hemispherical shells under arbitrary loading formulated using elastic bending theory
F-111A and XB-70A aircraft instrumentation systems used to investigate dynamic response within air breathing propulsion systems of supersonic aircraft
Dynamic response of initially stressed inflatable thin membrane shells
Statistical analysis of influencial aspects of wind profile disturbances design and dynamic response of space vehicles
Effects of lateral cable oscillations on dynamic response of cable-connected space station
Numerical integration method for calculating dynamic response of nonlinear elastic structures
Fluid dynamic response characteristics of Explorer ionization gage data for orbital analysis
Microelectronic data and remote control function transmission system for wind tunnel testing of aircraft dynamic response to gusts and turbulence
Lunar dynamic response to discontinuities in interplanetary magnetic field to determine electrical conductivity and internal temperature
Experimental results prove the feasibility of substructure testing to measure local damping properties directly. Dynamic responses of a structure can be predicted quantitatively, and specimens are less costly and more easily tested with better controlled tests and environments.
Spherical shell dynamic response on colliding with special elastic impact surface with stress wave analysis
Structural aspects of airframe design and dynamic response of launch vehicle to wind
One of the more significant technological problems associated with the orbital operation of large astronomical telescope's is the fabrication and maintenance of the primary mirror surface to the tolerance required for diffraction-limited performance. An interesting approach to the solution of this problem involves continuously measuring and automatically correcting the optical surface of a thin deformable mirror by means of discrete actuators located on its rear surface: The realization of diffraction-limited performance from a telescope in space by this method rests on the ability of the designer to achieve extremely accurate control of a highly complex, interacting, multivariable system. This paper presents the results of a detailed study of the discrete control of linear distributed systems with specific application to the design of a practical controller for a plant representative of a telescope primary mirror for an orbiting astronomical observatory. The problem of controlling the distributed plant is treated by employing modal techniques to represent variations in the optical figure. Distortion of the mirror surface, which arises primarily from thermal gradients, is countered by actuators working against a backing structure to apply a corrective force distribution to the controlled surface. Each displacement actuator is in series with a spring attached to the mirror by means of a pad intentionally introduced to restrict the excitation of high-order modes. Control is then exerted over a finite number (equal.to the number of actuators) of the most significant modes. Through the application of the modal expansion technique the mirror equation of motion is transformed tb a set of uncoupled, linear, time-invariant, ordinary differential equations. The desired dynamic response and static accuracy may then be achieved by the application of classical single-variable design techniques. The formulation of a quadratic performance index which incorporates a measure of image quality permits determination of the trade-off between the-number of actuators and optical purity. A criterion for defining actuator placement and pad size is presented which minimizes the tendency of the controller to excite the unmonitored modes.
Dynamic response of mass-loaded and unloaded shells