TELEMETRY CHALLENGES FOR BALLISTIC MISSILE TESTING IN THE CENTRAL PACIFIC
KeywordsBallistic Missile Defense
National Missile Defense
Theater Ballistic Missile Defense
MetadataShow full item record
RightsCopyright © International Foundation for Telemetering
Collection InformationProceedings from the International Telemetering Conference are made available by the International Foundation for Telemetering and the University of Arizona Libraries. Visit http://www.telemetry.org/index.php/contact-us if you have questions about items in this collection.
AbstractThe Ballistic Missile Defense Organization (BMDO) is developing new Theater Missile Defense (TMD) and National Missile Defense (NMD) weapon systems to defend against the expanding ballistic missile threat. In the arms control arena, theater ballistic missile threats have been defined to include systems with reentry velocities up to five kilometers per second and strategic ballistic missile threats have reentry velocities that exceed five kilometers per second. The development and testing of TMD systems such as the Army Theater High Altitude Area Defense (THAAD) and the Navy Area Theater Ballistic Missile Defense (TBMD) Lower Tier, and NMD systems such as the Army Exoatmospheric Kill Vehicle and the Army Ground-Based Radar, pose exceptional challenges that stem from extreme acquisition range and high telemetry data transfer rates. Potential Central Pacific range locations include U.S. Army Kwajalien Atoll/Kwajalein Missile Range (USAKA/KMR) and the Pacific Missile Range Facility (PMRF) with target launches from Vandenberg Air Force Base, Wake Island, Aur Atoll, Johnston Island, and, possibly, an airborne platform. Safety considerations for remote target launches dictate utilization of high-data-rate, on-board instrumentation; technical performance measurement dictates transmission of focal plane array data; and operational requirements dictate intercepts at exoatmospheric altitudes and long slant ranges. The high gain, high data rate, telemetry acquisition requirements, coupled with loss of the upper S-band spectrum, may require innovative approaches to minimize electronic noise, maximize telemetry system gain, and fully utilize the limited S-band telemetry spectrum. The paper will address the emerging requirements and will explore the telemetry design trade space.
SponsorsInternational Foundation for Telemetering
Showing items related by title, author, creator and subject.
MISSILE FLIGHT SAFETY AND TELEMETRY AT WHITE SANDS MISSILE RANGENEWTON, HENRY L.; WHITE SANDS MISSILE RANGE, NM (International Foundation for Telemetering, 1991-11)Missile Flight Test Safety Managers (MFTSM) and other flight safety personnel at White Sands Missile Range (WSMR) constantly monitor the realtime space position of missile and airborne target vehicles and the telemetered missile and target vehicle performance parameters during the test flight to determine if these are about to leave Range boundaries or if erratic vehicle performance might endanger Range personnel, Range support assets or the nearby civilian population. WSMR flight safety personnel rely on the vehicle telemetry system to observe the Flight Termination System (FTS) parameters. A realtime closed loop that involves the ground command-destruct transmitter, the vehicle command-destruct receiver (CDR), other FTS components, the missile S-band telemetry transmitter, and the ground telemetry acquisition/ demultiplex system is active when the vehicle is in flight. The FTS engineer relies upon telemetry to provide read-back status of the flight termination system aboard the vehicle. WSMR flight safety personnel use the telemetry system to assess realtime airborne vehicle systems performance and advise the MFTSM. The MFTSM uses this information, in conjunction with space position information provided by an Interactive Graphics Display System (IGDS), to make realtime destruct decisions about missiles and targets in flight. This paper will aid the missile or target developer in understanding the type of vehicle performance data and FTS parameters WSMR flight safety personnel are concerned with, in realtime missile test operations.
Closed loop control of guided missiles using neural networks.Sadati, Seyed Hossein. (The University of Arizona., 1993)An optimal guidance law for a missile flight is one which determines appropriate controls to produce a flight path such that some mission objective will be achieved in the most efficient manner. Optimal Control Theory is often used to accomplish this task. One must bear in mind, however, that the usefulness of optimal control is sharply divided between two distinct classes of dynamical systems, namely, linear systems and nonlinear systems. For linear systems, the theory is complete in the sense that given a quadratic cost, a closed-loop feedback guidance law may be determined. For nonlinear systems, generally the best one can do is to determine an open-loop guidance law numerically using a software package such as MISER (1). (Some notable exceptions exist where a complete analytical synthesis of the closed-loop control may be obtained for nonlinear systems, e.g., in (2).) Although open-loop optimal guidance laws for nonlinear systems can now be computed quite efficiently with the advances of sophisticated numerical techniques along with high-speed digital computers, the highly-nonlinear and complex dynamics of missiles precludes the possibility of on-line implementation of open-loop optimal control. It has always been realized that if optimal closed-loop solutions could be obtained for comprehensive nonlinear systems such as missiles, then guidance laws based on such results would be superior to any other guidance laws available today. This superiority is due to, among other things, the elimination of some of the restrictive, and in many cases unrealistic assumptions made in the derivation of most current guidance laws in use such as, for instance, "tail-chase", unbounded control, simplified dynamics and/or aerodynamics, and non-maneuvering target, to name a few. In this study, an optimal closed-loop control law is obtained off-line by means of a Neural Network which is then used as an on-line controller for a generic missile. In the nonlinear case, the missile/target scenario is set up as a mathematical model using realistic dynamics. Then, given a Performance Index, the open-loop control is obtained by solving the problem using the optimal control software MISER for a number of different initial configurations. These open-loop solutions are then used to "teach" a neural network via backpropagation. Through simulation, it is then demonstrated how well the neural network performs as a feedback controller. The miss distance as well as the value of the Performance Index are used as measures of performance to be compared under the original open-loop control and the neural network closed-loop control. This problem is further extended to include a time lag in the missile dynamics. The effect of this time delay in the overall performance of the optimal controller is then examined.