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Taylor, J. & Collins, D.J. 2009. New records of the shrimp genus Lissosabinea (Caridea: Crangonidae) from Australia including descriptions of three new species and a key to world species. Memoirs of Museum Victoria 66: 175–187. Five species of Lissosabinea (Crustacea: Caridea: Crangonidae) are reported from Australia: three species are new to science, L. arthuri sp. nov. from 260–265 metres off Victoria, L. beresfordi. sp. nov. from 370–410 metres off Tasmania and L. lynseyae sp. nov. from 414–421 metres off Western Australia. Two species are new records for Australian waters, L. ecarina Komai, 2006 from 110 metres and L. indica (De Man, 1918) from 110–451 metres off the continental shelf of north-western Western Australia. These records expand the number of Lissosabinea species previously recorded world wide from fi ve to eight. A revised key and illustrated guide to the world species is provided.

Utilization of neural network techniques to recognize and classify acoustic signals has long been pursued and shows great promise as a robust application of neural network technology. Traditional techniques have proven effective but in some cases are quite computationally intensive, as the sampling rates necessary to capture the transient result in large input vectors and thus large neural networks. This thesis presents an alternative transient classification scheme which considerably reduces neural network size and thus computation time. Parameterization of the acoustic transient to a set of distinct characteristics (e.g. frequency, power spectral density) which capture the structure of the input signal is the key to this new approach. Testing methods and results are presented on networks for which computation time is a fraction of that necessary with traditional methods, yet classification reliability is maintained. Neural network acoustic classification systems utilizing the above techniques are compared to classic time domain classification networks. Last, a case studs is presented which looks at these techniques applied to the acoustic intercept problem. http://archive.org/details/featurebasedneur1094524169 Lieutenant Commander, United States Navy Approved for public release; distribution is unlimited.

In a space booster on takeoff, a control system must be employed to prevent the rocket from falling over as it is forced upward by the engines. One accurate dynamic model of the space booster on takeoff is the inverted pendulum. This paper investigated the inverted pendulum system from development of equations of motion, through implementation of an actual inverted pendulum system using state variable feedback control. The concept of state variable feedback was analyzed in determining a solution to the problem of control of the inverted pendulum. Most importantly, design and construction of a working, solid state controlled, inverted pendulum demonstration model was accomplished. http://archive.org/details/controlstrategie1094520475 Lieutenant Commander, United States Navy Approved for public release; distribution is unlimited.

This work addresses the application of numerical optimization technique to the pole-placement problem in multivariable optimal control. An algorithm is developed to select a set of weighting matrix element such that the conventional transient response criteria are satisfied. General properties of the optimal system in terms of stablity, robustness and relative weights between state and control variables were explored by applying the method to the design of two mult ivariable systems. Results indicated that this method provides good insight to the problem for the designer and is therefore a useful tool in multivariable control synthesis. http://archive.org/details/automatedpolepla1094521173 Approved for public release; distribution is unlimited.

In airborne anti-submarine warfare there is a need to more accurately determine the positions of sonobuoys on the surface of the vater. This report develops two algorithms which employ extended Kalman filters to determine estimated position. The bearing from the aircraft to the sonobuoy is the primary measurement. Range information is not available. The first algorithm is a six-state filter which was reduced from the 13-state system developed by the Orincon Corporation Its states include relative jjosition, relative velocity, and inertial misalignments. The second algorithm includes two cascaded Kalman filters. The primary two-state filter estimates sonobuoy position. A secondary filter estimates drift from information obtained from the primary filter. Both algorithms successfully estimated sonobuoy position for simulated aircraft data. The effect of a ircraf t-to-sono bucy range, the frequency of measurement, and changes in altitude are also analyzed. http://archive.org/details/estimationofsono1094518706 Lieutenant, United States Navy Approved for public release; distribution is unlimited.

Neural networks were applied to the Engine Condition and Monitoring System of the F/A-18 aircraft. Due to recent fleet experience with compressor blade failures in flight, neural networks were applied to three engine conditions; flameout due to compressor failures, normal operating conditions, and low oil pressure conditions. An attempt was made to predict compressor failure using the neural networks. A back propagation and back propagation/Kohonen network were successfully tested in recognizing the various conditions with data previously unseen by the networks. Both networks demonstrated promise in predicting failures although not enough data was available for conclusive results. http://archive.org/details/applicationofneu1094526888 Lieutenant Commander, United States Navy Approved for public release; distribution is unlimited.

The State Rate Feedback Implicit Model Follower control concept is examined in detail from a classical and modern control theory viewpoint. State Rate Feedback Implicit Model Following (SRFIMF) is a concept whereby control of the dynamic response of a system is achieved by the measurement and feedback of a state rate, normally acceleration. In addition to a basic description of the concept, emphasis is placed on the effect of noise in the measurement of the required feedback quantities. Control of the pitch attitude of the AV-8A Harrier VTOL aircraft is used as an example of the application of the control concept. The model of the Harrier used in this study includes the effect of both sensor measurement errors and gust load inputs. http://archive.org/details/astudyofstaterat1094519077 Lieutenant, United States Navy Approved for public release; distribution is unlimited.

This thesis discusses the modification of aid additions to an existing Optimal Systems Control FORTE AN Program (OPTSYS) originally obtained from Professor Arthur E. Bryson of Stanford University and subsequently redesigned to run interactively on the IBM 33 33 VVCMS by Lieutenant Commander John G. Hoden of the Naval Postgraduate School (NPS). The modified FOBTEAN program (OPTSYSX) and the additional FOETEAN Programs (OPTCALC) and (OPTPLOT) are now designed to run interactively under VM/CMS on the IBM 3033 utilizing a library double precision numerical integration subroutine and high resolution precision plotting software to provide the user with a highly accurate time response of a system which has been designed on the OPTSYSX Program. This series of programs permits the user to rapidly design, analyze and test all types of Optimal Systems Co ntrol problems. Examples of the various types of problems are worked through to illustrate all of the capabilities available. http://archive.org/details/developmentofgra1094519259 Commander, United States Navy Approved for public release; distribution is unlimited.

http://archive.org/details/applicationsofmo1094526890 NA NA

The successful application of holographic interferometry to the study of density fields around opaque bodies in wind tunnel experiments has been reported in the literature. The present report extends this technique to the study of the asymmetric flow fields encountered near the wing-fuselage junction of an aerodynamic model in the transonic flow regime. Finite fringe interferometry has been used to investigate the three dimensional density field about a partially transparent wing-body structure. The resulting asymmetric density field and shock wave structure are shown to be an accurate representation of the phenomena encountered in aerodynamic corner flow. http://archive.org/details/applicationofhol1094515994 Lieutenant, United States Navy Approved for public release; distribution is unlimited.