OREGON STATE UNIV CORVALLIS Dept. of MECHANICAL ENGINEERING
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Works:  7 works in 7 publications in 1 language and 7 library holdings 

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Most widely held works by
OREGON STATE UNIV CORVALLIS Dept. of MECHANICAL ENGINEERING
(DURIP) Spontaneous Raman System for the Study of Enhanced Combustion and NonThermal Plasmas by
Richard B Peterson(
Book
)
1 edition published in 1990 in English and held by 1 WorldCat member library worldwide
This report describes the instrumentation purchased on the DURIP grant AFOSR890093 and the research work that this instrumentation will support. The objective of the grant was to acquire elements of a spontaneous Raman system for gas phase diagnostic work on currently funded combustion studies. Toward this end, we have acquired a neodymium: YAG pulsed laser with frequency doubling, an optical multichannel analyzer (OMA), a computer system required to operate the OMA, and a flat flame burner for validation and testing of the Raman setup. Raman spectroscopy; Laser; OMA; Combustion ignition plasma; Computer systems; Logistics. (jg)
1 edition published in 1990 in English and held by 1 WorldCat member library worldwide
This report describes the instrumentation purchased on the DURIP grant AFOSR890093 and the research work that this instrumentation will support. The objective of the grant was to acquire elements of a spontaneous Raman system for gas phase diagnostic work on currently funded combustion studies. Toward this end, we have acquired a neodymium: YAG pulsed laser with frequency doubling, an optical multichannel analyzer (OMA), a computer system required to operate the OMA, and a flat flame burner for validation and testing of the Raman setup. Raman spectroscopy; Laser; OMA; Combustion ignition plasma; Computer systems; Logistics. (jg)
Linear Theory of a Projectile With a Rotating Internal Part in Atmospheric Flight(
)
1 edition published in 2003 in English and held by 0 WorldCat member libraries worldwide
Dynamic modeling of the atmospheric flight mechanics of a projectile equipped with an internal rotating disk is investigated and a modified projectile linear theory is established for this configuration. To model this type of projectile requires alteration of several of the coefficients of the epicyclic dynamics leading to changes in the fast and slow epicyclic modes. A study of the frequency and damping properties of the epicyclic modes is conducted by systematically varying disk mass, rotational speed, and location. It is shown that the presence of an internal rotating disk can cause substantial changes in the epicyclic dynamics, including instability, in some configurations
1 edition published in 2003 in English and held by 0 WorldCat member libraries worldwide
Dynamic modeling of the atmospheric flight mechanics of a projectile equipped with an internal rotating disk is investigated and a modified projectile linear theory is established for this configuration. To model this type of projectile requires alteration of several of the coefficients of the epicyclic dynamics leading to changes in the fast and slow epicyclic modes. A study of the frequency and damping properties of the epicyclic modes is conducted by systematically varying disk mass, rotational speed, and location. It is shown that the presence of an internal rotating disk can cause substantial changes in the epicyclic dynamics, including instability, in some configurations
Model of Predictive Control of a DirectFire Projectile Equipped With Canards(
)
1 edition published in 2005 in English and held by 0 WorldCat member libraries worldwide
Launch uncertainties in uncontrolled directfire projectiles can lead to significant impact point dispersion, even at relatively short range. A model predictive control scheme for directfire projectiles is investigated to reduce impact point dispersion. The control law depends on projectile linear theory to create an approximate linear model of the projectile and quickly predict states into the future. Control inputs are based on minimization of the error between predicted projectile states and a desired trajectory leading to the target. Through simulation, the control law is shown to work well in reducing projectile impact point dispersion. Parametric trade studies on an example projectile configuration are reported that detail the effect of prediction horizon length, gain settings, model update interval, and model step size
1 edition published in 2005 in English and held by 0 WorldCat member libraries worldwide
Launch uncertainties in uncontrolled directfire projectiles can lead to significant impact point dispersion, even at relatively short range. A model predictive control scheme for directfire projectiles is investigated to reduce impact point dispersion. The control law depends on projectile linear theory to create an approximate linear model of the projectile and quickly predict states into the future. Control inputs are based on minimization of the error between predicted projectile states and a desired trajectory leading to the target. Through simulation, the control law is shown to work well in reducing projectile impact point dispersion. Parametric trade studies on an example projectile configuration are reported that detail the effect of prediction horizon length, gain settings, model update interval, and model step size
Linear Theory of a DualSpin Projectile in Atmospheric Flight(
)
1 edition published in 2000 in English and held by 0 WorldCat member libraries worldwide
The equations of motion for a dualspin projectile in atmospheric flight are developed and subsequently utilized to solve for angle of attack and swerving dynamics. A combination hydrodynamic and roller bearing couples forward and aft body roll motions. Using a modified projectile linear theory developed for this configuration, it is shown that the dynamic stability factor, S(g), and the gyroscopic stability factor, S(g) are altered compared to a similar rigid projectile, due to new epicyclic fast and slow arm equations. Swerving dynamics including aerodynamic jump are studied using the linear theory
1 edition published in 2000 in English and held by 0 WorldCat member libraries worldwide
The equations of motion for a dualspin projectile in atmospheric flight are developed and subsequently utilized to solve for angle of attack and swerving dynamics. A combination hydrodynamic and roller bearing couples forward and aft body roll motions. Using a modified projectile linear theory developed for this configuration, it is shown that the dynamic stability factor, S(g), and the gyroscopic stability factor, S(g) are altered compared to a similar rigid projectile, due to new epicyclic fast and slow arm equations. Swerving dynamics including aerodynamic jump are studied using the linear theory
Improved Dispersion of a FinStabilized Projectile Using a Passive Moveable Nose(
)
1 edition published in 2001 in English and held by 0 WorldCat member libraries worldwide
A key and often quoted metric associated with gun systems is impact point accuracy. The extent of impact dispersion is a complex function of a battery of parameters, including gun geometry and tolerances, the fire control system, projectile manufacturing tolerances, etc. The work reported here investigates potential impact point accuracy improvement for a penetratortype projectile realized by replacing the rigid nose cone wind screen with a passive gimballed nose. By comparing the impact point dispersion of a rigid projectile with a similar gimballed nose projectile, it is shown that impact point accuracy can be significantly improved. For the example penetrator projectile considered, impact point dispersion is reduced by more than 50%
1 edition published in 2001 in English and held by 0 WorldCat member libraries worldwide
A key and often quoted metric associated with gun systems is impact point accuracy. The extent of impact dispersion is a complex function of a battery of parameters, including gun geometry and tolerances, the fire control system, projectile manufacturing tolerances, etc. The work reported here investigates potential impact point accuracy improvement for a penetratortype projectile realized by replacing the rigid nose cone wind screen with a passive gimballed nose. By comparing the impact point dispersion of a rigid projectile with a similar gimballed nose projectile, it is shown that impact point accuracy can be significantly improved. For the example penetrator projectile considered, impact point dispersion is reduced by more than 50%
On the Swerve Response of Projectiles to Control Input(
)
1 edition published in 2008 in English and held by 0 WorldCat member libraries worldwide
The swerve response of fin and spinstabilized projectiles to control mechanism input is sometimes not intuitive and often surprises smart weapon designers. This report seeks to explain the basic parameters that govern swerve of projectiles excited by control input. By modeling the overall effect of any control mechanism as a nonrolling reference frame force or moment applied to the projectile, we obtain general expressions for swerve in terms of basic vehicle parameters. These compact expressions are used to show that maximum swerve response for a finstabilized projectile is achieved when the force is applied near the nose of the projectile, while maximum swerve response for a spinstabilized projectile is achieved when the force is applied near the base of the projectile
1 edition published in 2008 in English and held by 0 WorldCat member libraries worldwide
The swerve response of fin and spinstabilized projectiles to control mechanism input is sometimes not intuitive and often surprises smart weapon designers. This report seeks to explain the basic parameters that govern swerve of projectiles excited by control input. By modeling the overall effect of any control mechanism as a nonrolling reference frame force or moment applied to the projectile, we obtain general expressions for swerve in terms of basic vehicle parameters. These compact expressions are used to show that maximum swerve response for a finstabilized projectile is achieved when the force is applied near the nose of the projectile, while maximum swerve response for a spinstabilized projectile is achieved when the force is applied near the base of the projectile
A Comparison of Different Guidance Schemes for a Direct Fire Rocket with a Pulse Jet Control Mechanism(
)
1 edition published in 2002 in English and held by 0 WorldCat member libraries worldwide
Compared to gun launch ammunition, uncontrolled direct fire atmospheric rockets are terribly inaccurate, to the point where they are used most effectively on the battlefield as area weapons. Dispersion characteristics can be dramatically improved by outfitting the rocket with a suitable control mechanism and sensor suite. In the work reported here, a lateral pulse jet control mechanism is considered. The lateral pulse jet mechanism consists of a finite number of small thrusters spaced equally around the circumference of the rocket. Using a simulation model that includes projectile, flight control system, and inertial measurement unit dynamics, three different control laws are contrasted, namely, proportional navigation guidance, parabolic and proportional navigation guidance, and trajectory tracking control laws. When the number of individual pulse jets is small, a trajectory tracking control law provides superior dispersion reduction. However, as the number of pulse jets is increased, the relative performance of the parabolic and proportional navigation guidance control law is slightly better than the trajectory tracking control law. When the number of pulse jets is small, the proportional navigation guidance, as well as the parabolic and proportional navigation guidance control laws, exhibits large mean miss distance. All control laws appear to be equally susceptible to accelerometer and gyroscope errors that corrupt inertial measurement unit rocket state feedback
1 edition published in 2002 in English and held by 0 WorldCat member libraries worldwide
Compared to gun launch ammunition, uncontrolled direct fire atmospheric rockets are terribly inaccurate, to the point where they are used most effectively on the battlefield as area weapons. Dispersion characteristics can be dramatically improved by outfitting the rocket with a suitable control mechanism and sensor suite. In the work reported here, a lateral pulse jet control mechanism is considered. The lateral pulse jet mechanism consists of a finite number of small thrusters spaced equally around the circumference of the rocket. Using a simulation model that includes projectile, flight control system, and inertial measurement unit dynamics, three different control laws are contrasted, namely, proportional navigation guidance, parabolic and proportional navigation guidance, and trajectory tracking control laws. When the number of individual pulse jets is small, a trajectory tracking control law provides superior dispersion reduction. However, as the number of pulse jets is increased, the relative performance of the parabolic and proportional navigation guidance control law is slightly better than the trajectory tracking control law. When the number of pulse jets is small, the proportional navigation guidance, as well as the parabolic and proportional navigation guidance control laws, exhibits large mean miss distance. All control laws appear to be equally susceptible to accelerometer and gyroscope errors that corrupt inertial measurement unit rocket state feedback
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