Course Correction Fuze Concept Analysis for In-Service 155 mm Spin-Stabilized Gunnery Projectiles

The threat imposed by terrorist attacks is a major hazard for military installations, for example, in Iraq and Afghanistan. The large amounts of rockets, artillery projectiles, and mortar grenades (RAM) that are available pose serious threats to military forces. An important task for international research and development is to protect military installations and implement an accurate early warning system against RAM threats on conventional computer systems in out-of-area field camps. This work presents a method for determining the trajectory, caliber, and type of a projectile based on the estimation of the ballistic coefficient. A simulation-based optimization process is presented that enables iterative adjustment of predicted trajectories in real time. Analytical and numerical methods are used to reduce computing time for out-of-area missions and low-end computer systems. A GUI is programmed to present the results. It allows for comparison between predicted and actual trajectories. Finally, different aspects and restrictions for measuring the quality of the results are discussed.

show abstract

“…Other mathematical models for typical fin stabilized artillery rockets are presented in [11][12][13][14][15][16].…”

Section: Ballistic Modelmentioning

confidence: 99%

Simulation‐Based Early Prediction of Rocket, Artillery, and Mortar Trajectories and Real‐Time Optimization for Counter‐RAM Systems

Ramezani

Rothe

2017

Mathematical Problems in Engineering

View full text Add to dashboard Cite

show abstract

“…Salman et al [8] use H ∞ control to compute the roll axis autopilot of a similar projectile concept as the one presented in the present work, Gagnon and Lauzon [9] give an overview and make a comparison of various projectile concepts whereas, Ilg [10] present a complete work on the GNC loop of a guided munition. Mracek et al [11] investigate several autopilot topologies for general spinning airframes, Semerci et al [12] use linear quadratic optimal control for the control of a spinning missile and Calise et al [13] present an adaptive autopilot design for guided munitions based on neural networks.…”

Section: Introductionmentioning

confidence: 98%

Flight Control for a Class of 155 mm Spin-stabilized Projectiles with Course Correction Fuse (CCF)

Theodoulis

Wernert

2011

AIAA Guidance, Navigation, and Control Conference

View full text Add to dashboard Cite

This paper presents a study on trajectory correction autopilot configuration for a class of fin-guided spin-stabilized ammunitions. The proposed algorithm is heavily based on the system's linear parameter-varying model valid inside its entire flight envelope. This model offers an accurate approximation of the airframe nonlinear dynamics and is also used for stability analysis. A decentralized optimal linear quadratic integral servo controller strategy is proposed for the autopilot that offers accurate tracking and disturbance rejection for both the longitudinal/lateral projectile dynamics. The gains of the controller are smoothly scheduled to provide full flight envelope coverage and the tracking qualities of the overall configuration are tested using pulse-type reference signals. Finally, nonlinear simulations of the overall control configuration are given in order to illustrate the effectiveness of the proposed autopilot.

show abstract

“…The resulting spin-stabilized canard-guided projectile is a so-called dual-spin guided weapon. 5,6,7 Such a practice permits to regulate the projectile airframe pitch/yaw dynamics as done in the case of skid-to-turn missiles, 8 where, however, the dynamics of each axis are controlled separately.…”

Section: Introductionmentioning

confidence: 99%

Pitch/Yaw Channels Control Design for a 155mm Projectile with Rotating Canards, using a H∞ Loop-Shaping Design Procedure

Sève

Theodoulis

Wernert

et al. 2014

AIAA Guidance, Navigation, and Control Conference

View full text Add to dashboard Cite

This article details the design of a skid-to-turn autopilot for a 155mm spin-stabilized canard-guided projectile. The proposed concept possesses a so-called dual-spin configuration: the aft section contains the payload and is highly-spinning in order to provide the system with dynamic gyroscopic stability, whereas the forward section is roll-decoupled from the aft one by means of a coaxial motor, and includes all the necessary guidance and control software and hardware. A set of two pairs of nose-mounted rotating aerodynamic control surfaces are used to regulate the projectile airframe pitch/yaw dynamics. The autopilot design, based on an accurate linearized model, remains a challenging task because of the heavy cross-coupling between the normal and lateral axes dynamics generated by the high-spin rate of the aft section. A H∞ loop-shaping design approach is used in order to synthesize a low complexity structured fixed-order robust controller, taking into account modeling uncertainty and the limited performance of the actuators and sensors. Two kinds of autopilot feedback structures are considered such that they correspond to two different positions for the sensors. The influence of this sensor position on the open-loop projectile pitch/yaw dynamics is also emphasized.

show abstract

Course Correction Fuze Concept Analysis for In-Service 155 mm Spin-Stabilized Gunnery Projectiles

Cited by 40 publications

References 3 publications

Simulation‐Based Early Prediction of Rocket, Artillery, and Mortar Trajectories and Real‐Time Optimization for Counter‐RAM Systems

Simulation‐Based Early Prediction of Rocket, Artillery, and Mortar Trajectories and Real‐Time Optimization for Counter‐RAM Systems

Flight Control for a Class of 155 mm Spin-stabilized Projectiles with Course Correction Fuse (CCF)

Pitch/Yaw Channels Control Design for a 155mm Projectile with Rotating Canards, using a H∞ Loop-Shaping Design Procedure

Contact Info

Product

Resources

About