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

Theodoulis, Spilios; Wernert, Philippe

doi:10.2514/6.2011-6247

Cited by 8 publications

(8 citation statements)

References 14 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…For the Jacobian on the right we can apply the drag-only approximation in sec. II.E.1 and use (14). If we do this and use similar arguments about insensitivity to position and velocity as those leading to (49) we arrive at the approximation…”

Section: Iiib2 Velocity To Be Gainedmentioning

confidence: 92%

“…The stability and disturbance rejection for 2D canard controlled spinning projectiles can be improved by incorporation of a dynamics synthesizing autopilot and several such designs have been presented recently. 14,15,16 It has been shown that good tracking performance can be achieved e.g. by a controller of the proportional-integral type designed using linear parameter varying theory incorporating ℋ 2 or ℋ ∞ conditions.…”

Section: Ib1 Related Workmentioning

confidence: 99%

See 1 more Smart Citation

Velocity To Be Gained Guidance for a Generic 2D Course Correcting Fuze

Robinson

Strömbäck

2015

AIAA Guidance, Navigation, and Control Conference

View full text Add to dashboard Cite

A guidance strategy for generic 2D course correcting fuzes is developed using a perturbation based trajectory prediction method together with a velocity to be gained (VTG) control formulation. The open loop dynamics for the VTG that results in the atmospheric case is a slight modification of the vacuum dynamics and similar approaches for control can be applied. We formulate and solve a time varying linear quadratic (LQ) optimal control problem to obtain a guidance strategy that makes efficient use of controls over the flight. The resulting guidance strategy requires only low complexity updates in-flight. Using simulations of a standard 155mm artillery shell with canard control in varying firing scenarios it is shown that excellent dispersion reduction can be obtained with only modest requirements on control authority.

show abstract

Section: Iiib2 Velocity To Be Gainedmentioning

confidence: 92%

Section: Ib1 Related Workmentioning

confidence: 99%

Velocity To Be Gained Guidance for a Generic 2D Course Correcting Fuze

Robinson

Strömbäck

2015

AIAA Guidance, Navigation, and Control Conference

View full text Add to dashboard Cite

show abstract

“…He pointed out that the stability for this kind of projectiles is reduced due to the following two factors: the addition of canards and the reduced angular momentum of the forward part. Theodoulis and Wernert [14] present the quasilinear parameter-varying model of the dual-spin-stabilized projectile and analysed the stability of the projectile on different characteristic points of the whole flight envelope. Zhu [15] took account of the control effects of canards and then established a revised stability criterion according to the Hurwitz stability criterion which can be reduced to that of conventional spinstabilized projectiles.…”

Section: Introductionmentioning

confidence: 99%

Flight Stability of Canard-Guided Dual-Spin Projectiles with Angular Rate Loops

Zheng

Zhou

2020

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

Generally, as a precision-guided weapon, the missile has many disadvantage such as high price, difficult maintenance, and low yield. Modern war requires more and more new guided ammunition with high precision, low cost, and low collateral damage. Therefore, as a simple guided conventional ammunition technology, the dual-spin projectile has attracted the attention of ammunition experts recently. This paper proposes a dual-spin projectile scheme based on the rotation control method. Firstly, the concept of the dual-spin projectile is introduced. Secondly, the mathematical model of the dual-spin projectile is established, and the angular motion equation is finally obtained by using some linearized assumptions. Finally, the sufficient and necessary conditions of coning motion stability for dual-spin projectile with angular rate loops are analytically derived and further verified by numerical simulations. It is noticed that the upper bound of the control gain is affected by the delay angle of the control system and the spinning rate of the projectile.

show abstract

“…To investigate and enhance the performance of dual-spin atmospheric projectiles, several works have been done [1][2][3][4][5][6][7][8][9][10]. In these works, several issues such as dynamic, stability, control, and guidance have been studied.…”

Section: Introductionmentioning

confidence: 99%

“…Theodoulis et al [8][9][10] have studied some guidance, control, and dynamic issues in a class of n guided spin stabilized vehicles. In these works, the nose roll angle is controlled by a coaxial servomotor, whereas the lateral guidance and control are performed by two pairs of rotating canards placed on the nose [9,10]. The complete nonlinear equations of motion are stated in a non-rolling body frame [8][9][10].…”

Section: Introductionmentioning

confidence: 99%

Integrated Optimization of Guidance and Control Parameters in a Dual Spin Flying Vehicle

Nobahari

Kermani

2017

Scientia Iranica

View full text Add to dashboard Cite

In this paper, integrated optimization of the guidance and control parameters of a dual-spin ying vehicle is presented. The vehicle is composed of two parts: a freerolling aft body, including the engine and the stabilizing ns, and a roll-isolated front body, including all necessary guidance and control equipment, such as onboard computer, control ns, and an inertial navigation system. After developing the governing equations of motion, control loops and the guidance algorithm are constructed. Controllers are designed for two operating points and the guidance algorithm consists of a midcourse and a terminal phase. In midcourse phase, a virtual target, located on the nominal trajectory, is followed using proportional navigation law; while, in the terminal phase, the vehicle is guided toward the real target. A new nonlinear saturation function is de ned in order to saturate the maximum lateral acceleration command as a function of dynamic pressure. Finally, the integrated tuning of 23 guidance and control parameters is formulated as an optimization problem. The optimization problem is solved using a metaheuristic algorithm, called tabu continuous ant colony system. The performance of the optimized guidance and control system is evaluated using Monte Carlo simulations based on the complete nonlinear model.

show abstract

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

Cited by 8 publications

References 14 publications

Velocity To Be Gained Guidance for a Generic 2D Course Correcting Fuze

Velocity To Be Gained Guidance for a Generic 2D Course Correcting Fuze

Flight Stability of Canard-Guided Dual-Spin Projectiles with Angular Rate Loops

Integrated Optimization of Guidance and Control Parameters in a Dual Spin Flying Vehicle

Contact Info

Product

Resources

About