Abstract
The balance of stability and maneuverability is the foundation of the trajectory correction projectile. For the terminal correction projectile without an attitude feedback loop, a larger control force is expected which may cause an instability. This paper proposes a novel method to derive instability boundaries for the control force magnitude. No additional coordinate system is needed in this method. By introducing the concept of angular compensation matrix, the exterior ballistic linearized equations considering control force are established. The necessary prerequisite for a stable flight under control is given by the Routh stability criterion. The instability boundaries for the control force magnitude are derived. The results of example flights are 13.5% more accurate compared with that in relevant research. Numerical simulations demonstrate that if the control force magnitude lies in the unstable scope derived in this paper, the projectile loses its stability. Furthermore, the effects of the projectile pitch, velocity, and roll rate on flight stability during correction are investigated using the proposed instability boundaries.
Highlights
Trajectory correction projectiles/fuzes can meet the requirement of low collateral damage and higher delivery accuracy in modern warfare
For the pursuit of further improvements in accuracy, the guidance law based on target imager feedback is proposed and becomes a tendency in the future [11, 12]
The purpose of this section is to derive the boundary for control force that causes an instability and makes some efforts to build the balance between the maneuverability and stability for the projectile under control
Summary
Trajectory correction projectiles/fuzes can meet the requirement of low collateral damage and higher delivery accuracy in modern warfare. Cooper G and Fresconi F [20] regarded the projectile with activating canards asymmetric and investigated its flight stability under control They established dynamic equations in the body reference frame. By proposing the non-spinning coordinate originally, the research investigated the influence of force magnitude on the flight stability and derived the analytic damping rate expression of the projectile under control by an analogy to non-controlled projectile. Such an analogy can only get a rough scope of the control force for flight stability. The magnitude boundaries of the control force that result in flight instability are derived and analyzed. The influence of flight parameters on the stability is analyzed by the instability boundaries
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