Abstract
The components of an electromagnetic shell system should be able to sustain the impact of high-strength instantaneous acceleration when the system is launched. The dynamic characteristics of high overload present significant challenges in the component (electronic and mechanical) design and part assembly of a steering gear system. This paper proposes a new design strategy for the servo system of a high-overload electromagnetic projectile. First, according to the special environment index parameters of a high-overload electromagnetic shell steering system, a new anti-overload deceleration mechanism that combines a triangular thread lead screw, a shift fork, and the entire anti-high-overload mechanical structure is proposed. The transient dynamic vibration characteristics of the entire high overload are analyzed. Based on the integrated module method for complex mechanical and electrical equipment, a mathematical model of the full closed-loop electromagnetic shell actuator system is established, and its dynamic characteristics are analyzed. Finally, a prototype of the high-overload electromagnetic projectile steering system is manufactured. By testing the maximum rudder deflection angle and the frequency and step responses of the system, the dynamic characteristics of the new high-overload electromagnetic shell actuator system are verified. This study provides a new method for designing high-overload electromagnetic shell steering gears.
Highlights
The actuator system of an electromagnetic projectile is an important executive device of the flight control system, which drives the deflection of a rudder surface
The results indicated that the new electromagnetic shell actuator structure met the requirements of high-overload resistance
3) Based on the integrated module method of complex electro-mechanical equipment, a dynamic mathematical model of the steering gear system was established to analyze the dynamic characteristics of the steering gear system
Summary
The actuator system of an electromagnetic projectile is an important executive device of the flight control system, which drives the deflection of a rudder surface. As described in reference [5], the impact acceleration of a vehicle launch system, ammunition launched by artillery, and penetration ammunition should be greater than 5000 g, 104 g, and 105 g, respectively. This poses significant challenges in designing the dynamic and static characteristics of the steering gear, which directly affect the mobility and impact accuracy of the electromagnetic shell [6]. The design of the electric actuator for electromagnetic projectiles should meet
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