Missile

About: Missile is a research topic. Over the lifetime, 12829 publications have been published within this topic receiving 94307 citations. The topic is also known as: guided missile & missiles.

Missile having rotor ring

Abstract: A missile having a rotor ring, which has at least one adjustable fin actuated by the relative rotation between the rotor ring and the missile. At least one motor is arranged between the rotor ring and the missile, and a control device is provided which allows the motor to work as a generator and performs the fin adjustment.

Missile flight control using active flexspar actuators

Abstract: A new type of subsonic missile flight control surface using piezoelectric flexspar actuators is presented. The flexspar design uses an aerodynamic shell which is pivoted at the quarter-chord about a graphite main spar. The shell is pitched up and down by a piezoelectric bender element which is rigidly attached to a base mount and allowed to rotate freely at the tip. The element curvature, shell pitch deflection and torsional stiffness are modeled using laminated plate theory. A one-third scale TOW 2B missile model was used as a demonstration platform. A static wing of the missile was replaced with an active flexspar wing. The 1 in 2.7 in active flight control surface was powered by a bimorph bender with 5 mil PZT-5H sheets. Bench and wind tunnel testing showed good correlation between theory and experiment and static pitch deflections in excess of . A natural frequency of 78.5 rad with a break frequency of 157 rad was measured. Wind tunnel tests revealed no flutter or divergence tendencies. Maximum changes in lift coefficient were measured at which indicates that terminal and initial missile load factors may be increased by approximately 3.1 and 12.6 g respectively, leading to a greatly reduced turn radius of only 2400 ft.

Adaptive Integrated Guidance and Control Based on Backstepping and Input‐to‐State Stability

Abstract: This paper presents an approach of integrated guidance and control (IGC) design for interception of maneuvering targets (evaders). An IGC model with uncertainties in the pitch plane is formulated, and, by adopting a backstepping scheme, an adaptive nonlinear IGC approach is developed. Theoretical analysis shows that the design approach makes the line-of-sight (LOS) rate be input-to-state stable (ISS) with respect to target maneuvers and missile model uncertainties, and the stability of the missile dynamics can be guaranteed as well. The numerical simulation confirms the effectiveness of the proposed design approach.

Prediction of Microwave Attenuation Characteristics of Rocket Exhausts

Abstract: This paper summarizes an approximate technique for predicting microwave attenuation from propel]ant composition for a given motor configuration and missile trajectory. The solution involves calculations of electron density and collision frequency and knowledge of microwave frequency. The prediction of the electron density requires treatment of the effects of thermal ionization of alkali metals, detachment and recombination processes during nozzle expansion, inviscid plume expansion, plume-air mixing, afterburning, and missile velocity and altitude. The collision frequency is calculated using existing techniques and data. Effects of propellant composition, motor configuration, and missile trajectory are examined. Predicted X and K band attenuation is generally lower than measured values for sea level, static motor firings. This may be caused by other mechanisms not considered, such as chemi-ionizat ion. Predicted effects of mixing and afterburning were not great, but this area needs further study. Although the predictions are only approximate, they are useful for assessing microwave attenuation characteristics of rocket systems during early design and development stages.