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.

Nonlinear dynamic autopilot design for the non-minimum phase missile

Abstract: We propose some new ideas to stabilize the center of mass of high angle of attack missile. The dynamics which describe a missile are known to be non-minimum phase. We first design a controller arising from the local linear controllers integration with respect to some of the state variables. Next, from the concept of nonlinear asymptotic tracking problem, we propose to circumvent the non-minimum phase phenomenon and to achieve the stabilization by appropriately choosing some of the parameters which govern the exponential decaying of the error function between the output of the system under consideration and the reference desired function. These parameters satisfy the Hurwitz polynomial. In both cases, it is shown that the required missile performances are met.

Low cost guidance for the Multiple Launch Rocket System (MLRS) artillery rocket

Abstract: The US Army Aviation and Missile Command has demonstrated the application of advanced technology to significantly improve the accuracy and range of the US Army's Multiple Launch Rocket System (MLRS) through the Guided MLRS Advanced Technology Demonstration (ATD). The addition of a cost-effective guidance and control package to the rocket results in a weapon system that can defeat the target at ranges up to 70 km with significantly fewer rounds. This not only increases the destructive capability of the system but also reduces the cost of the expended ammunition, the cost to transport the ammunition to the combat zone, and the number of launchers required to execute the mission. The guidance kit is housed in the nose of the MLRS and consists of an inertial measurement unit (IMU), four independent electro-mechanically actuated canards, a Global Position System (GPS) receiver, GPS antennas, a thermal battery, a guidance computer, and power supply electronics. Roll decoupling of the warhead and motor section was required to allow roll control of the guidance section to enable accurate inertial navigation and was accomplished by joining the two sections with a roll bearing. Five flight missiles were built and tested during the ATD. Two IMU vendors were selected to provide flight units (3 flights used vendor A and 2 flights used vendor B). A tightly coupled 8 channel GPS receiver was flown on all flights. This paper discusses the ATD development effort and presents flight test results.

Improved command to line-of-sight for homing guidance

Abstract: The command to line-of-sight (CLOS) guidance is known to require very high acceleration commands as the distance between a missile and its target becomes closer. Therefore, the CLOS is generally used for midcourse guidance. In order to use the CLOS for homing, an additional feedforward acceleration command (FFC) is necessary. In this correspondence an improved CLOS (ICLOS) technique which includes FFC is proposed. Its performance improvement is demonstrated by applying the technique to a surface-to air missile (SAM). >

The motions of rolling symmetrical missiles referred to a body-axis system

Abstract: Report presenting the linearized equations of motion have been derived for a rolling missile with slight aerodynamic asymmetries. Time histories of rolling-missile motions referred to a body-axis system have been prepared to show the types of missile motions that can be encountered.