Topic
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.
Papers published on a yearly basis
Papers
More filters
Patent•
15 Oct 1993
TL;DR: In this paper, a fast and reliable switch for multi-channel, bi-directional fiber optics data link (FODL) systems is proposed, which can be used in multiple fiber optics guided missile launch systems and fiber optics based surveillance systems with multiple outposts.
Abstract: A fast and reliable switch (50) for multi-channel, bi-directional fiber optics data link (FODL) systems. The FODL channel switching is accomplished through a software command on the subcarrier frequency (SCF) code without using any moving components or wavelength sensitive optical devices. A fiber star coupler (92) and in-line erbium doped fiber amplifiers (94A-94Q) transform the FODL system into an electrically switchable, fiber star network with low optical power loss penalty. The switch can be used in multiple fiber optics guided missile launch systems and fiber optics based surveillance systems with multiple outposts. The switching scheme allows the launcher/controller (60) to perform a time-sharing control on multiple missiles (or outposts) (80-80P) by switching the SCF code sent to the programmable SCF generator of the OE unit in the controller (launcher). The scheme can also easily be extended to operate in a multiple control station mode that uses multiple control station at the launcher/controller (60) to control multiple missiles or outposts (80A-80P).
32 citations
TL;DR: In this paper, a comparison of three-dimensional, viscous, turbulent Navier-Stokes simulation for generic missile bodies with wind-tunnel tests have been performed with and without lateral jet thrusters for the Mach number range of 2-5 and angles of attack of 0-20 deg.
Abstract: Comparison of three-dimensional, viscous, turbulent Navier–Stokes simulation for generic missile bodies with wind-tunnel tests have been performed with and without lateral jet thrusters for ow Mach number range of 2–5 and angles of attack of 0–20 deg. Computationalresults show good overall engineering predictive capability for the surface pressure, normal force coef cient, and jet interaction effects. Further analysisof the computationalresults shows that the favorable upstream pressure zone (lambda zone) created by the lateral jet, unfavorable pressure loss behind the jet caused by its blockage effect, and the jet wraparound effect are the three principal competing physical mechanisms that inhibit or enhance the jet ampli cation factor. Canted jet studies to enhance the rst of these effects show substantial increase in favorable pressure; however, it does not recover axial component of the thrust vector. Qualitative computations for multijets and hot/binary gas thruster jets have been presented to demonstrate the overall computational capability for missile design applications.
32 citations
Patent•
26 Jul 1994
TL;DR: In this article, an improved imaging system was proposed to provide a 3D image for applications demanding visibility through fog, haze, smoke and other obscurants, such as enhanced vision for helicopters, ships, buses, trucks, traffic observation stations for an intelligent highway or security cameras for plants and military installations.
Abstract: An improved imaging system. The inventive imaging system (10) is adapted to transmit a plurality of first radar signals at millimeter wave frequencies at an area including an object along with background clutter. The return signals are processed to provide a three dimensional image for applications demanding visibility through fog, haze, smoke and other obscurants. Such applications include enhanced vision for helicopters, ships, buses, trucks, traffic observation stations for an intelligent highway or security cameras for plants and military installations. In a guidance system application, for example, the inventive system would include an electronically scanning antenna (12) to provide range and amplitude signals representative of a target area. The range and amplitude signals (18, 20) are compared to stored signals (26, 30) to create the three dimensional image. The stored signals are selected for comparison based on the dive angle of the missile (28, 32). The three dimensional image is then processed (22, 24, 34, 36, 38, 40) to derive guidance commands for the missile.
32 citations
Patent•
03 Jan 1967
TL;DR: In this paper, reaction engine control systems employing relatively moveable plug-cowl configurations with associated control systems are described for providing control of thrust direction and magnitude, engine operating conditions, missile kinematics, and other parameters of liquid and solid propellant rockets.
Abstract: Missile configurations with engine and propellant control systems are the subject of this application together with weapons and navigational techniques employing same. Reaction engine control systems employing relatively moveable plug-cowl configurations with associated control systems are described herein for providing control of thrust direction and magnitude, engine operating conditions, missile kinematics, and other parameters of liquid and solid propellant rockets.
32 citations
TL;DR: In this article, a new integrated guidance and control design scheme based on variable structure control approach for missile with terminal impact angle constraint is proposed, which can guide missile to hit the target with desired impact angle and desired flight attitude angle simultaneously.
32 citations