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.
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TL;DR: The SCRAM project at Johns Hopkins University as mentioned in this paper developed a family of supersonic combustion ramjet (SCRAM) missiles for use as fleet defense weapons and tested them at Mach numbers of 4-10 at angles of attack up to 15 deg.
Abstract: During the period of 1962-1978, the Applied Physics Laboratory of Johns Hopkins University developed the technology for a family of missiles named SCRAM for use as fleet defense weapons. SCRAM is the acronym for supersonic combustion ramjet missile. The development work began with the conceptual design of two missile configurations and calculations of the expected performance for a variety of missions to provide defense for the surface fleet. A novel class of multimodule fixed-geometry hypersonic inlets was designed and wind-tunnel models were built and tested at Mach numbers of 4-10 at angles of attack up to 15 deg. Injector and combustor development was carried out in direct connect test apparatus. Considerable effort was directed to the development and testing of a wide variety of storable, reactive liquid fuels including boranes and aluminum alkyls. Many new testing techniques and diagnostic instruments were developed that are still key elements of scramjet test operations. The program culminated with the testing of the entire engine in free jets at Mach numbers of 57.3 and the design of a family of revised vehicle configurations that could exploit the full capability of the performance observed in the ground test program. This article presents the highlights of the technology program and references recently released documents.
67 citations
28 Jun 2000
TL;DR: In this paper, a nonlinear coupled 3-axis generic missile model is used as a design example for a gain-scheduled autopilot, which can be reduced to quasi-LPV form so that LPV design methodology can be applied.
Abstract: In this paper, we will apply linear parameter-varying (LPV) control theory to the design of gain-scheduled missile autopilot. A nonlinear coupled 3-axis generic missile model is used as our design example. We will show that this model can be reduced to quasi-LPV form so that LPV design methodology can be applied. Simulation of the gain-scheduled controller with the nonlinear missile model yields excellent results and serves to validate both the quasi-LPV modeling procedure and the LPV control theory in practice.
66 citations
21 Aug 2006
TL;DR: In this paper, an impact angle-based guidance law and an impact time based guidance law are proposed to guide a ship into a collision course so that the ship can intercept a target effectively under several constraint conditions.
Abstract: *† The general objective of most guidance laws is to guide a missile into a collision course so that the missile intercepts a target effectively under several constraint conditions. As the defense system for warships has been advanced recently, many researchers are working on the development of new guidance laws for anti-ship missiles. This paper deals with an impact angle based guidance law and an impact time based guidance law. The impact angle guidance law can be used to generate appropriate trajectories and intercept a target with desired impact angle. How to geometrically set the waypoint passing angles as well as the desired impact angle are proposed. The impact time guidance law based on proportional navigation guidance is also proposed in this paper. The proposed guidance law can be applied for the formation flight of anti-ship missiles. As several missiles intercept a target simultaneously, the missiles can complete the given mission more efficiently. Finally the two guidance laws are combined together to enhance the survivability and kill probability. Numerical simulations are performed to evaluate the performances of the proposed guidance laws using impact angle and impact.
66 citations
TL;DR: The results of these tests may be summarized in a homogeneous perforation formula in the case of a velocity lower than 200 m/sec: V 2 c = 1.7δρ 1 3 θe 2 M 4 3 where Vc is the minimum velocity for perfation, o diameter of the missile, M its mass, σ the ultimate compressive strength of the concrete, ϱ its density and ρ its thickness as discussed by the authors.
66 citations
06 Jun 1984
TL;DR: In this paper, the authors explore the nature and sources of these limits and present numerical examples to illustrate what kinds of numbers are required to achieve successful radar homing with an autopilot.
Abstract: When an aerodynamically controlled missile is used in a homing application, the transfer function of the vehicle becomes part of an overall homing and attitude control feedback loop. Therefore, the missile must be designed so that its aerodynamics meet the constraints required to accomplish homing successfully. For radar homing, these constraints are stringent enough to require an autopilot that controls the aerodynamic transfer function using body instruments and internal feedback loops. Even with an autopilot, there are limits on the aerodynamic moment parameters such as M ? and M ? that must be considered at the very beginning of the missile system design. This paper explores the nature and sources of these limits and presents numerical examples to illustrate what kinds of numbers are required.
66 citations