Aeronautics and astronautics – Missile stabilization or trajectory control – Remote control
Reexamination Certificate
2003-01-08
2003-12-23
Gregory, Bernarr E. (Department: 3662)
Aeronautics and astronautics
Missile stabilization or trajectory control
Remote control
C244S003100, C244S003130, C244S003140, C342S061000, C342S062000, C342S195000, C701S003000
Reexamination Certificate
active
06666401
ABSTRACT:
The present invention relates to a missile defense system. In particular, the invention is directed to a missile defense system employing intercept missiles that are programmed to intercept and destroy incoming missiles, wherein the course and trajectory of the intercepting missile is dynamically adjusted in near real-time based on information received from an incoming missile tracking station. The adjustment in course and trajectory of the intercept missile provides improved accuracy, reliability and success rates for a missile intercept system.
BACKGROUND AND SUMMARY OF THE INVENTION
A conventional missile defense system typically includes one or more missiles designed to intercept and destroy an incoming missile launched by a hostile force. The course and trajectory of these intercept missiles generally provides an initial intercept course calculated based on trajectory information relating to the incoming missile that is obtained by tracking the incoming missile. However, such intercept course and trajectory information is typically not accurate or reliable enough to ensure a strike on the incoming missile. This information is only useful in the initial stages of the intercept process, and is most valuable if the course and trajectory of the incoming missile does not change after the intercept missiles have been launched.
Realizing this shortcoming, designers of conventional missile intercept systems use additional means to adjust the course and trajectory of the intercept missiles when the intercept missiles come within a predetermined range of the incoming missile. For example, the intercept missiles may typically include heat-seeking (e.g. infrared) and/or radar based tracking technologies. Thus, when a conventional intercept missile is within a range in which these additional tracking means are useful, course adjustments may be made using these technologies.
Unfortunately, these conventional tracking technologies are easily circumvented using well known technologies. For example, when an incoming missile detects an intercept missile (or other object) within a predetermined range, the targeted missile may release various countermeasures to confuse and misguide the intercept missile. For example, the incoming missile may release chaff that includes metallic shavings that may counter radar based tracking systems, or flares that may circumvent heat-seeking or infrared tracking systems. Use of these types of countermeasures often confuse the navigation systems of the intercept missiles, causing them to miss completely and/or detonate at an improper time or location.
Moreover, because programming the initial course and trajectory of an intercept missile is based only on initial tracking data, if the trajectory or course of the incoming missile changes during flight, conventional intercept systems are ill equipped to adjust their trajectory during flight to accommodate such a change in target path.
Recently, numerous test failures involving these types of conventional missile defense systems have been reported. Either the intercept missile entirely misses the intended target, or the detonation of the intercept missile is not sufficient to destroy or disable the incoming missile.
It is well known that many conventional munitions, such as, for example, so-called “smart bombs” include circuitry that enables them to be guided to their intended (stationary) target location using information from global positioning system (GPS) satellites. For example, coordinates of an intended target may be input into the guidance or navigation system of the munition, and the guidance or navigation system may perform periodic checks during flight to ensure that its real-time position is correct, and to ensure proper trajectory and course. This is relatively straightforward when dealing with a stationary target.
The present invention envisions an exemplary missile defense system in which the intercepting missiles are updated with information from a tracking system to dynamically adjust its trajectory and course in-flight substantially in real-time. This type of continuous dynamic course adjustment will provide advantages over conventional missile defense systems and will not be subject to the same types of simple countermeasures that are currently available. Moreover, the exemplary missile defense system of the present invention may include GPS receiving technology to provide further efficiency and accuracy with respect to the dynamic course and trajectory adjustments.
The intercept missiles of the present invention may be provided with circuitry, such as, for example, a navigation computer, that enables information from the incoming missile tracking stations to be used to adjust the course and trajectory of the intercept missile in substantially real-time, as needed. Inputs to the course and trajectory correction circuitry may include, for example, a receiver for receiving information regarding the course and trajectory of the incoming missile from a tracking station, and position location information that may be included in conjunction with GPS data for enhanced accuracy.
Additionally, the intercept missile may be a munition that includes a negatively charged palette of explosives that would, upon release from the intercepting missile be attracted to the incoming missile, whereupon detonation should result in destruction, detonation, or disability of the incoming missile. For example, the incoming missile will typically have a positive charge on its hull due to friction caused by high speed passage through the atmosphere. A negatively charged palette of explosives would therefore be attracted to the positively charged hull of the incoming missile. The negatively charged palette may then attach itself to the hull of the incoming missile, or be detonated in close proximity to the incoming missile, thereby disabling, disarming or destroying the incoming missile. Alternatively, an explosive released by the intercept missile may be detonated at a location proximate the incoming missile path without using a negatively charged palette. For example, the explosive, upon detonation, could release sufficient amounts of a disabling agent, such as, for example, flak, to cover a sufficient area that, if passed through by an incoming missile, would cause the incoming missile to detonate or otherwise become disabled or disarmed. The detonation location of the explosive palette of the intercept missile may be precisely determined using the GPS system information and/or the trajectory and course adjustment system of the missile defense system of the present invention.
To that end, an exemplary embodiment of the present invention is directed to a missile defense system including at least one intercept missile, the missile defense system comprising an incoming missile tracking system for detecting the launch or identifying an incoming missile, and determining the course and/or trajectory of the incoming missile, a communication system for receiving incoming missile information from the incoming missile tracking system and transmitting course and trajectory information to the intercept missile, this course and trajectory information being based on the incoming missile information, circuitry for adjusting the course and trajectory of the intercept missile based on the incoming missile information and the location of the intercept missile received from on-board GPS receiver circuitry in substantially real-time.
A method of providing missile defense is also contemplated, the method comprising identifying an incoming missile, continuously monitoring said incoming missile to determining a course and trajectory of said incoming missile and any changes thereto, transmitting said course and trajectory information of said incoming missile to a receiving station, transmitting intercept course and trajectory information to an intercept missile, said intercept course and trajectory information being based on said course and trajectory of said incoming missile, and dynamically adjusting said intercept course and trajectory info
Gregory Bernarr E.
Nixon & Vanderhye PC
Technology Patents, LLC
LandOfFree
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