Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance
Reexamination Certificate
1990-03-12
2001-05-15
Carone, Michael J. (Department: 3641)
Aeronautics and astronautics
Missile stabilization or trajectory control
Automatic guidance
Reexamination Certificate
active
06231003
ABSTRACT:
BACKGROUND OF THE INVENTION
1. Field of the Invention
The present invention relates to defense mechanisms for atmospheric and extraterrestrial vehicles. More particularly, the present invention relates to an apparatus releasable from the vehicle which can either serve as a decoy, by diverting an approaching threat, and/or serve as a kinetic kill device by positioning itself to collide with the threat.
2. Description of the Related Art
Defensive strategies used by aircraft to defend against approaching threats include passive defense to avoid a threat, active defense to deceive a threat, and lethal defense to kill the source of the threat. Methods currently being used to implement these defensive strategies include low altitude sanctuary, terrain masking, expendable countermeasures, electronic countermeasures (ECM), air-to-air missiles, air-to-surface missiles, and most recently, low observable, or “stealth” technology. These methods provide a substantial measure of survivability in a very hostile threat environment, but face continual pressure to keep pace with threat upgrades. Examples of prior art decoys/targets are included in the following references:
U.S. Pat. No. 2,957,417, issued to D. D. Musgrave, entitled “Missile Decoy”, discloses a decoy system comprising a shroud fixed to the fins of a missile having an internal reflective surface of partial parabolic shape.
U.S. Pat. No. 2,898,588, issued to C. L. Graham, entitled “Attack Deviation Device”, discloses a device comprising a hollow elongated member which is towed behind an aircraft. There is structure in the member for reflecting radar signals impinging thereon.
U.S. Pat. No. 4,808,999, issued to D. Toman, entitled “Towed Decoy with Fiber Optic Link”, discloses a decoy which is towed behind an aircraft using a tow line which incorporates a fiber optic link through which signals are transmitted.
U.S. Pat. No. 4,419,669, issued to D. M. Slager, entitled “Controlled Scintillation Rate Decoy”, discloses a decoy having a spherical body with microwave reflectors for reflecting incident radar energy in a manner to provide the decoy with the selected radar cross section.
U.S. Pat. No. 3,290,681, issued to R. H. Beteille, entitled “Device for Jamming Radar Detection and Interception of Ballistic Missiles”, discloses the use of decoys consisting of metallized inflatable balloons.
U.S. Pat. No. 3,568,191, issued to J. C. Hiester, entitled “Method for Defending an Aircraft Against a Frontal Attack”, discloses a method of launching a rocket in the direction of travel of an aircraft, the rocket containing, in a collapsed, condition a collapsible reflector having three orthogonal surfaces of wire mesh. The reflector is ejected from the rocket, expanded, and thereby towed, the reflector serving as a target for attracting the interceptor.
U.S. Pat. No. 3,126,544, issued to W. H. Greatbatch, Jr., entitled “Method of Deception for an Aircraft”, discloses deployment of a spherically shaped decoy that is provided with a plurality of target plates. The decoy is illuminated with RF energy, the interceptor being deceived into following the decoy target.
U.S. Pat. No. 3,045,596 entitled “Guided Missile”, issued to R. S. Rae discloses a controlled missile having structure including a spherical body having spaced ports for the discharge of jets in such a manner so as to lift and propel the missile. The guided missile is launched and controlled in aerial flight by the operator from the time of launching to the time of contact with a target. The Rae device weighs on the order of 300 pounds and is two feet in diameter. It carries explosives.
None of the aforementioned references disclose a defense system or apparatus having 1) a guidance system capable of operating independently of the launch vehicle and/or operator, and 2) a propulsion system having the ability to accurately maneuver the body relative to the threat in the absence of a substantial axial velocity so as to eliminate the threat.
As will be disclosed below, present applicants have developed a novel apparatus for defending a vehicle against an approaching threat which provides these capabilities. This patent application is related to patent application Ser. No. 07/491,798, entitled “Killer Volleyball Defense System” filed concurrently herewith and patent application Ser. No. 07/493,087, entitled “Killer Volleyball Launcher”. All three patent applications are assigned to the present assignee, Rockwell International Corporation.
The term “Killer Volleyball” or “KV”, as used herein and in the aforementioned, concurrently filed patent applications, refers to the presently disclosed and claimed apparatus for defending a vehicle. This is the terminology used during its development by Rockwell International Corporation.
OBJECTS AND SUMMARY OF THE INVENTION
It is a principal object of the present invention to defend a vehicle from an approaching threat without the need for a propulsion system which provides a substantial axial velocity in the direction of the threat.
Another object is to defend the vehicle from a threat which may be approaching from the aft sector.
Another object is to defend an atmospheric vehicle from an approaching airborne threat.
These and other objects are achieved by the present invention which is an apparatus for defending a vehicle against an approaching threat. In its broadest aspects, the apparatus (i.e. Killer Volleyball) comprises a body deployable from the vehicle having at least one reference axis thereon. A plurality of spaced divert thruster means are associated with the body for translating the body relative to the threat upon deployment from the vehicle. A plurality of spaced attitude control thruster means are associated with the body for providing roll, pitch and yaw to orient the reference axis to a desired orientation relative to the threat. A guidance system, associated with the reference axis, is provided for communicating electronic signals to the attitude control thruster means and divert thruster means for controlling the position of the body relative to the threat to eliminate the threat. The guidance system preferably operates independently of the vehicle after deployment.
In its narrower aspects, the body is substantially spherical with a uniformly textured outer surface. It is particularly adaptable for use with atmospheric vehicles being defended against airborne threats. In one embodiment the guidance system includes a seeker means for tracking the threat, the seeker means providing electrical information for the guidance system to maneuver the apparatus for a collision with the threat, thereby providing a kinetic kill and elimination of the threat. In another embodiment the apparatus serves as a decoy, emitting a signal for diverting the threat away from the vehicle, thereby eliminating the threat.
Other objects, advantages and novel features of the present invention will become apparent from the following detailed description of the invention when considered in conjunction with the accompanying drawings.
REFERENCES:
patent: 3045596 (1962-07-01), Rae
patent: 3374967 (1968-03-01), Plumley
patent: 3792477 (1974-02-01), Tomiyasu
patent: 4034372 (1977-07-01), Margerum
patent: 4264907 (1981-04-01), Durand et al.
patent: 4286498 (1981-09-01), Block et al
patent: 4711414 (1987-12-01), Dunn
patent: 4718320 (1988-01-01), Brum
patent: 4856734 (1989-08-01), Davies
patent: 4928906 (1990-05-01), Sturm
patent: 4955558 (1990-09-01), Machell et al.
Hibma Richard A.
Hilscher Richard W.
Miralles Carlos T.
Ward Jerry D.
Wright Blaine G.
Carone Michael J.
Ginsberg Lawrence N.
The Boeing Company
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