Patent Grant
8074516
Projectiles such as missiles, bombs, interceptors, and similar targeted airframes utilize sensors for guidance. Typically one or more sensors are located in a forward section, or nose, of the projectile often necessitating the use of a radome assembly to provide the sensor a path to obtain data pertaining to flight characteristics, position, or target location. Ceramic radomes are commonly used but have several shortcomings.
Typical ceramics provide poor erosion resistance and are subject to damage from rain and particulates. This damage may “blind” the projectile during flight and/or cause premature warhead ignition. Increases in projectile velocity result in increased radome surface temperatures and it is common to use a symmetric ceramic radome incorporating various structural elements such as, ablative thermal protective overlaps, structural cutouts, fasteners, doublers, and the like. Each of these elements may involve significant labor to construct and implement, additional weight, and increased complexity. Moreover, conventional radomes utilizing additional structural elements may provide a potential leak path requiring in the use of multiple gaskets and seals to isolate internal components from the environment.
Methods and apparatus for non-axisymmetric radome according to various aspects of the present invention include a non-symmetric housing for a forward portion of a projectile. Multiple sensors may be positioned in an off-axis configuration within the non-symmetric housing reducing the possibility of one sensor interfering with the operation of another sensor. The non-symmetric housing may also be configured with a strengthening member suitably adapted to provide additional resistance to bending moments caused by external loading along a surface of the non-symmetric housing.
A more complete understanding of the present invention may be derived by referring to the detailed description and claims when considered in connection with the following illustrative figures. In the following figures, like reference numbers refer to similar elements and steps throughout the figures.
Elements and steps in the figures are illustrated for simplicity and clarity and have not necessarily been rendered according to any particular sequence. For example, steps that may be performed concurrently or in different order are illustrated in the figures to help to improve understanding of embodiments of the present invention.
The present invention may be described herein in terms of functional block components and various processing steps. Such functional blocks may be realized by any number of hardware or software components configured to perform the specified functions and achieve the various results. For example, the present invention may employ various housings, connectors, sensors, and the like, which may carry out a variety of functions. In addition, the present invention may be practiced in conjunction with any number of projectiles such as guided missiles or supersonic interceptors, and the system described is merely one exemplary application for the invention. Further, the present invention may employ any number of conventional techniques for launching and guiding projectiles, sensing environmental conditions, and the like.
Various representative implementations of the present invention may be applied to any system for guiding projectiles. Certain representative implementations may include, for example, a supersonic guided interceptor. Referring to
The projectile 200 comprises a moving system, for example to deliver a payload such as a warhead. The projectile 200 may comprise any system that is configured to travel, either by an on-board propulsion system or ballistically, such as a guided missile, a rocket, a bomb, a hit-to-kill interceptor, a kinetic energy penetrator, or a countermeasure. For example, the projectile 200 may comprise a multi-stage propulsion system comprising a booster stage and a secondary stage rocket motor enabling an intercontinental range. Alternatively, the projectile 200 may be configured with an air breathing engine adapted for a range of less than 200 miles.
The projectile 200 may also be suitably configured to travel at any appropriate speed or altitude. For example, the projectile 200 may be adapted to travel at or near transonic speeds. In another embodiment, the projectile 200 may travel at supersonic speeds. In a third embodiment, the projectile 200 may be suitably configured for at least stratospheric flight. The projectile 200 may also comprise additional elements such as a set of extendable tail fins or other control surfaces to provide stabilization and/or control the direction of flight.
The sensors 206 provide information relating to the surrounding environment to another system, such as a guidance system. The sensors 206 may comprise any suitable system that is responsive to radio frequency (RF) or light waves in the visible and/or non-visible spectra such as electromagnetic radiation detecting systems, laser guided seekers, digital camera lenses, optical positioning sensors, photodiode detectors, focal plane arrays, photodiodes, and the like. For example, referring to
The non-axisymmetric forebody 204 at least partially encloses a portion of internal elements located in a forward section of the projectile 200 such as a warhead, a fuze, a guidance system, a control system, or sensing equipment. The non-axisymmetric forebody 204 may comprise any suitable system configured to house or cover the elements such as an aerodynamic housing. The non-axisymmetric forebody 204 may also act as a protective covering and/or shield to the internal elements. For example, the non-axisymmetric forebody 204 may be suitably adapted to provide protection against particulate matter that may strike the projectile 200 during flight or the non-axisymmetric forebody 204 may protect against thermal loads which could damage internal elements or degrade the performance of the sensors 206. The non-axisymmetric forebody 204 may also be used to protect, shield, or insulate internal elements from stray frequencies, waves, or other interference such as RF radiation and electromagnetic interference.
The non-axisymmetric forebody 204 may be configured in any suitable size or dimension. The inner volume of the non-axisymmetric forebody 204 may vary depending on the type of projectile 200 the non-axisymmetric forebody 204 is connected to or on the number of elements located within the non-axisymmetric forebody 204. Referring to
The location of the sensors 304, 306 and the shape of the non-axisymmetric forebody 204 may result in greater moment loading for the non-axisymmetric forebody 204 than for the axisymmetric forebody 102. The greater loading on the non-axisymmetric forebody 204 may be due at least in part to pressure forces exerted on a curved upper portion 312 of the non-axisymmetric forebody 204 which do not exist on the traditional axisymmetric forebody 102. The pressure forces may be exerted along the curved upper portion 312 in one or more phases of flight such as during launch and/or during in-flight maneuvers. For example, an interceptor traveling at greater than supersonic velocity may experience a dramatic increase in pressure loads along the curved upper portion 312 during maneuvers associated with terminal phase interception of a target due at least in part to the mass of each sensor and its respective location within the non-axisymmetric forebody 204 and the addition of a payload to a forward portion of the non-axisymmetric forebody 204 or nosecone 208.
Additionally, the alignment of the forward sensor 306 and/or payload in relation to the projectile body 202 and the longitudinal axis 210 may increase the likelihood of dynamic jitter and smearing on the forward sensor 306 reducing the effectiveness of the projectile 200. To counter this potential, the non-axisymmetric forebody 204 may require additional structural stiffening and/or increased resistance to bending moments. For example, referring to
The non-axisymmetric forebody 204 may comprise any suitable material such as metal, plastic, elastomer, composite, or any suitable combination thereof. The non-axisymmetric forebody 204 may also comprise a combination of different materials which may be coupled together and adapted to perform different functions. For example, in one embodiment, the non-axisymmetric forebody 204 may comprise a window 302 section bonded to the strengthening member 310 section forming a one-piece structure. A single seal located at the transition between the non-axisymmetric forebody 204 and the body of the projectile 200 may be used to isolate internal components from the environment.
The window 302 acts as a transparent surface disposed between at least one of the sensors 304, 306 and the exterior of the projectile 200. The window 302 may comprise any system that is configured to be substantially transparent to a passing energy wave over a particular frequency or range of frequencies. The window 302 may be comprised from a variety of RF transparent materials such as composites or ceramics depending upon a particular application. For example, in one embodiment the window 302 may be comprised of an organic resin such as Bismaleimide, Cynate Ester, Polyimide, or Phthalonitrile.
During flight of the projectile 200, operating temperatures on the surface of the non-axisymmetric forebody 204 may exceed 400 degrees Fahrenheit creating ablation concerns. Ablation resulting from increased surface temperatures on the window 302 or across the non-axisymmetric forebody 204 may affect the reliability of the sensors 304, 306. The window 302 may therefore also be configured to incorporate a thermal protection system (TPS). The TPS may comprise any suitable method for increasing the heat tolerance of the window 302 or for dissipating heat from the window 302. For example, in one embodiment, a glass or quartz reinforced organic composite may be used when the window 302 is subjected to high thermal shock loading. In another embodiment, the window 302 may be subject to longer term high temperature thermal soaks of approximately 2,000 degrees Fahrenheit during supersonic or transonic flight and suitable high temperature materials such as polymeric silicone may be used.
The window 302 may be formed by any suitable fabrication method such as resin transfer molding, filament winding, or similar composite lay up processes. The window may also be formed to at least substantially create the non-axisymmetric forebody 204 shape. For example, the window 302 may comprise the final shape and size of the non-axisymmetric forebody 204 and be suitably configured to attach to the forward end of the projectile 100 and/or a nosecone 208.
The strengthening member 310 increases the structural capabilities of the non-axisymmetric forebody 204. The strengthening member 310 may comprise any suitable system for improving structural qualities such as a beam, longitudinal stiffeners, or a fiber reinforced composite layer. For example, referring to
The strengthening member 310 may be disposed immediately adjacent to at least a portion of the window 302. For example, referring again to
The strengthening member 310 may also be configured to incorporate electrical cabling. The cabling may be used to provide power to or send and receive signals from the sensors 304, 306. Referring to
In a second embodiment, the strengthening member 310 may comprise an integrated cabling system such as a length of flex cable disposed within the overall strengthening member 310 laminate. The integrated cabling system may or may not be configured to provide additional structural capabilities to the strengthening member 310.
The window 302 and the strengthening member 310 may be coupled together by any suitable method such as with mechanical fasteners or adhesively. For example, referring to
In operation, a non-axisymmetric forebody 204 may be connected to a forward portion of a projectile 200. The non-axisymmetric forebody 204 may house or cover one or more sensors 304, 306 which may be used to guide the projectile 200 to a target. The non-symmetric design of the non-axisymmetric forebody 204 allows each sensor 304, 306 to operate in an offset configuration reducing the likelihood of operational interference between sensors 304, 306.
During flight, the non-axisymmetric forebody 204 may be subjected to increased bending loads due to unequal forces along the surface of the non-axisymmetric forebody 204. For example, if the projectile 200 has to perform a course correction at a high speed, such as at or above the transonic range, an upper surface of the non-axisymmetric forebody 204 may experience pressure loading which could significantly impact targeting performance of the projectile or damage the non-axisymmetric forebody 204.
A strengthening member 310 may be incorporated into a portion of the non-axisymmetric forebody 204 to increase structural performance. In one embodiment, the strengthening member 310 may be integrated into a lower portion of a window 302 assembly. The strengthening member 310 may be suitably adapted to provide increased stiffness against bending moments created by forces along the upper portion of the non-axisymmetric forebody 204.
In the foregoing specification, the invention has been described with reference to specific exemplary embodiments. Various modifications and changes may be made, however, without departing from the scope of the present invention as set forth in the claims. The specification and figures are illustrative, rather than restrictive, and modifications are intended to be included within the scope of the present invention. Accordingly, the scope of the invention should be determined by the claims and their legal equivalents rather than by merely the examples described.
For example, the steps recited in any method or process claims may be executed in any order and are not limited to the specific order presented in the claims. Additionally, the components and/or elements recited in any apparatus claims may be assembled or otherwise operationally configured in a variety of permutations and are accordingly not limited to the specific configuration recited in the claims.
Benefits, other advantages and solutions to problems have been described above with regard to particular embodiments; however, any benefit, advantage, solution to problem or any element that may cause any particular benefit, advantage or solution to occur or to become more pronounced are not to be construed as critical, required or essential features or components of any or all the claims.
As used herein, the terms “comprise”, “comprises”, “comprising”, “having”, “including”, “includes” or any variation thereof, are intended to reference a non-exclusive inclusion, such that a process, method, article, composition or apparatus that comprises a list of elements does not include only those elements recited, but may also include other elements not expressly listed or inherent to such process, method, article, composition or apparatus. Other combinations and/or modifications of the above-described structures, arrangements, applications, proportions, elements, materials or components used in the practice of the present invention, in addition to those not specifically recited, may be varied or otherwise particularly adapted to specific environments, manufacturing specifications, design parameters or other operating requirements without departing from the general principles of the same.
This application claims the benefit of U.S. Provisional Patent Application No. 61/076,069, filed Jun. 26, 2008, and incorporates the disclosure in its entirety by reference.
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