Patent Application
20150122113
Rocket launchers have been widely used to transport and fire a payload of one or more rockets at a given target. These rocket launchers have been used on a variety of land and air vehicles acting as a firing platform for the rocket launcher. However, until recently the rockets used in these rocket launchers have been relatively primitive aim-and-shoot type rockets with no guidance or no intelligent or smart communication with the rocket beyond a firing mechanism triggering the launch of the rocket from the launcher. Part of the reason for this is that electrical connections between the rocket and the launcher are subjected to extreme conditions, particularly upon rocket launch. With the advancement of rockets and their ability to comprise on-board guidance and other technology, there is a need for reliable electrical communication between the rockets and rocket launchers.
Features and advantages of the invention will be apparent from the detailed description which follows, taken in conjunction with the accompanying drawings, which together illustrate, by way of example, features of the invention; and, wherein:
Reference will now be made to the exemplary embodiments illustrated, and specific language will be used herein to describe the same. It will nevertheless be understood that no limitation of the scope of the invention is thereby intended.
As used herein, the term “substantially” refers to the complete or nearly complete extent or degree of an action, characteristic, property, state, structure, item, or result. For example, an object that is “substantially” enclosed would mean that the object is either completely enclosed or nearly completely enclosed. The exact allowable degree of deviation from absolute completeness may in some cases depend on the specific context. However, generally speaking the nearness of completion will be so as to have the same overall result as if absolute and total completion were obtained. The use of “substantially” is equally applicable when used in a negative connotation to refer to the complete or near complete lack of an action, characteristic, property, state, structure, item, or result.
As used herein, “adjacent” refers to the proximity of two structures or elements. Particularly, elements that are identified as being “adjacent” may be either abutting or connected. Such elements may also be near or close to each other without necessarily contacting each other. The exact degree of proximity may in some cases depend on the specific context.
An initial overview of technology embodiments is provided below and then specific technology embodiments are described in further detail later. This initial summary is intended to aid readers in understanding the technology more quickly but is not intended to identify key features or essential features of the technology nor is it intended to limit the scope of the claimed subject matter.
Rocket launchers, as discussed above, have historically been simple point-and-shoot mechanisms which have, in the past, shot only “dumb” rockets that fire in the direction pointed when fired. Recent advancements in ballistics and smart missiles have enabled existing rocket launchers to be retrofitted to contain smart rockets with onboard guidance systems. With the application of new smart rockets in existing launching systems different forms of electrical connection have been established between an end control system and the guidance system or guidance head on each individual rocket. However, this connection between the rocket, generally located somewhere between the rocket and the rocket launcher, is typically subjected to extreme conditions, namely the exhaust or rocket blast, upon launch of the rocket from the rocket launcher. The connector on the rocket launcher, hereinafter referred to as the launcher connector, as subjected to high intensity blasts, particularly in the event of numerous launches over time, may become damaged and unable to operate correctly. Further, rocket launchers and rockets may often be utilized in war or battle scenarios where reloading times may need to be reduced to a minimum in order to allow the vehicle or other platform firing the rocket to return to a ready-to-fire state as soon as possible.
The present invention provides a rocket launching system comprising a guidance section connector interface system capable of providing or facilitating a “smart” connection between the rocket and the rocket launcher (and ultimately the end control system), while at the same time preserving the integrity of the launcher connector to facilitate repetitive “smart” rocket launches. Some embodiments of the rocket launching system and the guidance section connector interface system can further allow easy handling and quick re-loading capabilities.
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Further, a dummy rocket shroud (not shown) may be provided opposite the rocket connector shroud 120 through which the rocket connector 122 is affixed. This dummy shroud can be provided cover the portion of the guidance section connector interface associated with the rocket 110, for example, to equalize wind resistance or drag on each side of the rocket 110 during flight after launch.
The second connection 224 can be designed to be the dominant connection over the first connection 124. Stated differently, the first connection 124 can be designed to separate or decouple in favor of the second connection 224 upon launching of the rocket 110. Configuring the second connection 224 in this manner ensures that when the rocket 110 is launched, the connector saver 220 will remain connected or coupled to the launcher connector 230, thus allowing the connector saver 220 to protect the launcher connector 230 by shielding the launcher connector 230 from the blast of the rocket 110. In one aspect, the connector saver 220 can be configured to receive the launcher connector 230 within an interior portion of the connector saver 220, thus causing a portion of the connector saver 220 to extend around and about the launcher connector 230, thus serving as a shroud or protector situated about the launcher connector 230.
It will be recognized by those skilled in the art that a variety of forms or types of interfaces or connections can be used to provide a suitable connection between the connector saver 220 and the launcher connector 230, so long as the first connection 124 is designed to separate or decouple in favor of the second connection 224. In one exemplary embodiment, the first connection 124 can comprise a type of press, friction, or interference fit, while the second connection 224 can comprise an automatic locking or coupling mechanism that dominates the first connection 124 by facilitating decoupling of the first connection during launch of the rocket while maintaining coupling of the second connection 224. Exemplary connections contemplated herein for forming the first connection 124 include, but are not limited to, press fit, friction fit, or interference fits including interlocking lip and corresponding hollows, each of which may or may not require some level of plastic or elastic deformation to form the connection. Exemplary connections contemplated herein for forming the second connection 224 include, but are not limited to, automatic locking or coupling mechanisms, press fit, friction fit, interference fit, and others, including those taught with respect to the first connection 124, provided these are made to be dominant over the first connection 124 such that they do not release prior to or before the second connection 224.
More specifically, the coupling or locking mechanisms contemplated for forming the second connection 224 may include quick-connect type systems with sliding lock collars, such as those used for pneumatic air hose connections. Additional connections for the second connection 224 may include snap rings, push-pull type connections, electromagnets, threaded collars or any other type of auto locking connector as will be recognized by one of ordinary skill in the art. It has been discovered that quick-connect type systems are of some advantage as they provide a reliable connection and may be attached and removed relatively quickly.
It will be appreciated that the various connecting components within the guidance section connector interface 200 (i.e., those components supported on the rocket and those supported on the rocket launcher) should be properly aligned to achieve an effective and proper connection. In one aspect, alignment can be achieved prior to locating the rocket 110 in its fully loaded position. It will also be recognized that common rocket launchers have a plurality of rocket guide sleeves 154 arranged in a tight proximity one to another which may result in a degree of difficulty in easily recognizing which launcher connector 230 corresponds to which rocket guide sleeve 154. In order to facilitate quick loading and reloading of a plurality of rockets, and to ensure proper alignment of the components of each of the guidance section connector interface systems 200 respectively associated with the several different rockets and the rocket launcher, the rocket launching system 10, or each of the guidance section connector interface systems, can further comprise a clocking system. The clocking system can be configured to facilitate alignment of the rocket 110 in the correct angular orientation or position within the rocket guide sleeve 154 of the rocket launcher 150 into which the rocket 110 is inserted, and about the longitudinal axis of the rocket guide sleeve 154. In one embodiment of the present invention the clocking system can comprise a slot 156 formed into the front face 152 of the rocket launcher 150. A guide 112, which can be located on and supported about the outer surface of the rocket 110, can be configured to correspond in size and shape to, and fit within, the slot 156. This can be achieved with a relatively small clearance. The guide 112 and slot 156 can ensure proper clocking and alignment of the rocket connector 122 (having coupled thereto the connector saver 220) and the launcher connector 230 as the rocket 110 is inserted completely into the rocket launcher 150 in the aft direction. This can be achieved as the guide 112 will be caused to contact the front face 152 of the rocket launcher 150, the guide acting as a stopper preventing further insertion of the rocket 110 into the guide sleeve 154 of the rocket launcher 150 if the angular orientation of the rocket 110 relative to the guide sleeve 154 is out of an acceptable range. To achieve full insertion of the rocket 110 into the guide sleeve 154, the rocket can be rotated about its longitudinal axis to align the guide 112 up with the slot 156, wherein the guide 112 can be caused to pass through the slot 156 to achieve complete insertion of the rocket 110 within the rocket launcher 150. In one exemplary embodiment, the clocking system may be configured, such that the guide 112 and slot 156 are located about the rocket 110 and rocket launcher 150, respectively, so that the guide 112 passes through the slot 156 at a point in time just prior to connection of the rocket connector 122 and the connector saver 220 with the launcher connector 230. In another exemplary embodiment, the clocking system can comprise a guide that runs along the rocket and that extends to an end of the rocket, such that alignment is achieved before any part of the rocket is received within the guide sleeve 154 of the rocket launcher 150.
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In one exemplary embodiment, the funnel 270 can comprise a tapered conical interior 272 of a larger diameter than the launcher connector 230, which can be configured to guide the connector saver 220 into proper alignment with the launcher connector 230 and any pins and pin holes associated therewith (e.g., pins of the connector saver 220 designed for insertion into pin holes 232 of the launcher connector 230). The funnel 270 may be permanently affixed to the connector saver 220 using any suitable means, such as by gluing or epoxying. In another embodiment, the funnel 270 can be unitarily formed with the connector saver 220. In still another embodiment, the funnel 270 can be removably coupled to the connector saver 220, such as via threads. The present embodiment depicts the use of threads 274 for affixing the funnel 270 to the connector saver 220 using a threaded connection. However, those skilled in the art will recognize that other types of suitable means may be used for removably affixing the funnel 270 to the connector saver 220.
For purposes of the present invention, the connection between the connector saver 220 and the funnel 270 can be configured to be more dominant than the first connection 124 in order to ensure the connector saver 220 (and the funnel 270) remain on the launcher connector 230 during a rocket launch as the guidance section connector interface is caused to separate or decouple. In the event the funnel 270 is used, the funnel 270 can be configured and caused to engage and mate with the launcher connector 230 in any manner similar to the connector saver 220 as discussed above, including push-pull and quick-connect type systems. In addition to the connection types discussed above with respect to the connector saver 220 and the launcher connector 230, the funnel 270 may have tapered tabs 276 on an interior surface which may snap onto or over a flange edge 234 of the launcher connector 230, such that the funnel 270 is caused to snap onto the launcher connector 230 as the rocket 110 is loaded into the rocket launcher 150 and the various components and connection elements of the guidance section connector interface 200 are caused to couple together.
Additionally, it should be noted that the connector saver 220 and funnel 270 components can be formed of any suitable material. In one example, aerospace plastic can be used, which has proven to be particularly effective as it is relatively easy to machine and it is reliable.
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The slideable shaft 232 can be supported at a second end by a shaft receiver 240. The slideable shaft 232 can be inserted into an interior portion of the shaft receiver 240 and rotatably and/or slidably supported therein, the slideable shaft 232 specifically being configured to slide co-axially relative to the shaft receiver 240. This sliding function allows the launcher connector 230 to be initially in an outward position, and then to move inward as the rocket 110 is inserted into the rocket launcher 150. Specifically, the launcher connector 230 can be initially positioned a certain distance forward from the front face 152, allowing for an electrical connection to be established prior to full insertion of the rocket 110. This ability to position the launcher connector 230 farther forward initially, and then to subsequently be able to be caused to slide back during rocket insertion allows for a certain degree of error in placement of the rocket connector 122 on each individual rocket 110, such as to facilitate a proper and operable electrical connection in the event a rocket 110 is not fully inserted into the rocket launcher 150.
The guidance section connector interface 200 can further comprise a biasing member, such as a rubber member, a spring 260, etc., configured to bias the sliding shaft 232 and therefore the launcher connector 230 in the forward direction. This spring 260 can provide a biasing force sufficient to ensure a proper connection and ensure that the inserted rocket 110 and corresponding rocket connector 122 does not just push the launcher connector 230 down without establishing an electronic connection. It should be appreciated that the shaft receiver 240 may receive the sliding shaft 232 into a hollow within the shaft receiver 240 or the shaft receiver 240 may be received in a hollow within the sliding shaft 232, so as to allow this relative sliding motion with the spring 260 providing the discussed biasing force. It should be noted that the spring can be appropriately sized and configured so that a user of the rocket launcher is still able to push the rocket in the aft direction after the electrical connection is made to cause engagement of a detention mechanism (not shown) as part of a normal operation of the rocket launcher.
The shaft receiver 240 can be coupled to a coupler 250 which can be affixed to the rocket launcher 150. The connection between the coupler 250 and the shaft receiver 240 may be provided via a hinge assembly that is also part of the guidance section connector interface system, the hinge assembly comprising a pin 252 operable with the coupler that allows the shaft receiver 240 (and the slideable shaft 232) to pivot relative to the coupler 250, which pivoting function facilitates the capability of the slideable shaft 232 (and the launcher connector 230) to float in a bi-directional manner relative to the hole 162 located on the front face 152 of the rocket launcher 150, as previously discussed. Additionally, clearance between the coupler 250 and the slideable shaft 240 can be provided by the hinge assembly, and particularly gaps 254A and 254B. These gaps 254A and 254B can permit the shaft receiver 240 to float in different directions, therefore allowing the slideable shaft 162 to similarly float. More specifically, the hinge assembly can be configured to permit the shaft receiver 240 and slideable shaft 232 (and launcher connector 230) to rotate along a first axis (e.g., a longitudinal axis of the slideable shaft 232) as well as along a second axis (e.g., axis into the page of
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In addition, one skilled in the art will recognize that the launcher connector may be configured to be compatible with prior point-and-shoot dumb rockets, as discussed above, in addition to “smart” rockets as contemplated herein, wherein a connector saver that function as discussed herein may be similarly implemented on the rocket connection of the point-and-shoot dumb rocket.
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Prior to insertion of the rocket into the rocket launcher, a connector saver is installed onto the rocket connector thus forming a first electrical connection. As discussed above, this connection may be of any type; however, a friction fit has shown some advantages with regard to connection strength reliability. As the rocket is slid into the rocket launcher the connector saver mates with a launcher connector to form a second connection. As discussed above, this connection may be of any type; however, the second connection can be configured to dominate the first connection so as to ensure that the first connection separates or releases over the second connection. It should be noted that while any connection configurable to be stronger than the first connection is suitable, push-pull or quick-connect systems which lock when mated have provided advantages for ensuring proper strength of the connection while remaining easy to remove prior to re-loading the rocket launcher with a new rocket after firing a first rocket.
It is to be understood that the embodiments of the invention disclosed are not limited to the particular structures, process steps, or materials disclosed herein, but are extended to equivalents thereof as would be recognized by those ordinarily skilled in the relevant arts. It should also be understood that terminology employed herein is used for the purpose of describing particular embodiments only and is not intended to be limiting.
Reference throughout this specification to “one embodiment” or “an embodiment” means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment of the present invention. Thus, appearances of the phrases “in one embodiment” or “in an embodiment” in various places throughout this specification are not necessarily all referring to the same embodiment.
As used herein, a plurality of items, structural elements, compositional elements, and/or materials may be presented in a common list for convenience. However, these lists should be construed as though each member of the list is individually identified as a separate and unique member. Thus, no individual member of such list should be construed as a de facto equivalent of any other member of the same list solely based on their presentation in a common group without indications to the contrary. In addition, various embodiments and example of the present invention may be referred to herein along with alternatives for the various components thereof. It is understood that such embodiments, examples, and alternatives are not to be construed as de facto equivalents of one another, but are to be considered as separate and autonomous representations of the present invention.
Furthermore, the described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments. In the following description, numerous specific details are provided, such as examples of lengths, widths, shapes, etc., to provide a thorough understanding of embodiments of the invention. One skilled in the relevant art will recognize, however, that the invention can be practiced without one or more of the specific details, or with other methods, components, materials, etc. In other instances, well-known structures, materials, or operations are not shown or described in detail to avoid obscuring aspects of the invention.
While the foregoing examples are illustrative of the principles of the present invention in one or more particular applications, it will be apparent to those of ordinary skill in the art that numerous modifications in form, usage and details of implementation can be made without the exercise of inventive faculty, and without departing from the principles and concepts of the invention. Accordingly, it is not intended that the invention be limited, except as by the claims set forth below.
