Patent Application
20230249092
The present invention relates to fields of rocketry and, in particular, model rocketry, and rocket nose cones.
Modern model rocketry rose to prominence in the early 1950s, due to heightened interest driven by the “space race,” a competitive effort by the United States and Soviet Union to advance the exploration of outer space. Hobbyists' enthusiasm for model rocketry was not always tempered by sufficient expertise and safety, and critics soon emerged, noting the dangers of volatile liquid rocket fuels used by amateurs. For example, G. Harry Stine, of Popular Mechanics, noted these dangers regularly in articles during this time period. Children in particular are drawn to model rocketry, due to their active imaginations and interest in the unknown frontier of outer space, but their appreciation for safety is far lower than that of adults.
Amid this backdrop, Orville and Robert Carlisle, two brothers with expertise in pyrotechnics and model rocketry, developed a new, safer form of model rocket engine, in a standard form to be inserted into a re-usable model rocket body. See U.S. Pat. No. 2,841,084, entitled “Toy Rocket,” to Orville H. Carlisle. This new model rocket engine was intended to be single-use and disposable, preventing tampering, refueling or tinkering by the amateur hobbyists. Consulting further with model rocketry pioneer Vernon Estes, the brothers developed an even safer, more reliable form of the engine, using safer, solid rocket fuels. Eventually, Estes began an independent company based on these model rocketry improvements—Estes Industries.
Critics, including Stine himself, were impressed with these safety improvements, and model rocketry became ever more popular, and remains an extremely popular hobby to the present day. Throughout the intervening decades, space flight and model rocketry have experienced regular resurgences in interest, and to this day, Estes Industries leads the amateur model rocketry market.
Yet, notwithstanding this considerable time period, the essential design and components of model rockets still strongly resemble those of model rockets in the 1950s and 1960s.
The present invention presents a number of improvements and new designs for model rockets, as will be set forth in greater detail below.
It should be noted that some of the disclosures set forth as background, such as, but not limited to, the above language under the heading “Background,” do not relate exclusively to prior art and the state of the art in the field(s) of the invention, and should not be construed as an admission with respect thereto.
Systems, devices and methods for model rocketry are provided. According to some aspects of the invention, new forms of model rocket nose cones, other model rocket components, and methods for their use, are provided. In some embodiments, a new form of reversibly-divisible nose cone is provided, including a plurality of housing sections (e.g., 2 (“two”) housing sections) and, in some embodiments, a locking mechanism(s) configured to hold the plurality of housing sections together. In some embodiments, such a locking mechanism is unlocked, and the housing sections are separated, at least in part, by the fluid dynamics of the surrounding air flow (e.g., greater exposure to air resistance during and after an ejection phase) during model rocket flight. In some embodiments, such a locking mechanism is unlocked, at least in part, by an ejection charge issuing from a model rocket engine. In some embodiments, such a locking mechanism is unlocked, at least in part, by tension from shock cord(s) of a model rocket. In some embodiments, a plurality of such locking mechanisms are provided for a single nose cone. In some such embodiments, such locking mechanism(s) are provided at particular points where the plurality of housing sections are joined. For example, in some embodiments, such a locking mechanism is provided on or about a tip of the nose cone. As another example, in some embodiments, such a locking mechanism is provided on or about a lower section of the nose cone. However, in some embodiments, such a locking mechanism is provided over a wider area of the plurality of housing sections. For example, in some embodiments, such a locking mechanism is provided along a length of abutting parallel edges of such a plurality of housing sections being held together by the locking mechanism.
In some embodiments, such a locking mechanism includes one or more tab(s) and pockets configured to interlock with such tabs. In some embodiments, such tab(s) and pocket(s) are in the form of a tongue-and-groove locking mechanism. In some such embodiments, such a tongue-and-groove of such a locking mechanism are each flat-surfaced, interfacing with each other at a flat angle, and are held together by surface friction. In some embodiments, such a locking mechanism is in the form of a dovetail joint. In some embodiments, such a locking mechanism is in the form of one or more interlocking hooks. In some embodiments, such a locking mechanism is in the form of one or more interlocking barbs.
In particular, in some such embodiments, a plurality of shock cord mounting arms, extending, one each, from a lower housing wall of each of the plurality of housing sections, are included. In some such embodiments, such shock cord mounting arms are curved or angled. In some such embodiments, such shock cord mounting arms include at least one mounting point, for connecting one or more model rocket shock cord(s). In some such embodiments, such a mounting point is an eyelet, through which a shock cord is threaded. In some such embodiments, the shock cord(s) are then knotted, tied or otherwise attached to the mounting points in preparation for a model rocket flight. In some embodiments, such a shock cord(s) is/are wound around such a plurality of shock cord mounting arms in preparation for a model rocket flight. During an ejection phase of such a model rocket flight, the shock cord(s) then unfurl from the plurality of shock cord mounting arms, aiding in the separation of the plurality of housing sections.
In some embodiments, the plurality of housing sections may include a number of additional aspects. For example, in some embodiments, at least one of the plurality of housing sections includes one or more gas-channeling openings, permitting air and/or an ejection charge to enter and aid in separating the plurality of housing sections. Examples embodiments of some such openings are set forth below, in reference to
As another example, in some embodiments, the shock cord mounting arms may be provided in the form of a spool, about which one or more shock cord(s) may be wound. In some such embodiments, when such a shock cord is so wound around such a spool, the inward pressure of the shock cord aids in pressing the plurality of housing sections together until ejection. For example, one such example of such a type of housing section forming a spool is provided in
Further aspects of the invention will be set forth in greater detail, below, with reference to the particular figures.
The features and advantages of the example embodiments of the invention presented herein will become more apparent from the detailed description set forth below when taken in conjunction with the following drawings.
The example embodiments of the invention presented herein are directed to systems, devices and methods for model rocketry, including reversibly-divisible model rocket nose cones with a plurality of housing sections, other model rocket components, and systems and methods for their use, which are now described herein. This description is not intended to limit the application of the example embodiments presented herein. In fact, after reading the following description, it will be apparent to one skilled in the relevant art(s) how to implement the following example embodiments in alternative embodiments.
As with other model rocket systems, a model rocket system using the nose cone of the present invention may involve rocket flights in conventional phases, including: 1) a launch phase, 2) a flight phase, 3) a peak phase, 4) an ejection phase (e.g., deploying a parachute, streamer or other drag device), 5) a descent phase, and 6) a recovery phase. During such an ejection phase, an ejection charge from an upper part of a single-use solid rocket fuel engine (or other form of rocket engine) may be directed upward, toward a nose cone mounted on the main body of the rocket, in some embodiments. In some embodiments, when joined, reversible joint 103 has a sufficient strength to hold housing section 101 and housing section 102 together when the nose cone they form is mounted on the main body of a rocket, throughout a launch phase, flight phase and peak phase of a model rocket flight. However, in some embodiments, reversible joint 103 will cease holding housing section 101 and housing section 102 together, and increased forces (air resistance, centrifugal and/or other forces) cause housing section 101 and housing section 102 to separate, after the ejection phase. For example, in some embodiments, housing section 101 and housing section 102 are more greatly exposed to an environment external to a main body of a rocket, after such an ejection phase, bringing such forces to bear. In some embodiments, housing section 101 and housing section 102 may each include multiple, at least partially rounded or otherwise curved housing portions: A) an upper housing portion 107, which is at least partially conical, to be exposed during a flight phase and a peak phase of a model rocket flight, and B) a lower housing portion 109, including a neck 110 (configured to insert into a main body of a rocket) which is at least partially cylindrical, having a smaller, inset outer surface diameter than the upper portion. In some embodiments, the outer surface diameter of such an upper housing portion has a cylindrical outer surface with a diameter that matches, or substantially matches, the cylindrical outer surface diameter of a main body of a model rocket. Thus, in some embodiments, a lip 111 formed at the transition between the upper housing portion 107 and the lower housing portion 109 abuts, and forms a flush surface with, an upper edge of a main body of a rocket, which is a hollow cylinder. Such embodiments are discussed in greater detail below, in reference to
In some such embodiments, a plurality of shock cord mounting arms 113 are included, extending, one each, from lower housing walls 115 of each of the plurality of housing sections 100. In some embodiments, the shock cord mounting arms 113 are attached to, and/or integrated with, lower housing walls 115. In some such embodiments, such shock cord mounting arms are curved or angled, for example, due to mounting arm bend(s) 117. In some such embodiments, such shock cord mounting arms include at least one mounting point, for connecting one or more shock cord(s). For example, in some such embodiments, such a mounting point is an eyelet, such as example shock cord mounting eyelet 119 and example shock cord mounting eyelet 121. In some embodiments, to connect a model rocket shock cord(s) to each of the plurality of shock cord mounting arms 113, the shock cord(s) are threaded through example shock cord mounting eyelet 119 and/or example shock cord mounting eyelet 121. In some such embodiments, the shock cord(s) are then knotted, tied or otherwise attached in preparation for a model rocket flight. In some embodiments, such a shock cord(s) is/are wound around such a plurality of shock cord mounting arms in preparation for a model rocket flight.
As with any other embodiment, example, and or figure set forth in the present application, the embodiments set forth in, and discussed with reference to,
Also, pictured in greater detail in the view of
In some embodiments, assembled model rocket 301 may include a number of additional components, at least some of which are not conventional. For example, in some embodiments, multiple shock cords, and/or a new form of split-ended shock cord 309, may be included. In such embodiments, such a shock cord includes multiple ends 311, at least one of which may be mounted to an interior surface 313 of main body 305 (e.g., glued onto main body 305 with on a shock cord mounting tab 315), but each of a plurality of nose cone-attaching ends 317 of split-ended shock cord 309 being threaded through and/or attached to, one of the plurality of housing sections 100 of nose cone 303. As discussed above, and as pictured, in some embodiments, shock cord(s) may be separately attached to each of the plurality of housing sections 100 via shock cord mounting arms 113.
One conventional component of a model rocket which has been omitted in the present figure is protective wadding, which might ordinarily be provided within main body 305 at or about the location shown as wadding area 319. Especially in embodiments where a parachute, such as example parachute 320, is held within nose cone 303 (e.g., in payload bay 321), nose cone 303 may provide sufficient protection from an ejection charge emanating upward through main body 305, as shown by example vector arrow 323 from single-use, solid fuel rocket engine 325, that wadding is not necessary to protect it (or any other drag device or other payload object(s).
Other more conventional components of model rocket 301 may include a rocket motor holding bracket 327, guiding fins 329, and a launch rod guide 331. Of course, in various embodiments, other conventional and unconventional rocket components may also be included. For example, in some embodiments, another form of rocket engine or motor, other than single-use, solid fuel rocket engine, may be included in model rocket 301 (e.g., a repackable and/or refillable rocket engine). In some embodiments, amateur or professional grade rocket components may instead be included, in addition to, or instead of, model rocket components.
At step 401, in some embodiments, a plurality of housing sections for forming a reversibly-divisible nose cone is provided. Examples of such a plurality of housing sections are provided elsewhere in this application (for example, as housing section 101 and housing section 102, set forth above). Proceeding to step 403, in some embodiments, the user(s) proceeds to add an object(s) to an internal payload bay formed by internal void(s) (e.g., such as internal void(s) 201) of each of the plurality of housing sections. Proceeding next to step 405, the user(s) then proceed to assemble a reversibly-divisible nose cone by locking each of the plurality of housing sections together (e.g., using any of the locking mechanism(s) set forth in the present application, in various embodiments), creating such a payload bay enclosing such an object(s).
Proceeding to step 407, the user(s) obtain a model rocket shock cord (such as example split-ended shock cord 309) and attach the end(s) of the model rocket shock cord to shock cord mounting arm(s) attached to one or more of the plurality of housing sections (e.g., at a lower surface of the plurality of housing sections). In some embodiments, the user(s) may also, or alternatively, wind the shock cord around the shock cord mounting arms and, in some embodiments, such winding aids in holding the plurality of housing sections together until an ejection phase of a rocket flight. Prior to that time, however, in step 409, the user(s) may next provide additional parts of a model rocket, such as those set forth in reference to
As discussed elsewhere in this application, following launch the model rocket may obtain a peak altitude during flight (e.g., after the engine propellant has been exhausted), in step 413. In some embodiments, the nose cone may then be ejected from the main body of the model rocket and more fully exposing it to atmosphere around the model rocket (e.g., by the firing of an ejection charge from the top end of the model rocket engine, directed at the nose cone), in step 415. In some embodiments, forces from that exposure then come to bear on the nose cone, reversing the locking mechanism(s), and dividing the nose cone into a plurality of nose cone sections (which are no longer directly attached and/or fixed in orientation to one another, in some embodiments). As a result, in step 417, the object(s) held within the payload bay are then released into the atmosphere, in some embodiments. For example, in some embodiments, such an object(s) is a parachute, streamer, or other drag device, tethered to the plurality of housing sections (e.g., to an interior wall of the payload bay). The model rocket may then enter a descent phase, in step 419, after which it may be recovered by the user(s), in step 421. In some embodiments, after the steps 401 et seq. have been completed, the process restarts.
Of course, the embodiments set forth herein are only examples of the wide range of options for implementing new forms of divisible model rocket nose cones, and other rocket components, falling within the scope of the invention, as will be readily apparent to a person of ordinary skill in the art implementing the present invention. For practical reasons, a particular example order and number of steps have been set forth as steps 401 et seq., but it will also be readily understood that, in various embodiments, fewer, more or a different order of steps may be followed, still within the scope of the invention.
Also pictured in the present figure, a new form of locking mechanism is provided, including at least one male tab 505, of housing section 501, which fits a complementary female notch 507, of housing section 502. In some embodiments, male tab 505 can be snapped into place within female notch 507, creating a dovetail joint locking the plurality of housing sections together, and forming a reversibly-divisible nose cone.
Although some of the above embodiments include ejection charge channeling holes in the lower walls of a nose cone housing(s), it should be understood that, in some other embodiments, no holes whatsoever are provided in the lower walls of a nose cone housing(s). In some embodiments, a solid surface is provided for the lower walls of a nose cone housing(s).
It should be noted that, although examples of at least partially elliptical nose cone are provided—meaning, an elliptical in shape when viewed from the side (or having an “elliptical profile”) to be inserted to a particular depth pictured, is provided in figures of the present application, a number of different, other forms and shapes of nose cone, seated in different ways, and to different depths within a main body of a rocket (with or without a seamless transition) may instead be included, in other embodiments. For example, in some embodiments of any of the nose cone aspects of the present application, such a nose cone are rounded in shape when viewed from the side (having a “rounded profile”). As another example, in some embodiments of any of the nose cone aspects of the present application, such a nose cone is semi-elliptical in shape when viewed from the side (having an “a semi-elliptical profile”). As another example, in some embodiments of any of the nose cone aspects of the present application, such a nose cone has a long elliptical shape when viewed from the side (having an “a long elliptical profile”). As another example, in some embodiments of any of the nose cone aspects of the present application, such a nose cone has a parabolic shape when viewed from the side (having an “a parabolic profile”). As another example, in some embodiments of any of the nose cone aspects of the present application, such a nose cone has an ogive shape when viewed from the side (having an “an ogive profile”). As another example, in some embodiments of any of the nose cone aspects of the present application, such a nose cone has an at least partially cylindrical shape when viewed from the side (having an “a cylindrical profile”). As another example, in some embodiments of any of the nose cone aspects of the present application, such a nose cone has wing(s), a faring(s) and/or fin(s). As another example, in some embodiments of any of the nose cone aspects of the present application, such a nose cone includes a canopy. As another example, in some embodiments of any of the nose cone aspects of the present application, such a nose cone includes a bridge. As another example, in some embodiments of any of the nose cone aspects of the present application, such a nose cone includes a window (e.g., for mounting a camera inside the nose cone's payload bay). As another example, in some embodiments of any of the nose cone aspects of the present application, such a nose cone includes a capsule (e.g., for mounting a camera inside the nose cone's payload bay).
In addition, in some embodiments, housing section 800 includes ejection charge receiving pockets 807. In some embodiments, ejection charge receiving pockets 807 include angled walls 809, creating concavities 810, directing an ejection charge upward, among other benefits.
In addition, in some embodiments, again as set forth above for housing section 800, housing section 811 includes ejection charge receiving pockets, now shown as ejection charge receiving pockets 817. In some embodiments, ejection charge receiving pockets 817 include angled walls 819, creating concavities 821, directing an ejection charge upward, among other benefits.
In a virtually unlimited number of alternative embodiments, locking mechanism(s) may be provided at a wide variety of other locations, in a wide variety of numbers, patterns and arrangements, other than the examples specifically set in the present application. The examples set forth in the present application are merely examples, illustrating some principles of the invention.
Like certain other embodiments set forth in the present application, plurality of housing sections 1001 include a locking mechanism, in the present example, being in the form of reversible joints, such as example reversible joint 1007, including slanted male portions 1009 and a female pocket portion 1011, which fit one another. As with the example plurality of housing sections 1001, such joints do not line the entire interfacing area, along abutting parallel edges 1013, of each of the plurality of housing sections 1001. Instead, such joints are provided at particular points where the plurality of housing sections 1001 are to be joined. For example, in some embodiments, at least one such joint (for example, lower fastener 1015) is provided on or about the lower section 1019 of the plurality of housing sections 1001.
In addition, another form of lower fastener is formed by spool 1003, in some embodiments. For example, in some embodiments, each of the shock cord mounting arms 1005 include a lower tab 1021, each such lower tab including an exposed, lower shock-cord mounting eyelet, such as example eyelet 1023. In some such embodiments, after threading and/or tying the shock cord (not pictured) to each of such an eyelet, the shock cord may then be wound around the spool 1003 formed by conjoining plurality of housing sections 1001 and shock cord mounting arms 1005. In this way, and especially in embodiments where the shock cord includes an elastomeric material, spool 1003, with such a shock cord wound tightly around it, serves as a locking mechanism which is effective until an ejection charge ejects a nose cone formed from the conjoined plurality of housing sections, causing the shock cord to extend and unfurl from spool 1003, which then separates (along with plurality of housing sections 1001).
As with other embodiments of nose cone housing sections set forth in the present application, housing section 1101 includes an upper portion 1103, and a lower portion 1105. Also as with other example housing sections set forth in the present application, when joined together with another, similar housing section, housing section 1101 forms a nose cone, also with a corresponding upper portion and lower portion. For example, when so joined, upper portion 1103 forms a generally conically-shaped tip, and lower portion 1105 forms a generally cylindrical neck, due to the half-cylindrical shape of neck section 1107. As discussed above, such a cylindrical neck is configured to be inserted into a main body of a rocket, such as any of the main bodies for rockets discussed in this application. However, neck section 1107 is more greatly elongated than most other nose cone sections set forth in the present application, and more greatly elongated than traditional model rocket nose cones—that is the ratio of the length to width of neck section 1107 and lower portion 1105 generally, is greater than in most other nose cone section embodiments in the present application, and in the art.
In addition, as with some other embodiments of nose cone sections set forth in the present application, a spool section 1109 is included, about which a model rocket shock cord may be wound, in some embodiments. The diameter of spool section 1109 is narrower than other spool sections set forth in the present application, relative to the width of the upper portion 1103, lower portion 1105, than other embodiments of the present application. In addition, unlike other nose cone sections including integrated spool(s) set forth in this application, housing section 1101 includes a tapering transitional area 1111, between the spool section 1109 and a neck section 1107. As discussed above, this tapering transitional area 1111 forms an outward, sloped lower surface(s) of nose cone, when housing section 1101 is combined with another, similar housing section. When an ejection charge collides, upwardly, with such sloped lower surface, it may causing the ejection charge to press, and hold the housing sections together (at least initially during an ejection phase, as the nose cone is ejected from a main body of the rocket in which it was inserted).
As with other housing sections for nose cones set forth in this application, housing section 1101 may include any other features set forth elsewhere in this application, and in the art. For example, in some embodiments, an attachment point, such as threading hole 1215 may be included, about which a shock cord(s) may be tied, in some of such embodiments. In addition, in some embodiments, one or more interlocking tabs, such as example tab 1217, or example tabs 1117, and complementary pockets, such as example tab-receiving, interlocking pockets, such as example tab-receiving pocket 1119, may be included. Such a series of tabs, and pockets into which such tabs insert and interlock, may serve as a type of locking mechanism, temporarily joining multiple housing sections (e.g., two halves) to form a rocket nose cone, in accordance with some embodiments.
As with other embodiments of nose cone housing sections set forth in the present application, housing section 1301 includes an upper portion 1303, and a lower portion 1305. Also as with other example housing sections set forth in the present application, when joined together with another, similar housing section (not pictured, but would appear the same as housing section 1301 in some embodiments), housing section 1301 forms a nose cone, also with a similar corresponding upper portion and lower portion. In some such embodiments, such a similar housing section is identical to housing section 1301, to which housing section 1301 may be joined, and includes all structures and arrangements as discussed herein with respect to housing section 1301. In other embodiments, such a similar housing section is a mirror image structure to housing section 1301, to which housing section 1301 may be joined. When so joined together, upper portion 1303 forms a generally conically-shaped tip, and lower portion 1305 forms a generally cylindrical neck, due to the half-cylindrical shape of neck section 1307, similar in nature to other cylindrical neck structures set forth in the present application (such as, for example, the cylindrical neck set section 1107 forth in
As with other housing sections for model rocket nose cones set forth in the present application, in some embodiments, housing section 1301, and/or a similar housing section to which it may be joined, includes one or more shock cord mounting arms, such as the example shock cord mounting arm(s) 1309 (and/or similar or identical shock cord mounting arm(s) located on such another, similar housing section to housing section 1301 as discussed above), and/or, in some embodiments, other shock cord mounting structures. As with other shock cord mounting arms set forth in the present application, in some embodiments, shock cord mounting arm(s) 1309 may include one or more eyelets, such as example eyelet 1311, through which one or more shock cords may be threaded, and to which such shock cords may be tied, or otherwise bound, to shock cord mounting arm(s) 1309. For example, in some embodiments, to connect a model rocket shock cord(s) to such a shock cord mounting arm(s) 1309, the shock cord(s) are threaded through example eyelet 1311. In some such embodiments, the shock cord(s) are then knotted, tied or otherwise attached to eyelet 1311 in preparation for a model rocket flight and recovery. In some embodiments, the shock cord(s) are threaded through (but not tied to) example eyelet 1311, and then tied to the similar or identical eyelet present on the counterpart, other similar housing section to housing section 1301 (discussed above) prior to joining the two housing sections together in preparation for flight and recovery. In this way, upon ejection from an interior of a main body of a model rocket, e.g., at the apogee of flight, and greater exposure to wind, the shock cord permits the separation of the two sections forming the model rocket nose cone, in some embodiments, because the shock cord may pay out through example eyelet 1311.
In addition, in some embodiments, housing section 1301 includes one or more internal mounting arms, such as example internal mounting arm(s) 1315, located at least partially within a payload-carrying volume, such as example payload bay(s) 1317. In some such embodiments, additional device(s) may be provided within payload bay(s) 1317. For example, in some embodiments, a parachute or other model rocket recovery device may be so provided, held within payload bay(s) 1317, which may be released upon such a separation (as discussed above). In some embodiments, such additional device(s) may be connected to housing section 1301, for example, via a device tether or cord (not pictured) connected with such additional device(s). For example, in some embodiments, such a device tether or cord may be tied to example upper eyelet 1319, mounted on interior mounting arm(s) 1315, present within payload bay(s) 1317. Alternatively, or in addition, in some embodiments, for example, such a device tether or cord may be tied to a similar or identical upper eyelet, mounted on a similar or identical interior mounting arm attached to, or integral with, the housing section similar or identical to housing section 1301 (interlocked with housing section 1301 to form the nose cone (as discussed above)), which similar or identical interior mounting arm is therefore also present within payload bay(s) 1317. In some embodiments, payload bay(s) 1317 may include a payload bay configured to hold electronics (i.e., an “electronics bay” or “e-bay”). In some embodiments, devices provided within such an e-bay may include an electronic device, such as a camera, which, similarly to the recovery device set forth above, may be exposed and/or released from such an e-bay upon such ejection and separation of the two nose cone sections.
In some embodiments, such an electronic device may include a different form of connector than a tether or cord, such as a proprietary connector, for interfacing with upper eyelet 1319, or another connector disposed on a structural component of the payload bay(s) 1317.
In some embodiments, such a shock cord(s) is/are wound around any or all of the shock cord mounting arms present in preparation for a model rocket flight. And, in some embodiments, where at least one of the multiple shock cord mounting arms are included within each of the housing sections (i.e., housing section 1301, and such a similar housing section to which it is joined, as discussed above), such a shock cord, when so wound, may aid in conjoining the housing sections, at least, unless and until an ejection charge separates neck section 1307 from the interior of a main body of a rocket, in some embodiments.
As with other shock cord mounting arms set forth in the present application, in some embodiments, shock cord mounting arm(s) 1309 and/or internal mounting arm(s) 1315 may be attached to, or integrated with, the remainder of housing section 1301 at or about particular connection or mounting points or areas of housing section 1301.
However, in some embodiments, rather than being attached to or formed by shock cord mounting arm(s) 1309 and/or internal mounting arm(s) 1315, in some embodiments, as pictured, any or all of the eyelets discussed herein may each be a form of reversible connector hardware (e.g., in a proprietary format). In some such embodiments, such eyelets (and such reversible connector hardware) may include a stronger and/or denser material (e.g., a metal) than materials present elsewhere in housing section 1301 (e.g., formed from a polymer, such as a plastic, such as polyethylene terephthalate (PET)). As another example, in some embodiments, shock cord mounting arms 1309 may include example main structural bars or other parts 1321, which may be composed of materials present in the majority of housing section 1301. However, in some such embodiments, example main structural bars or other parts 1321 may be connected to such eyelet(s), e.g., via a hole into which a pointed and/or threaded end of the eyelets is inserted and fastened. In some embodiments, and, again, as with other shock cord mounting arms set forth in the present application, example shock cord mounting arms 1309 may be curved or angled, for example, due to mounting arm bend(s). In some such embodiments, such bend(s) may be caused by the angle of attachment of such eyelets as discussed above. For example, in some embodiments, as pictured, such eyelets are mounted on such main structural bar(s) or other parts 1315 at an angle (such as a right angle, to such bar(s), again, as pictured).
It should be noted that, although the example of two (2) nose cone housing sections, forming a model rocket nose cone, has been provided, for ease of understanding, in other embodiments, any number of nose cone housing sections (e.g., 3, 4, 5, etc.) may be provided. In some such embodiments, each of such a plurality of nose cone housing sections may be (e.g., radially) symmetrical and/or similar or identical to each other. However, in other embodiments, such nose cone housing sections may, alternatively, not by identical or symmetrical with each other. Furthermore, although the example of a model rocket nose cone is provided, it should be understood that many, if not all, of the aspects set forth in the present application with respect to model rocket nose cones may be provided for other types of rockets, such as, but not limited to, ballistic missiles.
As with any other embodiment, example, and or figure set forth in the present application, the embodiments set forth in, and discussed with reference to,
This application claims the benefit of co-pending U.S. patent application No. 63/275,393, filed Nov. 3, 2021, titled “Model Rockets with Divisible Nose Cones,” the entire contents of which are hereby incorporated by reference herein in their entirety.
| Number | Date | Country | |
|---|---|---|---|
| 63275393 | Nov 2021 | US |
