Patent ID: 12240603

DETAILED DESCRIPTION

FIG.1Aillustrates an example of OAW vehicle10that is used as a payload launch vehicle to launch a payload12. In this example, the payload12is illustrated as being releasably mounted on the exterior of the OAW vehicle10by one or more payload supports14, and the payload12is intended to be released from the OAW vehicle10when a desired staging condition has been achieved. The staging condition can be one or more of a desired speed of the OAW vehicle10, and/or an altitude of the OAW vehicle10, and/or a coordinate position of the OAW vehicle10such as geographic coordinates, Earth-centered inertial coordinates or Earth-center, Earth-fixed coordinates. In some embodiments, referring toFIGS.19A and19B, the payload12can be mounted within an interior13of the OAW vehicle10, and one or more payload doors15on the OAW vehicle10can be opened to permit release of the payload12from the interior13.FIG.19Adepicts the OAW vehicle10with a pair of the payload doors15with the payload doors15closed, and the payload (not visible) within the interior of the OAW vehicle10. In an embodiment, a single payload door15can be used instead of a pair of the payload doors15.FIG.19Bdepicts the payload doors15open showing the payload12within the interior13ready to be deployed from the OAW vehicle10. After releasing the payload12, the payload doors15can be closed, and the OAW vehicle10can be controlled to glide back to a landing site which can be at or near the launch site, or remote from the launch site.

The payload12can be any type of payload that can be launched using the OAW vehicle10. The payload12may have its own propulsion system or the payload12may be devoid of propulsion. For example, the payload12may comprise a propulsion rocket16(best seen inFIGS.2and3) for propulsion. The propulsion rocket16may be ignited after release of the payload12from the OAW vehicle10whereby the payload12can be controlled to continue on a desired flight trajectory. The payload12may include one or more control surfaces (not shown), such as adjustable fins, to assist in controlling the trajectory of the payload12after release.

As best seen inFIGS.2-3, the payload12can be mounted on the OAW vehicle10so that a longitudinal axis of the payload12is parallel to a longitudinal axis LA of the OAW vehicle10. However, the payload12can have other orientations on the elongated airfoil body20, and the payload12may not even have a longitudinal axis.

The presence of the payload12is optional. For example,FIG.1Billustrates another embodiment of the OAW vehicle10without the payload12or the payload supports14. The OAW vehicles10inFIGS.1A and1Bcan be otherwise identical to one another.

Referring toFIGS.1-5, the OAW vehicle10comprises an elongated airfoil body20with an airfoil shaped cross-section (FIGS.4and5). The airfoil body20has a top surface22, a bottom surface24, a first longitudinal end26, a second longitudinal end28, a first longitudinal edge30at a first juncture between the top surface22and the bottom surface24that extends from the first longitudinal end26to the second longitudinal end28and defines a leading edge of the elongated airfoil body20, and a second longitudinal edge32at a second juncture between the top surface22and the bottom surface24that extends from the first longitudinal end26to the second longitudinal end28and defines a trailing edge of the elongated airfoil body20. The elongated airfoil body can have an airfoil-shaped cross-section substantially over the entire length between the first longitudinal end26and the second longitudinal end28(in other words, any cross-section taken along a section line, such as section line4-4depicted inFIG.2, at any point along the longitudinal axis LA would result in an airfoil shape, for example similar to the airfoil shape shown in FIG.4orFIG.5). The elongated airfoil body20can be made of materials known in the aircraft/aerospace industry.

The elongated airfoil body20can be provided with one or more control surfaces or fins34for providing directional control during flight.FIGS.1-3illustrate the control surfaces34as being disposed on the top surface22. However, the control surfaces34can alternatively be disposed on the bottom surface24, or one or more control surfaces in addition to the control surfaces(s)34on the top surface22can be provided on the bottom surface24. In some embodiments, control surfaces on the payload12can be used to help provide directional control of the OAW vehicle10while the payload12is mounted on the OAW vehicle10. The payload12may be mounted along the center of the OAW vehicle10between the two control surfaces34for mass balance.

Each of the control surfaces34is preferably adjustable in order to adjust their orientation on the OAW vehicle10. For example, with reference toFIGS.1A and6, each control surface34may be mounted on the OAW vehicle10in a manner to permit each control surface34to be adjustable about a vertical axis A by a suitable drive mechanism (not shown) within the elongated airfoil body20.

To provide propulsion, a propulsion device40is mounted to the elongated airfoil body20at the first longitudinal end26as best seen inFIGS.1-3. The propulsion device40can have any configuration that is suitable for providing propulsion to the OAW vehicle10. For example, the propulsion device40can be a rocket engine that is powered by a liquid propellant, a solid rocket motor that is powered by a solid propellant, or a hybrid rocket motor that uses a solid propellant and a liquid and/or gaseous propellant (FIG.3). The propulsion device40is preferably disposed substantially within the elongated airfoil body20, with substantially only some or all of an exhaust nozzle extending from the elongated airfoil body20. In other embodiments, the propulsion device40can be only partially disposed within the elongated airfoil body20with a majority of the propulsion device40located outside the elongated airfoil body20. With reference toFIG.2, in one embodiment the propulsion device40can comprise a full-length linear aerospike engine42. The aerospike engine42can extend at least 75% of an entire distance between the leading edge30and the trailing edge32. In another embodiment, the propulsion device40can comprise a truncated linear aerospike engine42. An aerodynamic fairing44can be provided between the aerospike engine42and the OAW vehicle10. A full length aerospike engine is useful in some embodiments because it makes an aerodynamically better nose as the OAW vehicle10re-enters the Earth's atmosphere and flies to a landing. A truncated aerospike engine may be used if the end/nose of the truncated aerospike engine is rounded or otherwise made more aerodynamic. The propulsion device40has a thrust axis that is preferably substantially parallel to the longitudinal axis LA, and in one embodiment, the thrust axis extends through the center of the elongated airfoil body20(i.e. midway between the leading edge30and the trailing edge32and extending in the span direction of the airfoil body20).

The OAW vehicle10includes at least one fuel tank that provides fuel to the propulsion device40. Preferably, the fuel tank is disposed entirely within the elongated airfoil body20. Referring toFIG.4, in one embodiment, the OAW vehicle10includes at least one liquid fuel tank50, for example three liquid fuel tanks50, and at least one liquid oxidizer tank52, for example two liquid oxidizer tanks, within the elongated airfoil body20. The tanks50,52are fluidly connected to the propulsion device40in a conventional manner to supply fuel to the propulsion device40.FIG.5illustrates another embodiment that includes at least one liquid fuel tank50, for example five liquid fuel tanks, and at least one liquid oxidizer tank52, for example two liquid oxidizer tanks, within the elongated airfoil body20. In each of the embodiments inFIGS.4and5, the liquid fuel tanks50and the liquid oxidizer tanks52are arranged and extend longitudinally within the elongated airfoil body20with longitudinal axes of the tanks50,52parallel, or substantially parallel, to the longitudinal axis LA of the elongated airfoil body20as best seen inFIG.6. The fuel and oxidizer (if used) can be any conventional fuel and oxidizer known in the art. A solid propellant can be provided if the propulsion device40is a hybrid rocket motor, a solid rocket motor, or a solid rocket motor augmented by a liquid monopropellant or oxidizer.

In an embodiment, the OAW vehicle10can be used as a Stage1for a launch vehicle. Referring toFIG.8, operation of the OAW vehicle10as a Stage1will be described assuming the propulsion device40is an aerospike engine. The OAW vehicle10is prepared for launch by arranging the OAW vehicle10into a vertical orientation at a suitable launch site with the longitudinal axis LA arranged vertically as shown at60. The rocket engine or other propulsion device is then ignited to launch the OAW vehicle10while it is in the vertical orientation. If the OAW vehicle10is to launch a payload, such as the payload12or upper stage, the payload is mounted onto the OAW vehicle10prior to launch, for example while the OAW vehicle10is in a horizontal orientation prior to the OAW vehicle10being arranged vertically for launch. The payload12can be mounted externally as depicted inFIG.8or internally of the OAW vehicle10as described with respect toFIGS.19A-19B. The OAW vehicle10climbs to its staging altitude/velocity and then shuts down/terminates thrust. The payload/upper stage(s) then separate and flies to orbit. The OAW vehicle10then continues to climb due its momentum. The OAW vehicle10then reaches apogee. Once the OAW vehicle10hits apogee and begins falling towards Earth, the nozzle of the aerospike engine is already positioned to be the aerodynamic nose of the OAW vehicle10.

In some embodiments, referring toFIG.11, the OAW vehicle10can have a flight trajectory that could be an orbital trajectory about the Earth. As part of the flight trajectory, in one embodiment the OAW vehicle10can be controlled to execute a skip-glide trajectory with at least one skip68. Skip-glide may also be referred to as a boost-glide or skip reentry, and is a technique used to extend the range of the OAW vehicle10by employing aerodynamic lift in the high upper atmosphere. In some embodiments, the skip-glide trajectory can include two or more (i.e. a plurality) of the skips68. The skip-glide trajectory can be executed prior to releasing the payload12from the OAW vehicle10or after releasing the payload12from the OAW vehicle10.

The OAW vehicle10is controlled to ultimately land at a landing site on Earth while gliding. As the OAW vehicle10falls back to Earth, it can fly surfboard style, and then fly in an oblique orientation to its landing site. As the OAW vehicle10begins its descent (which may also be referred to as reentry), it is oriented in a longitudinal orientation with the longitudinal axis LA parallel to a direction of flight, and with the longitudinal end26forming a leading nose of the OAW vehicle10. This may be referred to as “surfboard reentry” orientation. Assuming that the propulsion device40is the linear aerospike engine42, the aerospike engine42becomes the leading edge/nose of the OAW vehicle10during descent/reentry. One benefit of this orientation is placing the center of mass of the OAW vehicle10, mostly driven by the mass of the aerospike engine42, ahead of the aerodynamic center for the return flight. Another benefit is that the more delicate parts of the OAW vehicle10, such as the payload supports14and the control surfaces34will be on top of, and therefore in the aerodynamic shadow of, the OAW vehicle10during descent/reentry in order to afford maximum protection from the thermal environment during descent/reentry heating.

With reference toFIG.9, once the OAW vehicle10has sufficiently decelerated, the OAW vehicle10is controlled, using the control surfaces34, in order to reorient itself into an oblique orientation a as the OAW vehicle10continues its return flight path in the direction of flight back to the intended landing site. The oblique orientation a can be any angle suitable for allowing the OAW vehicle10to glide while continuing to decelerate. In one non-limiting example, the angle α can be about 40 degrees.

With reference toFIG.10, the OAW vehicle10continues its gliding descent toward the landing site in an oblique orientation which can be the same as or different than inFIG.9. The OAW vehicle10lands at the landing site while gliding in an oblique orientation. The landing site can include a runway70. Prior to landing, the OAW vehicle10can deploy landing gear which can be internally stowed in conventional manner within the OAW vehicle10.

In an embodiment, the OAW vehicle10can be carried by a glider to launch the OAW vehicle10at altitude. The OAW vehicle10can be carried by the glider with the longitudinal axis LA parallel to the direction of flight of the glider or in any other orientation. The glider is towed by a tow aircraft, and the glider may have one or more propulsion rockets for propelling the glider. The glider with the OAW vehicle10attached is towed to an altitude by the tow aircraft. The glider then lets loose of the tow line and, if the glider includes propulsion rocket(s), the glider carries the OAW vehicle10to a second altitude. When the glider reaches a suitable altitude, the OAW vehicle10is released from the glider. The OAW vehicle10will have some aerodynamic lift. It can fly its mission and then fly back to a landing strip in its oblique orientation. Alternatively, the OAW vehicle10can fly back to the tow aircraft and reconnect with the tow line to be towed back to its base, or fly back to the glider and reconnect to the glider. Once the base is reached, the OAW vehicle10can disconnect from the tow line or the glider and can then land as a glider.

In another embodiment, referring toFIGS.20A and20B, the OAW vehicle10can be towed behind an aircraft80via a tow line82. The aircraft80can be any aircraft that is suitable for towing the OAW vehicle10. An example of a suitable aircraft is a C-17 Globemaster. The OAW vehicle10can have an internally mounted payload like inFIGS.19A-B, or an externally mounted payload like inFIGS.1A,2and3, or no payload like inFIG.1B. The aircraft80can launch with the OAW vehicle10in tow. The aircraft80and the OAW vehicle10can then proceed to a designated location and/or loiter for long periods of time with the OAW vehicle10in an oblique flight orientation (FIG.20A) or with the OAW vehicle10flying perpendicular to the direction of flight (FIG.20B).

FIGS.12-18illustrate another embodiment of the OAW vehicle10. In this embodiment, the engine40is optional (and is depicted in broken lines). The OAW vehicle10is otherwise similar to the OAW vehicle ofFIG.1Bincluding the control surfaces.

Additional embodiments can include the following.

Embodiment 1. A method described herein can include arranging an oblique all-wing vehicle into a vertical orientation with a longitudinal axis thereof arranged vertically; and launching the oblique all-wing vehicle while in the vertical orientation by igniting a rocket engine thereof.

Embodiment 2. The method of embodiment 1, further comprises: after launching the oblique all-wing vehicle, controlling the oblique all-wing vehicle to land at a landing site on Earth while gliding.

Embodiment 3. The method of embodiment 2, comprising controlling the oblique all-wing vehicle to initially descend in a longitudinal orientation with the longitudinal axis parallel to a direction of flight with a longitudinal end forming a leading nose of the oblique all-wing vehicle, followed thereafter by reorienting the oblique all-wing vehicle to an oblique orientation in which the oblique all-wing vehicle lands at the landing site while gliding.

Embodiment 4. The method of embodiment 1, comprising controlling the oblique all-wing vehicle to execute a skip-glide trajectory with at least one skip.

Embodiment 5. The method of embodiment 4, wherein the skip-glide trajectory comprises a plurality of skips.

Embodiment 6. A method of launching a payload described herein can include releasably mounting a payload onto an oblique all-wing vehicle having a longitudinal axis and a rocket engine at a longitudinal end of the oblique all-wing vehicle; arranging the oblique all-wing vehicle into a vertical orientation with the longitudinal end facing toward ground; launching the oblique all-wing vehicle while in the vertical orientation by igniting the rocket engine; and releasing the payload from the oblique all-wing vehicle after the oblique all-wing vehicle achieves a desired staging condition.

Embodiment 7. The method of embodiment 6, wherein the payload comprises a rocket engine, and further comprising: after releasing the payload from the oblique all-wing vehicle, controlling the rocket engine of the payload to ignite.

Embodiment 8. The method of embodiment 6, further comprising after releasing the payload from the oblique all-wing vehicle, controlling the oblique all-wing vehicle to land at a landing site on Earth while gliding.

Embodiment 9. The method of embodiment 8, comprising after releasing the payload from the oblique all-wing vehicle, controlling the oblique all-wing vehicle to initially descend in a longitudinal orientation with the longitudinal axis parallel to a direction of flight with the longitudinal end forming a leading nose of the oblique all-wing vehicle, followed thereafter by reorienting the oblique all-wing vehicle to an oblique orientation in which the oblique all-wing vehicle lands at the landing site while gliding.

Embodiment 10. The method of embodiment 6, comprising controlling the oblique all-wing vehicle to execute a skip-glide trajectory with at least one skip.

Embodiment 11. The method of embodiment 10, wherein the skip-glide trajectory comprises a plurality of skips.

Embodiment 12. The method of embodiment 10, wherein the skip-glide trajectory is executed prior to releasing the payload from the oblique all-wing vehicle or after releasing the payload from the oblique all-wing vehicle.

Embodiment 13. The method of embodiment 6, comprising mounting the payload onto the oblique all-wing vehicle while the oblique all-wing vehicle is in a horizontal orientation.

Embodiment 14. The method of embodiment 6, comprising mounting the payload onto an exterior surface of the oblique all-wing vehicle.

Embodiment 15. The method of embodiment 14, comprising mounting the payload onto the exterior surface of the oblique all-wing vehicle between a pair of adjustable control surfaces on the exterior surface.

Embodiment 16. The method of embodiment 6, wherein the oblique all-wing vehicle includes: an elongated airfoil body having a longitudinal axis, a top surface, a bottom surface, a first longitudinal end, a second longitudinal end, a first longitudinal edge at a first juncture between the top surface and the bottom surface that extends from the first longitudinal end to the second longitudinal end, and a second longitudinal edge at a second juncture between the top surface and the bottom surface that extends from the first longitudinal end to the second longitudinal end; the elongated airfoil body having an airfoil-shaped cross-section, with the first longitudinal edge defining a leading edge of the elongated airfoil body and the second longitudinal edge defining a trailing edge of the elongated airfoil body; and further comprising: the rocket engine is mounted to the elongated airfoil body at the first longitudinal end; and the exterior surface is the top surface.

The examples disclosed in this application are to be considered in all respects as illustrative and not limitative. The scope of the invention is indicated by the appended claims rather than by the foregoing description; and all changes which come within the meaning and range of equivalency of the claims are intended to be embraced therein.