Patent Publication Number: US-2023150648-A1

Title: Methods and apparatus for space-efficient aircraft deployment

Description:
FIELD OF THE DISCLOSURE 
     This disclosure relates generally to aircraft deployment and, more particularly, to space-efficient aircraft deployment. 
     BACKGROUND 
     Deployable aircraft are typically launched from ground or mid-air launch positions to deliver a payload. In particular, some deployable aircraft can carry a payload at significant altitudes while maintaining controlled flight, despite relatively large wind speeds. However, the deployable aircraft can be relatively large to withstand such conditions and, thus, can utilize considerable space in launch vehicles. 
     SUMMARY 
     An example method of deploying an aircraft includes separating the aircraft from a launch vehicle, the aircraft having a wing pivotably coupled to a fuselage, rotating, about an axis of rotation, the wing relative to the fuselage from a first rotational orientation to a second rotational orientation different from the first rotational orientation, wherein, in the first rotational orientation, the wing extends along a direction that substantially aligns with a longitudinal axis of the fuselage, and extending the wing in a lateral direction away from the fuselage in the second rotational orientation. 
     An example assembly includes a fuselage, and a deployable wing pivotably coupled to the fuselage about an axis of rotation, the wing rotatable between a first rotational orientation and a second rotational orientation different from the first rotational orientation, the wing extending along a direction substantially aligned with a longitudinal axis of the fuselage in the first rotational orientation, the wing to be extended in a lateral direction away from the fuselage in the second rotational orientation as the wing is rotated to the second rotational orientation. 
     An example aircraft deployment assembly includes a fuselage, a deployable wing pivotably coupled to the fuselage about an axis of rotation relative to the fuselage, the wing rotatable between a first rotational orientation and a second rotational orientation different from the first rotational orientation, the wing extending along a direction substantially aligned with a longitudinal axis of the fuselage in the first rotational orientation, the wing to be extended in a lateral direction away from the fuselage in the second rotational orientation as the wing is being deployed, and an outer casing defining a cross-sectional perimeter to enclose the fuselage and the deployable wing with the wing in the first rotational orientation. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         FIG.  1    illustrates an example deployment sequence of an example aircraft in accordance with teachings of this disclosure. 
         FIGS.  2 A- 3 B  are detailed views of the example aircraft of  FIG.  1   . 
         FIGS.  4 - 6    illustrate another example aircraft in accordance with teachings of this disclosure. 
         FIGS.  7  and  8    illustrate another example aircraft in accordance with teachings of this disclosure. 
         FIGS.  9 A- 9 C  illustrate yet another example aircraft in accordance with teachings of this disclosure. 
         FIG.  10    is a flowchart representative of an example method to implement examples disclosed herein. 
         FIGS.  11 A- 12 C  illustrate example inflatable wing portions that can be implemented in examples disclosed herein. 
         FIGS.  13 - 14    illustrate example airfoils that can be implemented in examples disclosed herein. 
         FIGS.  15 A and  15 B  illustrate an example wing portion that can be implemented in examples disclosed herein. 
         FIGS.  16 A and  16 B  illustrate another example wing portion that can be implemented in examples disclosed herein. 
         FIG.  17    illustrates an example wing design methodology that can be implemented with examples disclosed herein. 
     
    
    
     The figures are not to scale. In general, the same reference numbers will be used throughout the drawing(s) and accompanying written description to refer to the same or like parts. As used herein, unless otherwise stated, the term “above” describes the relationship of two parts relative to Earth. A first part is above a second part, if the second part has at least one part between Earth and the first part. Likewise, as used herein, a first part is “below” a second part when the first part is closer to the Earth than the second part. As noted above, a first part can be above or below a second part with one or more of: other parts therebetween, without other parts therebetween, with the first and second parts touching, or without the first and second parts being in direct contact with one another. As used in this patent, stating that any part is in any way on (e.g., positioned on, located on, disposed on, or formed on, etc.) another part, indicates that the referenced part is either in contact with the other part, or that the referenced part is above the other part with one or more intermediate part(s) located therebetween. As used herein, connection references (e.g., attached, coupled, connected, and joined) may include intermediate members between the elements referenced by the connection reference and/or relative movement between those elements unless otherwise indicated. As such, connection references do not necessarily infer that two elements are directly connected and/or in fixed relation to each other. As used herein, stating that any part is in “contact” with another part is defined to mean that there is no intermediate part between the two parts. 
     Unless specifically stated otherwise, descriptors such as “first,” “second,” “third,” etc., are used herein without imputing or otherwise indicating any meaning of priority, physical order, arrangement in a list, and/or ordering in any way, but are merely used as labels and/or arbitrary names to distinguish elements for ease of understanding the disclosed examples. In some examples, the descriptor “first” may be used to refer to an element in the detailed description, while the same element may be referred to in a claim with a different descriptor such as “second” or “third.” In such instances, it should be understood that such descriptors are used merely for identifying those elements distinctly that might, for example, otherwise share a same name. As used herein, “approximately” and “about” refer to dimensions that may not be exact due to manufacturing tolerances and/or other real world imperfections. 
     DETAILED DESCRIPTION 
     Methods and apparatus for space-efficient aircraft deployment are disclosed. Some known implementations utilize a launch vehicle to deploy an aircraft in the air or near orbital altitudes so that the aircraft can carry or deliver a payload, at and/or through relatively high altitudes, for example. Due to constraints of the aforementioned launch vehicle, the capabilities of the deployed aircraft can be limited. In particular, physical limitations (e.g., payload capacity, weight, volume, wing size, wing shape, etc.) and/or power draw of the launch vehicle may constrain flight capabilities of the deployed aircraft. 
     Examples disclosed herein implement a space-efficient method to stow and deploy an aircraft to efficiently utilize an internal volume of a corresponding launch vehicle. According to examples disclosed herein, an arrangement and/or a relative positioning of components (e.g., fuselage, wing, payload, etc.) within a cavity (e.g., within a diameter of the cavity) of the launch vehicle enables utilization of smaller and more light weight launch vehicles with enhanced flight capabilities compared to known systems. Examples disclosed herein enable cost-efficient manufacturing and a lower overall weight of the deployed aircraft, thereby enabling significant fuel savings and a longer-duration of sustained flight. Further, examples disclosed herein can utilize folding of an aircraft to fit the aircraft within the tight spatial constraints of the launch vehicle. 
     Examples disclosed herein implement launch systems (e.g., mid-air launch systems, orbital launch systems, space launch systems, etc.) that can advantageously facilitate space-saving of a launch vehicle. Examples disclosed herein can be stored in a compact volume by including deployable aircraft with foldable wing portions (e.g., rotatable wing portions, inflatable wing portions, etc.). The foldable wing portions can improve maneuverability, reduce overall weight, and improve flight endurance of the deployable aircraft. Further, examples disclosed herein can enable increased payload capacity of the launch vehicle. Moreover, examples disclosed herein can enable relatively quick deployment of the aircraft (e.g., faster rotation of the wing, and/or faster inflation of inflatable wing portions, etc.). 
     According to examples disclosed herein, an example wing is rotatable between a first rotational orientation (e.g., a retracted or folded position) and a second rotational orientation (e.g., an extended position) with respect to a first axis. According to examples disclosed herein, the wing extends along a direction that is generally aligned with a longitudinal axis of the fuselage in the first rotational orientation. 
     In some examples, the wing extends in a direction perpendicular to the longitudinal axis in the second rotational orientation. In some examples, the wing includes at least one of a rigid spar or a telescoping spar. In other examples, the wing can include an inflatable wing portion. In some such examples, the inflatable wing portion may include chordwise stitching or spanwise stitching. 
     As used herein, “chordwise” refers to a direction along a chord of an airfoil section and “spanwise” refers to a direction along a span of the wing. In some examples, the inflatable wing portion may include a coiled wing. For example, the coiled wing may include at least one of a Storable Tubular Extendible Member (STEM) shape, a bi-STEM shape, or a lenticular boom shape that folds out along an axial direction parallel to the wing. In other examples, the wing may include a fiber reinforced flexible membrane. 
     As used herein, stating that a first object or feature is substantially parallel or aligned with a second object or feature means that the first object is substantially parallel or aligned within 5 degrees of the second object. Similarly, stating that a first object or feature is substantially perpendicular to a second object means that the first and second objects or features are between 85 degrees to 95 degrees from one another. 
       FIG.  1    illustrates an example deployment sequence (e.g., an unfolding sequence)  100  of an example aircraft  102  in accordance with teachings of this disclosure. The example aircraft  102  is depicted as being unfolded as it is deployed from an example launch vehicle (e.g., an outer casing or housing of a launch vehicle)  103 . 
     At example time  104 , the example aircraft  102  is propelled forward from the launch vehicle  103 , as generally indicated by an arrow  106 . Additionally or alternatively, the example aircraft  102  is ejected rearward from the launch vehicle  103 . In some examples, the example launch vehicle  103  (e.g., a shell, a housing or outer casing of the launch vehicle  103 ) can detach in multiple pieces (e.g., projectile cover halves, casing portions, etc.) to release (e.g., remove) the example aircraft  102  therefrom. In some examples, the example shell outer casing defines a circular perimeter (e.g., cross-sectional perimeter) and/or cross-sectional area to enclose the example aircraft  102 . The example aircraft  102  is depicted at time  104  in  FIG.  1    in a folded state and has a fuselage  108  and a wing  110 , with the wing  110  extending in a direction that is substantially parallel (e.g., within 5 degrees) to a longitudinal axis of the fuselage  108 . 
     At example time  112 , the example aircraft  102  is depicted in an unfolded state such that the wing  110  is unfolded from the fuselage  108  by being rotated about the pivot  114  along a direction generally indicated by an arrow  115 . In this example, the wing  110  extends along a direction that is substantially perpendicular (e.g., within 5 degrees) to the fuselage  108 . Additionally or alternatively, at time  112 , a tail wing assembly  116  is also unfolded with respect to the fuselage  108 . 
     At time  118 , the example aircraft  102  is depicted in a fully expanded (e.g., fully unfolded) state with an expandable (e.g., foldable) wing portion  120  extending outward from the wing  110 . In this example, the expandable wing portion  120  is extended laterally relative to the fuselage  108 . Additionally or alternatively, an expandable tail wing portion  122  is unfolded (e.g., extended outward) from the tail wing assembly  116 . 
       FIGS.  2 A- 3 B  are detailed views of the example aircraft  102  of  FIG.  1   . Turning to  FIG.  2 A , the example aircraft  102  is depicted in a folded state. The example aircraft  102  includes the wing  110  and the fuselage  108  with the wing  110  extending in a direction that is substantially parallel to the fuselage  108 . In some examples, at least a portion (e.g., a distal portion) of the wing  110  contacts the fuselage  108  in the folded state. 
       FIG.  2 B  is a front view of the example aircraft  102  of  FIG.  2 A . In particular, the example aircraft  102  is shown in a folded state with the wing  110  in contact with the fuselage  108 . An example perimeter  200  illustrates a cross-sectional representation of the aircraft  102  in the folded state. The perimeter  200  surrounds (e.g., partially surrounds, fully surrounds, encloses) the fuselage  108 , the wing  110 , components  202  of the aircraft  102 , and a cavity (e.g., void)  204 . In the illustrated example of  FIG.  2 B , the cavity  204  is shown as multiple voids or spaces between the perimeter  200  and the aircraft  102 . The perimeter  200  (e.g., a diameter of the perimeter  200 ) can vary based on the size, configuration, design, and shape of the wing  110 , the fuselage  108 , the components  202 , and the cavity  204 . In some examples, the size of the perimeter  200  can determine spatial constraints of a launch vehicle, for example. 
       FIGS.  3 A and  3 B  illustrate the example aircraft  102  in an unfolded state (e.g., expanded state).  FIG.  3 A  is an overhead or a plan view of the example aircraft  102  while  FIG.  3 B  is a front view of the example aircraft  102 . In the example of  FIGS.  3 A and  3 B , the expandable wing portion  120  is extended outward from the wing  110  (e.g., fully deployed state) in a lateral direction from the fuselage  108 . Further, in this example, the expandable tail wing portion  122  is extended outward from the tail wing assembly  116 . 
       FIGS.  4  and  5    illustrate an example aircraft  400  in accordance with teachings of this disclosure. Turning to  FIG.  4   , the example aircraft  400  is depicted in a deployed position (e.g., deployed state) and includes a fuselage  402 , and wings  404  which, in turn, includes wing tip portions  406  and  408  on opposed lateral ends of the aircraft  400 . In the illustrated example of  FIG.  4   , each of the wings  404  extends along a direction substantially perpendicular to a longitudinal axis  410  of the fuselage  402 . Further, the wing tip portions  406  and  408  fold with respect to their respective wings  404  at corresponding hinges  412  and  414 , as generally indicated by arrows  416 ,  418 , respectively. The example wing tip portions  406  and  408  can include a stabilizer or a winglet disposed on or proximate distal ends of the wing tip portions  406  and  408 . In this example, the wing  404  is deployed at a rotational orientation that is substantially perpendicular to the longitudinal axis  410 . However, the wing  404  can be oriented at any appropriate rotational orientation relative to the longitudinal axis  410  of the fuselage  402 . 
       FIG.  5    illustrates the example aircraft  400  in a folded state with the wing  404  at an orientation substantially parallel to the longitudinal axis  410  of the fuselage  402 . The wing  404  extends along a direction that aligns with the longitudinal axis  410  of the fuselage  402 , for example. In the example of  FIG.  5   , a pivot  500  is positioned on the longitudinal axis  410  of the fuselage  402 . However, in other examples, the pivot  500  can be disposed on a forward portion or section of the fuselage  402 , an aft portion of the fuselage  402 , or any suitable location on the fuselage  402 . In this example, the wing  404  is rotatably coupled to the fuselage at the pivot  500 . The example wing  404  can rotate about an axis  502  corresponding to the pivot  500 . Additionally or alternatively, the example wing  404  can contact a top surface of the fuselage  402  in the folded state. 
     In the example depicted in  FIG.  5   , the wing tip portions  406  and  408  fold about hinge axes  504  and  506 . For example, the wing tip portions  406  and  408  fold inward toward the fuselage  402  along directions generally indicated by the arrows  416 ,  418 , respectively. In some examples, the wing tip portions  406  and  408  are to contact a bottom surface of the wing  404  when the wing tip portions  406  and  408  are unfolded and/or deployed. However, additionally or alternatively, the wing tip portions  406  and  408  can fold to contact a top surface of the corresponding wing  404 . 
       FIG.  6    is a front view of the example aircraft  400  of  FIG.  5   . An example perimeter  600  illustrates a cross-sectional representation of the aircraft  400  in the folded state. The perimeter  600  surrounds (e.g., partially surrounds, fully surrounds, encloses) the fuselage  402 , the wing  404 , the wing tip portions  406  and  408 , and a cavity  602 . In the illustrated example of  FIG.  7   , the cavity  602  is shown as a space between the perimeter  600  and the aircraft  400 . A diameter of the perimeter  600  may vary based on the size, configuration, design, and shape of the wing  404 , the wing tip portions  406  and  408 , and the fuselage  402 . The perimeter  600  is shown in  FIG.  6    to emphasize the stowed position of the example aircraft  400 . 
     The example aircraft  400  shown in  FIGS.  4 - 6   , is configured as a rigid wing configuration. However, in other examples, the example aircraft  400 , the wing  404  or the wing tip portions  406  and  408  can include any combination of rigid wing, expandable and/or inflatable wing configurations. 
       FIGS.  7  and  8    illustrate an example aircraft  700  that can be implemented in examples disclosed herein.  FIG.  7    is a side view of the example aircraft  700 . The example aircraft  700  of  FIGS.  7  and  8    is similar to the example aircraft  400  of  FIGS.  4 - 6    but, instead, includes a channel  702  to store a chute  704 . In the example of  FIG.  7   , the aircraft  700  is depicted in a folded state with the wing  404  at an orientation substantially parallel to the fuselage  402 . In particular, the wing tip portions  406  and  408  are folded inwards toward the fuselage  402  to contact a bottom surface of the wing  404 . In this example, the chute  704  is stored in a housing  706  and is deployed in a direction generally indicated by an arrow  708  that opposes the direction of movement of the example aircraft  700 . 
       FIG.  8    is a front view of the example aircraft  700 . An example area or perimeter  800  illustrates a cross-sectional space and/or area of the aircraft  700  that may or may not be defined by physical features and/or components. The perimeter  800  surrounds (e.g., partially surrounds, fully surrounds, encloses) the fuselage  402 , the wing  404 , the wing tip portions  406  and  408 , the chute  704 , the channel  702 , the housing  706 , and a cavity  802 . The perimeter  800  is illustrated in  FIG.  8    depicts a stowed position of the example aircraft  700  and a stowed position of the chute  704 . 
       FIGS.  9 A- 9 C  illustrate an example aircraft  900  that can be implemented in examples disclosed herein. Turning to  FIG.  9 A , the example aircraft  900  is depicted in a deployed position. The example aircraft  900  includes a fuselage  902 , and a wing  904  with wing booms  906  and  908 . The wing booms  906  and  908  can include a stabilizer or a winglet disposed on or proximate distal ends of the wing booms  906  and  908 . The example aircraft  900  is depicted with the wing  904  deployed at a rotational orientation in which the wing  904  extends generally perpendicular to the fuselage  902 . However, the wing  904  can be oriented at any rotational orientation nonparallel to a longitudinal axis  910  of the fuselage  902 . In this example, the wing  904  is rotatably coupled to the fuselage  902  such that the wing  904  rotates along a direction generally indicated by an arrow  912 . Further, in the example illustrated in  FIG.  9   , the wing  904  can include a rigid portion  914  and an inflatable portion  916 . Additionally or alternatively, wing booms  906  and  908  can have corresponding rigid portions  918 ,  920 , as well as respective inflatable portions  922 ,  924  respectively. The example portions  918 ,  920  can define tail booms while the inflatable portions  922 ,  924  can define stabilizers and/or fairings, for example. 
       FIG.  9 B  is a front view of the example aircraft  900  and  FIG.  9 C  is a side view of the example aircraft  900 . In the illustrated examples of  FIGS.  9 B and  9 C , the wings  904  include the wing booms  906 ,  908  and extend in a direction generally perpendicular (e.g., within 5 degrees) to the fuselage  902 . 
       FIG.  10    is a flowchart representative of an example method  1000  to implement examples disclosed herein. The example method  1000  can be executed to deploy an example aircraft (e.g., the example aircraft  102  of  FIG.  1   , the example aircraft  400  of  FIGS.  4 - 6   , and/or the example aircraft  700  of  FIGS.  7  and  8   ). 
     The example method  1000  of  FIG.  10    begins at block  1002 , at which an example aircraft  102  is stowed (e.g., folded) in an example launch vehicle  103 . 
     At block  1004 , the example launch vehicle  103  is launched. 
     At block  1006 , the example aircraft  102  is separated and/or deployed from the launch vehicle  103 . In particular, the example aircraft  102  can be launched in forward or rearward directions from the launch vehicle  103 . In this example, the aircraft is deployed with the wing  110  in a folded position. However, in other examples, the wing  110  can be deployed in a partially unfolded position. 
     At block  1008 , the wing  110  is rotated about a pivot  114 . Additionally or alternatively, the tail wing assembly  116  is rotated with respect to the fuselage  108 . In other examples, the wing  110  is rotated from a first position parallel to a centerline of the fuselage  108  to a second position nonparallel to the centerline of the fuselage  108 . 
     At block  1010 , the expandable wing portion  120  is extended out with respect to the fuselage  108 . In other examples, the expandable tail wing portion  122  is extended out with respect to the fuselage  108 . In other examples, the expandable wing portion  120  and the expandable tail wing portion  122  are extended out simultaneously with respect to the fuselage  108 . 
     At block  1012 , the expandable wing portion  120  is folded out relative to the wing  110 . In some examples, the expandable wing portion  120  is deployed via an inflation of the expandable wing portion  120 . In some examples, the expandable tail wing portion  122  is folded out relative to the tail wing assembly  116 . In other examples, the expandable wing portion  120  can include a rigid spar or a telescoping spar. 
       FIGS.  11 A- 11 B  illustrate an example inflatable wing portion  1100  that can be implemented in examples disclosed herein. Turning to  FIG.  11 A , the example inflatable wing portion  1100  is depicted in a folded state with a distal end  1102  coiled (e.g., rolled) inwards. Turning to  FIG.  11 B , the example inflatable wing portion  1100  is depicted in an unfolded state (e.g., deployed position, inflated state, etc.) with the distal end  1102  coiled outwards. 
       FIGS.  12 A- 12 C  illustrate an example inflatable wrapped wing portion  1200  that can be implemented in examples disclosed herein. In the examples depicted in  FIGS.  12 A- 12 C , the wing portion  1200  extends via an inflation of the wing portion  1200 . Turning to  FIG.  12 A , the example wrapped wing portion  1200  has a cross-sectional shape  1204  (e.g., a STEM shape). In the example of  FIG.  12 B , the wrapped wing portion  1200  has a cross-sectional shape  1208  (e.g., a bi-STEM shape). Turning to  FIG.  12 C , the example wrapped wing portion  1200  has a cross-sectional shape  1210  (e.g., a lenticular shape). 
       FIG.  13    illustrates an example airfoil  1300  that can be implemented in examples disclosed herein. The example airfoil  1300  includes inflatable portions  1302  that extend spanwise from a fuselage. In this example, stitching  1304  attaches the inflatable portions  1302  together such that the airfoil  1300  is at least partially inflatable. In the example depicted in  FIG.  13   , the stitching  1304  and the inflatable portions  1302  extend spanwise along the airfoil  1300 . Additionally or alternatively, the stitching  1304  and the inflatable portions  1302  can extend chordwise along an example wing. 
       FIG.  14    illustrates an example airfoil  1400  that can be implemented in examples disclosed herein. The example airfoil  1400  has a rigid spar  1402  and an inflatable portion  1404 . The inflatable portion  1404  inflates or extends out from the rigid spar  1402  in a direction generally indicated by arrows  1406 . In some examples, the rigid spar  1402  is at least one of a telescoping spar or an accordion spar (further detail in  FIGS.  15 A- 16 B ). In some examples, the spar  1402  is segmented and extends out from a fuselage in response to an inflation of the inflatable portion  1404 . 
       FIGS.  15 A and  15 B  illustrate an example expandable wing portion  1500  that can be implemented in examples disclosed herein. Turning to  FIG.  15 A , the example wing portion  1500  has an expandable spar  1502  and expandable ribs  1504  that define an airfoil of the wing portion  1500 . The example expandable spar  1502  extends in an axial direction of the wing portion  1500 . In this example as depicted in  FIG.  15 A , the expandable wing portion  1500  has an inflatable portion  1506  that inflates in a direction generally indicated by arrows  1508 . 
     Turning to  FIG.  15 B , at time  1510 , the example expandable wing portion  1500  is depicted in a folded state, with the ribs  1504  and the spar  1502  retracted. At time  1512 , the example expandable wing portion  1500  is depicted in an unfolded state (e.g., deployed position) with the spar  1502  and the ribs  1504  extended. In some examples, at least one of the expandable spar  1502  or the ribs  1504  is extended in response to an inflation of the spar  1502 . 
       FIGS.  16 A and  16 B  illustrate an example accordion spar  1600  that can be implemented in examples disclosed herein. Turning to  FIG.  16 A , the example accordion spar  1600  includes segments  1602  that connect via pins  1604 . In the view of  FIG.  16 A , the example accordion spar  1600  is depicted in a folded state (e.g., retracted), with the segments  1602  oriented nonlinearly. Turning to  FIG.  16 B , the example accordion spar  1600  is depicted in an unfolded state (e.g., extended or deployed position) with the segments  1602  rotated about the pins  1604 . 
       FIG.  17    illustrates an example wing design methodology  1700  to implement examples disclosed herein. The example wing design methodology  1700  utilizes calculations of stress on the upper and lower elements  1702  and  1704  to determine a wing structure. For example, the internal pressure of a wing must be relatively high to prevent failure (e.g., buckling, ripping, etc.) of the wing (e.g., wing material, wing spar, etc.). 
     From the foregoing, it will be appreciated that example systems, methods, apparatus, and articles of manufacture have been disclosed that efficiently utilize the spatial constraints of a launch vehicle, thereby saving space and weight of the launch vehicle. In particular, an arrangement and/or a relative positioning of components (e.g., fuselage, wing, payload, etc.) within a diameter of the launch vehicle advantageously utilizes space of the launch vehicle. Examples disclosed herein can enable cost-efficient manufacturing and a lower overall weight of the stowed aircraft. Accordingly, examples disclosed herein can enable increased payload capacity of the aircraft and/or the launch vehicle. 
     Although certain example systems, methods, apparatus, and articles of manufacture have been disclosed herein, the scope of coverage of this patent is not limited thereto. On the contrary, this patent covers all systems, methods, apparatus, and articles of manufacture fairly falling within the scope of the claims of this patent. The following claims are hereby incorporated into this Detailed Description by this reference, with each claim standing on its own as a separate embodiment of the present disclosure. 
     Example 1 includes a method of deploying an aircraft, the method comprising separating the aircraft from a launch vehicle, the aircraft having a wing pivotably coupled to a fuselage, rotating, about an axis of rotation, the wing relative to the fuselage from a first rotational orientation to a second rotational orientation different from the first rotational orientation, wherein, in the first rotational orientation, the wing extends along a direction that substantially aligns with a longitudinal axis of the fuselage, and extending the wing in a lateral direction away from the fuselage in the second rotational orientation. 
     Example 2 includes the method of example 1, wherein the axis of rotation is a first axis of rotation, and further including rotating a wing portion relative to the wing about a second axis of rotation. 
     Example 3 includes the method of example 1, wherein the wing extends in a direction substantially perpendicular to the longitudinal axis in the second rotational orientation. 
     Example 4 includes the method of example 1, further including stowing the aircraft in the launch vehicle when the wing is in the first rotational orientation, and launching the launch vehicle. 
     Example 5 includes the method of example 4, further including rotating the wing to the first rotational orientation prior to stowing the aircraft. 
     Example 6 includes the method of example 4, wherein the fuselage of the stowed aircraft includes a channel to store a chute, the chute deployable when the wing is in at least one of the first rotational orientation or the second rotational orientation. 
     Example 7 includes an assembly for use with an aircraft, the assembly comprising a fuselage, and a deployable wing pivotably coupled to the fuselage about an axis of rotation, the wing rotatable between a first rotational orientation and a second rotational orientation different from the first rotational orientation, the wing extending along a direction substantially aligned with a longitudinal axis of the fuselage in the first rotational orientation, the wing to be extended in a lateral direction away from the fuselage in the second rotational orientation as the wing is rotated to the second rotational orientation. 
     Example 8 includes the assembly of example 7, wherein the axis of rotation is a first axis of rotation, and further including a wing portion pivotably coupled to the wing about a second axis of rotation. 
     Example 9 includes the assembly of example 8, wherein the second axis of rotation is substantially parallel to the longitudinal axis of the fuselage when the wing is rotated to the second rotational orientation. 
     Example 10 includes the assembly of example 8, wherein the first rotational orientation is a stowed position in which the first wing portion is folded to contact the fuselage. 
     Example 11 includes the assembly of example 8, wherein the second rotational orientation is a deployed position in which the first wing portion is rotated away from the fuselage. 
     Example 12 includes the assembly of example 8, wherein the wing portion is a first wing portion, and further including second and third wing portions, the second wing portion pivotably coupled to the first wing portion wherein the second and third wing portions at least partially define a second deployable wing of the aircraft. 
     Example 13 includes the assembly of example 7, wherein the wing extends substantially perpendicular to the longitudinal axis in the second rotational orientation. 
     Example 14 includes the assembly of example 7, wherein the wing is at least one of a rigid spar or a telescoping spar. 
     Example 15 includes the assembly of example 7, wherein the wing includes an inflatable wing portion. 
     Example 16 includes the assembly of example 7, further including a channel of the fuselage to store a chute. 
     Example 17 includes the assembly of example 9, further including a pivot point to pivotally couple the wing to the fuselage, the pivot point positioned at least one of symmetrically or asymmetrically on the wing. 
     Example 18 includes an aircraft deployment assembly comprising a fuselage, a deployable wing pivotably coupled to the fuselage about an axis of rotation, the wing rotatable between a first rotational orientation and a second rotational orientation different from the first rotational orientation, the wing extending along a direction substantially aligned with a longitudinal axis of the fuselage in the first rotational orientation, the wing to be extended in a lateral direction away from the fuselage in the second rotational orientation as the wing is being deployed, and an outer casing defining a cross-sectional perimeter to enclose the fuselage and the deployable wing with the wing in the first rotational orientation. 
     Example 19 includes the assembly of example 18, wherein the outer casing defines a cavity in a space between the fuselage, the deployable wing and the casing, the fuselage and the deployable wing to eject from the outer casing. 
     Example 20 includes the assembly of example 18, wherein the outer casing includes a first casing portion and a second casing portion, the deployable wing to eject from the first and second outer casing portions when the first casing portion detaches from the second casing portion. 
     Although certain example methods, apparatus and articles of manufacture have been disclosed herein, the scope of coverage of this patent is not limited thereto. On the contrary, this patent covers all methods, apparatus and articles of manufacture fairly falling within the scope of the claims of this patent. 
     The following claims are hereby incorporated into this Detailed Description by this reference, with each claim standing on its own as a separate embodiment of the present disclosure.