Abstract:
A deployable wing that is folded so as to fit into a carrier such as an airplane that is released and automatically with the aid of parachutes to deploy and fly a given distance without assistance other than steering to reach a given destination and a propeller driven by a gas powered engine is actuated to propel the wing an extended distance. A guard is disposed adjacent to the propeller to assure that the lines of the parachutes do not get tangled into the propeller blades.

Description:
TECHNICAL FIELD 
     This invention relates to deployable wings that are carried in the crated state and deployed by aircraft and automatically deployed in the form of a glider and in particular to propulsion mechanism added on to the deployable wing to extend the range thereof. 
     BACKGROUND OF THE INVENTION 
     This invention constitutes an improvement over the apparatus disclosed in U.S. Pat. No. 5,474,257 granted to Fisher et al on Dec. 12, 1995 entitled “Deployable Wing”, U.S. Pat. No. 5,884,863 granted to Fisher et al on Mar. 23, 1999 entitled “Method and Apparatus For Deploying A Wing ” and U.S. Pat. No. 5,878,979 granted to Fisher et al on Mar. 9, 1999 entitled “Method And Apparatus For Landing A Wing”, which all are incorporated herein by reference. These patents essentially details a deployable wing that includes mechanism for controlling the landing thereof. In particular, the wing is foldable to a relatively narrow mechanism that is capable of being lifted into air via a cargo type of aircraft such as the Air Force&#39;s C-130 airplane and is released from the cargo bay and an actuator is activated to cause the wing to deploy and extend into a relatively delta airfoil. The wing consists of diverging leading edge spars attached to a keel spar and cross spars that support a fabric sail. The sail is made in substantially two major portions, an upper section and a lower section that define a relatively closed chamber having an opening or ram air intake at the fore end (nose stagnation point) to lead ram air internally thereof. The wing includes a leading edge with a front point, trailing edge, and controllable wing tips. The wing may have a king post attached to and extending from the keel, a cargo pod mounted to the wing via the keel. The wing carries a first parachute attached to the slider slidably mounted on the keel of the wing where the parachute provides force for causing the wing to deploy to its full open and gliding position. A second parachute attached to the wing is used for decelerating the wing and allowing it to land in a controllable and safe descent to the ground. This second parachute system assures that the wing descend to the ground in primarily a vertical direction relative to ground. The wing may be controlled by an automatic navigational system or by a remotely controlled radio transmitter. 
     While such systems have utility in certain applications where it is desirable to deliver a pay load several miles, say up to thirty (30) miles from the point of drop off from the aircraft, there are other applications, where it is desirable to extend the distance and that is the essence of this invention. It should be pointed out that there are no controllable wings that are designed to deliver a pay load to an extended distant destination prior to this invention. This invention contemplated adapting an internal combustion piston engine to the wing and activating the engine automatically or by remote control at a given point during the flight of the wing after it is deployed. Incorporation of the propulsion will extend the range of the otherwise glider and will afford the option of dropping a payload (or other mission objective) then return under power to a recovery point. The invention contemplates mechanism to assure that the parachute and/or its chords connected to the wing which are used to assist in the landing thereof does not get tangled up with the propeller driven by the engine. 
     SUMMARY OF THE INVENTION 
     An object of this invention is to provide a deployable wing with propulsion means for extending the range thereof; 
     A feature of this invention is the addition of a internal combustion piston engine and propeller mounted on the vehicle. 
     Another feature of this invention is the provision of mechanism for preventing the landing parachute and its cords from being tangled in the propeller/engine mechanism. 
     The foregoing and other features of the present invention will become more apparent from the following description and accompanying drawings. 
    
    
     BRIEF DESCRIPTION OF THE DRAWINGS 
     FIG. 1 is a perspective view, partly broken away, of the prior art deployable wing; 
     FIG. 2 is a perspective view of the wing depicted in FIG. 1 with the addition of the motivating mechanism for extended flight of this invention; and 
     FIG. 3 is a diagrammatic view showing the deployment of the wing and its gliding descent to land. 
    
    
     These figures merely serve to further clarify and illustrate the present invention and are not intended to limit the scope thereof. 
     DETAILED DESCRIPTION OF THE INVENTION 
     Referring now in specific detail to the drawings, with like reference numerals identifying similar or identical elements, FIG. 1 illustrates a perspective view, partially broken away, of one embodiment of the deployable wing  10  of the present application. As illustrated in FIG. 1, wing  10  includes a fabric sail  12  defining a leading edge  14  and a trailing edge  16 . Fabric sail  12  preferably includes an upper section  12   a  substantially joined along its perimeter to a lower section (not shown) and a plurality of fabric ribs (not shown) connected to the upper and lower sections of the fabric sail. Joining the upper and lower sections forms an envelope which can be filled with air through a ram air intake  20  preferably located at the foremost point of the wing. In the present embodiment fabric sail  12  further includes an integral stowed cover flap  13  comprising a first section  13   a  and a second section  13   b , each of which is disposed along the leading edge of wing  10  as shown in FIG.  1 . First and second sections  13   a ,  13   b  each further include complimentary zipper members  15   a ,  15   b  which matingly engage in a conventional manner to contain fabric sail  12  within the integral cover as described hereinbelow when stowed or packed. In the present embodiment cover  13  is preferably made of dacron fabric while zipper members  15   a ,  15   b  are of a sufficiently high strength and durability to operate under deployment conditions, although other materials may be utilized depending upon the design configurations of the wing. 
     With continued reference to FIG. 1, wing  10  further includes an internal structure comprising two leading edge spars (not shown), two cross-spars  22   a ,  22   b , a keel  24 , a kingpost  26  and a control device, such as elevon struts  28   a ,  28   b . The leading edge spars are pivotally attached at one end between faceplates  17   a  and  17   b  to form foremost point  21 . Pivotally connected the leading edge spars at a second end thereof are elevon struts  28   a ,  28   b . Keel  24  is mounted at a first end between faceplates  17   a  and  17   b , and is mounted at an opposite end between rear plate members  27   a  and  27   b  and is disposed between the leading edge spars. Cross spars  22   a ,  22   b  each include an outboard end which is pivotally attached to a corresponding leading edge spar and further include inboard ends, opposite the outboard ends, which are pivotally attached to keel  24 , preferably via a common slider  80 . Kingpost  26  is also preferably mounted to keel  24  via the common slider. When erected, kingpost  26  extends substantially perpendicular to keel  24 , through an opening in fabric sail  12 , to provide an upper attachment point for wires  31   a ,  31   b  which support the wing on landing and when the wing experiences negative loads or inverted flight. In the present embodiment kingpost  26  is pivotally attached to slider  32  such that linear movement of the slider in the direction of arrow “A” causes kingpost  26  to erect through the fabric sail, substantially perpendicular to the keel. 
     The leading edge spars and cross spars are preferably pivotally mounted such that in a closed or pre-deployed position the leading edge spars and cross spars  22   a ,  22   b  rest substantially parallel to keel  24 . In the closed position the common slider is preferably disposed adjacent the foremost point and kingpost  26  is preferably disposed adjacent and substantially parallel to keel  24 . In the closed position complimentary zipper members  15   a ,  15   b  are matingly engaged in a conventional manner to contain fabric sail  12  within the integral cover. Preferably, the leading edge spars, cross spars, keel, elevon struts, kingpost and wing tips  29   a ,  29   b  are all substantially disposed within fabric sail  12  in the closed position. 
     The length of each leading edge spar is dependent upon the desired size of wing  10 , which is only limited by practical considerations: size once folded, desired cruise speed, weight of the payload, etc. Once opened, or deployed, the leading edge spars form an angle therebetween. The size of the angle depends upon aerodynamic considerations including aspect ratio, yaw stability, and deployment simplicity, among others. Typically, the angle ranges from about 90° to about 150° with about 105° to about 110° preferred due to simplicity of the deployment mechanism geometry. Angles greater than about 150° result in more complex, and therefore less desirable, mechanical/structural geometry and decreasing yaw stability, while angles less than about 90 ∠ result in decreasing glide ratio. Yaw stability is where wing sweep allows the wing to tend to maintain its flight directly into the wind, commonly known as maintaining the yaw heading. As the wing yaws, the windward wing tends to drag more than the leeward wing, thereby correcting for the yaw. 
     Cross spars  22   a ,  22   b  provide structural integrity to the wing  10  by providing strength to the leading edge spars to ensure that in the deployed position the leading spars remain in the open position with the appropriate angle therebetween. The distance between the attachment point of the outboard ends to their respective leading edge spars and the inboard ends to the keel determine the length of cross spars  22   a ,  22   b.    
     With continued reference to FIG. 1, keel  24  similarly provides structural integrity to wing  10  by ensuring that the wing  10  opens to and maintains its full length from the leading edge  14  to the trailing edge  16 , commonly known as the wing&#39;s chordwise length. The length of the keel  24  is substantially equivalent to the chordwise length of the wing at the root (very center line) which, as with the leading edge spars&#39; length, is determined on a practical basis with aeronautical considerations effecting the ultimate size. Keel  24  also connects payload  50  to wing  10  via mounting member  36 . 
     The present embodiment also includes elevon struts  28   a ,  28   b  which are each connected to a motor or fluid actuator  30   a ,  30   b , the actuators being located externally of fabric sail  12  and mounted to the leading edge spars. The motor or actuator is conventional in design and operates to deflect or rotate each elevon struts  28   a ,  28   b  independently, out of the plane of the sail, thereby controlling the flight of the wing. By rotating the elevon struts, wing tips  29   a ,  29   b  are twisted up or down relative to the leading edge. This helical twisting of the sail results in an aerodynamic force sufficient to pitch or roll the wing. Rotating or deflecting the elevon struts in unison generates an aerodynamic force substantially behind the pressure center of the wing which is located at the point about 55% down the keel from the foremost point  16 , thereby forming a moment force about the pressure center which is used for pitch control of the wing. By rotating or deflecting the elevon struts  28   a ,  28   b  singularly or in opposite directions, aerodynamic forces at the wing tips  29   a  and  29   b  can be controlled in magnitude and direction, up or down. For example, if the elevon strut  28   a  is rotated up while elevon strut  28   b  is rotated down, downward force is generated on tip  29   a  and an upward force on tip  29   b , resulting in a roll or turn in the direction of strut  28   a.    
     These elevon struts  28   a ,  28   b , or other control devices, can be operated with any conventional motor capable of generating sufficient torque to overcome the aerodynamic forces at a speed sufficient for control response. Factors important in determining the required torque include wing area, wing loading, aspect ratio, and elevon strut length, among others. A wing having a 30 foot wing span, for example, with a sail area of about 190 ft 2  and a 700 lb load requires about 40 to about 80 ft lb torque while a 15 ft wing span wing with an area of 45 ft 2  and a 90 lb load needs about 15 to about 25 ft lb torque for control. 
     In the present embodiment, the length of kingpost  26  is approximately 4 ft. which, as with the keel&#39;s and leading edge spars&#39; length, is determined on a practical basis with aeronautical considerations effecting the ultimate size. In addition to providing an upper attachment point for wires  31   a, b  as described above, kingpost  26  also provides support for strap  32  which is attached at one end between front plate members  33   a ,  33   b , extends over the kingpost and is attached at an opposite end between rear plate members  27   a ,  27   b . Strap  32  is of a sufficient length such that when the strap extends over the kingpost and is strapped between plate members  33   a ,  33   b  and  27   a ,  27   b , there is enough slack present in the strap to allow the strap to be pulled free of the kingpost when parachutes  44  deploy. 
     Attached to strap  32  at approximately its midpoint, in the present embodiment, is parachute attachment line  34 . The point at which line  34  attaches to strap  32  is the point at which the wing  10  with cargo pod, or payload  50  will hang substantially horizontal beneath the parachutes without excessive rotation or pitching. Likewise, the length of strap  32  is length at which the payload will hang substantially horizontal beneath the parachutes. Attachment of line  34  to strap  32  is achieved in the present embodiment through loops which are sewn onto strap  32  and line  34  and which are connected by a clevis fitting, though any conventional method of attachment which will allow for parachute deployment may be utilized. Attachment line  34  is joined at an opposite end to parachute deployment system  40  and includes a second line  34   a  which branches from the attachment line  34  and attaches to a secondary release mechanism  39 ?? disposed within mounting block  38 . Mounting block  38  is connected to wing mounting member  36  which is mounted to both keel  24  and payload pod  0 , the mounting member thereby attaching the payload to the wing. The secondary release mechanism  39  provides controlled release of a parachute deployment system  40  which is described in greater detail below. The present embodiment may include a platform  94  mounted to the underside of cargo pod  50  which aids in the mounting of the wing in the aircraft and in the landing thereof. An antenna  49  may also be carried on the fore end of the wing  10  for the radio control navigation. 
     In accordance with this invention a gasoline reciprocating-piston engine  96  of any suitable type and preferably in the 40-80 horsepower range, is attached to the support  36  of wing  10 . The engine powers a propeller  100  mounted on shaft  101  is driven by the engine  96  via the main engine shaft  102 , pulleys  104  and  106  and belt  108  interconnecting the pulleys. The propeller is of the fixed pitch version and preferably, the pitch is selected for the cruise mode of the wing. An radio frequency receiver is utilized to actuate the starter (not shown) of engine to turn it on during flight and de-activate the engine upon the descent mode. A generally circular shaped frame  110  made from tubular metallic material is supported to the pod  50  that is disposed aft of the propeller and has a bottom arcuate portion  112  that extends below the tip of the propeller blade  114 . The frame assures that the parachute and its lines do not snare when deployed as will be described hereinbelow. 
     The operation of wing  10  is as follows: As mentioned above the wing  10  is preferably deployed from an aircraft  70 . Prior to deployment wing  10  is placed in the closed or pre-deployed position and is loaded into the cargo bay of the airplane. The present embodiment includes a platform  94  mounted to the underside of cargo pod  50  that serves to secure the wing inside the airplane and to facilitate its extraction therefrom. When the aircraft has reached the site over which wing  10  is to be deployed, the wing is deployed from the aircraft, exiting therefrom, as shown in FIG.  8 . Upon exiting the aircraft a static line deploys pilot parachute  72  which decelerates and stabilizes the wing, and releases a drogue parachute  74 . Drogue parachute  74  then initiates deployment of wing  10  and then disengages from the wing. Deployment of wing  10  is described in greater detail in commonly assigned U.S. Pat. No. 5,884,863 granted to Fisher et al., on Mar. 23, 1999, which is hereby incorporated by reference. 
     Once deployed, the wing inflates with ram air and begins flight, gliding through the air where it is preferably guided to its desired destination by the on-board autopilot or radio frequency navigator system. At a predetermined time of the flight, either by an on-board control system or a signal from the radio frequency transmitted, the engine  96  is activated and powers the wing  10 . Once wing  10  reaches its desired location, an extraction rocket is initiated, preferably by a first servo motor, but alternatively may be initiated prior to reaching its desired destination by a manual override signaling a second servo motor, or if electronic failure has occurred, by a mechanical system. Once initiated, and at which time the engine is turned off, the rocket is deployed from pod  50 , thereby extracting pilot parachute  44 , attached thereto. Pilot parachute  44  thereby releases a cluster of landing parachutes  46 , which are attached thereto and which act as a brake to decelerate the wing as described hereinabove. Parachutes  46  are connected via line  34  to line  34   a  which is attached to the secondary release mechanism  39 . 
     Upon deployment of landing parachutes  46 , a force is exerted on line  34   a  which activates the secondary release mechanism  39   a , the operation of which is described above. The secondary release mechanism  39  provides controlled movement of the landing parachutes  46  from an initial position extending rearwardly behind the wing, substantially in line with wing mounting member  36 , to a position above the wing, after release of line  34   a  from the secondary release mechanism, thereby pulling strap  32  free from kingpost  26  as described hereinabove. The parachute system along with the secondary release mechanism allows for a rapid, substantially vertical descent of the wing while avoiding extreme rotation imparted on the wing by the deployment of the landing parachutes. The deployable wing of the present application is therefore capable of unmanned cargo delivery to a predetermined destination which is some distance beyond which the wing can fly without the assistance of the gasoline engine. 
     Although this invention has been shown and described with respect to detailed embodiments thereof it will be appreciated and understood by those skilled in the art that various changes in form and detail thereof may be made without departing from the spirit and scope of the claimed invention.