referring to fig1 in the drawings , a helicopter 11 having a composite drive shaft with captured end adapters according to the present invention is illustrated . helicopter 11 has a fuselage 13 and a main rotor assembly 15 , including main rotor blades 17 and a main rotor shaft 18 . helicopter 11 has a tail rotor assembly 19 , including tail rotor blades 21 and a tail rotor shaft 20 . main rotor blades 17 generally rotate about a longitudinal axis 16 of main rotor shaft 18 . tail rotor blades 21 generally rotate about a longitudinal axis 22 of tail rotor shaft 20 . main rotor blades 17 and tail rotor blades 21 are driven by a drive means 25 carried by fuselage 13 . torque is transmitted from drive means 25 to tail rotor assembly 19 through at least one composite drive shaft having captured end adapters that is disposed within a tail boom 27 . the present invention may also be utilized on other types of rotary wing aircraft . referring now to fig2 a and 2b in the drawings , a tilt rotor aircraft 111 according to the present invention is illustrated . as is conventional with tilt rotor aircraft , rotor assemblies 113 a and 113 b are carried by wings 115 a and 115 b , and are disposed at end portions 116 a and 116 b of wings 115 a and 115 b , respectively . tilt rotor assemblies 113 a and 113 b include nacelles 120 a and 120 b , which carry the engines and transmissions of tilt rotor aircraft 111 , as well as , rotor hubs 119 a and 119 b on forward ends 121 a and 121 b of tilt rotor assemblies 113 a and 113 b , respectively . tilt rotor assemblies 113 a and 113 b move or rotate relative to wing members 115 a and 115 b between a helicopter mode in which tilt rotor assemblies 113 a and 113 b are tilted upward , such that tilt rotor aircraft 111 flies like a conventional helicopter ; and an airplane mode in which tilt rotor assemblies 113 a and 113 b are tilted forward , such that tilt rotor aircraft 111 flies like a conventional propeller driven aircraft . in fig2 a , tilt rotor aircraft 111 is depicted as a civilian - type tilt rotor aircraft , and is shown in the airplane mode ; and in fig2 b , tilt rotor aircraft 111 is depicted as a military - type tilt rotor aircraft , and is shown in the helicopter mode . as shown in fig2 a and 2b , wings 115 a and 115 b are coupled to a fuselage 114 . tilt rotor aircraft 111 includes at least one composite drive shaft having captured end adapters that passes through wings 115 a and 115 b and fuselage 114 from tilt rotor assembly 113 a to tilt rotor assembly 113 b . referring now to fig3 in the drawings , a quad tilt rotor aircraft 211 having a composite drive shaft with captured end adapters according to the present invention is illustrated . as with the tilt rotor aircraft of fig2 a and 2b , tilt rotor assemblies 213 a , 213 b , 213 c , and 213 d are carried by wings 215 a , 215 b , 215 c , and 215 d , respectively . tilt rotor assemblies 213 a , 213 b , 213 c , and 213 d include nacelles 220 a , 220 b , 220 c , and 220 d , which carry the engines and transmissions of quad tilt rotor aircraft 211 , as well as , rotor hubs 219 a , 219 b , 219 c , and 219 d on forward ends of tilt rotor assemblies 213 a , 213 b , 213 c , and 213 d , respectively . tilt rotor assemblies 213 a , 213 b , 213 c , and 213 d move or rotate relative to wing members 215 a , 215 b , 215 c , and 215 d between a helicopter mode in which tilt rotor assemblies 213 a , 213 b , 213 c , and 213 d are tilted upward , such that quad tilt rotor aircraft 211 flies like a conventional helicopter ; and an airplane mode in which tilt rotor assemblies 213 a , 213 b , 213 c , and 213 d are tilted forward , such that quad tilt rotor aircraft 211 flies like a conventional propeller driven aircraft . in fig3 , quad tilt rotor aircraft 111 is shown in the airplane mode . as shown in fig3 , wings 215 a , 215 b , 215 c , and 215 d are coupled to a fuselage 214 . quad tilt rotor aircraft 211 includes at least one composite drive shaft having captured end adapters that passes through wings 215 a and 215 c and fuselage 214 from tilt rotor assembly 213 a to tilt rotor assembly 213 c , and / or at least one composite drive shaft having captured end adapters that passes through wings 215 b and 215 d and fuselage 214 from tilt rotor assembly 213 b to tilt rotor assembly 213 d . quad tilt rotor aircraft 211 may also include at least one composite drive shaft having captured end adapters that passes through fuselage 214 in the fore and aft direction connecting the shaft system in forward wings 215 a and 215 c to the shaft system in aft wings 215 b and 215 d . it should be understood that the present invention may be used with any aircraft on which it would be desirable to have a composite drive shaft with captured end adapters according to the present invention , including unmanned aerial vehicles that are remotely piloted . in addition , it will be appreciated that the present invention may be used in non - torque applications , such as an aircraft refueling boom or a landing gear actuator shaft . the composite drive shaft with captured end adapters may also be in other industries beside the aircraft industry , such as the automotive industry and the manufacturing industry . indeed , the present invention may be used in any application in which it is desirable to have a low - weight , high - strength , high - speed , and / or high - torque composite drive shaft . referring now to fig4 and 9 in the drawings , a drive shaft assembly 311 comprising a composite material portion , referred to herein as a composite tube 313 , and captured end adapters 315 a and 315 b according to the present invention is illustrated . end adapters 315 a and 315 b are captured in composite tube 313 at end portions 317 a and 317 b of composite tube 313 , respectively , during the process of manufacturing composite tube 313 . in the preferred embodiment , composite tube 313 is a braided fiber and resin transfer molded component . such components are typically more damage tolerant and have a higher ballistic survivability . the braided fiber may be either a two - dimensional or a three dimensional braided fiber . however , it should be understood that composite tube 313 may also be manufactured by filament winding , fiber placement , or any other processes that are deemed appropriate . although end adapters 315 a and 315 b are shown as being identical in shape and form , it will be appreciated that composite tube 313 may be manufactured such that end adapters 315 a and 315 b may be of different types , shapes and sizes to facilitate connection to a wide variety of different driving and driven components . referring now to fig5 - 7 in the drawings , end adapter 315 a is illustrated prior to being captured during the process of manufacturing composite tube 313 . it should be understood that any discussion or description herein of end adapter 315 a applies equally to end adapter 315 b , and vice versa . end adapter 315 a is preferably formed from a metallic material , such as aluminum , titanium , or steel , but may be formed from any other suitable rigid material , including non - metallic material . end adapter 315 a preferably includes an interface portion 319 that is configured to be coupled to the end adapter of a driving or driven shaft or component ( not shown ). as is shown , interface portion 319 includes a plurality of optional spaced apart engagement teeth 321 and fastener holes 323 . it will be appreciated that optional engagement teeth 321 and fastener holes 323 are representative of any type of clamping or clasping means for coupling end adapter 315 a to the driving or driven shaft or component . interface portion 319 transitions into a neck portion 325 . neck portion 325 may be configured in a wide variety of cross - sectional shapes and sizes , depending upon the desired application . for example , as is shown , neck portion 325 has a reduced cross - sectional area . this allows clearance for and easy access to fasteners ( not shown ) that pass through fastener holes 323 . it will be appreciated that in some applications , neck portion 325 may not be necessary . end adapter 315 a terminates opposite interface portion 319 with an interior end 326 . end adapter 315 a includes an adapter - tube interface 327 that is configured to engage composite tube 313 . in the preferred embodiment , adapter - tube interface 327 comprises a plurality of lugs 329 spaced around the periphery of adapter - tube interface 327 . lugs 329 protrude radially outward to engage the interior surface of composite tube 313 , as is shown in fig8 , between lugs 329 and composite laminate 351 . each lug 329 includes a lug face 331 , opposing lug flanks 333 , and opposing lug ends 335 . lugs 329 are separated by a generally longitudinal groove having a bottom that is referred to herein as a lug base 337 . lug faces 331 form circumferentially exterior top surfaces that engage the circumferentially interior surface of composite tube 313 , as shown in fig8 . lug faces 331 may be smooth , flat , or curved . opposing lug flanks 333 are preferably radially aligned longitudinal surfaces having filet radii . as will be explained in more detail below , the filet radii function to reduce stress concentration and provide a smooth transition for the fibers of composite tube 313 . opposing lug flanks 333 function to transmit torque from end adapter 315 a to composite tube 313 and vice versa . the leading lug flank 333 of one lug 329 and the trailing lug flank 333 of the adjacent lug 329 form an angle a . the number of lugs 329 and angle a are determined by the design requirements of the drive shaft , including the load and stress distributions for optimized drive shaft strength , and the method of mating the drive shaft with other components or shafts . it will be appreciated that lug flanks 333 may be angled with respect to an axis 334 of the drive shaft , or may be crowned . in this manner , lead correction can be applied to lugs 329 . opposing lug ends 335 transition from neck portion 325 at one end and from interior end 326 at the opposing end , and taper toward each other with increasing radial distance . opposing lug ends 335 function to support axial tensile and compressive loads and bending moments . it will be appreciated the taper of lug ends 335 may be steep , such as 90 °, to carry additional axial forces and bending moments . lug bases 337 may be flat , smooth , or curved . although end adapter 315 a is shown disposed partly within composite tube 313 and partly outside of composite tube 313 , it should be understood that end adapter 315 a may be disposed entirely within composite tube 313 , and may include an internal interface portion . in an alternate embodiment , lugs 329 are hollowed out , as is indicated by the dashed line 339 in fig7 . this hollowing out of one or more of lugs 329 reduces the weight of end adapter 315 a . as shown in fig1 , in another alternate embodiment , at least one circumferential groove 330 across lug faces 331 ( not shown ) and extending radially inward from lug faces 331 may be included to further facilitate bending moments . in such embodiments , it is preferred that the circumferential grooves extend radially inward to lug base 337 . referring now to fig8 in the drawings , end adapter 315 b interfaced with composite tube 313 is shown in a cross - sectional view taken at viii - viii of fig4 . as is shown , lugs 329 of end adapter 315 b are captured by the layers of composite laminate 351 that is part of composite tube 313 . as set forth above , in the preferred embodiment , composite laminate 351 is a braided composite . this capturing process is performed during the process of laying up and manufacturing composite tube 313 . in the preferred embodiment , lugs 329 are entirely surrounded by braided fibers 351 . the layering of composite laminate 351 down to lug bases 337 between lug flanks 333 provides a positive engagement between composite tube 313 and end adapters 315 a and 315 b for the transmission of torque . this configuration eliminates the need to rely solely upon the stiffness of the components and / or the adhesion between the components to transfer the torque , as is required in hexagonal connections and circular connections with adhesive . filets 353 at the intersection of lug flanks 333 and lug bases 337 aid in reducing stress concentrations in composite laminate 351 and lugs 329 . filets 353 also provide a smooth transition from lug bases 337 to lug flanks 333 to prevent a resin rich situation at the intersection . the preferred process of manufacturing drive shaft assembly 311 will now be described . first , end adapters 315 a and 315 b of a selected configuration are placed on an elongated mandrel . then , composite tube 313 , which comprises polymer or plastic fibers , is applied over the mandrel and end adapters 315 a and 315 b by an appropriate braiding technique , such as two - dimensional or three dimensional braiding , to form a composite preform . in some applications , it may be desirable to place an adhesive film on the adapter - tube interface between end adapter 315 a and the polymer or plastic fibers , so that the adhesive is disposed between end adapter 315 b and composite tube 313 . next , one or more tools or molds configured to match the composite preform , including end adapters 315 a and 315 b , the mandrel , and the composite tube 313 , are clamped down over the entire assembly . then , the assembly is heated , evacuated , injected with resin , and cured to form drive shaft assembly 311 . as set forth above , in alternate embodiments , composite tube 313 may be formed by other means , such as filament winding , filament placement , or any other type of composite manufacturing technique . in such instances , pre - impregnated fibers are applied over the mandrel and end adapter 315 b by filament winding or filament placement processes . the assembly is then enclosed in vacuum bags and evacuated . next , the resin is cured . then , the vacuum bags and mandrel are removed . because no fasteners are required , no drilling of fastener holes is necessary , and no fasteners protrude outward . this reduces the possibility of interference with electrical lines , hydraulic lines , and other components when installed and operated on the aircraft . the only post - cure processing that is required is simple trimming of the exposed ends of composite laminate 351 . by manufacturing drive shaft assembly 311 in this manner , misalignment of end adapters 315 a and 315 b is greatly reduced , and little or no balance correction is required . it will be appreciated that end adapters 315 a and 315 b can be recovered from drive shaft assembly 311 by simply burning off composite laminate 351 , should any drive shaft assembly 311 either contain a manufacturing defect , or become damaged during use . this ability to recover and re - use end adapters 315 a and 315 b represents tremendous savings in labor , time , and cost . the composite drive shaft according to the present invention provides significant benefits and advantages , including : ( 1 ) the costs of manufacturing the shaft are lower ; ( 2 ) the shaft is less susceptible to corrosion ; ( 3 ) the shaft has greater strength ; ( 4 ) the shaft is lighter ; ( 5 ) because the end adapters do not clamp or bite into the composite material , the integrity of the composite material is maintained ; ( 6 ) because bolts are not necessary , fewer parts are necessary ; ( 7 ) because bolt holes are not drilled through the composite and end adapters , crack initiation and propagation is greatly reduced ; ( 8 ) the shaft can be used in high speed and high torque applications ; ( 9 ) post - cure cutting and machining of the composite tube are minimized ; and ( 10 ) the end adapters can be recovered from damaged assemblies and re - used . it is apparent that an invention with significant advantages has been described and illustrated . although the present invention is shown in a limited number of forms , it is not limited to just these forms , but is amenable to various changes and modifications without departing from the spirit thereof .