referring now to fig1 and 2 a fin stabilized subcaliber projectile 10 has cylindrically shaped smooth surface fore and aft body sections 12 and 14 respectively and a central externally grooved body section 16 disposed intermediate fore and aft body sections 12 and 14 . the longitudinal axis 18 of the subcaliber projectile 10 is held parallel to and in axial alignment with the longitudinal axis of a gun tube 20 by a plurality of sabot segments 22 which separate and discard after the subcaliber projectile 10 exits from the muzzle of gun tube 20 . the profile of the sabot segments 22 comprises an aft tapered ramp surface of revolution section 24 and a forward tapered ramp surface of revolution section 26 . intermediate the aft ramp 24 and the forward ramp 26 is a cylindrical obturating band seat 28 having an annular band locking projection 30 thereon . an annularly shaped obturating band 32 , having an annular groove 34 therein , made of a plastic material such material as nylon , is force fit over the sabot band seat locking projections 30 so that projection fits into band groove 34 . the obturating band 32 is axially positioned so that the center of gravity at point &# 34 ; x &# 34 ; of the total in - bore saboted projectile lies on the centerline 18 of the sub - caliber projectile 10 within and under the obturating band 32 . each of the sabot segments 22 have internal concentric traction grooves 36 in a central section and are operatively disposed on an arcuate interface sabot surface 38 intermediate fore and aft ramps 26 , 24 respectively . to provide initial guidance for the in - bore projectile 10 during engraving and early motion , as well as small additional support through in - bore travel in gun tube 20 , some form of borerider is required . a thin cylindrical skirt member , 40 arcuately extends over forward ramp 26 , as shown in fig1 and is used to perform this borerider function aforedescribed . a conical shell borerider member 42 extending from a forward end of forward ramp 26 , as shown in fig2 is an alternate means for performing this initial guidance function . the exact means of additional support is not important in the present invention , because there is no significant overturning movement generated by inertial forces which must be countered by a structurally strong borerider , thus boreriding surfaces or fins aft of the obturating band may be used . since the transverse forces in the present embodiments of fig1 and 2 are smaller than found in conventional sabot - projectile configuration the borerider in the present invention may be made lighter than is normally required . the concept of double - ramp versus conventional saddle - back sabot configuration is illustrated by finite element analysis of two examples shown in fig3 a , 3b , 4a , and 4b . referring now to fig3 a and 3b a conventional saddle - back type sabot segment 44 is shown with pressure forces &# 34 ; p &# 34 ; acting on the rear face 46 and penetrator axial stress &# 34 ; o &# 34 ; acting in the opposite direction . to illustrate the shear load transfer qualities , no acceleration will be imposed on this example . a method for calculating taper profiles to yield desirable characteristics may be found in the proceedings of u . s . army science conference , west point , n . y ., 1978 , &# 34 ; sabot design for 105 mm apfsds kinetic energy projectile &# 34 ;, w . h . drysdale et al . a dot is used in saddle - back sabot 44 to locate each element of the sabot that has a tensile hoop stress . since a segmented sabot cannot support hoop tension , the seam must open in these regions . the areas of hoop tension form a path completely through the sabot , which would open to allow propellant gas to leak out . the variation in shear stress &# 34 ; τ &# 34 ; at the sabot projectile interface 48 versus axial distance for the saddle - back sabot example is shown by curve 50 . the result is very nonuniform , with peak values of shear stress indicated at both ends of the sabot and very low values in the center . this type of shear stress variation is conducive to domino failures , with shear grooves failing sequentially along the interface 50 . when the same material and loading parameters are used to calculate the stess in a double - ramp sabot 52 versus axial distance a substantially uniform curve is generated as shown in fig4 b . only two elements near the forward taper 54 of fig4 a had hoop tension . the sheer stress &# 34 ; τ &# 34 ; variation at the interface 56 is ploted as curve 58 , and is seen to be relatively uniform across the total axial interface distance z . in operation high pressure propelling gas pressure , as indicated by arrows 60 in fig1 and 2 , acts on the aft tapered ramp surfaces of revolution 24 in such manner as to constrict the aft portion of the sabot 22 as well as providing propelling force to the sabot . the constricting action of the propellant gases clamp the sabot segments 22 tightly together and to the subprojectile 10 and act as an efficient high pressure seal in these areas . the propellant gas acting on the aft tapered ramp surfaces 24 creates very high compressive hoop and radial stresses . these stress are higher than the gas pressure , so there is no tendency for pressure to leak into the narrow slits between the sabot segments and to force them apart . the obturating band 32 also acts to prevent propellant gas leakage between the gun tube 20 and the peripheral bore riding surfaces sabots . the propelling forces 60 acting on the sabots 22 are transferred to the subprojectile 10 across the interfaces 38 and interlocking concentric grooves 16 and 36 . the maximum load transfer is best accomplished as previously stated when the interface traction is uniform in the axial direction and at its maximum allowable values . factors affecting this load transfer are the gas pressure , projectile acceleration , subprojectile material and configuration , sabot material and configuration , and the profile of the sabot taper . on the interface 38 , under the aft taper ramp 24 , the constricting force of the gas pressure operating on surface 24 , allows certain levels of load transfer to be accomplished by means of frictional forces . since there is no substantial gas pressure acting on the forward ramp 26 , the load transfer at the portion of this interface under ramp 26 must be accomplished by means of grooves , or threads . the sum of the interface lengths under the aft ramp 24 and of the length of concentric traction grooves 16 and 36 represents the total supported length of the subprojectile 10 . this length is made sufficiently long to both adequately support the subprojectile 10 during in - bore travel and transmit the propelling force from the sabot to subprojectile . in accordance with the present teaching the present invention makes it practical to obtain a lightweight sabot which can supply adequate axial and lateral support to launch high length to diameter ratio subprojectiles under high accelerations with improved leathality . since the sabot weight is parasitic to the increased velocity and range obtainable from the concept of a sabot , the lightness of the sabot has a major impact on the efficiency of the projectile system . while there has been described and illustrated specific embodiments of the invention , it will be obvious that various changes , modifications and additions can be made herein without departing from the field of the invention which should be limited only by the scope of the appended claims .