Launch system

Abstract

A launch system includes a launcher and a launch vehicle. The launch vehicle upper portion has a diameter greater than the lower portion, which includes a propulsion system. The launcher includes: a launch tube, a piston assembly, and an actuation system. The piston assembly is selectively movable along a piston axis, co-axial with the central axis of the launch tube, between two axial positions to thereby eject the launch vehicle from the launch tube. The piston assembly includes a piston member, and a launch load application member projecting upwardly from the piston member. The launch load application member provides load-bearing contact to the launch vehicle, and is laterally off-set from the central axis. The actuation system is coupled to the piston assembly and selectively accelerates the piston assembly between the two axial positions, thereby imparting a launch force to the launch vehicle via the launch load application member during launch.

Description

[0001] LAUNCH SYSTEM

[0002] TECHNOLOGICAL FIELD

[0003] The presently disclosed subject matter relates to launch systems for launching launch vehicles, in particular to cold launch systems.

[0004] BACKGROUND

[0005] Vertical launch systems (VLS) for launching missiles are well known in the art. Conventionally, VLS include at least two different categories: hot launches and cold launches.

[0006] In a conventional cold VLS, the missile is conventionally ejected from the cell or launch tube, for example via gas produced by a gas generator or via an ejector piston, which is generally not necessarily part of the missile.

[0007] Cold VLS, while conventionally more complex than the hot VLS category, provides relatively greater safety, as a malfunctioning missile is effectively ejected out of the launch tube and the threat of such a missile damaging the launch tube or immediate area is much reduced. Some surface to air missiles (SAM) and ship launched missiles are cold launched.

[0008] In many applications of such launches it is sometimes desirable to orient the missile in a non-vertical direction, along a desired elevation and / or azimuth, as soon as possible.

[0009] Many types of missile launch systems are known in the art.

[0010] By way of non-limiting example, US 6,752,060 discloses method of launching a missile in a given direction is described comprising the following steps. Step (i) - storinga missile in a housing. Step (ii) - ejecting the missile from the housing while imparting a tumbling motion to the missile, the direction of tumble being selected to decrease the angle between the longitudinal axis of the missile and the given direction. Step (iii) -firing the missile and steering it to the given direction. By such a method a missile launcher is provided which is capable of firing a missile at any azimuth angle of between 0 and 360°, within 0.1 second of receiving a signal to launch. The missile may be launched by a single ejector piston at the base of the missile acting in a direction off-set from the longitudinal axis of the missile.

[0011] Also way of non-limiting example, US 8,468,923 discloses an apparatus for selectively affecting a launch trajectory of a projectile from a canister. The apparatus includes means for selectively positioning the projectile with respect to the canister and a sabot operably associated with the projectile and the means for selectively positioning the projectile. A projectile launch system includes a canister, a projectile disposed in the canister, and means for selectively positioning the projectile with respect to the canister. A method for affecting a launch trajectory of a projectile includes providing a canister and a projectile disposed in the canister and adjusting a position of the projectile with respect to the canister.

[0012] Also way of non-limiting example, DE 102014002822 relates to a method for starting a guided missile mounted in a shaft, wherein the guided missile lifts completely out of the shaft, the missile subsequently being deflected to a target flight direction, and wherein after deflecting the missile a roll rate about a longitudinal axis is impressed.

[0013] Also way of non-limiting example, DE 102018133073 relates to a starting device with a launching container and an ejection mechanism, wherein a rocket arranged or to be arranged in the launching container can be ejected from the launching container by means of the ejection mechanism. A too high maximum acceleration during the starting process is avoided in that the ejection mechanism has a scissor carrier with an articulated chain with several scissor levers. The scissor carrier can be spread by means of an actuator arrangement for ejecting the rocket.

[0014] Also way of non-limiting example, CN 113772113 relates to a ship-borne vertical launching load launching method, belongs to the technical field of load launching, and ostensibly solves the problems of long response time and low launching efficiency in theship-borne vertical launching load launching process in the prior art. The method comprises the following steps: 1, turning the direction of a nozzle of the transverse power device; 2, enabling the load to leave the vertical launching cylinder; 3, performing disturbance compensation on the load; 4, moving the load to a putting area.

[0015] GENERAL DESCRIPTION

[0016] According to an aspect of the presently disclosed subject matter, there is provided a launch system comprising a launcher and a launch vehicle:

[0017] the launch vehicle comprising:

[0018] an upper launch vehicle portion having a first diameter and a lower launch vehicle portion having a second diameter, the first diameter being greater than the second diameter, the lower launch vehicle portion comprising a propulsion system selectively actuable for propelling the launch vehicle after launch from the launcher;

[0019] the launcher comprising:

[0020] a launch tube defining a launch tube lumen having a central longitudinal axis, the launch tube lumen having an internal diameter being sized to enable accommodating the launch vehicle therein prior to launch;

[0021] a piston assembly movably mounted within the launch tube lumen, and selectively axially movable along a piston central axis, nominally co-axial with the central longitudinal axis, between a first axial position and a second axial position to thereby eject the launch vehicle from the launch tube during launch;

[0022] the piston assembly comprising a piston member and a launch load application member, the piston member having an upper facing surface, the launch load application member projecting upwardly from the upper facing surface, wherein load-bearing contact between the piston assembly and the launch vehicle is via the launch load application member, and wherein the launch load application member is laterally off-set with respect to the central longitudinal axis (and to the piston central axis) by a non-zero offset dimension;

[0023] an actuation system coupled to the piston assembly and operative to selectively accelerate the piston assembly from the first axial position to the second axialposition, thereby imparting a launch force to the launch vehicle via the launch load application member during launch;

[0024] wherein in the first axial position the launch vehicle is accommodated in the launch tube lumen, and wherein in the second axial position the launch vehicle is provided with sufficient momentum to be fully ejected from the launch tube lumen.

[0025] For example, the launch vehicle has a vehicle longitudinal axis, and wherein the vehicle longitudinal axis is nominally co-axial with the central longitudinal axis when the launch vehicle is accommodated in the launch tube lumen and the piston assembly is in said first axial position.

[0026] Additionally or alternatively, for example, said launch lumen comprises a lumen axial length parallel to the central longitudinal axis between said first axial position and a launch tube upper opening, and wherein the launch vehicle comprises a launch vehicle axial length, wherein said launch vehicle axial length is not greater than said lumen axial length.

[0027] Additionally or alternatively, for example, said upper launch vehicle portion is axially contiguous with said lower launch vehicle portion, wherein said upper launch vehicle portion has a first length, and wherein said lower launch vehicle portion has a second length.

[0028] Additionally or alternatively, for example, said internal diameter is greater than said first diameter by a non-zero clearance dimension.

[0029] Additionally or alternatively, for example, said launch force is nominally parallel to said central longitudinal axis.

[0030] Additionally or alternatively, for example, the launch vehicle has a center of gravity, laterally spaced from the launch force, and wherein said launch force induces a turning moment on the launch vehicle about a turning axis orthogonal to said central longitudinal axis.

[0031] Additionally or alternatively, for example, the piston assembly allows pivoting of the launch vehicle along at least one lateral axis orthogonal to the central longitudinal axis, or, the piston assembly allows pivoting of the launch vehicle with respect to thepiston assembly along at least one lateral axis orthogonal to the central longitudinal axis, said lateral axis being parallel with said turning axis. For example, the launch vehicle is prevented from pivoting about the lateral axis within the launch lumen during launch while said upper launch vehicle portion is within the launch lumen. Additionally or alternatively, for example, during launch the launch vehicle is pivoted by a first pivot angle range about the lateral axis within the launch lumen during launch after said upper launch vehicle portion has cleared the launch lumen. For example, said first pivot angle range is correlated to a first ratio of the offset dimension to the second diameter, and to a second ratio of the second length to the lumen axial length. For example, said first ratio is greater than zero, and up to 0.5.

[0032] Additionally or alternatively, for example, the launch vehicle comprises an outer skin, the outer skin comprising an upper outer skin portion corresponding to the upper launch vehicle portion and defining said first diameter, and a lower skin portion corresponding to the lower launch vehicle portion and defining said second diameter. Alternatively, for example, the launch vehicle comprises a sabot and projectile, the projectile having an outer skin, the outer skin comprising an upper outer skin and a lower outer skin, the sabot being in overlying relationship with the upper outer skin, the sabot corresponding to the upper launch vehicle portion and defining said first diameter, the lower outer skin corresponding to the lower launch vehicle portion and defining said second diameter; for example, the sabot is operative to become detached from the projectile after the launch vehicle is ejected from the launcher or at least after the upper launch vehicle portion has cleared the launcher.

[0033] Alternatively, for example, the launch load application member comprises a launch vehicle coupling portion and a base portion, , wherein the launch vehicle coupling portion is reversibly and selectively affixable with respect to the launch vehicle to enable selective coupling / decoupling with respect to the launch vehicle, wherein the base portion is connectable to the piston element, and wherein the launch vehicle coupling portion is configured for enabling the launch vehicle to pivot with respect to the base portion about the lateral axis. For example, the launch vehicle comprises a coupling area at a bottom end of the launch vehicle, and wherein the coupling area is configured for coupling with launch vehicle coupling portion such as to enabling the launch vehicle to pivot with respect to the base portion about the lateral axis.Additionally or alternatively, for example, the launch load application member comprises a launch vehicle coupling portion, a base portion, and a pivotable joint therebetween, wherein the launch vehicle coupling portion is reversibly and selectively affixable to enable selective coupling / decoupling with respect to the launch vehicle, wherein the base portion is connectable to the piston element, and wherein the pivotable joint is configured for enabling the launch vehicle coupling portion to pivot with respect to the base portion about the lateral axis. For example, the launch vehicle coupling portion is provided at a bottom end of the launch vehicle, and the launch vehicle coupling portion constitutes part of the launch vehicle.

[0034] Additionally or alternatively, for example, the piston assembly comprises a support base having an upper face for coupling with or abutting against a bottom end of the launch vehicle. For example, the support base is movably mounted with respect to the launch load application member. For example, at the first axial position, and during launch as the piston assembly is accelerated between the first axial position and the second axial position, the launch vehicle is supported by the support base. Additionally or alternatively, for example, the bottom end of the launch vehicle is mechanically in load bearing contact with the upper face of the support base, prior to and during launch. Additionally or alternatively, for example, load-bearing contact between the piston assembly and the launch vehicle, while the launch vehicle is accommodated within the launch lumen as well as during launch up to being separated from the piston assembly, is exclusively via the launch load application member and also via the base member. Additionally or alternatively, for example, the launch load application member axially spaces the base member from the upper facing surface of the piston member, at least in the first axial position. Additionally or alternatively, for example, the load application member comprises a launch vehicle coupling portion, a base portion, and a pivotable joint therebetween. For example, the launch vehicle coupling portion is connected to the support base, the support base being for coupling with the launch vehicle in an abutting relationship. Additionally or alternatively, for example, the base portion is connectable to the piston element. Additionally or alternatively, for example, the pivotable joint is configured for enabling the launch vehicle coupling portion, together with the launch vehicle, to pivot with respect to the base portion about a lateral axis. Additionally or alternatively, for example, the pivotable joint permanently and pivotably interconnectsthe piston element with the support base, such that after launch the piston element and the support base remain pivotably interconnected. For example, the pivotable joint comprises any one of a hinge arrangement and a universal joint arrangement. Additionally or alternatively, for example, the pivotable joint detachably and pivotably interconnects the piston element with the support base, such that after launch the piston element and the support base detach from one another via the pivotable joint. For example, the launch vehicle coupling portion comprises a concave surface, and the pivotable joint has a complementary convex surface, and wherein the concave surface and the convex surface have a common center of curvature. For example, during launch and as the piston assembly reaches the second axial position, the support base is ejected together with the launch vehicle coupling portion.

[0035] Additionally or alternatively, for example, the piston element pivots with the respective support base about the center of curvature.

[0036] Additionally or alternatively, for example, the concave surface is cylindrical and wherein the convex surface is cylindrical, or, wherein the concave surface and the convex surface are each part of a sphere.

[0037] Additionally or alternatively, for example, the launch vehicle coupling portion is embedded in the bottom surface of the support base and is formed as a recess.

[0038] Additionally or alternatively, for example, the launch load application member is movably positionable with respect to said upper facing surface of the piston member to thereby enable the magnitude of the offset dimension to be selectively adjusted.

[0039] Additionally or alternatively, for example, the piston assembly is rotatably positionable with respect to the central longitudinal axis to thereby enable an azimuth of the launch vehicle to be selectively adjusted.

[0040] Additionally or alternatively, for example, the actuation system comprises a hollow telescopic piston rod axially movable along the central longitudinal axis, powered by high pressure gas generated by a pyrotechnic source, to thereby expand the telescopic piston rod thereby carrying the piston assembly to the second axial position.

[0041] Additionally or alternatively, for example, the actuation system operates to selectively generate an actuation force that is applied at a center of the piston element, theactuation force being co-axial with the central longitudinal axis of the launch lumen, and wherein the actuation force induces the launch force at the launch load application member.

[0042] According to this aspect of the presently disclosed subject matter, there is also provided a launcher for selectively launching a launch vehicle, the launcher comprising:

[0043] a launch tube defining a launch tube lumen having a central longitudinal axis, the launch tube lumen having an internal diameter being sized to enable accommodating the launch vehicle therein prior to launch;

[0044] a piston assembly movably mounted within the launch tube lumen, and selectively axially movable along a piston central axis, nominally co-axial with the central longitudinal axis, between a first axial position and a second axial position to thereby eject the launch vehicle from the launch tube during launch;

[0045] the piston assembly comprising a piston member and a launch load application member, the piston member having an upper facing surface, the launch load application member projecting upwardly from the upper facing surface, wherein load-bearing contact between the piston assembly and the launch vehicle is via the launch load application member, and wherein the launch load application member is laterally off-set with respect to the central longitudinal axis (and to the piston central axis) by a non-zero offset dimension;

[0046] an actuation system coupled to the piston assembly and operative to selectively accelerate the piston assembly from the first axial position to the second axial position, thereby imparting a launch force to the launch vehicle via the launch load application member during launch;

[0047] wherein in the first axial position the launch vehicle is accommodated in the launch tube lumen, and wherein in the second axial position the launch vehicle is provided with sufficient momentum to be fully ejected from the launch tube lumen.

[0048] For example, said launch lumen comprises a lumen axial length parallel to the central longitudinal axis between said first axial position and a launch tube upper opening.

[0049] Additionally or alternatively, for example, said launch force is nominally parallel to said central longitudinal axis.Additionally or alternatively, for example, the piston assembly allows pivoting of the launch vehicle along at least one lateral axis orthogonal to the central longitudinal axis, or, the piston assembly allows pivoting of the launch vehicle with respect to the piston assembly along at least one lateral axis orthogonal to the central longitudinal axis, said lateral axis being parallel with said turning axis.

[0050] Additionally or alternatively, for example, the launch load application member comprises a launch vehicle coupling portion, a base portion, and a pivotable joint therebetween, wherein the launch vehicle coupling portion is reversibly and selectively affixable to enable selective coupling / decoupling with respect to the launch vehicle, wherein the base portion is connectable to the piston element, and wherein the pivotable joint is configured for enabling the launch vehicle coupling portion to pivot with respect to the base portion about the lateral axis. For example, the launch vehicle coupling portion is provided at a bottom end of the launch vehicle, and the launch vehicle coupling portion constitutes part of the launch vehicle.

[0051] Additionally or alternatively, for example, the piston assembly comprises a support base having an upper face for coupling with or abutting against a bottom end of the launch vehicle. For example, the support base is movably mounted with respect to the launch load application member. For example, at the first axial position, and during launch as the piston assembly is accelerated between the first axial position and the second axial position, the launch vehicle is supported by the support base. Additionally or alternatively, for example, the bottom end of the launch vehicle is mechanically in load bearing contact with the upper face of the support base, prior to and during launch. Additionally or alternatively, for example, load-bearing contact between the piston assembly and the launch vehicle, while the launch vehicle is accommodated within the launch lumen as well as during launch up to being separated from the piston assembly, is exclusively via the launch load application member and also via the base member. Additionally or alternatively, for example, the launch load application member axially spaces the base member from the upper facing surface of the piston member, at least in the first axial position. Additionally or alternatively, for example, the load application member comprises a launch vehicle coupling portion, a base portion, and a pivotable joint therebetween. For example, the launch vehicle coupling portion is connected to the support base, the support base being for coupling with the launch vehicle in an abuttingrelationship. Additionally or alternatively, for example, the base portion is connectable to the piston element. Additionally or alternatively, for example, the pivotable joint is configured for enabling the launch vehicle coupling portion, together with the launch vehicle, to pivot with respect to the base portion about a lateral axis. Additionally or alternatively, for example, the pivotable joint permanently and pivotably interconnects the piston element with the support base, such that after launch the piston element and the support base remain pivotably interconnected. For example, the pivotable joint comprises any one of a hinge arrangement and a universal joint arrangement. Additionally or alternatively, for example, the pivotable joint detachably and pivotably interconnects the piston element with the support base, such that after launch the piston element and the support base detach from one another via the pivotable joint. For example, the launch vehicle coupling portion comprises a concave surface, and the pivotable joint has a complementary convex surface, and wherein the concave surface and the convex surface have a common center of curvature. For example, during launch and as the piston assembly reaches the second axial position, the support base is ejected together with the launch vehicle coupling portion.

[0052] Additionally or alternatively, for example, the piston element pivots with the respective support base about the center of curvature.

[0053] Additionally or alternatively, for example, the concave surface is cylindrical and wherein the convex surface is cylindrical, or, wherein the concave surface and the convex surface are each part of a sphere.

[0054] Additionally or alternatively, for example, the launch vehicle coupling portion is embedded in the bottom surface of the support base and is formed as a recess.

[0055] Additionally or alternatively, for example, the launch load application member is movably positionable with respect to said upper facing surface of the piston member to thereby enable the magnitude of the offset dimension to be selectively adjusted.

[0056] Additionally or alternatively, for example, the piston assembly is rotatably positionable with respect to the central longitudinal axis to thereby enable an azimuth of the launch vehicle to be selectively adjusted.Additionally or alternatively, for example, the actuation system comprises a hollow telescopic piston rod axially movable along the central longitudinal axis, powered by high pressure gas generated by a pyrotechnic source, to thereby expand the telescopic piston rod thereby carrying the piston assembly to the second axial position.

[0057] Additionally or alternatively, for example, the actuation system operates to selectively generate an actuation force that is applied at a center of the piston element, the actuation force being co-axial with the central longitudinal axis of the launch lumen, and wherein the actuation force induces the launch force at the launch load application member.BRIEF DESCRIPTION OF THE DRAWINGS

[0058] In order to better understand the subject matter that is disclosed herein and to exemplify how it may be carried out in practice, embodiments will now be described, by way of non-limiting example only, with reference to the accompanying drawings, in which:

[0059] Fig. 1 is a schematic cross-sectional side view of a launcher, prior to launch, according to a first example of the presently disclosed subject matter, with the piston element in the first axial position.

[0060] Fig. 2 is a schematic cross-sectional side view of the example of Fig.l, just after launch, with the piston element in the second axial position.

[0061] Fig. 3 is a schematic side view of the launch vehicle of the launcher example of Fig. 1, according to a first example of the presently disclosed subject matter.

[0062] Fig. 4 is a schematic cross-sectional side view of an alternative variation of the launch vehicle example of Fig. 3.

[0063] Fig. 5 is a schematic side view of a portion of the launcher example of Fig. 1, prior to launch.

[0064] Fig. 6 is a schematic side view of the portion of the launcher example of Fig. 5 illustrating maximum pivoting.

[0065] Fig. 7 is a schematic cross-sectional side view of the example of Fig.l, with the piston element in the third axial position.

[0066] Fig. 8 is a schematic cross-sectional side view of the example of Fig.l, with the piston element in the second axial position.

[0067] Fig.9 is a schematic illustration of the example of Fig.1, illustrating various stages of launch.

[0068] Fig. 10 is a schematic side view of an alternative variation of the piston assembly example of Fig. 1.

[0069] Fig. 11 is a schematic side view of an alternative variation of the piston assembly example of Fig. 10.

[0070] Fig. 12A is a schematic side view of another alternative variation of the launch vehicle and piston assembly example of Fig. 1, at the first axial position; Fig. 12B is a schematic side view of the example of Fig. 12A, at the second axial position.DETAILED DESCRIPTION

[0071] Referring to Figs. 1 and 2, a launch system according to a first example of the presently disclosed subject matter, generally designated with reference numeral 10, comprises a launch vehicle 100 and a launcher 300.

[0072] As will become clearer herein, the launch system 10 is particularly configured for providing the launch vehicle 100 with a desired elevation angle after cold launch from the launcher 300, i.e., once the launch vehicle 100 has been ejected from and has fully cleared the launcher 300, and prior to the propulsion system 150 of the launch vehicle 100 being actuated to propel the launch vehicle 100 towards a target.

[0073] Referring also to Fig. 3, the launch vehicle 100 defines a central vehicle longitudinal axis VLA, and comprises an upper vehicle portion 110 and a lower vehicle portion 130.

[0074] In at least this example, the upper launch vehicle portion 110 is axially contiguous with the lower launch vehicle portion 130.

[0075] In any case, the said upper launch vehicle portion 110 has a first length LI and a first diameter DI, and the lower launch vehicle portion has a second length L2 and a second diameter D2.

[0076] According to an aspect of the presently disclosed subject matter, the first diameter DI is greater than the second diameter D2. This aspect of the presently disclosed subject matter shall be discussed in more detail below.

[0077] The propulsion system 150 of launch vehicle 100 comprises a rocket motor system that is selectively actuable for propelling the launch vehicle 100 after launch from the launcher 300, i.e., once the launch vehicle 100 has been ejected from and has fully cleared the launcher 300. The rocket motor system can include one or more rocket engines. The one or more rocket engines can be liquid fuel engines for example, the propulsion system also including suitable liquid fuel tanks (not shown). Alternatively, the one or more rocket engines can be solid fuel engines for example, the propulsion system also including suitable solid fuel (not shown).

[0078] The launch vehicle 100 can also comprises one or more of: a guidance system, a communication system, a payload and so on (not shown). The launch vehicle 100 can alsocomprise a plurality of guidance fins that deploy after launch to provide stability and control to the launch vehicle 100 when the forward speed is sufficient high to enable suitable aerodynamic forces to be generated by the airflow over the fins.

[0079] The launch vehicle 100 also has a nose 105 that is aerodynamically contoured in at least this example. For example, the nose can have a conical or ogive shape.

[0080] In at least this example, the one or more rocket motors of the rocket motor system lack nozzle guide vanes in the path of the respective rocket engine exhaust. In other alternative variations of this example, the respective one or more rocket motors of rocket motor system include nozzle guide vanes in the path of the respective rocket engine exhaust.

[0081] In at least this example, the launch vehicle has a center of gravity CG that is laterally aligned with the vehicle longitudinal axis VLA.

[0082] In at least this example, the launch vehicle 100 constitutes a projectile, and comprises an outer skin 140 defining an outside of the launch vehicle 100. The outer skin 140 comprising an upper outer skin portion 141 corresponding to the upper launch vehicle portion 100 and defining the first diameter DI, and a lower skin portion 143 corresponding to the lower launch vehicle portion 130 and defining the second diameter D2. In such examples, the launch vehicle 100 integrally defines a projectile that is propelled towards the target after launch.

[0083] However, in at least some alternative variations of the above examples, the respective launch vehicle can be configured differently. For example, and referring to Fig.

[0084] 4, the respective launch vehicle 100' is similar to the launch vehicle 100 disclosed above, mutatis mutandis, but with the following differences. In at least this example, the launch vehicle 100' comprises a sabot 160' and a projectile 170'. The projectile 170' has an outer skin 140' defining an outside of the projectile 170'. The outer skin 140' comprises an upper outer skin 141' and a lower outer skin 143'. The sabot 160' is in overlying relationship with the upper outer skin 141'. The sabot 160' corresponds to the respective upper launch vehicle portion 110', and defines the first diameter DI. The lower skin portion 143' corresponds to the lower launch vehicle portion 130' and defines the respective second diameter D2'. In at least this example, the sabot 160' is operative to become detached from the projectile 170' after the launch vehicle 100' is ejected from the respective launcher. For example, the sabot 160' can be made from two or more sabot portions that are fall apart and away from oneanother and from the projectile 170' after launch. It is to be noted that the longitudinal length of the sabot 160' can be reduced, so long as the bottom end of the sabot 160' is at second length L2 from the uppermost point of the launch vehicle 100'.

[0085] Referring again to Fig. 1 and Fig. 2, the launcher 300, which is per se novel, comprises a launch tube 350, a piston assembly 400, and an actuation system 500.

[0086] The launch tube 350 defines a launch tube lumen 355 having a central longitudinal axis CLA. The launch tube lumen 355 is bound by internal surface of the walls 356 of the launch tube 350. In at least this example each one of the launch tube 350, the launch tube lumen 355, and the internal surface of the walls 356 of the launch tube 350, is cylindrical.

[0087] The launch tube lumen 355 has an internal diameter D3 that is sized to enable accommodating the launch vehicle 100 therein at least prior to launch.

[0088] The internal diameter D3 is greater than the first diameter DI by a spacing or clearance, having a clearance dimension CD. The spacing or clearance radially separates the upper vehicle portion 110 from the by the internal surface of the walls 356 of the launch tube 350 by the clearance dimension CD, circumferentially around the upper vehicle portion 110. The clearance dimension CD is, on the one hand, sufficient small to maintain the launch vehicle 100 snugly in place within the launch tube lumen 355 with the vehicle longitudinal axis VLA nominally co-axial with the central longitudinal axis CLA, prior to launch as well during transportation, and, on the other hand, sufficiently large such as to allow the upper vehicle portion 110 to pass through the upper part of the launch tube lumen 355 without inducing high frictional forces.

[0089] The launch tube 350 has an open upper end 351 defined by a free edge, and a closed lower end 359.

[0090] In at least this example, the launch tube 350 can comprise a cap 360 for selectively closing upper end 351. The cap 360 can be opened just prior to launch for example via hinge arrangement. Alternatively, the cap 360 can be fracturable, such as during launch the launch vehicle pierces and fractures the 360 to allow the launch vehicle to exit the launch tube 350. In other alternative variations of these examples, the cap can be omitted.Ref erring again also to Fig. 3, the piston assembly 400 is movably mounted within the launch tube lumen 355, and is selectively axially movable within the launch tube lumen 355 along the central longitudinal axis CLA through a stroke ST, between a first axial position AX1 and a second axial position AX2, to thereby eject the launch vehicle 100 from the launch tube 350 and thus from the launcher 300.

[0091] In the first axial position AX1 the launch vehicle 100 is fully accommodated in the launch tube lumen 355 (Fig. 1), whereas in the second axial position AX2 the launch vehicle 100 is fully ejected from the launch tube lumen 355 (Fig. 2), and has vertically cleared the open upper end 351.

[0092] In at least this example, the vehicle longitudinal axis VLA is nominally co-axial with the central longitudinal axis CLA when the launch vehicle 100 is accommodated in the launch tube lumen 355 and the piston assembly 400 is in the first axial position AX1.

[0093] The launch lumen 355 comprises a lumen axial length LL parallel to the central longitudinal axis CLA between the first axial position AX1 and the launch tube upper opening 351. The launch vehicle 100 comprises a launch vehicle axial length L, wherein the launch vehicle axial length L is not greater than the lumen axial length LL.

[0094] In at least this example, the piston assembly 400 comprises a piston member 410, a launch load application member 450, and a support base 490.

[0095] In at least this example, the piston member 410 is nominally cylindrical, having a cylindrical periphery 415 facing the internal surface of the walls 356 of the launch tube 350.

[0096] The piston assembly 400 has a central piston axis (also interchangeably referred to herein as "piston axis" or "piston central axis") PA, nominally co-axial with central longitudinal axis CLA, and passing through the geometrical center of the piston member 410. Thus, the piston assembly 400 is movably mounted within the launch tube lumen 355 and selectively axially movable along the piston axis between the first axial position AX1 and the second axial position AX2.

[0097] The piston member 410 comprises an upper facing surface 430 and a lower facing surface 440.For example, the support base 490 comprises an upper face 498 for coupling with or at least abutting the bottom end of the launch vehicle 100, and a bottom end 495 facing the upper facing surface 430 of the piston member 410. For example, the support base 490 can be disc-shaped.

[0098] At the first axial position AX1, and referring to Fig. 5, the bottom end 495 is spaced from the upper facing surface 430 by a spacing SX in a direction along the piston axis PA.

[0099] The support base 490 has a thickness dimension LP between the upper face 498 and the bottom end, in a direction parallel to the vehicle longitudinal axis VLA.

[0100] The launch load application member 450 projects upwardly from the upper facing surface 430, and the support base 490 is movably mounted with respect to the launch load application member 450.

[0101] At the first axial position AX1, and during launch as the piston assembly 400 is accelerated between the first axial position AX1 and the second axial position AX2, the launch vehicle 100 is supported by the support base 490. Thus, the bottom end 195 of the launch vehicle 100 is mechanically in load bearing contact with the upper face 498 of the support base 490, prior to and during launch.

[0102] According to an aspect of the presently disclosed subject matter, load-bearing contact between the piston assembly 400 and the launch vehicle 100, while the launch vehicle 100 is accommodated within the launch lumen 355 as well as during launch up to being separated from the piston assembly 400, is exclusively via the launch load application member 450, and in at least this example, also via the base member 490.

[0103] According to this aspect of the presently disclosed subject matter, the launch load application member 450 is laterally off-set with respect to the central longitudinal axis CLA (and thus also with respect to the piston axis PA) by a non-zero offset dimension OD. In particular, the launch load application member 450 is laterally off-set with respect to the center of gravity CG while the launch vehicle 100 is accommodated within the launch lumen 355 as well as during launch up to the launch vehicle 100 being separated from the piston assembly 400.The launch load application member 450 also axially spaces the base member 490 (and thus also a bottom end 190 of the launch vehicle 100) from the upper facing surface 430, at least in the first axial position AX1.

[0104] The actuation system 500 is operatively coupled to the piston assembly 400.

[0105] The actuation system 500 is operative to selectively accelerate the piston assembly 400 from the first axial position AX1 to the second axial position AX2, thereby imparting a launch force LF to the launch vehicle 100 via the launch load application member 450, and thereby launching the launch vehicle 100 from the launcher 300.

[0106] The actuation system 500 can comprise any suitable mechanism for selectively accelerating the piston assembly 400 from the first axial position AX1 to the second axial position AX2. For example, a hollow telescopic piston rod (not shown) is axially movable along the piston axis PA (and thus from the central longitudinal axis CLA), and is powered by high pressure gas generated by a pyrotechnic source, to thereby expand the telescopic piston rod thereby carrying the piston assembly 500 to the second axial position AX2. For example, the pyrotechnic source can include any suitable pyrotechnic gas generator.

[0107] Alternatively for example, any other suitable actuation system can be used for accelerating the piston assembly 400 the first axial position AX1 to the second axial position AX2, and many such systems are well known in the art.

[0108] In any case, the actuation system 500 operates to selectively generate an actuation force AF that is applied at the axial center 405 of the piston element 410, on the lower facing surface 440, and the actuation force AF is co-axial with the piston axis PA and the central longitudinal axis CLA of the launch lumen 355. The actuation force AF induces the launch force LF at the launch load application member 490.

[0109] It is to be noted that the launch force LF that is applied by the piston assembly 400 onto the launch vehicle 100 is radially spaced from the piston axis PA, and thus from the central longitudinal axis CLA of the launch lumen 355, by offset dimension OD.

[0110] The launch force LF is nominally parallel to the central longitudinal axis CLA.As disclosed above, in at least this example, the launch vehicle 100 has a center of gravity CG that is laterally aligned with the vehicle longitudinal axis VLA. Thus, since the launch force LF is off-set laterally by offset dimension OD with respect to central longitudinal axis CLA, and thus with respect to the center of gravity CG at least at the beginning of the launch with the launch vehicle 100 in the second axial position AX2, the launch force LF induces a turning moment TM on the launch vehicle about a turning axis TA orthogonal to the central longitudinal axis CLA.

[0111] The turning moment TM is the product of the launch force LF and the moment arm MA between the launch force LF and the center of gravity CG.

[0112] The turning axis TA intersects the center of gravity of gravity CG of the launch vehicle 100.

[0113] In the first axial position AX1 the moment arm MA is equal to the offset dimension OD. However, during at least a latter part of the launch process, the magnitude of the moment arm MA increases as will become clearer herein.

[0114] Referring also to Figs. 5 and 6, the launch load application member 450 allows pivoting of the launch vehicle 100 with respect to the piston assembly 400 (and thus pivoting of the vehicle longitudinal axis VLA with respect to the central longitudinal axis CLA) along at least one lateral axis APA orthogonal to the central longitudinal axis CLA. In at least this example, the at least one lateral axis APA is parallel with respect to the turning axis TA.

[0115] As will become clearer herein, such pivoting has a maximum limit schematically illustrated in Fig. 6 corresponding to the far end 496 of the bottom end 495 of the base element 490 coming into abutting contact with upper facing surface 430 of the piston element 410. However, and as will become clearer herein, in at least some examples such maximal pivoting is not reached in view of the relative sizes of the first diameter DI, second diameter D2, second length L2, and internal diameter D3.

[0116] The launch load application member 450 comprises a launch vehicle coupling portion 452, a base portion 456, and a pivotable joint therebetween 454. The launch vehicle coupling portion 452 is connected to the support base 490, which is in turn configured for coupling with the launch vehicle 100 in an abutting relationship. The baseportion 456 is connectable to the piston element 410, in particular to the upper facing surface 430. The pivotable joint 454 is configured for enabling the launch vehicle coupling portion 452 (together with the launch vehicle 100) to pivot with respect to the base portion 456 about the lateral axis APA. In at least this example, the pivotable joint 454 permanently and pivotably interconnects the piston element 410 with the support base 490. Thus, after launch the piston assembly 400 remains as is, with the piston element 410 and the support base 490 pivotably interconnected. For example, the pivotable joint 454 can comprise a hinge arrangement, or a universal joint arrangement.

[0117] However, in at least some alternative variations of the above examples, and referring to Fig. 10, the respective pivotable joint 454’ does not permanently interconnect the respective piston element 410’ with the respective support base 490’. Rather, the respective pivotable joint 454’ detachably and pivotably interconnects the piston element 410' with the support base 490', such that after launch the piston element 410' and the support base 490' detach from one another via the pivotable joint 454'.

[0118] For example, the respective launch vehicle coupling portion 452' comprises a concave surface 452A', whereas the respective pivotable joint 454’ has a complementary convex surface 452B', wherein the concave surface 452A' and the convex surface 452B' have a common center of curvature at APA'. Other than being in abutment over one another, the launch vehicle coupling portion 452' and the pivotable joint 454’ are not pivotably affixed or otherwise affixed to one another. Thus, in this example, during launch and as the respective piston assembly 400' reaches the respective second axial position, the support base 490’ is ejected together with the launch vehicle coupling portion 452'. The support base 490’ can be in the form of a disc, flange, or ring, for example.

[0119] In any case, the respective piston element 410’ pivots with the respective support base 490’ about the center of curvature APA'. The concave surface 452A' and the convex surface 452B' can each be cylindrical, in which case the center of curvature APA' is an axis, and pivoting is only possible about this axis. Alternatively, the concave surface 452A' and the convex surface 452B' can each be part of a sphere (for example hemispherical), in which case the center of curvature APA' is a point, and pivoting is possible along a plurality of directions. In this example, the launch vehicle coupling portion 452' projects from a bottom surface of the support base 490’. However, in at leastsome alternative variations of the example of Fig. 10, and referring now to Fig. 11, the launch vehicle coupling portion 452' can be embedded in the bottom surface of the support base 490’, and is formed as a recess.

[0120] It is to be further noted that in at least some alternative variations of the above examples, and referring to Fig. 12A and Fig. 12B, the support base can be omitted, and the respective launch vehicle coupling portion 452' can be provided at the bottom end of the launch vehicle 100, as part of the launch vehicle 100. For example, the launch vehicle 100, in particular the launch vehicle coupling portion 452', comprises a coupling area 452A' at a bottom end of the launch vehicle 100, and for example the coupling area 452A' is configured for coupling with launch vehicle coupling portion of the launch load application member 450' of the piston assembly 400', such as to enabling the launch vehicle 100 to pivot with respect to the base portion about the lateral axis. The coupling area 452A' is in the form of a concave surface, whereas the respective pivotable joint of the launch load application member 450' has a complementary convex surface 452B', and projects upwards from the piston member 410'. The concave surface 452A' and the convex surface 452B' have a common center of curvature at APA' when in abutment with one another. However, other than being in abutment over one another at least at the first axial position AX1, the launch vehicle coupling portion 452' and the launch load application member 450' are not pivotably affixed or otherwise affixed to one another. For example, the coupling area 452A' can be provided in a flange, ring, or bottom edge, at the bottom end of the launch vehicle 100. The coupling area 452A' can be concave, and complementary to the convex form of the respective launch vehicle coupling portion.

[0121] In all the above examples, the aforesaid pivoting about the respective lateral axis APA is essentially free pivoting, and only limited by the scenario illustrated in Fig. 6 for example, and by the relative sizes of the first diameter DI, second diameter D2, and internal diameter D3, and the magnitude of the second length L2.

[0122] As can be understood from Fig. 1, the relatively small magnitude clearance dimension CD with respect to the first diameter DI results in that the launch vehicle 100 is essentially prevented from pivoting about the lateral axis APA within the launch lumen 355 during launch while the upper launch vehicle portion 110 is within the launch lumen 355. Practically, it is possible for the launch vehicle 100 to be tilted slightly towards the internal surface of the walls 356 of the launch tube 350, and for the upper launch vehicleportion 110 to abut against the internal surface of the walls 356. Thus, at the first axial position AX1 and while the upper launch vehicle portion 110 is within the launch lumen 355, the support base 490 is nominally orthogonal to the central longitudinal axis CLA.

[0123] On the other hand, as the launch vehicle 100 is raised from the first axial position AX1 towards the second axial position AX2 during the launching procedure, as soon as the upper launch vehicle portion 110 has cleared the open upper end 351, the launch vehicle 100 is now free to tilt towards the internal surface of the walls 356, under the action of the turning moment TM, until the external surface of the lower launch vehicle portion 130 abuts against the internal surface of the walls 356.

[0124] Referring to Fig. 7, the piston element 410 reaches a third axial position AX3, intermediate between the first axial position AX1 and the second axial position AX2, corresponding to the upper launch vehicle portion 110 having just cleared the open upper end 351. The launch vehicle 100 immediately pivots under the action of the turning moment TM by a first pivot angle 01 corresponding to the external surface of the lower launch vehicle portion 130 being in abutment against the internal surface of the walls 356.

[0125] The larger the magnitude of the first length LI, the longer the time from actuation until the launch vehicle 100 can begin to pivot.

[0126] The first pivot angle 01 is related to the second length L2, the thickness LP of the support base 490, and the radial clearance OP between the bottom end 190 of the launch vehicle 100 and the internal surface of the walls 356, as follows:

[0127] first pivot angle 01 = arcsine (OP / (L2 + LP))

[0128] The magnitude of the radial clearance OP is related to the second diameter D2 and the internal diameter D3, as follows:

[0129] OP = (D3 - D2) / 2

[0130] Concurrently, the launch force LF has a first moment arm MAI that is nominally just above or equal to the offset dimension OD, and the launch force LF remains parallel to the central longitudinal axis CLA.Thus, the larger the magnitude of the second length L2, the smaller the first pivot angle 01; the larger the difference between the internal diameter D3 and the second diameter D2, the larger the first pivot angle 01.

[0131] Typically, the thickness LP of the support base 490 is significantly smaller than the second length L2.

[0132] Furthermore, the larger the first length LI, the longer the pivoting is delayed after launch.

[0133] Referring to Fig. 8, as the piston assembly 400 continues to move from the third axial position AX3 to the second axial position AX2, the pivot angle 0 continually increases, reaching a second pivot angle 02 at the second axial position AX2. Concurrently, the magnitude of the moment arm MA also continually increases to a second moment arm MA2 at the second axial position AX2. In the second axial position AX2, the external surface of the upper launch vehicle portion 110 abuts the edge of the open upper end 351 as an axial location AL that is spaced from the bottom end 190 of the launch vehicle 100 along the vehicle longitudinal axis VLA by a third length L3.

[0134] The second pivot angle 02 is related to the third length L3, the thickness LP of the support base 490, and the radial clearance OP between the bottom end 190 of the launch vehicle 100 and the internal surface of the walls 356, as follows:

[0135] second pivot angle 02 = arcsine (OP / L3 + LP))

[0136] Concurrently, the launch force LF has a second moment arm MA2 that is significantly greater than the first moment arm MAI or the offset dimension OD.

[0137] Thus, the larger the magnitude of the third length L3 the smaller the second pivot angle 02; the larger the difference between the internal diameter D3 and the second diameter D2, the larger the second pivot angle 02.

[0138] Thus, as the launch vehicle 100 is launched from the launcher 300, and transits from the first axial position AX1 through the third axial position AX3 to the second axial position AX2, the launch vehicle 100 is pivoted by a first pivot angle range A01 about the lateral axis APA within the launch lumen 355.This pivot angle range A0 is from nominally zero (at the first axial position AX1) to the second pivot angle 02 (at the second axial position AX2).

[0139] Fig. 9 schematically illustrates various stages in the complete launch procedure according to the above examples.

[0140] At "A" in Fig. 9, the system 10 is at just prior to or at launch, with the piston assembly 400 in the first axial position AX1, corresponding to Fig. 1.

[0141] At "B" in Fig. 9, the system 10 is in the first phase of launch, in which the piston assembly 400 has reached the third axial position AX3 and the upper launch vehicle portion 110 has cleared the open upper end 351, corresponding to Fig. 7. Thus, the launch vehicle 100 has not been pivoted in any significant manner.

[0142] At "C" in Fig. 9, the system 10 is in the second phase of launch, in which the piston assembly 400 has transited to the second axial position AX2 and the launch vehicle has pivoted to the second pivot angle 02, corresponding to Fig. 8. At the second axial position AX2, the launch vehicle 100 is provided with sufficient momentum by the piston assembly 400 to be fully ejected from the launch tube lumen 355.

[0143] At "D" in Fig. 9, the system 10 is in the third phase of launch, in which the launch vehicle 100 has cleared the open upper end 351, corresponding to Fig. 2. Thus, after the configuration shown at "C", the launch vehicle automatically decouples with respect to the piston assembly 400, the upward momentum causes the launch vehicle 100 to continue in an upward direction, and the turning moment TM, while beginning to decelerate in the absence of the launch force LF acting on the launch vehicle 100 continues to pivot the launch vehicle 100 about the center of gravity CG.

[0144] At "E" in Fig. 9, the launch vehicle 100 has freely pivoted to a desired third pivot angle 03 after a predetermined but short time interval, sufficient such that the launch vehicle 100 has not lost height, whereupon the propulsion system 150 is actuated, propelling the launch vehicle 100 towards the target.

[0145] In examples in which the launch vehicle is configured as the launch vehicle 100' of Fig. 4, the sabot 160' is discarded at "D" or "E", and the respective rocket motor system is actuated, propelling the projectile 170' towards the target.It is to be noted that as the launch vehicle 100 is launched from the launcher 300, and transits from just past the third axial position AX3 to the second axial position AX2, the launch vehicle 100 is pivoted by a second pivot angle range A02 about the lateral axis APA within the launch lumen 355.

[0146] This second pivot angle range A02 is given by the difference between the second pivot angle 02 and the first pivot angle 01, i.e.:

[0147] A02 = 02 - 01

[0148] The larger the second length L2, the larger the second pivot angle range A02. The smaller the third length L3, the larger the second pivot angle range A02.

[0149] The magnitude of the first length LI essentially determines when the pivoting commences, while the magnitudes of the second diameter D2, second length L2 and the third length L3 determine the first pivot angle range A01 and the second pivot angle range A02.

[0150] The magnitude of the launch force LF, and the magnitude of the offset dimension OD, together with second pivot angle 02, determine the third pivot angle 03.

[0151] The third pivot angle 03 corresponds to the desired elevation angle for the launch vehicle 100 just prior to activating the rocket motor system.

[0152] Thus, by appropriately controlling or choosing the magnitudes of the first length LI, the second length L2, the third length L3, the first diameter DI, the second diameter D2, the internal diameter D3, launch force LF, and the offset dimension OD, the desired third pivot angle 03, and thus the desired elevation angle, can be obtained.

[0153] In some examples, the first pivot angle range is correlated to a first ratio of the offset dimension OD to the second diameter D2, and to a second ratio of the second length L2 to the lumen axial length LL. For example, the first ratio is greater than zero, and up to 0.5.

[0154] In the above examples, the upper vehicle portion 110 is nominally cylindrical (excluding the nose 105), having a uniform circular cross section along the first length LI and uniform first diameter DI. Similarly, in the above examples, the lower launchvehicle portion 130 is nominally cylindrical, having a uniform circular cross section along the second length L2 and uniform second diameter D2. However, in at least some alternative variations of the above examples, the respective upper vehicle portion can be non-cylindrical and / or have a non-cylindrical and / or non-uniform cross-section along the first length LI, and / or, the respective lower launch vehicle portion can be non-cylindrical and / or have a non-cylindrical and / or non-uniform cross-section along the second length L2. For example, the upper vehicle portion and / or the respective lower launch vehicle portion can be non-cylindrical and / or have a non-cylindrical and / or non-uniform crosssection along the first length LI or second length L2, respectively. For example, the upper vehicle portion and / or the respective lower launch vehicle portion can have a tapering (for example frustoconical) profile, and / or a triangular cross section, or other polygonal shaped cross section, or elliptical cross section, or superelliptical cross section.

[0155] It is to be noted that in the above examples, the launcher 300 is typically oriented vertically, such that the launch lumen 355 and the central longitudinal axis CLA are nominally vertical. However, in at least some alternative variations of these examples, the launcher 300 is instead oriented at a baseline elevation angle to the vertical, such that the launch lumen 355 and the central longitudinal axis CLA are nominally baseline elevation angle to the vertical. For example, such a baseline elevation angle can be in the range 0° to about 15°.

[0156] In any case, in at least the above examples and variations thereof, the launcher 300, as a unit, can be fixed to the ground in a position and oriented in azimuth such that the pivoting of the launch vehicle 100 occurs at the desired azimuth. In such examples, the respective lateral axis APA is orthogonal to a vertical plane at the desired azimuth.

[0157] Alternatively, the launcher 300 can be affixed on a turntable, the turntable being affixed to the ground or example, and the turntable can be rotated to thereby selectively enable the azimuth of the launcher 300 to be chosen such that the respective lateral axis APA is orthogonal to a vertical plane at the desired azimuth.

[0158] Alternatively, the launcher 300 can be affixed on a mobile launcher, for example a land or sea faring vehicle, and the vehicle can be maneuvered to thereby selectively enable the azimuth of the launcher 300 to be chosen such that the respective lateral axis APA is orthogonal to a vertical plane at the desired azimuth.Alternatively, the piston assembly 400 is rotatably mounted within the lumen 355 such as to enable the piston assembly 400 to be rotated about the central longitudinal axis CLA, to thereby selectively enable the azimuth of the launcher 300 to be chosen such that the respective lateral axis APA is orthogonal to a vertical plane at the desired azimuth.

[0159] In any case, in at least the above examples and variations thereof, additionally or alternatively, the respective launch load application member is in a radial offset dimension OD that is fixed. However, in at least some alternative variations of the above examples, the radial position of the respective launch load application member, and thus the magnitude of the respective offset dimension, can be varied in the respective launcher. For example, the respective launch load application member can be movably mounted to the respective piston member and to the respective support base, such that the radial position of the launch load application member with respect to the respective central longitudinal axis can be selectively varied prior to each launch if desired.

[0160] Thus, in at least some alternative variations of the examples of Figs. 1 to 11, the respective launch load application member of the respective piston assembly is movably positionable with respect to the respective upper facing surface to thereby enable the magnitude of the respective offset dimension to be electively adjusted. For example, the respective piston assembly comprises a radial rail member, and the launch load application member is movably mounted to the radial rail member, thereby allowing the launch load application member to be selectively moved to a range of different radial positions (with respect to the piston axis) along the radial rail member. In at least this example, the launch load application member can be locked at any desired radial position along the radial rail member, for example via screws, bolts, or any other suitable fastener.

[0161] Finally, it should be noted that the word “comprising” as used throughout the appended claims is to be interpreted to mean “including but not limited to”.

[0162] While there has been shown and disclosed examples in accordance with the presently disclosed subject matter, it will be appreciated that many changes may be made therein without departing from the scope of the presently disclosed subject matter as set out in the claims.

Claims

CLAIMS:

1. A launch system comprising a launcher and a launch vehicle:the launch vehicle comprising an upper launch vehicle portion having a first diameter and a lower launch vehicle portion having a second diameter, the first diameter being greater than the second diameter, the lower launch vehicle portion comprising a propulsion system selectively actuable for propelling the launch vehicle after launch from the launcher;the launcher comprising:a launch tube defining a launch tube lumen having a central longitudinal axis, the launch tube lumen having an internal diameter being sized to enable accommodating the launch vehicle therein prior to launch;a piston assembly movably mounted within the launch tube lumen, and selectively axially movable along a piston central axis, nominally co-axial with the central longitudinal axis, between a first axial position and a second axial position to thereby eject the launch vehicle from the launch tube during launch;the piston assembly comprising a piston member and a launch load application member, the piston member having an upper facing surface, the launch load application member projecting upwardly from the upper facing surface, wherein load-bearing contact between the piston assembly and the launch vehicle is via the launch load application member, and wherein the launch load application member is laterally off-set with respect to the central longitudinal axis by a nonzero offset dimension;an actuation system coupled to the piston assembly and operative to selectively accelerate the piston assembly from the first axial position to the second axial position, thereby imparting a launch force to the launch vehicle via the launch load application member during launch;wherein in the first axial position the launch vehicle is accommodated in the launch tube lumen, and wherein in the second axial position the launch vehicle is provided with sufficient momentum to be fully ejected from the launch tube lumen.

2. The launch system according to claim 1, wherein the launch vehicle has a vehicle longitudinal axis, and wherein the vehicle longitudinal axis is nominally co-axial with the central longitudinal axis when the launch vehicle is accommodated in the launch tube lumen and the piston assembly is in said first axial position.

3. The launch system according to any one of claims 1 to 2, wherein said launch lumen comprises a lumen axial length parallel to the central longitudinal axis between said first axial position and a launch tube upper opening, and wherein the launch vehicle comprises a launch vehicle axial length, wherein said launch vehicle axial length is not greater than said lumen axial length.

4. The launch system according to any one of claims 1 to 3, wherein said upper launch vehicle portion is axially contiguous with said lower launch vehicle portion, wherein said upper launch vehicle portion has a first length, and wherein said lower launch vehicle portion has a second length.

5. The launch system according to any one of claims 1 to 4, wherein said internal diameter is greater than said first diameter by a non-zero clearance dimension.

6. The launch system according to any one of claims 1 to 5, wherein said launch force is nominally parallel to said central longitudinal axis.

7. The launch system according to any one of claims 1 to 6, wherein the launch vehicle has a center of gravity, laterally spaced from the launch force, and wherein said launch force induces a turning moment on the launch vehicle about a turning axis orthogonal to said central longitudinal axis.

8. The launch system according to any one of claims 1 to 7, wherein the piston assembly allows pivoting of the launch vehicle along at least one lateral axis orthogonal to the central longitudinal axis.

9. The launch system according to any one of claims 1 to 7, wherein the piston assembly allows pivoting of the launch vehicle with respect to the piston assembly along at least one lateral axis orthogonal to the central longitudinal axis, said lateral axis being parallel with said turning axis.

10. The launch system according to any one of claims 8 to 9, wherein the launch vehicle is prevented from pivoting about the lateral axis within the launch lumen during launch while said upper launch vehicle portion is within the launch lumen.

11. The launch system according to any one of claims 8 to 10, wherein during launch the launch vehicle is pivoted by a first pivot angle range about the lateral axis within the launch lumen during launch after said upper launch vehicle portion has cleared the launch lumen.

12. The launch tube according to claim 11, wherein said first pivot angle range is correlated to a first ratio of the offset dimension to the second diameter, and to a second ratio of the second length to the lumen axial length.

13. The launch vehicle according to claim 12, wherein said first ratio is greater than zero, and up to 0.5.

14. The launch vehicle according to any one of claims 1 to 13, wherein the launch vehicle comprises an outer skin, the outer skin comprising an upper outer skin portion corresponding to the upper launch vehicle portion and defining said first diameter, and a lower skin portion corresponding to the lower launch vehicle portion and defining said second diameter.

15. The launch vehicle according to any one of claims 1 to 13, wherein the launch vehicle comprises a sabot and projectile, the projectile having an outer skin, the outer skin comprising an upper outer skin and a lower outer skin, the sabot being in overlying relationship with the upper outer skin, the sabot corresponding to the upper launch vehicle portion and defining said first diameter, the lower outer skin corresponding to the lower launch vehicle portion and defining said second diameter.

16. The launch vehicle according to claim 15, wherein the sabot is operative to become detached from the projectile after the launch vehicle is ejected from the launcher or at least after the upper launch vehicle portion has cleared the launcher.

17. The launch system according to any one of claims 1 to 16, wherein the launch load application member comprises a launch vehicle coupling portion and a base portion, wherein the launch vehicle coupling portion is reversibly and selectively affixable with respect to the launch vehicle to enable selective coupling / decoupling with respect to thelaunch vehicle, wherein the base portion is connectable to the piston element, and wherein the launch vehicle coupling portion is configured for enabling the launch vehicle to pivot with respect to the base portion about the lateral axis.

18. The launch system according to claim 17, wherein the launch vehicle comprises a coupling area at a bottom end of the launch vehicle, and wherein the coupling area is configured for coupling with launch vehicle coupling portion such as to enable the launch vehicle to pivot with respect to the base portion about the lateral axis..

19. The launch system according to any one of claims 1 to 16, wherein the piston assembly comprises a support base having an upper face for coupling with or abutting against a bottom end of the launch vehicle.

20. The launch system according to claim 19, wherein the support base is movably mounted with respect to the launch load application member.

21. The launch system according to claim 20, wherein at the first axial position, and during launch as the piston assembly is accelerated between the first axial position and the second axial position, the launch vehicle is supported by the support base.

22. The launch system according to any one of claims 19 to 21, wherein the bottom end of the launch vehicle is mechanically in load bearing contact with the upper face of the support base, prior to and during launch.

23. The launch system according to any one of claims 19 to 22, wherein load-bearing contact between the piston assembly and the launch vehicle, while the launch vehicle is accommodated within the launch lumen as well as during launch up to being separated from the piston assembly, is exclusively via the launch load application member and also via the base member.

24. The launch system according to any one of claims 19 to 23, wherein the launch load application member axially spaces the base member from the upper facing surface of the piston member, at least in the first axial position.

25. The launch system according to any one of claims 19 to 24, wherein the load application member comprises a launch vehicle coupling portion, a base portion, and a pivotable joint therebetween.

26. The launch system according to claim 25, wherein the launch vehicle coupling portion is connected to the support base, the support base being for coupling with the launch vehicle in an abutting relationship.

27. The launch system according to any one of claims 25 to 26, wherein the base portion is connectable to the piston element.

28. The launch system according to any one of claims 25 to 27, wherein the pivotable joint is configured for enabling the launch vehicle coupling portion, together with the launch vehicle, to pivot with respect to the base portion about a lateral axis.

29. The launch system according to any one of claims 25 to 28, wherein the pivotable joint permanently and pivotably interconnects the piston element with the support base, such that after launch the piston element and the support base remain pivotably interconnected.

30. The launch system according to claim 29, wherein the pivotable joint comprises any one of a hinge arrangement and a universal joint arrangement.

31. The launch system according to any one of claims 25 to 28, wherein the pivotable joint detachably and pivotably interconnects the piston element with the support base, such that after launch the piston element and the support base detach from one another via the pivotable joint.

32. The launch system according to claim 31, wherein the launch vehicle coupling portion comprises a concave surface, and the pivotable joint has a complementary convex surface, and wherein the concave surface and the convex surface have a common center of curvature.

33. The launch vehicle according to claim 32, wherein during launch and as the piston assembly reaches the second axial position, the support base is ejected together with the launch vehicle coupling portion.

34. The launch system according to any one of claims 32 to 33, wherein the piston element pivots with the respective support base about the center of curvature.

35. The launch system according to any one of claims 32 to 34, wherein the concave surface is cylindrical and wherein the convex surface is cylindrical.

36. The launch system according to any one of claims 32 to 34, wherein the concave surface and the convex surface are each part of a sphere.

37. The launch system according to any one of claims 32 to 34, wherein the launch vehicle coupling portion is embedded in the bottom surface of the support base and is formed as a recess.

38. The launch system according to any one of claims 1 to 37, wherein the launch load application member is movably positionable with respect to said upper facing surface of the piston member to thereby enable the magnitude of the offset dimension to be selectively adjusted.

39. The launch system according to any one of claims 1 to 38, wherein the piston assembly is rotatably positionable with respect to the central longitudinal axis to thereby enable an azimuth of the launch vehicle to be selectively adjusted.

40. The launch system according to any one of claims 1 to 39, wherein the actuation system comprises a hollow telescopic piston rod axially movable along the central longitudinal axis, powered by high pressure gas generated by a pyrotechnic source, to thereby expand the telescopic piston rod thereby carrying the piston assembly to the second axial position.

41. The launch system according to any one of claims 1 to 40, wherein the actuation system operates to selectively generate an actuation force that is applied at a center of the piston element, the actuation force being co-axial with the central longitudinal axis of the launch lumen, and wherein the actuation force induces the launch force at the launch load application member.

42. A launcher for selectively launching a launch vehicle, the launcher comprising:a launch tube defining a launch tube lumen having a central longitudinal axis, the launch tube lumen having an internal diameter being sized to enable accommodating the launch vehicle therein prior to launch;a piston assembly movably mounted within the launch tube lumen, and selectively axially movable along a piston central axis, nominally co-axial with the central longitudinal axis, between a first axial position and a second axial position to thereby eject the launch vehicle from the launch tube during launch;the piston assembly comprising a piston member and a launch load application member, the piston member having an upper facing surface, the launch load application member projecting upwardly from the upper facing surface, wherein load-bearing contact between the piston assembly and the launch vehicle is via the launch load application member, and wherein the launch load application member is laterally off-set with respect to the central longitudinal axis by a nonzero offset dimension;an actuation system coupled to the piston assembly and operative to selectively accelerate the piston assembly from the first axial position to the second axial position, thereby imparting a launch force to the launch vehicle via the launch load application member during launch;wherein in the first axial position the launch vehicle is accommodated in the launch tube lumen, and wherein in the second axial position the launch vehicle is provided with sufficient momentum to be fully ejected from the launch tube lumen.

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