IL143491A - Multi-range projectile - Google Patents

Abstract

Multi-range projectile including a missile and a booster connected to the missile, the missile including a missile rocket motor, the booster including a booster rocket motor, wherein igniting the missile rocket motor launches the multi-range projectile within a first range without the booster, and wherein igniting the booster rocket motor, launches the multi-range projectile within a second range.[IN-MAS-2002-00402A]

Description

MULTI-RANGE PROJECTILE Ref. 001852IL Agent for the Applicant: Eliav Korakh Borochov, Korakh, Eliezri MULTI-RANGE PROJECTILE FIELD OF THE INVENTION The present invention relates to missiles in general, and to methods and systems for varying the range of a missile, in particular.

BACKGROUND OF THE INVENTION Rocket bodies such as missiles and space craft are known in the art. A missile is launched from either a fixed launch site, a launch vehicle, an aircraft, or a ship. A missile can be either an interceptor, such as ground to air, air to air, ballistic, such as intercontinental ballistic missile (ICBM), or launched from a site in sea, air or land to a target in sea, air or land. A missile is propelled by a propulsion system, which includes either solid fuel or liquid fuel.

The distance that a given missile can travel is generally within a predetermined range. In order to save cost and inventory of different types of missiles each having a specific range, it is desirable to employ a missile whose range is variable. Thus, the same missile can be launched to targets lying at considerably different distances from the launch site. Multi-range missiles are known in the art.

The Aster missile manufactured by Aerospatiale, France, is a two stage variable range surface to air missile. The booster is sized according to the required intercept domain. The missile is fitted with a thrust vector control, employing steerable nozzles, which allow the missile to hit targets at very short ranges. The booster separates from the missile a few seconds after the vertical launch. The short range of the Aster missile is 1.7 km and the long range, greater than 30 km.

US Patent No. 3,124,072 issued to Herrmann, and entitled "Missile Propulsion", is directed to a multi-purpose missile having a variable range capability. The missile has a forward section in which a booster is housed and an after section, which contains the warhead. At a preset time in mid-flight and at the correct azimuth, the booster is separated from the warhead case, a drag brake is activated and the warhead comes to a near vertical position over the target. At this position, spin rockets are ignited and the warhead case spins at a rapid rate. An expulsion device is then activated, which expels the warheads in quick succession. Each missile homes on the target and is guided to the target.

US Patent No. 4,880,187 issued to Rourke et al., and entitled "Multipurpose Modular Spacecraft", is directed to a spacecraft capable to perform a wide range of different space missions. The multipurpose spacecraft includes a short-range space vehicle. The short-range space vehicle includes a plurality of small modular propulsion sets and a large propulsion module. The multipurpose spacecraft can be employed for short-range mission by activating the small modular propulsion sets, or for long-range missions, by employing the large propulsion module. The multipurpose spacecraft can be refueled in space, by replacing the small modular propulsion sets and the large propulsion module.

US Patent No. 2,856,851 issued to Thomas, and entitled "Apparatus for Zoning Rockets", is directed to a projectile having a short range and a long range. The projectile includes a rocket motor housing, whose both ends are threaded. A warhead can be attached to either of the two threaded ends and fins are attached to the other threaded end. The rocket motor housing is divided into a small combustion chamber and a large combustion chamber by a zoning wall. A nozzle is fixed to the rocket motor housing, at the end of the small combustion chamber. A larger nozzle is fixed to the rocket motor housing, at the end of the large combustion chamber. The zoning wall includes a pair of inter-traps having a sealing diaphragm there between. The inter-trap at the side of the small combustion chamber has a large central opening and the inter-trap at the side of the large combustion chamber has a plurality of small openings.

Fuel grains are attached to the inner walls of the small combustion chamber and the large combustion chamber. Each of a pair of end traps supported by the rocket motor housing, separates the fuel grains in each combustion chamber from the respective nozzle. A consumable igniter is located in the small combustion chamber and another consumable igniter is located in the large combustion chamber.

For short range operation of the projectile, the warhead is attached to the far end of the rocket motor housing respective of the small combustion chamber, fins are attached to the other end. The consumable igniter in the small combustion chamber is fired, thus burning the fuel grain therein. Since the hot gases do not pass through the zoning wall, the fuel grain in the large combustion chamber is not ignited. Since the openings in the inter-trap at the side of the large combustion chamber are small, the forces generated in the small combustion chamber are not great enough to rupture the sealing diaphragm into the large combustion chamber.

For long range operation of the projectile, the warhead is attached to the far end of the rocket motor housing respective of the large combustion chamber, fins are attached to the other end. The consumable igniter in the large combustion chamber is fired, thus burning the fuel grain therein. Since the opening in the inter-trap at the side of the small combustion chamber is large, the pressure generated in the large combustion chamber is sufficient to rupture the sealing diaphragm. Hence, the consumable igniter in the small combustion chamber ignites the fuel grain in the small combustion chamber.

SUMMARY OF THE PRESENT INVENTION It is an object of the present invention to provide a novel method and system for multi-range targeting, which overcomes the disadvantages of the prior art.

In accordance with the present invention, there is thus provided a multi-range projectile which includes a missile and a booster. The missile is connected to the booster. The missile includes a missile rocket motor and the booster includes a booster rocket motor. Igniting the missile rocket motor launches the multi-range projectile within a first range, without the booster. Igniting the booster rocket motor, launches the multi-range projectile within a second range, which is the sum of the range of the missile and the range of the booster.

In accordance with another aspect of the present invention, there is thus provided a method for launching a multi-range projectile. The method includes the steps of determining a range of a target, for the multi-range projectile and selecting a multi-range projectile structure, according to the determined range. The method further includes the steps of launching the selected multi-range projectile structure from a launch site and managing the removal of the booster, when the booster rocket motor is exhausted.

BRIEF DESCRIPTION OF THE DRAWINGS The present invention will be understood and appreciated more fully from the following detailed description taken in conjunction with the drawings in which: Figure 1A is a schematic illustration of a projectile in a long range mode at the time of launch, constructed and operative in accordance with a preferred embodiment of the present invention; Figure 1B is a schematic illustration of the projectile of Figure 1A, in a short range mode; Figure 2A is a schematic illustration of a long range flight path of the missile of Figure 1 A; Figure 2B is a schematic illustration of a short range flight path of the missile of Figure 1B; Figure 3A is a schematic illustration of a projectile, constructed and operative in accordance with another preferred embodiment of the present invention; Figure 3B is a schematic illustration of the adapter of Figure 3A; Figure 3C is a schematic illustration of the launch of the projectile of Figure 3A, toward a long range target; Figure 3D, is a schematic illustration of the launch of the projectile of Figure 3A, toward a short range target; Figure 4A is a schematic illustration of a missile system, constructed and operative in accordance with a further preferred embodiment of the present invention; Figure 4B is a schematic illustration of the separation device of Figure 4A, in de-activated mode; Figure 4C is a schematic illustration of the missile of Figure 4A in the process of being ejected of a canister; Figure 4D is a schematic illustration of the separation device of Figure 4A, in the activated mode; Figure 5A is a schematic illustration of a short range flight path of the missile of Figure 4A; Figure 5B is a schematic illustration of a long range flight path of the missile of Figure 4A; Figure 6A is a schematic illustration of a missile system, constructed and operative in accordance with another preferred embodiment of the present invention; Figure 6B is a schematic illustration of the separation device of Figure 6A, in de-activated mode; Figure 7A is a schematic illustration of a missile system, constructed and operative in accordance with a further preferred embodiment of the present invention; Figure 7B is a schematic illustration of the separation device of Figure 7A, in de-activated mode; Figure 8A is a schematic illustration of a multi-range missile, constructed and operative in accordance with another preferred embodiment of the present invention; Figure 8B is a schematic illustration of a short range flight path of the missile of Figure 8A; Figure 8C is a schematic illustration of a mid-range flight path of the missile of Figure 8A; Figure 8D is a schematic illustration of a long range flight path of the missile of Figure 8A; Figure 9A is a schematic illustration of the flight path of a air-to-surface bomb assembly, constructed and operative in accordance with a further preferred embodiment of the present invention; Figure 9B is a schematic illustration of the flight path of the bomb of Figure 9A, which is launched toward a target, with the aid of a booster; Figure 10A is a schematic illustration of a short range flight path of an air-to-air missile assembly, constructed and operative in accordance with another preferred embodiment of the present invention; Figure 10B is a schematic illustration of a long range flight path of the missile of Figure 10A, which is launched toward a target, with the aid of a booster; and Figure 11 is a schematic illustration of method for launching a multi-range projectile, operative in accordance with a further preferred embodiment of the present invention.

DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS The present invention overcomes the disadvantages of the prior art by providing a booster attached to a missile, in which the missile can be launched for either a long range mission with the booster (i.e., as a multi-stage projectile), or a short range mission without the booster (i.e., as a single-stage projectile). In a long range mission, the booster propels the missile from the launch site, separates from the missile in mid-air after being consumed and then the missile propels itself for the rest of the flight.

In a short range mission, the missile is launched alone to the mission, leaving the booster on the launch site. The missile can be launched from a fixed location on land, from a canister, from an aircraft, from a land vehicle, from a naval vehicle, or from a spaceship.

Reference is now made to Figures 1A, 1 B, 2A and 2B. Figure 1A is a schematic illustration of a projectile in a long range mode at the time of launch, generally referenced 100, constructed and operative in accordance with a preferred embodiment of the present invention. Figure 1 B is a schematic illustration of the projectile of Figure 1 A, in a short range mode. Figure 2A is a schematic illustration of a long range flight path of the missile of Figure 1A. Figure 2B is a schematic illustration of a short range flight path of the missile of Figure 1 B.

Projectile 100 includes a missile 102 and a booster 104. Missile 102 includes a nose section 106, missile fore fins 108, missile aft fins 110 and a missile rocket motor 112. Booster 104 includes booster fins 114 and a booster rocket motor 116. Operation of missile fore fins 108, missile aft fins 110 and booster fins 114 controls the flight path of projectile 100. Each of missile rocket motor 112 and booster rocket motor 116 is a propellant known in the art, such as solid fuel, liquid fuel, and the like. Booster 104 is attached to the aft section of missile 102, by an adapter (not shown). In case of a military missile, nose section 106 includes a warhead or a guiding system. In case of an observatory missile, nose section 106 includes surveillance equipment, weather equipment, scientific equipment, and the like.

Following is a description of a scenario of a long range flight of projectile 100. Initially, (Figure 2A), booster 104 is firmly connected to missile 102 by the adapter and projectile 100 is placed on a launch site 118. Projectile 100 is launched from launch site 118 by igniting booster rocket motor 116, thereby commencing the long range flight (stage A). In stage B, when booster rocket motor 116 is exhausted, missile rocket motor 112 is ignited. The adapter breaks apart under the forces generated by the burning of missile rocket motor 112, booster 104 separates from missile 102 and booster 104 drops to the surface. It is noted that the adapter can be released by other means such as electromechanical forces, pyrotechnic elements, and the like. Missile 102 continues the long range flight to the target (not shown). It is noted that missile rocket motor 112 can be ignited when booster rocket motor 116 is partially exhausted.

Following is a description of a scenario of a short range flight of projectile 100. With reference to Figures 1B and 2B, booster 104 is firmly connected to missile 102 by the adapter and projectile 100 is placed on launch site 118. Missile rocket motor 112 is ignited, whereby the adapter breaks apart due to the forces generated by the burning missile rocket motor 112. Missile 102 separates from booster 104 and missile 102 is propelled by missile rocket motor 112, toward the short range target (not shown), while leaving booster 104 on launch site 118 (stage A).

Missile rocket motor 112 alone, according to the example of Figure 1B, enables missile 102 to fly toward a short range target. On the other hand, the combination of booster rocket motor 116 and missile rocket motor 112, according to the example of Figure 1A, enables missile 102 to fly toward a long range target.

Reference is now made to Figures 3A, 3B, 3C and 3D. Figure 3A is a schematic illustration of a projectile, generally referenced 150, constructed and operative in accordance with another preferred embodiment of the present invention. Figure 3B is a schematic illustration of the adapter of Figure 3A. Figure 3C is a schematic illustration of the launch of the projectile of Figure 3A, toward a long range target. Figure 3D, is a schematic illustration of the launch of the projectile of Figure 3A, toward a short range target.

With reference to Figure 3A, projectile 150 includes a missile 152 and a booster 154. Missile 152 includes a plurality of missile fore fins 156, a plurality of missile aft fins 158, a missile rocket motor 160 (Figure 3D) and a missile aft section 180. Booster 154 includes a booster rocket motor 162 and a deflector 164 located at a booster fore section 166. Missile 152 is connected to booster 154, by an adapter 168.

Adapter 168 includes a plurality of adapter slots 170 (Figure 3B), equal to the number of missile aft fins 158. The width Ws of each of adapter slots 170 is substantially equal to or greater than the width (not shown) of each of missile aft fins 158, thereby allowing connection of missile aft section 180 to booster fore section 166. The outer surface of adapter 168 has an aerodynamic shape, in order to reduce the drag during the flight of projectile 150. The inner wall of adapter 168 and the outer wall of booster fore section 166, are each in the form of a conical section of substantially identical shape and dimensions. Booster fore section 166 is forced into adapter 168, thereby generating radial forces between the inner wall of adapter 168 and the outer wall of booster fore section 166.

Deflector 164 is conical and is made of a material, such as carbon fibers, cork, rubber based compositions, metal, and the like which are resistant to the high temperatures generated by missile rocket motor 160. Deflector 164 allows the burning propellant fuel of missile rocket motor 160 to deflect and diffuse around the outer surface of booster 154.

Projectile 150 is located inside a canister 172. Canister 172 includes a plurality of missile supports 174, a plurality of booster supports 176 and an exit cover 178. Canister 172 is an enclosure for storage and transport of missile 152 and booster 154 up to the launch of either missile 152 alone, or missile 152 together with booster 154. Canister 172 is substantially sealed in order to prevent deterioration of the materials of missile 152 and booster 154, exposed to various weather conditions, and to keep missile 152 and booster 154 in a dry controlled condition.

Canister 172 includes appropriate provisions to prevent movement of missile 152 and booster 154 during storage and transportation. For example, either missile 152 or booster 154 can be fixed in place within canister 172, by a rigid foam (not shown), which encloses the free space between missile 152 or booster 154 and the inner wall of canister 172. Such a rigid foam, for example, made of Rohacell, is firm enough to prevent the movement of missile 152 and booster 154 within canister 172. However, such a rigid foam is sufficiently soft to absorb shocks generated by either missile 152, or booster 154 and missile 152, after ignition of the fuel therein and the launch thereof from canister 172. Alternatively, other provisions can be employed, such as collapsible rods, and the like.

Missile supports 174 are attached to the inner wall of canister 172 and to missile 152. Booster supports 176 are attached to the inner wall of canister 172 and to booster 154. Missile supports 174 and booster supports 176 support missile 152 and booster 154, respectively, before either the launch of missile 152 alone, or the launch of missile 152 together with booster 154. Missile supports 174 collapse when exposed to the forces generated by the launch of missile 152, thereby allowing missile 152 to exit canister 172. It is noted that supports (e.g., missile supports or booster supports) can be made to slide against the inner walls of the canister or in special rails, thereby allowing the element attached thereto (i.e., missile or booster) to exit the canister.

Missile supports 174 and booster supports 176 collapse (when exposed to the forces generated by the launch of missile 152 and booster 154), thereby allowing missile 152 and booster 154 to exit canister 172. If both missile 152 and booster 154 are enclosed within the rigid foam as described herein above, missile supports 174 and booster supports 176 can be disposed.

With reference to Figure 3C, booster rocket motor 162 is ignited, thereby propelling missile 152 together with booster 154 out of canister 172. Missile supports 174 and booster supports 176 collapse due to the movement of missile 152 and booster 154, respectively. Missile 152 shatters exit cover 178 and projectile 150 exits canister 172. Thus, missile 152 is launched toward a long range target. In mid-flight, when the propellant fuel of booster rocket motor 162 is exhausted, missile rocket motor 160 (Figure 3D) is ignited. The thrust force of missile rocket motor 160 causes adapter 168 to break apart, whereby booster 154 disconnects form missile 152 and booster 154 drops to the surface. Missile 152, then continues the flight toward the long range target, in a self-powered mode.

With reference to Figure 3D, missile rocket motor 160 is ignited and missile rocket motor 160 propels missile 152. Missile supports 174 collapse due to the movement of missile rocket motor 160, missile 152 shatters exit cover 178 and exits canister 172. Adapter 168 breaks apart under the thrust force of missile rocket motor 160 and missile 152 disconnects from booster 154. Thus, missile 152 is launched toward a short range target.

Reference is now made to Figures 4A, 4B, 4C, 4D, 5A, 5B, 6A, 6B, 7A and 7B. Figure 4A is a schematic illustration of a missile system, generally referenced 200, constructed and operative in accordance with a further preferred embodiment of the present invention. Figure 4B is a schematic illustration of the separation device of Figure 4A, in de-activated mode. Figure 4C is a schematic illustration of the missile of Figure 4A in the process of being shot out of a canister. Figure 4D is a schematic illustration of the separation device of Figure 4A, in the activated mode. Figure 5A is a schematic illustration of a short range flight path of the missile of Figure 4A. Figure 5B is a schematic illustration of a long range flight path of the missile of Figure 4A. Figure 6A is a schematic illustration of a missile system, generally referenced 250, constructed and operative in accordance with another preferred embodiment of the present invention. Figure 6B is a schematic illustration of the separation device of Figure 6A, in de-activated mode. Figure 7A is a schematic illustration of a missile system, generally referenced 300, constructed and operative in accordance with a further preferred embodiment of the present invention. Figure 7B is a schematic illustration of the separation device of Figure 7A, in de-activated mode.

With reference to Figure 4A, missile system 200 includes a missile 202, a booster 204, a canister 206, a plurality of missile supports 208, a plurality of booster supports 210, an adapter (not shown) and a separation device 212. Canister 206 includes an exit cover 214. Missile 202 includes a missile rocket motor 216 and a missile aft section 220. Booster 204 includes a booster rocket motor 218 and a booster fore section 222. Missile 202, booster 204, missile supports 208, booster supports 210, the adapter and separation device 212 are located within canister 206.

Canister 206, missile supports 208, booster supports 210 and the adapter are similar to canister 172, missile supports 174, booster supports 176 and adapter 168, respectively, as described herein above in connection with Figure 3A. The adapter connects booster fore section 222 with missile aft section 220. With reference to Figure 4B, separation device 212 includes a gas cylinder 226, a hollow cylinder 228, an upper seal 230, a lower seal 232 and a gas cylinder activator 234. Gas cylinder 226 includes an outlet 236. Gas cylinder 226 contains pressurized gas, such as air, nitrogen, helium, and the like. Gas cylinder activator 234 is a mechanism, such as mechanical, electromechanical, pyrotechnic valve, and the like, which opens outlet 236, when activated.

Gas cylinder 226 is connected to missile aft section 220. Hollow cylinder 228 is connected to booster fore section 222. It is noted that this adapter can be inversely connected so that gas cylinder 226 is connected to booster fore section 222 and hollow cylinder 228 is connected to missile aft section 220. Upper seal 230 and lower seal 232 seal the gap between the outer surface of gas cylinder 226 and the inner surface of hollow cylinder 228. Gas cylinder activator 234 is connected to booster fore section 222 and to outlet 236.

Initially, booster 204 is connected to missile 202 by the adapter and both booster 204 and missile 202 are located at a launch site 224 (Figure 5A) within canister 206. At this stage, outlet 236 is closed, thereby keeping the pressurized gas inside gas cylinder 226.

Following is a scenario of a short range flight of missile 202. Gas cylinder activator 234 is activated, thereby opening outlet 236 and causing the pressurized gas of gas cylinder 226 to escape rapidly through outlet 236 (Figure 4D). The volume between hollow cylinder 228 and gas cylinder 226 is sealed by upper seal 230 and lower seal 232. At this stage, booster 204 is stationary. Hence, the pressurized gas which pressurizes this volume, causes gas cylinder 226 to accelerate in a direction designated by an arrow 238, thereby ejecting missile 202 out of canister 206 in direction 238 (Figure 4C and stage A of Figure 5A). At this stage, missile supports 208 collapse under the forces generated by the movement of missile 202. Furthermore, the adapter breaks apart by the forces generated by the movement of missile 202 and missile 202 disconnects from booster 204.

Missile 202 ejects out of canister 206 while shattering exit cover 214, without the aid of either missile rocket motor 216 or booster 204 (stage A of Figure 5A). In stage B (Figure 5A), missile rocket motor 216 is ignited, whereby missile 202 commences a self-powered flight toward the short range target. Gas cylinder 226 disconnects from missile aft section 220, by the forces generated by the burning missile rocket motor 216 and gas cylinder 226 drops to the surface.

Following is a scenario of a long range flight of missile 202. Initially, separation device 212 is maintained in the de-activated mode and the adapter keeps booster 204 connected to missile 202 (Figures 4A and 5B). When booster rocket motor 218 is ignited, booster 204 propels missile 202 out of canister 206 (stage A, Figure 5B). In stage B of Figure 5B, when booster rocket motor 218 is exhausted, missile rocket motor 216 is ignited. The adapter breaks apart as a result of the forces generated by the burning of missile rocket motor 216, booster 204 disconnects from missile 202 and booster 204 drops to the surface. Missile 202, then continues to fly toward the long range target. It is noted that at stage B, the separation device 212 can be activated right before or simultaneous with igniting missile rocket motor 216.

With reference to Figure 6A, missile system 250 includes a missile 252, a booster 254, a canister 256, a plurality of missile supports 258, a plurality of booster supports 260, an adapter (not shown) and an separation device 262. Canister 256 includes an exit cover 264. Missile 252 includes a missile rocket motor 266 and a missile aft section 268. Booster 254 includes a booster rocket motor 270 and a booster fore section 272. Missile 252, booster 254, missile supports 258, booster supports 260, the adapter and separation device 262 are located within canister 256.

Canister 256, missile supports 258, booster supports 260 and the adapter are similar to canister 172, missile supports 174, booster supports 176 and adapter 168, respectively, as described herein above in connection with Figure 3A. The adapter connects booster fore section 272 with missile aft section 268. With reference to Figure 6B, separation device 262 includes a gas generator 274, a hollow cylinder 276 and an igniter 282. Gas generator 274 includes a propellant substance 284 and an open end 286.

Gas generator 274 is connected to missile aft section 268. Hollow cylinder 276 is connected to booster fore section 272. Igniter 282 is connected to booster fore section 272 and to propellant substance 284. It is noted that this adapter can be inversely connected so that hollow cylinder 276 is connected to missile aft section 268 and gas generator is connected to the booster fore section 272.

Initially, booster 254 is connected to missile 252 by the adapter and both booster 254 and missile 252 are located at launch site, such as in Figure 5A. Following is a scenario of a short range flight of missile 252.

Igniter 282 is activated, thereby igniting propellant substance 284. The ignition of propellant substance 284 generates gases which escape through open end 286 and pressurizes the volume between hollow cylinder 276 and gas generator 274. The pressurization forces of the gas, cause gas generator 274 to accelerate in a direction designated by an arrow 288, thereby ejecting missile 252 out of canister 256 in direction 288, such as stage A of Figure 5A. At this stage, missile supports 258 collapse under the forces generated by the movement of missile 252. Furthermore, the adapter breaks apart by the forces generated by the movement of missile 252 and missile 252 disconnects from booster 254.

Missile rocket motor 266 is ignited, whereby missile 252 commences a self-powered flight toward the short range target, such as in stage B of Figure 5A. Gas generator 274 disconnects from missile aft section 268, by the forces generated by the burning of missile rocket motor 266 and gas generator 274 drops to the surface.

For a long range flight of missile 252, booster rocket motor 270 is ignited, whereby booster 254 propels missile 252 out of canister 256 toward the long range target, such as in stage A of Figure 5B. Missile supports 258 and booster supports 260, collapse under the propelling force of booster 254. When the propellant fuel of booster rocket motor 270 is consumed, missile rocket motor 266 is ignited, such as in stage B of Figure 5B. The thrust force of missile rocket motor 266 causes the adapter to break apart, whereby booster 254 disconnects form missile 252 and booster 254 drops to the surface. Missile 252, then continues the flight toward the long range target, in a self-powered mode.

With reference to Figure 7A, missile system 300 includes a missile 302 a booster 304, a canister 306, a plurality of missile supports 308, a plurality of booster supports 310, an adapter (not shown) and an separation device 312. Canister 306 includes an exit cover 314. Missile 302 includes a missile rocket motor 316 and a missile aft section 318. Booster 304 includes a booster rocket motor 320 and a booster fore section 322. Missile 302, booster 304, missile supports 308, booster supports 310, the adapter and separation device 312 are located within canister 306.

Canister 306, missile supports 308, booster supports 310 and the adapter are similar to canister 172, missile supports 174, booster supports 176 and adapter 168, respectively, as described herein above in connection with Figure 3A. The adapter connects booster fore section 322 to missile aft section 318. With reference to Figure 7B, separation device 312 includes a hollow cylinder 324, a spring 326 and a trigger 328. It is noted that separation device 312 can be adapted to work without cylinder 324.

Trigger 328 maintains spring 326 in the compressed mode, during storage and transportation of missile system 300. Trigger 328 is a mechanical, electromechanical, pyrotechnic device, and the like. When trigger 328 is activated, spring 326 is released and returns to the extended mode. For example, trigger 328 can be connected to missile aft section 318 and to booster fore section 322, through a pair of wires 330 and 332, respectively, thereby maintaining spring 326 in a compressed state. Alternatively, trigger 328 is connected to booster fore section 322 and to spring 326, thereby acting directly on spring 326 and maintaining spring 326 in the compressed state. Hollow cylinder 324 is connected to booster fore section 322. Spring 326 is located inside hollow cylinder 324.

Following is a scenario of a short range flight of missile 302. Trigger 328 is activated, whereby spring 326 is released from the compressed mode and returned to the initial extended mode. During the extension phase, spring 326 applies a force on missile aft section 318 and ejects missile 302 out of canister 306, such as in stage A of Figure 5A. Furthermore, the adapter breaks apart by the forces generated by the movement of missile 302 and missile 302 disconnects from booster 304. Since missile 302 is disconnected from booster 304, missile 302 exits canister 306 without the propelling power of either missile rocket motor 316 or booster rocket motor 320, while shattering exit cover 314. At this stage, missile supports 308, collapse under the forces generated by the movement of missile 302. Missile rocket motor 316 is then ignited, thereby commencing the self-powered flight of missile 302 toward the short range target, such as in stage B of Figure 5A.

For a long range flight of missile 302, booster rocket motor 320 is ignited, thereby propelling missile 302 out of canister 306 toward the long range target, such as in stage A of Figure 5B. When the propellant fuel of booster rocket motor 320 is consumed, missile rocket motor 316 is ignited, such as in stage B of Figure 5B. The thrust force of missile rocket motor 316 causes the adapter to break apart, whereby booster 304 disconnects form missile 302 and booster 304 drops to the surface. Missile 302, then continues the flight toward the long range target, in a self-powered mode.

Reference is now made to Figures 8A, 8B, 8C and 8D. Figure 8A is a schematic illustration of a multi-range missile, generally referenced 350, constructed and operative in accordance with another preferred embodiment of the present invention. Figure 8B is a schematic illustration of a short range flight path of the missile of Figure 8A. Figure 8C is a schematic illustration of a mid-range flight path of the missile of Figure 8A. Figure 8D is a schematic illustration of a long range flight path of the missile of Figure 8A.

With reference to Figure 8A, multi-range missile 350 includes a missile 352 and a plurality of boosters 354! and 3542. Missile 352 includes a missile rocket motor 356. Booster 354! includes a booster rocket motor 358! . Booster 3542 includes a booster rocket motor 3582.

Missile 352 is connected to booster 354i by a missile-booster adapter (not shown). Booster 354! is connected to booster 3542 by a booster-booster adapter (not shown). Other boosters, if present, are interconnected by other booster-booster adapters. A separation device 360! is located between missile 352 and booster 35^ for separating missile 352 from booster 35^. A separation device 3602 is located between booster 354! and booster 3542 for shooting missile 352 together with booster 354! off of booster 3542. If additional boosters are present, then additional separation devices are located between every two consecutive boosters. Each of the missile-booster adapter and booster-booster adapters is similar to adapter 168 of Figure 3B, as described herein above. Each of separation devices 360! and 3602 is similar to separation devices 212, 262 and 312 of Figures 4A, 6A and 7A, respectively, as described herein above.

With reference to Figure 8B, multi-range missile 350 is initially located on a launch site 362. Separation device 360i is activated, whereby missile 352 separates from booster 354-t, while the missile-booster adapter breaks apart. Missile rocket motor 356 is ignited, whereby missile 352 is propelled toward a short range LM, without either of boosters 354i or 3542 (stage A).

With reference to Figure 8C, multi-range missile 350 is initially located on a launch site 362. Separation device 3602 is activated, whereby missile 352 and booster 354i shoot together off of booster 3542 and booster 354i disconnects from booster 3542. At this stage, the booster-booster adapter breaks apart under the forces generated by the movement of booster 354! relative to booster 3542. In stage A, booster rocket motor 358i is ignited and missile 352 commences a mid-range flight of a range L-,. In stage B, when booster rocket motor 358! is exhausted, missile rocket motor 356 is ignited. The missile-booster adapter breaks apart under the forces generated by the burning of missile rocket motor 356, booster 354! disconnects from missile 352 and booster 354! drops to the surface. Missile 352, then continues the mid-range flight, in a self-powered mode.

With reference to Figure 8D, booster rocket motor 3582 is ignited. Since booster 3542 is connected to booster 354 f and booster 354! is connected to missile 352, booster 354i and missile 352 are launched by the propelling power of booster rocket motor 3582 (stage A). Thus, missile 352 commences a long range flight of a range L2.

In stage B, when booster rocket motor 3582 is exhausted, booster rocket motor 358! is ignited. The booster-booster adapter breaks apart under the forces generated by the burning of booster rocket motor 358!, booster 3542 separates from booster 354i and booster 3542 drops to the surface. Missile 352 continues the long range flight by the propelling of booster rocket motor 358i .

In stage C, when booster rocket motor 358i is exhausted, missile rocket motor 356 is ignited. The missile-booster adapter breaks apart under the forces generated by the burning of missile rocket motor 356, booster 354i separates from missile 352 and booster 354! drops to the surface. Missile 352, then continues the long range flight, in a self-powered mode.

It is noted that L2 > L1 > LM. Hence, missile 352 can be launched either toward a target located at a short range LM, at a mid-range L1t or at a long range L2. It is furthermore noted that other boosters in addition to boosters 354! and 3542 can be employed with missile 352, thereby increasing the variety of ranges available to missile 352.

Reference is now made to Figures 9A and 9B. Figure 9A is a schematic illustration of the flight path of a air-to-surface bomb assembly, generally referenced 400, constructed and operative in accordance with a further preferred embodiment of the present invention. Figure 9B is a schematic illustration of the flight path of the bomb of Figure 9A, which is launched toward a target, with the aid of a booster.

With reference to Figure 9A, air-to-surface bomb assembly 400 includes a bomb 402 and a booster 404. Booster 404 includes a booster rocket motor 406 and booster fins 408. Booster 404 is connected to bomb 402 by a bomb-booster connector (not shown). Booster 404 is connected to helicopter 412 by a booster release mechanism 416. It is noted that booster 404 does not include an element for defusing burning gases (e.g., deflector 164 of Figure 3A).

Booster release mechanism 416 is an electromechanical mechanism, hydraulic mechanism, pneumatic mechanism, pyrotechnic mechanism, and the like. The pilot of helicopter 412 can activate either the bomb-booster connector, or booster release mechanism 416, thereby dropping either bomb 402 alone, or launching bomb 402 by the propelling power of booster 404, respectively.

Helicopter 412 hovers above a target 418 on a surface 420 (i.e., land or sea). The pilot activates the bomb-booster connector, thereby disconnecting booster 404 from bomb 402. Bomb 402 disconnects from helicopter 412 and falls toward target 418, due to the force of gravity (stage A). In stage B, bomb 402 hits target 418 and explodes.

With reference to Figure 9B, helicopter 412 is either hovering or flying toward a target 422. The pilot activates booster release mechanism 416, and ignites booster rocket motor 406. Thus, bomb 402 and booster 404 disconnect from helicopter 412 and both commence a flight toward target 422 (stage A). In stage B, booster fins 408 are operated in order to maneuver bomb 402 toward target 422. In stage C, bomb 402 hits target 422 and explodes.

Reference is now made to Figures 10A and 10B. Figure 10A is a schematic illustration of a short range flight path of an air-to-air missile assembly, generally referenced 450, constructed and operative in accordance with another preferred embodiment of the present invention. Figure 10B is a schematic illustration of a long range flight path of the missile of Figure 10A, which is launched toward a target, with the aid of a booster.

With reference to Figure 10A, missile assembly 450 includes a missile 452 and a booster 454. Missile 452 includes a missile rocket motor 456, missile fore fins 458 and missile aft fins 460. Booster 454 includes a booster rocket motor 462 and booster fins 464. Booster 454 is connected to missile 452 by a missile-booster connector (not shown). Booster 454 is connected to aircraft 470, by a booster release mechanism 472. Aircraft 470 is of a type known in the art, such as airplane, helicopter, vertical short take-off and landing aircraft (VSTOL), vertical take-off and landing aircraft (VTOL), and the like.

Aircraft 470 is flying toward a short range target 474. The pilot of aircraft 470 activates the missile-booster connector, whereby missile 452 disconnects from booster 454. Missile 452 disconnects from aircraft 470. Simultaneously, missile rocket motor 456 is ignited, whereby missile 452 is propelled (stage A). Missile fore fins 458 and missile aft fins 460 are operated to maneuver missile 452 toward short range target 474, whereby missile 452 hits short range target 474 (stage B).

With reference to Figure 10B, aircraft 470 is flying toward a long range target 476. Booster 454 is connected to missile 452, by a missile-booster connector (not shown). The pilot activates booster release mechanism 472, whereby missile 452 and booster 454 disconnect from aircraft 470. Simultaneously, booster rocket motor 462 is ignited, whereby missile 452 is propelled toward long range target 476 by the propulsion power of booster rocket motor 462 (stage A). In stage B, the missile-booster connector is activated, whereby booster 454 disconnects from missile 452 and falls by the force of gravity (stage B). Simultaneously, missile rocket motor 456 is ignited, whereby missile 452 continues the long range flight toward long range target 476, by the propulsion power of missile rocket motor 456. In stage C, missile 452 hits long range target 476. It is noted that missile-booster connector 3601 (Figure 8A), booster-booster connector 3602, and the bomb-booster connector and the missile-booster connector as described herein above in connection with Figures 9A and 10A, respectively, are generally similar.

Reference is now made to Figure 11 , which is a schematic illustration of method for launching a multi-range projectile, operative in accordance with a further preferred embodiment of the present invention. In step 500, the range of a target of the multi-range projectile is determined. With reference to Figure 8C, a launch management system (not shown), determines that the target (not shown), is located at mid-range. Thus, the launch management system selects a multi-range projectile structure which includes missile 350 and booster 354i (step 502).

In step 504, the launch management system launches the selected multi-range projectile structure. With reference to Figure 8C, stage A, the launch management system launches missile 352 together with booster 354^ by igniting booster rocket motor 358! (Figure 8A). In step 506, the removal of burnt-out boosters is managed. With reference to Figure 8C, stage B, when booster rocket motor 358! is exhausted, the launch management system ignites missile rocket motor 356. The missile-booster adapter breaks apart under the forces generated by the burning of missile rocket motor 356, whereby booster 354i disconnects from missile 352 and booster 354! drops to the surface (stage B of Figure 8C). Missile 352 commences a self-powered flight toward the mid-range target. It is noted that alternatively, an operator can replace the launch management system.

It will be appreciated by persons skilled in the art that the present invention is not limited to what has been particularly shown and described herein above. Rather the scope of the present invention is defined only by the claims, which follow. 001852IL 143491/3

Claims (41)

1. CLAIMS Multi-range projectile comprising: a missile including a missile rocket motor; a booster coupled to said missile, said booster including a booster rocket motor; a launce management system, coupled with said missile and with said booster for igniting said missile rocket motor and launching a single-stage projectile, when a target is within a first range, said single-stage projectile including said missile and excluding said booster, and for igniting said booster rocket motor and launching a multi-stage projectile, when said target is within a second range, said multi-stage projectile, including said missile and said booster.

2. The multi-range projectile according to claim 1 , wherein said first range is substantially shorter than said second range.

3. The multi-range projectile according to claim 1 , wherein said missile is configured to be launched from a launch site situated in an environment selected from the list consisting of: land; air; water; and space. 001852IL 143491/2

4. The multi-range projectile according to claim 3, wherein said launch site is substantially stationary.

5. The multi-range projectile according to claim 3, wherein said launch site is in motion.

6. The multi-range projectile according to claim 3, wherein said launch site is an aircraft selected from the list consisting of: airplane; helicopter; vertical short take-off and landing aircraft; and vertical take-off and landing aircraft.

7. The multi-range projectile according to claim 1 , wherein a target of said multi-range projectile is located at a site selected from the list consisting of: land; air; water; and space. 001852IL 143491/2

8. The multi-range projectile according to claim 1 , further comprising a canister, containing said missile and said booster, from which either said single-stage projectile or said multi-stage projectile is launched .

9. The multi-range projectile according to claim 8, wherein said canister comprises a plurality of missile supports and a plurality of booster supports, coupled with said missile and with said booster, respectively.

10. The multi-range projectile according to claim 9, wherein each of said missile supports and each of said booster supports, slides against inner walls of said canister.

11. The multi-range projectile according to claim 9, wherein said missile supports collapse when said single-stage projectile is launched.

12. The multi-range projectile according to claim 9, wherein said missile supports and said booster supports collapse when said multi-stage projectile is launched.

13. The multi-range projectile according to claim 1 , wherein a nose section of said missile includes an element selected from the list consisting of: 001852IL 143491/2 warhead; surveillance equipment; weather equipment; and scientific equipment.

14. The multi-range projectile according to claim 1 , wherein each of said missile rocket motor and said booster rocket motor is a propellant selected from the list consisting of: solid; and liquid.

15. The multi-range projectile according to claim 1 , wherein said booster comprises a deflector coupled with a fore section of said booster.

16. The multi-range projectile according to claim 15, wherein said deflector is made of a material selected from the list consisting of: metal; carbon fiber; cork;, and rubber based compositions.

17. The multi-range projectile according to claim 1 , wherein said missile is coupled with said booster, by a missile-booster adapter, and 001852IL 143491/2 wherein said missile-booster adapter disconnects from said missile when said missile rocket motor is ignited, thereby separating said booster from said missile.

18. The multi-range projectile according to claim 1 , wherein a separation device is located between said missile and said booster, and wherein said missile separates from said booster, when said separation device is activated.

19. The multi-range projectile according to claim 18, wherein said separation device comprises a gas cylinder and a gas cylinder activator coupled with said gas cylinder.

20. The multi-range projectile according to claim 18, wherein said separation device comprises a gas generator and an igniter coupled with said gas generator, said gas generator includes a propellant substance.

21. The multi-range projectile according to claim 18, wherein said separation device comprises a spring and a trigger, said trigger maintains said spring in a compressed state. 001852IL 143491/2

22. The multi-range projectile according to claim 1 , further comprising at least an additional booster.

23. The multi-range projectile according to claim 22, wherein igniting a selected one of said at least one additional booster, launches said multi-stage projectile toward a respective range, which is longer than said second range.

24. The multi-range projectile according to claim 22, wherein said at least one additional booster comprises a deflector coupled with a fore section of said at least one additional booster.

25. The multi-range projectile according to claim 22, wherein said missile is coupled with a selected one of said at least one additional booster by a missile-booster adapter, and wherein said missile-booster adapter disconnects from said missile when said missile rocket motor is ignited, thereby separating said selected at least one additional booster from said missile.

26. The multi-range projectile according to claim 22, wherein successive ones of said at least one additional booster are interconnected by a booster-booster adapter, and 001852IL 143491/2 wherein said booster-booster adapter disconnects from a selected one of said at least one additional booster, when a booster rocket motor of said selected at least one additional booster is ignited, thereby separating said successive at least one additional booster from said selected at least one additional booster.

27. The multi-range projectile according to claim 22, wherein a separation device is located between said missile and a selected one of said at least one additional booster, and another separation device is located between successive ones of said at least one additional booster, wherein said missile separates from said selected at least one additional booster, when said separation device is activated, and wherein a first one of said at least one additional booster separates from a second one of said at least one additional booster successive to said first at least one additional booster, when said other separation device is activated.

28. The multi-range projectile according to claim 27, wherein each of said separation device and said other separation device, comprises a cylinder filled with compressed gas and a gas activator coupled with said cylinder. 001852IL 143491/4

29. The multi-range projectile according to claim 27, wherein each of said separation device and said other separation device, comprises a gas generator and an igniter coupled with said gas generator, said gas generator includes a propellant substance.

30. The multi-range projectile according to claim 27, wherein each of said separation device and said other separation device, comprises a spring and a trigger, said trigger maintains said spring in a compressed state.

31. The multi-range projectile according to claim 1 , wherein said missile is released from an aircraft.

32. Method for launching a multi-range projectile, the multi-range projectile including a missile and at least one booster coupled with the missile, the method comprising the steps of: determining a range of a target, for said multi-range projectile; selecting a multi-range projectile structure configuration, according to said determined range, said multi-range projectile structure configuration including either said missile for shorter ranges and or said missile and at least one of said at least one booster, for longer ranges; and launching said selected multi-range projectile structure. 001852IL 143491/3

33. The method according to claim 32, wherein said multi-range projectile is launched from a launch site situated in an environment selected from the list consisting of: land; air; water; and space.

34. The method according to claim 33, wherein said launch site is in motion while performing said launching step.

35. The method according to claim 32, wherein said launching step is performed from a substantially stationary launch site.

36. The method according to claim 32, further comprising the steps of: determining that a booster is exhausted; disconnecting said exhausted booster from a successive booster; and igniting said successive booster.

37. The method according to claim 32, further comprising the steps of: determining that a booster is exhausted; disconnecting said exhausted booster from said missile; and igniting said missile. 001852IL 143491/2

38. Multi-range projectile, according to any of claims 1-31 substantially as described hereinabove.

39. Multi-range projectile, according to any of claims 1 -31 substantially as illustrated in any of the drawings.

40. Method for launching a multi-range projectile, according to any of claims 32-37 substantially as described hereinabove.

41. Method for launching a multi-range projectile, according to any of claims 32-37 substantially as illustrated in any of the drawings. Advocate & Patent attorney Borochov, Korakh, Eliezri & co.