JPH11264699A - Opposing apparatus for depolying intercepting element from spin stabilized rocket - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a defending unit against an enemy missile of a low production cost by reducing a danger to friend soldier in a battle area. SOLUTION: A non-explosive intercepting element 14 contained in a payload part 17 by a slidable sleeve assembly 16 retracted in a nose direction by a driving mechanism 21 is assembled as a nose of a spin stabilized rocket 10. At the time of shooting, a trigger releasing assembly 46 is operated after a programmed predetermined delay. A driving rod 26 is released by an operation of the releasing assembly. The sleeve assembly is urged by an urging fore of a compressed spring unit 30, moved forward together with a sleeve member 22. Thus, the intercepting element is separately projected at a predetermined angular speed by a centrifugal force of the rocket to form an intercepting cloud by a non-explosive element.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a countermeasure device for stopping an enemy missile, and more particularly to the deployment of a non-explosive interceptor element deployed from a spin-stabilized rocket in a direct hit path of an enemy missile.

[0002]

BACKGROUND OF THE INVENTION Battlefield battles involving weapons such as tanks, mobile artillery vehicles, and other artillery are susceptible to attack by enemy armored destruction guided missiles. Defense countermeasures that counteract or stop such incoming enemy attacks typically use explosive means to destroy enemy missiles, thereby threatening friendly soldiers in the battlefield. Currently available countermeasures with guided missiles are costly and complex in construction, and the use of explosives as countermeasures, among other things, shows potential harm to friendly soldiers. The use of countermeasures achieved by approach fuze is particularly dangerous to friendly soldiers. What is needed is that it does not explode itself, and at least reduces the danger to nearby friendly soldiers,
Or an attack defense device that uses non-explosive intercepting elements to reduce and effectively intercept and stop incoming guided missiles.

[0003] Known protective devices, such as US Patent No. 4,388,869, deserve comment. The teachings of this patent involve the use of non-explosive rods and pellets that are scattered in the orbit of a satellite target traveling in outer space. The target spacecraft is engaged and destroyed by a collision or approach rod. A drawback of such known devices is the ability to deploy the interceptor at a precise time and in a uniform array, such as a cloud of interceptors, that effectively destroys enemy missiles. Other defensive devices employ an auto-igniter that fires a projectile containing a heavy metal ball-shot element. A delay fuze explodes an explosive that randomly disperses the shot and secondary projectiles against enemy missiles. Unlike the present invention, secondary projectiles and shot-like particles pose a danger to friendly soldiers. Other known countermeasures involve the use of guided missiles that are triggered by a contact fuze or otherwise guided by an optical sensor to engage an enemy missile that is flying. The high probability of successfully defending against such enemy-guided missiles is the occurrence of a cloud of non-explosive intercepting elements deployed directly on the ballistics at the correct time and in a constant pattern ensuring collision and destruction I understood.

[0004]

According to the teachings of the present invention,
An airborne device is provided that is directed along an intercept path to disperse a plurality of non-explosive intercepting elements directly into a predetermined configuration that produces a continuous cloud in the path of an incoming enemy missile. The device is in the form of a spin-stabilized rocket having a longitudinal axis, a rear end, a leading end, a nose-cone body, and a payload portion intermediate the nose-cone body and the rear end, wherein the payload is in the longitudinal direction of the rocket. It is arranged circumferentially around the shaft ship. The payload consists of a source of non-explosive intercepting elements that are propelled from the payload portion at a constant tangential velocity in flight in response to the centrifugal force generated by the spin-stabilizing rocket's rotational speed. In one preferred embodiment, the release mechanism for the non-explosive interceptor element comprises a slidably driven sleeve assembly. During flight, a release device is provided in the form of a slidably driven sleeve assembly over the payload portion, and when the sleeve assembly is retracted from the rearward end to the leading end to expose the payload portion and eliminate confinement, Release the non-explosive interceptor. An intercepting cloud is formed by dispersing non-explosive intercepting elements. The clouds are deployed directly on the ballistics, stopping enemy missiles.

[0005] In one preferred embodiment, the interceptor comprises:
Centrifugal force of a spin-stabilized rocket, housed in a series of tubular structures arranged radially around the longitudinal axis to create a specially shaped intercepting cloud, drives the non-explosive intercepting element into a specific formation Let it. In another preferred embodiment, the non-explosive intercepting element is randomly placed within the payload portion to form a constant cloud of airborne elements at the enemy missile's intercept path at precise time of deployment. In a further preferred embodiment, the release mechanism for the payload is maintained in the retracted state by a sleeve assembly releasably secured to the rocket engine housing by shear screws. The payload portion is opened by a pyrotechnic device activated by a delay device, releasing a non-explosive intercepting element and creating an intercept cloud in the ballistics of the incoming enemy missile. The pyrotechnic device is positioned between the nose cone and the payload portion and generates the necessary thrust to shear the bolt without disturbing the alignment of the non-explosive intercepting elements loaded within the payload portion. The payload portion is provided with a centrally located thrust bar that directs the pyrotechnic force load path to the rocket engine housing without applying charge to the non-explosive intercepting element. The firework force shears the screws that restrain the sleeve, allowing the release of undisturbed non-explosive intercepting elements.

[0006] The form of the non-explosive intercepting element is preferably spherical and aligned with the payload portion in a hexagonal stacked arrangement, wherein a continuous layer is added with the non-explosive intercepting elements contacting each other tangentially. Can be Advantageous non-explosive intercepting elements may be cylindrical or amorphous and create a more effective intercepting cloud. These and other features of the invention,
Aspects and advantages will be better understood from the following description, claims and the accompanying drawings.

[0007]

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a defense countermeasure device.
In one embodiment, the rocket identified generally at 10 can be used to protect weapons such as tanks and other mobile vehicles such as cannons to defend against guided missiles. Such countermeasures should intercept incoming missiles in a manner that minimizes the risk of friendly soldiers in the battlefield. The use of explosive countermeasures against enemy missiles, which rely on contact fuze or close fuze to explode defenses near the incoming missile, presents a perceived danger to friendly soldiers operating in the target combat zone I do. Therefore, the defense device of the present invention employs a non-explosive interceptor that at least reduces that risk. The construction and operation of the counter-attack is very costly to produce due to the novel mechanical devices employed to deploy the non-explosive interceptor at a given distance where the counter encounters an incoming enemy missile. It does not take. The enemy missile tracker is achieved with a W-band 94 GHz radar set, and the laser set also operates to command counter-missile flight and updates the countdown delay timer to deploy non-explosive intercepting elements I do.

The protection device of the present invention shown in FIG.
A spin-stabilized rocket 10 that rotates between 00 RPM and 11,000 RPM. The rocket has a rear end 11,
A leading end 12 adapted to carry a deployable source of a non-explosive interceptor element 14. Similar elements in the various figures are labeled with the same reference numerals. Apparatus 10 includes a solid propellant motor 15, shown in dashed outline configuration, for a slidable sleeve assembly 16, a payload portion 17, a nose conical body 18, and a sleeve assembly generally identified by reference numeral 20. Is a rocket with a diameter of 102 mm having a driving mechanism of (1). The payload portion 17 includes a movable wall 19 and a rear fixed wall 22. The non-explosive intercepting element 14 is packed into the payload portion 17 and is housed therein until the slidable sleeve assembly 16 is retracted and no longer covers the non-explosive intercepting element 14, When the space 16 is retracted and no longer covers the non-explosive intercepting element 14, the non-explosive intercepting element is propelled out of the payload portion at a constant angular velocity in response to the centrifugal force generated by the rocket spin rate.

[0009] The method of placing the non-explosive intercepting element within the payload portion 17 offers advantages for the effectiveness of the device.
In one preferred embodiment (FIGS. 3 and 5), the non-explosive interceptor is randomly loaded into the payload portion 17. This is an inexpensive method that, when deployed, creates randomly distributed intercepting clouds. In another preferred embodiment (FIG. 2), the non-explosive intercepting element is of a particular shape, such as a sphere or elongated rod, and has a series of rows of tubular structures extending radially about the longitudinal axis of the rocket. Packed into. The advantage of the second preferred embodiment is the special form of the intercepting cloud generated by the constant velocity propelling the non-explosive intercepting element and the uniform weight distribution of the load in the rocket, which makes the flight pattern more accurate Secure control. Both embodiments have good shot-down success with their respective interception clouds.

As shown in FIGS. 1 and 2, the non-explosive interceptor elements 14 are packed around a series of rows of radially extending tubes 23 or cylinders and arranged about the longitudinal axis 25 of the rocket. Form a column of non-explosive intercepting elements.
In a preferred variant, the non-explosive intercepting element is randomly loaded into the payload portion 17 shown in FIG. In either embodiment, when the sleeve assembly 16 is driven in the direction of flight, the portion of the packed non-explosive interceptor element is released from confinement within the payload 17 and may be of a randomly deployed element or other. It forms a particular form of interception cloud in an embodiment. Referring again to FIG. 1, at an appropriate time,
An actuated drive mechanism 20 is shown, which drives the slidable sleeve assembly 16 in a direction from the rearward end 11 to the leading end 12 of the spin-stabilized rocket 10. The slidable sleeve assembly 16 is integrally fixed to the nose cone shaped body 18 and moves therewith. The support wall 19 has an annular opening 30 which is closed by a cup-shaped bracket 28. The drive mechanism 20 is centered within the payload portion 17 along a central longitudinal axis 25 and includes a drive cylinder 24 that houses a drive rod 26. The drive rod 26 extends along the longitudinal axis, has one end releasably supported at the rear end 11 of the rocket, and has a front end 32 secured to the bracket 28. The bracket 28 is also provided at the front end 2 of the drive cylinder 24.
Accept 9. The support wall 19 extends across the inside diameter of the rocket and mates with the sleeve member 21 at a joint 27 where the sleeve member 21 is secured to the nose cone body 18.

The sleeve member 21 and the nose conical body 18
And the wall 19 is welded or otherwise united at the joint 27 so that the assembly 16 moves as a single unit. A slide support casing 34 concentrically surrounds the drive cylinder 24. The slide support casing 34 has a larger diameter than the drive cylinder 24 and forms an annular space 36 between the casing 34 and the drive cylinder 24. The slide support casing extends rearward in the payload portion, with its front end 37 fixed to the support wall 19 and its rear end not attached. The support wall 19 is fixed to the slide support casing 34. The slide support casing 34 is slidably disposed within a fixed tube 35 which is part of the payload portion 17 forming the bottom support for the non-explosive intercepting element. Because the slide support casing 34 is fixed to the front support wall 19, the slide support casing slides in the fixed tube 35 toward the leading end 12 when the support wall is moved forward. Slide support casing and drive cylinder 24
Within the space 36 formed between the bracket 28 and the rear fixed support wall 22 of the bracket 28 and the payload portion 17 is a spring unit 40 wound in compression around the drive cylinder. Be placed. In environments where the greater driving force provided by the helical spring 40 is required, an auxiliary mechanism is provided in the form of a fireworks device.

Referring to FIGS. 4 and 5, a drive rod 26 releasably mounted at the rear end 11 and extending through the opening 42 into the drive cylinder 24 runs along the longitudinal axis 25 through the center of the rocket. The drive rod 26 terminates at the other end of the drive cylinder 24 through the opening 42 and is secured to the bracket 28 within the notch 44. Drive rod 26
The rear end of the rocket 10 is releasably supported by the rear end 11 of the rocket 10 and is locked in place by the trigger assembly 46. As shown in FIGS. 3 and 5, non-explosive intercepting elements 14 are randomly packed within the payload portion 17. In contrast to the type of non-explosive intercepting element cloud formation 50 that occurs when deploying the assembly shown in FIG. 4, the randomly loaded element 14 of FIG. 5 is a continuous cloud of randomly distributed elements 14. To form Deployment occurs in the same manner as described in connection with FIG. 4, except that the non-explosive intercepting element is randomly propelled out of the payload section to form a continuous intercepting cloud. The size and shape of the cloud are the same as those described in connection with FIG.

The drive mechanism 20 causes the nose cone 18 and the sleeve member 21 to be biased by the helical spring unit 40 pressed against the end of the cup-shaped bracket 28 covering the annular opening 30 of the movable payload front wall 19. It is set so as to push in the direction of the leading end 12 of the rocket. A dashpot 48 is secured to the drive rod 26 within the drive cylinder 24 to help control the speed of movement of the drive rod 26 within the cylinder 24 that opens the payload portion 17. The continuous intercept size and profile of the non-explosive intercepting element can be governed by the speed at which the sleeve member 21 opens the payload portion 17 and extrudes the non-explosive intercepting element 14 in a constant cloud pattern by centrifugal force. Is understood. The rapid release of all non-explosive intercepting elements in a short time causes a rather condensed intercepting cloud, and the slower the speed at which the non-explosive intercepting elements are propelled out of the payload portion 17, the lower the continuous intercepting cloud. Is more distributed.

Returning now to FIG. 4, the trigger assembly 46 is actuated to release the drive rod 26, thereby setting the sleeve assembly 16 in motion toward the leading end 12 of the rocket 10 for the first time. The condition of the rocket 10 exposing a row of non-explosive intercepting elements is shown. The non-explosive interceptor element 14 is deployed by the centrifugal force of the spin-stabilized rocket. Laboratory tests have shown that the device produces a continuous cloud 50 of spherical interceptors. Non-explosive interceptors have a diameter of 5 distributed over the trajectory of incoming enemy missiles.
It may be spherical, such as a / 16 inch hole bearing, or 1/4 to 3/4 inch long and 5/1 in diameter.
It will be appreciated that a 6 inch steel rod may be used. With respect to time, deployment occurs, for example, in the range of 256 to 512 microseconds after launch.

In another preferred embodiment, the rocket structure employs a pyrotechnic unit to expose a payload portion to release a non-explosive intercepting element. FIG.
Referring to, the rocket is identified by the number 100. The main structure for accommodating the rocket engine 103 constituting the rocket is an engine housing 102, a payload portion 11
7 and a nose cone body 118. Housing 10
2 is a solid propulsion engine, which produces a nominal 1200 lbs thrust, 52 g acceleration and about 10,000 to 11000 r.
Provide pm rotation to the rocket. The front end of the housing 102 includes a frame protection wall 120 on which a cowling structure 122 is formed. Cowling 122 has the same diameter as rocket engine housing 102 and projects toward payload portion 117. The outside of the cowling 122 is threaded to receive and attach the payload portion 117 and the nose cone body 118.

The payload portion 117 is provided on the sleeve member 12.
Formed within 1, this sleeve member surrounds a payload portion 117 that contains a load of the non-explosive interceptor element shown in FIGS. 3A, 3B and 3C. The payload portion 117 and the nose cone body 118 are connected to the thread 12 outside the nose cone body.
7 is assembled by engaging threads inside the sleeve 121 to form a split front portion 126 of the rocket 100. In front of the payload portion 117, the firewall 130 facing the rear end of the nose cone portion 118
including. The rear end of the payload portion 117 is surrounded by a support wall member 132 that serves to accommodate the non-explosive intercepting elements in a stacked configuration. The support wall member 132 is fixed to a threaded bush 134 having a flange portion 136 and an inner threaded portion 138 formed therein. The rear end rocket engine housing has a protective wall 139 with an outer threaded flange portion 141 at the rear end. The entire forward portion 126 and the rocket housing 102 are threaded portions 141 and 134
It will be understood that they may be screwed together by joining.

The payload portion 117 extends between the fire wall 130 and the support wall member 132 and is located at the center 1 of the fire wall 130.
A rod 140 is releasably held at 42 to the fire wall 130. The rear end of the rod 140 is fixed to the support wall 132 and the bush 134 by being welded in place. As described below, the rod 140, in conjunction with the firewall 130, functions to provide separation of the forward portion 126 of the rocket from the engine housing to release non-explosive intercepting elements. The nose cone portion 118 includes a countdown delay controller 150 and a fireworks unit 152.
To accommodate. As shown in FIG. 6, the countdown delay control device 150 includes a battery unit 154, a battery 1
It includes a 56, 9 channel wireless control receiver 160 and a control circuit 162. It will be appreciated that the opponent must perform its task within a very narrow time window of milliseconds.

In practice, the device responds to a radar tracking unit, which is a W-band 94 GHz radar set. The radar is placed in cooperation with the launcher. Radar trackers are capable of catching enemy rockets at hundreds of meters, and they track enemy rockets and constantly provide range and target coordinates. This data is fed into the launcher signal processor, which calculates the deployment time of the intercept target point and the non-explosive intercept element, and calculates the delay time before the fireworks unit is activated from the firing time. .
The operation of the delay control circuit is started simultaneously with the launch of the opposing rocket. The first countdown of the delay time can be updated. In update mode, the radar processor sends commands to the radio control receiver 160 in the rocket, which converts the digital commands into a series of pulses, which are demodulated and decoded by the circuit 162. The pyrotechnic device is ignited when the radar tracking signal compares or matches the updated decoding data.

The portion 126 is held in place against a threaded bush 134 by screws 170 designed to shear in response to the force of the pyrotechnic device 152. The delay control device 150 and the storage unit 154 powered by the battery set 156 at the moment when the scheduled or updated delay time has elapsed,
And the pyrotechnic device exerts sufficient explosive power on the wall 130 to push the nose cone 118 and push the payload 11
Pull 7 forward. The explosive force is applied from the wall 130 to the rod 140 attached to the flange 136 of the bush 134.
To cause the screw 170 to shear. With explosive power,
The entire forward portion 126 is separated from the engine housing 102, exposing the non-explosive intercepting element to the centrifugal force of the spin countermeasure rocket.

The non-explosive intercepting element is pushed out of the payload section as previously described, creating a cloud of intercepting elements as shown in FIG. If the first row of non-explosive interceptors falls and engages the target, the remaining elements of the cloud impact the missile as well. Within a fraction of a second after deployment, the entire cloud consumes its emitted energy from the rocket and begins to fall harmlessly to Earth. In most cases,
A single interceptor hits the incoming missile and fires it. It will be appreciated that the only explosive element that occurs during the engagement is that of stopping enemy missiles, reducing and possibly minimizing the danger to friendly soldiers on the ground during the engagement. It will be appreciated that the rival has no munitions or secondary munitions, eliminating the need for "safe and armed" equipment. The inherent danger to those who load a single round of ammunition onto a rocket or handle this device is greatly reduced.

If the missile misses its target altogether, it will eventually fall to Earth, but pose no danger since it will not accommodate any unexploded cargo. The present invention avoids the situation of counter-missiles equipped with explosives which, by themselves, cause a detonation in the hollow with the passage of delay and pose a danger. The use of heavy metals or debris-like elements deployed by explosive forces poses a danger to friendly soldiers. Although the present invention has been described in considerable detail with reference to certain preferred embodiments, other embodiments are possible. Therefore, the scope of the appended claims should not be limited to the description of the preferred embodiments contained herein.

[Brief description of the drawings]

FIG. 1 is a longitudinal cross-sectional view of a defensive anti-rocket launch showing confinement of a non-explosive interceptor element within a payload portion.

FIG. 2 is a cross-sectional view taken along line 2-2 of FIG. 1 showing the confinement of the payload portion and the non-explosive intercepting element.

3 is a cross-sectional view of the payload portion taken along line 3-3 of FIG. 5, with the non-explosive intercepting elements randomly packed in the compartment, FIG. 3A is a schematic diagram of a spherical non-explosive intercepting element, FIG. 3B.
3C is a schematic view of a cylindrical non-explosive intercepting element, and FIG. 3C is a schematic view of an amorphous non-explosive intercepting element.

FIG. 4 shows a longitudinal view of a defensive rocket showing a slidable sleeve assembly driven in the direction of flight to uncover a loaded non-explosive intercepting element over a partial enemy missile, indicating the initial formation of an intercepting cloud. It is sectional drawing.

FIG. 5 is a longitudinal cross-sectional view of a defensive anti-rocket showing a sleeve assembly surrounding a non-explosive intercepting element randomly arranged within a payload portion.

FIG. 6 is a longitudinal cross-sectional view of a protective anti-rocket delay unit showing a releasable sleeve secured by a shearable screw.

7 is a cross-sectional view taken along line 7-7 of FIG. 6, showing a hexagonal stacking arrangement of non-explosive intercepting elements.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 10 Spin stabilized rocket 11 Rear end 12 Leading end 14 Non-explosive intercepting element 16 Slidable sleeve assembly 17 Payload part 18 Nose conical body 19 Movable wall 20 Drive mechanism 22 Fixed wall 23 Tube 24 Drive cylinder 25 Longitudinal Direction axis 26 Drive rod 28 Cup-shaped fracket 34 Slide support casing 40 Winding spring unit 46 Trigger assembly 50 Cloud formation.

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[Procedure amendment]

[Submission date] April 1, 1999

[Procedure amendment 1]

[Document name to be amended] Statement

[Correction target item name] Claims

[Correction method] Change

[Correction contents]

[Claims]

 ──────────────────────────────────────────────────続 き Continued on front page (72) Inventor Jane M. Lin United States California 90275 Rancho Palos Verdes Silver Arrow Drive 5065

Claims (35)

[Claims] 1. A defensive anti-spin stabilized rocket carrying a non-explosive interceptor element to intercept and destroy incoming enemy missiles, comprising: a rocket housing; and a controller for directing the rocket along an intercept path. Means for deploying the non-explosive interceptor at a predetermined time after launch comprising a payload portion containing a source of the non-explosive interceptor; and means for confining the non-explosive interceptor during flight. A drive for activating the confinement means for deploying the non-explosive intercepting element; and a time control for operating the confinement drive, wherein the non-explosive intercepting element comprises an intercepting path. The spin-stabilized rocket described above, wherein the spin-stabilized rocket is deployed along a centrifugal force of the spin-stabilized rocket to form a cloud of non-explosive intercepting elements. 2. The invention according to claim 1, wherein the driving device is a fireworks device that generates explosive power. 3. The non-explosive intercepting element is spherical in shape.
The invention according to claim 1. 4. The invention of claim 1, wherein the non-explosive intercepting element is an elongated rod. 5. The non-explosive intercepting element is uneven in shape.
The invention according to claim 1. 6. The non-explosive interceptor element deployment wherein a continuous cloud of said non-explosive interceptor element forms in the intercept path of an incoming enemy missile propelled outward from the payload portion at a constant tangential velocity. The invention according to 1. 7. A non-explosive interceptor element is stored within the payload portion in a series of tubes extending radially about a longitudinal axis, wherein the non-explosive interceptor element is propelled outwardly from the payload portion. 2. The invention according to claim 1, wherein a continuous cloud of a predetermined form is formed in an intercepting path of the incoming missile. 8. The containment means comprises a retractable sleeve assembly surrounding the payload portion, said sleeve assembly being slidably mounted in the direction of the leading end of the rocket and being actuated in response to a time control. The invention according to claim 1, wherein the driving device is driven by a driving device. 9. The method of claim 1, wherein the confinement means comprises a sleeve assembly releasably mounted to the rocket engine housing with the fastener being removed in response to an explosive force actuated by a time control. The described invention. 10. A drive for compressing a slidable drive rod releasably held by a release mechanism and confining means toward a leading end of the rocket in response to actuation of the release mechanism. 8. The invention of claim 7, comprising a helical spring maintained below. 11. The invention according to claim 1, wherein the time control device is a delay device preset at a time when the rocket is launched. 12. The invention of claim 8, wherein the drive rod is slidably received within a fixed drive cylinder having means for controlling the speed of movement of the drive rod. 13. The invention according to claim 1, wherein a rocket is propelled by said solid propellant. 14. A defensive anti-spin stabilizer adapted to intercept an incoming enemy missile, employ a non-explosive interceptor element propelled by the centrifugal force of a rotating rocket, and have a rearward end and a nose cone body. Rocket, which is loaded with a non-explosive interceptor source to be deployed on the incoming missile's direct impact roadway, circumferentially surrounding the rocket, closing the payload portion in flight, A slidable sleeve assembly having a shroud for receiving the non-explosive interceptor element and operating in an open position to expose a payload portion, and a drive rod guide for advancing the sleeve assembly at a constant speed to a retracted position. A drive mechanism for retracting the sleeve assembly at a predetermined time after firing, wherein the drive rod is releasable by a latch mechanism. Further comprising a delay control for unlatching the drive rod after firing, the unlatching biasing the sleeve assembly to its open position, wherein the non-explosive interceptor element is disengaged from the payload portion at a constant tangential velocity. A defensive anti-spin stabilized rocket that generates a constant continuous cloud of non-explosive intercepting elements on the trajectory of enemy missiles that are propelled and fly. 15. The invention according to claim 14, wherein the non-explosive intercepting element has a spherical shape. 16. The invention of claim 14, wherein the drive comprises a compression wound spring biasing the sleeve assembly to its open position. 17. The invention of claim 14, wherein the continuous cloud has a diameter in the range of 4-6 feet. 18. The invention of claim 14, wherein the continuous cloud is formed in a predetermined pattern of non-explosive intercepting elements. 19. The invention according to claim 14, wherein the delay control device is preset at the time of firing and unlatches the drive rod a predetermined time after firing. 20. The delay control device is actuated from a remote location shortly before an incoming enemy missile intercept occurs.
4. The invention according to 4. 21. The drive device is a detonator type detonator.
The invention according to claim 14. 22. The non-explosive interceptor element is disposed within the payload portion within a series of radially extending tubes to generate a predetermined continuous cloud upon launch from a rocket.
4. The invention according to 4. 23. The invention according to claim 15, wherein the continuous cloud is in the form of an annular ring. 24. The invention of claim 14, wherein the circumferential shroud surrounding the payload portion is integral with the nose-cone body and is moved when the nose-cone body is driven. 25. The drive device includes a drive cylinder fixedly mounted within the payload portion and concentrically mounted within the casing, wherein the casing is mounted to and movable with the nose conical body. By
2. A nose cone body defining an annular space between the drive cylinder and the nose cone body, wherein the drive rod extends through the drive cylinder and has a leading end attached to the nose cone body.
4. The invention according to 4. 26. A biasing spring is disposed in compression within the annular space between the drive cylinder and the casing and biases the nose conical body forward, thereby retracting the sleeve assembly. The invention according to claim 14. 27. The invention of claim 14, wherein the drive cylinder comprises a constant speed dashpot for controlling the speed at which the drive rod is propelled by the biasing spring. 28. The invention of claim 14, wherein the delay control is associated with a drive rod release mechanism. 29. A defensive anti-spin stabilizing rocket adapted to intercept an enemy missile flying along an intercept path, the rocket having a rear end and a nose cone body, and a centrifugal force of the rotating rocket. Employs a non-explosive intercepting element driven by force, a. A rear end rocket housing; b. A payload portion loaded with a source of a non-explosive interceptor element to be deployed at a point of intersection with the interceptor path and housed within a sleeve portion; c. A nose cone having a pyrotechnic device for generating explosive power and a countdown delay control device for activating the pyrotechnic device upon elapse of the delay time; d. Fastener means releasably attached to the rocket housing, the fastener means being detached in response to the explosive force generated by the pyrotechnic device over the delay time, the sleeve member and the nose A spin stabilized rocket as described above wherein the conical portion is separated from the rocket housing and the non-explosive intercepting element is propelled outward from the payload portion to create an intercepting cloud. 30. The invention according to claim 29, wherein said fastener means is a shearable screw. 31. The invention according to claim 29, wherein the countdown time of the delay control device is started simultaneously with the launch of the rocket. 32. The invention of claim 29, wherein the payload portion is separated from the nose cone portion by a firewall and the rocket housing is separated from the payload portion by a support wall. 33. The payload portion comprises a rod member extending axially between the fire wall and the support wall.
3. The invention according to 3. 34. The invention according to claim 32, wherein the fireworks device is arranged adjacent to the fire wall. 35. The invention according to claim 33, wherein the rod member is fixed to the support wall and is releasably disposed adjacent to the fire wall.