Airborne platform protection apparatus and associated system and method

Abstract

A protection apparatus adapted to protect a moving platform against an incoming threat is provided. The protection apparatus is deployed from the moving platform in a first direction toward the threat, with the threat moving in a second direction toward the moving platform at a threat velocity. The protection apparatus comprises a projectile housing. A first deployable device is operably engaged with the projectile housing, and is adapted to capture the threat upon deployment such that the protection apparatus mass is combined with the threat mass via the first deployable device. A second deployable device is operably engaged with the projectile housing, and is configured to be deployed upon the first deployable device capturing the threat. The second deployable device is further configured to decrease the velocity of the combined protection apparatus and threat masses in the second direction. Associated systems and methods are also provided.

Description

BACKGROUND OF THE INVENTION

1. Field of the Invention

The present invention relates to a defensive device and, more particularly, to a protection apparatus and associated system and method for protecting an airborne platform from an incoming threat.

2. Description of Related Art

Many aircraft such as, for example, commercial aircraft are vulnerable to attack, such as with rockets and missiles, during take-off and landing, generally at a low altitude and low airspeed. Some active protection systems have been developed that can be implemented to destroy the warhead section of such threats using a threat-defeating interceptor having its own warhead that can be launched from platforms such as airborne helicopters and armored ground vehicles protection. However, such active protection systems utilize an interceptor carrying an explosively-loaded warhead, which may result in undesirable risk to the platform being protected in instances where the platform is, for example, a commercial aircraft. That is, the explosive warhead carried by the interceptor and used to defeat the threat may result in an undesirable risk to a commercial aircraft upon the explosion resulting from the threat being defeated.

More particularly, airborne platforms such as, for example, helicopters, airplanes, and the like, both military and civil as well as private and commercial, are subject to threats that can be generally categorized as follows:

• i. Chemical Energy (CE) threats such as, for example, missiles and unguided rockets, including but not limited to shoulder fired missiles, such as anti-aircraft type missiles, having a speed on the order of about 1,000 ft/sec to about 3,000 ft/sec.
• ii. Shoulder-fired low cost CE threats such as, for example, rocket-propelled grenades (“RPG”) having a speed on the order of about 400 ft/sec.

In this regard, specific defensive countermeasure (“CM”) techniques generally, and in theory, must be applied to defeat each respective type of threat. For example, a CE threat can be defeated by a fragmenting or blasting type of CM that can hit one or more critical locations of the warhead of the threat such that the warhead is asymmetrically detonated and thus becomes unable to form a penetrator or a penetrating jet typically characterizing such a threat, since simply destroying the body of the CE threat could still allow the penetrator formation and result in the piercing of the armor of and subsequent damage to the platform. However, the resulting explosions of the CM, and possibly the warhead of the threat, would represent a high risk to a slow-moving airborne platform.

Thus, there exists a need for a non-explosive protective weapon system capable of being effective to protect against incoming threats aimed at slow-moving and low-flying airborne platforms such as commercial aircraft during take-off and landing. In some instances, a simple configuration and/or construction of the protection apparatus, that is effective without using explosives, may be advantageous in terms of operational effectiveness, cost effectiveness, ease of construction/maintenance, and dependability.

BRIEF SUMMARY OF THE INVENTION

The above and other needs are met by the present invention which, in one embodiment, provides a protection apparatus adapted to protect a moving platform associated therewith against an incoming threat having a mass. The protection apparatus has a mass and is adapted to be deployed from the moving platform in a first direction toward the threat, wherein the threat is moving in a second direction toward the moving platform at a threat velocity. Such a protection apparatus comprises a projectile housing. A first deployable device is operably engaged with the projectile housing, and is adapted to capture the threat upon deployment such that the protection apparatus mass is combined with the threat mass via the first deployable device. A second deployable device is operably engaged with the projectile housing, and is configured to be deployed upon the first deployable device capturing the threat. The second deployable device is further configured to decrease the velocity of the combined protection apparatus and threat masses in the second direction.

Another advantageous aspect of the present invention comprises a protection system adapted to protect a moving platform associated therewith against an incoming threat having a mass. Such a protection system comprises a launching device adapted to operably engage the moving platform. A protection apparatus has a mass and is configured to be deployed by the launching device in a first direction toward the threat, with the threat moving in a second direction toward the moving platform at a threat velocity. Such a protection apparatus comprises a projectile housing. A first deployable device is operably engaged with the projectile housing, and is adapted to capture the threat upon deployment such that the protection apparatus mass is combined with the threat mass via the first deployable device. A second deployable device is operably engaged with the projectile housing, and is configured to be deployed upon the first deployable device capturing the threat. The second deployable device is further configured to decrease the velocity of the combined protection apparatus and threat masses in the second direction.

Yet another advantageous aspect of the present invention comprises a method of protecting a moving platform against an incoming threat having a mass. Such a method comprises deploying a protection apparatus from the moving platform in a first direction toward a threat in response to detection thereof, with the threat moving in a second direction toward the moving platform at a threat velocity. The protection apparatus has a mass and comprises a projectile housing having a first and a second deployable device operably engaged therewith. The first deployable device is deployed from the projectile housing to capture the threat such that the protection apparatus mass is combined with the threat mass via the first deployable device. The second deployable device is then deployed from the projectile housing, upon the first deployable device capturing the threat, such that the second deployable device decreases the velocity of the combined protection apparatus and threat masses in the second direction.

Embodiments of the present invention thus provide a protection apparatus having certain advantageous features. For example, some embodiments implement a cuing sensor that is capable of, for instance, detecting the threat(s); discriminating the threat(s) from non-threats; determining the threat flight path, including distance, speed, and angular position, to determine if the platform to be protected will actually be threatened; timely directing the launch of an appropriate protection apparatus to capture the threat and prevent the threat from reaching the platform or otherwise disabling or deflecting the threat. Accordingly, a protection apparatus can be timely launched with an appropriate launch time and exit speed so to engage the threat at a pre-determined safe distance (otherwise referred to herein as the intercept distance) from the platform. Embodiments of the present invention therefore meet the above-identified needs and provide significant advantages as further detailed herein.

BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWING(S)

Having thus described the invention in general terms, reference will now be made to the accompanying drawings, which are not necessarily drawn to scale, and wherein:

FIG. 1 is a schematic of functionality of a protection apparatus according to one embodiment of the present invention for protecting a moving airborne platform against an incoming threat;

FIG. 2 is a schematic of a moving airborne platform being exposed to an incoming threat;

FIG. 3 schematically illustrates a protection apparatus according to one embodiment of the present invention being launched from a moving airborne platform in response to an incoming threat; and

FIGS. 4-8 schematically illustrate a protection apparatus according to one embodiment of the present invention being deployed to intercept an incoming threat and alter a trajectory characteristic thereof to thereby allow the moving airborne platform to escape the threat.

DETAILED DESCRIPTION OF THE INVENTION

The present invention now will be described more fully hereinafter with reference to the accompanying drawings, in which some, but not all embodiments of the invention are shown. Indeed, this invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this disclosure will satisfy applicable legal requirements. Like numbers refer to like elements throughout.

FIGS. 1 and 2 schematically illustrate functionality of a protection apparatus according to one embodiment of the present invention, such a protection apparatus being indicated by the numeral 100 for protecting a moving airborne platform 50 against an incoming threat 75. In such a scenario, the threat 75 (such as, for example, an unguided rocket, or an optical, radar or infrared guided/heat-seeking missile) has a weight W_threat (and corresponding mass) and an approaching velocity V_threat toward the airborne platform 50 such as, or example, an airplane. An airborne platform 50, such as an airplane, initially taking off at a low altitude, for example, about 50 ft from the ground, may have a velocity V_platform of about 150 mph or higher. At this point, the aircraft 50 is vulnerable to the threat 75 since maneuverability of the aircraft 50 is limited and the airspeed thereof is relatively low.

According to embodiments of the present invention, the aircraft 50 includes a threat detection system 600 having, for example, an optical sensor, an infrared sensor, and/or a radar device, configured to detect the incoming threat 75 directed toward the aircraft 50. Such a threat detection system 600 may comprise, for example, a cuing sensor (or “second detection device”) associated therewith. In such embodiments, the cuing sensor may be configured to, for example, direct the launching device 500 via a controller device (“second controller device”—not shown) to launch the protection apparatus 100 in response to detection of the incoming threat 75 (see, e.g., FIG. 3). The threat detection system 600 may be implemented in many different manners. For example, the threat detection system 600 may be mounted to the platform 50 on or in close proximity to the launching device 500, may be mounted in the protection apparatus 100, or may be disposed remotely with respect to the launching device 500 and/or the platform 50.

In embodiments of the present invention, the threat detection system 600/cuing sensor is important to the effectiveness of the protection apparatus 100, and the parameters of the threat detection system 600/cuing sensor are defined, at least in part, by the type of threat 75 and an intercept distance 125 from the platform 50 that the threat 75 is intercepted. That is, the threat 75 must be intercepted at a distance of at least the intercept distance 125 from the platform 50, as shown in FIG. 1, in order for the desired level of protection to be provided. The intercept distance 125 may be determined from a variety of factors such as, for example, the sensitivity of the threat detection system 600/cuing sensor, the time necessary to actuate the launching device 500 and to launch the protection apparatus 100, the time required to deploy the first deployable device 300 (as further discussed herein) from the protection apparatus 100, the acceleration and intercept speed of the protection apparatus 100, the nature of the platform 50 to be protected, the speed of the threat 75, and/or the launch distance of the threat 75 with respect to the platform 50. However, one skilled in the art will readily appreciate that many other factors may determine an appropriate intercept distance 125. Various embodiments of the threat detection system 600/cuing sensor/controller device/launching device 500 implemented in the present invention are disclosed, for example, in U.S. patent application Ser. No. 10/787,843, filed Feb. 26, 2004, and Ser. No. 11/225,814, filed Sep. 13, 2005, both entitled Active Protection Device and Associated Apparatus, System, and Method and assigned to Chang Industry (the assignee of the present invention), both of which are hereby incorporated herein in their entirety by reference.

Embodiments of the protection apparatus 100 are particularly configured to protect the platform 50 against an incoming threat 75, wherein such a threat 75 may be, for instance, a chemical energy (CE) type such as a rocket-propelled grenade (“RPG”), a kinetic energy (KE) type threat, or any other type of threat 75 which may be addressed and intercepted by a protection apparatus 100 as described herein or extensions or variants thereof within the spirit and scope of the present invention. Still further, the term “platform” as used herein is intended to be entirely nonrestrictive and may include, for example, an airborne vehicle such as a helicopter, an airplane (commercial, civilian, or military), an unmanned drone, or the like. However, the platform 50 does not necessarily need to be a “vehicle,” but may also comprise, for example, an orbiting satellite.

In one embodiment, the protection apparatus 100 is configured as an aerodynamic missile-like interceptor device, as shown in FIGS. 3 and 4, wherein the protection apparatus 100 generally includes a projectile housing 250 having a leading portion 200 and a trailing portion 225, a first deployable device 300, and a second deployable device 400 (as shown in FIGS. 7 and 8) The components of the protection apparatus 100 combine to define a protection apparatus weight W_intercept (or corresponding mass), wherein the protection apparatus 100 includes a propulsion system (not shown) for allowing the protection apparatus 100 to attain a particular intercept velocity V_intercept upon launch. One skilled in the art will appreciate that such a propulsion system may be configured in many different manners, as appropriate, though, in one embodiment, the propulsion system is configured to be non-explosive or minimally explosive.

The first deployable device 300 is operably engaged with and housed by the projectile housing 250, particularly about the trailing portion 225 thereof. In some instances, however, the first deployable device 300 may be housed and/or deployed from a medial portion of the projectile housing 250 (see, e.g., FIG. 4). In one embodiment, the first deployable device 300 is configured to be deployed from the trailing portion 225 of the projectile housing 250 (FIGS. 4 and 5), after the protection apparatus 100 is launched from the launching device 500 of the platform 50, so as to intercept and capture the threat 75 such that the protection apparatus weight W_intercept (or corresponding mass) is combined with the threat weight W_threat (or corresponding mass) via the first deployable device 300 (see, e.g., FIG. 6). In such a manner, the combination of the protection apparatus and threat weights, for example, at least partially reduces the velocity, momentum, or kinetic energy of the threat 75, without causing the threat 75 to detonate or otherwise explode.

As shown in FIGS. 5-8, the first deployable device 300 may further comprise, for example, a net-like structure or a decelerator device formed of, for instance, an aramid fiber material such as Kevlar™ brand fiber material from DuPont, a fiberglass material, a carbon fiber material, a lightweight metal or polymer material, or combinations thereof. Such a first deployable device 300 is configured to be, for example, sufficiently strong, tear resistant, and light weight such that, when deployed projectile housing 250, spreads out radially from the projectile housing 250 to define a capture area for capturing the threat 75. In one embodiment, the first deployable device 300 is configured to be deployed without significantly slowing the velocity V_intercept of the protection apparatus 100. Further, if the first deployable device 300 is a net-like structure, each net opening is configured/sized to be smaller than the maximum cross-sectional area of the threat 75 to be intercepted. In some instances, the net-like structure of the first deployable device 300 and/or the net opening defined thereby is configured to be resilient or at least partially yielding or plastically deformable so as to reduce the “impact” experienced by the threat 75 upon capture thereof by the first deployable device 300. The reduction in the “impact” upon capturing the threat 75 may be desirable because, in some instances, the threat fuse is a piezoelectric device configured to produce a detonation pulse to the warhead carried by the threat 75 when an impact pressure is sensed. The first deployable device 300 and/or the protection apparatus 100 must thus be configured to dampen or otherwise minimize the apparent “impact” experienced by the threat 75 upon capture thereof. In addition, the first deployable device 300, in one alternate embodiment, may be configured to deflect the threat 75 upon capture such that, if the threat 75 does detonate, the direction of detonation is away from the platform 50.

When deployed, the first deployable device 300 may have many different shapes such as, for example, generally rectangular or circular. In some advantageous instances the first deployable device radially extends to have a height dimension at least as tall as the platform 50. In other advantageous instances, the first deployable device 300 is configured to have a deployment actuator (not shown) operably engaged therewith for deploying the same from the projectile housing 250 to radially extend therefrom. In some instances, the first deployable device 300 is configured to be deployed by the deployment actuator via a controller device (“first controller device”—not shown), wherein the controller device is configured to be responsive to the detection of the threat 75 by a first detector device or fusing sensor (not shown) carried by the protection apparatus 100 about the leading portion 200 or in the medial portion of the projectile housing 250. One skilled in the art will appreciate, however, that the first deployable device 300 may be deployed in many different manners such as, for example, via a timing sequence or via a threat detection signal from the threat detection system 600/cuing sensor, and the implementation of a fusing sensor in embodiments of the present invention is merely exemplary of one alternate embodiment that is not intended to be limiting in any manner. Various embodiments and configurations of such a fusing sensor implemented in the present invention are disclosed, for example, in U.S. patent application Ser. No. 10/787,843, filed Feb. 26, 2004, and Ser. No. 11/225,814, filed Sep. 13, 2005, both entitled Active Protection Device and Associated Apparatus, System, and Method and assigned to Chang Industry (the assignee of the present invention), both of which are hereby incorporated herein in their entirety by reference.

One skilled in the art will further appreciate that the cuing sensor comprising the second detection device, and the fusing sensor comprising the first detection device, according to embodiments of the present invention, may each more generally comprise a range-finding apparatus configured to sense the threat 75 as well as determine a range thereof with respect to the platform 50. Accordingly, any such range-finding apparatus may comprise, for example, any one or more of a laser detection and ranging device (LADAR), a radio detection and ranging device (RADAR), and a light detection and ranging device (LIDAR), wherein such range-finding apparatuses may be configured to operate in any appropriate spectrum or at any appropriate frequency, using any appropriate signal-generating and/or signal-detecting mechanism. For example, an appropriate signal for such a range-detecting apparatus may be generated in the millimeter wave range or the microwave range, or in the infrared spectrum or the visible light spectrum, while the signal-generating mechanism may comprise a laser or a light-emitting diode (LED). Accordingly, one skilled in the art will appreciate that the examples of detection devices presented herein are not intended to be limiting in any manner.

The deployment actuator and the first deployable device 300 are configured such that the first deployable device 300 is relatively quickly deployed, such as on the order of milliseconds or less, once notified by the first controller device of the detection of the threat 75 in proximity to the protection apparatus 100 by the fusing sensor. Further, the area of the first deployable device 300 may be, for example, at least 50 feet in width (or diameter), with a height of at least 10 feet, or as necessary to correspond to the height of the airborne platform 50. However, the dimensions of the first deployable device 300 are preferably sized such that, at a minimum deployment altitude of the protection apparatus 100/first deployable device 300, the first deployable device 300 will not contact the ground. For example, given the layouts of most airports, the platform 50 will generally be at least 20 feet in air before being vulnerable to attack by a threat 75 and, as such, the first deployable device 300 can be sized accordingly. However, one skilled in the art will appreciate that these examples are not intended to be limiting in any manner since the first deployable device 300 may be appropriately sized to meet many different circumstances where an airborne platform 50 is to be protected from a threat 75.

Preferably, the deployment actuator is configured to be non-explosive with respect to the manner in which the first deployable device 300 is deployed from the projectile housing 250. For example, the deployment actuator may be configured to operate via a pressurized fluid or compressed gas, such as air, nitrogen, or other appropriate gas or fluid. One skilled in the art will appreciate, however, that the deployment actuator can be configured in many different manners such as, for example, to use a mild explosive or a mechanical device for deploying the first deployable device 300. In some instances, the first deployable device 300 includes, for example, weighted members 325 (see, e.g., FIGS. 4-8) disposed about the perimeter thereof that are deployed by the deployment actuator to facilitate the radial spread of the first deployable device 300. The perimeter portion of the first deployable device 300 may also be configured to capture the threat 75 and/or deflect the threat 75 from the trajectory toward the platform 50. As discussed, the first deployable device 300, the weight (mass) of the protection apparatus 100, and/or the velocity of the protection apparatus 100 are preferably configured such that, upon capture and/or deflection of the threat 75 thereby, the threat 75 is not detonated or otherwise caused to explode. In this manner, the explosive threat to the platform 50 is reduced or minimized if the threat 75 is captured in relatively close proximity to the platform 50, and the risk or injury/damage to persons and/or property on the ground is also reduced.

To reiterate, the protection apparatus 100 launched from the airborne platform 50 has a weight W_intercept (mass) and a velocity of V_intercept. After the deployed first deployable device 300 has captured the threat 75, the combined weight W_threat+W_intercept (mass) will have a smaller velocity toward the airborne platform 50 due to the reduction in the momentum or kinetic energy of the threat 75 caused by the interaction with the protection apparatus 100 via the first deployable device 300. That is, when the threat 75 is captured by the first deployable device 300, the weight thereof will be combined such that the combined momentum in the direction of the airborne platform 50 will be:
V_combined={(W_threat×V_threat)−(W_intercept×V_intercept)}/(W_threat+W_intercept)

As a result, V_combined will be lesser than V_threat. However, the decrease in the velocity V_threat of the threat 75 may not be sufficient to prevent the threat 75 from impacting the airborne platform 50. As such, embodiments of the present invention further comprise a second deployable device 400 operably engaged with the protection apparatus 100. As shown in FIGS. 7 and 8, the second deployable device 400 may comprise, for example, a parachute-type device or a decelerator device housed by the leading portion 200 of the projectile housing 250, and formed of, for instance, an aramid fiber material such as Kevlar™ brand fiber material from DuPont, a fiberglass material, a carbon fiber material, a lightweight metal or polymer material, or combinations thereof. Such a second deployable device 400 is configured to be, for example, sufficiently strong, tear resistant, and light weight such that, when deployed from the projectile housing 250, the second deployable device 400 spreads out radially from the projectile housing 250 for decelerating, slowing, and/or altering the trajectory of the threat 75. In some instances, however, the second deployable device 400 may be housed and/or deployed from a medial portion of the projectile housing 250.

The protection apparatus 100 is configured such that commensurately with or soon after the threat 75 is captured by the first deployable device 300, the second deployable device 400 is deployed by a deployment actuator (not shown) operably engaged therewith, in some instances, via the first controller device that may also be operably engaged therebetween. In other instances, the deployment actuator and/or the first controller device may be configured to be responsive to the impact between the first deployable device 300 and the threat 75, via an appropriate detection mechanism (not shown) such as, for example, an accelerometer or any other suitable mechanical, electrical, or electromechanical device, to deploy the second deployable device 400 as the threat 75 is captured. When deployed, the second deployable device 400 may have many different shapes such as, for example, generally rectangular or circular. The deployed second deployable device 400 thereby acts to decelerate and/or alter the trajectory of the combined weights of the protection apparatus 100 and the threat 75. Preferably, the deployment actuator for deploying the second deployable device 400 is configured to be non-explosive with respect to the manner in which the second deployable device 400 is deployed from the projectile housing 250. For example, the deployment actuator may be configured to operate via a pressurized fluid or compressed gas, such as air, nitrogen, or other appropriate gas or fluid. One skilled in the art will appreciate, however, that the deployment actuator can be configured in many different manners such as, for example, to use a mild explosive or a mechanical device for deploying the second deployable device 400.

According to various embodiments of the present invention, the protection apparatus 100 also includes various componentry 275 (FIGS. 4-7) disposed within the projectile housing 250 for providing the functionality disclosed herein. For instance, the componentry 275 may include the deployment actuator(s) for the first and second deployable devices 300, 400, the first controller device, the first detection device (fusing sensor), a power supply (i.e., a charged capacitor power supply) for powering any or all of the devices included in the componentry 275, and a safing and arming device (not shown). The safing and arming device is a mechanism configured to prevent an unintentional or otherwise faulty launch of the protection apparatus 100, the first deployable device 300, and/or the second deployable device 400. For example, the safing and arming device may be controlled by an operator of the platform 50 so as to arm (allow operation) of the protection apparatus 100 upon takeoff and to safe (disallow operation) the protection apparatus 100 upon landing. In some instances, the safing and arming device may be further configured to allow the first and second deployable devices 300, 400 to function only upon launch of the protection apparatus 100 from the platform 50.

According to embodiments of the present invention, the time required for the threat 75, captured by the first deployable device 300, to reach the original position of the platform 50 is D/V_combined, where D is the intercept distance 125. However, during this time, the airborne platform 50 is continuing to move at a forward velocity V_platform and, thus, will proceed from the original position by a distance d=V_platform×(D/V_combined), where the distance d is indicated by the numeral 175 in FIG. 1.

In one exemplary scenario, a threat 75 may comprise a rocket-propelled grenade (RPG), where such an RPG may have a weight W_threat of about 5 lbs, and typically has a velocity V_threat of about 700 ft/sec. Once launched from the platform 50, a protection apparatus 100 according to embodiments of the present invention may have a weight W_intercept of, for example, about 5 lbs, and a velocity V_intercept of about 500 ft/sec. Once captured by the first deployable device 300, the velocity V_combined of the combined protection apparatus and threat weights (10 lbs) toward the airborne platform 50 will be about 100 ft/sec. If a suitable intercept distance D for the protection apparatus 100 to capture the threat 75 is determined to be about 50 ft from the airborne platform 50, the combined protection apparatus and threat weights will take about 0.5 sec to traverse the 50 ft intercept distance D. During this 0.5 sec, the airborne platform 50, presuming a velocity V_platform of 150 mph or 220 ft/sec (a Boeing 737 taking off has a speed of about 150 mph at an altitude of about 50 feet), will have traveled a distance of about 110 feet along its flight path (which may be presumed, in some instances, to be generally perpendicular to the trajectory of the threat 75) from its original position where it would have originally been impacted by the threat 75.

However, the first deployable device 300 capturing the threat 75 may not be sufficient in itself to slow down some threats, such as a high-speed shoulder-launched optically-or radar-guided missile, to allow the platform 50 to escape. A typical optically-guided missile may weigh, for example, about 10 lbs and have a velocity of about 2,500 ft/sec. As a result, the second deployable device 400 is important for reducing the velocity of the threat 75 as soon as possible after the threat 75 is captured by the first deployable device 300.

Various exemplary scenarios addressed by embodiments of the present invention are provided below in Table 1:

TABLE 1
			Scenario I:	Scenario II:
			RPG threat;	RPG threat;	Scenario III:
			Protection	Protection	High speed guided
			apparatus	apparatus	missile threat;
			without second	with second	Protection apparatus
			deployable	deployable	with second
Parameters	Description	Unit	device	device	deployable device
Hypothetical	Wthreat	lb	5	5	10
Numbers	Vthreat	Ft/sec	700	700	2500
	Wintercept	lb	5	5	5
	Vintercept	Ft/sec	500	500	500
	Vplatform	mph	150	150	300
Calculated	Diameter of second	ft	0 (No	6	6
Results	deployable device		second
			deployable
			device)
	Intercept distance from platform	ft	50	50	50
	Time for threat to reach	sec	0.5	105	1.15
	airplane after capture by first
	deployable device
	Platform displacement from	Ft	110	2233	506
	original position
Notes:
The above calculations are based on the air density of 0.077 lb/ft3 and drag coefficient of 1.2.

Many modifications and other embodiments of the invention set forth herein will come to mind to one skilled in the art to which this invention pertain having the benefit of the teachings presented in the foregoing description and the associated drawings. Therefore, it is to be understood that the invention is not to be limited to the specific embodiments disclosed and that modifications and other embodiments are intended to be included within the scope of the appended claims. Although specific terms are employed herein, they are used in a generic and descriptive sense only and not for purposes of limitation.

Claims

1. A protection apparatus adapted to protect a moving airborne platform associated therewith against an incoming threat having a mass, the protection apparatus having a mass and adapted to be deployed from the moving airborne platform in a first direction toward the threat, the threat moving in a second direction toward the moving airborne platform at a threat velocity, said protection apparatus comprising:

a projectile housing;

a first deployable device operably engaged with the projectile housing, the first deployable device being adapted to capture the threat upon deployment such that the protection apparatus mass is combined with the threat mass via the first deployable device; and

a second deployable device operably engaged with the projectile housing, the second deployable device being configured to be deployed upon the first deployable device capturing the threat, the second deployable device being further configured to decrease the velocity of the combined protection apparatus and threat masses in the second direction.

2. An apparatus according to claim 1 wherein the first deployable device comprises one of a net structure and a decelerator structure.

3. An apparatus according to claim 1 wherein the second deployable device comprises one of a parachute structure and a decelerator structure.

4. An apparatus according to claim 1 further comprising a deployment actuator operably engaged with one of the first and second deployable devices.

5. An apparatus according to claim 4 wherein the deployment actuator is configured to be non-explosive.

6. An apparatus according to claim 1 further comprising a first detector device operably engaged with the projectile housing and configured to sense a disposition of the threat with respect to the projectile housing.

7. An apparatus according to claim 6 further comprising a first controller device operably engaged with one of the first and second deployable devices, the first controller device being responsive to the first detector device to deploy the first deployable device to capture the threat and to deploy the second deployable device to slow the velocity of the combined protection apparatus and threat masses in the second direction.

8. An apparatus according to claim 1 wherein the projectile housing further comprises a leading portion configured to house the second deployable device and a trailing portion configured to house the first deployable device.

9. An apparatus according to claim 1 further comprising a safing/arming device operably engaged with one of the first and second deployable devices, and configured to prevent deployment thereof until the protection apparatus is deployed from the moving platform.

10. An apparatus according to claim 9 wherein the safing/arming device is configured to be remotely controlled.

11. An apparatus according to claim 1 wherein the projectile housing is configured to be deployed by a launching device adapted to be operably engaged with the moving platform.

12. An apparatus according to claim 11 wherein the launching device is further configured to deploy the projectile housing in response to a second controller device operably engaged with the launching device.

13. An apparatus according to claim 12 wherein the second controller device is further configured to direct the launching device to deploy the projectile housing in response to detection of the incoming threat by a second detection device operably engaged therewith.

14. A protection system adapted to protect a moving platform associated therewith against an incoming threat having a mass, said protection system comprising:

a launching device adapted to operably engage the moving platform; and

a protection apparatus having a mass and configured to be deployed by the launching device in a first direction toward the threat, the threat moving in a second direction toward the moving platform at a threat velocity, said protection apparatus comprising: a projectile housing; a first deployable device operably engaged with the projectile housing, the first deployable device being adapted to capture the threat upon deployment such that the protection apparatus mass is combined with the threat mass via the first deployable device; and a second deployable device operably engaged with the projectile housing, the second deployable device being configured to be deployed upon the first deployable device capturing the threat, the second deployable device being further configured to decrease the velocity of the combined protection apparatus and threat masses in the second direction.

15. A system according to claim 14 wherein the first deployable device comprises one of a net structure and a decelerator structure.

16. A system according to claim 14 wherein the second deployable device comprises one of a parachute structure and a decelerator structure.

17. A system according to claim 14 further comprising a deployment actuator operably engaged with one of the first and second deployable devices.

18. A system according to claim 17 wherein the deployment actuator is configured to be non-explosive.

19. A system according to claim 14 further comprising a first detector device operably engaged with the projectile housing and configured to sense a disposition of the threat with respect to the projectile housing.

20. A system according to claim 19 further comprising a first controller device operably engaged with one of the first and second deployable devices, the first controller device being responsive to the first detector device to deploy the first deployable device to capture the threat and to deploy the second deployable device to slow the velocity of the combined protection apparatus and threat masses in the second direction.

21. A system according to claim 14 wherein the projectile housing further comprises a leading portion configured to house the second deployable device and a trailing portion configured to house the first deployable device.

22. A system according to claim 14 further comprising a safing/arming device operably engaged with one of the first and second deployable devices, and configured to prevent deployment thereof until the protection apparatus is deployed from the moving platform.

23. A system according to claim 22 wherein the safing/arming device is configured to be remotely controlled.

24. A system according to claim 14 wherein the launching device is further configured to deploy the projectile housing in response to a second controller device operably engaged with the launching device.

25. A system according to claim 24 wherein the second controller device is further configured to direct the launching device to deploy the projectile housing in response to detection of the incoming threat by a second detection device operably engaged therewith.

26. A method of protecting a moving platform against an incoming threat having a mass, said method comprising:

deploying a protection apparatus from the moving platform in a first direction toward a threat in response to detection thereof, the threat moving in a second direction toward the moving platform at a threat velocity, the protection apparatus having a mass and comprising a projectile housing having a first and a second deployable device operably engaged therewith;

deploying the first deployable device from the projectile housing to capture the threat such that the protection apparatus mass is combined with the threat mass via the first deployable device; and

deploying the second deployable device from the projectile housing, upon the first deployable device capturing the threat, such that the second deployable device decreases the velocity of the combined protection apparatus and threat masses in the second direction.

27. A method according to claim 26 wherein deploying the first deployable device further comprises deploying the first deployable device, comprising one of a net structure and a decelerator structure, from the projectile housing.

28. A method according to claim 26 wherein deploying the second deployable device further comprises deploying the first deployable device, comprising one of a parachute structure and a decelerator structure, from the projectile housing.

29. A method according to claim 26 wherein one of deploying the first deployable device and deploying the second deployable device further comprises deploying the one of the first and second deployable devices with a non-explosive deployment actuator operably engaged therewith.

30. A method according to claim 26 further comprising detecting a disposition of the threat with respect to the projectile housing with a first detector device operably engaged therewith.

31. A method according to claim 30 wherein deploying the first and second deployable devices further comprises deploying the first deployable device to capture the threat and deploying the second deployable device to slow the velocity of the combined protection apparatus and threat masses in the second direction with a first controller device operably engaged therewith in response to the first detector device.

32. A method according to claim 26 wherein deploying the first and second deployable devices further comprises deploying the first deployable device from a trailing portion of the projectile housing and deploying the second deployable device from a leading portion of the projectile housing.

33. A method according to claim 26 further comprising preventing deployment of one of the first and second deployable devices, until the protection apparatus is deployed from the moving platform, with a safing/arming device operably engaged therewith.

34. A method according to claim 26 wherein deploying the protection apparatus further comprises deploying the protection apparatus from the moving platform with a launching device adapted to be operably engaged therewith.

35. A method according to claim 34 wherein deploying the protection apparatus further comprises deploying the protection apparatus from the moving platform with a launching device in response to a second controller device operably engaged with the launching device.

36. A method according to claim 35 wherein deploying the protection apparatus further comprises directing the launching device to deploy the protection apparatus with the second controller device in response to detection of the incoming threat by a second detection device operably engaged with the second controller device.