Patent Application
20100320312
The present invention relates to target-seeking missiles and, in particular, it concerns a miniature target-seeking missile for attacking surface targets, and corresponding methods of operation of a missile.
Various types of target-seeking missiles have been developed to address differing operational needs in modern warfare, each characterized by particular combinations of features. In general, missiles for targeting aircraft (i.e., air-to-air missiles and surface-to-air missiles) require extremely high speeds, typically in the range of 3-4 mach, in order to close in upon a fast-moving target. Particularly in the case of air-to-air missiles, high seeker gimbal angles and high maneuverability are also required in order to facilitate targeting of an enemy aircraft which is at a high angle off boresight. In order to maintain aerodynamic stability under these extreme operating conditions, some of the most recent generations of air-to-air missiles employ three or more independently controlled sets of symmetrically deployed aerodynamic control surfaces, particularly to allow independent management of the sensitive roll control-loop of the missile in flight. Thermal imaging seekers typically cover wide angles approaching full hemispherical coverage. The missiles are typically large, often with a pre-launch weight in the region of 100 kg.
Guided missiles for targeting surface targets (i.e., air-to-surface and surface-to-surface missiles) are configured for very different operating conditions, and therefore differ greatly from air-to-air missiles. For example, missiles for targeting surface targets typically do not require such high speeds, and are typically subsonic or at most around the speed of sound. Many guided missiles provide capabilities for following progress of the missile in flight and correcting, or even changing, the target during flight. Particularly in such cases, relatively slow speeds are preferred to allow time for controlling the missile. The combination of lower speeds, lower maneuverability and often relatively high weight avoid many of the problems of aerodynamic control, particularly of the roll parameter, present in air-to-air missiles. As a result, missiles for surface targets commonly employ a set of four fins for controlling pitch, yaw and roll.
A further distinction between missiles for surface targets and those for airborne targets is the range of seeker gimbal angles required. Surface-to-surface missiles and air-to-surface missiles typically home-in towards a target which is itself stationary or relatively slow moving. This ensures that the target is always more-or-less ahead of the missile, thereby allowing the use of imaging seekers with relatively small gimbal deflection angles, such as about ±30°.
At the small end of the scale of surface-to-surface guided missiles are man-portable or man-packable missiles which try to bring the capabilities of precision attack weapons to the infantry arena. Shoulder-launched anti-tank missiles are already well established, but their high price tag (typically in excess of US $40,000) limits their use to high-value or strategic targets. In order to provide a lower-cost option which would be suitable for lower-value “soft” targets, attempts have been made to scale-down and simplify missiles along the same conceptual lines as the anti-tank missiles to provide a miniature guided missile for mass production as an infantry weapon.
One recent example of these attempts is described in U.S. Pat. No. 6,244,535 to Felix. Felix describes a low cost miniature missile for use against low-value “soft” targets. The missile is described as having a weight of about 2 kg, length of about 46 cm, and body diameter of about 4 cm. It is driven by a low-speed rocket motor and employs 3 or 4 canards for aerodynamic control which are said to generate lateral accelerations of up to between 4 G and 8 G at 220 m/s. The missile implements a reduced performance navigation law based on a “simplified” guidance system. For target tracking, the missile employs a fixed (non-gimbaled) imaging sensor with a frame rate below 15 Hz in order to reduce costs and simplify processing. The fixed imaging sensor requires use of a non-optimal flat fly-out trajectory in order to avoid losing the target from the edge of the field of view. The missile operates in a “fire-and-forget” modality with inferior (“simplified”) tracking algorithms based on two-dimensional edge detection algorithms only.
For short range targets, situations frequently arise where the location of a desired target is well known but the target is obscured from view from the launching position. The missile of Felix, limited to “fire-and-forget” modality, clearly cannot be used against obscured targets. Furthermore, the flat fly-out trajectory of the Felix missile results in a line of sight close to the ground which is susceptible to momentary disruption by intervening objects during flight, thereby risking target tracking failure.
For longer ranges, it is known to use anti-tank missiles to attack a target which is obscured from direct view of the launch location. Such situations are typically classified in the art as “BLOS” (“beyond the line of sight”) for situations where the target is immediately behind a visible cover or “NLOS” (“no line of sight”) for situations where some intervening object (e.g., a hill or building) obscures the region of the target. In either case, the target can be attacked by launching a missile along an elevated flight path until the obscuring obstacle no longer obstructs view of the target and then locking-on to the target. In a BLOS scenario, the missile is typically initially locked-on to the cover or another object adjacent to the target and then the target is updated (“fire-and-update”) when the target comes into view. For NLOS scenarios, the missile is typically launched along an initial flight path under inertial guidance and locks on to the target during flight (LOAL-“lock-on-after-launch”). For shorter ranges, however, existing surface-to-surface missiles lack sufficient maneuverability to start along a high flight path and still bend the flight path down sharply enough to reach the target. The problem becomes even more pronounced where a target is located immediately behind a shielding structure such as a wall or building so that it may not become clearly visible until the missile is almost overhead. Additionally, in the modern warfare arena, there is a growing need for pinpoint attack capabilities which can target terrorists or other specific localized threats located within a civilian environment with the minimum possible collateral damage.
There is therefore a need for a small guided missile which would provide an effective solution for short range obscured targets, and which would allow pinpoint targeting of small targets with reduced collateral damage.
The present invention is a miniature target-seeking missile for attacking surface targets, and corresponding methods of operation of a missile.
According to the teachings of the present invention there is provided, a miniature target-seeking missile comprising: (a) a missile body; (b) a plurality of aerodynamic surfaces associated with the missile body, the plurality of aerodynamic surfaces including a plurality of control surfaces for controlling roll, pitch and yaw of the missile; (c) a set of at least three actuators associated with the control surfaces for controlling the control surfaces; (d) a seeker arrangement associated with the missile body, the seeker arrangement including an imaging sensor mounted on a gimbal mechanism; (e) a rocket motor associated with the missile body and configured for propelling the missile up to a maximum subsonic speed; and (f) a control system including at least one processor, the control system associated with the seeker arrangement and with the set of actuators, the control system controlling the actuators so as to navigate the missile to a target, wherein the plurality of aerodynamic surfaces and the actuators are configured such that a maximum lateral deflection of the missile flight path achieves a radius of curvature of the flight path smaller than 200 meters.
According to a further feature of the present invention, the gimbal mechanism has a range of deflection extending in at least one sense to an angle of at least 80 degrees deflection relative to a boresight direction of the missile. Preferably, the gimbal mechanism has a range of deflection which is asymmetric relative to a boresight direction of the missile body, the asymmetric range of deflection extending in one direction to at least about 120 degrees off-boresight.
According to a further feature of the present invention, the rocket motor is configured for accelerating the missile to a maximum speed of at least 100 meters per second, and preferably between 130 and 180 meters per second.
According to a further feature of the present invention, the missile has a mass of no more than two-and-a-half kilograms.
According to a further feature of the present invention, the plurality of aerodynamic surfaces includes three sets of at least two control surfaces, each of the sets being independently controlled by one of the actuators for controlling a corresponding one of roll, pitch and yaw of the missile.
According to a further feature of the present invention, the at least two control surfaces of each set of control surfaces are mechanically linked so as to actuated together by one of the plurality of actuators.
According to a further feature of the present invention, the at least two control surfaces of each set of control surfaces are deployed symmetrically about a central axis of the missile body.
According to a further feature of the present invention, the maximum lateral deflection of the missile flight path generates a lateral acceleration of at least 12 G at a speed of 180 meters per second.
According to a further feature of the present invention, there is also provided a warhead deployed within the missile body.
According to a further feature of the present invention, there is also provided an inertial navigation system associated with the processor.
According to a further feature of the present invention, the processor is configured to navigate the missile after launch according to an inertially defined flight path.
According to a further feature of the present invention, there is also provided a wireless communications link associated with the processor for transmitting images from the imaging sensor to a remote location.
According to a further feature of the present invention, the plurality of aerodynamic surfaces are configured such that, during descent through air, a terminal velocity of the missile is subsonic.
According to a further feature of the present invention, the plurality of aerodynamic surfaces include a plurality of folding aerodynamic surfaces assuming a folded state for deployment within a canister and configured to open after launch to a deployed state.
According to a further feature of the present invention, the control system is configured for navigating the missile along a flight path so as to reach the surface target at an incident elevation angle of greater than 75 degrees.
According to a further feature of the present invention, the control system is configured to switch between a plurality of modes for navigating the missile to a given surface target along any one of a plurality of flight-path types.
According to a further feature of the present invention, a first of the flight-path types is configured to achieve a higher maximum altitude than a second of the flight-path types.
According to a further feature of the present invention, each of the plurality of flight-path types is configured to achieve a corresponding desired incident elevation angle at the surface target.
There is also provided according to the teachings of the present invention, a miniature missile system including the aforementioned miniature target-seeking missile and a hand-held launcher for receiving and launching the missile, the launcher defining a launching direction of the missile, the control system being configured to select one of the plurality of flight-path types as a function of at least an elevation angle at which the launching direction is held prior to launching of the missile.
There is also provided according to the teachings of the present invention, a miniature missile system including the aforementioned miniature target-seeking missile and a hand-held launcher for receiving and launching the missile.
According to a further feature of the present invention, the launcher is configured to eject the missile prior to operation of the rocket motor with a momentum no greater than 20 kg.m/s.
According to a further feature of the present invention, the launcher includes an ejector mechanism for ejecting the missile without releasing a rearward flame.
According to a further feature of the present invention, the missile and the launcher further include components of a wireless communications link, and wherein the launcher includes a display for displaying images from the imaging sensor transmitted via the wireless communications link, and wherein the launcher further includes a user input device for updating a currently tracked target within the images for transmission via the wireless communications link as a target update input to the missile.
According to a further feature of the present invention, there is also provided a controller subsystem separate from the launcher, the controller subsystem including a display for displaying images output from the imaging sensor and a user input device for updating a currently tracked target within the images.
According to a further feature of the present invention, the controller subsystem and the missile include components of a wireless communications link, transmission of the images from the missile to the controller subsystem and transmission of the user input from the controller subsystem to the missile being performed via the wireless communications link.
According to a further feature of the present invention, the controller subsystem includes a mobile computer, and wherein the user input device includes a click-to-select pointing device.
There is also provided according to the teachings of the present invention, a miniature missile system including the aforementioned miniature target-seeking missile and a launcher for receiving and launching the missile, the launcher being configured for mounting on an airborne platform.
According to a further feature of the present invention, the launcher includes: (a) a canister for at least partially containing the missile before launch; and (b) a canister displacement mechanism selectively operable to displace the canister relative to the airborne platform through a motion including a component of rotation so as to facilitate locking on with the seeker arrangement to a target.
According to a further feature of the present invention, the motion includes a component of rotation about an axis substantially parallel to a central axis of the missile body.
According to a further feature of the present invention, the motion includes a component of rotation about an axis substantially perpendicular to a central axis of the missile body.
There is also provided according to the teachings of the present invention, a missile system comprising: (a) a target-seeking missile including a control system having a programmable data storage device for storing a software component of the control system; (b) a first launcher for launching the target-seeking missile, the first launcher including a first version of the software component for configuring the control system to navigate the target-seeking missile according to a first set of navigation rules, and a data connection for uploading the first version of the software component into the programmable data storage device; and (c) a second launcher for launching the target-seeking missile, the second launcher including a second version of the software component for configuring the control system to navigate the miniature target-seeking missile according to a second set of navigation rules, and a data connection for uploading the second version of the software component into the programmable data storage device, such that the target-seeking missile navigates according to the first set of navigation rules if launched from the first launcher and according to the second set of navigation rules if launched from the second launcher.
According to a further feature of the present invention, the first launcher is a hand-held launcher, and wherein the first set of navigation rules are configured for surface-to-surface flight paths.
According to a further feature of the present invention, the second launcher is configured for mounting on an airborne platform, and the second set of navigation rules are configured for air-to-surface flight paths.
There is also provided according to the teachings of the present invention, a method for operating a surface-to-surface missile comprising: (a) providing a target-seeking missile configured to selectively navigate to a target according to any of at least two flight-path types, a first of the flight-path types attaining a higher maximum altitude for a given target than a second of the flight-path types, the target-seeking missile being deployed within a launcher which defines a launching direction, the launcher being displaceable to allow variation of an elevation angle of the launching direction; (b) detecting a current elevation angle of the launching direction prior to launching of the missile; (c) if the current elevation angle lies within a first range of launch-pose angles, selecting the first flight-path type; and (d) if the current elevation angle lies within a second range of launch-pose angles, selecting the second flight-path type.
There is also provided according to the teachings of the present invention, a missile for use against a target comprising: (a) a missile body; (b) an explosive charge deployed within the missile body; (c) a communications link for receiving a switching command from a remote location; and (d) a remotely controlled fuze arrangement associated with the explosive charge and the communications link, the remotely controlled fuze arrangement being responsive to the switching command to switch during flight of the missile between at least two states including: (i) an armed state for detonation of the explosive charge against the target, and (ii) a disabled state in which the missile impacts the target as a kinetic shell.
According to a further feature of the present invention, there is also provided an imaging sensor associated with the missile body and the communications link, and wherein the communications link is configured to transmit images from the imaging sensor to a remote location.
According to a further feature of the present invention, the missile is part of a missile system which also includes a remote controller unit including: (a) a communications link for communicating with the missile; (b) a display associated with the communications link and configured to display the images from the imaging sensor; and (c) a user input device for inputting the switching command for transmission to the missile.
According to a further feature of the present invention, the missile is a target-seeking missile having a mass no greater than two-and-a-half kilograms.
There is also provided according to the teachings of the present invention, a method for operating a missile carrying an imaging sensor, an explosive charge and a switchable fuze arrangement against a target, the method comprising the steps of: (a) providing images from the imaging sensor to a remote operator; (b) receiving from the remote operator a switching input; and (c) responsive to the switching input, switching the fuze arrangement between at least two states including: (i) an armed state for detonation of the explosive charge against the target, and (ii) a disabled state in which the missile impacts the target as a kinetic shell.
According to a further feature of the present invention, the armed state is configured to detonate the explosive charge immediately on impact of the missile against a target.
According to a further feature of the present invention, the remotely controlled fuze arrangement is further switchable in response to the switching command to a delayed detonation state in which the fuze arrangement detonates the explosive charge a given period after impact.
According to a further feature of the present invention, the armed state is configured to detonate the explosive charge a given period after impact.
The invention is herein described, by way of example only, with reference to the accompanying drawings, wherein:
The present invention is a miniature target-seeking missile for attacking surface targets, and corresponding methods of operation of a missile.
The principles and operation of missiles according to the present invention may be better understood with reference to the drawings and the accompanying description.
Referring now to the drawings,
By way of introduction, it has been found that attempts to scale down surface-attack aerodynamic missiles to a miniature lightweight high-maneuverability missile (e.g., of weight less than two-and-a-half kilograms) tend to result in aerodynamic instability. To address this problem, it has been found that effective control and high maneuverability can be achieved with a subsonic lightweight missile by adopting various features typically associated with highly supersonic air-to-air missiles.
Thus, with reference to
It should be noted that the terms “pitch” and “yaw” are used herein as the typical examples of the independently controlled planes of rotation. However, as known in the art, the independent planes may alternatively be other planes, such as intermediate axes at ±45 relative to the standard “pitch” and “yaw” axes, as in the case of an X-tail configuration. In the latter case, pure pitch would be controlled by a combination of two sets of surfaces and pure yaw would be controlled by the same two sets of surfaces operated in a different manner. In all such cases, however, it is still accurate to say that roll, pitch and yaw are controlled by three sets of at least two control surfaces, and that each set of control surfaces are independently controlled.
Missile 10 is preferably implemented with a seeker arrangement 22 associated with missile body 12, typically located at the leading tip of the body and including an imaging sensor mounted on a gimbal mechanism. A rocket motor 24 is deployed within missile body 12, typically at the rear end, for propelling missile 10. A control system 26, including at least one processor, controls actuators 14, 16, 18 so as to navigate missile 10 along a flight path towards a surface target.
Before addressing the features of preferred embodiments of the present invention in more detail, it will be useful to define certain terminology as used herein in the description and claims. Firstly, the present invention relates to a guided missile which is a target-seeking, aerodynamic missile. The term “guided missile” defines the class of projectiles which have both a propulsion system (to distinguish from guided bombs or artillery shells) and can be steered during flight (to distinguish from non-steerable rockets). The term “aerodynamic missile” defines a missile which has aerodynamic surfaces (wings or fins) which allow it to fly through the air along a non-ballistic trajectory, thereby distinguishing from ballistic missiles. The term “target-seeking” is used to refer to a missile which includes a sensor system which provides information during flight to facilitate navigating towards a desired target. In the case of the present invention, the sensor system is preferably in the form of a seeker arrangement with an imaging sensor mounted on a gimbal mechanism. The information from the sensor system may be used independently by the missile, such as in a “fire-and-forget” mode, and may additionally or alternatively be used remotely, such as in a “fire, observe and update” mode.
The present invention relates primarily, although not exclusively, to a “surface-attack missile”, i.e., a surface-to-surface or air-to-surface missile, for targeting a surface target. The term “surface target” is used herein to refer to any target which is not airborne and not submersed. Thus defined, the term “surface target” includes, but is not limited to, personnel, stationary and moving vehicles, fixed structures and other objects, whether located at ground level, in or on a building, on a raised platform or at sea. It should be noted that the present invention is also useful for use against stationary or slow-moving airborne targets, such as slow flying helicopters or tethered observation balloons.
Reference is made to different “flight-path types” which may be selected for the missile of the present invention. The term “flight-path types” is used to refer to various navigation rules or parameters which specify different options for paths to be followed by the missile in flight. Thus different flight-path types applied to a given situation of target location and range will result different in different paths to be followed by the missile. The flight-path type may be defined by a particular navigation rule, by particular parameters used within a navigation rule, or by specific features of the desired flight path such as a maximum altitude to be reached or a required incident elevation angle on reaching the target. The term “incident elevation angle” is used to refer to the angle between the direction of motion of the missile when reaching the target and a horizontal plane, such that a horizontal approach would have an incident elevation angle of zero and a vertical descent would have an incident elevation angle of 90 degrees. In certain cases, a direction (compass bearing or direction relative to the launch location) may also be used to define the desired flight path.
Reference is also made to a “boresight direction” of the missile. The boresight direction is taken to be a direction defined by a central longitudinal axis passing along the body of the missile, intuitively corresponding to the “forward” direction of the missile. This direction is defined by the structure of the missile and does not necessarily correspond to the actual direction of motion of the missile in flight, which may vary according to the attack angle required for flight and other aerodynamic factors.
In certain preferred embodiments of the present invention, the gimbal movement of the seeker assembly is asymmetric relative to the boresight direction. In other words, the angular deflection of the gimbal about a given axis permits deflection to a greater angle in one direction away from boresight than in the opposing direction. In more technical terminology, it may be stated that the range of motion of the gimbal in certain preferred embodiments is asymmetric under reflection in a plane passing through the gimbal axis parallel to the boresight direction.
Most preferred implementations of the missile of the present invention include an “inertial navigation system” or “INS”. The term INS is well known in the art, and refers to a navigation system based upon a full set of three linear acceleration sensors and three angular acceleration sensors, thereby fully determining the motion of the missile and allowing reliable navigation along a desired flight path. This is in contrast to many surface-attack missiles which employ a reduced set of motion sensor sufficient for implementing proportional tracking algorithms and the like. Optionally, additional systems may be used to supplement or correct drift of the INS. These may include GPS sensors or image-correlation techniques anchored to a geographic database of images.
Reference is also made to a “hand-held” surface launcher. “Hand-held” in this context refers to a device the weight of which is supported primarily or exclusively by one or both arms of an operator during use. This definition distinguishes a class of light weapons from shoulder-launched devices where the weight is primarily borne by the operator's shoulder. Typically, hand-held weapons are limited to a maximum operative weight (missile plus launcher) of no more than about 4-7 kilograms.
Reference is also made to a “launching direction” of a missile within a launcher. The “launching direction” is the direction in which the missile is ejected from the launcher, and typically corresponds closely to the boresight direction of the missile when positioned within the launcher.
Turning now to features of preferred embodiments of the present invention in more detail, missile 10 preferably has a total pre-launch weight (not including the launcher) of no more than two-and-a-half kilograms and a body diameter of between 3 and 6 cm. The missile is preferably relatively short, having a body length less than ten times the body diameter.
Missile 10 is preferably configured to be a relatively slow subsonic missile, preferably with a maximum speed no greater than 0.7 mach, and more preferably no greater than 0.6 mach. This maximum speed results from the balance of thrust from rocket motor 24 against aerodynamic drag of the missile. In addition to the aforementioned sets of control surfaces 14, 16, 18, missile 10 preferably also features a set of relatively large wings 28 which preferably extend radially outwards from missile body 12 by at least about 1.5 times the body diameter, and preferably extend at their widest part along at least a quarter of the length of missile body 12. The relatively large aerodynamic surfaces cause sufficient drag such that, during free descent through air, a terminal velocity (i.e., the maximum equilibrium velocity reached without propulsion) of the missile is subsonic, and most preferably no more than about 0.5 mach. This is particularly valuable for air-to-surface operations since it renders the closing velocity towards a target controlled and well defined substantially independent of the altitude from which the missile was launched.
Most preferably, four similar wings 28 are spaced symmetrically around missile body 12, with control surfaces 14, 16, 18 angularly spaced at intermediate angles so as to minimize aerodynamic interference between flow patterns over wings 28 and the control surfaces. Alternatively, one or two sets of control surfaces may be implemented as control flaps associated with a corresponding set of wings 28. The plurality of aerodynamic surfaces and actuators are preferably configured such that a maximum lateral deflection of the missile flight path, when in flight at the aforementioned maximum subsonic speed, achieves a radius of curvature of said flight path smaller than 200 meters. This allows the missile to achieve high incident elevation angles of attack at targets located at relatively short range, preferably allowing impact at a target at an incident elevation angle in excess of 75° for ranges from 500 meters and beyond (up to near the maximum range of the missile).
Turning now to seeker arrangement 22, the imaging sensor may be implemented either as a day-time imaging sensor (e.g., based on CCD technology) for imaging in the visible light waveband, or a night-time sensor based on a far infrared thermal imaging sensor or an image intensifying night-vision sensor in the visible waveband. In certain implementations, a dual waveband seeker with two imaging arrangements may be used.
Unlike air-to-air missiles, the surface-attack function of the present invention does not require large gimbal deflection capabilities in all directions. On the other hand, the high maneuverability and the highly curved flight paths employed in certain modes of operation of missile 10 (to be described below) require large gimbal deflection angles at least in the “down” direction of regard. For this reason, the gimbal mechanism of seeker arrangement 22 preferably has a range of deflection which is asymmetric relative to the boresight direction of the missile body, and which extends in one direction to at least about 120 degrees off-boresight. In the opposite “up” direction, a maximum deflection in the range of 20-40 degrees is typically sufficient. Lateral gimbal ranges of motion may be significantly more limited. Where necessary, the limitations of the lateral (yaw) gimbal motion can be compensated for by use of roll of the missile, either within its canister before launch or during flight, in order to turn the high-deflection gimbal direction towards the target. An implementation of use of roll of a launch canister will be described below with reference to FIGS. 11 and 12A-12C.
Missile 10 also preferably includes a warhead 30 deployed within missile body 12. Warhead 30 is preferably less than 0.7 kilograms in weight, and may be any desired type of warhead. Examples include, but are not limited to, fragmentation warheads, shaped charges, explosively formed projectile warheads, incendiary warheads, stun-grenades, and dispersal systems for other lethal or non-lethal payloads such as paint.
According to one particularly preferred aspect of the present invention, equally applicable to various other missiles carrying an explosive charge, missile 10 includes a remotely controlled fuze arrangement which is switchable by the launch-controller or an additional controller in-the-loop (as will be described below) during flight of the missile between at least two, and most preferably three, different states: an armed state for immediate detonation on impact a delayed detonation state for detonation a short period after impact (for example, half a second after penetrating through a window into a building or vehicle); and a disabled state. The latter disabled state is of particular significance in the context of the miniature and highly precise missile of the present invention by providing an option to switch the missile prior to impact to become a purely kinetic “bullet”. This allows selective targeting of a small target or an individual without causing injury to people or property in close proximity to the target. This feature exhibits further synergy with the high incident angle flight-paths of the present invention by ensuring that the kinetic missile impacts the target from above, thereby minimizing the risk of the missile penetrating the intended target and continuing to cause injury to standers-by beyond the target. The possibility of converting the missile to a purely kinetic weapon during flight on the basis of real-time images returned from the missile seeker allows for completion of an intended operation under a wide range of circumstances where the operation might otherwise have needed to be aborted due to the risk of extensive collateral damage.
As mentioned earlier, preferred implementations of missile include an inertial navigation system (INS) 32 associated with the processor of control system 26. The INS may be supplemented by a global positioning system (GPS) sensor (not shown), thereby allowing the missile to navigate reliably towards a target defined by geographic coordinates. Even in such a case, in order to achieve the desired pinpoint accuracy, the closing stages of approach to a target are preferably navigated on the basis of information from the imaging sensor by pointing or locking onto a target.
Control system 26 preferably further includes a wireless communications link associated with the processor for transmitting images from the imaging sensor to a remote location. This allows for remote control of the missile's operation, such as by updating a target after launch, which is particularly important for targets which are obscured from the point of launch.
Turning now to FIGS. 3 and 4A-4E, it is a particular feature of certain preferred embodiments of the present invention that missile 10 may be stored and launched from a canister 34 which can be integrated into one or more type of launcher. In order to reduce the size of canister 34, at least some and preferably all of the aerodynamic surfaces are implemented as folding aerodynamic surfaces assuming a folded state for deployment within canister 34 (
In one particularly preferred implementation of the present invention, canister 34 is integrated into a hand-held launcher 42 (
For a stand-alone implementation of the present invention as a hand-held weapon, a display arrangement 44 is preferably integrated into launcher 42 for displaying a targeting image, preferably corresponding to the image from the seeker system 22, for target selection prior to and/or after launch. In cases other than hand-held launchers, one or more canister 34 including a missile 10 may be incorporated into a launcher mounted on any desired platform, and the display arrangement may be located at an arbitrary location adjacent to or remote from the launcher. Examples of suitable platforms include, but are not limited to, land vehicles, airborne platforms, fixed terrestrial platforms and seaborne platforms. Certain applications exemplified in the context of an airborne platform will be discussed further below.
Turning now to
The different flight-path types may be defined in various different ways. According to a first option, the flight-path types are defined by a desired incident elevation angle at which the missile should reach the target. Within operational limitations of the missile's maneuverability, this angle is preferably substantially independent of the range from the launch location to the target. Thus, by way of a non-limiting example, the missile may be configured to provide three available flight-path types: a first “low” mode configured to reach the target at a shallow incident elevation angle of about 0-30°; a second “medium” mode configured to reach the target at an intermediate incident elevation angle of about 30-75°; and a third “high” mode configured to reach the target at an incident elevation angle in excess of about 75°, and more preferably at 85°-90°, i.e., from almost directly above.
Continuing the same non-limiting example, the corresponding launcher pose angles for selecting one of these three modes may be chosen to be: 20°-40° for “low” mode 1; 41°-60° for “medium” mode 2; and over 61° for “high” mode 3. It will be noted that these angles are intuitively appropriate for the corresponding “low”, “medium” and “high” flight paths, and additionally provide synergy by ensuring that the missile is launched within a range of angles which is generally suited to the flight path it is to follow. Nevertheless, it is important to note that the differing flight paths are primarily not dictated by the launch angle but rather by control system 26 which ensures that, after initial stabilization, missile 10 will follow substantially the same “medium” mode path whether it was initially launched at 45° or 55°. The ranges of elevation angle used to select the different modes are preferably non-overlapping. Typically, the selection of a flight-path type is performed after initial locking-on to an intended target. In this case, the aforementioned pose angles used to select the different modes are most preferably measured relative to the line of sight to the selected target.
It will be noted that the capability to select different height flight-paths, including options of steep incident elevation angles, provides profound operational advantages. For straight-forward line-of-site applications, the present invention provides a default “low” mode which brings the missile quickly and efficiently to the desired target. The “low” mode also allows engagement of extremely short-range targets from 50 meters upwards. The “medium” and “high” options provide valuable extra flight time for verifying and/or updating the target designation, and allow operation in BLOS and NLOS modes where the high trajectory brings the initially obscured target into view. The high angle of elevation at impact also allows highly selective targeting of an object or individual in a crowded environment, either with the warhead activated or with the warhead disabled as described above in order to minimize collateral damage.
In the scenario of
With regard to the user interface for the controller sub-system, it is particularly preferred that the controller subsystem includes a mobile computer 46 with a “click-to-select” pointing device 48 for the user input. The phrase “click-to-select” is used herein to refer to any conventional user input device which allows quick and accurate control of a cursor or selection of a point on a computer screen. Thus, options for the pointing device include, but are not limited to, a mouse, a joystick, a trackball, a touchpad, and a touch-sensitive screen. In the last two examples, the tap of a finger or stylus is effective as the “click-to-select” operation.
In the case of the gunner, as an alternative to the joystick option, certain embodiments of the present invention employ the hand-held launcher as a pointing device. In this case, sensors in the launcher which detect angular motion of the launcher allow the operator to change a pointing direction of the launcher in order to control the direction of regard of the gimbaled imaging sensor, a selection point within the current field of view, or the position of a currently viewed sub-window of the current field of view, depending upon the particular control process to be performed. In each case, the result of the motion is visible as a change on display 44.
Although the operation of missile 10 has been exemplified above with reference to selection of alternative flight-path types of different trajectory heights, it should be noted that the same concept may be used to select a lateral (left or right) or even rear approach to a selected target. In the case of launch from a hand-held launcher, selection of a lateral approach direction may be achieved by pointing the launch direction to the corresponding side of the line of sight to the designated target. Additional details regarding definition of such lateral approach flight paths will be discussed below in the context of airborne platform implementations with reference to
Turning now to
As already illustrated in the context of surface-to-surface applications, the missile of the present invention may be configured to fly various different types of flight path wherein at least part of certain flight-path types is inertially defined prior to launch.
Specifically, flight path 50 in
Flight path 52 illustrates the use of an inertially defined initial stage of a flight path to turn rearward (or in any other desired direction) relative to the airborne platform direction. After the missile has turned towards the target, a lock-on-after-launch procedure is used to acquire the target and the flight path then continues in a manner similar to flight path 50. As before, operation of the missile may be networked such that control may be performed from the airborne platform, from a remote controller subsystem, of by any other combination of operators on the network.
Turning now to
It should be noted that the features of
Referring now to
Referring now to
Referring specifically to
Finally, it should be noted that a particularly preferred system based on the missile of the present invention allows use of a single version of the hardware of missile 10 with a wide range of different launchers. This greatly simplifies stocking of different branches of the armed forces, allowing a single armament to be stocked and supplied to multiple branches. However, in order to perform optimally in different applications such as those described, various different modes of operation are required for the different applications.
In order to achieve these different modes of operation without requiring hardware modification, it is a particularly preferred feature of the present invention that the control system of missile 10 includes a programmable data storage device for storing a software component of the control system. In a most preferred case, the missile itself is supplied essentially un-programmed, thereby rendering it non-functional in case it were to be stolen. The required software component for each different type of application is then supplied via a data connection from the corresponding launcher when the missile is loaded into the launcher and prepared for use. Thus, for example, the hand-held launcher 42 of
It should be noted that the principle of specializing dual-purpose or multi-purpose hardware by uploading of different software components from different launchers is believed to be of patentable significance outside the context of the missile of the present invention, for example, in modifying operation of missile intended for both air-to-air and surface-to-air applications automatically when linked to the corresponding launch system.
It will be appreciated that the above descriptions are intended only to serve as examples, and that many other embodiments are possible within the scope of the present invention as defined in the appended claims.
| Number | Date | Country | Kind |
|---|---|---|---|
| 177527 | Aug 2006 | IL | national |
| Filing Document | Filing Date | Country | Kind | 371c Date |
|---|---|---|---|---|
| PCT/IL07/01028 | 8/16/2007 | WO | 00 | 9/5/2010 |
