WO2005121687A1

WO2005121687A1 - Apparatus and method for operating a smoke generator device

Info

Publication number: WO2005121687A1
Application number: PCT/IL2005/000168
Authority: WO
Inventors: Nir Padan
Original assignee: Nir Padan
Priority date: 2004-06-06
Filing date: 2005-02-10
Publication date: 2005-12-22
Also published as: IL162372A0

Abstract

An apparatus and method for operating a smoke generator pod (198) is disclosed. The apparatus includes a smoke generator pod (198) associated with a combat platform (130, 146, 158). The method provides for manual or automatic controls for the time-sensitive activation of the smoke generator as a result of local or remote events occurring on local or remote combat platforms where the events are optionally communicated between the platforms (130, 146, 158) via a data link channel (172, 174, 176, 178, 180, 182). The apparatus and method provide visually enhanced inter-vehicular situational awareness to the operating crew of the combat platforms participating in combat training exercises or in real combat.

Description

APPARATUS AND METHOD FOR OPERATING A SMOKE GENERATOR DEVICE

BACKGROUND OF THE INVENTION

The present invention relates to an apparatus and method for operating a smoke generator device. More particularly, the present invention relates to an apparatus and method for utilizing a smoke pod in order to provide inter-vehicular visually enhanced situational awareness to the operating crews of combat vehicles during aerial training exercises or during real air combat.

DISCUSSION OF THE RELATED ART Aerial vehicles have been utilizing airborne smoke generator systems for decades. In order to provide aerodynamic efficiency current airborne smoke generator systems are typically packaged into externally and detachably mounted smoke pod units having the desirable aerodynamic characteristics. A smoke pod unit is typically self-contained and encloses a smoke-producing system that includes internal storage devices designed to store the ingredients required for a smoke-producing chemical mixture, a smoke generator device, and an electrical control system. Smoke pods containing smoke generator systems are generally used for heightening the visual impact of the flight by smoke emission during a flight. The smoke emitted typically includes different smoke types qnd different smoke colors. Smoke emission is particularly effective for aerial demonstrations, air show displays, flight testing and the like. Currently, the activation of the smoke generator within the smoke pod and the resulting highly visible smoke emission is accomplished directly through the manual manipulation of the smoke generator system controls by the operating crew of the aerial vehicle. Presently, no option exists in which smoke generation on an aerial platform or on a ground station could be automatically initiated and maintained for pre-defined periods by internal software implemented in an on-board computer in response to the occurrence of pre-defined events associated with the platform. Presently, no option exists where smoke generation is software-initiated initiated and software-maintained for predefined periods on a first combat platform or in a first ground station in response to signals transmitted from a second combat platform or from a second ground station via a data link. A new technology in the world's military aviation is the tactical data link system. Data links are non-voice telecommunication networks that allow for the digital transmission of data for all users in the airspace. The unique characteristics of this technique provide several advantages over the former aerial communications systems and enable a wide scope of new applications. An air-to- air data link allows real-time exchange of tactical data within and between the operating airborne ground-based or sea-based units. For example, in the attack and reconnaissance role, the data link allows radar-derived surface data to be transferred from one aircraft to one or more radar-silent attacking aircraft. Since an air-to-air data link system connects several aircraft in a full two-way link in real-time, it allows the group of linked aircraft to share real-time information and as a result considerably improve group co-operation. The transmission of aircraft- specific information through the air-to-air data link to other aerial platforms provides for a common aggregate of selectively shared data, such as navigational data, surveillance data, intelligence data, command and control data, tactical data, and the like.. Typically, data received through the data link channel is automatically fed into the communication channel from a pre-defined set of onboard sensors via an on-board data bus that is installed on the sending platform where the process is controlled by suitable software modules implemented in an on-board aircraft computer. Sent data is received via an on-board transceiver unit and inserted into the on-board data bus for suitable utilization by the systems of the receiving platform where the distribution of the data is controlled by suitable computer programs implemented in an on-board aircraft computer. The on-board data bus is equipped with appropriate data classification and data routing units that feed the received data to various operational on-board units, such as digital displays, weapon controls, navigation systems, flight controls, and the like. Typically an on-board aircraft computer is referred to as the mission computer. The mission computer (MC) provides multiplex (MUX) bus control, such as MIL- STD-1553. The MUX data bus provides an integrated control system and a standard interface for all the equipment connected to the bus. Furthermore, the bus provides a point at which bus traffic is available for access by monitoring instrumentation and recording systems. The MC functions include providing the interface between the flight control sensors the computer to the pilot's digital display indicators (DDIs), which provide primary flight information or system status, caution, warning, and failure annunciation. Aerial combat training systems are used by the military to train air, sea, and ground-based personnel in the use of weapon systems. Such systems simulate the firing of a weapon and optionally indicate whether the target would have been hit had an actual weapon been fired. The most important part of all advanced aircrew training and practice is the performance of procedures designed to simulate as closely as possible "live" combat operations. These simulated operations typically take place in a realistic environment. For aerial combat vehicles, such as fighter aircraft the operations include various types of airborne engagements, such as aerial combats, performed by two or more aircraft. The engagements involve simulated launching of offensive ordnance and defensive countermeasures, such as the activation of aerial guns, the launching of air-to-air missiles, the launching of IR flares, and the like. The simulated ordnance launch is typically activated following the occurrence of pre-defined events, such as the locking of a missile targeting system to the target aircraft, and the simulated countermeasure launch is activated following the detection of a simulated threat. The probability of the "hit" could be determined consequent to sophisticated analysis performed by the mission computer, involving for example time-sensitive trajectory calculations, and the like. The simulated activation of the weapon systems should be appropriately communicated to the aircrew of the target aircraft as well as to the other aircraft involved in the exercise and optionally to a ground station or to a sea-based platform. Currently, the appropriate notification is typically transmitted verbally via a radio voice channel. More advanced solutions propose automatic signaling via the utilization of an array of expensive and complex devices, such as laser beams, GPS, pyrotechnic charges, strobes, and the like. All the existing proposals necessitate specific installation of expensive equipment or considerable modifications of existing equipment. Simulated air combat operations often involve unintentional and dangerous trespasses on the pre-defined safety limitations, mission parameters, and rules of the training flight maneuvers. Such limitations include exceeding the confines of the combat space, flying beyond a pre-defined speed limit, flying above or below pre-defined altitude limits, to maneuver such as to generate a dangerous aircraft attitude (impended stall), and getting into close proximity to other aircraft (collision course). Currently, various cautioning, warning, and alerting systems are installed in an aircraft in order to detect dangerous situations, such as an impending stall state, a developing collision course, and the like. Consequent to the detection of a dangerous situation the warning systems provide appropriate situation-specific visual and/or aural indications to the aircrew of the specific vehicle. Thus, the indications are typically structured into audio format, such as a shrill sound replayed via the earphones, or into a visual format, such as the lighting up of an specific LCD, a display of a graphical structure on a display screen, and the like. Typically, the warning indicators are visible and audible for the aircrew of the platform only. Where necessary the indications are communicated to the other aircraft and/or a ground station via a voice channel. It could be easily perceived by one with ordinary skills in the art that in order to enhance the situational awareness of aircrews operating a group of aerial platforms in a co-operative manner, the situation-specific or event-specific indications should be substantially enhanced. The indications should be preferably external to a platform and should be visually striking in order to signal the occurrence of an event to the crew of co-operating platforms. In "live" combat situations the visual indications_. could be exploited for decoying or other purposes. A set of signaling techniques could provide the necessary indications where the elements of the signaling could reflect the visual impression of the emulated event or situation. Preferably the signaling should be performed in a fully automatic manner in order to reduce the delay inherent in the voice-based communication.

SUMMARY OF THE PRESENT INVENTION One aspect of the present invention regards an apparatus for enhanced external visual signaling associated with a combat platform. The apparatus comprises the elements of a smoke generator device enclosed in a smoke generator housing, the smoke generator housing connected externally to and carried externally by a combat platform, and a smoke generator controller device to activate, to terminate and to control the operations of the smoke generator device, the smoke generator controller device operating in response to manual commands or software commands generated subsequently to the sensing of predefined events occurring on the combat platform or on one or more remote combat platforms. A second aspect of the present invention regards a method for enhanced external visual signaling associated with a combat platform. The method comprises the steps of: identifying an event indicator generated in response to the occurrence of an event associated with the operations of a combat platform, responding to the event by relaying the event indicator to an external enhanced visual signaling application designed for the processing of the event in association with the event-specific parameters, generating a local or remote signaling command in accordance with the results of the processing of the event indicator with association with the event-specific parameters, and communicating the local signaling command to a signaling device to provide for enhanced external visual signaling. BRIEF DESCRIPTION OF THE DRAWINGS The present invention will be understood and appreciated more fully from the following detailed description taken in conjunction with the drawings in which: Fig. 1 is a schematic illustration of an environment wherein the proposed apparatus and method could operate, in accordance with the first preferred embodiment of the present invention; Fig. 2 is a block diagram depicting the on-board components relevant to the operation of the proposed apparatus and method, in accordance with the first preferred embodiment of the present invention; Fig. 3 is a schematic illustration of an environment wherein the proposed apparatus and method could operate, in accordance with the second preferred embodiment of the present invention; Fig. 4 is a block diagram depicting the on-board components relevant to the operation of the proposed apparatus and method, in accordance with the second preferred embodiment of the present invention; Fig. 5 is a schematic illustration of an environment wherein the proposed apparatus and method could operate, in accordance with the third preferred embodiment of the present invention; Fig. 6 is a block diagram depicting the on-board components relevant to the operation of the proposed apparatus and method, in accordance with the third preferred embodiment of the present invention; Fig. 7 is a block diagram depicting the structure of the smoke pod, in accordance with the preferred embodiments of the present invention; Fig. 8 is a block diagram depicting the structure of the on-board

Mission Computer, in accordance with the second and third preferred embodiments of the present invention; Fig. 9 is a block diagram of the Mission, Platform Configuration, and

Weapon Systems Parameters database, in accordance with the second and third preferred embodiment of the present invention; Fig. 10 is a block diagram depicting the operative components of the Enhanced External Visual Signaling (EEVS) application, in accordance with the second and third preferred embodiment of the present invention; Fig. 11 is .a flow chart describing the operation of the proposed method regarding the simulated firing of an air-to-air missile during an aerial combat training exercise, in accordance with the third preferred embodiment of the present invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An apparatus and method for the real-time execution of enhanced external visual signaling the purpose of which is to indicate the occurrence of one or more real or simulated events taking place on a combat aerial vehicle. The occurrence of the event is be to be communicated to the operating crew of one or more operationally co-operating aerial vehicles engaged either in an air combat training exercise or in "live" air combat. Simulated events are typically taking place during aircrew training missions. Such events could include a simulated aerial weapon systems activation (for example, a simulated burst of gun fire) simulated aerial weapon systems on-going operation (for example, the simulation of a short period A/A missile engine "burn") on a first aerial vehicle, and a simulated warhead or projectile impact detonation on a second aerial vehicle. Real events could include potentially dangerous flight situations, such as maneuvering in close proximity to other aircraft, flying near the limits of the flight envelope, crossing the confines of a pre-defined combat space, and the like. The occurrence of the one or more real or simulated event is typically detected by on-board weapon activation sensors, by inertial systems, by on-board dedicated aerodynamic sensors, by software systems capable of calculating the length of ordnance system-specific operating stages, such as the flight period of a simulated missile, by software systems recognizing potential hazards, and the like. The occurrence of an event could be initiated by the intentional activation of specific weapon system operation components associated with the air crew interface. Consequent to the detection of one or more real or simulated event a signaling device is activated for the duration of the event in order to provide enhanced external visual signaling representing the event. The signaling device visually communicates the occurrence of the event both to the aircrew of the aerial vehicle on which the event took place and more importantly to the aircrews of other distinct co-operating aerial vehicles. For specific events the detection of the event is followed by communication of the event indicator via a data link from a first aerial vehicle to a second aerial vehicle. Consequently, the received event indicator could effect on the second aerial vehicle the activation and the operation of the signaling device in order to provide enhanced external visual signaling that represents the indicated event. The signaling is operative in visually communicating the indicated event both to the aircrew of the second aerial vehicle on which the event took place, to the aircrew of the first aerial vehicle, and to the aircrews of other distinct co-operating aerial vehicles. The signaling characteristics, such as sequencing, period, and the like, are determined in accordance with the requirements of the clients. The requirements would be translated to base parameters and will be fed into the system. Such base parameter for example, could be an indicator signifying "simulate and signal visually missile launch, missile burn, and missile hit." An associated parameter could indicate the type and the operational characteristics of the simulated missile in order to define the period of the simulated missile engine "burn", the fight characteristics of the simulated missile, and the like. The operating characteristics of the signaling could be further determined by system-specific and weapon system-specific operating parameters. In order to provide optimal signaling the entire set of data available in the computing devices of the signaling platform (altitude, airspeed, flight zone, and the like) and the entire set of status data indicative of the operation of electrical and mechanical components of the platform (IF flare launcher system, missile launcher system, aerial gun system, and the like), could be obtained by the signaling command system subject to the restrictions and requirements determined by the client. Thus, the signaling could be initiated automatically following the sensing of some pre-defined event and terminated automatically as a result of the sensing of another pre-defined event (activating and deactivating the gun trigger). The signaling could be initiated automatically and terminated in accordance with real-time dynamic time calculations performed by the mission computer (simulated missile launch, missile time of flight (TOF)

"burn" and hit) based on the information stored regarding the characteristics of the missile, the environmental conditions, such as combat altitude, air pressure, and the like, the constantly changing inter-platform geometry, and the like. The signaling could be further initiated and terminated in a fully manually mode (activation of the IR flares launching trigger). Additionally the system-specific parameters could include information concerning the availability of a data link system, the type of the data link, the communication options, and the like. In the preferred embodiments of the present invention the signaling device is a smoke generator system that may be housed in specifically adapted smoke generator housing, such as a new specifically designed and developed smoke pod, an existing smoke pod specifically adapted for enhanced signaling, a converted missile body or a converted external fuel tank. Preferably an existing already certified housing will be used, such as an adapted pylon, an adapted fuel tank or an adapted missile body. The housing of the smoke generator would be designed, developed and/or adapted such as to provide suitable operational flight envelope enhancements in accordance with the operational requirements of maneuverings associated with typical air-to-air training exercises. Thus, the smoke generator housing and the contained components within should be suitably strengthened and optionally structurally modified in order to allow accurate and efficient operations at air speeds higher than 350 nautical miles per hour (for example, at supersonic speeds). The smoke generator housing and the contained component within should be further capable of providing signaling capability at heights up to 40 kilo-foot. The smoke generator housing could contain a specifically developed smoke generation controller unit physically or wirelessly linked to an internal data bus of the aerial vehicle and operating independently of an on-board mission computer. The smoke generator housing includes a smoke generator device that is activated in response to specific commands received from the on-board mission computer of the aerial vehicle via a data bus or in response to specific commands received from the in-built smoke generation controller installed in the smoke generator housing. The smoke generator effects the emission of smoke for a specific period of time. The emitted smoke provides an enhanced visual effect that is readily noticeable and recognizable by the aircrews of the aerial vehicles in the combat space or by the ground crew operating ground-based equipment participating in the exercise (for example, anti-aircraft guns and/or ground-to-air missiles). The commands for the activation of the smoke generator are selectively generated either in the mission computer of the aerial vehicle consequent to the reception of the event indicators or alternatively by the built-in smoke generator controller unit in the smoke generator housing consequent to the reception of an event indicator from the mission computer via the data bus. The smoke generator commands include various parameters regarding, for example, the required duration of the smoke emission, the type and color of smoke to be generated, and the like. Note should be taken, that different types and colors of smoke could be emitted simultaneously, such as for example, a specific smoke color indicating a missile launch and an another smoke color for indicating IR flare launching. The smoke generator controller processes the commands and activates the smoke generator in accordance with the command parameters. Note should be taken that in other embodiments of the present invention diverse other signaliiig devices could be used in order to provide for enhanced external visual signaling, such as pyrotechnic devices, strobe devices, laser devices, and the like. In one preferred embodiment of the present invention, the wireless communication of the event indicators from a first aerial vehicle to a second aerial vehicle is performed via a tactical data link system used for air-to- air data communications between aerial vehicles. For the implementation of the apparatus and method a new smoke pod could be developed or an existing standard smoke pod could be suitably upgraded. The smoke generator system is installed in a military aircraft, such as a manned or unmanned fighter aircraft, combat aircraft, bomber, trainer aircraft, and the like. The smoke generator system is installed in a fixed wing and/or rotating wing aircraft in order to provide visually enhanced signaling for the representation of the following events: a) simulation of various air-to-air, air-to-ground missile launching and simulation of missile flight during air combat exercises, b) simulation of aerial gun operation during air combat exercises, c) simulation of IR flares launching during air combat exercises in order to provide a low-cost alternative for the high cost method currently used, d) simulation of warhead impact and detonation during air combat exercises, e) testing and evaluation event indications during flight testing, e) safety indications, such as anti-collision warning, altitude blocking, operational/restricted area limitations, minimum/maximum altitude violations, loss of control indications, and the like, f) indications of various real air combat events. In the aerial vehicle the proposed apparatus and system necessitates the adaptation of several cockpit controls and electrical connections in order to provide for the activation and control of the smoke generator system. The proper representation of certain events requires on-board or external high-speed computers with the capability of providing high-resolution data processing. The MUX BUS interface and other similar systems provide ready access to event- generating data. Such data includes for example, gun trigger position, missile flight time flare system status, proximity to other aircraft, altitude, attitude, velocity, and the like. The proposed apparatus ands system provides the option of real-time resetting of the relevant software parameters. Some of the software parameters could be re-set in real-time by the operating crew of the aerial vehicle or by authorized members of a remotely located airborne or grourid-based control and command team. For example, the minimum permissible lower flight ceiling could be dynamically modified during a combat training exercise in accordance with the prevailing meteorological conditions, such as cloud cover height, and the like. In exceptional circumstances, other software parameters could be modified in an operating crew-specific, weapon system-specific and platform-specific manner The proposed apparatus and method could be implemented such as to operate in air-to-air, air-to-ground, ground-to-air, air-to-sea, and sea-to-air mode where the ground-to-air and the air-to-ground modes involve ground-based vehicles, such as anti-aircraft missile units, anti-aircraft artillery batteries, armored vehicles, and the like, enhanced with specific components of the proposed apparatus and method, such as similar or identical smoke generator devices, and communicatively linked to the aerial vehicles via a tactical data link. For example, a simulated ground-to-air anti-aircraft missile launch toward a target aircraft could be signaled to the crew of the targeted vehicle by the activation of a smoke generator installed on the launching ground-based vehicle while an associated simulated warhead impact and detonation on the targeted aerial vehicle could be communicated via a ground-to-air data link from the ground-based vehicle to the aerial vehicle in order to activate the smoke generator of the aerial vehicle and thereby indicate a "hit" of the ground-to-air missile on the aircraft. In another example, a simulated air-to-ground missile launch from an aerial vehicle towards a ground-based vehicle could effect the activation of the smoke generator on aerial vehicle for the calculated duration of the flight of the missile until the designated target. The simulated warhead impact and detonation on the ground- based vehicle could be communicated from the aerial vehicle to the ground-based vehicle that in turn could effect the activation of a smoke generator device on the ground-based vehicle and thereby signaling "hit" to the crew of the aerial vehicle. The underlying ideas of the present invention could be reduced to practice and implemented in several related and successively advanced preferred embodiments. In specific environments the different apparatuses and the different methods associated with the different embodiments could be co-located, implemented, and be optionally operative at the same time on the same platform or group of platforms. In such a case the decision concerning which of the embodiments is to be used could be pre-determined by the client or could be determined (in a pre-planned manner or dynamically during the operation) by the operating crews of the platforms in accordance with the prevailing conditions. In contrast, in other environments different embodiments of the present inventions could be applied to different platforms (or groups of platforms) in accordance with the prevailing financial, operational, and administrative constraints. Thus, in an environment where data link systems are unavailable or the configuration of the available platforms does not support the data link option then either the first or the second preferred embodiment of the present invention could utilized. On non- advanced platforms (such as basic trainers, for example) without an on-board computer being installed the first preferred embodiment of the present invention could be implemented. In the first preferred embodiment of the present invention the smoke signaling system is controlled manually by the operating crew of a combat platform in order to provide enhanced visual signaling concerning specific events to the operating crews of other platforms. In the first preferred embodiment smoke signaling in initiated, maintained and terminated in accordance with the manual manipulation of the smoke generator system controls by the operating crew. The manual manipulation of the smoke signaling controls will effect the sending of one or more manual signaling commands directly to the smoke generator system via an electrical signal path. In response to the commands the smoke generator system effects the appropriate emission of smoke signals. In the second preferred embodiment of the present invention the smoke signaling system is controlled automatically by a specific smoke signaling software comprising specifically developed smoke signaling computer modules that are installed in an on-board computing unit, such as an aircraft computer (AC) or a mission computer (MC). Indications regarding events occurring on the platform or events associated with the platform-environment situational relationship are collected by various on-board sensors. The resulting indicative signals are fed into the mission computer. The mission computer stores a set of smoke-signaling related parameters. In accordance with the received indicative event signals and the stored smoke signaling parameters the smoke signaling software controls the event-specific smoke signaling operations. The software modules dynamically generate one or more sequences of local time-sensitive smoke signaling commands and send the sequences of time-sensitive commands to the smoke generator system. In response to the commands the smoke generator systems emits smoke in order to provide enhanced visual signaling to the operating crews of one or more platforms, and in order to provide enhanced situational awareness to the operating crews. Note should be taken that the option for manual control mentioned in the first preferred embodiment could be still provided in the framework of the second preferred embodiment. In the third preferred embodiment the option of remotely activated signaling is added. The smoke signaling commands generated by the smoke signaling software on a first platform could be directed either to control local smoke signaling (as was described in the second preferred embodiment) or could be directed to control remote smoke signaling. Remote smoke signaling is accomplished by the transmission of the smoke signaling commands to a second platform via a data link channel. In the third preferred embodiment the smoke signaling software is suitably upgraded in order to enable the reception of remote commands sent from the first platform via a data link channel in order to enable suitable processing of the remotely received commands in the mission computer of a second platform. The remotely received smoke signaling commands are formatted into suitable command sequences and sent to the smoke generator device of the second platform to effect a sequence of time-sensitive smoke emissions. Note should be taken that the option for manually controlled signaling mentioned in the first preferred embodiment and the option for automatic local computer-controlled signaling mentioned in the second preferred embodiment could be provided in the framework of the third preferred embodiment. Referring now to Fig. 1 that describes in a highly schematic manner the environment in which the proposed apparatus and method could operate, in accordance with the first preferred embodiment of the present invention. Combat space 10 contains a first aerial vehicle 16, a second aerial vehicle 12, a third aerial vehicle 14, a ground-based combat vehicle 40, and a sea-based combat vessel (not shown). The aerial vehicles 16, 12, 14 are fixed-wing military fighter aircraft engaged in an aircrew combat training exercise, more particularly in a simulated visual range air-to-air combat typically referred to as DGFT (dogfight) in order to improve and enhance the maneuvering, control and weapon system-handling capabilities of the aircrew operating the vehicles 12, 14, 16.. It would be easily perceived that the first, second and third aerial vehicles 16, 12, 14 respectively, could be other types of aircraft, such as attack aircraft, bomber aircraft, rotating- wing aircraft, Unmanned Aerial Vehicles (UAVs), unmanned combat aerial vehicles (UCAVs), trainer aircraft, and the like. In the context of the training practice the aircraft 16, 12, 14 could be engaged in a ground attack on ground- based vehicle 40 or could manage defensive maneuvering against ground-to-air attacks by ground-based vehicle 40. In such a case the combat exercise could be operative for the anti-aircraft crew of the ground-based vehicle 40. First aircraft 16, second aircraft 12 and third aircraft 14 are equipped with simulated weapon systems 46, 22, 34, respectively. The simulated weapon systems could include various weapon system elements, devices, and sub-systems. Thus, a simulated aerial gun system could include targeting, sighting and tracking elements of an aerial gun system as well as image acquiring devices coupled to the operation of the system, sensors associated with the weapon system activator units, and the like. The simulated weapon systems 46, 22, 34 are activated by the simulated weapon system controls 44, 18, 32, respectively. For example, when a typical aerial weapon system, such as an aerial gun system, operates in a simulation mode, a signal generated by specific gun-activating devices, such as the gun trigger, are not sent to the actual gun units in order to effect the firing of the guns but are routed via a signal path to specific pre-defined components of a simulated weapon system, such as for example an image acquiring and image recording device. As a result, the simulated firing of the gun would effect the creation of a recording showing the target during the entire period of "firing". The simulated missile launcher system included in the simulated weapon systems 46, 22, 34 could include the targeting, sighting and tracking elements of an air-to-air missile system. The simulated missile launcher system could further include a practice missile including a targeting sub-system but without a missile motor, a warhead or flight controls. When the missile system operates in a simulation mode the signals generated by the missile-activating devices, such as the missile-launch switch, are not used for the activation of the missile engine units in order to effect the launching of the missile but are routed via an internal signal path to missile launch simulation components. The simulated weapon systems 46, 22, 34 could further include a simulated countermeasure system, such as an IR flare launching system, and the like. First aircraft 16, second aircraft 12, and third aircraft 14 further include a smoke generator system 50, 24, 38, respectively. The smoke generator systems 50, 24, 38 are housed in a smoke generator housing, such as an upgraded or newly developed smoke pod uploaded externally on the aircraft 16, 12, 14. The systems 50, 24, 38 could be housed in the practice missile, in a converted external fuel tank, or the like. In the first preferred embodiment of the present invention, the smoke generator systems 50, 24, 38 are controlled by smoke generator manual controls 48, 20, 36, respectively. The manual controls 20, 36, 48 are installed in the cockpits of the aerial vehicles 12, 14, 16, respectively in order to allow the operating crew of the vehicles 12, 14, 16 to control the operation of the smoke generator systems 24, 38, 50, respectively by the manual manipulation of the controls 20, 36, 48. Still referring to Fig. 1, in the context of the aircrew training exercise first aircraft 16 and third aircraft 14 are co-operatively engaged in a simulated close range air combat against second aircraft 12. First aircraft 16 is in a specific position in the combat space 10 that is suitable for the realization of a threat 42 against second aircraft 12. First aircraft 16 activates simulated weapon systems 46 in order to simulate a threat 42 against second aircraft 12. The simulated weapon is an air-to-air missile. Consequent to the activation of the suitable elements of the simulated weapon by the operating crew, a signal representing the missile launch command is sent to the smoke generator system 50 installed on the first aircraft 16. The signal is preferably generated by the manual manipulation of the smoke generator manual controls 48 by the operating crew of the aircraft. A smoke generator contained in a smoke generator housing is activated and smoke signaling 52 is emitted from the smoke generator housing in order to provide external visually enhanced indication of the missile launch. The smoke signaling

52 is controlled in a time-sensitive manner by the appropriate manipulation of the controls 44 by the operating crew of the first aircraft 16. Typically the smoke signaling 52 is maintained for some pre-defined period of time substantially overlapping the duration of the pre-determined missile engine "burn" of the simulated missile or the duration of the time of flight (TOF) of the simulated missile in accordance with pre-defined operating procedures. The smoke signaling 52 is a reasonable emulation of the smoke-trail typically emitted by the engine of a real missile. Thus, the smoke signaling 52 provides a strong visual indication of the missile launch and missile flight to the aircrews of first aircraft 16, second aircraft 12, and third aircraft 14. The indication of the on-going simulated missile attack by the smoke signaling 52 further provides the crew of the second aircraft 12 with the option of responding to the attack by performing suitable defensive maneuvering as well as by activating simulated countermeasures 28. The crew of second aircraft 12 activates the simulated IR flare system in the simulated weapon system 22. The commands generated by the control elements operative in the launching of the IR flares are routed to the simulated weapon system elements. In order to provide visual signaling concerning the activation of the simulated weapon system 22 to the operating crews of the first aircraft 16 and the third aircraft 14, the operating crew of the second aircraft 12 could activate manually smoke generator system 24 installed in the second aircraft 12. Consequent to the manipulation of the smoke generator manual controls 20 by the operating crew of the second aircraft 12 the smoke generator system 24 is activated and smoke will be emitted or smoke signaling 26 will be performed. The signaling 26 could comprise of distinct bursts of smoke such as to emulate the characteristic flashes accompanying the launching of operative IR flares. Note should be taken that the above-mentioned scenario is exemplary only. The first aircraft 16 could utilize other simulated weapon systems, such as an aerial gun. The second aircraft 12 could manage a simulated attack while the first aircraft 16 could be engaged in defensive maneuvers and actions. In addition, the simulated engagement could take place between one or more aircraft in the combat place and the ground-based vehicle 40 equipped substantially with the same type of apparatus and operating substantially the same method. Note should be taken that the above described components comprising the proposed apparatus, the functionality of the above- described components, and the functional relationships thereof are exemplary only. For example, in alternative versions of the first preferred embodiment the simulated weapon systems controls could have a dual purpose, such a) activating the simulated weapon systems, and b) simultaneously activating the smoke generator systems. A dynamically set position of a master control element, such as a switch or push-button, could determine whether the activation of the simulated weapon system effects the activation of the smoke generator system. Optionally, the smoke generator manual controls could include various smoke emission mode controls, such as dynamically set switches, the position of which will determine the type, duration, and color of the emitted smoke. Optionally, the operating crew of the aircraft could initiate and control smoke signaling consequent to the occurrence of specific event that is independent of the simulated weapon systems. For example, smoke signaling could be activated manually for decoying purposes, for emergency communication purposes (following the failure of voice communications), and the like. In accordance with diverse pre-determined operating procedures, smoke signaling could be utilized to indicate potentially dangerous and/or extreme flight circumstances. Referring now to Fig. 2 that illustrates the operative components installed in an exemplary aerial vehicle that are pertinent to the operation of the apparatus and method in accordance with the first preferred embodiment of the present invention. The components include aerodynamics sensors 58, weapon system sensors 56, a smoke generator device 70, simulated weapon systems 68, and an operating crew controls and displays 60. Operating crew controls and displays 60 are grouped sets of switching and display devices ergonomically located on one or more panels within the cockpit of the aircraft. Controls and displays 60 are utilized by the operating crew of the aircraft in order to monitor the operation of the aerial platform and the associated sub-systems. Controls and displays 60 include simulated weapon system controls 62, weapon systems and aerodynamics displays complex 64, and smoke generator manual controls 62. Weapon system sensors 56 are a set of devices operative in the monitoring of the operative status of the diverse weapon systems installed in the aerial vehicle. For example, a weapon system sensor associated with the aerial gun system is the remaining ammunition counter. The remaining ammunition sensor is monitoring the number of rounds left in the ammunition sub-system of the aerial gun system. The sensor provides the information to the weapon systems and aerodynamics displays complex 64. The number is then displayed on a suitable display device within the complex 64 in order to provide the aircrew with the information. Critical weapon system sensors include sensors associated with the sighting and targeting sub-systems, and the like. The function of the weapon systems sensors 56 is basically to provide weapon system related situational awareness to the aircrew. An extremely important group of weapon system sensors are "defensive" sensors the function of which is the identification, recognition of external threat signals and the activation of warning devices. Aerodynamic sensors 58 are a set of devices operative in sensing the status of the aerodynamic control surfaces. Sensors 58 further sense the extent of the aerodynamic forces acting on platform and display the results to the operating crew. For example, a critical aerodynamic sensor 58 is the altimeter. The successively sampled value representing the altitude of the aerial vehicle generates periodically a sensor signal. The value signal is relayed to the suitable display in the weapon systems and aerodynamics displays complex 64 to be presented to the operating crew of the aircraft. Weapon systems and aerodynamics displays complex 64 are one or more display screens on which flight-specific, platform-specific and weapon-system status-specific information is displayed to the aircrew. For example, the simulated launching of a missile could be basically indicated by a simple graphical indicator or the activation of a LED device. Optionally a curve representing the virtual flight path of the simulated missile could be shown. Furthermore, specific events, such as for example a missile hit on a targeted aircraft are also displayed. The displays complex 64 is responsible for the display of various weapon sensor data and aerodynamic sensor data. Critical indications, such as warnings and emergency states are also displayed in a suitably impressive manner. Note should be taken that above-described configuration is exemplary only. Simulated weapon systems controls 62 are a set of control devices, such as switches, push-buttons, and the like, that enable the operating crew of the aerial vehicle to activate, maintain, and terminate the operation of the simulated weapon systems 68. Smoke generator controls 66 are a set of control devices, such as switches, push-buttons and the like, that enable the operating crew of the of the aerial vehicle to activate, to maintain and to terminate the operation of the smoke generator device 70. The function of the smoke generator device 70 is to provide enhanced visual signaling to the operating crews of diverse aerial, ground-based or sea-based platform that either operate in a co-operative manner with the aerial vehicle performing the signaling or are engaged in active combat against the aerial vehicle performing the signaling. Still referring to Fig. 2, during a simulated aerial engagement or a simulated air-to-air combat consequent to the appropriate information collected by the weapon systems sensors 56, relayed to the weapon systems and aerodynamics displays complex 64, and displayed to the operating crew of the aircraft, a simulated weapon systems 68 is activated via the manipulation of the simulated weapon systems controls 62 by the operating crew. Optionally and substantially simultaneously, the smoke generator device 70 could be activated by the operating crew via the smoke generator controls 66. in order to indicate the activation of the simulated weapon system 68 the smoke generator device 70 emits smoke that provides for enhanced visual signaling to friendly or enemy combat platforms. Visual signaling effected by the activation of the smoke generator device 70 could be initiated consequent to various events taking place on the platform, such as attack-recognition events, emergency events, aerodynamic events, and the like. Referring now to Fig. 3 that illustrates in a highly schematic manner the environment in which the proposed apparatus and method operates, in accordance with the second preferred embodiment of the present invention. Combat space 72 contains a first aerial vehicle 102, a second aerial vehicle 74, a third aerial vehicle 90, a ground-based combat vehicle 100, and a sea-based combat vessel (not shown). The aerial vehicles 102, 74, 90 are fixed- wing military fighter aircraft engaged in an aircrew combat training exercise, more particularly in a simulated visual range air-to-air combat typically referred to as DGFT (dogfight) in order to improve and enhance the maneuvering, control and weapon system-handling capabilities of the aircrew operating the vehicles 102, 74, 90. It would be easily perceived that the first, second and third aerial vehicles 102, 74, 90, respectively, could be other types of aircraft, such as attack aircraft, bomber aircraft, rotating-wing aircraft, Unmanned Aerial Vehicles (UAVs), unmanned combat aerial vehicles (UCAVs), trainer aircraft, and the like. In the framework of the training practice the aircraft 102, 74, 90 could be engaged in a ground attack on ground-based vehicle 100 or could manage defensive maneuvering against ground-to-air attacks by ground-based vehicle 100. In such a case the combat exercise could be operative in the anti-aircraft crew of the ground-based vehicle 100. First aircraft 102, second aircraft 74 and third aircraft 90 are equipped with simulated weapon systems 106, 78, 94, respectively. The simulated weapon systems could include, for example, the targeting, sighting and tracking elements of an aerial gun system. The gun system is operating in a simulation mode in which the signal generated by the gun-activating elements, such as the gun trigger, are not sent to the actual gun units in order to effect the firing of the guns but are routed via an internal data bus to a smoke generator system 110, 82, 98, respectively, after being suitably processed by an on-board mission computer 108, 80, 96 and optionally by smoke generator controllers (not shown) associated with smoke generator system 110, 82, 98 . The simulated weapon systems could include the targeting, sighting and tracking elements of an air-to-air missile system. The simulated missile system further includes a practice missile that could include a targeting sub-system but is not equipped with a missile motor, a warhead or flight controls. The missile system is operating in a simulation mode in which the signal generated by the missile-activating elements, such as the missile-launch switch, are not used for the activation of the missile engine units in order to effect the launching of the missile but are routed via an internal data bus to the smoke generator system 110, 82, 98 after being suitably processed by an onboard mission computer 108, 80, 96 and optionally by a smoke generator controller. The simulated weapon systems 106, 78, 94 could further include a simulated countermeasure system, such as an IR flare launching system, and the like. First aircraft 102, second aircraft 74, and third aircraft, 90 further include a smoke generator system 110, 82, 98, respectively. The smoke generator systems 110, 82, 98 are housed in a smoke generator housing, such as an upgraded or newly developed smoke pod uploaded externally on the aircraft 102, 74, 90. The systems 110, 82, 98 could be housed in the practice missile, in a converted external fuel tank, or the like Still referring to Fig. 3, in the context of an aircrew training exercise first aircraft 102 and third aircraft 90 are co-operatively engaged in a simulated close range air combat against second aircraft 74. First aircraft 102 is located in the combat space 72 such that it is provided with the option of realizing a threat 88 against second aircraft 74. First aircraft 102 activates simulated weapon systems 106 in order to simulate a threat 88 against second aircraft 74. The simulated weapon is an air-to-air missile. Consequent to the activation of the weapon by the operating crew the launch command is routed to the mission computer 108. The mission computer 108 activates simulated weapon system 106 and the smoke generator system 110. The smoke generator is activated and smoke signaling 112 is emitted from the smoke generator housing in order to provide external visually enhanced indication of the missile launch. The smoke signaling 112 continues as long as the duration of the pre-determined missile engine "burn" of the simulated missile or as long as the duration of the time of flight (TOF). If it determined by calculations performed by the suitable software of the mission computer 108 that the simulated missile "impacted" on the second aircraft 74 prior to the termination of the TOF period or to the termination of the engine "burn" period then the smoke signaling 112 terminates. The smoke signaling 112 is a reasonable emulation of the smoke-trail typically emitted by^' the engine of a real missile. The smoke signaling 112 provides a strong visual indication of the missile launch and missile flight to the aircrews of first aircraft 102, second aircraft 74, and third aircraft 90. The indication of the on-going simulated missile attack by the smoke signaling 112 further provides the crew of the second aircraft 74 with the option of responding to the attack by performing suitable defensive maneuvering as well as by activating simulated countermeasures 86. The crew of second aircraft 74 activates the IR flare system in the simulated weapon system 78. The commands generated by the control elements operative in the launching of the IR flares are routed to the on-board mission computer 80 that generates and relays a suitable command to the smoke generator system 82. The system 82 activates the smoke generator that will perform smoke signaling 84. The signaling 84 will comprise of distinct bursts of smoke such as to emulate the characteristic flashes accompanying the launching of operative IR flares. Consequent of the termination of the attack 88 the probability of the simulated warhead impact on the second aircraft 74 is calculated by the mission computer 108 of the first aircraft 102 utilizing specific analysis, aircraft characteristics, flight data, weapon characteristics and the relative locations of the opposing aircraft 74. Note should be taken that the following scenario is exemplary only. First aircraft 102 could utilize other simulated weapon systems, such as an aerial gun. Second aircraft 74 could manage a simulated attack while first aircraft 102 could be engaged in defensive maneuvers and actions. In addition, the simulated engagement could take place between one or more aircraft in the combat place and ground-based vehicle 100 equipped substantially with the same type of apparatus and operating substantially the same method. Referring now to Fig. 4 that illustrates the operative components installed in an exemplary aerial vehicle that are pertinent to the operation of the apparatus and method in accordance with the second preferred embodiment of the present invention. The components include a data bus 114, a mission computer

116, a smoke generator device 118, a set of weapon system sensors 120, an aircrew display terminal 122, aerodynamic sensors 124, and a smoke generator controller device 126. Data bus 114 is a signal transmission path across the aerial vehicle on which diverse signals are dropped off or picked up at every device attached to the line. A unique identity is assigned to each device and each signal. Typically a device is allocated an address while the destination of the signal is embedded in a specific signal header. Thus, a device attached to the data bus 114 can recognize those signals intended for it and ignore those signals that are intended for other devices. Mission computer 116 is a computing device that accepts information in the form of digitalized data and manipulates the data for some result based on a program or sequence of instructions on how the data is to be processed. Mission computer 116 also includes the means for storing data and programs for some necessary duration. Mission computer 116 is responsible for controlling the computerized components of the aerial vehicle. In the context of the present invention, for example, the mission computer 116 receives sensor signals from weapon system sensors 120, from aerodynamic sensors 124, processes the weapon sensor data and the aerodynamic sensor data in accordance with pre-defined rules embedded in one or more of the stored computer programs, generates command signals for the smoke generator device 118 and feeds the data bus 114 with the generated command signals in order to be sent to the smoke generator device 118. Smoke generator device 118 is responsible for the generation and the emission of smoke for a period determined by the software and control tables implemented in mission computer 116. Typically, the smoke generator device 118 is controlled by the mission computer 116 consequent to the processing of sensor signals and the generation of command signals by the mission computer 116. Smoke generator device 118 could also be controlled by a specific smoke generator controller 126. The smoke generator controller 126 is typically a stand-alone micro-processor that receives sensor signals directly from the data bus 114, processes the sensor signals and generates appropriate command signal for controlling the smoke generator device 118. Note .should be taken that the smoke generator device could be controlled by manual commands introduced by the crew of the aircraft as it was described herein above in association with the first preferred embodiment of the invention. The mission computer 116 and/or the smoke generator controller 126 could optionally handle the manual commands in a suitable manner, such as for example, enabling the crew to determine the timing of the smoke generation, and the like. Weapon system sensors 120 are a set of devices operative in sensing the status of the diverse weapon systems installed in the vehicle. For example, a critical sensor of the aerial gun system is associated with the activation of the gun trigger. The gun trigger is basically an electric push button that generates a specific signal when pressed. When the crew of the aerial vehicle activates the gun trigger a weapon sensor signal indicating the activation of one or more guns is transmitted through the data bus 114 to the mission computer 116. In accordance with the mode of the operation the signal is processed by the computer 116 that generate a control signal either functional in the operative firing of the one or more guns or in the controlling of the smoke generation device 118. Still referring to Fig. 4 aerodynamic sensors 124 are a set of sensor devices operative in sensing the status of the aerodynamic control surfaces. Sensors 124 provide useful information to the operating crew and to the mission computer regarding the extent of the aerodynamic forces acting on platform by suitable display formats. For example, a critical aerodynamic sensor display 124 is the altimeter. The successively sampled value representing the altitude of the aerial vehicle generates periodically a sensor signal. The value signal is relayed to the mission computer 116 via the data bus 114. The computer 116 processes the signal in such a manner as to compare the altitude value embedded in the signal against a set of pre-determined altitude limits. In accordance with the result of the comparison the computer 116 could generate a control signal that will be addressed to the smoke generation device 118 (or the smoke generator controller device 126) for the purpose of smoke generation and smoke emission control. Aircrew terminal displays 122 are one or more display screens on which flight- specific, platform-specific and weapon-system status-specific information is displayed. For example, the simulated launching of a missile could be basically indicated by a simple graphical indicator. Optionally a curve representing the Line of Sight (LOS) of the simulated missile could be shown. Furthermore critical events, such as for example a missile hit on a targeted aircraft could also displayed. The terminal displays 122 are responsible for the display of various weapon sensor data and aerodynamic sensor data. Critical indications, warnings and emergency states are also displayed in a suitably impressive manner. Note should be taken that above-described configuration is exemplary only. In other embodiments of the present invention more than one mission computer 116 could be installed either for purposes of emergency backup, replication of functions, load sharing or for application-specific partitioning. Thus, there could be installed on the aerial vehicle a set of discrete computing devices connected to the data bus 114, such as a fire control computer, a navigational computer, a platform control computer, and the like. Note should be taken that smoke signaling could be activated in response to the occurrence of specific on-board events, such as the recognition of an urgent external threat, emergency situations, and the like. Referring now to Fig. 5 that illustrates in a highly schematic manner the environment in which the proposed apparatus and method could operate, in accordance with the third preferred embodiment of the present invention. Combat space 128 contains a first aerial vehicle 158, a second aerial vehicle 130, a third aerial vehicle 146, a ground-based combat vehicle 172, and a sea-based combat vessel (not shown). The aerial vehicles 158, 130, 146 are fixed-wing military fighter aircraft engaged in an aircrew combat training exercise, more particularly in a simulated visual range air-to-air combat typically referred to as DGFT (dogfight) in order to improve and enhance the maneuvering, control and weapon system-handling capabilities of the aircrew operating the vehicles 158, 130, 146..

It would be easily perceived that the first, second and third aerial vehicles 158,

130, 146 respectively, could be other types of aircraft, such as attack aircraft, bomber aircraft, rotating-wing aircraft, Unmanned Aerial Vehicles (UAVs), unmanned combat aerial vehicles (UCAVs), trainer aircraft, and the like. In the framework of the training practice the aircraft 158, 130, 146 could be engaged in a ground attack on ground-based vehicle 172 or could manage defensive maneuvering against ground-to-air attacks by ground-based vehicle 172. In such a case the combat exercise could be operative in the anti-aircraft crew of the ground-based vehicle 172. The first aircraft 158, second aircraft 130 and the third aircraft 146 are equipped with simulated weapon systems 164, 134, 152, respectively. The simulated weapon systems could include the targeting, sighting and tracking elements of an aerial gun system. The gun system is operating in a simulation mode in which the signal generated by the gun-activating elements, such as the gun trigger, are not sent to the actual gun units in order to effect the firing of the guns but are routed via an internal data bus to a smoke generator system 168, 138, 156 after being suitably processed by an on-board mission computer 166, 136, 154 and optionally by a smoke generator controller (not shown). The simulated weapon systems could include the targeting, sighting and tracking elements of an air-to-air missile system. The simulated missile system further includes a practice missile that could include a targeting sub-system but is not equipped with a missile motor, a warhead or flight controls. The missile system is operating in a simulation mode in which the signal generated by the missile-activating elements, such as the missile-launch switch, are not used for the activation of the missile engine units in order to effect the launching of the missile but are routed via an internal data bus to the smoke generator system 168, 138, 156 after being suitably processed by an on-board mission computer 166, 136, 154 and optionally by a smoke generator controller. The simulated weapon systems 164, 134, 152 could further include a simulated countermeasure system, such as an IR flare launching system, and the like. First aircraft 158, second aircraft 130, and third aircraft 146 further include a smoke generator system 168,

138, and 156, respectively. The smoke generator systems 168, 138, 156 are housed in a smoke generator housing, such as an upgraded or newly developed smoke pod uploaded externally on the aircraft 158, 130, 146. The systems 168,

138, 156 could be housed in the practice missile, in a converted external fuel tank, or the like. First aircraft 158, second aircraft 130, and third aircraft 146 include a data link control system 162, 140, 148, respectively. The responsibility of the data link control systems 162, 140, 148 is establish and control data communications between first aircraft 158, second aircraft 130, third aircraft 146 and optionally ground-based vehicle 172 On the drawing under discussion first aircraft 158 and second aircraft 130 are communicatively linked by data link channel 172, first aircraft 158 and third aircraft 146 are communicatively connected by data link channel 180, third aircraft 146 and second aircraft 130 are connected by data link channel 144. In addition first aircraft 158 and ground-based vehicle 172 are connected by data link channel 174 and third aircraft 130 and ground-based vehicle 172 are connected by data link channel 176. The data link channels 172, 174, 176, 178, 180, 182 allow for high-speed, secure, two-way transmission of data between the aircrafts 158, 130, 146 and optionally the ground-based vehicle 172 in the combat space 128. Still referring to Fig. 5 in the context of the aircrew training exercise first aircraft 158 and third aircraft 146 are co-operatively engaged in a simulated close range air combat against second aircraft 130. First aircraft 158 is in a suitable position to realize a threat 160 against second aircraft 130. First aircraft 158 activates simulated weapon systems 164 in order to simulate a threat 160 against second aircraft 130. The simulated weapon is an air-to-air missile. Consequent to the activation of the weapon by the operating crew the launch command is routed to the smoke generator system 168 via mission computer 166. The smoke generator is activated and smoke signaling 170 is emitted from the smoke generator housing in order to provide external visually enhanced indication of the missile launch. The smoke signaling 170 continues as long as the duration of the pre-determined missile engine "burn" of the simulated missile or as long as the duration of the time of flight (TOF). If the simulated missile will "impact" on the second aircraft 10 prior to the termination of the TOF period or to the termination of the engine "burn" period then the smoke signaling 26 will cease.

The smoke signaling 170 is a reasonable emulation of the smoke-trail typically emitted by the engine of a real missile. Thus, the smoke signaling 170 provides a strong visual indication of the missile launch and missile flight to the aircrews of first aircraft 158, second aircraft 130, and third aircraft 146. The indication of the on-going simulated missile attack by the smoke signaling 170 further provides the crew of the second aircraft 130 with the option of responding to the attack by performing suitable defensive maneuvering as well as by activating simulated countermeasures 144. The crew of second aircraft 130 activates the IR flare system in the simulated weapon system 134. The commands generated by the control elements operative in the launching of the IR flares are routed to the smoke generator system 138 via the mission computer 136. The system 138 activates the smoke generator that will perform smoke signaling 142. The signaling 142 will comprise of distinct bursts of smoke such as to emulate the characteristic flashes accompanying the launching of operative IR flares. Consequent of the termination of the attack 160 the probability of the simulated warhead impact on the second aircraft 130 is calculated by the mission computer of the first aircraft 158 utilizing specific analysis, aircraft characteristics, flight data, weapon characteristics and the relative locations of the opposing aircraft 158, 130. If the first aircraft 158 and the second aircraft 130 are equipped with a tactical data link then in accordance with the results of the probability calculation either a "no-hit" indicator message or a "hit" indicator message is transmitted by the data link control system 162 via the data link communication channel 172 from the first aircraft 158 to the second aircraft 130. If the second aircraft 130 receives a "hit" indicator message by the data link control system 140 the message is processed such as to create a smoke generator activation command. The command is routed to the smoke generator system 138 in order to activate the device and effect the emission of a smoke signaling 142 that will indicate visually to the aircraft 158, 146 in the combat space 128 than a successful "hit" was accomplished. Note should be taken that the following scenario is exemplary only.

The first aircraft 158 could utilize other simulated weapon systems, such as an aerial gun. The second aircraft 130 could manage a simulated attack while the first aircraft 158 could be engaged in defensive maneuvers and actions. In addition, the simulated engagement could take place between one or more aircraft in the combat place and the ground-based vehicle 172 equipped substantially with the same type of apparatus and operating substantially the same method. Note should be taken that the above described exemplary engagement and the associated scenario regarding the utilization of the proposed apparatus and method involves the usage of data from both platforms. The first platform initiates an attack against the second platform. As a result, the simulation of the attacking missile launch and the simulation of the missile flight are performed on the first platform. The simulation of the anti-missile defense (simulated launch of IR countermeasures in combination with engine power reduction) is performed on the second platform. The summing of the attack/defense information collected from both platforms is performed typically in the mission computer of the attacking platform. The mission computer of the first platform is enabled to determine a "hit" and consequently enabled to send a suitable signal to the second platform to effect smoke signaling on the second platform that indicates a "hit" on the second platform. Referring now to Fig. 6 that illustrates the operative components installed in an exemplary aerial vehicle that are pertinent to the operation of the apparatus and method in accordance with the third preferred embodiment of the present invention. The components include a data bus 174, a mission computer 176, a data link transmitter/receiver device 178, a smoke generator device 180, a set of weapon system sensors 182, an aircrew display terminal 184 a set of aerodynamic sensors 186, and a smoke generator controller device 188. Data bus 174 is a signal transmission path across the aerial vehicle on which diverse signals are dropped off or picked up at every device attached to the line. A unique identity is assigned to each device and each signal. Typically a device is allocated an address while the destination of the signal is embedded in a specific signal header.

Thus, a device attached to the data bus 174 can recognize those signals intended for it and ignore those signals that are intended for other devices. Mission computer 176 is a computing device that accepts information in the form of digitalized data and manipulates the data for some result based on a program or sequence of instructions on how the data is to be processed. Mission computer 176 also includes the means for storing data (including the program, which is also a form of data) for some necessary duration. Mission computer 176 is responsible for controlling the computerized components of the aerial vehicle. In the context of the present invention, for example, the mission computer 176 receives sensor signals from a weapon system sensor 182, from an aerodynamic sensor 186, processes the weapon sensor data and the aerodynamic sensor data in accordance with pre-defined rules embedded in one or more of the stored programs, generates command signals for the smoke generator device 180 and feeds the data bus 1740 with the command signals in order to be sent to the smoke generator device. Data link transmitter/receiver 178 is a transceiver device that is a combination transmitter/receiver in a single package. Device 178 is responsible for the transmission of the appropriate signals via the data link to other vehicles and for the reception of the signals communicated from other vehicles via the data link. Thus, for example, a command signal generated in the mission computer 176 for communication to another device is formatted such as to be recognized by the device 178 as data for transmission. The signal is then transmitted via the link to an address representing another vehicle. The signals received by the device 178 are typically routed to the mission computer 176for decoding and processing. If, for example, "hit" indication data is received then mission computer 176 will generate and format a command signal intended to smoke generator device 180 and will feed the command to the data bus 174. Smoke generator device 180 is responsible for the generation and the emission of smoke for a pre-determined period. Typically the smoke generator device 180 is controlled by the mission computer 176 consequent to the processing of sensor signals and the generation of command signals by the mission computer 176. Smoke generator device 180 could also be controlled by a specific smoke generator controller 188. The smoke generator controller 188 is typically a stand-alone micro-processor that receives sensor signals directly from the data bus 174, processes the sensor signals and generates appropriate command signal for controlling the smoke generator device. Note should be taken that the smoke generator device 180 could be controlled by manual commands introduced by the crew of the aircraft. The mission computer 176 and/or the smoke generator controller 188 will handle the manual commands in a suitable manner, such as for example, enabling the crew to determine the timing of the smoke generation, and the like. Weapon system sensors 182 are a set of devices operative in sensing the status of the diverse weapon systems installed in the vehicle. For example, a critical sensor of the aerial gun system is the gun trigger. The gun trigger is basically an electric push button that generates a specific signal when pressed. When the crew of the aerial vehicle activates the gun trigger a weapon sensor signal indicating the activation of one or more guns is transmitted through the data bus 174 to the mission computer 176. In accordance with the mode of the operation the signal is processed by the computer 176 that generate a control signal either functional in the operative firing of the one or more guns or in the controlling of the smoke generator device 180. Still referring to Fig. 6 aerodynamic sensors 186 are a set of devices operative in sensing the status of the aerodynamic control surfaces. Sensors 186 further sense the extent of the aerodynamic forces acting on platform via the reading of measuring devices. For example, a critical aerodynamic sensor 186 is the altimeter. The successively sampled value representing the altitude of the aerial vehicle generates periodically a sensor signal. The value signal is relayed to the mission computer 176 via the data bus 174. The computer 176 processes the signal in such a manner as to compare the altitude value embedded in the signal against a set of pre-determined altitude limits. In accordance with the result of the comparison the computer 176 could generate a control .signal that will be addressed to the smoke generation device 180 (or the smoke generator controller device 188) for the purpose of smoke generation and smoke emission control. Aircrew terminal displays 184 are one or more display screens on which flight- specific, platform-specific and weapon-system status-specific information is displayed. For example, the simulated launching of a missile could be basically indicated by a simple graphical indicator. Optionally a curve representing the virtual flight path of the simulated missile could be shown. Furthermore, specific events, such as for example a missile hit on a targeted aircraft are also displayed. The terminal displays 184 are responsible for the display of various weapon sensor data and aerodynamic sensor data. Critical indications, warnings and emergency states are also displayed in a suitably impressive manner. Note should be taken that above-described configuration is exemplary only. In other embodiments of the present invention more than one mission computer 176 could be installed either for purposes of emergency backup, replication of functions, load sharing or for application-specific partitioning. Thus, there could be installed on the aerial vehicle a set of discrete computing devices connected to the data bus 174 such as a fire control computer, a navigational computer, a platform control computer, and the like. Referring now to Fig. 7, in accordance with the preferred embodiments of the invention, a smoke pod 198 is typically uploaded on an external weapon station located on the underside of the wings or the aircraft body. The smoke pod 198 could be a newly developed device or could be upgraded suitably from an existing smoke pod, such as for example, the Smokewinder smoke pod, developed and manufactured by the Sanders Aircraft Corporation. The smoke pod 198 is linked to the platform data bus 190 via a wired line through a pylon, a suitable connector port, and a suitable signal line in the interior of the aircraft. The pod 198 could be linked to the platform data bus 190 in a wireless manner through the utilization of short range wireless technologies, such as for example Bluetooth, Wi-Fi, and the like. The data bus 190 carries a plurality of signals among diverse device and components in the aircraft. Each signal is assigned a specific identifier in order for the addressed device and/or component to recognize the signal, such as a signal to be processed by the device. The signal addressed to the smoke pod could be raw signals generated as a result of some event or could be signaling command processed by the mission computer. Where the smoke pod 198 does not include an active smoke generator controller device 200 the signals are pre- processed by the mission computer and delivered to the smoke pod 198 as formatted smoke generation commands with the appropriate execution parameters already inserted. In contrast, if the smoke pod 198 includes an active smoke generator controller device 200 then the event-specific raw signals are transmitted directly to the smoke pod 198 and processed by the smoke generator controller in order to format the signals and determine the suitable parameters. Thus, the smoke pod recognizes and processes several smoke-generation-specific signals or commands; a manual signaling signal/command 192, a local signaling signal/command 194, and a remote signaling signal/command 196. The signals 192, 194, 196 are relayed to the smoke generator controller 200. The controller 200 is a microprocessor with built-in software modules. The software processes the incoming signals and according to the type of the signal generates smoke generation-specific commands, such "activate smoke generator for 5 seconds", and the like. The commands are operative in the activation of the valve control unit 202 that enables flow of a chemical mixture from the chemical mixture container 208 through the chemical mixture/smoke conduit 204. The operation of the smoke generator 206 effects the transformation of the chemical mixture into smoke. As long as the valve is open smoke is generated in the conduit 204 and emitted from the smoke pod 198 via a specific pipe into the trailing airflow. The controller 200 provides feedback signals to the platform data bus 190 in order to indicate the status of the smoke generator to the crew of the aircraft. Referring now to Fig. 8 in the second and third preferred embodiments of the present invention the mission computer 212 is responsible for controlling the operation of the smoke pod. The mission computer 212 is a high-speed computing unit, such as an advanced microprocessor, installed on-board of an aerial vehicle and provided with appropriate communication capabilities. The mission computer 212 is connected to the data bus 210. In the second and third preferred embodiments of the invention, the computer 212 comprises a processor device 216 to perform calculations, a Digital Signal Processor (DSP) device 218 to handle and process electronic signals, a sound device 220 to generate sound output and receive sound input, an I/O device 222 to operate in conjunction with the various input/output devices such as reading from a device, writing to a device, and the like, and a storage device 224 to store permanently or temporarily the various data structures, such as application software programs, utilities, operating systems, data tables, and the like,. The storage device 224 is responsible for the storage of the software systems and the associated data structures. Device 224 stores an operating system 226, an I/O handler 228, a database handler 232, a Mission, Platform Configuration and Weapon Systems Parameters (MPCWSP) Database 234 and an Enhanced External Visual Signaling (EEVS) application 234. In the In the third preferred embodiment of the invention the mission computer 212 further comprises a communication device 214 to open, maintain, and handle communication channels among the various aerial vehicles in the combat space.. In addition, in the third preferred embodiment of the invention, the storage device 224 a data bus control system 230. Referring now to Fig. 9, in the second and third preferred embodiment of the present invention, the Mission, Platform Configuration and Weapon Systems Parameters (MPCWSP) database 240 is a data structure that stores important information concerning the aerial vehicle. The information could be utilized by the EEVS application 236 of Fig. 8. The information regards operational parameters, such as the characteristics of the current mission (training mission, combat mission, air-to-air, air-to-ground), the configuration data of the aerial platform (external configuration, fuel load, type of operative weapon systems, and the characteristics of the on-board weapon systems. The MPCWSP database 240 comprises several tables storing functional data. The tables include a mission parameters table 242, a local platform characteristics table 246, a local aircraft configuration table 244, a local weapon system characteristics table 250, a remote platform characteristics table 254, a remote weapon systems characteristics table 258, a combat constraints table 240, a n EEVS apparatus configuration table 252, and a user preferences table 256. Referring now to Fig. 10, in the second and third preferred embodiment of the present invention the EEVS application 260 is a functionally linked set of computer programs operative in the execution of the proposed method. The EEVS application 260 is installed on the storage device 224 of the mission computer 212 of Fig. 8. Alternatively, the EEVS application 260 could be installed on the storage device of the smoke generator controller located in the smoke pod housing the smoke generator system. Alternatively, some of the programs constituting the EEVS application 260 could be implemented in the mission computer while other programs could be implemented in the smoke generator controller 200 of Fig. 7. The EEVS application 260 comprises am application control module or main logic module 262, a database interface module 264, a parameters processor module 268, a platform and systems status monitor 268, a situation analyzer module 272, a local signaling command builder 270, , a response selector module 276, an event processor module 280, and a user interface module 278. In addition, in the third preferred embodiment of the present invention, the EEVS application 260 further includes a remote signaling command builder 274. Referring now to Fig. 11 at step 282 the targeting system of a practice missile uploaded on an attacking aircraft participating in an aerial combat exercise is locked on a targeted aircraft. The lock-on-target event is suitably communicated to the operating crew of the attacking aircraft, such as utilized a graphical display on the sighting device. As a result, the operating crew of the attacking aircraft performs a simulated missile launch at step 284 by the activation of a specific activation device, such as a missile launch push bottom. An electrical signal is generated signifying a simulated missile launch. The signal is sent via the platform data bus to the mission computer. At step 286 the EEVS application is activated in the mission computer. The database interface module extracts the operative characteristics of the missile, such as missile engine burn duration or time of flight (TOF) of the missile, from the host weapon systems characteristics table 250 in the MPCWSP database 240 in Fig. 9and the missile flight duration is computed. Subsequently the local signaling command builder 270 of EEVS application 260 of Fig. 10 generates smoke generation commands and transmits the command with the suitable parameters to the smoke pod. At step 288 the smoke activation command fires the smoke generator system in the smoke pod uploaded on the on the attacker aircraft in order to provide for enhanced external visual signaling indicating "missile-in-flight". The parameters embedded in the smoke-activation command effect the generation and the emission of smoke for a period reflected either by the missile engine burn duration parameter or by the time of flight parameter or until the situation analyzer module determines that a simulated warhead impact/detonation was achieved on the targeted aircraft (step 290). Thus, smoke generation and therefore smoke emission is terminated either at the end of the missile engine burn period or at the end of the sustainable missile flight period or at that point in time where the situation analyzer module 272 of Fig. 10 determines the occurrence of an emulated warhead impact/detonation on the targeted aircraft (step 292). At each stage of the simulated flight of the missile the situation analysis module of the EEVS application is successively calculates the probability of the hit by constantly comparing the course and location of the targeted aircraft with the theoretical trajectory and the virtual location of the simulated missile (step 294). The successive locations of the targeted aircraft are typically received via GPS. If both attacker aircraft and targeted aircraft are equipped with a tactical data link then at step 296 the response selector module 276 of Fig. 10 determines that according to the situation analyzer module a hit was achieved on the targeted aircraft. In the third preferred embodiment of the present invention, the response selector module 276 instructs. the remote signaling command builder 274 to generate a remote hit indication command. The remote signaling command is transmitted via a data link communication channel to the targeted aircraft. The command is received by the command processor 280 of the

EEVS application 260 implemented on the targeted aircraft. The processed hit indicator command effects the generation of a local signaling command by the local signaling command builder 270. The command is transmitted via the platform data link to the smoke generator device enclosed in the smoke pod uploaded on the targeted aircraft. At step 300 the hit indicator command activates the smoke generation system in the smoke pod and effects the emission of smoke to provide enhanced external visual signaling indicating "missile hit". Note should be taken that indications of the missile hit event are communicated to the crew of the attacker aircraft as well as the crew of the targeted aircraft via the user interface module 278 of Fig. 10. The event is suitably displayed on the display devices of the crews on both aircraft. In the second preferred embodiment of the invention where the aircrafts are not equipped with a tactical data link system then the crew of the attacker aircraft transmits a verbal message regarding the accomplishment of a "missile hit" via a voice radio channel to the crew of the targeted aircraft. As a result, the crew of the targeted aircraft could activate manually the smoke generator uploaded in the smoke pod on the attacker aircraft in order to generate smoke signal is a pre-defined manner. In other preferred embodiments of the present invention the enhanced visual signaling system installed in an externally mounted pod could be controlled in a wireless manner from the carrier platform. For example, the relevant events that are taking place on-board of the carrier vehicle, such as an airborne fighter aircraft, a sea-based military vessel or diverse ground-based equipment, which is equipped with a signaling system pod including a standalone signaling controller, could be communicated to the controller via a short-range radio link. Thus, the activation of a specific triggering device could be suitably communicated to the independent signaling controller via, for example, existing wireless technologies, such as Bluetooth, Wi-Fi, and the like. Alternatively, the signaling system could be controlled from a remote off-platform system where the operational commands could be communicated to the signaling system via a data link system, a satellite communication link, and the like. Remote signaling commands/signals could be generated by a mission computer on a combat platform consequent to the occurrence of pre-defined events that are non-related to the operation of the weapon systems. For example, smoke signaling commands/signals generated by the mission computer as a result of a pre-defined platform attitude, altitude, velocity and the like, could be communicated to remote platforms via the data link channel for the generation of remotely controlled enhanced visual signaling. In yet other preferred embodiments of the invention, the control of the smoke signaling operations is controlled by a remote computing device storing the suitable EEVS application and the associated MPCWSP database. The sensor signals indicative of on-board events are sent from the combat platform directly to the remote computing device via data link channels. The remote computing device receives the sensor signals and in accordance with the received signals performs the required signal processing, situation analysis, calculations, signaling command/signal generation, and signal transmission. Thus, the smoke signaling commands/signals are relayed back to the sending combat platform for the activation of the smoke generation device on the combat platform. It will be appreciated by persons skilled in the art that the present invention is not limited to what has been particularly shown and described hereinabove. Rather the scope of the present invention is defined only by the claims, which follow.

Claims

CLAIMS I/WE CLAIM:

1. An apparatus for enhanced external visual signaling associated with a combat platform, the apparatus comprising the elements of: a smoke generator device enclosed in a smoke generator housing, the smoke generator housing connected externally to and carried externally by a combat platform; and a smoke generator controller device to activate, to terminate and to control the operations of the smoke generator device, the smoke generator controller device operating as a response to the sensing of pre-defined events occurring on the combat platform or on one or more remote combat platforms.

2. The apparatus of claim 1 further comprises a data link control system to provide data communication among two or more remote combat platforms for transmitting and receiving remote signaling commands among the platforms.

3 The apparatus of claim 1 wherein the smoke generator controller device comprises the elements of: an enhanced external visual signaling application comprising a group of logically interconnected computer routines to process event indications in response to events occurring on the combat platform and to relay the results of the processing to the smoke generator device; and a mission platform configuration and weapon systems parameter database comprising a group of data structures representing the operational characteristics of the combat platform the associated weapon system-specific, communications system-specific and signaling apparatus-specific parameters.

4. The apparatus of claim 3 wherein the enhanced external visual signaling application comprises the elements of: an application control module to manage the loading and the timely execution of the application modules; a database interface module to access the data structures of the mission platform configuration and weapon systems parameter database, to retrieve the parameters associated with the platform event indicators; a parameter processor module to select the parameters required for processing in response to the event indicators, to receive the parameters from the database interface module and to process the parameters in association with the event indicators; a local signaling command builder to generate signaling commands on the combat platform in response to the event indicators and the processed parameters; a remote signaling command builder to generate signaling commands to be communicated via the data link system to one or more remote combat platform; a situation analyzer module to determine automatic actions to perform in accordance to the event indicators, and the operational parameters and the generated signaling commands; a response selector module to determine a response to a analyzed situation; and an event processor module to process a complex event indicator and relay the processed complex event indicators to the response selector module.

5. The apparatus of claim 4 wherein the enhanced external visual signaling application further includes a user interface module to receive manual user commands and to display event indicators and signaling commands for user monitoring.

6. The apparatus of claim 2 wherein the mission platform configuration and weapon systems parameter database comprises the elements of: a mission parameters table to hold mission-specific information; a local combat platform characteristics table for holding parameters that define the apparatus-relevant characteristics of the local combat platform; a local combat platform weapon systems characteristics table to hold the list and operating parameters of the weapon systems; a remote combat platform characteristics table to store parameters that define the characteristics of a remote combat platform; a remote combat platform weapon systems characteristics table to hold the list and operating parameters of the weapon systems; an application configuration table to hold parameters that define the operational configuration of the application; a user preferences table to store data concerning the preferences of a user concerning the operations of the application; a combat operations constraints table to hold information that defines the allowed operational limits of the combat platform.

7. The apparatus of claim 6 further comprises a local combat platform configuration table to hold platform configuration parameters; and a remote combat platform configuration table to hold platform configuration parameters.

8. The apparatus of claim 1 wherein the combat platform is an aerial vehicle.

9. The apparatus of claim 8 wherein the aerial vehicle is a fighter aircraft.

10. The apparatus of claim 9 wherein the aerial vehicle is a trainer aircraft.

11. The apparatus of claim 10 wherein the aerial vehicle is an unmanned combat aerial vehicle.

12. The apparatus of claim 1 wherein the combat platform is a ground vehicle.

13. The apparatus of claim 12 wherein the ground vehicle is associated with an anti-aircraft missile battery.

14. The apparatus of claim 1 wherein the combat platform is a sea-based combat vessel.

15. The apparatus of claim 1 wherein the smoke generator controller is a computing device on-board of the local combat vehicle.

16. The apparatus of claim 15 wherein the smoke generator controller is a microprocessor installed in the smoke generator housing.

17. The apparatus of claim 16 wherein the smoke generator controller device is a remote computing device installed on-board of a remote combat vehicle or installed on-board of a ground-based vehicle or installed on- board of a sea-based vessel, or installed in a ground-based command station, or installed on-board a space-based platform.

18. A method for enhanced external visual signaling associated with a combat platform, the method comprising the steps of: identifying an event indicator generated in response to the occurrence of an event associated with the operations of a combat platform; responding to the event by relaying the event indicator to an external enhanced visual signaling application designed for the processing of the event in association with the event-specific parameters; generating a local or remote signaling command in accordance with the results of the processing of the event indicator with association with the event-specific parameters; and communicating the local signaling command to a signaling device to provide for enhanced external visual signaling.

19. The method of claim 18 further comprises the steps of: communicating the remote signaling command to a communication device on the combat platform in order to transmit the remote signaling command via a wireless communication channel to a remote combat platform.

20. The method of claim 18 wherein the event is a local event generating automatically an event indicator originated directly as a result of the operation of the operating crew controlling the various sub-systems of the combat platform.

21. The method of claim 20 wherein the event is a remote event generating automatically an event indicator in response to the wireless reception of a remote signaling command transmitted from a remote combat platform.

22. The method of claim 21 wherein the event is a local event generated in response to a direct manual command introduced by the operating crew of the combat platform.

23. The method of claim 18 wherein the external enhanced visual signaling is performed through the activation and control of a smoke generator device installed on the combat platform and on the remote combat platform.

24. The method of claim 18 wherein the event indicator is generated by the activation of a simulated weapon system.

25. The method of claim 24 wherein the event indicator is generated by the activation of a simulated missile launching system.

26. The method of claim 25 wherein the event indicator is generated in response to the behavior of the combat platform.

27. The method of claim 26 wherein the event indicator is generated in response to attitude, altitude, or speed of the combat platform.

28. The method of claim 18 wherein the processing of the event indicator is continuous along a time axis until the alternative consequences of the event are completed. 29 The method of claim 18 wherein the continuous processing of the event indicator includes activation of the signaling for a pre-determined period, calculating the potential results of the event, and communicating the results of the calculations as remote commands to the remote combat platform. 30. The method of claim 18 wherein the combat platform is an aerial combat vehicle, i 31. The method of claim 18 wherein the aerial combat vehicle is a fighter aircraft. 32. The apparatus of claim 6 wherein the combat operations constraints table is updatable in real-time by the operating crew of the combat platform and by a remotely located control and command team.