Abstract: A guidance system for remote guidance of a remote platform(s) towards a target destination is disclosed. The guidance system includes a light module including a light source operable for beam to illuminating the remote platform, and a spatial light modulator (SLM) placed in the optical path of the light beam emitted from the light source. The guidance system includes a controller operable for obtaining data indicative of guidance information for navigating the remote platform towards the target destination. The controller operates the SLM to encode the guidance information in the light beam. The guidance information may be encoded in light pattern including at least one of the following: a spatial light pattern formed in a cross-section of the light beam, a temporal light pattern in the light beam, and a spatiotemporal light pattern.

Abstract: The presently disclosed subject matter includes a Ux V system simulator. According to some examples synthetic images are display on the display device, the synthetic images showing an artificial representation of an environment in which operation of a Ux V is being simulated, the images are shown as if viewed from a vantage point of an imaging payload located onboard the Ux V; the images are processed to extract thereform values of one or more graphic image parameters; responsive to a command issued with respect to the synthetic images, the extracted values are compared with respective predefined reference values; A simulation of the issued command is executed only if the comparison between the extracted values and respective reference values complies with at least one predefined condition, thereby increasing similarity between the operation of the simulator and the operation of the real UAV system being simulated.

Abstract: The presently disclosed subject matter is directed to devices for carrying and releasing stores from a vehicle, such as ejector racks for carrying and releasing a store with respect to an air vehicle.

Abstract: A fragmentation warhead is provided, capable of being mounted in a carrier vehicle, the warhead having a longitudinal axis. In at least one example the warhead includes a shell that extends along the longitudinal axis. The shell includes a fixed shell portion and a fragmentation portion, and defines therebetween a cavity for accommodating therein an explosive charge. The fragmentation portion includes at least one set of serially adjacent fragments in correspondingly serially contiguous relationship in the fragmentation portion and in generally helical relationship with respect to the longitudinal axis. A corresponding carrier vehicle and a corresponding missile are also provided.

Abstract: The presently disclosed subject matter includes a method, a system and a delay compensation unit configured for compensating a delay in communication between a sensing unit and a control unit. A succession of two or more captured images are received from the sensing unit; information indicative of command dynamics parameters are obtained from the control unit; based on the information and a respective transfer function which models the dynamics of the sensor module, the expected reaction of the sensor module to the command is determined; and information indicative of the reaction before the command is executed in the sensing unit can be provided.

Abstract: The presently disclosed subject matter includes a method and system configured for enabling using a high resolution imaging assembly for surveying large areas as well as for tracking objects within the surveyed area, notwithstanding the bandwidth limitation of the communication link.

Abstract: A refueling device for use in in-flight refueling operation between a tanker aircraft and a receiver aircraft includes a selectively steerable body and a controller. The selectively steerable body configured for being towed by a tanker aircraft via a fuel hose at least during in-flight refueling, and includes a boom member having a boom axis and configured to enable fuel to be transferred from the fuel hose to a receiver aircraft along the boom axis during the in-flight refueling operation. The controller is configured for selectively steering the body to an engagement enabling position spaced with respect to the receiver aircraft and for aligning the boom axis in an engagement enabling orientation at the spaced position, and for subsequently moving the boom member along the boom axis towards the receiver aircraft for enabling fuel communication therebetween.

Abstract: A method for controlling in-flight refueling of a receiver aircraft having a fuel receptacle, comprising: automatically steering a refueling device to an engagement enabling position, including: repeatedly determining a spatial disposition of the refueling device with respect to the receiver aircraft, the refueling device being capable of engaging and refueling the receiver aircraft via a boom member, when the device arrives to the engagement enabling position at which the boom member is in a predetermined spaced and spatial relationship with respect to the fuel receptacle of the receiver aircraft; repeatedly calculating steering commands based at least on the repeatedly determined spatial dispositions and characteristics of a spatial control system of the refueling device; sending the steering commands to the spatial control system; whereby at the engagement enabling position, the boom member of the refueling device is capable of engaging with the fuel receptacle to enable refueling of the receiver aircraft.

Abstract: A system and method for cooling an external surface of a heat conductive body heated by a heat source is provided. The system includes a tank containing an evaporation liquid, a conduit supplying the evaporation liquid to the external surface of the body, a controllable supply valve for regulating a flow rate of egress of the evaporation liquid from the tank, and a control unit for controlling operation of the supply valve. The control unit includes a temperature sensor producing a temperature sensor signal representative of the temperature of the body at the predetermined place; and a controller capable of generating control signals for controlling operation of the controllable supply valve to provide a pulsed supply of the evaporation liquid to the external surface of the body for obtaining a desired temperature decrease of the body.

Abstract: A control system configured to control a deceleration process of an air vehicle which comprises at least one tiltable propulsion unit, each of the at least one tiltable propulsion units is tiltable to provide a thrust whose direction is variable at least between a general vertical thrust vector direction and a general longitudinal thrust vector direction with respect to the air vehicle.

Abstract: A method of treatment of liquid including supplying liquid to be treated to at least one liquid treatment module having a liquid inlet, a permeate outlet and a brine outlet, monitoring liquid pressure within the at least one liquid treatment module and upon exceedance of a liquid pressure threshold in the at least one liquid treatment module, reducing the liquid pressure in the at least one liquid treatment module by performing at least one of the following functions: opening a liquid pressure reducing valve at the brine outlet, increasing a liquid volume output of a circulation pump which removes brine from the at least one liquid treatment module, equilibrating liquid pressures between a liquid pressure inside the at least one liquid treatment module and inside a liquid feed tank and opening a liquid pressure reducing valve at the liquid inlet.

Abstract: A variety of refueling devices, systems and methods are disclosed for use in in-flight refueling. In one example one such device is towed by a tanker aircraft via a fuel hose at least during in-flight refueling, and has a boom member with a boom axis. The boom member enables fuel to be transferred from the fuel hose to a receiver aircraft along the boom axis during in-flight refueling. The device maintains a desired non-zero angular disposition between the boom axis and a forward direction at least when the refueling device is towed by the tanker aircraft in the forward direction via the fuel hose.

Abstract: The presently disclosed subject matter includes a system and a graphical user interface configured to enable an Ux V operator (e.g. an APCS operator) to direct the Ux V to view a selected object from a desired viewing angle, notwithstanding the fact that the desired viewing angle of the object is not exposed in a displayed image.

Abstract: The presently disclosed subject matter includes a collision warning and avoidance system and method for detecting a collision risk between an interrogating aircraft and at least one interrogated aircraft. Signals received from the at least one interrogated aircraft or by the at least one interrogated aircraft and at least one other interrogating aircraft are used for determining various situation awareness data which is used for determining whether the interrogating aircraft is in a risk of collision. If indeed a collision risk exists a collision warning is generated, the collision warning including data indicative of at least an estimated location of the at least one interrogated aircraft.

Abstract: A variety of refueling devices, systems and methods are disclosed for use in in-flight refueling. In one example one such device is towed by a tanker aircraft via a fuel hose at least during in-flight refueling, and has a boom member with a boom axis. The boom member enables fuel to be transferred from the fuel hose to a receiver aircraft along the boom axis during in-flight refueling. The device maintains a desired non-zero angular disposition between the boom axis and a forward direction at least when the refueling device is towed by the tanker aircraft in the forward direction via the fuel hose.

Abstract: Methods are provided for operating an air vehicle, the air vehicle including fixed wings configured to provide mild stall characteristics including a post-stall regime, and a propulsion system capable of generating a controllable thrust, the thrust being variable at least between an idle thrust and a maximum thrust. During a landing maneuver, the air vehicle is caused to attain an angle of attack corresponding to said post-stall regime, and during the landing maneuver, there is concurrently generated a thrust level of said thrust greater than said idle thrust to provide a thrust vector having a thrust lift force component at landing. Corresponding control systems are also provided, and air vehicles including such control systems are also provided.

Abstract: A warhead assembly is provided for a projectile includes a forward module having a precursor warhead, and an aft module including a main warhead. The warhead assembly includes a deployment system for selectively deploying the warhead assembly from a retracted configuration to a deployed configuration, at predetermined conditions, to thereby provide a longitudinal displacement between the forward module and the aft module. The deployment system includes an expansion member accommodated between the forward module and the aft module, and configured for being longitudinally expanded under the predetermined conditions to thereby increase a longitudinal dimension of the expansion member and thereby urge the forward module and the aft module away from one another to provide said longitudinal displacement. A corresponding deployment system and projectile are also provided.