Israel Aerospace Industries or IAI is Israel's prime aerospace and aviation manufacturer, producing aerial systems for both military and civilian usage. It has 16,000 employees as of 2013. IAI is wholly owned by the government of Israel.In addition to local construction of fighter aircraft, IAI also designs and builds civil aircraft and performs local maintenance and reconfiguration of foreign-built military and civilian aircraft. In addition, the company works on a number of missile, avionics, and space-based systems.Although IAI's main focus is aviation and high-tech electronics, it also manufactures military systems for ground and naval forces. Many of these products are specially suited for the Israel Defense Forces needs, while others are also marketed to foreign militaries. Wikipedia.
Israel Aerospace Industries | Date: 2016-07-28
An add-on brake system includes a housing accommodating a linear actuator including: an electric motor having a rotor and a stator; a nut arrangement coupled to the rotor; a linear threaded plunger associated having a first end linearly protruding from one end of the arrangement and a second end linearly protruding from an opposite end thereof; an inboard brake pad coupled to the housing; and an outboard brake pad associated with the second end, oriented transverse to the plunger. The plunger has an initial unclamped position in which the second end protrudes to an extent n_(1 )from the other end of the arrangement, yielding a spacing S_(1 )between the inboard and outboard brake pads, and a final clamped position in which the second end protrudes to an extent n_(2)>n_(1 )from the other end of the arrangement, yielding a spacing S_(2)
Israel Aerospace Industries | Date: 2016-10-31
An inflatable dummy target comprising a chassis of inflatable ducts wrapped with a sheet. The chassis of inflatable ducts can include one or more ring shaped ducts and one or more elongate ducts. The chassis can include at least two ring shaped ducts interconnected by one or more elongate ducts. The dummy target can include several attached axi-symmetrical sections, each section have a chassis of inflatable ducts. Each section can be conical, frustoconical or cylindrical, thereby achieving a concave or convex dummy target geometry.
Israel Aerospace Industries | Date: 2017-02-01
Systems and methods are disclosed for providing a controlled temperature in a control volume. Such systems include a main chamber (defining the control volume), a mixing chamber and a gasflow source. The mixing chamber is in selective fluid communication with the main chamber, and has at least one mixing chamber inlet, and a ram air inlet for allowing ram airflow at a first temperature to be channeled into the mixing chamber. The gasflow source provides a source gasflow at a greater, second temperature to the mixing chamber. The mixing chamber provides the mixing chamber outflow at a third temperature by selectively allowing the ram airflow and the source gasflow in the mixing chamber to mix therein, or, by selectively allowing the ram airflow in the mixing chamber to flow to the main chamber (in absence of source gasflow). A controller is operative to provide a desired level for the third temperature.
Israel Aerospace Industries | Date: 2017-02-08
Images are processed to compensate for rolling shutter effects. A pair of images are registered. A set of pixel rows in the first image and a corresponding set of pixel rows in the second image are obtained. A parametric model is generated characterizing a transformation between pixels in the set of pixel rows in the first image with pixels in the corresponding set of pixel rows of the second image. Using the generated parametric model, the set of pixel rows in the second image is warped with respect to the set of pixel rows in the first image, reducing rolling shutter effects.
Israel Aerospace Industries | Date: 2017-03-08
A cover assembly is provided, for use with an instrument package having a common aperture. The cover assembly includes an inner cover member and an outer radome member. The inner cover member is substantially transparent to electromagnetic (EM) radiation of at least a first wavelength range. The outer radome member is configured for selectively and reversibly covering the inner cover member and transparent to EM radiation of at least a second wavelength range different from the first wavelength range. The second wavelength range includes a radio frequency (RF) wavelength range. The outer radome member is configured for being mounted in overlying relationship with respect to the common aperture of the instrument package. The outer radome member is configured for being initially in overlying relationship with respect to the inner cover member and for being selectively removed from the overlying relationship with respect to the inner cover member at least during flight conditions.
Israel Aerospace Industries | Date: 2017-03-15
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.
Israel Aerospace Industries | Date: 2016-11-22
A reaction control system (RCS) is provided for use with an air vehicle having a nose portion and a center of gravity aft of the nose portion. The RCS includes a belt element configured for selectively securing the RCS to the nose portion, and also includes a plurality of micro-rocket modules affixed to the belt element, each micro-rocket module being configured for being selectively activated to provide corresponding control moments to the air vehicle when secured to the nose portion thereof. A corresponding air vehicle, and a method for modifying an air vehicle, are also provided.
Israel Aerospace Industries | Date: 2017-01-04
A fin deployment system for a projectile is provided, the fin deployment system defining a longitudinal axis and including: an actuator plate, a first mechanical stop arrangement, an actuation assembly, a plurality of fin assemblies, and a second mechanical stop arrangement. The actuator plate is pivotable from a first pivot position to a second pivot position about the longitudinal axis. The first mechanical stop arrangement is configured for initially locking the actuator plate at the first pivot position, and for selectively unlocking the actuator plate from the first pivot position responsive to an actuating force, to thereby allow the actuator plate to pivot to the second pivot position. The actuation assembly is for selectively applying the actuating force to the first mechanical stop arrangement, to thereby unlock the actuator plate from the first pivot position. Each fin assembly includes a fin pivotable from a stowed position to a deployed position about a respective fin hinge defining a respective deployment axis, each fin assembly forming a kinematic pair with the actuator plate such that the pivoting of the actuator plate between the first pivot position and the second pivot position, and the pivoting of each fin from the respective the stowed position to the respective the deployed position, are concurrent. The second mechanical stop arrangement is for locking the fin assemblies in the respective deployed positions responsive to the actuator plate pivoting from the first pivot position to the second pivot position.
Israel Aerospace Industries | Date: 2017-02-01
An aircraft pylon comprising a body for mounting to an aircraft, a suspension mechanism mounted on said body and being configured for attaching thereto a payload, and a moving door configured for selectively covering and uncovering at least a part of said suspension mechanism
Agency: European Commission | Branch: H2020 | Program: RIA | Phase: MG-1.1-2014 | Award Amount: 5.28M | Year: 2015
The European industry is currently a world leader in aviation and to maintain its leading position and competitiveness in the dynamic global market, Europes industry must develop quickly and efficiently high quality products by meeting time-critical market demands and customers needs. Industrial competition is becoming fiercer not only from established regions, such as the USA, but from new emerging challengers, such as Brazil, Canada, etc. Technological leadership and innovation is becoming the major competitive differentiator, most notably in terms of costs, and environmental performance. The market demands shorter cycles of new technology integration and, on the other hand, competitors enter the market with aggressive prices. It is forecasted that in 2050, innovative products and services demanded by the market will be based on state of the art design, manufacturing and certification processes with a significant reduction of the environmental impact. Recent studies have shown that the development and deployment of new structural technologies will have the greatest impact in the reduction of weight and operational costs compared to other technologies. Against this background, composite materials technology is of fundamental importance to current and future aircraft structures where high specific properties and integration of multiple functionalities are essential to improve weight, fuel efficiency, reduce CO2 emissions, and certification costs. The vulnerability of composite structures to localised, dynamic, sudden, and unexpected loads, may result in unpredictable complex localized damage and a loss of post-impact residual strength. The aim of the EXTREME project is to develop novel material characterisation methods and in-situ measurement techniques, material models and simulation methods for the design and manufacture aerospace composite structures under EXTREME dynamic loadings leading to a significant reduction of weight, design and certification cost.