Lod, Israel

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.


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Patent
Israel Aerospace Industries | Date: 2015-03-25

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.


Patent
Israel Aerospace Industries | Date: 2015-03-29

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.


Patent
Israel Aerospace Industries | Date: 2017-04-12

An add-on brake system (1) for clamping a wheel disc a vehicle includes a housing (10) accommodating a direct-drive linear actuator, which includes: an electric motor constituted by a rotor (70) and a stator (80); a nut arrangement (73) fixedly and directly coupled to the rotor (70) and configured for revolving therewith; a linear threaded plunger (20) associated with the nut arrangement (73) for being driven thereby in a linear direction upon the revolution of the latter, the plunger (20) having a first end linearly protruding from one end of the nut arrangement (73) and a second end linearly protruding from an opposite end of the nut arrangement (73). The system also includes: at least one inboard brake pad (50) fixedly coupled to the housing; at least one outboard brake pad (60) associated with the second end of the linear threaded plunger (20), oriented transverse to the linear threaded plunger (20) and configured for being driven thereby in the linear direction. The linear threaded plunger (20) has an initial unclamped position in which the second end protrudes to a first extent n_(1) from the other end of the nut arrangement, yielding a first spacing S_(1) between the inboard and outboard brake pads (50, 60), and a final clamped position in which the second end protrudes to a second extent n_(2) > n_(1) from the other end of the nut arrangement (73), yielding a second spacing S_(2) < S_(1) between the inboard and outboard brake pads (50, 60), allowing clamping the wheel disc.


Grant
Agency: Cordis | Branch: FP7 | Program: CP-IP | Phase: AAT.2013.1-4. | Award Amount: 37.06M | Year: 2013

AFLoNext is a four year EC L2 project with the objective of proving and maturing highly promising flow control technologies for novel aircraft configurations to achieve a quantum leap in improving aircrafts performance and thus reducing the environmental footprint. The project consortium is composed by forty European partners from fifteen countries. The work has been broken down into seven work packages. The AFLoNext concept is based on six Technology Streams: (1) Hybrid Laminar Flow technology applied on fin and wing for friction drag reduction. (2) Flow control technologies applied on outer wing for performance increase. (3) Technologies for local flow separation control applied in wing/pylon junction to improve the performance and loads situation mainly during take-off and landing. (4) Technologies to control the flow conditions on wing trailing edges thereby improving the performance and loads situation in the whole operational domain. (5) Technologies to mitigate airframe noise during landing generated on flap and undercarriage and through mutual interaction. (6) Technologies to mitigate/control vibrations in the undercarriage area during take-off and landing. AFLoNext aims to prove the engineering feasibility of the HLFC technology for drag reduction on fin in flight test and on wing by means of large scale testing as well as for vibrations mitigation technologies for reduced aircraft weight and for noise mitigation technologies. The peculiarity of the AFLoNext proposal in terms of holistic technical approach and efficient use of resources becomes obvious through the joint use of a flight test aircraft as common test platform for the above mentioned technologies. To improve aircraft performance locally applied active flow control technologies on wing and wing/pylon junction are qualified in wind tunnels or by means of lab-type demonstrators.


Grant
Agency: Cordis | Branch: H2020 | Program: RIA | Phase: MG-8.2a-2014 | Award Amount: 4.18M | Year: 2015

Container terminals serve thousands of ships, store billions of TEUs, compete to serve the next vessel, and introduction of larger ships will result in new challenges. While advances have been made in terminal automation (Automated Ground Vehicle (AGV), gate control, yard cranes, etc.), with current technologies terminals are limited by their ability to maintain growth and quality of service. To address these trends and demands the Robotic Container Management System (RCMS) has been developed. As a contribution to its implementation, Project main objectives are: A. to develop a detailed simulation model for RCMS to be evaluated in 2 Terminals (Gdansk and Koper) plus a set of generic simulation tools to be used in all terminals; B. to assess and compare RCMS performance with other state-of-the-art container handling technologies for 2 Terminals (Gdansk and Koper) with different features; C. to assess and compare RCMS performance with other state-of-the-art container handling technologies for 2 ports (Gdansk and Koper), with focus on comparison between RCMS solution and port surface extension; D. to assess impact of RCMS in a simulated transport network in terms of efficiency, reliability, capacity, performance indicators (travel times, average speed, etc.) and impacts (noise and air pollution) in the Port of La Spezia. Main results will be: a well-defined RCMS control logic; a dynamic physical AGV model to test AGV behavior; definition of operational procedures for RCMS; a generic simulation tool enabling testing of RCMS for various sites by non-simulation experts; an efficient entire terminal design with RCMS; a set of validated and quantified benefits of RCMS compared to commonly used handling systems; a set of Key Performances Indicators of the transport network using RCMS. Consortium is made by leading industries, SMEs, Research/Academic Centers and 3 ports/terminals as End-users. Project duration is 21 months and estimated eligible costs are 4 million


Grant
Agency: Cordis | 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.


Patent
Israel Aerospace Industries | Date: 2015-09-04

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.


Patent
Israel Aerospace Industries | Date: 2015-09-22

An inflatable dummy target fittable into a carrier missile capable of being released from the carrier missile during exo-atmospheric flight; upon release, the dummy target or portion thereof is capable of being inflated and manifest characteristics that resemble GTG missile characteristics, wherein the GTG missile characteristics include IR signature, RF signature and GTG missile


Patent
Israel Aerospace Industries | Date: 2015-01-27

An ice detecting apparatus comprising: a body including at least one ice detector mounted thereon and having an ice detecting surface and a scraping member so mounted relative to said body as to allow their movement one relative to the other and configured for scraping ice from said detecting surface during said movement.


Patent
Israel Aerospace Industries | Date: 2015-01-27

Methods are provided for operating an air vehicle having fixed wings. Such methods include the step of providing an operating map of angle of attack associated with the fixed wings with Reynolds number, including conditions of separated flow over the fixed wings and conditions of attached flow over the fixed wings. Such methods also include the step of using the operating map for guidance, causing the air vehicle to operate at least within a low Reynolds numbers range corresponding to the operating map, such as to avoid or minimize risk of causing the air vehicle to operate at conditions of separated flow over the fixed wings.

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