Derouineau
Jean-Lu Derouineau, Cornebarrieu FR
Patent application number | Description | Published |
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20130321169 | AIRPORT SURFACE COLLISION-AVOIDANCE SYSTEM (ASCAS) - An airport surface collision-avoidance system (ASCAS). An exemplary system includes sensors (e.g., radar) at light modules about an aircraft, with user interface devices located with airport ground personnel and in the cockpit of the aircraft. The system helps to avoid collisions on the airport surface, i.e., during taxiing clear of airport buildings, during taxiing close to airport buildings, during gate operations (push-back and standing), etc. The system includes components for communicating sensor information to ground service equipment (tug tractor, baggage cart, refueling truck, etc.). The system can determine possible collision for any part of the aircraft (wingtip, tail assembly, engine cowl, fuselage, door, etc). | 12-05-2013 |
Jean-Luc Derouineau, Cornebarrieu FR
Patent application number | Description | Published |
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20080264084 | PRESSURIZED CLOSED COOLING SYSTEM - An aircraft air conditioning system includes an air supply system (engine bleed or cabin air compressor taking ambient air and pressurizing it at or above cabin pressure) and a cooling system (air cycle or vapor cycle cooling packs to reject heat outside the vessel). These systems can exist as independent systems or combined into a single unit. Air supply and cooling are powered from either engine bleed air or electric power. In order to increase the airflow through the cabin, some cabin air is re-circulated and mixed with fresh air from the air supply system. | 10-30-2008 |
20090326737 | SMART HYBRID ELECTRIC AND BLEED ARCHITECTURE - An aircraft architecture may be designed to create an optimal balance between electric power and bleed power in order to match or improve current more electric architecture (MEA) performance while simplifying power extraction from the engines as well as simplifying the electrical system. Conventional aircraft architectures may use electric only ECS and cabin pressurization systems (so-called “no bleed” systems). Alternatively, older conventional aircraft may use strictly engine bleed air to provide power for ECS and cabin pressurization systems. The present invention, on the other hand, provides an architecture which may optimize the use of both engine bleed air and MEA designs to provide a system that may be simpler and potentially more reliable and available as compared to conventional aircraft architectures. | 12-31-2009 |
20140062755 | HELICOPTER COLLISION-AVOIDANCE SYSTEM USING LIGHT FIXTURE MOUNTED RADAR SENSORS - A helicopter collision-avoidance system is disclosed. An exemplary system includes at least one lamp, such as a light emitting diode (LED) lamp, an incandescent lamp, a halogen lamp, an infrared lamp, or the like; a radar emitter configured to emit a radar signal; a radar detector configured to receive a radar return signal associated with reflections of the emitted radar signal that are reflected from an object; and a radio frequency (RF) system configured to wirelessly transmit radar information associated with the received radar return signal to a radar information receiver configured to receive the wirelessly transmitted radar information. The light module is located at one of a plurality of light positions on an external surface of a helicopter. | 03-06-2014 |
Jean-Luc Derouineau, Phoenix, AZ US
Patent application number | Description | Published |
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20090224599 | PARALLELED HVDC BUS ELECTRICAL POWER SYSTEM ARCHITECTURE - A power generation and distribution system utilizes two or more AC generators each of which may be driven by a separate prime mover such as a turbine. The generators may be driven at different rotational speeds. AC power from the generators may be rectified and applied to a common DC bus. Electrical loads may be applied to the common bus and may establish an electrical power requirement. Allocation of electrical power requirement may be made among the generators based on power available from the turbines. | 09-10-2009 |
20110133545 | AIRCRAFT ELECTRICAL POWER SYSTEM ARCHITECTURE USING AUXILIARY POWER UNIT DURING APPROACH AND TAXI - An electrical power system architecture uses an auxiliary power unit as an electrical power source during taxi (ground idle) and approach idle (if required). Using the APU as a power source enables a low pressure spool driven electrical generator to be off-line when its speed is too low for it to operate effectively. | 06-09-2011 |
Jean-Luc Derouineau, Toulouse FR
Patent application number | Description | Published |
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20120078450 | DISPLAY INFORMATION TO SUPPORT CLIMB OPTIMIZATION DURING CRUISE - Methods and systems are provided for executing a single continuous altitude change by an aircraft to cruise altitude using an electronic flight bag via a flight management system. The method comprises the determination of an altitude change in a flight plan during the cruise phase of the flight plan. Based on the altitude change and a mathematical model of the aircraft an optimum vertical trajectory profile or the aircraft is determined from which an angle of attack (AOA) and a thrust is derived to achieve the optimum vertical trajectory. From the AOA and the thrust, the required aircraft control variables are determined that may be applied to the engines and the control surface actuators of the aircraft. | 03-29-2012 |