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Matches 1 - 50 out of 917

Document Document Title
WO/2019/092189A1
Embodiments of the invention comprise a ball valve (100) for intended use in aircraft fuel systems comprising of an integrated valve housing (120), a ball housing portion (115), a ball member (112) housed rotatably within the ball housin...  
WO/2019/079884A1
A method of and a system for detecting a fuel leak in an aircraft, the aircraft comprising a first engine and a second engine. The method comprises upon determining that the aircraft has reached a first mode of operation: acquiring a fir...  
WO/2019/075566A1
A method of and a system for operating a fuel pump management system of an aircraft. The method comprises receiving, from a fuel gauge, an electronic reading of a level of fuel fluid contained in a fuel tank; and analysing the electronic...  
WO/2019/077457A1
An aircraft (100) is provided that includes a fuel storage tank (108) for aviation fuel, and avionics systems interconnected by an avionics bus. The fuel storage tank (108) receives aviation fuel during a fuel uplift for a flight accordi...  
WO/2019/063682A1
The invention relates to a method for propelling an aircraft. In order to obtain electric energy, fuel is combusted and an electric machine is used, wherein the fuel is used to cool at least one part of the electric machine, and the fuel...  
WO/2019/061000A1
The present disclosure provides methods and systems for providing a lateral center of gravity of an aircraft on an aircraft display. A fuel distribution in the aircraft fuel tanks is determined. A lateral center of gravity of the aircraf...  
WO/2019/012445A1
Embodiments of the present invention provide a fuel tank communication system. The communication system includes a main body (30) used to connect two fuel bladder flanges (12, 20) to one another. The communication system provides two sep...  
WO/2018/233977A1
System (1) for inerting at least one volume (3) in an aircraft, said system comprising at least one generator of inerting gas (2) fed with compressed air originating from a passenger cabin, and means for distributing (11) the inerting ga...  
WO/2018/225010A1
Liquid fuel tank comprising a plurality of liquid level detection capacitive sensors, each arranged along an edge of the fuel tank such that the capacitance of said sensors varies with the volume of fuel present in the fuel tank, wherein...  
WO/2018/188054A1
A fuel tank separate-dropping system for an unmanned aerial vehicle. A fuel tank storage chamber (7) is provided on a base bottom plate (1); and one end of the fuel tank storage chamber (7) is communicated with a fuel tank storage groove...  
WO/2018/178463A1
The invention relates to a water sensor for detecting water in gas oil filters, comprising a first and a second electrode (1.1, 1.2); a first and a second earth connection (3.1, 3.2) for earthing the first electrode (1.1) and the second ...  
WO/2018/171239A1
A negative pressure low dead oil anti-bubble aeroplane fuel tank apparatus, comprising a fuel tank outer shell, an oil suction hose (3) arranged inside the fuel tank outer shell, a fueling port (9) arranged on the fuel tank outer shell, ...  
WO/2018/127667A3
The present invention relates to a measurement device (1) for measuring the amount of oxygen present in a gas to be analysed, said device (1) comprising: at least one measurement member (3) for measuring the amount of oxygen, a first inl...  
WO/2018/127667A2
The present invention relates to a measurement device (1) for measuring the amount of oxygen present in a gas to be analysed, said device (1) comprising: at least one measurement member (3) for measuring the amount of oxygen, a first inl...  
WO/2018/115651A1
An accumulator (23) designed to damp the pressure waves of the hydraulic shocks originating in a downstream section (22) of a duct (2) is arranged inside the duct, with the opening (28) of the accumulator pointing downstream. This result...  
WO/2018/110650A1
A moving body (2) is provided with a main body (21), a propulsion engine (22), and an energy supply unit (3). The propulsion engine (22) propels the main body (21). The energy supply unit (3) supplies energy to the propulsion engine (22)...  
WO/2018/085839A1
Systems and methods of forming fiber reinforced polymer (FRP) composites with electrostatic dissipative properties are described herein. The FRP composite is bonded to a surface and integrates a grounding system to dissipate electro-stat...  
WO/2018/074720A1
Disclosed is a multicopter comprising a fuel tank mounting part. A multicopter (100) according to an embodiment of the present invention is provided with a plurality of rotary blades and generates electricity using fuel to drive the rota...  
WO/2018/068979A1
The invention relates to a drive system (9) for a vehicle, in particular an airplane (1), comprising the following components: - an internal combustion engine (15) for converting chemical energy stored in a liquid fuel (12) into mechanic...  
WO/2018/054987A1
A refuelling system suitable for use with an overwing fuelled aircraft comprising: (b) a stored fuel grade identification means for identifying the fuel grade stored in the fuel storage vessel and available type(s) of delivery of the fue...  
WO/2018/002682A1
A vessel (1) designed for enclosing at least one sensor (10) is arranged within a fuel tank. The vessel is provided with a fuel inlet (50) connected to a refuelling arrangement of the tank, and with through-holes (20, 30) for the fuel to...  
WO/2017/216462A1
The invention concerns an assembly comprising: a fuel supply circuit (15, 15a, 15b) configured to supply fuel to a turbine heat engine, an electronic module (14, 14a, 14b), a power source (13, 13a, 13b) for supplying power to the electro...  
WO/2017/207069A1
The present invention relates to an air separation module for an aircraft inerting system. The air separation module comprises an inlet for receiving a source of air, a first outlet for exhausting nitrogen enriched air and a second outle...  
WO/2017/182733A1
Device (1) for distributing and injecting inert gas in a fuel tank of an aircraft (11), the said device comprising at least one gas distribution pipe a first end of which is intended to be connected to an inert-gas generator (3). Accordi...  
WO/2017/182758A1
The present invention relates to a spool (22) for a fuel circuit valve (20) of an aircraft engine, extending along a longitudinal axis (23) and comprising a narrowed intermediate section (32) extending between two end cylindrical section...  
WO/2017/184359A1
A method of recovering performance of an air separation module (ASM) is described. A recovery system includes an air source providing inlet air, a filter to output clean air and a heater heating the air. The ASM is coupled to the system ...  
WO/2017/184657A1
A reservoir contaminant regulation system is described. The system includes a reservoir, a tank, a set of tubing, a pressure regulator, and a vent. The reservoir is configured to hold various volumes of a working fluid. The pressurized t...  
WO/2017/182160A1
The invention relates to a fuel additising device (1) having a fuel container (10) and a feed line (20) which is connected by its first end (21) to the fuel container (10) and via which fuel (F) can be conducted from the fuel container (...  
WO/2017/180840A1
A system for calculating maintenance predictions and making improvements to performance deficiencies to one or more components in an on-board inert gas generating system (OBIGGS) is described. The OBIGGS components include an ozone conve...  
WO/2017/176490A1
Liquid storage systems for space vehicles include at least one storage tank including a tank inlet, a tank outlet, and a plurality of liquid storage compartments coupled to each other in series between the tank inlet and the tank outlet....  
WO/2017/168199A1
According to an exemplary embodiment, an inerting and pressurization system for a fuel tank (120) may be provided. The inerting and pressurization system may include an inert gas supply network,a number of valves and a number of air sepa...  
WO/2017/157526A1
An aircraft fluid line coupling assembly comprising an inner tube (1), an outer tube assembly (2) having an outer tube (4), wherein the inner tube (1) extends into the outer tube (4), and having first connector means (9) of a twist-to-co...  
WO/2017/153704A1
A fuelling method is described which comprises the steps of dispensing an initial quantity of fuel to a fuel tank, waiting for a predetermined settling period for the fuel dispensed to the fuel tank to homogenise and settle, after the pr...  
WO/2017/149196A1
A floatplane (100) comprising a fuselage (102), at least one primary wing (104) attached to the fuselage (102), a float arrangement comprising a number of floats (106), and propulsion means (500) for driving the floatplane (100), charact...  
WO/2017/146814A1
An aft pivot assembly can include a mount device securable to an aft portion of a payload of an aircraft for facilitating release of the payload. The aft pivot assembly can include a shaft operable with the mount device and a release com...  
WO/2017/127478A1
An example ullage-recirculating catalytic inerting system includes: (i) a plurality of fuel tanks having (a) respective inert gas ports for discharging the inert gas within a respective fuel tank, and (b) respective ullage gas ports for ...  
WO/2017/124051A1
A multiply-redundant system that prevents a driver from starting and/or moving a vehicle if a compressed natural gas fill system is not correctly and completely disconnected from the vehicle. One or more sensors in combination with one o...  
WO/2017/093921A1
A substantially polyhedral liquid fuel tank comprises: a plurality of capacitive sensors for detecting the level of liquid, arranged along an edge of the fuel tank such that the capacitance of said sensors varies with the volume of fuel ...  
WO/2017/089679A1
The invention concerns a power generation system (1) intended to be mounted in an aircraft, comprising at least: - a fuel cell (5) intended to generate power comprising an anode (7) and a cathode (6), - a hydrogen storage device (10) com...  
WO/2017/080854A1
An aircraft fuel system comprising at least one fuel tank; a source of inerting gas; an inlet for introducing the inerting gas into the at least one fuel tank; and a vent system arranged to allow the inward and outward venting of air fro...  
WO/2017/077100A1
An aircraft fuel tank inerting system, comprising a paramagnetic pump arranged, in use, to apply a magnetic field to a source of gas so as to provide a motive force for removing oxygen from said gas.  
WO/2017/072459A1
The invention relates to an access door of an aircraft comprising: an outer panel (10) intended to be arranged on the outside the aircraft and so as to be in contact with a first surface of a covering (12) of the aircraft, and an inner p...  
WO/2017/072460A1
The invention relates to an aircraft access door comprising an outer panel (10) and an inner panel (11). The inner panel (11) comprises at least one tapped metal part (20) capable of receiving at least one screw (44) so as to rigidly con...  
WO/2017/072298A1
The invention relates to a door to access an aircraft, comprising: an outer panel (10) intended for being arranged on the outside of the aircraft and resting on a first surface of a skin (12) of the aircraft; an inner panel (11) intended...  
WO/2017/064209A3
An aircraft fuel tank inerting system (100), comprising an oxygen absorption unit (30) containing a Cobalt or a Cobalt derived material.  
WO/2017/064209A2
An aircraft fuel tank inerting system (100), comprising an oxygen absorption unit (30) containing a Cobalt or a Cobalt derived material.  
WO/2017/051210A1
A fluid gauging system comprises a set of fuel level probes (1 -7) and two computation modules (23A, 23B) adapted for inferring fluid level information based on measurement signals which originate from the probes. In a refuelling operati...  
WO/2017/011449A1
The present disclosure is directed to a fuel cell system for generating oxygen depleted air. The fuel cell system may include a fuel cell having an anode, a cathode, and an electrolyte positioned between the anode and the cathode. The ca...  
WO/2016/170108A1
An aircraft fuel pump assembly (30) comprises a pump (40), a canister (42) arranged to enclose the pump and mount the pump within an aircraft fuel tank (20, 22, 24). The assembly also includes a discrete electronics unit (60) configured ...  
WO/2016/156393A1
An aircraft (2) having at least one thrust providing jet engine (4, 6) and a fuselage with an integrated pressurized cabin comprises an environmental control system (16) comprising at least one pneumatic air cycle air conditioning unit (...  

Matches 1 - 50 out of 917