An unmanned aerial vehicle has an internal combustion engine, and a fuel and lubrication system comprising a fuelling system for fuelling the engine and a lubrication system for delivering lubricating oil to the engine. The fuelling system comprises a fuel reservoir from which fuel can be delivered to the engine. The fuel reservoir comprises a main tank and a header tank. The lubrication system comprises an oil tank. The oil tank is accommodated internally within the main tank to provide an integrated assembly. The arrangement provides for warming of lubrication oil for the UAV engine using several available heat sources. Further, the arrangement facilitates a configuration and layout intended to minimise or negate any undesirable moments of inertia for the UAV during flight as fuel and oil is consumed.

A method and apparatus for modular power distribution includes an end module and at least one switching module having a switching module electrical power interface configured to electrically connect to at least one of the end module electrical power interface or another switching module electrical power interface, and having at least one of a switching element, an input/output connector, a switching module communication interface, or a bus bar connector, wherein the modules are physically secured.

A portable removable air-cooling accessory device for an air cooled engine, in a piston and/or light aircraft, and a method of using the air-cooling accessory to cool the engine of the light aircraft are described. The portable removable air-cooling accessory device includes at least a fan assembly, a housing having an enclosure forming and airflow channel, a rechargeable battery, and electrical components for controlling and monitoring the portable removable air-cooling accessory device is placed on the opening of the oil access door or the engines air cooling inlets to provide cooling airflow over the engine when a hot start scenario is anticipated.

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 an independent liquid level detection capacitive sensor is arranged along each edge of the fuel tank bottom and of the side walls; wherein the tank is electrically conductive and each level sensor comprises an electrically insulating plate arranged thickness-wise between sensor and tank, such that tank and sensors are capacitively uncoupled. Method for obtaining the fuel volume comprising: obtaining the reading of the liquid level detection capacitive sensors arranged on the edges of the tank; calculating the volume, corresponding to the fuel, of the geometric solid defined by the fuel tank and by the upper surface of the fuel as defined by the liquid level readings from the sensors.

A liquid storage system comprising: a tank for containing a liquid, the tank enclosing a liquid storage space; and a tank liner fixedly attached to an internal surface of the tank (16). The tank liner comprises: a plurality of elements, each element having a hardness value of 2 GPa or above; and a binder material in which the plurality of elements are embedded. The elements have a higher hardness value than the binder material. A distance between a first element and the internal surface of the tank in a direction normal to the internal surface of the tank is different to a distance between a second element and the internal surface of the tank in the direction normal to the internal surface of the tank, the first element being different to the second element.

A heat shield assembly is disclosed. In various embodiments, the heat shield assembly defines a first circumferential side and a second circumferential side and an inboard end and an outboard end and includes a first layer defining a first surface of the heat shield assembly and having a first tab member disposed proximate the inboard end at the first circumferential side and a second tab member disposed proximate the outboard end at the first circumferential side; and a second layer defining a second surface of the heat shield assembly and having one or more first crimped portions extending along the first circumferential side and configured to engage the first tab member and the second tab member.

A portable removable air-cooling accessory device for an air cooled engine, in a piston and/or light aircraft, and a method of using the air-cooling accessory to cool the engine of the light aircraft are described. The portable removable air-cooling accessory device includes at least a fan assembly, a housing having an enclosure forming and airflow channel, a rechargeable battery, and electrical components for controlling and monitoring the portable removable air-cooling accessory device is placed on the opening of the oil access door or the engines air cooling inlets to provide cooling airflow over the engine when a hot start scenario is anticipated.

A passenger transport system comprising at least one electromechanical self-powering RF signal generator having a push & return mechanism, and at least one passenger seat having a seat region, wherein said push & return mechanism is installed, said generator, which is provided with an RF transmitter, is equipped to self-generate electric power based on a mechanical force applied on the push & return mechanism by a passenger sitting in the seat region, and whereby said generated electric power is used for the RF transmitter to transmit an RF signal on an adjustable frequency in case the passenger sitting in the seat region thereby presses a switch of the push & return mechanism, and which passenger transport system further comprises: a central RF receiver for receiving transmitted RF signals which have features to identify the individual passenger seats he RF signals are transmitted from, and means for based on the received RF signals deriving information indicating which of the passenger seats are and/or are not occupied.

An unmanned aerial vehicle (UAV) includes a vehicle body and a flight control circuit. The vehicle body includes a housing and a fan. The housing includes two vents arranged at two ends of the housing and in communication with an internal space of the housing. The two vents and the internal space form a heat dissipation air passage. The fan is arranged at one of the two vents, and is configure to drive external air into the heat dissipation air passage and expel internal air from the heat dissipation air passage. The flight control circuit is arranged inside the housing and is configured to control flight parameters of the UAV. The heat dissipation air passage is configured to dissipate heat generated by the flight control circuit.

A method and apparatus for modular power distribution includes an end module and at least one switching module having a switching module electrical power interface configured to electrically connect to at least one of the end module electrical power interface, to another switching module electrical power interface, or to at least one voltage converter module, and having at least one of a switching element, an input/output connector, a switching module communication interface, or a bus bar connector, wherein the modules are physically secured.