Disclosed are systems and methods of rapidly cooling thermal loads by providing a burst mode cooling system for rapid cooling. The burst mode cooling system may include a complex compound sorber configured to rapidly absorb ammonia.

Disclosed are systems and methods of rapidly cooling thermal loads by providing a burst mode cooling system for rapid cooling. The burst mode cooling system may include a complex compound sorber configured to rapidly absorb ammonia. The system may be used to provide pulses of cooling to directed energy systems, such as lasers and other systems that generate bursts of heat in operation.

The subject disclosure relates an aerial system to track a detected obstacle. The aerial system may comprise a plurality of aircraft, an aircraft storage system to house the plurality of aircraft, an aircraft controller in communication with each of a tracking system and the plurality of aircraft. In operation, one or more of the plurality of aircraft may engage the detected threat. At least one of the plurality of aircraft may include a target neutralization device to strike the detected threat.

A protection and defence system for an infrastructure against a threat approaching the infrastructure, comprising at least one effector. When a threat is determined, the at least one effector dispenses a non-lethal countermeasure which damages the threat and thus causes its crash. Vision and target tracker, such as at least a camera and tracker, and at least one directing/actuating drive are allocated to the effector or effectors. The effector and the vision and target tracker thereof are supported by a modular platform which can be fixedly installed to/on various infrastructures, can be removed therefrom and be used in a mobile mode. In addition, the platforms comprise a sensor that detects the spatial position of the effectors.

The subject disclosure relates an aerial defense system to defend against a detected threat. The aerial defense system may comprise a plurality of defensive aircraft, an aircraft storage system to house the plurality of defensive aircraft, an aircraft controller in communication with each of a targeting system and the plurality of defensive aircraft, and a human machine interface (HMI) device to provide operator interaction. In operation, one or more of the plurality of defensive aircraft may engage the detected threat. At least one of the plurality of defensive aircraft may include a target neutralization device to strike, or otherwise engage, the detected threat.

A system platform includes a gas turbine engine coupled to a high power generator. The high power generator, driven by the gas turbine engine, supplies power to high power subsystems of the platform.

An electromagnetic mobile active system for fitting in a missile with a detonation-operated magnetic field compressor. The magnetic field compressor has at least one stator coil and at least one armature casing, which is at least partially surrounded by the stator coil and kept at a radial distance. The magnetic field compressor has at least one explosive charge embedded in the armature casing. The magnetic field compressor has at least one power source. For activating the detonation of the explosive charge, a trigger system is provided. The trigger system can be controlled by a pulse of current from the power source, depending on a signal supplied by the missile. A great amount of electrical energy can be generated in the stator coil by the detonation. For the directional radiation of the electrical energy generated by the detonation of the explosive charge, the active system has at least one directional antenna.

A fixed-wing combat aircraft comprising an electrical power source, a propulsion system, a low-power non-propulsion assembly comprising a flight control system, a high-power non-propulsion assembly comprising an electrical weapon system, and a management unit configured to selectively establish on command multiple operating modes comprising: a flight mode, in which the management unit distributes the electrical power supplied by the electrical power source to the propulsion system and to the low-power non-propulsion assembly, and an attack mode, in which the management unit limits the electrical power supplied by the electrical power source to the propulsion system and to the low-power non-propulsion assembly to the power required to allow the aircraft to glide, and reserves a majority of the available electrical power for the high-power non-propulsion assembly.

A fleet mission control system for a network of aerial vehicles including power thermal management systems is provided. According to examples of the disclosed technology a control system receives one or more mission objectives for a network of aircraft including two or more aerial vehicles. Each aerial vehicle includes a power-thermal management system. The control system receives system state information for the network of aircraft. The system state information includes PTMS state data. The control system determines a set of aircraft commands for the network of aircraft based on the one or more mission objectives and the PTMS state data, and generates an output signal based on the set of aircraft commands.

A pulse generator for generating an HPEM pulse includes a Marx generator having a plurality of capacitors that are connected in series between two output poles, providing a Marx voltage between the output poles during operation of the Marx generator. A DS resonator has two input poles and each of the input poles is connected to a respective one of the output poles by a respective supply line. The capacitors are physically disposed along a profile line having two ends at each of which a respective one of the output poles is located. A distance between the output poles is smaller than a longitudinal extent of the Marx generator along the profile line.