A laser weapon system is described. Particularly, embodiments describe subsystems of a laser weapon system including those necessary for laser generation, operational control, optical emission, and heat dissipation configured to provide a lightweight unit of reduced dimensions.

A thermal management system for a pulse load on an aircraft. The thermal management system utilizing the reserve fuel from the aircraft to create thermal capacitance such that the instantaneous capacity of the cooling system to remove heat from the aircraft may be sized less than the rate of heat generated by the pulsed load (e.g. laser, radar, rail gun etc.) The reserve fuel is maintained at a temperature in a reservoir and cooled via a cooling system. Fuel from the reservoir is selectively mixed with fuel exiting the pulsed load heat exchanger to provide fuel to the inlet of the heat exchanger at a predetermined temperature, the temperature based at least upon the heat generated by the laser, flow rate of fuel and efficiency of the heat exchanger.

Systems and methods are provided for decreasing thermalization time and/or increasing coefficients of performance by adding waste heat. A thermal management system may include a coolant loop and be configured to cool a target component via the coolant loop, the thermal management system may be further configured to heat the target component during a thermalization period with a waste heat source via the same coolant loop with which the thermal management system is configured to cool the target component.

A thermal management system for a pulse load on an aircraft. The thermal management system utilizing the reserve fuel from the aircraft to create thermal capacitance such that the instantaneous capacity of the cooling system to remove heat from the aircraft may be sized less than the rate of heat generated by the pulsed load (e.g. laser, radar, rail gun etc.) The reserve fuel is maintained at a temperature in a reservoir and cooled via a cooling system. Fuel from the reservoir is selectively mixed with fuel exiting the pulsed load heat exchanger to provide fuel to the inlet of the heat exchanger at a predetermined temperature, the temperature based at least upon the heat generated by the laser, flow rate of fuel and efficiency of the heat exchanger.

Systems and methods for augmenting power output when operating a load having relatively brief periods of high energy demand and high heat generation. A system comprises a gas turbine engine including a coolant injection assembly, an electrical generator coupled to the gas turbine engine, a high-energy operating load coupled to the electrical generator, and a cooling system adapted to provide cooling to the high-energy operating load. The cooling system is coupled and adapted to provide coolant to the coolant injection assembly of the gas turbine engine. A method comprises coupling the cooling system to the coolant injection assembly at the inlet of the gas turbine engine, selectively diverting at least a portion of the coolant of the cooling system to the coolant injection assembly, and spraying the diverted coolant into air entering the gas turbine engine.

Disclosed is an energy beam interceptor that includes an interceptor vehicle of either a missile or a lighter than air vehicle that carries an energy beam generator with a minimum power output of approximately 500 W, a high density power supply that power the energy beam generator, an energy beam targeting apparatus that directs emissions from the energy beam generator and an energy beam targeting controller that targets emissions from the energy beam generator with the energy beam targeting apparatus.

Disclosed is an energy beam interceptor that includes an interceptor vehicle of either a missile or a lighter than air vehicle that carries an energy beam generator with a minimum power output of approximately 500 W, a high density power supply that power the energy beam generator, an energy beam targeting apparatus that directs emissions from the energy beam generator and an energy beam targeting controller that targets emissions from the energy beam generator with the energy beam targeting apparatus.

An exemplary high-speed hybrid propulsion system for a tiltrotor aircraft includes two pivotal nacelles, each nacelle comprising an electric motor coupled to a proprotor; an electric aircraft system; an electric generator; an electrical bus electrically connected to the electric generator, the electric motors, and the electric aircraft system; and a convertible turbofan engine coupled to an electric generator through a drive shaft.

A supply module for supplying a weapon system includes an electric storage device and a thermal storage device that stores coolant. The supply module also includes at least one electrical connection via which power can be transferred from the electric storage device to the effector system, and at least one thermal connection via which the coolant can be transferred from the thermal storage device to the effector system.

A system for detecting and neutralizing a target aerial vehicle comprises a counter-attack unmanned aerial vehicle (UAV) comprising a flight body and a flight control system supported about the flight body operable to facilitate flight of the UAV, and an aerial vehicle countermeasure supported by the flight body. The system can comprise an aerial vehicle detection system comprising at least one detection sensor operable to detect a target aerial vehicle while in-flight, and operable to provide command data to the counter-attack UAV to facilitate interception of the target aerial vehicle by the counter-attack UAV. Upon interception of the target aerial vehicle, the counter-attack UAV is operable to disrupt operation of the detected target aerial vehicle with the aerial vehicle capture countermeasure, thereby neutralizing the target aerial vehicle. The counter-attack UAV and systems may be autonomously operated. Associated systems and methods are provided.