43 results about "Climb" patented technology

A hybrid propulsion aircraft is described having a distributed electric propulsion system. The distributed electric propulsion system includes a turbo shaft engine that drives one or more generators through a gearbox. The generator provides AC power to a plurality of ducted fans (each being driven by an electric motor). The ducted fans may be integrated with the hybrid propulsion aircraft's wings. The wings can be pivotally attached to the fuselage, thereby allowing for vertical take-off and landing. The design of the hybrid propulsion aircraft mitigates undesirable transient behavior traditionally encountered during a transition from vertical flight to horizontal flight. Moreover, the hybrid propulsion aircraft offers a fast, constant-altitude transition, without requiring a climb or dive to transition. It also offers increased efficiency in both hover and forward flight versus other VTOL aircraft and a higher forward max speed than traditional rotorcraft.

The invention discloses a horizontal stage separation design method for a parallel double-waverider two-stage injection aircraft. The horizontal stage separation design method comprises the following steps: constructing a combined body structure of an orbit-stage waverider aircraft and a boosting-stage waverider aircraft; when the flight of the assembly structure reaches an interstage separation condition, the lift force borne by the two side wings of the boosting-stage waverider aircraft is unbalanced, and then the assembly structure rolls by 90 degrees in the lateral direction of the aircraft body; under the condition that the lateral rolling of the combined body structure is kept by 90 degrees, the track-level waverider aircraft is pushed by the power of the track-level waverider aircraft to perform horizontal separation action along the upper surface of the boosting-level waverider aircraft; after the orbit-level waverider aircraft is separated from the boosting-level waverider aircraft, the orbit-level waverider aircraft continues to laterally roll by 90 degrees and climbs to a target orbit, and the boosting-level waverider aircraft reversely rolls by 90 degrees to recover an initial flight state, so that horizontal-level separation of the orbit-level waverider aircraft and the boosting-level waverider aircraft is realized. According to the horizontal interstage separation method, the problems of high pressure, high heat flow and stability in the conventional separation process under the hypersonic speed condition are solved.

The invention discloses an air-based launched heavy reusable aerospace vehicle system. A transonic aircraft back-loaded aerospace vehicle is launched in the air by adopting a large-scale wing body fusion layout. The aerospace vehicle comprises an orbiter and two outer storage tanks. A carrier aircraft carries the orbiter, and the two outer storage tanks are symmetrically installed on the two sidesof the orbiter. When air-based launching is carried out, the aircraft firstly climbs to a specified height, and then a combined body of the outer storage tank and the orbiter is separated so that theorbiter climbs to the storage tank, a propellant is exhausted, and the outer storage tank is thrown away. And finally, the orbiter continuously accelerates and adjusts a posture to a specified heightto do circular motion around the earth. Cost of launching the heavy reusable aerospace vehicle is greatly reduced, and a proportion of injection weight to total take-off weight is greatly increased.

A turbofan engine has an engine core including in flow series a compressor, a combustor and a turbine. The engine further has a fan located upstream of the engine core, has a supersonic intake for slowing down incoming air to subsonic velocities at an inlet to the fan formed by the intake, has a bypass duct surrounding the engine core, wherein the fan generates a core airflow to the engine core and a bypass airflow through the bypass duct, and has a mixer for mixing an exhaust gas flow exiting the engine core and bypass airflow exiting bypass duct. The engine further has a thrust nozzle rearwards of the mixer for discharging mixed flows, the thrust nozzle having a variable area throat. The engine further has a controller controlling the thrust produced by the engine over a range of flight operations including on-the-ground subsonic take-off and subsequent off-the-ground subsonic climb.

The invention discloses an unmanned aerial vehicle flight control strategy design method using a gust environment. The method comprises the following steps: establishing a flight dynamics model of an unmanned aerial vehicle in the gust environment; the roll angle of the unmanned aerial vehicle, the roll angle speed caused by the wind field gradient and the vertical wind speed change rate are selected as state quantities, iterative training is conducted on the state quantities through a reinforcement learning Q-learning algorithm, and an optimal control strategy is obtained; a flight control decision is made for the unmanned aerial vehicle in the gust environment according to the obtained optimal control strategy, and the real-time roll angle of the unmanned aerial vehicle is controlled through a PID controller to change the course of the unmanned aerial vehicle, so that the unmanned aerial vehicle finds up airflow and climbs by using the unmanned aerial vehicle; the method effectively overcomes the problems that a conventional common unmanned aerial vehicle flight control method using the gust environment needs a complicated debugging process and is not ideal in effect, can automatically adapt to different gust environments, and remarkably improves the all-weather safe flight capability of the unmanned aerial vehicle.

The invention relates to an unmanned aerial vehicle decoy-resistant flight path control method based on active and passive composite guidance, and the method comprises the steps: entering a flight path tracking control stage when an unmanned aerial vehicle climbs to a specified flight height; performing distance estimation in a satellite navigation/inertial navigation/voyage calculation or integrated navigation mode, and when the distance is smaller than the detection and tracking action distance of the unmanned aerial vehicle passive guide device, entering a passive search stage; when an unmanned aerial vehicle passive radar seeker intercepts and tracks a target or bait, entering a passive guidance tracking stage; when the distance between the unmanned aerial vehicle and the center pointT of the target position is smaller than the range of the active radar recognition and tracking action distance of the unmanned aerial vehicle, enabling the unmanned aerial vehicle to enter a strabismus flight active search stage; and after the unmanned aerial vehicle recognizes that the target is a real target, enabling the unmanned aerial vehicle to enter a front-view attack stage, determining whether the unmanned aerial vehicle meets a diving attack condition or not according to the active and passive composite guide information, and if yes, enabling the unmanned aerial vehicle quickly to enter diving to strike the target.

A method and system for improving aircraft performances during take-off is described. The system (1) can include means (4, 6, 7) for determining an optimised take-off position of the control surfaces (S1-Sn) of the aircraft, in the case where a regulatory safety criterion relating to the minimum gradient of climb with a breakdown engine is predominant.