4results about How to "Improve flight quality" patented technology

The invention provides a fixed horizontal tail type fly-by-wire aircraft leveling control law design method, which comprises the following steps of: when an aircraft meets a condition of entering a leveling control law, recording a flight control law integral channel instruction ELNMINT at a triggering moment; generating an elevator control command component ELFLAREFWD through a forward command shaping module based on the joystick displacement signal; the method comprises the following steps: introducing an integral channel instruction ELNMINT into a leveling control law, and obtaining a bias instruction component ELFLAREOFFSET under the leveling control law after the integral channel instruction ELNMINT passes through an instruction amplitude limiting module; subtracting the bias instruction ELFLAREOFFSET from the integral channel instruction ELNMINT to obtain an instruction initial value ELFLAREFADER0 which needs to be faded during instruction transition; after the instruction initial value ELFLAREFADER 0 passes through a desalting device module, a real-time control surface control instruction component ELFLAREFADER is formed; and an elevator control instruction ELCMD under the leveling control law is obtained. According to the method, the switching transient state can be reduced by introducing the flight control law integral channel instruction component into the leveling control law, and the method has remarkable advantages in the aspects of improving the flight safety, optimizing the flight quality, enhancing the system flexibility, improving the automation level and the like.

The utility model discloses a paperboard unmanned aerial vehicle which is characterized in that a first mounting clamping position is arranged at the top of a vehicle body, a wing embedding part is arranged at the rear part of the first mounting clamping position, and first fixing structures are arranged at two side parts of the vehicle body. The wing body is provided with a second installation clamping position which can be connected with the first installation clamping position in a clamped mode, a wing embedding groove where the wing embedding part can be inserted is formed in the rear portion of the second installation clamping position, and the wing embedding part and the wing body can form a wing of the paperboard unmanned aerial vehicle after the wing embedding part is inserted into the wing embedding groove. The wing body is further provided with a second fixing structure corresponding to the first fixing structure in position, the two ends of the wing body are sleeved with elastic fixing sleeves, and each elastic fixing sleeve is elastically hung on the first fixing structure and the second fixing structure on the same side so that the fuselage body can be fixedly connected with the wing body. According to the paperboard unmanned aerial vehicle, the positioning effect between the fuselage and the wings can be improved, the accuracy of the relative position between the fuselage and the wings is guaranteed, and the flight quality of the unmanned aerial vehicle is improved.

This invention discloses a short takeoff / vertical landing (STOVL) aircraft with a hybrid propulsion system. It employs a fuselage frame as the main load-bearing structure, combined with an aerodynamic layout of all-moving canards, main wings, mid-section wings, and twin vertical tails. The hybrid propulsion system comprises four sets of cross-rotating motor-propellers and thrust-direction-adjustable STOVL level flight engines. The engines operate throughout the entire flight, while the motor-propellers are only engaged during STOVL and mode switching. Through linear adjustment of motor power, coordinated changes in engine thrust direction and magnitude, and speed-dependent aerodynamic lift of the wings, seamless and smooth transitions are achieved between STOVL / hovering, mode switching, high-speed level flight, and payload modes. Compared to existing technologies, this design reduces structural dead weight and control complexity, extends endurance, and balances STOVL flexibility with high-speed cruise efficiency.

The invention provides an aircraft controlled by combination of flexible wings and grid rudders. The aircraft comprises an aircraft body, the grid rudders and the flexible wings, the grid rudder is arranged at the tail end of the aircraft main body, and attitude control is performed on the aircraft through deflection of the grid rudder; the flexible wings are installed on the side wall of the aircraft body and located on the sides, away from the tail end of the aircraft body, of the grid rudders, and the flexible wings are unfolded and changed within the unfolding angle range. Through the installation of the flexible wings, the problems that the control capability of the grid rudder is insufficient in the transsonic speed stage and the pressure center coefficient is obviously changed are effectively solved, and the static stability of the aircraft is improved by controlling the change of the unfolding angle of the flexible wings. According to the aircraft, efficient and stable control can be achieved in the full-speed domain, compared with a traditional aircraft, the aircraft has the advantage of being lower in resistance during subsonic-speed and supersonic-speed flight, and good stability and high maneuverability are shown in the transonic-speed stage.