13results about How to "Increase the voyage" patented technology

This disclosure relates to a fuselage shell of a drone and the drone itself. The fuselage shell includes a housing for enclosing a space for accommodating internal components of the drone. The housing includes a bottom wall and a front end wall, a transition wall, and a main body wall sequentially disposed on the bottom wall from front to back along the drone's longitudinal direction. The orthographic projection area of ​​the front end wall along the longitudinal direction is a first projection area. The orthographic projection area of ​​the area enclosed by a first connecting line at the junction of the transition wall and the main body wall and the bottom wall along the longitudinal direction is a second projection area. The first projection area is completely located within the second projection area. The transition wall is a continuous, smooth curved surface extending rearward from the front end wall. This technical solution optimizes the shape of the housing, making it more rounded, suitable for guiding airflow during flight, reducing fuselage drag, and increasing the drone's range.

The invention relates to a corrugated wall surface airfoil profile and a design method thereof, which are applied to an unmanned aerial vehicle, and are characterized in that a corrugated wall surface is arranged in a chordwise region of the upper surface of the airfoil profile, and the corrugated wall surface is used for inducing a boundary layer of the upper surface of the airfoil profile to transition in advance and inhibiting generation of laminar flow separation bubbles; the corrugated wall surface is of a sine function corrugated structure, and the sine curve of the corrugated wall surface meets the following formula. According to the invention, the sine wave pattern-shaped wall surface structure with specific geometric parameters is arranged in the chordwise middle rear area of the upper surface of the wing profile, so that local pressure distribution of the surface of the wing profile is changed, a boundary layer is induced to transit in advance, generation of laminar separation bubbles is inhibited, wall surface friction resistance and differential pressure resistance are reduced, and the stability of the wing profile is improved. The problem that the low-altitude low-speed unmanned aerial vehicle wing type drag reduction effect is limited is solved.

The application discloses a wing surface continuous deformation mechanism based on a slide bar-flexible truss-skin, which comprises a rigid wing box (40% of the terminal chord length), a flexible upper skin, four independent flexible trusses, a slide bar and a rigid trailing edge. The trusses are connected with the upper skin together, and the whole driving system serves as the lower skin of the wing. The slide bar slides back and forth at the leading edge of the wing, the deformation mechanism is stretched or bent, and the curved surface of the wing is changed. The upper surface skin of the wing is made of a skin prepared from a material capable of bearing large deformation. The motor drives the slide bar to generate a driving force, when the driving force is applied to the leading edge direction, the trailing edge deflects downward, and when the driving force is applied to the trailing edge direction, the trailing edge deflects upward, so that the deformation is completed.

The utility model belongs to the technical field of shape design and control of aircrafts, and relates to an electric tilt-rotor aircraft. Comprising a fuselage, two wings located on the two sides of the fuselage, an empennage, a plurality of supporting rods arranged below the wings and rotors arranged at the two ends of the supporting rods. The rotor wings comprise a plurality of tilting rotor wings and a plurality of fixed rotor wings; the number of the supporting rods is even, and the supporting rods are divided into two sets with the same number and are symmetrically arranged on the two sides of the machine body. A tilting rotor wing is arranged at the front end of each supporting rod; a fixed rotor wing is arranged at the rear end of each supporting rod; the tilting rotor wings are connected with the front ends of the supporting rods through tilting mechanisms, and the tilting mechanisms are used for adjusting the orientation of the tilting rotor wings. The electric tilting rotor aircraft provided by the utility model can realize the functions of vertical take-off and landing, tilting transition and cruise flight.

The invention discloses a variable rotor duct system and a tilt rotor aircraft, and relates to the technical field of aircrafts, the variable rotor duct system comprises a transmission shaft, a rotor assembly and a duct assembly; the transmission shaft is in transmission connection with an aircraft body; the rotor assemblies are connected to the transmission shaft; the duct assembly comprises a deformation shell and a first driving mechanism, the first driving mechanism is connected to the transmission shaft, and the deformation shell is arranged outside the rotor wing assembly in a surrounding mode in the circumferential direction; the first driving mechanism is in transmission connection with the deformation shell, the first driving mechanism can drive the deformation shell to circumferentially expand in the direction away from the transmission shaft so as to form a duct configuration, and the first driving mechanism can further drive the deformation shell to circumferentially contract in the direction close to the transmission shaft so as to form a fairing configuration. According to the variable rotor duct system and the tilt rotor aircraft provided by the invention, the rotor duct system gives consideration to high hovering efficiency and low forward flight resistance, and the overall aerodynamic efficiency and engineering application value of the tilt rotor aircraft are improved.

The three-duct tilting electric vertical take-off and landing aircraft comprises an aircraft body, the aircraft body adopts a streamline design, and an integrated electric ducted fan fused with the aircraft body is arranged at the rear part of the aircraft body; a duct sealing device is arranged at an inlet and an outlet of the integrated electric ducted fan; left and right wings are arranged on two sides of the fuselage, and left and right tilting electric ducted fans are respectively mounted in the middles of the left and right wings; the three electric ducted fans are arranged in a triangular space; a horizontal tail and a vertical tail are arranged at the tail part of the fuselage, and the horizontal tail and the vertical tail are arranged by adopting an integrated cross-shaped empennage; wing control surfaces are arranged on the rear edges of the left and right wings, a horizontal tail control surface is arranged on the rear edge of the horizontal tail, and a vertical tail control surface is arranged on the rear edge of the vertical tail. The aircraft adopts a combined layout of double tilting ducts and a single fixed fusion duct, so that high stability of vertical take-off and landing, moment self-balance in a transition stage and high aerodynamic efficiency in a cruise stage are realized.

The invention relates to the technical field of aviation aircraft design, and discloses a variable camber wing based on a bistable composite material structure driving multi-section rotation, which comprises a wing leading edge structure, a multi-section rotation rigid skin, an internal truss structure connected with the multi-section rotation rigid skin, a bistable composite material driving structure and a transmission mechanism, the bistable composite material driving structure is arranged between the rigid skin hinge and the transmission mechanism; and the transmission mechanism is arranged between the truss structure in the rigid skin and the sliding chute of the wing leading edge structure. The control precision and reliability are improved through relative change of the three rigid wings, and the problems that in the prior art, the structure is complex, the weight is large, the actuation efficiency is low, and the bearing capacity is low are solved.

The invention belongs to the technical field of underwater vehicle control, and particularly relates to a vertical plane navigation attitude control method for a variable-mass underwater vehicle, which can effectively maintain a depth control attitude, reduce energy consumption and improve a voyage, and is beneficial to exerting the optimal maneuvering performance and maneuvering performance of the underwater vehicle. Aiming at the problems of increased navigation resistance, increased energy consumption, increased depth control error and shortened voyage caused by changes of a navigation pitch angle and a rudder angle due to factors such as fuel consumption, cross-sea-area seawater temperature, salinity change and large-range depth change of an underwater vehicle, the invention can effectively maintain a depth control attitude, reduce energy consumption and improve voyage, and has the advantages of simple structure, low cost and high efficiency. And the optimal maneuvering performance and maneuvering performance of the underwater vehicle can be developed. By combining a buoyancy balance control strategy with navigation control, a depth control attitude is kept, so that the energy consumption of vertical plane navigation control is remarkably reduced, the control precision is remarkably improved, and the optimal maneuverability and maneuverability of the underwater vehicle are favorably exerted.

The application relates to the technical field of aircraft design, and discloses a cooperative control method and system for multi-mode flight of an aircraft and the aircraft. The method comprises the following steps: S1. a cruising efficiency optimization step: in a cruising flight mode, current Mach number, an angle of attack and real-time pressure distribution data from a pressure sensor array arranged at the rear of the upper surface of a main wing of the aircraft are acquired; based on the Mach number and the angle of attack, a target pressure distribution feature under the current working condition is solved in real time through a pre-stored optimization model; the working parameters of a boundary layer management propulsion module integrated in the main wing are dynamically adjusted so that the real-time pressure distribution data approaches the target pressure distribution feature; and S2. a mode conversion cooperation step: in response to a command for conversion to a vertical take-off and landing mode, a preset cooperative conversion sequence is executed. The system-level unification of cruising aerodynamic efficiency and vertical take-off and landing flexibility significantly improves the mode conversion stability and the comprehensive efficiency of the whole task profile.

The invention relates to an aircraft and an aircraft cluster thereof, and belongs to the technical field of aircrafts, the aircraft comprises an aircraft body, a tiltable duct, an engine mechanism and a connecting device, the connecting device comprises a male buckle and a female buckle which are arranged on a frame, and the male buckle and the female buckle on adjacent aircrafts are buckled to realize butt joint of the adjacent aircrafts; through the tiltable duct arranged on the aircraft body and the engine mechanism on the duct, efficient conversion between vertical take-off and landing and horizontal cruising of the aircraft is achieved, and the aircraft has the maneuverability and flexibility of a helicopter and the high-speed cruising ability of a fixed-wing aircraft; meanwhile, through a connecting device formed by matching a male buckle and a female buckle which are arranged on the aircraft body, the adjacent aircrafts can be mechanically butted quickly and stably, so that marshalling connection and separation during multi-aircraft collaborative operation are facilitated, a combined flight mode can be formed, and the loading capacity, the voyage and the task adaptability are effectively improved; and a reliable structure basis is provided for modular extension and cluster application.

The utility model discloses an intelligent variable-wing centrifugal plasma charging turbojet stealth unmanned aerial vehicle. Comprising a fairing, an upper fuselage, a lower fuselage, a tail, an intelligent rudder wing, a turbine set, a plasma device, an air expansion cavity, a small impeller, a large impeller, a lower shell, an upper shell, a positioner, a connector, an end cover, a motor set, a coupler, an ion pulser, an electroactive exciter, a farad module, a control power supply, a centrifugal electronic speed controller, a flight controller, a right electronic speed controller, a left electronic speed controller, a measurement and control instrument, a left paddle set, a voltage plate and an active belt. The unmanned aerial vehicle comprises aileron wheels, ailerons, wheels, a rear landing gear and a front landing gear. The unmanned aerial vehicle overcomes the defects that a low-altitude hybrid wing unmanned aerial vehicle does not have jet propulsion combining vertical take-off and landing with efficient cruising, does not have intelligent wing changing, and is high in energy consumption, short in voyage, large in engine noise, not environmentally friendly and the like. The intelligent variable-wing ailerons and the intelligent rudder wings are utilized to realize loss control, energy consumption reduction, response speed improvement, impact reduction and the like, the voyage of the unmanned aerial vehicle is improved, noise is reduced, and the unmanned aerial vehicle is easy to control and has a stealth function.

The invention discloses a lift fan matrix vertical lifting high-altitude rocket launching platform and a using method, and belongs to the technical field of aerospace. The launching platform comprises at least two platform modules, electric ducted lift fans, a battery pack, a rocket docking clamping lock, a high-pressure push rod push-away system, a platform module docking locking mechanism and a flight control system, wherein the platform modules can be separated and docked, and the electric ducted lift fans are installed in the platform modules in a distributed mode. During use, the platform vertically ascends and descends to carry the rocket to a preset high altitude, the rocket is safely separated from the platform in a mode of pushing away first and then separating / descending, and then the rocket is ignited and launched. The electric lift fan matrix is adopted for providing power, the rocket launching platform has the advantages of being high in loading capacity, high in platform stability, capable of being repeatedly used, low in launching cost and the like, and the rocket launching efficiency can be effectively improved.

The utility model provides a modularized tailstock type coaxial unmanned aerial vehicle, which belongs to the technical field of unmanned aerial vehicles and comprises a coaxial unmanned aerial vehicle module A, wing modules B and a tail thrust module C. The wing modules B are detachably connected to two sides of the coaxial unmanned aerial vehicle module A. The tail thrust module C is detachably connected to the tail of the coaxial unmanned aerial vehicle module A; the coaxial unmanned aerial vehicle module A comprises an upper rotor blade, a lower rotor blade, a fuselage and a periodic variable-pitch steering engine room, the periodic variable-pitch steering engine room is mounted at the top of the fuselage, and the upper rotor blade is mounted at the top of the periodic variable-pitch steering engine room. The problems that a conventional coaxial unmanned aerial vehicle is short in endurance time, short in voyage and low in flight speed, and a conventional tailstock type unmanned aerial vehicle is low in hovering efficiency and forward flight efficiency due to the fact that a rotor wing needs to give consideration to hovering and cruising states are solved.