44results about How to "Enhanced cruise capability" patented technology

The invention discloses an unmanned aerial vehicle with a remote control system and a flight control system, and relates to the technical field of agricultural moth trapping. The unmanned aerial vehicle comprises a shell, rotor wings, rotor wing supports, a brushless motor, a lithium battery, a screw socket, a broad spectrum moth trapping lamp, a spiral supporting frame, a conductive net barrel, a circuit system and the flight control system. The lithium battery is installed in the center of the upper end face of the shell. The four corners of the shell are evenly provided with the rotor wing supports. The other ends of the rotor wing supports are connected with the upward brushless motor perpendicular to the shell through the circuit system. Rotor wings are installed at the upper end of the brushless motor. A spiral supporting frame is installed in the center of the lower bottom face of the shell. The broad spectrum moth trapping lamp in threaded connection with the shell through the screw socket is arranged in the spiral supporting frame. The broad spectrum moth trapping lamp is sleeved with the conductive net barrel which is in sleeved connection with the screw socket. The circuit system is connected with the flight control system. The unmanned aerial vehicle has the advantages that the broad spectrum moth trapping lamp and the conductive net barrel are installed at the bottom of the shell, moths are killed in the flight process, design is scientific and reasonable, environmental protection is achieved, efficiency is high, and operation is easy.

The invention provides a trailing edge with adjustable degrees of curvature for an aircraft wing. The aircraft wing comprises a middle wing part with the fixed degree of curvature. The middle wing part comprises a main beam. The trailing edge with the adjustable degrees of curvature comprises a rear beam, a plurality of trailing edge pole group structures and a trailing edge driving mechanism, wherein the trailing edge pole group structures are arranged in parallel. The rear beam is connected with the rear end of the main beam. The trailing edge driving mechanism comprises rockers driven by a driving device. One ends of the rockers are connected with the rear beam in a rotatable mode, and the other ends of the rockers are connected with the trailing edge pole group structures in a rotatable mode. The trailing edge pole group structures are plane pole group structures based on 5R closed-loop units and respectively have one degree of freedom. Each trailing edge pole group structure comprises a plurality of pairs of 5R closed-loop units, a plurality of networking triangular units, a tail-end 4R closed-loop unit and a tail-end triangular unit. Each pair of 5R closed-loop units comprises the upper 5R closed-loop unit and the lower 5R closed-loop unit. Meanwhile, the invention provides a leading edge with adjustable degrees of curvature for the aircraft wing.

The invention belongs to the field of design of aviation aircrafts, and relates to a method for designing a fixed-wing aircraft capable of vertically taking off and landing. The method for designing the aircraft is used for a mixed-mode aircraft and can be realized under current technical conditions, and vertical taking-off and landing are achieved on the basis of the fixed-wing aircraft. When the contradiction between vertical flight and wing-borne flight is handled with, design is conducted with the wing-borne flight as the main working point, higher cruise efficiency and higher cruise capacity are pursued to the larger extent under the current technical conditions, and the requirement for efficient long-time cruise is better met. When the contradiction between the vertical flight and the wing-borne flight is handled with, through coordinated optimization design of two working points, part of performance of the vertical flight is considered, the efficiency and other performance of the vertical flight is improved on the premise of satisfying the cruise performance index, and design failure caused by unreasonable performance of the vertical flight is avoided.

The invention provides a dual-purpose self-powered unmanned aerial vehicle aviation protection base station for land and sea, which includes a wind-solar hybrid power generation layer, a drone supply layer, a core component layer and a support that are sequentially arranged from top to bottom; the wind-solar hybrid power generation layer includes solar power generation device and wind power generation device; the UAV supply layer includes a charging platform, and a guide module and a charging module located on the charging platform; the core component layer includes an energy storage unit, a control circuit and an information relay module; the energy storage unit is used to combine wind and wind The electricity generated by the complementary power generation layer is stored; the control circuit is used to control the opening and closing of the solar panel as the hatch of the UAV supply layer, and the switching of the electric energy supply of the solar power generation device, wind power generation device, and energy storage unit; information relay The module is used to strengthen and relay the signal collected by the UAV within the signal range, and transmit it to the shore-based management center. The base station design of the present invention prolongs the endurance time of the drone and expands the cruising range.

The present invention provides a split winglet configured to be attached to the wing of an aircraft. The split winglet may include an upper winglet extending smoothly from the wingtip above a chord plane of the wing, and a pelvic fin protruding from a lower surface of the upper winglet below the chord plane. The upper winglet may include a transition portion that curves upwardly from the wing tip to a generally flat portion. The upper and lower surfaces of the upper winglet may be bounded by leading and trailing edges swept toward the direction of airflow, parallel to the chord plane, and curved toward the direction of airflow, terminating at A little bit distal to the wing tip. Similarly, the upper and lower surfaces of the pelvic fin may be bounded by leading and trailing edges that are curved towards the direction of the airflow and terminate at a point distal to the wing tip.

The invention belongs to an overall aerodynamic configuration form of an aircraft, belongs to the field of the advanced overall aerodynamic configuration of the aircraft and especially relates to theaircraft with a combined type jointed wing structure. The aircraft comprises a fuselage main body, a front wing, a propelling system and a rear wing; the propelling system comprises a nacelle on wingand a nacelle bracket; the rear wing comprises a M-shaped lifting wing and a V-shaped tail wing; the M-shaped lifting wing has the posture stabilizing and posture control functions; the V-shaped tailwing has a posture stabilizer and an operation plane. The invention has the beneficial effects that the technical scheme is adopted so that the aircraft has simple structure and reasonable configuration and is beneficial to the promotion of lift-drag ratio, cruising performance, aerodynamic efficiency and stability of the aircraft.

Disclosed is a road for charging electric vehicle. The road includes an electrified rail which includes an electrode plate for connecting an electric plate of the electric vehicle, an insulated cover covering on the plate electrode so as to prevent electric leakage and a neutral layer covering on the insulated cover for connecting a neutral electrode plate of the electric vehicle. The electrode plate includes a first electrode plate and a second electrode plate. The first electrode plate is disposed above the second electrode plate and between the first electrode plate and the second electrode plate there is a gap so that the electric plate of the electric vehicle is able to be sandwiched between the first electrode plate and the second electrode plate while charging. According to the present invention, the road surface is provided with electrified rail, thus the electric vehicle can charge while driving.

The invention discloses a solid rocket vehicle, and belongs to the field of recyclable rocket design. The solid rocket vehicle specifically comprises a head load compartment, a rocket body, wings, a rudder, horizontal tail rudders, an adjustable gas flow baffle, ad a tilt buffer; the head load compartment is in a lifting-body shape, the wings are located on both sides of the middle of the rocket body, and the horizontal tail rudders are located on both sides of the rear of the rocket body; and the rudder is located on the back of the rocket body, and the adjustable gas flow baffle is mounted on the rocket body and placed at the lower back portion of the outlet of an engine nozzle. The solid rocket vehicle comprehensively applies the lifting-body load compartment, the wing-level full-actingtail rudders and the landing buffer to increase the lifting force of a flight test platform, and the lift-block ratio and the delay time of the flight test platform are improved, so that the cruisingcapability of the flight test platform is improved; and the method of control rolling rotating of the differential horizontal tail rudders is used, the complexity of a control mechanism is simplified, the self-control of the drop point is achieved by using the cruising capability and the tilt strategies of the flight test platform, and landing recovery is easier.

The invention discloses a four-rotor drone with a remote control system, and relates to the technical field of agricultural moth luring. Including casing, rotor, rotor bracket, brushless motor, lithium battery, screw seat, broad-spectrum moth trap lamp, spiral support frame, conductive mesh cylinder, circuit system and flight control system; lithium battery is installed in the center of the upper end of the casing , and the four corners are evenly distributed with rotor brackets; the other end of the rotor bracket is connected to a brushless motor perpendicular to the upward surface of the casing through the circuit system; the upper end of the brushless motor is equipped with a rotor; Support frame; inside the spiral support frame, there is a broad-spectrum moth-attracting lamp connected to the casing through a screw socket; the broad-spectrum moth-attracting lamp is covered with a conductive mesh cylinder, and the conductive mesh cylinder is socketed with the screw socket; the circuit system is connected to the flight control system . The beneficial effect of the invention is that a broad-spectrum moth-attracting lamp and a conductive mesh tube are installed at the bottom of the casing to kill moth pests during flight, and the design is scientific and reasonable, environmentally friendly and efficient, and easy to operate.

The present invention discloses a quadrotor unmanned aerial vehicle possessing a remote control system, and relates to the agricultural moth trapping technology field. The quadrotor unmanned aerial vehicle possessing the remote control system comprises a chassis, a rotor, rotor supports, a brushless motor, a lithium battery, a screw socket, a broad spectrum moth trapping light, a spiral supporting rack, a conductive web clothed cylinder, a circuit system and a flight control system. The lithium battery is arranged in the center of the upper end face of the chassis, the rotor supports are distributed at the four corners of the chassis evenly, and the other ends of the rotor supports are connected with the brushless motor which is vertical with the chassis and faces upwards via the circuit system. The upper end of the brushless motor is equipped with the rotor, the spiral supporting rack is arranged in the center of the lower bottom surface of the chassis, and the broad spectrum moth trapping light which is in threaded connection with the chassis via the screw socket is arranged inside the spiral supporting rack and is covered by the conductive web clothed cylinder. The conductive web clothed cylinder is in cup joint with the screw socket, and the circuit system is connected with the flight control system. The beneficial effects of the present invention are that: the broad spectrum moth trapping light and the conductive web clothed cylinder are arranged at the bottom of the chassis and can kill moth pests during the flight process, and the quadrotor unmanned aerial vehicle possessing the remote control system is scientific and reasonable in design, is environment friendly and efficient, and is easy to operate.