10 results about "Biplane" patented technology

The invention provides a multi-master-control biplane real-time network control method and system and a computer readable storage medium, and the method comprises the steps: firstly, carrying out the priority configuration of master stations in a master station set to obtain a priority sequence, selecting one master station from the master station set as an initial active master station, taking the other master stations as standby master stations, and carrying out the priority configuration of the master stations in the master station set; the method comprises the following steps of: acquiring an initial active master station, judging whether the initial active master station is abnormal or not in real time, and selecting a standby master station as the active master station through a preset standby master station switching algorithm if the initial active master station is abnormal, so that the redundancy of the whole system is improved, and even if the master station goes wrong, the standby master station can be quickly connected to work; when the movable master station sends data, two paths of data are sent to the terminal connected with the double planes through the double planes, the data transmission redundancy of the aircraft is further improved due to the existence of the double planes, the data transmission stability is improved, and the stability of the aircraft is further improved.

The application discloses a kind of double-body aircraft's capture trajectory wind tunnel test method, the purpose is to establish simulation in wind tunnel launch weapon from double-body aircraft separation capture trajectory test capability, belong to wind tunnel test technical field.This method includes: using tail support rod and balance to support launch weapon in six-degree-of-freedom mechanism, using double balance and double tail support to support double-body aircraft in half-arm angle of attack mechanism.According to the mass ratio of double-body aircraft and launch weapon, determine to solve six-degree-of-freedom equation for single body (launch weapon) or two bodies (launch weapon and double-body aircraft).Through the motion of six-degree-of-freedom mechanism, realize the displacement and attitude angle of launch weapon, and carry out motion compensation to the displacement of double-body aircraft, realize the pitching motion of double-body aircraft by moving half-arm angle of attack mechanism.This method has the advantages of wide simulation range, high simulation data accuracy and reliable data.

The invention belongs to the technical field of ocean exploration equipment, and particularly relates to a variable-structure multi-joint gliding type underwater robot and a working method thereof.The variable-structure multi-joint gliding type underwater robot comprises a sealed electric control cabin, a double-wing cabin, a two-degree-of-freedom joint and a sealed buoyancy adjusting cabin; the sealed electric control cabin, the double-wing cabin, the two-degree-of-freedom joint and the sealed buoyancy adjusting cabin are distributed in a linear mode, the sealed electric control cabin is located at the front end of the variable-structure multi-joint gliding type underwater robot, and a detection sensor, a control circuit board and a battery system are integrated in the sealed electric control cabin. The double-wing cabin is located at the rear end of the sealed electric control cabin, the double-wing cabin drives a sliding table to move through an underwater lead screw motor, and the sliding table and a connecting rod form a slider-crank mechanism; through fusion of the wing folding and unfolding mechanism and the multi-joint design, the performance bottleneck of a traditional underwater robot is broken through, and the maneuverability and the task adaptability of the underwater robot are remarkably improved.

The invention relates to an electric short-distance take-off and landing double-wing aircraft which comprises an aircraft body, wings and a lift augmentation power assembly. The wings comprise an upper wing, a lower wing and a vertical fin, one ends of the upper wing and the lower wing are connected through the vertical fin, the upper wing and the lower wing are equal in chord length, and the ratio of the chord length to the distance between the upper wing and the lower wing is 0.8; the high lift power assembly comprises a folding propeller, a driving motor and a slotted flap. The range extending power system comprises a variable pitch propeller, a fuel engine, a motor, a power conversion unit and a storage battery; the folding propellers are mounted at the front edges of the wings; the fuel engine is connected with the variable-pitch propeller, and the motor is connected with the variable-pitch propeller and the power conversion unit. Compared with the prior art, performance breakthrough is achieved through oil-electricity hybrid power; on the premise of not excessively increasing the extension length of the wings, the lift force is directly increased by increasing the total area of the wings through the double-layer wings, and the infiltration area of the aircraft is reduced by adopting the canard wings to carry out large-attack-angle longitudinal control.

1. The name of the design product: wing gate double-wing movement (link extension mechanism). 2. The use of the design product: wing gate movement for access control barrier. 3. The design points of the design product: in shape. 4. The picture or photo that best indicates the design points: perspective view 1.

The invention provides a deformable double-wing aircraft. The deformable double-wing aircraft comprises a fuselage, wings, an empennage, a propeller, an airborne control system, a wing group rotating shaft, a wing group truss, a wing servo motor, a wing rotating joint, a wing rotating shaft, a wing group servo motor and a wing group rotating shaft base, the wings comprise an upper wing and a lower wing; two ends of the wing group rotating shaft extending towards the outer side of the fuselage are respectively connected with the upper wing and the lower wing through wing group trusses; the wing group rotating shaft is connected with the wing group rotating shaft base and the wing group servo motor on the inner side of the fuselage; wing servo motors and wing rotating joints are symmetrically mounted at the two ends, extending towards the outer side of the fuselage, of the upper wing and the lower wing; the power output end of each wing servo motor is connected with a wing rotating shaft; the wing rotating shafts are respectively connected with the wing group trusses and the wing rotating joints. The deformable double-wing aerodynamic layout with high lift force and lift-drag ratio in two flight stages of low-speed take-off and landing and high-speed cruising is realized, and aerodynamic requirements in different flight stages can be met.

1. Name of the product designed: Aircraft (electrically powered biplane capable of vertical takeoff and landing). 2. Purpose of this design product: This design product is used for aviation vehicles. 3. The key point of the design of this product lies in its shape. 4. The picture or photo that best illustrates the design points: three-dimensional picture.

The invention provides a supersonic low-resistance and low-sonic-boom configuration adopting a double-wing double-fuselage layout form, and belongs to the technical field of supersonic aircraft design. The problem that a traditional supersonic civil aircraft layout is limited in shock wave resistance reducing effect is solved. The aircraft comprises a left fuselage, a right fuselage, a front middle wing, wings, an end plate, a rear middle wing, an air inlet channel, an engine and a T tail. The inner sides of the left fuselage and the right fuselage are contracted into non-axisymmetric structures and are fixedly connected through the front middle wing and the rear middle wing; the front middle wing is a single wing, and the rear middle wing is double wings; the wing and the rear middle wing are fixed into a double-wing structure, upper and lower wing bottom edges are parallel, vertex angles are opposite, and wing tips are fixed through an end plate; the air inlet channel is rectangular and is arranged between the upper wing and the lower wing, and an engine is arranged in the air inlet channel; the tails of the left and right fuselages are fixed through a T tail. The problem that the shock wave resistance reduction effect of a traditional supersonic civil aircraft layout is limited is solved, the shock wave resistance generated in the flight process is reduced, and the sound detonation intensity influence can be reduced.

This invention relates to a small tandem biplane unmanned aerial vehicle (UAV) configuration with ducted thrust reduction at the wingtip, comprising: a fuselage; a main wing fixedly connected to the middle or front of the fuselage; a horizontal tail fixedly connected to the rear of the fuselage, arranged in tandem with the main wing; and a ducted propulsion unit disposed at the wingtip of the main wing and / or the horizontal tail, the ducted propulsion unit comprising a duct body, ducted blades rotatably disposed within the duct body, and a motor for driving the ducted blades to rotate; wherein the axial direction of the duct body extends in the same direction as the average incoming flow direction at the corresponding wingtip. This invention solves the problems of wingtip drag reduction, propulsion efficiency, and structural adaptability in existing small tandem biplane UAVs, achieving synergistic effects of drag reduction and propulsion, and improving aerodynamic efficiency, endurance, and flight safety.

The present invention provides a deformable biplane aircraft, comprising a fuselage, wings, a tail, a propeller, an onboard control system, a wing assembly shaft, a wing assembly truss, a wing servo motor, a wing rotary joint, a wing assembly shaft, a wing assembly servo motor, and a wing assembly shaft base. The wings comprise upper and lower wings. The wing assembly shaft extends outward from the fuselage at two ends connected to the upper and lower wings, respectively, via the wing assembly truss. The wing assembly shaft is connected to the wing assembly shaft base and the wing assembly servo motor on the inside of the fuselage. The upper and lower wings are both symmetrically equipped with wing servo motors and wing rotary joints at two ends extending outward from the fuselage. The power output end of each wing servo motor is connected to the wing assembly shaft. The wing assembly shaft is respectively connected to the wing assembly truss and the wing rotary joint. The present invention realizes a deformable biplane aerodynamic layout with high lift and lift-to-drag ratio in both low-speed takeoff and landing and high-speed cruising flight stages, and can meet the aerodynamic requirements of different flight stages.