7results about How to "Enhanced cruise capability" patented technology

The invention discloses a vertical take-off and landing fixed-wing aircraft, and relates to the technical field of aircrafts. According to the invention, the conversion from a multi-rotor flight mode to a fixed-wing flight mode and from the fixed-wing flight mode to the multi-rotor flight mode can be easily realized. Due to the structural layout characteristics of the aircraft, the safety of the aircraft is guaranteed, and the aircraft can be safely and reliably landed according to the fault degree and urgency of the aircraft even if the aircraft breaks down seriously and only forced landing can be selected. Through multi-rotor-wing assisting control, the forced landing buffering function of the telescopic empennage assembly and the safety protection measure of a protection sponge lining in the manned cabin, various safety modes and measures such as an internal safety protection air bag, an external safety protection air bag and a forced landing parachute of the manned cabin can be selectively used according to the fault degree and urgency of the aircraft; and safe or low-damage forced landing of the aircraft is realized.

The invention discloses a main wing tilting and folding mechanism for supporting multi-mode variant flight of an aircraft. The main wing tilting and folding mechanism comprises a main bearing plate in a fuselage, a driving mechanism and a central wing, wherein the driving mechanism and the central wing are mounted on the main bearing plate in the fuselage; the driving mechanism comprises a transmission belt mechanism, a driving support arm and two driving rod groups; the transmission belt mechanism is mounted on a main bearing plate in the machine body; the driving support arm is fixed on a main bearing plate in the machine body in a sliding manner and is driven to move back and forth through a transmission belt mechanism; two ends of the driving rod group are respectively hinged with one side of the driving support arm and the corresponding outer wing; the outer wing is connected with the central wing through a crossed roller bearing; in the process that the transmission belt mechanism drives the driving supporting arms to move front and back, the driving rod sets are synchronously driven to move front and back, and therefore the outer wings are driven to rotate around the central wing with the crossed roller bearing as the support. The tilting wing unmanned aerial vehicle has enough high strength, rigidity and stability, and switching among multiple flight modes of the tilting wing unmanned aerial vehicle can be achieved.

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 belongs to the technical field of design of aircraft power devices, and particularly relates to a design method of an aircraft take-off power assisting device. The takeoff power assisting device is installed on the lower portion of an aircraft, the design method comprises the steps that a power module, a connecting module, a control module and a walking supporting module are designed for the takeoff power assisting device, and the power module is used for providing power for the takeoff power assisting device; the connecting module is used for realizing connection and separation of the take-off power assisting device and the airplane; the control module is used for controlling the take-off power assisting device; the walking supporting module is used for supporting the take-off power assisting device to walk. The acceleration of the aircraft in the takeoff acceleration skating process is increased, the takeoff range is shortened, and the takeoff performance of the aircraft is improved; secondly, the empty weight and aerodynamic resistance of the aircraft are not increased in the process of enhancing the take-off performance; and finally, the design constraint of the airborne engine related to the take-off performance is solved, and the airborne engine can be optimally designed completely according to the requirement of high-speed flight.

The invention discloses a hummingbird-imitating flapping wing aircraft with adjustable flapping amplitude, and relates to the technical field of aircrafts, the hummingbird-imitating flapping wing aircraft specifically comprises a main framework of the aircraft, the main framework comprises a front side plate and a rear side plate which are arranged in parallel, the two sides of the front side plate are rotatably connected with flapping wings, and the front side plate and the rear side plate are connected with a driving structure for driving the flapping wings to flap up and down; a posture control mechanism for changing the flight posture of the aircraft is arranged on the rear side of the main framework and comprises a pitching control structure rotationally connected with the rear side plate, and a yaw control structure for driving the two flapping wings to rotate reversely and a rolling control structure for driving the two flapping wings to move in the same direction are arranged on the rear side of the pitching control structure; the flapping wing comprises a rocker arm and a sleeve connected with the rear side plate, the rocker arm is connected with a front edge beam, the sleeve is perpendicular to the front edge beam in position, a wing film is laid between the sleeve and the front edge beam in an extending mode, reinforcing ribs are arranged on the wing film, the flapping wing can have the hovering and level flight capacity, and the flapping amplitude can be adjusted.

The utility model relates to the field of inspection robot power supply, concretely relates to a kind of intrinsic safety type inspection robot lithium battery multipath parallel driving walking structure, including four brushless motors connected with four wheels respectively, the brushless motor all adopt intrinsic safety type, battery pack for its separate power supply is equipped on each brushless motor, the intrinsic safety type inspection robot lithium battery multipath parallel driving walking structure, by the parallel power supply mode of intrinsic safety type lithium battery, 4 intrinsic safety type brushless motor driving of intrinsic safety type inspection robot is driven, realize the intrinsic safety driving design of inspection robot, lighten the robot load weight, improve the cruising ability. Parallel driving walking control structure is powered by 5-way intrinsic safety lithium battery, lithium battery is designed as Ex ib I Mb explosion-proof grade, wherein 4-way is respectively powered to four driving wheels, 1-way is powered to control host computer. After parallel connection of each lithium battery, double overcurrent overvoltage charge-discharge protection of ib grade is realized after battery protection circuit.

The invention provides a vehicle control method and device, electronic equipment and a storage medium, and the method comprises the steps: obtaining a motion path of a vehicle, and dividing the motion path of the vehicle into a plurality of discrete road segment nodes based on a discrete space algorithm; the target speed trajectory of the vehicle is determined based on the speed trajectory optimization constraint condition and a speed trajectory optimization model, the target speed trajectory comprises the speed, the acceleration and the traction force of each discrete road segment node, and the speed trajectory optimization model is used for solving the speed trajectory under the condition of minimum energy consumption based on the speed trajectory optimization constraint condition. Taking the speed trajectory under the condition of minimum energy consumption as a target speed trajectory, wherein the speed trajectory optimization constraint condition comprises parameters of discrete road section nodes; determining a future time period state of the vehicle based on the current state information of the vehicle and the target speed trajectory; a control strategy of the vehicle is adjusted based on the future period state of the vehicle. The cruising ability of the vehicle can be improved at least.