44 results about "Aerodynamic drag" patented technology

Embodiments of the present application provide a wind speed estimation method, device and aircraft. In the wind speed estimation method, flight data of the aircraft is obtained, and then a horizontal disturbance acceleration of the aircraft in a navigation coordinate system is obtained according to a vertical acceleration, a horizontal acceleration and an attitude angle of the aircraft in the navigation coordinate system in the flight data. Further, an air resistance of the aircraft in the horizontal direction is obtained according to a mass of the aircraft and the horizontal disturbance acceleration of the aircraft in the navigation coordinate system. Finally, the wind speed of the flight environment of the aircraft is obtained according to the air resistance and a speed of the aircraft relative to the navigation coordinate system, so that the wind speed of the flight environment of the aircraft can be estimated, the accuracy of the wind speed estimation is improved, and in the flight adaptation to different climate environments, only a few key parameters need to be adapted, so that the engineering practicability of the model is greatly improved.

The invention discloses an elastic compensation jet device and a using method and a design method thereof, and belongs to the technical field of high-speed jet. In order to solve the problems that a traditional jet device and a use method are seriously limited in use scene, the advantages of jet fluid cannot be played when the traditional jet device is used on an uneven bearing surface, and the speed of jet flow is seriously attenuated due to the influence of air resistance, the invention provides the elastic compensation jet device, and a jet part is connected with a mobile carrier through an elastic compensation structure; according to the using method, when the movable carrier drives the jet flow part to work through the elastic compensation structure, high-speed fluid sprayed out of the jet flow nozzle is in a film shape. A series of defects and limitations of low efficiency, poor effect, large fluid flow, easy abrasion of a working surface, limited use scene and the like of a traditional jet mode are overcome, and the beneficial effects of high efficiency and high-standard jet are achieved.

This application provides a vehicle emergency braking control method, vehicle, and related equipment, belonging to the field of vehicle braking control technology. The method determines whether an emergency braking condition is currently occurring based on collected sensor data. If an emergency braking condition is present, it determines the current collision risk value based on the relative distance to obstacles and the theoretical braking distance. Based on this collision risk value, the vehicle's aerodynamic components are adjusted to improve the overall vehicle's drag coefficient. The higher the current collision risk value, the higher the drag coefficient corresponding to the target state of the aerodynamic components. This solution considers the relative distance to obstacles during emergency braking, calculates the risk value that may still result in a collision under emergency braking conditions, and then adaptively adjusts the aerodynamic components based on this risk value, thereby improving the safety and stability of the vehicle's emergency braking process.

This invention discloses a pneumatically drag-reducing autonomous underground robot and its control method, belonging to the field of underground robot technology. It includes a wedge-shaped head, a front shell, a rear shell, an electric actuator, anchoring units, a pneumatic system, and a control system. The wedge-shaped head ejects compressed gas in the forward direction. The wedge-shaped head is fixedly mounted at the front end of the front shell, which is positioned at the front end of the rear shell. The electric actuator is located within the cavity of the rear shell, driving either the front or rear shell to move. Two anchoring units are located on either side of the front shell to provide anchoring force. The pneumatic system provides compressed gas to the wedge-shaped head. The control system controls the operation of the electric actuator and the gas ejection, enabling the pneumatically drag-reducing autonomous underground robot to move autonomously in the soil. This invention not only significantly improves exploration efficiency but also effectively reduces reliance on external equipment, lowers labor costs and exploration time, while simultaneously improving the accuracy and real-time performance of exploration data.

An aerial mobility vehicle includes a wing extending from a fuselage of the aerial mobility vehicle; a folding portion disposed at an edge portion of the wing, configured to extend from the wing to form a portion of the wing during unfolding of the folding portion, and configured to move to coincide with the wing to reduce an air resistance area of the wing in a vertical direction during folding of the folding portion; an actuator connected to the folding portion and configured to power the folding portion to unfold or fold to the wing; and a controller connected to the actuator and configured to control the actuator to fold the folding portion during vertical takeoff and landing of the fuselage, and configured to control the actuator to unfold the folding portion during cruising of the fuselage.

An airless tire coupled to a rim is disclosed. The airless tire includes a contact portion that extends along the circumferential direction of the tire and has a predetermined width, at least a portion of which contacts the ground when the tire rotates, a coupling portion that is coupled to the rim, side portions that are formed extending from both sides of the contact portion along the tire surface to the coupling portion, and a plurality of side grooves that are arranged radially with respect to the center of rotation of the tire and are formed as recesses in the side portions. The airless tire is lightweight, has low rolling resistance, has excellent heat dissipation due to increased surface area, and can reduce air resistance by improving the airflow along the side of the tire during driving.

This utility model discloses a blade, a propeller, and an aircraft, belonging to the field of aircraft technology. The blade includes a connected root and a shaft. The root has a root centerline, and the distance from the end of the blade furthest from the root to the root centerline is a first length. At the first position of the blade, the angle of attack is 18.38°±2.5°; at the second position, the angle of attack is 9.58°±2.5°; and at the third position, the angle of attack is 6.61°±2.5°. The distance from the first position of the blade to the root centerline is 20% to 25% of the first length; the distance from the second position of the blade to the root centerline is 50% to 58% of the first length; and the distance from the third position of the blade to the root centerline is 80% to 95% of the first length. The blade of this utility model, through the design of the angle of attack at multiple key positions of the main body of the propeller shaft, reduces air resistance and improves aerodynamic efficiency. The propeller and aircraft of this invention improve the aerodynamic efficiency of the propeller and the flight efficiency of the aircraft.

The application belongs to the technical field of aerospace manufacturing, and discloses a high-performance ceramic matrix composite functional surface for hypersonic transition regulation and control. Based on a numerical simulation method, a hypersonic cone transition process of a microstructure functional surface with different microstructure parameters is predicted, and the influence of the microstructure parameters on the transition position and aerodynamic drag is obtained. The microstructure functional surface design is completed by comprehensively considering the ceramic matrix material manufacturing constraints. The corrugated wall microstructure is manufactured by ultrasonic vibration assisted grinding, and the micro-hole array is processed by femtosecond laser. According to the segmented integrated manufacturing concept, a plurality of simulation cone sample pieces with the microstructure functional surface are processed. The simulation cone sample pieces with the microstructure functional surface are tested in a wide speed range in a hypersonic wind tunnel. According to the wind tunnel test data and the results of the numerical simulation, a high-fidelity data set and a low-fidelity data set are established, a multi-fidelity surrogate model is constructed, the microstructure parameters are subjected to multi-objective optimization, and an optimal solution set is obtained.

The present application relates to the technical field of unmanned aerial vehicle flight control, and relates to an unmanned aerial vehicle wind resistance adaptive control method based on real-time environment sensing, which comprises issuing a desired rotating speed instruction to an electronic speed regulator according to an attitude control loop, synchronously acquiring actual quadrature axis current and absolute physical acquisition time; extracting a quadrature axis current sequence to identify and update rotor aerodynamic drag coefficients and motor viscous friction coefficients; combining the identified coefficients to calculate a desired quadrature axis current and construct a time domain reference sequence, deducing a synchronous desired quadrature axis current and subtracting the actual quadrature axis current, mapping actuating current residuals into single-rotor disturbance torque residuals; inverting a three-dimensional wind speed vector of the machine body and using a confidence decay coefficient to correct and generate an effective wind field vector; calculating a dynamic weighted feedforward control vector and fusing it with a feedback control vector to solve a desired angular velocity instruction and execute wind resistance control. The present method does not require a physical anemometer, and can realize environment wind field sensing and adaptive feedforward compensation only by online identification of underlying electrical data and parameters.

This utility model discloses a blade, a propeller, and a drone, belonging to the field of aircraft technology. The blade includes a connected root and a blade body. The root has a root centerline, and the distance from the end of the blade furthest from the root to the root centerline is a first length. The blade angle of attack is designed at multiple positions at a distance of the first length from the root centerline. This utility model reduces air resistance and improves aerodynamic efficiency by designing the angle of attack at multiple key positions of the blade. The blade profile is optimized, resulting in lower torque within a higher speed range, thereby reducing the motor's output power and increasing the drone's endurance. The aerodynamic efficiency of the propeller is improved, thus enhancing the drone's flight efficiency.

This application provides a method, apparatus, device, and medium for maintaining the configuration of low-Earth orbit satellite formations, which can solve problems such as frequent control, high fuel consumption, and shortened on-orbit life caused by ignoring the differences in aerodynamic drag between satellites in related technologies. The method includes: acquiring the difference in the semi-major axis decay rate between a reference satellite and a companion satellite in the formation; predicting the relative drift trajectory of the companion satellite relative to the reference satellite in the velocity direction based on the difference in the semi-major axis decay rate and the initial semi-major axis difference; determining an orbital control strategy based on the relative drift trajectory and a preset configuration maintenance threshold; executing the orbital control strategy to adjust the orbital altitude of the companion satellite when the drift reaches or exceeds the configuration maintenance threshold; resetting the semi-major axis difference after adjusting the orbital altitude of the companion satellite, and returning to the step of acquiring the difference in the semi-major axis decay rate.

This aircraft improves upon the shortcomings of the Osprey, offering a highly economical, high-speed VTOL aircraft that surpasses it in both performance and functionality. [Solution] By employing two types of propellers, a propeller and a main rotor, as thrusters for the VTOL aircraft of this invention, the structurally complex and heavy tilt rotor mechanism becomes unnecessary, simplifying the aircraft's structure and reducing manufacturing and operating costs. The lighter aircraft also improves maneuverability and extends the range. Furthermore, in fixed-wing mode, the main rotor is stopped, and the arms of the rotor fixing device mounted on the aircraft are extended to completely catch the main rotor and maintain an attitude that minimizes air resistance. By using the propeller as the thruster for horizontal flight and stopping the rotation of the main rotor, air resistance is minimized, making it possible to achieve a maximum speed exceeding that of the Osprey.

The application discloses a six-leaf misplacement superposition storage type on-board wind power generation and drag reduction mechanism, and belongs to the technical field of on-board power generation and aerodynamic drag reduction of floating aircrafts. The mechanism is composed of a tail sealing storage cabin, an expansion rod, a generator set, six-leaf misplacement superposition blades, a locking mechanism with an end face sealing disc, an expansion hub mechanism, an electric control sliding and pushing mechanism, a cabin door opening and closing system and a fan fixing base. The expansion hub is internally provided with a blade driving assembly, which can drive the blades to be mispositioned and superposed in a centripetal manner around the hinge points, and the whole machine can be slidably stored along the cabin axis. The device can automatically switch working conditions according to the flight speed of the airship, develops power at low speed, and is stored at high speed to reduce drag; the six-leaf symmetric layout ensures that the gravity center of the whole machine is in the middle, the locking mechanism cooperates with the cabin door to realize sealing, and the streamline shape of the airship body is maintained. The application has stable structure, considers power generation endurance and flight performance, and is suitable for various large floating airships.

This utility model provides a vehicle with a closed wheel and a closed wheel assembly, including: a rim, a bracket assembly, and a sealing plate; the bracket assembly is provided inside the rim, the bracket assembly includes an integrally formed hub and several spokes, and a sealing plate is provided between two adjacent spokes and the rim, each sealing plate has a through hole near the hub, and one sealing plate is provided with an air valve position. This utility model, while ensuring the advantage of closed wheels in reducing air resistance, effectively reduces unsprung mass by optimizing structural parameters, which helps to improve the vehicle's handling, ride comfort, acceleration performance, and braking performance.

The application discloses a motorcycle drag reduction and noise reduction optimization design method based on a bionic technology, and comprises the following steps: S1, simulating and analyzing a flow field and a sound field during motorcycle driving; S2, determining a position of a concave-convex structure based on the simulation analysis result of the flow field and the sound field of the motorcycle in S1; S3, designing and optimizing parameters of the concave-convex structure through an artificial intelligence optimization design platform; and S4, manufacturing the concave-convex structure according to the parameters of the concave-convex structure obtained in S3, installing the concave-convex structure to a target position of the motorcycle, and completing the design. The application can change the air flow mode to achieve the target of aerodynamic drag reduction and aerodynamic noise reduction through the bionic flow control method from the flow nature, and simultaneously avoids active control means to avoid increasing the system complexity, and realizes an integrated solution of aerodynamic drag reduction and aerodynamic noise reduction.

This invention relates to the field of aerodynamics and provides a racing car aerodynamic device with attitude adaptive function. It includes a monocoque casing and further comprises: a front wing adjustment device, including: a front suspension motion structure for driving the front wing drive mechanism; a front wing drive mechanism for adjusting the angle of attack of the front wing flaps; a front wing including front wing flaps; and a rear wing adjustment device, including: a rear suspension motion structure for driving the rear wing drive mechanism; a rear wing drive mechanism for adjusting the angle of attack of the rear wing flaps; and a rear wing including rear wing flaps, an inner bulkhead, and a rear wing endplate. The rear wing flaps are disconnected by the inner bulkhead, and the rear wing flaps are rotatably connected to the rear wing endplate. This invention can suppress the shift of the wind pressure center under braking conditions, reduce aerodynamic drag under acceleration conditions, and improve the handling stability of the racing car at high speeds under roll conditions; it also reduces the attitude sensitivity of the racing car's aerodynamics.

An impeller with a plurality of blades that extend between a first wheel disc and a second wheel disc of the impeller can be configured for use within a centrifugal fan of a range hood. The plurality of blades of the impeller can each form a sawtooth segment that includes oblique teeth that function to reduce the effects of air resistance on the operation of the impeller and reduce the noise generated by the impeller in use. The oblique teeth of each sawtooth segment can be arranged such that the dimensions of the oblique teeth gradually decrease as the sawtooth segment extends from the first wheel disc toward the second wheel disc to further improve the functionality of the impeller.

A rim for a motor vehicle for optimizing the aerodynamic drag of the motor vehicle. The rim includes a rim bed for securely seating a tire on the rim, a base structure including a hub ring for improving the rolling performance of the rim, spokes arranged between hub ring and rim bed, and at least two accommodating cavities each having at least one cover element accommodated therein to form an at least partially closed base structure.

An aerial vehicle (AV) 100 includes a rotor system 150 with a set of rotor arms 152 and a set of propellers 154 to provide a lift force during a vertical take-off of the AV 100; and a set of landing gears movably coupled to the rotor arms 152 for movement between a deployed position to support the aerial vehicle 100 during landing and take-off, and a retracted position to form an enclosure 210 around the set of propellers 154 to reduce aerodynamic drag during a forward movement of the AV 100 after the vertical take-off. The sets of landing gears can includes a pair of L-shaped landing gears 200, a C-shaped cross sectional landing gears, an another C-shaped cross sectional landing gears, a U-shaped slidable landing gears, and a flap-shaped slidable landing gears.

The application discloses a car cover capable of reducing aerodynamic drag and an application method thereof, and relates to the technical field of aerodynamic drag reduction. The car cover comprises, from bottom to top, a release layer, a glue layer, a drag reduction microstructure base layer, a surface coating layer and a transparent protective film which are arranged in sequence in layers; the cross section shape of the rib is different in height isosceles triangle, wherein the base of the isosceles triangle is arranged on the base layer; the top angle of the isosceles triangle is 20-90 degrees; and the drag reduction microstructure base layer is designed and processed on the basis of the current car cover for protecting car paint, so that the aerodynamic performance of the car is improved.

This invention discloses a modular folding aircraft based on solar panels, comprising an aircraft fuselage, landing gear, inner wing section, middle wing section, outer wing section, a modular structure, and solar panels. The fuselage is a streamlined structure, the landing gear is a tailwheel type and positioned below the fuselage, the three wing sections are located on both sides of the fuselage, and are symmetrically distributed with the fuselage. The three wing sections are connected by the modular structure, which allows the three wing sections to fold and unfold. Flexible solar panels are mounted on top of the three wing sections. The advantages of this invention are that the aircraft is equipped with a flight control system, enabling autonomous flight. It can autonomously fold and deform to change its flight attitude, reducing air resistance. Simultaneously, it can adjust the folding angle of the three wing sections according to the angle of sunlight to better absorb solar energy, thereby improving photoelectric conversion efficiency and achieving long-endurance functionality.

This invention provides a dynamic performance testing system for equipment based on turntable servo control and load torque simulation. The system includes: a simulation and command generation module for running a semi-physical simulation model of the equipment under test (BT), determining the expected motion trajectory of the BT in a virtual combat environment, and generating disturbance torque commands and motion control commands; a data communication and control module for sending motion control commands to each rotary axis of the five-axis turntable to control the BT to reproduce the expected motion trajectory; a load torque application module for sending disturbance torque commands to a load torque simulator and applying disturbance torques of air resistance and mechanical friction to the rotary axes, and real-time monitoring of the actual motion posture data of the BT under the disturbance torque; and a performance testing module for comparing and analyzing the actual motion posture data with the expected motion trajectory to obtain the performance parameters of the BT. This significantly improves the realism and accuracy of equipment dynamic performance testing and evaluation.

The present invention relates to the field of aircraft technology and discloses an aircraft and its arm. The aircraft arm, applicable to an aircraft, comprises an arm main body and an external extension part, which are integrally formed. The external extension part extends radially outward and forms a structure that gradually tapers along a first direction, wherein the external extension part comprises a streamlined surface structure to reduce aerodynamic drag during flight. The integral molding and connection of the arm main body and the vertical stabilizer in this disclosure can improve the stiffness of the vertical stabilizer surface, reduce the risk of loosening or of detaching of the vertical stabilizer, decrease the number of parts, and reduce weight.

This application relates to the technical field of aerodynamic drag reduction, and in particular to a method and system for aerodynamic drag reduction of trains. The method includes: establishing a numerical simulation model of the train's aerodynamic characteristics, simulating and analyzing the turbulent flow field structure around the train, and determining specific flow locations associated with aerodynamic drag reduction; setting up blowing and suction control regions of different ranges at the specific flow locations, and analyzing and determining the active drag reduction control region with drag reduction effect; setting air vents in the active drag reduction control region, performing normal blowing and suction control through the air vents, analyzing and obtaining the variation curve of the aerodynamic drag reduction rate with train speed and blowing and suction control parameters, obtaining the normal blowing and suction mode with drag reduction effect and the critical velocity value based on the variation curve, and establishing a flow velocity control database; and performing active aerodynamic drag reduction control based on the flow velocity control database. This application achieves the effect of accurately determining the active drag reduction control region with drag reduction effect and performing aerodynamic drag reduction control at the required locations.

This invention discloses an adaptive route optimization method for unmanned aerial vehicles (UAVs) that considers boundary layer turbulence effects. It acquires meteorological observation data, remote sensing image data, and reanalysis data within the flight airspace as multi-source data. A boundary layer turbulence feature acquisition module calculates turbulence feature parameters within the flight airspace based on the multi-source data, constructing a three-dimensional turbulence feature field. A dual-channel energy consumption prediction module constructs aerodynamic drag energy consumption models and attitude control energy consumption models respectively through its aerodynamic drag energy consumption prediction channel and attitude control energy consumption prediction channel, and then superimposes them to obtain a comprehensive energy consumption prediction model. A turbulence-sensitive cost map construction module uses the comprehensive energy consumption prediction model and introduces a turbulence risk penalty factor to calculate the comprehensive energy consumption cost of each grid, generating a turbulence-sensitive cost map. An adaptive route optimization module employs an improved heuristic search algorithm to perform route search and dynamic optimization based on the turbulence-sensitive cost map, aiming to find the optimal route from the starting point to the destination with the minimum energy consumption.

The present invention provides a vehicle flow path assembly and a vehicle that can reduce air resistance and improve aerodynamic performance. [Solution] The flow path assembly comprises a first flow path member 1 and a second flow path member 2, wherein a first flow path is formed inside the first flow path member 1, and the first flow path has a first flow path opening and a second flow path opening, and a second flow path is formed inside the second flow path member 2, and the second flow path has a third flow path opening and a fourth flow path opening, the second flow path opening is used to communicate with the fourth flow path opening, and the first flow path and the second flow path are connected to have at least a first flow path path, in the first flow path path, the third flow path opening is for introducing a first fluid medium, and the first flow path opening is for releasing the first fluid medium.

The application discloses a bogie bottom drag reduction cladding plate and a high-speed train bogie, and the cladding plate comprises a torsion bar cladding plate for cladding a torsion bar of a bogie frame, a first cladding plate for connecting a cross beam on one side of the torsion bar, and a second cladding plate for connecting a cross beam on the other side of the torsion bar. The first cladding plate and the torsion bar cladding plate form a first flow guide slope, the second cladding plate and the torsion bar cladding plate form a second flow guide slope, and the flow guide directions of the first flow guide slope and the second flow guide slope are symmetrically arranged. The application guides the airflow originally acting on the region near the center pin hole and the torsion bar to the lower side of the torsion bar cladding plate, optimizes the partial cladding and flow guide of the originally complex and abrupt bottom profile near the center pin hole and the torsion bar, forms a relatively continuous bottom flow guide surface, weakens the direct interference between the airflow and the complex components of the bottom, reduces the local flow separation, backflow and vortex intensity, improves the bogie bottom flow field distribution, and further achieves the purpose of reducing the aerodynamic drag of the bogie region.

The application discloses a simulation analysis method for aerodynamic characteristics of a high-speed rocket sled-track system, and establishes a mathematical model and a finite element model of the rocket sled-track system, obtains the dynamic response of the rocket sled through numerical solution, and performs comparison and verification; a fluid domain is constructed according to the geometric shape of the rocket sled and three-dimensional characteristics of a flow field, global grid division of the flow field of the rocket sled is performed, and a finite element model is constructed; an RNG k-ɛ turbulent flow model is adopted, an inlet flow velocity and an outlet pressure boundary are set, aerodynamic drag and its coefficient acting on the rocket sled are analyzed and obtained, and aerodynamic load input is provided; a coupled dynamic model of the rocket sled-track system is constructed, a rigid-flexible coupled model of the sled-track system of a flexible track structure is established; track irregularity numerical excitation is reconstructed, and data of track irregularity of the rocket sled-track system are obtained; initial conditions and boundary conditions are set, different working conditions of the rocket sled under different Mach numbers with or without aerodynamic drag load are simulated, and the motion parameters of the mass center of the rocket sled are obtained. The application provides an analysis method for studying the influence of aerodynamic drag on the dynamic response of the rocket sled-track system.