428 results about "Flight stability" patented technology

A hover aircraft employs an air impeller engine having an air channel duct and a rotor with outer ends of its blades fixed to an annular impeller disk that is driven by magnetic induction elements arrayed in the air channel duct. The air-impeller engine is arranged vertically in the aircraft frame to provide vertical thrust for vertical takeoff and landing. Preferably, the air-impeller engine employs dual, coaxial, contra-rotating rotors for increased thrust and gyroscopic stability. An air vane assembly directs a portion of the air thrust output at a desired angle to provide a horizontal thrust component for flight maneuvering or translation movement. The aircraft can employ a single engine in an annular fuselage, two engines on a longitudinal fuselage chassis, three engines in a triangular arrangement for forward flight stability, or other multiple engine arrangements in a symmetric, balanced configuration. Other flight control mechanisms may be employed, including side winglets, an overhead wing, and / or air rudders or flaps. An integrated flight control system can be used to operate the various flight control mechanisms. Electric power is supplied to the magnetic induction drives by high-capacity lightweight batteries or fuel cells. The hover aircraft is especially well suited for applications requiring VTOL deployment, hover operation for quiet surveillance, maneuvering in close air spaces, and long duration flights for continuous surveillance of ground targets and important facilities requiring constant monitoring.

The invention discloses a high-tension transmission line inspection robot based on a multi-rotor aircraft, which comprises a four-rotor aircraft and an inspection system, wherein a double-power module supplies power to the four-rotor aircraft and the inspection system; the four-rotor aircraft comprises a robot body, four rotors, four rotor motors and four rotor motor drivers, the rotors, the rotor motors and the rotor motor drivers are matched, the four rotors are fixedly arranged on respective rotor motors, and the four drivers are respectively connected with respective rotor motors 3; and the inspection system performs shooting and data transmission on high-tension transmission lines. The robot disclosed by the invention performs air flight inspection based on four rotors, and is high in air flight stability and good in inspection speed. Through wireless camera shooting control, a visible light camera can be moved to a position near a suspected fault point so as to realize the emphasized detection of suspected fault points of the high-tension transmission lines.

A robot airplane for tour inspection of power line in counterwise driving structure of coxial double propeller uses two engines to control flight stability, GPS and GIS to confirm flight path, computer processor to adjust flight attitute and battery to provide power for motor, transducer and data link system. Its control system consists of navigation system, autonomous planning system, data link system and on line detection system.

A dual, coaxial rotor helicopter is provided that is relatively easy to fly. Thrust is provided by two ducted fans that are mounted at the rear of the aircraft and spaced apart laterally. Differential thrust generated by the fans provides yaw control for the aircraft, and forward thrust is provided by the fans working in combination. The coaxial rotors are preferably utilized primarily for lift, and not for forward thrust, which simplifies the control requirements. The coaxial rotor with ducted fan configuration also results in lower vibratory loads being imposed on the helicopter, thereby increasing its speed capability. The fan ducts serve to protect the fans, augment the fan thrust at low airspeeds, increase the efficiency of the fans at cruise speeds, and provide horizontal and vertical stabilizing surfaces to ensure aircraft flight stability.

A slider is formed of an air bearing surface coated with a wear limiting coating that substantially limits surface wear of the air bearing surface encountered in proximity recording. The wear limiting coating is comprised of a wear inhibiting layer formed on the air bearing surface and a sacrificial layer formed on the wear inhibiting layer. The two coatings of the wear limiting coating have different mechanical properties so that the sacrificial layer is burnished, exposing the wear inhibiting layer. This design substantially limits the surface wear of the air bearing surface typically encountered in proximity recording, resulting in less debris accumulation, which could otherwise adversely affect the performance of the proximity recording head. This self-limiting burnishing action overcomes the flying height variation due to manufacturing tolerances and provides extremely small and uniform magnetic spacing, which greatly enhances the proximity recording. Moreover, the burnishing action also achieves an improved flying stability and a reduction in the altitude sensitivity.

An aircraft that is housed within a gyroscope providing for improved flight stability that includes an inner hull which remains stationary within a rotating outer hull. A rotating plate includes a groove that traces a sinusoidal pattern around an inside periphery of the plate. Tracking arms have a portion that fit within the groove and another portion that connects to a piston. The rotation of the plate causes the tracking arms to travel within the sinusoidal groove and impart movement on the plurality of pistons which will intake air from above the upper surface of the inner hull configuration and create a negative pressure on the aircraft. The craft contains compression chambers which receive the air and which feed the various impeller thrusters which are rotational within three-fourths of a hemisphere.

The purpose of the present invention is to provide a kind of variable-pitch three-rotor aircraft. The variable-pitch three-rotor aircraft adopts a three-axis structure. Each axis adopts a rotor with a large diameter and low speed. The speed is set at a constant value. The pitch difference controls the balance of the pitching direction of the aircraft. A guide vane with a variable angle is designed under one of the rotors. Under the action of the down swirl generated by the rotor, by changing the angle between the guide vane and the down swirl, the The force of the downward swirl on the deflector, the moment of the force on the center of gravity cancels the counter moment of the rotor. The invention comprises a variable-pitch rotor, a guide vane, a tail pipe and a fuselage. The aircraft has stable flight and strong anti-interference ability, and is especially suitable as an aerial platform for small unmanned aircraft and aerial photography aircraft.

The invention relates to a tilted four-rotor aircraft. The tilted four-rotor aircraft comprises a fuselage, wherein the fuselage is provided with a front wing and a rear wing, two ends of the front wing and two ends of the rear wing are respectively provided with a set of rotor system, and the front wing and the rear wing are respectively and internally provided with a worm-wheel shaft which passes through the fuselage and is used for driving a rotor wing system to do tilted rotating motion; each set of rotor wing system comprises a direct-current brushless motor and a propeller, and the direct-current brushless motor is arranged at the end of the worm-wheel shaft and provided with the propeller. Compared with a conventional tilted double-rotor aircraft, the safety and reliability of the tilted four-rotor aircraft provided by the invention are higher; four rotors have strong lift force, so that the payload, flight radius and flight stability are all greatly improved. The tilted four-rotor aircraft provided by the invention can realize three flight modes, namely a helicopter mode, a transition mode and a horizontal propulsion mode, and has the characteristics of simple structure, high strength, reliable function realization and the like.

The invention relates to an elastic inner cavity type anti-vibration pesticide box for a plant protection unmanned aerial vehicle. The elastic inner cavity type anti-vibration pesticide box is characterized in that a check valve is fixed into a water injection opening, a ball valve is arranged at a water outlet, and a liquid storage bag is arranged between the check valve and the ball valve in a connected manner. The elastic inner cavity type anti-vibration pesticide box has the advantages that the liquid storage bag is elastic and anticorrosion, gaps between the liquid storage bag and a pesticide box are filled with elastic materials, the elastic materials can be compressed when the liquid storage bag is filled with pesticide liquid and is expanded, and can be expanded when the pesticide liquid in the liquid storage bag is reduced and the liquid storage bag is contracted, the gaps between the pesticide box and the liquid storage bag are always filled with the elastic materials, the inner wall of the liquid storage bag always clings to the pesticide liquid, and accordingly the liquid storage bag assuredly always keeps being fixedly positioned in the pesticide box when the plant protection unmanned aerial vehicle shakes; the integral gravity center of anti-vibration pesticide box only can longitudinally change without transverse changing along with reduction of the pesticide liquid in pesticide application procedures of the plant protection unmanned aerial vehicle, accordingly, the integral stability of the pesticide box can be greatly enhanced, and the problem of deterioration of the flight stability of an existing plant protection unmanned aerial vehicle in pesticide application procedures due to vibration of pesticide liquid in an existing pesticide box can be fundamentally solved.

The invention discloses a culvert-type vertical take-off and landing lifting body unmanned aerial vehicle and relates to the technical field of vertical take-off and landing unmanned aerial vehicles.The culvert-type vertical take-off and landing lifting body unmanned aerial vehicle comprises a fuselage (1), lifting force rotor wings (2), a take-off and landing culvert (3), tilting-rotating thrustculverts (7) and tilting-rotating thrust rotor wings (8). The take-off and landing culvert (3) is composed of a through hole penetrating through the upper surface and the lower surface of the fuselage (1), and the lifting force rotor wings (2) are arranged in the take-off and landing culvert (3). The tilting-rotating thrust culverts (7) are hinged to the rear end of the fuselage (1) through tilting-rotating control mechanisms (9), the tilting-rotating control mechanisms (9) are configured to be capable of enabling the included angle between the axis of each tilting-rotating thrust culvert (7)and the axis of the fuselage (1) to be variable, and the tilting-rotating thrust rotor wings (8) are arranged in the tilting-rotating thrust culverts (7). Under the conditions that the vertical take-off and landing capacity of the unmanned aerial vehicle is maintained and the overall weight of the unmanned aerial vehicle is not excessively increased, the flight speed of the unmanned aerial vehicle is increased, the flight stability of the unmanned aerial vehicle is improved, the rotor wing exposed problem is avoided through the culverts, and the flight safety and the take-off and landing hovering efficiency are improved.

The invention provides an unmanned aerial vehicle flight path tracking method adopting adaptive guiding lengths. The method includes the steps that firstly, the relation between the speed of an aerial vehicle and the range of the guiding lengths is determined by considering constraint of dynamic properties of the guidance law and dynamic properties of an unmanned aerial vehicle flight control system in combination with the requirements for real-time performance of the aerial vehicle; then, the distance deviation and the course deviation between a predicted flight path and an expected flight path under the guiding lengths subjected to discrete sampling are calculated and weighted to serve as a criterion for evaluating tracking effects of different guiding lengths; finally, a series of guiding lengths subjected to discrete sampling are evaluated according to the evaluation criterion, the optimal guiding length is obtained, and the unmanned aerial vehicle is guided to track the flight path. The defects that due to the fact that guiding lengths are fixed, the situation that tracking precision is not high, and flight stability and safety are difficult to guarantee probably exists in the flight path tracking process are overcome. In addition, the overshoot severity problem easily occurring under the large initial deviation condition and in the way point switching process can be well solved.

The invention provides an electromagnetic drive insect-like flapping-wing micro air vehicle. Two wings are respectively connected with two ends of a carapace through flexible hinges; the wings, the carapace and a baffle block form a 'baffle' structure; the carapace is rigidly connected to a chest; a cylindrical permanent magnet is attached to the center position at the lower part of the chest; a spiral coil is attached to the center position at the upper part of a machine body opposite to the permanent magnet; the spiral coil and the permanent magnet are respectively located at the upper side and the lower side of each wing when being assembled; and the spiral coil overlaps with the axis of the permanent magnet. By adopting the traditional four-connecting rod drive mechanism, the transmission efficiency of the air vehicle is greatly improved; better flight stability can be obtained by adjusting the center of gravity to overlap with a lift center; by adopting simple structures of the flexible hinges and the baffle block, a certain degree of passive reverse can be obtained in a flapping process due to interaction of inertia force and aerodynamic force; the assembly precision is improved by folding and assembling; and miniaturization of the air vehicle is easily achieved.

The invention provides a multi-rotor-wing unmanned plane which comprises a flight control assembly, a rack, a plurality of motors, a plurality of motor seats and a plurality of propellers. The rack comprises a machine body, a plurality of supports, a plurality of first connectors and a plurality of second connectors. The flight control assembly is arranged on the machine body, each support comprises a supporting rod and a swing rod, the supporting rods are connected with the machine body, one end of each swing rod is movably connected with the corresponding supporting rod through the corresponding first connector, and the included angles between the supporting rods and the swing rods are changeable; the other ends of the swing rods are provided with motor seat mounting portions, the motor seats are provided with connection shafts, the connection shafts are connected with the motor seat mounting portions, the second connectors are connected with the connection shafts and the motor seat mounting portions respectively, the motors are connected with the motor seats, and the propellers are connected with the motors. The multi-rotor-wing unmanned plane has the advantages of being simple in structure, flexible and convenient in angle adjustment operation, wide in application range, high in flight stability and high in interference resistance.

The invention discloses a heavy-load low-structure-complexity double-coaxial-twin-rotor unmanned aerial vehicle, wherein rotor transmission mechanisms are arranged at the left side and the right side of a vehicle body of an unmanned aerial vehicle body; through transmission mechanisms arranged on the unmanned aerial vehicle body, power is transmitted to the rotor transmission mechanisms arranged at the two sides of the unmanned aerial vehicle body through driving shafts; the rotor transmission mechanisms transmit the power to an upper rotor and a lower rotor through an upper rotor transmission rod and a lower rotor transmission rod via the transmission among four mutually engaged bevel gears; and the identical-rotating-speed and opposite-direction rotation of the upper rotor and the lower rotor is realized. A total variable-pitch mechanism is arranged between the upper rotor transmission rod and the upper rotor, and the regulation of the pitch angle and the roll angle of the unmanned aerial vehicle is realized; a variable-total-pitch mechanism is arranged between the lower rotor transmission rod and the lower rotor, the regulation of the total pitch of the unmanned aerial vehicle is realized; and the yaw angle and the total lift of the unmanned aerial vehicle are controlled. The heavy-load low-structure-complexity double-coaxial-twin-rotor unmanned aerial vehicle has the advantages that the characteristics of heavy effective load and high output power are realized; and a redundancy design method is adopted, and the flight stability of the unmanned aerial vehicle is improved through the design of multiple rotors and multiple sets of variable-pitch mechanisms.

The invention relates to the technical field of an unmanned aerial vehicle, in particular to a mixed layout unmanned aerial vehicle, which comprises a vehicle body, fixed wings, an empennage and a propulsion motor, wherein the fixed wings are fixed at the two sides of the vehicle body; the empennage is arranged at the tail part of the vehicle body; the propulsion motor is arranged at the back part of the vehicle body; a paddle is arranged on an output shaft of the propulsion motor; the middle part of the vehicle body is provided with a strip-shaped installing hole; a four-rotor folding mechanism is arranged in the strip-shaped installing hole. Unique multi-rotor vehicle arms capable of realizing wireless one-key folding are used, so that the unmanned aerial vehicle can take off or land like a rotor aircraft; when the unmanned aerial vehicle is about to enter a fast cruise stage, the four vehicle arms can be collected back to the two sides of the vehicle body, so that the unmanned aerial vehicle can fly in a fixed wing airplane mode. The relative streamline type vehicle body conforms to the aerodynamic requirements better than the multi-rotor; higher speed and smaller wind resistance can be realized; the integral flight stability of the mixed layout unmanned aerial vehicle is improved.

A lubricant is provided that can form a sufficiently thin one-molecule film surface even when it is highly polymerized. When used for a magnetic recording medium lubricant layer and / or a head slider lubricant layer of a magnetic recording device, it can make the film thickness of the lubricant layers very small, with the result that it can furnish an increased reliability to the magnetic recording device in a wide temperature-range environment without damaging the flying stability. This lubricant comprises a fluorine-containing polymer having a specific structure. Such a fluorine-containing polymer can be manufactured by reacting a compound having a specific structure and 1,3-butadiene diepoxide.

The invention relates to a composite rotor craft. The composite rotor craft comprises a craft main body, an energy device, a plug-in connector and a control device, wherein the craft main body comprises a main propeller and a plurality of auxiliary propellers; the main propeller comprises a main rotor I, a main rotor II and a main duct; the main rotor I and the main rotor II are fixed in the main duct through a main duct supporting frame; the part, in the main duct, of the outer edge of the main duct supporting frame is provided with a plurality of vertical connecting rods; cantilevers are outward and horizontally arranged at the bottoms of all the vertical connecting rods; the auxiliary propellers are arranged at the outer ends of all the cantilevers. The composite rotor craft has the benefits that the integration of various rotor flight modes is adopted, the flight efficiency is greatly improved, the flexibility of the craft is greatly improved, and the flight stability and reliability are also greatly improved; an advanced flight control mode is adopted, a plurality of rotors can be simultaneously controlled and adjusted, the control difficulty of the craft is greatly reduced, and the flight efficiency of the craft is improved.

The invention relates to a tilt-three-rotor craft. The tilt-three-rotor craft comprises a craft body, a pair of wings and three groups of rotor systems, wherein the wings are symmetrically arranged on two sides of the craft body, and the rotor systems are arranged on the craft body; a front rotor tilting shaft for driving the rotor systems to do titling motion are arranged in the wings, one group of rotor system is arranged at each of two ends of the front rotor tilting shaft, and the third group of rotor system is arranged at the rear end of the craft body. The tilt-three-rotor craft has the beneficial effects that vertical take-off and landing functions of a traditional helicopter can be realized, and a high-speed cruising function of the craft can be realized by tilting the three pairs of the rotors to the horizontal position; by utilizing three tilt rotors, the craft has good symmetry and high safety and high reliability; the three rotors have large lifting forces, so that the effective load, the flight radius and the flight stability are greatly improved. The tilt-three-rotor craft has the advantages of simple structure, high strength, reliability in realizing of the functions and the like.

An improved cruciform or cross parachute is formed by attaching the adjacent edges of the lateral arms to each other to form a three-dimensional canopy, when inflated, which is substantially square at the top and substantially round at the lower edge. The attachment of the adjacent edges of the arms are such as to provide generally vertical openings or vents through which air can flow outwardly from underneath the canopy, which form "corner air flow jets", thus allowing use of zero or near zero porosity fabric for constructing the canopy. Attachment of the adjacent edges of the arms at their outer tips forms a continuous hem at the lower edge of the canopy which eases packing and improves reliability. Arm air flow jets of U.S. Pat. No. 5,839,695 may also be included in addition to the corner air flow jets formed by attaching the adjacent arm side edges. Air flow from underneath the canopy through the air flow jets should be sufficient to achieve a degree of flight stability for the parachute of .+-.5.degree., or less, when using a zero or near zero porosity fabric for the canopy.

The invention, which belongs to the electromechanical technology field, provides a realization method applied to an unmanned aircaraft control terminal. The control terminal system is composed of a hand-controlled control panel, a tablet computer, and a wireless data link transmission radio station. The hand-controlled control panel provides a function of real-time control on aircraft flight for control personnel; the design of a key rocking bar is similar to the design of a remote controller of an ordinary model plane, wherein the design of the remote controller of the ordinary model plane is familiar to general control personnel, so that it is convenient for the control personnel to understand how to the use the hand-controlled control panel and to user it. According to the invention, beneficial effects of the provided realization method are as follows: because a function for displaying a flight state and a flight path of an aircraft and a hand-controlled control function are integrated into one, it is convenient for control personnel to carry out contrast operation; therefore, a flight stability augmentation control system with low cost can be used to replace an expensive self-driving flight control system that is generally employed by an unmanned aircraft system; and meanwhile, a convenient and visual control auxiliary function can be provided to the greatest extent; the control difficulty is simplified; working efficiency is improved; and a work burden is reduced.

A flying disc for use in recreational activities and sports, such as for catch and throw, Ultimate, disc golf, and the like. The flying disc is configured for enhanced flight characteristics, throwability, trick shot capability and durability. The flying disc includes a circular flight deck section and an outer rim connected thereto. Contoured features are provided in a pattern in the flight deck section. The contoured features define cavities in the flight deck section and protrude beneath the flight deck section. The contoured features provide a variety of gripping positions on the top and bottom of the disc for generating greater snapping force when releasing the disc. The contoured features also create a Coanda effect that stabilizes the disc during flight. And, since the contoured features are recessed from the top of the flight deck section, the advantages of flight stability are achieved without a loss of flight distance.

The invention discloses an unmanned aerial vehicle flight control method. The unmanned aerial vehicle flight control method comprises the steps of detecting a running state of an unmanned aerial vehicle, obtaining corresponding proportional integral differential (PID) parameters according to the running state of the unmanned aerial vehicle, outputting a control instruction according to the obtained PID parameters so as to control the rotation speed of a motor. The invention further discloses an unmanned aerial vehicle flight control device. By means of the unmanned aerial vehicle flight control method and device, the flight stability of the unmanned aerial vehicle can be improved.

The invention provides an unknown input observer based realization method of fault diagnosis for a minitype unmanned aerial vehicle distributed formation. According to a hierarchical concept of a distributed control system, controller designs of the single unmanned aerial vehicle and multi unmanned aerial vehicle formation are studied to ensure the flight stability of the minitype unmanned aerialvehicle distributed formation. When a fault of a single unmanned aerial vehicle final controlling element occurs, an effective unknown input observer distributed system fault detection method is provided, which completely decouples interference and completely eliminates adverse effects of the external interference on a fault diagnosis process. Furthermore, a method to estimate the fault by extending a state vector and a fault vector into an augmented vector is provided. According to the invention, the conventional unknown input observer is combined with an augmented system to realize fault detection, separation and estimation of the minitype unmanned aerial vehicle distributed formation. According to known minitype unmanned aerial vehicle model parameters, a numerical simulation can be established to carry out fault diagnosis on the final controlling element. The fault diagnosis method is used for fault diagnosis of a minitype unmanned aerial vehicle distributed formation.

The invention provides an aircraft, which belongs to the field of aircrafts. The aircraft provided by the invention comprises a frame; a first jib arm unit, which is installed on the frame; a second jib arm unit, which is installed on the frame; and a rotor wing power unit, which is arranged at the outer ends of the first jib arm unit and the second jib arm unit; wherein the first jib arm unit is provided with a first telescopic unit, the first jib arm unit is installed on the frame through a first rotating shaft, and a first rotation power unit is mounted on the frame and drives the first rotating shaft to rotate. According to the invention, a jib arm can rotate around the frame and enables the frame to be telescopic; in the running process of the aircraft, the flight attitude of the aircraft is adjusted through rotation of the rotating shaft, so wind resistance is reduced; as the jib arm is provided with the first telescopic unit, stretching or contraction of the jib arm is realized; when the jib arm contracts, the windward area of the jib arm can be reduced, which enables wind resistance to be further reduced and benefits crossing of narrow space; and when the jib arm stretches, the flight stability of the body of the aircraft is improved.

The invention discloses a switching system-based modeling and adaptive control method for a cargo handling unmanned gyroplane, relates to a modeling and adaptive control method for a cargo handling unmanned gyroplane, and aims at solving the problems that the motion mode of the unmanned gyroplane is disturbed and the flight stability is affected due to massive sudden increase or sharp reduction of the unmanned gyroplane at the moments of cargo grabbing and delivery. The method comprises the following steps of (1) building a position dynamics switching model of the cargo handling unmanned gyroplane; (2) determining an attitude dynamics model of the cargo handling unmanned gyroplane; (3) building an error dynamics model for trace tracking of the cargo handling unmanned gyroplane; (4) designing a switching adaptive controller and an adaptive updating law; (5) proving the system stability of two sub-modes of the cargo handling unmanned gyroplane and determining tracking time; and (6) proving the overall stability of the unmanned gyroplane in executing a cargo handling task and determining mode dependence dwell time. The switching system-based modeling and adaptive control method is applied to the field of unmanned plane flight control.