426 results about "Flight stability" patented technology

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 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.

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 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.

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 variable pneumatic layout structure for a projectile body, and particularly relates to a variable pneumatic layout structure capable of combining the stability of the projectile body in a free flight stage and the hitting accuracy of the projectile body in a correction stage. A variable pneumatic shape scheme is adopted; an empennage is locked into a small-empennage pneumatic layout in an original free flight section of a trajectory, so that the flight stability of the projectile body can be ensured, resistance can be reduced, and the range can be prolonged; in a tail section of the trajectory, the empennage is unfolded into a large-empennage pneumatic layout, so that the static stability of the projectile body is improved, projectile body attitude angle oscillation caused by surging force can be rapidly converged, and the requirements of a control system can be met. According to the variable pneumatic layout structure for the projectile body, the advantages of a fixed-empennage pneumatic layout and the large-empennage pneumatic layout are combined, so that a requirement on the static stability of the projectile body can be met, the influence of the projectile body attitude angle oscillation caused by surging force on the control system can be reduced, the range can be ensured, and a requirement on the correction accuracy can also be met; multiple range tests show that the scheme is feasible.