31results about How to "Take off and land smoothly" patented technology

The invention provides a rotor-type unmanned aerial vehicle automatically adjusting a gravity center after loading and an adjustment method. The rotor-type unmanned aerial vehicle includes a machine body provided with a rotor assembly, the bottom of the machine body is provided with a testing device for supporting the machine body to test the weight and the gravity center of the machine body and a translational mechanism connected with the machine body; the translational mechanism comprises a mobile output end for fixing a load. According to the rotor-type unmanned aerial vehicle automatically adjusting the gravity center and the adjustment method, a gravity center position of the unmanned aerial vehicle is controlled through installation of the testing device and the translational mechanism on the machine body, so that the unmanned aerial vehicle can perform smooth taking-off and landing and safe landing, and the security of the unmanned aerial vehicle is improved; and the adjustment method is simple in process, enables detection and adjustment to be carried out from time to time, and is applicable to a working condition that requires to frequently modify the machine body.

The invention discloses a solar energy charging rising and landing platform of an unmanned aerial vehicle. The solar energy charging rising and landing platform of the unmanned aerial vehicle comprises a supporting plate, a rising and landing platform, solar panels and a storage battery, wherein the supporting plate is of a rectangular structure, four supporting seats are mounted on the lower portion of the supporting plate in a welded mode, supporting legs are mounted on the supporting seats through hinge pins, the rising and landing platform is connected with the upper portion of the supporting plate through a plurality of springs, the table board of the rising and landing platform is arranged as a rectangular structure with a same size as the supporting plate, the solar panels are arranged on edges of four side faces of the supporting plate, each solar panel is rotatably connected with the supporting plate through hinges, the storage battery is connected to the solar panels, a plug is connected to the storage battery, the hinges are fixed to the solar panels and the supporting plate in a welded mode, and the supporting legs are telescopic rods. Integrally, the solar energy charging rising and landing platform of the unmanned aerial vehicle has the advantages of being convenient to carry, good in shock absorption, and having the solar energy charging function.

The invention provides a double-duct tilt aircraft. The double-duct tilt aircraft comprises duct rotor seats, a machine body, duct rotors, flaps, driven synchronous pulleys, synchronous belts, a driving synchronous pulley, an undercarriage, a turbine, a main wing, a storage battery set, a cockpit, an electronic operating device, a hydraulic power unit, a servo motor, a worm, a worm support, driven bevel gears, driving bevel gear shafts, a kerosene reciprocating engine, first cranks, first hydraulic cylinders, second hydraulic cylinders and second cranks. The flying speed and posture of the double-duct tilt aircraft are controlled by the duct rotors, the flaps and the main wing jointly, so that the double-duct tilt aircraft has the characteristics of being large in lift force, smooth and steady in taking off and landing and high in air flying speed. The cockpit is arranged on utmost upper portion of the double-duct tilt aircraft, so that a pilot has a good sight range, and the operation of the double-duct tilt aircraft is greatly facilitated. The main wing can be driven by the servo motor to rotate by 90 degrees and keep parallel to the machine body when parked, so that space is saved, and traffic jam in a city is eased.

The invention discloses an unmanned aerial vehicle for air route survey of air traffic. The unmanned aerial vehicle comprises an unmanned aerial vehicle head, an unmanned aerial vehicle body, a pair of side wings, a first balance wing, a second balance wing and a balance tailstock, wherein a radar height sensor, a Beidou positioning sensor, an ultrasonic detector and an infrared detector are arranged in the unmanned aerial vehicle head; a storage battery and a signal match are arranged in the unmanned aerial vehicle body, and an electric quantity detector is arranged below the unmanned aerialvehicle body; an information processor is arranged next to the electric quantity detector, and a command locker is arranged next to the information processor; a signal receiver is arranged below the command locker, and a wireless charging receiver is arranged below the signal receiver; and a positioning camera is arranged next to the wireless charging receiver, and a positioning supporting foot isarranged at the lower end of the unmanned aerial vehicle body. The unmanned aerial vehicle can maintain good stability and balance performance when encountering obstacles, severe weather and other special environments, self-charging can be realized, a locking mechanism is provided, instructions cannot be input from the outside during locking, and the situation of falling caused by the power consumption of the unmanned aerial vehicle when the unmanned aerial vehicle is instructed by the outside can be avoided.

The invention discloses a concrete abrasion resistance test system which comprises a concrete abrasion mechanism, a machine frame and a water inlet mechanism. The machine frame comprises an outer fixed machine frame body and an inner movable machine frame body. The concrete abrasion mechanism comprises a stirring motor and a cylinder. The cylinder comprises an outer cylinder body and an inner cylinder body. The water inlet mechanism comprises a water inlet pipe, a first hose and a first valve. A cylinder cover is arranged on the top of the inner cylinder body, and comprises two semicircular covers. Semicircular holes are correspondingly formed in the centers of the two semicircular covers and combined into a circular hole. A transparent inspection window is formed in the side wall of the outer cylinder body. The left side and the right side of the top of the outer fixed machine frame body are downwards connected with a first electric push rod and a second electric push rod respectively. The lower portion of the rear end of the outer fixed machine frame body is fixedly connected with a third electric push rod. The invention further discloses a concrete abrasion resistance test method using the concrete abrasion resistance test system. The test efficiency is improved, labor intensity is reduced, remote monitoring and control can be achieved, and good application and popularization value is achieved.

The invention relates to an unmanned aerial vehicle take-off and landing platform which comprises a box body composed of a bottom plate, side plates and a top plate; the bottom plate and the side plates are hinged; the side plates are fixedly connected through buckles, and the side plates and the top plate are fixedly connected through buckles; a plurality of third springs are evenly distributed on the bottom plate, a supporting plate is fixed to the top ends of the third springs, a plurality of supporting rods are hinged to the side wall of the supporting plate, free ends of the supporting rods are connected with the bottom plate in a sliding mode, and the top face of the supporting plate is used for parking an unmanned aerial vehicle. Protection devices are arranged on the side plates. According to the unmanned aerial vehicle, the springs are arranged on the bottom plate and the side plates, so that a damping device can be formed, acting force caused by bumping and vibration can be offset in the transportation process, and safe transportation of the unmanned aerial vehicle is guaranteed.

The invention discloses A landing gear for a snowy aircraft, relating to technical field relate to aircraft landing gears. The gear, include an airframe, the lower surface of the machine body is provided with a through hole, and the lower surface of the inner wall of the machine body is fixedly connected with a fixing rod, the right end of the fixing rod is fixedly connected with a driving device,The driving device is meshed with the second gear, and the driving device is positioned in the through hole. The inner wall of the second gear is fixedly connected with the rotating device. The rotating device is clamped on the inner wall of the U-shaped plate, and the lower surface of the rotating device is fixedly connected with the top end of the load-bearing pillar. The left side surface of the U-shaped plate is fixedly connected with the right side surface of the support plate. The landing gear for the snowy aircraft is provided with an electric motor, a first gear, a second gear, a bearing, a rotating shaft, a support column, a sleigh and a crawler, thereby realizing the smooth take-off and landing of the aircraft, avoiding the occurrence of skid and tire depression when the aircraft takes off and landing on the snowy ground, increasing the stability of the aircraft and reducing the discomfort of passengers.

The invention provides a manned flying saucer, relating to the technical field of aircrafts. The manned flying saucer comprises an electric automatic control system, a first-grade vacuum chamber and a second-grade vacuum chamber. A solar cell panel is installed on the top of the first-grade vacuum chamber; the second-grade vacuum chamber is arranged outside the first-grade vacuum chamber; a direct-current motor system is mounted on the bottom of the first-grade vacuum chamber and comprises a main engine rotor and stators locating at both sides of the main engine rotor; a storage battery pack is arranged around the direct-current motor system; a personnel cabin and a magazine are arranged at the periphery of the direct-current motor system; an auxiliary engine is arranged at the bottom of the second-grade vacuum chamber; air suction windows are arranged along the outer edge of the manned flying saucer; an atmospheric pressure highly-sensitive sensor is arranged at the lower end of the second-grade vacuum chamber and between the personnel cabin and the magazine; and a vertical-lift air suction window is arranged at the connection place of the second-grade vacuum chamber and the first-grade vacuum chamber. The manned flying saucer provided by the invention takes off and lands steadily, can stay in air for a long time and fly at a fast speed, is exempt from interference of electric waves and influence of road and weather conditions, is safe in flight, occupies a small area when landing and is especially applicable to aerial surveillance, command and urgent repair in the industries like the power supply industry, traffic and marine accident rescue, anti-terrorism and antiriot action and police enforcement.

The invention particularly relates to an indicator drive circuit structure for realizing five attack angle states of an airplane. The structure comprises an indicating lamp L1 (identification symbol:'V'), an indicating lamp L2 (identification symbol: '('), an indicating lamp L3 (identification symbol: ')') and an indicating lamp L4 (identification symbol: 'inverted V'). The brightness of the indicating lamp L1, the indicating lamp L2, the indicating lamp L3 and the indicating lamp L4 is logically controlled respectively by using different combination modes of the attack angle large signal A,the attack angle normal signal B and the attack angle small signal C, so that five states of large attack angle, relatively large attack angle, normal attack angle, relatively small attack angle and small attack angle are realized. The beneficial effects of the invention are that the whole circuit achieves five indication states, provides more accurate attack angle information for a pilot, adjuststhe attack angle in time in the take-off and landing and flight processes, guarantees the normal operation of take-off and landing, avoids the stall risk of a critical attack angle, and guarantees the stable flight.

The invention discloses a fixed wing aircraft model. The fixed wing aircraft model comprises an aircraft body, fixed wings fixed on the two sides of the aircraft body and a front duct power unit and a back duct power unit, wherein the front duct power unit is vertically arranged in the middle of the aircraft body, air flow generated by the front duct power unit faces the lower surface of the aircraft body, the back duct power unit is connected to the tail of the aircraft body through a back duct fixing seat, and different angles are formed between the back duct power unit and the aircraft body through rotation of a back duct rotating seat around the aircraft body. According to the fixed wing aircraft model convenient for vector control over flight forms, vertical take-off and landing are achieved, level flight can be achieved through the fixed wings, a precise vector control mechanism is arranged, and the flight modes are stably and quickly switched.

A lifting machine for electric emergency repair, comprising a base plate fixedly installed on the bottom surface and a top plate fixedly installed on the high-altitude iron frame, two guide rods corresponding to the left and right are fixedly installed between the base plate and the top plate, and two The take-off and landing spiral rod between the guide rods, the take-off and landing platform is installed on the take-off and landing screw-shaped rod, and the left and right sides of the take-off and landing platform are correspondingly provided with guide holes, the guide holes are matched with the guide rod, and the guide rod A guide sleeve is also slidably installed on the top, and the upper end surface of the guide sleeve is fixedly connected with the lower end surface of the lifting platform. A wedge panel is also fixedly installed between the front end of the guide sleeve and the bottom end of the lifting platform. The slot and the vertical slot connected with the horizontal slot, a sliding plate is installed in the accommodation cavity in the landing platform to slide up and down, and a sliding slot extending front and back is arranged in the guide sleeve, and the sliding slot is installed in the sliding slot. There is a sliding frame, which is provided with a hollow groove that allows the guide rod to penetrate, and the rear end wall of the hollow groove is set as an annular surface, and an annular pressing piece is fixedly installed on the annular surface.

The invention is suitable for the technical field of power grid operation, and provides an unmanned aerial vehicle attached operation system. The system comprises an unmanned aerial vehicle body; an attachment operation assembly which is used for cable high-altitude attachment operation and comprises an attachment machine, wherein the unmanned aerial vehicle attachment operation system further comprises a flexible take-off and landing assembly which comprises a first steering engine, a steering engine support, a first connector and a first connecting rod mechanism and further comprises a flexible operation assembly. The flexible operation assembly comprises a base, a second connector, a second steering engine, a second connecting rod mechanism, a spring and a guide rod. The unmanned aerial vehicle body and the attached operation assembly are arranged, the unmanned aerial vehicle is used as a carrier, and the unmanned aerial vehicle has the advantages of being good in maneuverability, easy to control, high in efficiency, low in high-altitude operation risk and capable of achieving high-altitude operation, low-altitude operation and boundary cable operation at the same time. The system also provided with a flexible take-off and landing assembly, so stable landing take-off and landing and stable flight and hovering operation of the unmanned aerial vehicle body are guaranteed; and a flexible operation assembly which is arranged, so that the attitude stability and smooth off-line of the unmanned aerial vehicle body during operation are facilitated.

The invention discloses an unmanned aerial vehicle parking apron used in a river. The parking apron comprises a lifting platform and a floater, the floater is connected under the lifting platform; thesurface, in contact with a water body, of the floater is a convex arc surface; a connector is arranged at the lowest point of the cambered surface; the connector is connected with a multi-section scale type flow guide plate, the multi-section scale type flow guide plate is provided with a plurality of sections capable of swinging relatively, the plurality of sections can swing under the action ofwater flow and are finally consistent with the water flow in direction, and the length of the multi-section scale type flow guide plate enables the multi-section scale type flow guide plate to exceedthe range covered by the lifting platform; the multi-section scale type flow guide plate is divided into a narrow section and a wide section in the length direction of the multi-section scale type flow guide plate according to the width, the end of the narrow section is connected with the connector on the floater, and the wide section is formed by rotationally connecting a plurality of sections.The connector of the floater is also connected with a gravity anchor through an anchor rope. According to the invention, the unmanned aerial vehicle parking apron can be stably parked on the flowing water surface without generating unnecessary rotation, and therefore taking-off and landing of an unmanned aerial vehicle are facilitated.

The invention discloses a method for measuring the positioning precision of a movable pulley in a ship lifting system. The method specifically comprises the following steps: installing a three-dimensional steel wire debugging device on a bulkhead, and placing a temporary bracket on the ground at the other opposite side; fixing one end of a steel wire rope on the three-dimensional steel wire debugging device, and hanging a heavy object at the other end to be supported on the temporary bracket; measuring whether the distances from the top of the movable pulley to the steel wire rope are equal atdifferent positions during dynamic operation, and if so, determining that the parallelism of the movable pulley meets the requirement; adjusting the three-dimensional steel wire debugging device to move the steel wire rope to the side of a hydraulic press guide rail; and measuring whether the distances from the side surfaces of the movable pulley to the steel wire rope at different positions during dynamic operation are equal, and if so, determining that the symmetry of the movable pulley meets the requirement. According to the invention, the parallelism and the symmetry degree of the movablepulley can be rapidly measured, and the mounting and positioning precision of the movable pulley is effectively ensured, so that the stable and safe lifting of the lifting platform is ensured.