86 results about "Aerospace engineering" patented technology

The invention discloses a foldable wing extensible in wingspan .The foldable wing comprises a front wing, a rear wing, a base and an actuating system, wherein the front wing comprises a left front inner wing and a right front inner wing which are arranged symmetrically, the rear ring comprises a left rear wing and a right rear wing which are arranged symmetrically, the end of the left front inner wing and the end of the right front inner wing are hinged and installed to one end of the base though front wing installing shafts, the actuating system is arranged at the other end of the base, a left front outer wing and a right front outer wing which slide in the length directions of the inner wings are respectively arranged on the left front inner wing and the right front inner wing, one end of the left rear wing and one end of the right rear wing are hinged and installed to a sliding block, the other end of the left rear wing and the other end of the right rear wing are in hinged connection with the left front outer wing and the right front outer wing, and the sliding block is driven by the actuating system to longitudinally move along the base back and forward .The foldable wing is large in wingspan variation amplitude and small in occupied space, leans against the base when being folded, the left front outer wing and the right front outer wing are rotatably unfolded around the front wing installing shaft, meanwhile the left front outer wing and the right front outer wing increase the wingspan width, a lift force and the lift-drag ratio are increased, and the flight efficiency is improved .

Disclosed are a cooling control device and method for an injection mold. The cooling control device comprises a controller, a water inlet pipe, an upper end cooling flow channel, a water outlet pipe and a lower end cooling flow channel, and the water inlet pipe, the upper end cooling flow channel, the water outlet pipe and the lower end cooling flow channel are arranged in the injection mold and are connected sequentially. A water inlet of the upper end cooling flow channel and a water inlet of the lower end cooling flow channel are connected with the water inlet pipe. A water outlet of the upper end cooling flow channel and a water outlet of the lower end cooling flow channel are connected with the water outlet pipe. The controller is connected with the water inlet end of a cooling circuit, the water outlet end of the cooling circuit and the inner surface of the injecting mold. The controller collects and calculates the temperature difference of working media of the upper end cooling flow channel and the lower end cooling flow channel, and the surface temperature difference of the injection mold, and adjusts the flow of a medium in the cooling circuit according to the temperature differences, so that the cooling of the injection mold is achieved. The cooling control device and method for the injection mold are reasonable in design, simple in structure, capable of reducing the rejection rate, and small in buckling deformation of an injection member.

An internal combustion engine exhaust cooling and removal apparatus includes a heat exchange assembly connected to an exhaust pipe of an internal combustion engine. A flexible hose is connected to the heat exchange assembly, and an exhaust fan assembly is connected to the flexible hose. Use of the internal combustion engine exhaust cooling and removal apparatus of the invention provides a clean air environment in an indoor confined space by removing the engine exhaust gases which are hazardous to one's health. The apparatus of the invention is especially useful with non-electric powered tools and machines, such as for indoor excavations with diesel-powered excavators or other construction equipment. The apparatus of the invention can also be used with diesel-powered saws.

The invention discloses an unmanned aerial vehicle automatic patrolling method for a direct current single-circuit tension tower. The method comprises the steps that S1, key patrolling points of the direct current single-circuit tension tower are determined; S2, shooting key points and flight path key points in the patrolling process are selected, and a patrolling flight route is set; S3, manual patrolling is conducted according to the set patrolling flight route, and in the patrolling process, coordinates of the flight path key points, coordinates of the shooting key points and angles of thehead of an unmanned aerial vehicle and a cloud deck at the shooting key points are collected; S4, according to the data collected in the manual patrolling process, an automatic flight task and an automatic shooting task of the unmanned aerial vehicle are generated; S5, the generated patrolling tasks are uploaded to the unmanned aerial vehicle, the unmanned aerial vehicle is controlled to automatically fly completely according to the tasks, when the unmanned aerial vehicle arrives at the shooting key points, the flight direction of the head of the unmanned aerial vehicle and the angle of the cloud deck are automatically adjusted, after in-place adjustment, a camera is trigged to shoot, and the unmanned aerial vehicle returns to the taking off point until all the tasks are completed. The method effectively solves the problems that manual patrolling for the direct current single-circuit tension tower is large in stress, low in safety and not high in efficiency.

The present invention provides an unmanned aerial vehicle transmission line inspection work site planning safety distance test method. The method comprises: an unmanned aerial vehicle model placement step, arranging an unmanned aerial vehicle model at a preset distance position at the side or the lower portion of a simulation transmission line; an voltage applying step, switching on a power generator, and applying voltage to the simulation transmission line until the unmanned aerial vehicle model generates sporadic discharge; and a recording step, recording the first discharge voltage value of the unmanned aerial vehicle model which generates sporadic discharge, and determining the preset distance as a site planning safety distance between the unmanned aerial vehicle model and the simulation transmission line under the first discharge voltage. The unmanned aerial vehicle transmission line inspection work site planning safety distance test method provides data support for the unmanned aerial vehicle inspection work through obtaining of the relation of the size and the material of the unmanned aerial vehicle model, the type and the size of the discharge voltage type and the site planning safety distance so as to improve the reliability of the unmanned aerial vehicle inspection work.

A ventilation load-reducing apparatus, which has a simple structure and is capable of further improving the efficiency of the heat recovery, and a vehicle air conditioner using the same are proposed. The ventilation load-reducing apparatus includes an inside air lead-out path 4 for ventilation which leads air of a vehicle-interior out of a vehicle from a rear side of the vehicle-interior, an outside air lead-in path 5 which leads outside air into a front side of the vehicle-interior, a ventilation heat recovery device 6 which recovers heat from the air led out through the inside air lead-out path 4, a recovered heat radiator 7 which releases the heat on the air led in through the outside air lead-in path 5, and a heat transmitter 8 which transmits the heat between the ventilation heat recovery device 6 and the recovered heat radiator 7. The ventilation load-reducing apparatus is independent of a refrigerant circulating system 9 of a vehicle air conditioner 2.