SUBSTANCE: invention relates to lifting equipment. Aerostatic lifter comprises flying lifting vehicle connected with surface power supply and control device via load-carrying electric cable (3) wound on the drum mounted on self-propelled platform. Flying-lifting vehicle comprises undercarriage (6), frame (7), and carcass (8) fitted on the frame to accommodate rotors (9) and stators (10) of rotor drives. Aforesaid self-propelled platform can carry undercarriage of aforesaid flying vehicle. Fixed carcass (8) accommodates a pair of coaxial rotors (9) running in opposite directions driven by drive stators with their armatures (11) mounted on frame (7). Aerodynamic surfaces (13) are arranged in inductive airflow zone to rotate driven by motors about their horizontal axes (15), when controlled from the surface power supply device via load-carrying electric cable (3). The latter device allows controlling flying vehicle horizontal and vertical directions.
EFFECT: higher mobility and expanded application range.
6 cl, 3 dwg
The invention relates to the field of technology, in particular to lifting devices, and can be used for lifting cargo and/or people in a variety of ways both at sea and on land.
Known aerodynamic containing swivel base, hinged on this basis sectional cargo boom drive its rotation in the vertical and horizontal planes, two symmetrically arranged longitudinal vertical plane cargo boom aerodyne power plant, which is equipped with a platform through which they established at the end of the root section of a cargo boom can be rotated relative to the platform relative to the longitudinal axis of the cargo boom. (USSR author's certificate No. 1397365 A1. Device for transfer of cargo at sea. - IPC4: VW 27/30. - Bull. No. 19, 23.05.88). A disadvantage of the known device is that it has a cargo boom, one end of which is hinged to the rotary Foundation, and others, requiring focus, which severely limits its capabilities.
The closest analogue of the present invention is a flying device for lifting and moving goods containing frame, chassis and mounted on the frame stators, which are placed in frames with blades and drives their rotation in the opposite directed the s, can move in vertical and horizontal directions when the Ground control by cable or by radio. Each blade is made of canvas or elastic material and attached one end to the frame and the other to the stator of the rotation drive (Patent RU №2097311 C1. Aerial device for lifting and moving goods. - IPC6: 66F 11/00, VS 29/00, VS 27/20. - 1997.11.27). The invention adopted for the prototype.
A disadvantage of the known device, taken as a prototype, is the lack of mobility and a large weight of the device, limiting the payload and low reliability and safety in operation.
The main task, which is aimed by the invention, is to increase mobility and payload, the expansion of the scope.
The technical result achieved the proposed technical solution is to increase the mobility and the expansion of the scope.
This technical result is achieved in that, in the famous aerodynamic, including aerial lifting device, which includes a chassis, a frame mounted on the chassis frame, which houses the blades and the stator drives the rotation of the blades in opposite directions to move the aircraft to the lifting device in a vertical and g is horizontal directions when the Ground control by cable or by radio, according to the proposed technical solution
the frame is stationary, it has a pair of coaxially spaced blade screws for rotation in opposite directions through the stator of the actuator, the armature of which is mounted on the frame and coupled with the control system spins a blade screws in the area of inductive air flow generated by rotation of the blades, installed aerodynamic surface can be rotated around its horizontal axis when managing with the ground device power supply aerial lifting device through the carrying cable spooled on the drum ground device, or on the radio;
ground device power supply and control systems aircraft lifting device mounted on a self-propelled platform with the ability to consolidate on her chassis aerial lifting device;
the carrying cable is connected to the shaft of the anchor aerial lifting device above the horizontal plane passing through the center of gravity of the aircraft to the lifting device;
on the upper end of the shaft of the anchor is set, for example, the radiosonde, isolated from the environment of the radio waves hood;
aerial lifting device equipped with a parachute device is m, mounted on the frame and connected to the halyard with the shaft of the anchor;
the frame is made niches for the placement of the payload.
Given the applicant an analysis of the level of technology has allowed to establish that the analogs are characterized by the sets of characteristics is identical for all signs declared aerodynamica, no. Therefore, the claimed technical solution meets the condition of patentability "novelty".
Search results of known solutions in this field of technology in order to identify characteristics that match the distinctive features of the prototype of the characteristics of the proposed technical solution, showed that they do not follow explicitly from the prior art. Of certain of applicant's prior art there have been no known impact provided the essential features of the claimed technical solution of transformations on the achievement of the technical result. Therefore, the claimed technical solution meets the condition of patentability "inventive step".
1 schematically shows the proposed aerodynamic; figure 2 - aerial lifting device, a side view in section, figure 3 is the same, top view.
Aerodynamic contains aerial lifting device 1, is connected to the ground unit 2 energy supply and management pose the STV carrying electric cable 3, spooled on the drum 4 mounted on self-propelled platform 5 (figure 1). Aerial lifting device 1 includes a chassis 6, frame 7 mounted on the chassis frame 8, which houses the blades 9, and the stator 10 drives the rotation of the blades 9 (figure 2). Self-propelled platform 5 ground device 2 is made with the possibility of fixing on her chassis 6 aerial lifting device 1. The frame 8 is stationary, it has a pair of coaxially spaced blade screws 9, rotating in opposite directions through the stator 10 of the actuator, the armature 11 which is installed on the shaft 12 fixedly mounted on the frame 7. In the area of inductive air flow generated by rotation of the blades 9, installed aerodynamic surface 13 can be rotated using actuators 14 around its horizontal axis 15 to the control ground unit 2 energy supply aerial lifting device 1 through the carrying cable 3 and moving aerial lifting device 1 in the vertical and horizontal directions with Ground control cable 3 or on the radio (figure 3). The shaft 12 is hollow on the upper end of which is installed, for example, the radiosonde 16, isolated from the environment of the radio waves by the cap 17. The carrying cable 3 is connected to laitat is determined as being lifting device 1 in the cavity of the shaft 12 above the horizontal plane 18, passing through the center of gravity 19 aerial lifting device 1, the latter equipped with a parachute device 20 mounted on the frame 8 and the United halyard 21 with the shaft 12. The frame 8 is made of a niche 22 for placement unit 23 of the control aerial lifting device 1 and the payload.
Aerodyna installation operates as follows.
In the transport position of the aircraft lifting device 1 mounted on the chassis 6 on self-propelled platform 5. When lifting the flying device 1 initiate a ground unit 2 energy supply from which power is fed to the armature 11 through the carrying cable 3. Armature 11 is put into rotation of the stators 10 and fixed on them blades 9 propellers, and in opposite directions, compensating between a reactive force of the rotating blades with the help of block 23, which create the possibility of rotation of the aerial lifting device 1 in the horizontal plane 18 and steady flight. Under the action of the lifting force P caused by the rotation of the blades 9, is the rise of the flying device 1 with the tension of the unwinding of the carrying cable 3 from the drum 4 mounted on self-propelled platform 5. Aerodynamic surface 13 located in the area inducting the air flow inside the frame 8, created by the rotation of the blades 9 by rotation around its horizontal axis 15 when the flight control from block 23 with the ground control device 2 through the carrying cable 3, create a stable steady rise aerial lifting device 1. In steady state, the blades 9 transmit lifting force P through the stator 10 on the shaft 12 fixed to the frame 7, the latter raises the frame 8, which is made of a niche 22 to accommodate payload. When controlling the aerodynamic surfaces 13 and the rotation speed of the blades 9 with the ground control device 2 through the carrying cable 3 or radio aerial lifting device 1 set move both in vertical and in horizontal directions, and the necessary corrective actions can be made by calculation on the computer in block 23, which has all the characteristics of the working bodies of aerodynamica. In case of an emergency in the air aerodynamic ejects the parachute device 20, which is on file 21 for the shaft 12 lowers aerial lifting device 1 to the ground.
The proposed aerodynamic allows you to raise aerial lifting device 1 with a payload of 250 kg to a height of up to 200 meters
1. Aerodynamic, including aerial lifting device is, which includes a chassis, a frame mounted on the chassis frame, a stator, and has the ability to move in vertical and horizontal directions when the ground control by cable or by radio, wherein the frame is made immobile, in which is placed a pair of coaxially spaced blade screws for rotation in opposite directions through the stator of the actuator, the armature of which is mounted on the frame and coupled with the control system spins a blade screws in the area of inductive air flow generated by rotation of the blades, installed aerodynamic surface can be rotated around its horizontal axis when managing with the ground device power aerial lifting device through the carrying cable spooled on the drum ground device, or on the radio.
2. Aerodynamic according to claim 1, characterized in that a ground device power supply and control systems aircraft lifting device mounted on a self-propelled platform with the ability to consolidate on her chassis aerial lifting device.
3. Aerodynamic according to claim 1, characterized in that the carrying cable is connected to the shaft of the anchor aerial lifting device above the horizontal plane passing through prices is p of gravity of the aircraft to the lifting device.
4. Aerodynamic according to claim 1, characterized in that on the upper end of the shaft of the anchor is set, for example, the radiosonde, isolated from the environment of the radio waves hood.
5. Aerodynamic according to claim 1, characterized in that the aerial lifting device equipped with a parachute device mounted on the frame and connected to the halyard with the shaft of the anchor.
6. Aerodynamic according to claim 1, characterized in that the frame is made niches for the placement of the payload.
SUBSTANCE: proposed device comprises outer suspension and cargo orientation system. The outer suspension incorporates crosspiece with hauling cables furnished with cargo grippers. The crosspiece is coupled, via two converging links, with flight vehicle lock. The cargo orientation system incorporates two drives mounted on fuselage. Every drive is connected, via flexible link and deflecting block, with one end of the said crosspiece. To compensate for flexible link length variation in flight, the orientation system additionally comprises, for aforesaid every drive, lever pivoted to the fuselage. The said lever accommodates additional deflecting unit fitted on one end of the lever and enveloped by the flexible link and is coupled with spring-loaded appliance arranged on the fuselage. The axle of one of the said deflecting units on every lever can be aligned with the lever axis of rotation. The other deflecting is fixed on the lever free end. Note that both levers can be spring-loaded by means of single acting power cylinders, or by torsions.
EFFECT: increased range of helicopter operation in civil and erection works, higher safety and easier crew operation.
4 cl, 2 dwg
SUBSTANCE: docking device contains "П"-shaped portal in form of two posts with cross-piece secured on tops, polyspasts of cargo hoisting device installed in portal posts, load grippers secured on free ends of flexible elements of polyspasts. Docking device has arch and second portal, portals are wheeled and are connected with each other at top by longitudinals. Arch consists of cross-piece and two columns attached to it, and it is mounted so as to be movable along longitudinals, on arch columns polyspasts of cargo hoisting device are installed with load grippers secured on free ends of flexible elements of polyspasts. On cross-pieces of portal with polyspasts and on arch capable of turning in vertical transversal plane there are installed two levers with block on each of them, flexible elements of polyspasts with load grippers secured are passed through blocks. Each lever is equipped with rotary mechanism.
EFFECT: increase in workability during lifting and shifting in docking of articles.
FIELD: technological processes.
SUBSTANCE: incrustation imitation is an article with front surface including substrate surface areas and picture formed by front surfaces of decorative elements. Each element in face-work has a basically prism-shaped base. At least one element is decorative and has at least one head in the form of embossed nose with face surface on the upper base basement. Lower base basements in the face-work lie in the same plane, side facet of each base contacts at least one another base, the substrate is solid, and elements are fixed in the article by substrate material. Method of incrustation imitation manufacturing involves composition of a picture out of face surfaces of decorative elements and element fixation in the substrate. Decorative elements with basically prism-shaped base and at least one at least one head in the form of embossed nose with face surface on the upper base basement are used, the nose having a face surface. Also space elements consisting of bases without heads are used in face-work. Lower base basements are placed in the same plane, face surfaces form a picture model, and each base is put tightly to the adjoining bases, so that adjoining base side facets abut each other. Then an imitation is formed by positioning bases inside the imitation and face element surfaces on the surface, and the substrate is cast.
EFFECT: significantly increased picture exactness and durability.
9 cl, 7 dwg
SUBSTANCE: hydraulic ram consists of a set of power hydraulic rams arranged on a frame, the spaces, via common manifolds, communicating with the pumping station. Hydraulic ram subpiston and superpiston spaces are connected in pairs with the pressure and drain manifolds via controlled gate valves to shut off one or several sets of the said hydraulic rams. Rulers and rods with a pointer are arranged on a fixed and movable hydraulic ram parts, respectively. Air feed and return manifolds communicate with the hydraulic ram upper spaces and air feed control gate valves. Blocks are arranged on along the reactor cover circumference to facilitate remote control over the reactor cover jointing with the grip in limited working space and to add to radiation safety. The pan with interlocks is arranged in the gap between the hydraulic ram set and the reactor cover lower surface, attached thereto.
EFFECT: load lifting without skew, measurement of the load motion regularity, draining water from hydraulic ram spaces and higher radiation safety.
4 cl, 5 dwg
FIELD: devices for equipment movement in vertical and horizontal positions during equipment positioning.
SUBSTANCE: device comprises a set of three panels and guiding grooves for support rollers created in adjacent panel surfaces. Groove directions in upper-central panel system are transversal to that of central-lower panel system. Device also has mutual panel displacement mechanism made as screw pair arranged between panels of each pair. Spherical support end of load jack screw is installed in upper plate socket through bearing. Lifting pivot is arranged on load jack body. Flange having extension to be connected to side surface of equipment frame is also made on flange body. Each row of support rollers is included in separator. Knurled band created on each support roller is located in central part thereof. Slots adapted to receive movable plates are created in support surfaces of guiding grooves for roller receiving in working area of roller knurl zone. The plates are faced with resilient material, namely with rubber layer from roller side. The plates are pressed to knurled bands by means of springs.
EFFECT: simplified structure and increased usage convenience.
FIELD: civil engineering; lifting and transporting facilities.
SUBSTANCE: invention relates to devices for mounting of loads mainly in flooring apertures, and it can be used for accurately directing load to building axis of mounted object with orientation to azimuth when carrying out mounting operation using flying vehicle, for instance, helicopter. Proposed device contains two rods some ends of which are connected to load, and guide for each rod. Each guide is made in form of two curved members whose lower parts are secured vertically at place of mounting parallel to each other with clearance, and upper parts are made diverging for catching and directing rods and tilted relative to building axis of mounted object for catching load swinging on external hanger of helicopter. Each rod is provided with section weakened in vertical, as compared with its strength in horizontal direction arranged at definite distance from place of load fastening.
EFFECT: enlarged sphere of application owing to provision of possibility of load mounting through confined apertures of floorings.
2 cl, 4 dwg
FIELD: mechanical engineering; lifting and transporting mechanisms.
SUBSTANCE: proposed mechanism has support on which load carrier is installed for turning relative to support on axle. According to first design version, carriers are installed ion turning axle of load carrier and on part of support peripheral relative to axle of turning of load carrier on corresponding shaft. Said carriers turnable together with load carriers and driven from its turning mechanism are furnished with mechanically intercoupled wheels. Some of the last are arranged for engagement with wheels rigidly secured on support concentrically relative to axle of carrier turning. According to other design version, two carriers turnable together with load carrier or two carriers driven by its turning mechanism are arranged on peripheral part of support relative to axle of turning of load carrier on corresponding shafts for turning, said carriers are furnished with mechanically intercoupled wheels. Some wheels are arranged for engagement with wheels rigidly secured on support concentrically relative to axle of turning of carriers.
EFFECT: reduced power intensity of vehicle load carrier suspension mechanism.
14 cl, 13 dwg
FIELD: mechanical engineering, in particular, handing equipment used for direct mounting of vertical elongated structures.
SUBSTANCE: lifter has vertical columns made in the form of rigidly connected paired telescopic poles and fitted with supporting shoes, bearing traverses and double-acting power cylinders. Extension-type parts of pair of telescopic poles are oriented in opposite directions. Bearing traverses are joined to upwardly directed extension-type parts, and supporting shoes are joined to downwardly directed extension-type parts. Each vertical column has individual upper shoulder with carriage and individual lower shoulder with carriage. Each of shoulders and respective carriages is located on extension-type part of respective telescopic pole. Shoulders are pivotally connected to respective carriages through power cylinders. Each of said shoulders is rigidly connected to immovable part of respective telescopic pole. Each of said shoulders and carriages has wedges for fixing thereof on extension-type parts of respective telescopic poles. To do that, said shoulders and carriages are provided with axial conical cavities, and said wedges are located in said cavities so that pressing of wedges to extension-type parts of telescopic poles may be adjusted. Carriages have lower and upper wedges.
EFFECT: increased efficiency of lifter owing to reliable lowering of bearing traverses to initial position, spreading apart of vertical columns and lifting of structures on site at altitude difference in the absence of foundation.
2 cl, 10 dwg
FIELD: mechanical engineering.
SUBSTANCE: invention relates to suspension mechanisms of vehicle load carrier and it can be used in different branches of industry. Proposed suspension has crank axle-shafts upper crank of which is connected for turning with vehicle support, and lower crank is connected for turning with load carrier and mechanism to balance load carried and mechanism to balance load carrier and mechanism to balance load carrier and mechanism to balance load carrier in horizontal plane relative to upper crank of axle-shaft. Said mechanism has slot made on side wall of load carrying by means of which side wall engages with upper crank of corresponding axle-shaft or with boss on support, it has bosses made on vehicle support and engaging with lower crank of axle-shaft.
EFFECT: improved balancing of load carrier.
FIELD: mechanical engineering; load-lifting facilities.
SUBSTANCE: proposed device contains load-carrying shaft with suspension hinge unit and rotation lock, slinging gears with wire ropes and damper. Damper is arranged between load-carrying shaft and suspension hinge unit, and being made in form of hollow housing with cover and vertical output shaft with collar, and between cover and collar of shaft of elastic member, and lower end of output shaft is connected with suspension hinge unit. Elastic member is made in form of hollow cylinder manufactured of elastomer. Radial clearance between outer surface of elastic member and damper housing and radial clearance between inner surface of elastic member and output shaft are chosen to conform to required conditions.
EFFECT: protection of drive members from overloads, reduced dynamic loads.
2 cl, 2 dwg
FIELD: aircraft engineering and ship building.
SUBSTANCE: set of inventions relates to apparatuses moving in air or water. Proposed apparatus comprises aerodynamic section wheel with top convex surface, fluid medium high-pressure source communicates with high-pressure jet generator arranged above the wing convex surface. Six design versions of proposed apparatus are distinguished for by the design of aforesaid high-pressure jet generator. Method of generating thrust consists in using high-pressure jet generator arranged above the wing convex surface. Five versions of the method are distinguished for by the design of aforesaid high-pressure jet generator.
EFFECT: higher efficiency.
11 cl, 16 dwg
SUBSTANCE: aircraft comprises airframe, wings, wings actuators and power plant with air intake, combustion chamber and nozzle apparatus. Power plant is arranged at airframe tail to make airframe the central member of circular air intake. Semi-closed detonation combustion chamber is formed by central member end face wall and nozzle apparatus inner wall and is coupled with circular air intake, adjustable circular slot-like nozzle formed byoairframe outer wall and inner wall of circular air intake. The air intake channel accommodates wings and aircraft control elements. Method of operating aircraft comprises accelerating it with subsequent switching on of engine by feeding prepared fuel mix into combustion chamber, its detonation and producing thrust. Fuel mix is fed into combustion chamber in two flows through porous end face wall and adjustable slot-like nozzle at frequency of 200 to 27000 Hz.
EFFECT: improved performances.
7 cl, 1 dwg
SUBSTANCE: invention relates to aircraft engineering and can be used in fighting forest fires, escape operations etc. Proposed flying vehicle comprises fuselage, at least two air screws and one electric motor to drive aforesaid screws. Electric power for vehicle engine is arranged on the ground or aboard the vehicle, along with halyard length adjustment device, halyard one end if fastened to fuselage. Rotary element is fixed between screws on fuselage the rotary element to change direction of airflow from screws. Aforesaid rotary element is deflected by hydraulic cylinder, its working chamber communicating with device feeding working (flame damping) liquid. The latter device can also be arranged on fuselage along with fire hose with mouthpiece (communicating with fire-damping liquid source) and shielded platform with a platform with hand-rail for evacuation of victims (on perimetre of fuselage) in rescue operation. Working liquid feed via fire hose into hydraulic cylinder chamber changes airflow direction parrying the moment from damping liquid jet. That keeps up stability of flying vehicle in fire fighting. Changing airscrew RPM allows docking the flying vehicle in rescue operation.
EFFECT: low costs and simple design.
7 cl, 3 dwg
SUBSTANCE: centrifugal-inertial propeller for flying saucers comprises (1), pushing surface, helical activator (2), holder with weights (9), working springs (3), arranged with the possibility of power accumulation, wheels arranged with the possibility to rotate helical activator from disk by means of Gall's chain (22) from motor (6), planks for perception of weights impact. Propeller is intended for creation of inertial force and provision of reactive force in process of action at pushing surface (15).
EFFECT: expanded arsenal of technical means.
FIELD: aircraft construction.
SUBSTANCE: invention concerns aircrafts. Flying sauce with inertial helical actuator propeller includes light rigid transparent vault (2), inertial helical actuator propeller, low-capacity internal combustion motor, and work spring (8).
EFFECT: simplified construction.
SUBSTANCE: airplane comprises fuselage, nose conical portion, wings, stabilisers, fuel tanks, rocket propulsion system and pipelines for supply of fuel components to it. Rocket propulsion system is installed in back part of fuselage and comprises turbopump set, two combustion chambers and flat central body in between. Rocket propulsion system of airplane comprises turbopump set with impellers of oxidant and fuel installed on shaft, turbine, start-up turbine and coaxially installed gas generator and combustion chamber. Two combustion chambers have been used, and flat central body is installed in between.
EFFECT: reduced time of speed-up.
4 cl, 4 dwg
SUBSTANCE: aircraft comprises plate body, cabin with control panel, installed in the body centre in its upper part. Aircraft also comprises central and lateral rocket engines, nozzles of which are inverted downwards, fuel tanks installed in peripheral zone of body, and chassis. Body of apparatus is equipped with two gravitational masses that rotate in opposite directions in single plane and interacting with inclined guide of body, and drive of rotating masses is connected to central rocket engine. Lateral rocket engines are installed with the possibility of rotation around longitudinal axis of body.
EFFECT: elimination of inertial loads in vertical plane and possibility to vary speed and direction of aircraft motion depending on ambient environment.
4 cl, 1 dwg
SUBSTANCE: airplane comprises fuselage, front and back wings, gas-turbine engines installed on wings, and rocket engine installed in back part of fuselage. On upper part of fuselage along its longitudinal axis there is aviation-based fighting laser installed, which is connected by air sampling pipelines that comprises controller valve to at least one gas-turbine engine and with rocket engine. Laser is arranged as gas-dynamic, comprises optical head and exhaust system, is connected by air sampling pipeline comprising controller valve to turbo-pump set downstream turbine.
EFFECT: improved fighting properties of airplane.
5 cl, 5 dwg
FIELD: aircraft engineering.
SUBSTANCE: invention relates to aircraft engineering and can be used in designing new flight vehicles. Proposed flight vehicle consists of dome-shaped compartment, partition, power plant, reduction gear, rotor, vertical shaft, bearing support, coil and three bearing wheels. A build-up ring-like wing has its fixed wing attached power plant, right below aforesaid partition ceiling. The said build-up movable wing is integrated with the rotor. Note that it has its ribs rigidly fixed to the hub and articulated with rotor blades.
EFFECT: increased safety, maneuverability and controllability.
2 cl, 6 dwg
FIELD: aircraft engineering.
SUBSTANCE: invention relates to flying stands. Proposed flying stand peripheral drive consists of engines (2), clutch and reduction gear box and is arranged above ring wings (4). Drive output shaft supports represents gear wheel (2) of chain transmission to transmit rotation via roller chain (3) to rim (5) of ring wheel (4). Aforesaid drive element can also represent a belt drive pulley to transmit rotation via drive belt to the pulley that represents the rim of ring wheel. Drive element can represent, as well, a gear wheel transmission planar to the plane of ring wheel rotation and transmitting power to ring wheel via gear wheel that makes the rim of the said wing.
EFFECT: simpler power transmission.
SUBSTANCE: invention relates to lifting and carrying cargoes in air. Proposed method consists in rotating regular coaxial multiple identical-orientation ribs along spiral, relative to common rotational axis, to produce lower air pressure above thin disk surface. The disk reverse rotation planes are located on thin disk edge. Ribs rotate above concave surface of thin disk. Thin disk edge features bend in lower direction to add to stiffness.
EFFECT: simplified design.
2 cl, 2 dwg