SK1142018U1 - Folding rotor - Google Patents

Abstract

The folding parachute for airplanes and wind turbines includes leaves (3) attached by a two-way joint (1) to the arms (5) hinged to the base rotor (6). The other leaf sections (3) are attached to the tension elements (13). The blades (3) have a negative strut and their adjustment angles automatically cycle through the force of the balancer (10) and the tensile movement (13) by the centrifugal force. The folding parachute has a storage dimension of three times less than the flight. The vertical axis wind turbine automatically consists of oversized winds and automatically develops the servomotor with speed.

Description

Technical field

The technical solution relates to folding pararotors of helicopters, gyroplanes, wind power equipment capable of changing their shape to the storage dimension, when converting the operation from the operational shape and dimension to the parking, mobile on the ground or windproof

BACKGROUND OF THE INVENTION

Rotors of aircraft with rotating wings or wind turbines are standardly without folding, which allows rapid and purposeful change of shape and size. Wind turbine protection for wind turbines is solved by changing the angles of the blades, in the case of vertical axis types, mostly the stiffness of the structure. The autorotation sheets of flying hybrid vehicles are not stored but fastened at the front and rear.

The essence of the technical solution

The essence of the invention is a foldable pararotor whose blades are attached by a two-way joint to the arms facing away from the base rotor on which they are attached by a rotary joint so that they allow the arm to be tilted towards the center and tilted by the leaves from above. The blades are also attached to the base rotor by pulling elements e.g. ropes between the buoyancy center of gravity and the leading edge of the leaves.

In front of the leading edge of the sheet profile is a balancer which, by centrifugal force and tension in the insertion of the tensile element, produces a constant buoyancy force which can be supplemented by a stabilizer at the opposite end of the balancer cross-section. The resultant buoyancy force just below the center of gravity does not cause the heeling moment from smaller deviations of its perpendicularity. The horizontal displacement forces are controlled horizontally.

If thrust units are used, t. j. propellers or turbochargers, their counter-thrust generates a rotor drive torque at the grippers at the end of the base rotor.

The control in the design of the electro-optic is a control drone which is at the end of the directional holder mounted on the cockpit and which allows to change the direction and thus the position of the center of gravity as well as the vertical tilting. An insertion profile can be inserted from the inside between the sheets to increase the rigidity of the assembly during sudden axis changes, which when unloaded unlocks at the roots of the sheets and adheres to the top of the sheets in a horizontal position.

The foldable steam engine adapted for the wind power installation shall contain sufficient centrifugal force balancers acting on the blade profile, including its weight, and be between the tension member grip at the leading edge and the buoyancy point. At that time, in the position of the sheet against the wind, the buoyancy acts centripetal and the excess centrifugal force strains the tensile elements at the inclination of the profile which rotates the sheet in the direction of rotation. The connecting ropes hold the weight of the leaves, the column allows the operational height of the operation. Energy collection either on the ground by a vertical shaft or in generators on the periphery of the base rotor. The leaves are almost vertical, a slight deflection counterbalances the pressure on the shoulders.

The low weight allows the collection of the high-altitude wind by attracting the folding pararotor set to autorotate and continuously recharge the batteries of the electropters by converting the electric motors to generators and vice versa.

Supplementary leaves at the rear under the sheets, by their inductive resistance, increase the buoyancy coefficient of specific designs.

The angle of attack and buoyancy at the various blade positions can be controlled by electrically actuating the stabilizer flaps, which are at the opposite end of the w / rungs. In this case, no additional control drone is required for larger rotor diameters, it is replaced by an electronic steering cycle.

BRIEF DESCRIPTION OF THE DRAWINGS FIG

In FIG. 1 is a front view of a foldable pararotor in a schematic representation. The slanted slope of the profiles at the moment of the longitudinal position of the leaves in the direction of flight

In FIG. 2 is a modification for a wind turbine. Marked in folded state during excessive wind.

EXAMPLES

Electric passenger transport.

The requirement for small dimensions in the parking space and economy of operation allows the use of electro

SK 114-2018 U1 especially in months with congested land transport. The center of gravity of the blades closer to the outer periphery of the rotation allows the composite state to be changed to the developed speed of the base rotor 6. This rotates upon the engagement of the electric motors 8 with the drive units. After deployment, the insertion profile 2 is secured in the root of the leaves 3 which, in conjunction with the additional leaves 4, cause a particularly high buoyancy at a relatively lower peripheral speed. The resulting uplift asymmetry will partially tilt the axis of rotation toward the backward rotating blade 3. The advantage is to achieve a satisfactory forward speed of about 0.4 circumferential speed, i.e. about 80 km / h, which is compared to shifting in dense ground traffic. satisfactory. Speed and direction control is by controlling the control drone 14 on the directional bracket behind the cockpit 12. Lift and climb is the power of the electric motors 8. Increased speed increases the centrifugal force and hence the angle of attack, which varies by the torque in the arm 5 of the balancer 10 in the two-way joint grip 1.

A prospective solution is a flight with sensing of electric energy from a power line by a drone with a connecting cable. This will enable economical passenger transport and high-capacity supply.

Another embodiment is a purpose-built electropower for timber harvesting. The difference is in the required buoyancy and at the lower speed required. The high operating diameter allows advantageous electrical input. In remote areas, wind self-charging of accumulators is possible. Similarly, there are designs for various assembly, extinguishing and rescue work.

Another embodiment is an ultra-light gyroplane for sporting activities such as jet ski towing. The advantage is the practicality of take-off from the rear seat without other auxiliary security, price and weight of the device.

Kids' versions allow for safe fun pulling down the hill while holding the directional bracket and low flight. Similarly, it is not safe to use it for descents from steep hills and ascents to slope streams.

Another embodiment is a vertical axis wind turbine. The light turbine is secured against excessive wind by self-laying in the shape as in fig. 2 dashed. The blade 3, after exceeding the set wind speed and turning on the braking, changes the vertical position by wind pressure and tilts to the base rotor at the location of the balancer 10, tilting to the base rotor with arm 5. By rotating 180 degrees 3. Direction to the wind will remain until service conditions are restored. The induced speed expands the turbine to the operating position. The adjustable pitch of the blades 3 allows the wind power of the electric vessels even in the headwind. The electric drive surpasses the additional power from the wind turbine resistance, whose column 11, even with the vertical shaft, is loaded with a low torque at a suitable deflection of the lower part of the blades 3 from the axis of the column 11, t. j. increased length of the tensile elements 13, which may have different designs (ropes, elastic profiles, telescopic profiles). The connecting ropes 9 allow low weight of the arms 5.

Claims (6)

PROTECTION REQUIREMENTS Collapsible pararotor for lifting the lift of rotary wings of helicopters, gyroplanes or wind power rotors, characterized in that the blades (3) are attached by a bidirectional joint (1) to the arms (5) which are hinged to the base rotor (6) on its at the ends of the at least one tensile element (13) between the leading edge and the center of gravity of the profile and there is a balancer (10) in front of the leading edge of the profile. _v . The collapsible pararotor according to claim 1, characterized in that it comprises electric motors (8) with thrust units clamped in a counter-rotating direction to the rotor torque by the grippers (7). Folding pararotor according to claim 1, characterized in that a directional holder with a control drone (14) is mounted on the cockpit (12) below the folding pararotor and there is an insertion profile (2) between the blades (3). The foldable pararotor according to claim 1, characterized in that it also comprises connecting ropes (9), a pole (11) or a generator on the ground. A collapsible pararotor according to claim 1, characterized in that it comprises additional blades (4) positioned below the blades (3) at the rear attached to the tensile profile elements (13) for gripping in the run-off part of the profile with crossbars the front part of which front thrust elements (13). The collapsible pararotor according to claim 1, characterized in that on the rear side of the crossbar (10) there is a stabilizer with flaps and their electric control.