Collapsible airfoil

IPC classes for russian patent Collapsible airfoil (RU 2492412):

F42B10/14 - using fins spread or deployed after launch, e.g. after leaving the barrel

B64C9/34 - collapsing or retracting against or within other surfaces or other members

B64C5/12 - for retraction against or within fuselage or nacelle

B64C3/56 - Folding or collapsing to reduce overall dimensions of aircraft

Another patents in same IPC classes:

Unfolding wing of two-stage missile / 2482434

Unfolding wing hingedly fixed on a body and a mechanism of wing unfolding arranged in the form of a rotary rod with two hingedly joined levers that create a parallelogram installed on the rod as capable along its axis with fixation from mutual rotation, being placed on various stages of the two-stage missile. The axis of the rod rotation is installed coaxially with the axis of the wing rotation. The wing is unfolded beyond its rear edge with the help of two fingers installed on one of levers of the unfolding mechanism.

Unfolding wing of two-stage missile / 2482433

Unfolding wing and a mechanism of wing unfolding are installed on different stages of a two-stage missile. The wing opens beyond its rear edge with the help of two fingers of a rotary level of an unfolding mechanism, the axis of rotation of which is installed coaxially with the axis of wing rotation.

Unfolding wing of two-stage rocket / 2478907

Wing and unfolding mechanism are arranged independently at different stages of the rocket. Unfolding mechanism is composed of revolving crank consisting of lever and pin fitted in thrust bearing. Pivot pins of wing and lever are aligned. Said lever is fitted on its pivot pin to revolve thereon and locked by pyro retainer fixed at said lever. Thrusts are fitted on lever pivot pin and on lever proper to accommodate contraction spring there between. Said lever if furnished with pins to interact with seats made in wing rear edge. Wing unfolds behind its rear edge by means of two pins fitted on said lever.

Aircraft outer wing deployment and fixation device / 2463210

Invention relates to aircraft engineering and concerns facilities for aircraft outer wings deployment and fixation. Aircraft outer wings deployment and fixation device comprises outer wings deployment assembly, assembly providing outer wings adherence and deployed outer wings fixation assembly. Outer wings deployment assembly contains two pull rods and pneumatic cylinder with piston. The first ends of pulling rods are connected with outer wings at a distance from outer wing rotation axis, the second of pulling rods are pivotally connected with piston of pneumatic cylinder. The assembly providing outer wings adherence contains shaft on which outer wings are installed, facilities providing outer wings adherence and friction lowering facilities (antifriction collars and rings). Outer wings fixation in deployed position assembly contains spring-loaded stem engaging piston of pneumatic cylinder.

Collapsible steer of guided missile / 2458316

Collapsible steer of a guided missile comprises a root part of the steer, a rotary part of the steer and a mechanism of steer opening. The root part of the steer is fixed on the output shaft of the drive. The rotary part of the steer comprises a transverse dead slot and is installed on two axles installed in the root part of the steer perpendicularly to the axis of the output shaft of the drive at both sides from it. The steer opening mechanism comprises a spring-loaded pusher interacting with the rotary part of the steer, arranged in the root part of the steer as capable of displacement along the drive shaft axis. The steer opening mechanism is additionally equipped with a source of high-pressure gas to move the pusher as the steer opens, and a rotary lever that kinematically connects the pusher and the rotary part of the lever.

Aircraft folding control surface / 2446988

Proposed control surface comprises root section and support. Root section is arranged aircraft airframe to turn thereon. Said root section accommodates support to turn about axis perpendicular to root section center surface. With support folded, part of control surface area ahead of root section turn axle is related to that behind said axle as 1:1 to 3:1. Folded control surface in unfolded position corresponds to condition of axial compensation.

Firing method of rocket missiles from launcher facilities of valley fire systems / 2427788

Method is based on loading of rocket missiles to launcher facility, selection of certain target, hitting method of that target with single shots, bursts or single salvo fire from launcher facility, and directly firing. Loading of each rocket missile to launcher facility is performed with blades folded around it owing to placing them under transport ring which is put on blades when they are folded around each rocket missile approximately to the middle of their length. When arranging rocket missile in tubular guides, launcher facility moves the transport ring to end position on stabilisers. During launching of rocket missile, the removal of the above ring is provided so that full unfolding of blades of stabiliser is performed simultaneously at escape of each rocket missile from its tubular guide of launcher facility.

Modular unmanned aircraft / 2422327

Invention relates to aircrafts and concerns aerodynamic configuration of unmanned aitcrafts. Modular unmanned aircraft contains body 1 of elongated form with carrying beam 2 positioned along the body 1. Suspension assemblies 3,4 are set on carrying beam 2 where rear suspension assembly 4 is combined with swivel block 6 of wing 7 of the aircraft. Semispan of the wing 7 is less than or equal to the distance between suspension assemblies 3, 4.

Method for installation of empennage blades of missile stabilising device / 2403530

Method for installation of missile stabilising device empennage blades includes assembly of empennage with rigidly fixed blades on vessel at the specified working angle of blade inclination, measurement and calculation of actual working angle of inclination of each installed blade. Discrepancy of actual and specified working angles of missile stabilising device empennage blades inclination is compensated due to arrangement of levelling site with specified width at surface of each blade, and its determining linear size is calculated according to the given formula.

Guided missile fin / 2396508

Guided missile fin comprises hollow vanes folding along missile surface and made from flexible plates jointed by edges. Vane flexible plates are bent to make a segment of cylindrical surface, its area being defined by the formula: where a is arm span, mm; b is half the length of lower edge, mm. Note that plate jointed edges are made curvilinear to mate cylindrical surface segment.

Aircraft folding control surface / 2446988

Folding aerodynamic surface / 2349498

Invention relates to the designs of folding aerodynamic surfaces of pilotless flight vehicles. The proposed device comprises fixed (1) and rotary (2) part hinged thereon, pushrod sliding inside the hinge holes and a helical converter of the pushrod translation into rotation of the rotary part of the said aerodynamic surface including a cylinder with helical surfaces and a pin interacting them. The helical converter is furnished with the second cylinder with the helical surfaces direction other than that of the fist cylinder helical surfaces. The cylinders are arranged concentrically relative to each other. Note here that one of the cylinders is connected to the aerodynamic surface fixed part while the other one is jointed to the rotary part. The pushrod is arranged inside the inner cylinder to reciprocate and rotate therein. The pin is fitted on the said pushrod to interact with helical surfaces of both cylinders. Note that helical surfaces of each cylinder are formed by side surfaces of helical slots (5,6) made on diametrically opposite side of the cylinders shells.

Folded aerodynamic surface / 2338663

Aerodynamic surface comprises fixed and hinged parts, pusher sliding inside the hinge holes and helical converter of the pusher translation motion into the rotary motion of the aforesaid aerodynamic surface rotary part, the converter including a helical-surface cylinder and a pin interacting with the said helical surface. The helical converter is furnished with the second cylinder with helical surfaces with direction opposite to that of the fist cylinder and an additional pin interacting with the second cylinder helical surfaces. Both cylinders are arranged aligned and prohibited to reciprocate by a thrust bearing. One of the cylinders is linked with the aerodynamic surface fixed part while the other one with its rotary part. The pusher is arranged inside the cylinders to reciprocate and revolve therein, the pins being fitted on the said pusher to interact with the cylinders helical surfaces via the spherical sleeves. The said helical surfaces of every cylinder are formed by the side surfaces of helical slots made on the opposite sides of the cylinders rings.

Integrated aircraft / 2349500

Proposed aircraft comprises a "wing-fuselage" assembly, cockpit, vertical and horizontal tail units, control surfaces, power plant, landing gear, aircraft and engine systems, equipment and instrumentation. The integrated aircraft tail part is formed by three movable surfaces arranged so that, in initial position, all said surfaces form a required geometry of the tail part. In the operating position two surfaces form a straight wing with elongation of at least λ>4 and feature symmetrical profiles with relatively great thickness of C=11 to 13%. The third surface is made up of sections with a negative concavity and extends for a distance equal to the maximum chord of this surface. All the said surfaces are articulated with the common pneumatic drive.

Aircraft capable of moving on ground / 2492066

Proposed aircraft has fuselage, wheels to run on ground attached to fuselage bottom, wings to create the lift arranged in symmetry on fuselage both sides and propellers mounted on wings and fuselage to generate the lift and traction. Said wings are attached to fuselage by means of position variators, each including multiple variable-volume chambers and volume variator arranged on one side of variable-volume chambers to adjust their expansion to allow every wing to be folded.

Seal assy and its application at aircraft / 2490166

Invention relates to aircraft engineering, particularly, to seal of joint between aircraft fuselage and wing. Seal assy comprises elongated bellows to be secured to fuselage and wing front box. Said bellows feature flat, flexed or wavy (omega-shape) cross-section with two lengthwise lateral parts. One lateral part is secured to wing box whole another one is attached to fuselage by means of appropriate mounts. Said mounts make a lock seam for attachment of bellows to airframe mounts. Seal assy seals the clearance between fuselage and wing to maintain pressure in tight fuselage.

Staroverov' wing (versions) / 2480375

Invention relates to aircraft engineering, particularly, to aircraft hardware intended for improving landing capabilities. Aircraft wing consists of outer wings. Note here that outer wings or their part turn about axis located in plan between perpendicular to aircraft axis and outer wing axis. Outer wing may turn relative to line making in plan with aircraft lengthwise axis the angle exceeding its sweep angle.

Aircraft outer wing deployment and fixation device / 2463210

Aircraft with folding wing and device for aircraft wing folding / 2403177

Invention relates to aircraft with folding wings and can be used in design of transport facilities for traveling over air or ground. Aircraft with folded wing contains cockpit, propulsion unit with pushing airscrew, fins installed in tail-end of aircraft, wheel landing gear, centre wing, pivotally connected with it outer wings, fixing locks. Connection of the outer wings with centre wing is executed with possibility to turn them up-back relative to axes located in horizontal plane and divergent at an angle 35°-55° to aircraft longitudinal axis from the front part of aircraft to its rear part, and their installation along aircraft with their front edge up and towards aircraft symmetry plane. Outer wings in folded position are fixed with struts fixed on tail-end of aircraft. Device for aircraft wing folding.

Lifting wing of aircraft / 2385822

Invention relates to aircraft industry. Lifting wing of aircraft consists of framework, skin, deflection elements of air flow slipping the upper and lower aerodynamic surfaces, outer wing with the engine on the end, which is attached to framework. Lifting wing has mini-wings located on both sides of the engine and creating the lifting force which compensates gravity force from engine weight. Between adjacent engines there located is common mini-wing.

Folding aerodynamic surface / 2349498

FIELD: weapons and ammunition.

SUBSTANCE: collapsible airfoil comprises a base and a hingedly connected rotary blade, a pusher and a screw converter of pusher progressive motion into rotary motion of the blade. The screw converter comprises two cylinders with helical surfaces and an interacting working element. Cylinders are arranged coaxially in series. One of cylinders is connected to the base, and the other one - with the blade, besides, the second cylinder has helical surfaces of another direction, in comparison to the helical surfaces of the first cylinder. The working element is made in the form of a threaded stem placed in inner cavities of cylinders with the possibility of progressive and rotary movements. The working element with one end is rigidly connected to the pusher sliding inside the first cylinder, and with the other end it is introduced into the second cylinder. Helical grooves made along the surface generator of the threaded stem in its middle part change their direction from one to another, which responds to helical surfaces of cylinders.

EFFECT: reliable opening of an airfoil under conditions of strong aerodynamic disturbances.

4 dwg

The invention relates to the field of rocket technology, and in particular to collapsible structures aerodynamic surfaces under the influence of aerodynamic disturbances.

A device called "Folding aerodynamic body managed projectile" [patent RU No. 2280230, F42B 10/14, 20.07.2006,]. This device has a stationary and pivotally hung on her rotary part (wheel), the axis of folding, spring and retainers. In the fixed part made the slot in which you installed the trunnion axis. Spring axis folding one end connected to the wheel and the other with a pin. When moving through the tube handlebar controlled projectile is held in its folded position by the wall. When you exit the container folded the wheel straightens due to the energy of the spring, which transmits the pushing pulse handlebars.

This device has a simple design.

However, the disadvantage of this device is the low reliability when opening the helm. There is a drop of efforts disclosure steering by reducing the torque generated by the spring during the opening, as the angle of twist of the spring is proportional to the point that it creates. In addition, shrinkage of the spring material during long-term storage in the cocked state forces to create accessories for the svedeniya spring immediately prior to use of aircraft (LA). And having a large length of the spring because of the twisting angle (135°) leads to a substantial increase in dimensions that are not acceptable for small AIRCRAFT.

Known design foldable aerodynamic surfaces, adopted as a prototype [patent RU NO. 2338663, B64C 3/56, B64C 9/34, F42B 10/20, 20.11.2008,]. Folding aerodynamic surface comprises a base (stationary part) and pivotally connected with him the blade (rotary part), the plunger, and a screw Converter translational movement of the pusher into rotational motion of the blade, comprising two cylinders with helical surfaces and interact with the work item, the cylinders are coaxially arranged in series, with one of the cylinders is connected to the base, and the other with the blade, and the second cylinder has a screw surface a different direction than the helical surface of the first cylinder. The helical surface of each cylinder is formed with lateral surfaces of the helical grooves made on diametrically opposite sides of the cylinder shells. Work item for this unit are the fingers mounted on the plunger and communicating with the helical surfaces of the cylinder through the spherical bushing.

This device is compact and compared with the analogous ensure the AET effective functioning of the coil of the transducer under high aerodynamic loads and large angles of opening.

However, the drawback is the lack of reliability of the device. In operation, the supporting sections of the fastening fingers on the plunger due to their small diameter and the fact that the contact of the fingers with the surface of the pusher is on the line, there are critical voltage, which can cause the destruction of the fingers (the cut surface of the pusher), which is especially likely if large aerodynamic loads and large angles of opening. This reduces the structural safety opening mechanism that can lead to unstable disclosure of aerodynamic surfaces, especially under the influence of aerodynamic disturbances. The area of contact of the fingers with screw slots of the cylinder is small, which greatly reduces the carrying capacity of the transmission. In addition, the grooves on the inner surfaces of shells cylinder prototype can be made through the entire thickness of the shells)that if you want to create a large angle of opening (135°) reduces the rigidity of the structure.

The objective of the invention is to improve the reliability of operation of folding aerodynamic surfaces.

The technical result, which can be obtained from the implementation of the present invention is the reliability of the disclosure of the aerodynamic surface and in conditions of strong wind disturbances by reducing the operating voltage in the fields, at the most intense stress.

The technical result is achieved by folding aerodynamic surface containing the base and pivotally connected with him the rotary blade, the plunger and the coil transducer of the translational motion of the pusher into rotational motion of the blade, comprising two cylinders with helical surfaces and interact with the work item, and the cylinders are coaxially arranged in series, one of the cylinders is connected to the base, and the other with the blade, and the second cylinder has a screw surface a different direction than the helical surface of the first cylinder, according to the invention, the work item is executed in the form of a threaded rod, placed in the inner cavity of the cylinder with the possibility of translational and rotational motion, one end of which is rigidly connected to the plunger, sliding inside the first cylinder and the other end is inserted in the second cylinder, with helical grooves, made by forming the surface of the threaded rod, in its middle part is changing its direction from one to the other, second helical surfaces of the cylinders.

Execution interacting with screw screw cylinder surfaces of the transducer of the working element in the form of a threaded rod, is placed in GNC the interior cavities of the cylinder with the possibility of translational and rotational movements, one end rigidly connected to the plunger, sliding inside the first cylinder and the other end is inserted in the second cylinder, enables the strength of the force elements of the mechanism aerodynamic surfaces when exposed to the design loads, so as to increase the cross-sectional area of the spiral grooves contact bearing elements increases and, unlike the prototype, is not on line and on the surface. Thereby increasing the carrying capacity of the transmission, reduces the level of operating voltage in areas exposed to the most intense stress.

Run the threaded rod with helical grooves, made by forming the surface of the threaded rod, in its middle part, changing its direction from one to the other, second helical surfaces of the cylinder, allows for smaller during actuator and screw transducer to provide the desired angle of folding of the aerodynamic surface. This design solution provides robust disclosure of the aerodynamic surface in conditions of strong wind disturbance.

A comparison of the claimed technical solution with the prototype allowed us to establish its compliance with the criterion of "novelty".

The study of other known technical solutions in the Anna area equipment signs, distinguishing the claimed solution to the prototype, were not detected, which suggests the claimed technical solution meets the criterion of "inventive step".

The proposed solution is illustrated by drawings, where:

figure 1 shows the aerodynamic surface in the folded position;

figure 2 - section a-a in figure 1;

figure 3 - aerodynamic surface in the open position;

figure 4 - cross-section B-B figure 3.

We offer folding aerodynamic surface (figure 1) consists of the base 1 and pivotally hung on her rotary blade 2, the plunger 3, is placed on the axis of rotation of the aerodynamic surfaces, and screw transducer translational motion of the plunger 3 in the rotational movement of the blade 2. Screw the Converter contains two cylinders 4, 5 and the threaded rod 6. Cylinders 4, 5 are sequentially aligned along the axis of rotation of the aerodynamic surface. The cylinder 4 is connected with the base 1 and the cylinder 5 with the blade 2. The rod 6 is placed in the internal cavities of both cylinders 4, 5 with the possibility of translational and rotational movements, with one end rigidly connected to the pusher 3 (screwed thread)that slides inside the cylinder 4, and the other end is inserted into the cylinder 5. Shell cylinders 4, 5 are three helical slots 7, 8, with side surfaces which maintains deistvuut three helical grooves 9 threaded rod 6. The cylinder 5 has a screw slot 8 right direction, and the cylinder 4 has a screw slot 7 of the left direction. And helical grooves 9 (2), made by forming the surface of the threaded rod 6, in its middle part is changing its direction from the left to the right, second helical grooves 7, 8 cylinders 4, 5. To hold the blade 2 in the open state, as well as to remove part of the load from the place of engagement of the rod 6 with screw slots of the cylinder 5, the device includes a locking mechanism (not shown).

The disclosure of the aerodynamic surfaces is as follows.

When triggered, the actuator (not shown) is pressurized in the cylinder bore 4, under which the plunger 3 moves the rod 6, pushing him out of the cylinder 4. At the other end of the rod 6 enters the cylinder 5 (Fig 3). The rod 6, moving along the cylinder 4 communicates with the helical slots 8, and the shaft 6 is rotated in the direction of the cut spiral grooves 9 on the angle of 67.5°. Since the other end of the rod 6 through the cylinder 5 is connected with the blade 2, the blade also rotates by the angle of 67.5°. Simultaneously, the rod 6, moving along the cylinder 5 communicates with the helical slots 8 (figure 4), causing the cylinder 5, and with it the blade 2 to turn on "more" to 67.5°. Thus the angle of rotation "is", DOS is IgA the desired angle of 135°. After turning the aerodynamic surface is fixed by a pin (not shown). The process of disclosure of the blade is completed.

Thus, on a small course threaded rod 6 is provided with the necessary angle of the folding blade 2, is achieved by a force sufficient to ensure reliable disclosure aerodynamic surfaces under the influence of aerodynamic disturbances.

Adjustment efforts on the disclosure of the blade 2 can be realized by changing the number of helical grooves on the rod 6 and the length of the spiral grooves 7, 8 in the cylinders 4, 5. Depending on the magnitude of the aerodynamic wind loads can adjust the elevation angle of the helical line. At low wind load, you can increase the elevation angle of the helical line on the rod 6, which will lead to the reduction of the stroke of the piston rod 6 and the dimensions of the coil of the Converter.

Experimental studies have shown the possibility of implementing technical solutions used in this device. Trials were conducted, the results of which confirm the reliability of the mechanism folding aerodynamic surfaces. Tests have shown that folding aerodynamic surface operates reliably under high aerodynamic loads and large angles of opening (135°), maintaining the strength of all the ways.

Calculations of stress-strain state of the power elements of the mechanism aerodynamic surfaces show sufficient durability when exposed to the considered load.

Thus, the presented data suggest the implementation of the use of the claimed invention, the following cumulative conditions:

- ensuring the reliability of the aerodynamic surface under high aerodynamic loads and large angles of folding in small characteristics;

for the inventive device in the form in which he characterized in the claims, confirmed the possibility of its implementation using the steps described in the application and known before the priority date tools and methods.

Therefore, the claimed invention meets the condition of "industrial applicability".

Folding aerodynamic surface containing the base and pivotally connected with him the rotary blade, the plunger and the coil transducer of the translational motion of the pusher into rotational motion of the blade, comprising two cylinders with helical surfaces and interact with the work item, and the cylinders are coaxially arranged in series, one of the cylinders is connected to the base, and the other with the blade, and the Torah cylinder has a screw surface of the other direction, than the helical surface of the first cylinder, wherein the working element is designed as a threaded rod, placed in the inner cavity of the cylinder with the possibility of translational and rotational motion, one end of which is rigidly connected to the plunger, sliding inside the first cylinder and the other end is inserted in the second cylinder, with helical grooves, made by forming the surface of the threaded rod, in its middle part is changing its direction from one to the other, second helical surfaces of the cylinders.