Aircraft aerodynamic flap with stall affecting device

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering. Proposed flap 11 incorporates stall affecting device arranged on flap side edge with wing sections 13 extending along wing span to form air passages for incoming air to pass there through. High-efficiency flap comprises channel extending onto flap side edge through which compressed air may be fed into noise-generating vortex. Stall affecting device comprises compressed air feed device, side edge outlet channel and jointing element.

EFFECT: reduced noise.

18 cl, 5 dwg, 2 tbl

 

The invention relates to aerodynamic flap of an aircraft and, above all, to create a significant increase in the lifting force to the flap (high-performance flap) aircraft with influencing disruption of the flow device or turbulization, as well as the same affect the disruption of the flow device.

From patent WO 00/02775 known As a highly effective flaps on the wing for large aircraft, which is extending in the flow direction of the slot in order to reduce the vortex trail behind the wing.

EP 1149761 A1 describes energizers, which are made in the form of elongated elements on the profile surface plane of the control.

US 6283406 B1 describes a blade rotor for helicopters, for which the influence of turbulence on the first longitudinal side is the intake passages for air intake, and on a second longitudinal side opposite the aforementioned first longitudinal side, the vent passages for venting.

EP 0689990 A1 describes a blade rotor for helicopters, which has an outlet and device for blowing air through data outlet.

Modern passenger aircraft used during the phases of takeoff and landing so-called AIDS podyemnyi for in order to perform the necessary rise at low speeds. Together with chassis data elements of design of the aircraft divisible by the slats and flaps (landing flaps)are the main generators of aerodynamic noise in a passenger aircraft. During landing when the engines are much grosseserrata, this noise can reach the same order of magnitude as that of the engines.

A comprehensive research program in the United States and Europe showed that essentially for the formation of this noise meet two areas forming the supporting means carrying power: the back side of the slat and the side flap. Noise levels in the last-mentioned formation caused by turbulence on a side face formed by the flow around the side edges. This flow is caused by the pressure difference between the upper and lower edge of the flap. The result is a relatively high angle of the flap vortex traces are formed on both upper and lower faces of the side surface, which after passing through a certain area are combined in a large swirl. The interplay of turbulence with the surface of the flap and then leads to the formation of noise.

Device for reducing aerodynamically induced noise on laterally the verge managed flap, first of all highly effective flap to increase the lift force (wing) aircraft, it is known from DE 10020177 A1. On the side face of the control flap formed turbulator through several stretches in the direction of the wing span elements, between which (elements) is flowing controlled air flaps. The speakers in the direction of the wing span of the elements have an elongated shape and provided in the form of brushes that pass through one or more sections of the chord of the profile of the flap control.

From US 3596854 known turbulator, which contains along a side face of the control flap cylindrical element with an opening towards the back side of the control flap outlet through which the discharged compressed air is accumulated on the side of the high pressure high performance flap. The direction of rotation of the swirl can be selected to increase or decrease the lifting force of highly effective flap.

The aim of the invention is the creation of the aerodynamic flap and, above all, highly effective flaps of the aircraft with influencing disruption of the flow device, and such devices that affect the breakdown of the flow close to the side face of the aerodynamic flap, which allows the th effective and low-cost implementation.

This goal is accomplished by the distinguishing features of independent claims. Other variants of implementation set forth in referenced in dependent clauses.

According to one aspect of the invention provides an aerodynamic flap of an aircraft, especially high-performance flap of an aircraft with influencing disruption of the flow device on at least one side edge of the aerodynamic flap, which includes extending transversely to the direction of air flow elements, along which flows flowing aerodynamic flap the air. Extending transversely to the direction of air flow elements are made on the side of the aerodynamic flap sections of the flap, which is designed in such a way that between the two parts of the flap has one or more air passages for through passes of rolling aerodynamic flap of the air.

Extending transversely to the direction of air flow areas flap motionless or without the possibility of rotation are located on the managed flap or made with him in the form of a single whole, and between the parts of the flap are made of air passages to be passed through the incident from the aerodynamic flap of the air. This is ristiriidassa transversely to the direction of air flow areas flap is made in the form of fingers and protruding from at least one side edge of the aerodynamic flap. In these embodiments, the implementation of a number of extending transverse to the direction of flow of air parcels flap is between three and nine, preferably between three and five.

Acting transversely to the direction of air flow sections of the flaps have at least one configured to move relative to the aerodynamic flap, the flap segment, and the segment of the flap is arranged to move so that he during corresponding movement opens at least one air passage, through which the incident on the aerodynamic flap air can flow from the lower side to the upper side of the aerodynamic flap. This may be provided by structurally embedded in the flap device and a regulating device and a docking mechanism for coupling the regulating device with a movable flap segment. With the help of docking mechanism during the movement segment of the flap, which is movable relative to the aerodynamic flap, can thibetica up or away from the aerodynamic flap on the top plane and thus opens the air passage for the through flow of air coming from the bottom side of the aerodynamic flap on its upper side. Adjusted the existing fixture and/or the docking mechanism can be but do not necessarily have to be both integral part of the aerodynamic flap.

The air passage may be designed in such a way that it forms accelerating the flow of air from the bottom side of the aerodynamic flap on the upper side of the nozzle.

Which is movable relative to the aerodynamic flap segment flap may extend over approximately half the chord of the profile of the aerodynamic flap. Also the length is configured to move relative to the aerodynamic flap segment flap when viewed in the direction of air flow may be between 30% and 70% of the length of the side face of the aerodynamic flap.

Moreover, to pair move made with the possibility of moving segment of the flap with the movement of the aerodynamic flap may be a mechanism coupling for coupling the control mechanism of the aerodynamic flap with a control mechanism of the segment rolling flap.

According to the second aspect of the invention provides an aerodynamic flap of an aircraft, especially high-performance flap of the aircraft, containing affecting disruption of the flow device on at least one side edge of the aerodynamic flap with stretching pop the fluvial flow direction of the air elements, along which flows flowing aerodynamic flap the air, thus affecting the disruption of the flow device contains a large number extending transversely to the direction of air flow elongated elements, which form is made in the form of a brush device, whose length is at least 75% of the total chord of the profile of the aerodynamic flap.

The elongated elements are in the form of a brush device can move away at an angle from the lateral edge of the aerodynamic flap and extend transversely to the direction of air flow.

Made in the form of a brush device may have a line shape is consistent with the form of the aerodynamic flap in the field made in the form of a brush device.

According to further aspect of the invention provides an aerodynamic flap of an aircraft, especially high-performance flap of the aircraft, containing affecting disruption of the flow device on at least one side edge of the aerodynamic flap, thus affecting disruption of the flow device has at least one device for supplying compressed air, and at least one opening on the side of the aerodynamic flap and is connected with at least one device for supplying compressed air channel for blowing satoh the air in the surrounding space of the aerodynamic flap.

When this outgoing channel may extend to the surface profile of the lateral faces and may enter the place of exit at an angle between 70 and 110 degrees to the contour of the side faces.

Output channel can be connected to pair with the system of the aircraft so that is vented through an output channel the compressed air can be fed from the system air sampling aircraft engines.

Alternative blown through the opening on the side of the aerodynamic flap channel compressed air generated by the dynamic pressure, with a connection for supplying compressed air to the outgoing channel.

Primarily affecting disruption of the flow device may contain at least one part facing the flow area of the aerodynamic flap channel, and is connected to the incoming channel and facing the side of the aerodynamic flap channel to be passed through the oncoming air.

According to further aspect of the invention provides a device for influencing the disruption of the flow of highly effective flaps of the aircraft and above all highly effective flaps of the aircraft, which has extending transversely to the direction of air flow elements to wrap the incident from the aerodynamic flap in which Suha, the device has a device connected to the host device on the flap so that the elongated elements on a side face of the aerodynamic flap are made by parts of the flap, between the parts of the flap are one or more air passages for through passes of rolling aerodynamic flap of the air.

According to further aspect of the invention provides a device for influencing the disruption of the flow of highly effective flaps of the aircraft and above all highly effective flaps of the aircraft, thus affecting breakdown flow device for blowing compressed air in the surrounding space of the aerodynamic flap includes at least one device for supplying compressed air and at least one output channel for blowing compressed air in the surrounding space of the aerodynamic flap, which is made with the possibility of placing on the side of the aerodynamic flap and fastener to connect the device to the compressed air output channel.

When this output is made so that it can be located in the aerodynamic flap so that it goes to the surface profile of the lateral faces.

Alternative or additionally, the output is ASCII channel may be performed so that that it can be located in the aerodynamic flap so that it comes out at the place of exit at an angle between 70 and 110 degrees to the path side. When this output channel can be connected to pair with the system of the aircraft so that is vented through the discharge channel of the compressed air can be fed from the system air sampling aircraft engines.

Alternative devices may be compressed air, through which is fed compressed air can be vented through the opening in the side face of the aerodynamic flap channel.

Affecting disruption of the flow device may contain at least one first incoming channel, which can be placed in the reversed flow region of the aerodynamic flap, and is connected with the first input channel and is made with the possibility of placing on the side of the aerodynamic flap exhaust channel for end-to-end passes the resulting air.

Below is illustrated an example embodiment of the invention with reference to the drawings. Shown:

Figure 1 - the device that affect the breakdown of flow with flap and, above all, a device for reducing aerodynamically induced noise on the side of the controlled flaps, first of all highly effective flap lettering the apparatus in accordance with the first embodiment of the invention.

Figure 2 - device affecting such stalls with flaps, and, above all, the device for reducing aerodynamically induced noise on the side of the controlled flaps, first of all highly effective flap of an aircraft in accordance with the second embodiment of the invention.

Figure 3 - device affecting such stalls with flaps, and, above all, the device for reducing aerodynamically induced noise on the side of the controlled flaps, first of all highly effective flap of an aircraft in accordance with a third example embodiment of the invention.

Figure 4 - device affecting such stalls with flaps, and, above all, the device for reducing aerodynamically induced noise on the side of the controlled flaps, first of all highly effective flap of an aircraft in accordance with the fourth embodiment of the invention.

Figure 5 - device affecting such stalls with flaps, and, above all, the device for reducing aerodynamically induced noise on the side of the controlled flaps, first of all highly effective flap of an aircraft in accordance with the fifth embodiment of the invention.

Figures 6 and 7 are diagrams showing the reduction of aerodynamically induced noise for two examples of the implementation of the ing the invention, ie is shown in figure 2 (figure 6) of the second embodiment of the invention, or as shown in figure 1 (figure 7) of the first example embodiment of the invention.

Below explains the different solutions that primarily reduce emitted from the swirls on the side noise. The leading factor evaluation for technical clarity, such modifications of the flap is the maximum lifting force that can be achieved with this configuration.

Figure 1 and 3 show the device affecting such stalls with flaps, and, above all, a device for reducing aerodynamically induced noise on the lateral marginal zone or on the side of the controlled flaps, first of all create a significant increase in the lifting force of the wing flap (high performance flap) of the aircraft in accordance with the first and third example embodiment of the invention. The device is used to effect the disruption of the flow with flap, primarily to reduce the aerodynamically induced noise on a side face 12; 32 managed flap 11; 31 and, above all, highly effective flaps of the aircraft. For a given direction of flight F aircraft managed flap washed by the air in the flow direction S. On the lateral marginal zone or on a side face 12; 32 managed flap 11; 31, i.e. on the side by the howl of the connecting line between the front and rear, when looking in the direction of air flow edge of the flap is provided for effecting the disruption of the flow device or turbulator with extending transversely or at an angle to the air flow direction or in the direction of the wing span elements, between which there is an ambient controlled flaps 11; 31 the air, i.e. the part of the ambient air flaps.

Common to both embodiments of the invention is that extending transversely to the flow direction or in the direction of the wing span of the elements are in the form of sections 13; 31; 33 surface of the control flap 11; 31 that forms one or more placed between the surface of the air passages through which the incident on a managed flap 11; 31 air passes through.

Shown in figure 1 the first example embodiment of the invention extending transversely to the flow direction or in the direction of the wing span of the flap 11, 31 parts 13 of the flap are narashima or stationary on the plane of the control 11. The parts of the flap is designed in such a way that between the sections 13 of the flap is formed of at least one air passage or formed of multiple air passages at a given washing flap when viewed in the direction of air flow. Thus at a given location acrylc the part washing managed flap 11 of the air flowing through the gaps. In one embodiment of the invention extending transversely to the flow direction or in the direction of the wing span of the parts of the flaps or sections 13 surfaces are made primarily in the form of fingers. The fingers extend from the end connected to the side face 12 of the control flap or flaps 11 and protrude outwards so that the second end opposite the first end forms a free end. Number of lots 13 surface is between three and nine, and in the preferred embodiment of the invention between three and five. This is based on the assumption that by irregularly performed a lateral side 12 avoid or at least reduce a single twist. Thus is formed a number of small vortex zones, which produce noise in the high frequency range, which, however, quickly extinguished in the atmosphere.

This principle of the solution according to the invention has already been proven in an experimental model in the wind tunnel. The results are presented in figure 7 for four different frequencies depending on the location of the flap. Thin bottom line is able to recognize a significant decrease aerodynamically generated noise compared to conventional flap (thick upper line).

Shown in figure 3 the third example assests the ment of the invention at least one of which extends transversely to the flow direction or in the direction of the wing span sections of the flap is made in the form of made to move relative to the aerodynamic flap 31 of the flap segment or segment 33 of the surface. This may be especially preferable that the aerodynamic flap 31 at least when viewed in the flow direction S before at least one movable segment 33 of the flap is located next is a segment 32 of the flap, still or connected rigidly with the flap 31. At least one of the following flap 32 can be placed both before and behind the rolling segment 33 of the flap. If there are many moving segments 33 of the flap may, but not necessarily, be provided in each case one of the subsequent segments 32 of the flap. Made with the possibility of moving the segment 33 of the flap after its opening or during his opening move opens the air passage, through which passes a portion surrounding the flap in accordance with the purpose of the air flowing from the lower side first when looking in the direction of the air flow area of the flap 31 to the upper side of the second relative to the first region of the rear region of the flap 31. Thus the opening movement is a managing movement that starts from the initial position, in which each of the adjacent faces is located on each of the adjacent rolling segment of the flap and front of nanocladius segment 32 of the flap thus, that the air passages are missing. Next move goes to the position in which each of the adjacent faces of the segments 33, 32 of the flap removed from each other so that there is formed an air passage between the front and moving back segments 32 or 33 of the flap. This means that the segment 33 of the flap, is arranged to move relative to the flap or control flap 31, during your turn opening on its top surface, i.e. the side facing the flow, can thibetica down relative to the flap 31 or the next segment 32 of the flap, and opens the air passage, through which the air passes through from the lower part of the flap 31 to its upper part. Air passage forms a nozzle, accelerating flowing from the bottom side of the control flap 31 on its upper side the air. The suction effect of this accelerated flow prevents swirl interaction side surface of the landing flap (flap) 31, thus eliminating the formation mechanism of the noise.

When many made with the possibility of moving segments of the flap and/or multiple subsequent rigidly attached to the flap 31 of the segments 32 of the flap, each of the rear segments 33 of the flap is fixed with the ability to move the relationship is to the front segment 32 of the flap.

Made with the possibility of movement relative to the aerodynamic flap 31 segment 33 of the flap extends in the flow direction is preferably 30% to 70% of the value of the chord of the profile of the flap 31 when viewed in the flow direction. Segment 33 of the flap may extend approximately half +/- 20% of the chord of the profile of the control flap 31, a movable segment 33 of the flap can be placed next segment of the flap which is rigidly attached to the flap 31, i.e. the movable segment 33 of the flap is located on the flap 31 approximately in the center. Made with the possibility of moving the segment 33 of the flap to move can be paired with the control mechanism of the control flap 31.

Shown in figure 2 the second example implementation of the invention on a side face 22 or the edge zone 22 of the control flap 21 is provided for effecting the disruption of the flow device containing extending transversely to the flow direction or in the direction of the wing span of the elements, between which there is an ambient control flaps 21 air. Affecting disruption of the flow device contains a large number of elongated extending in the direction of the wing span of the elements 23, which form a preferably extending essentially the entire chord of the aerodynamic flap 21 or h is 75% of the entire side face of the flap 21, made in the form of a brush device. Elongated elements 23 are made in the form of a brush device extending transversely to the direction of flow of the air or perform essentially at right angles from the side face 22 of the flap control 21. Made in the form of a brush 23, the device has a contour, which is aligned with the profile of the control flap 21, i.e. so that the contour line runs approximately parallel to the profile of the side face of the flap 21. In the same way as in the two previously described embodiments of the invention, the principle of operation of this device in the form of brushes just based on the fragmentation of large eddies into many small, which probably partially cancel each other out.

Preliminary results of an experiment in a wind tunnel with this variant of the invention disclose a significant reduction potential across the considered frequency range. This is shown in figure 6 for four different frequencies depending on the location of the landing flap. Thin bottom line is able to recognize a significant decrease in aerodynamically generated noise in comparison with the normal landing flap (thick upper line).

Figure 4 and 5 show the impact on the disruption of the flow device or to reduce the aerodynamically induced noise on the side of management is managing the flap first of all create a significant increase in the lifting force of the wing flap (high performance flap) of the aircraft in accordance with the fourth and fifth example embodiment of the invention. Reducing aerodynamically induced noise affecting disruption of the flow device is provided on a side face 42; 52 landing flap 41; 51, first of all highly effective flaps. This device contains at least one channel 43; 54 facing the side face 42; 52 managed flap 41; 51, through which the produced system of the aircraft or the flow of compressed air may be supplied in forming the noise turbulence. Channel 43; 54 comes to the surface profile of the controlled flaps 41; 51 transverse to the direction of flow of air or essentially perpendicular to the side face 42; 52.

Shown in figure 4 the fourth example of the invention, the compressed air blown through the opening on the side face 42 of the controlled flaps 41 channels 43, is generated through a system of air sampling aircraft engines.

Shown in figure 5 the fifth example of the invention, the compressed air blown through the opening on the side face 52 of the control flap 51 channels 54, which generates a dynamic pressure. Formed by the dynamic pressure of the compressed air is evacuated channel 53 on the front side of the controlled flaps 51 and is directed through the piping system on the side 52 of the landing flap 51.

By blowing air from the side and/or top surface of the landing flap 41; 51 achieved three effects for noise reduction: on the one hand, twist the side face can be "deflated" with landing flap and thus the mechanism of interaction of education of the noise can be eliminated, on the other hand, it is possible to reduce the force of the turbulence by insufflation of air into the core of the vortex to such an extent that there was no significant radiation of sound. The third effect is that coming from the side surface 42; 52 air jet, in the same way as the edge of the brush 22 are presented in the figure 2 embodiment, lead to the formation of smaller zones of turbulence.

The above-explained solutions are understood not only as an opportunity to reduce noise, but also aims to increase the lifting force. As a result, the speed of the landing of a passenger aircraft can be reduced, which would have a positive impact not only on the formation of noise. Through decisions in accordance with this invention can also be improved flight stability.

1. Aerodynamic flap (11; 31) of the aircraft with influencing disruption of the flow device on at least one side face (12; 32) of the aerodynamic flap (11; 31), which contains stretches pop the fluvial flow direction of the air elements, along which flows flowing aerodynamic flap (11; 31) of the air,
characterized in that
extending transversely to the direction of air flow elements are made on the side of the aerodynamic flap (11; 31) parts (13; 31, 33) of the flap, which is designed in such a way that between these sites (13; 31, 33) of the flap is made of one or more air passages for through passes of rolling aerodynamic flap (11; 31) of the air,
when this protruding transversely to the direction of air flow areas (13) of the flaps have at least one configured to move relative to the aerodynamic flap (31) segment (33) of the flap
when this segment (33) of the flap is arranged to move so that he during corresponding movement opens at least one air passage, through which the incident on the aerodynamic flap (11; 31) the air can flow from the lower side to the upper side of the aerodynamic flap (31).

2. Aerodynamic flap (11; 31) according to claim 1, characterized in that it is arranged to move relative to the aerodynamic flap (31) segment (33) of the flap when the move can be moved from the aerodynamic flap (31) on the side of the upward flow and opens, so what Braz, air passage for the through pass, flowing from the bottom side of the aerodynamic flap (31) on its upper side, of the air.

3. Aerodynamic flap (11; 31) according to claim 2, characterized in that the air passage forms accelerating the flow of air from the bottom side of the aerodynamic flap (31) on the upper side of the nozzle.

4. Aerodynamic flap (11; 31) according to claim 1, characterized in that the length is configured to move relative to the aerodynamic flap (31) segment (33) of the flap when viewed in the flow direction of air is between 30% and 70% of the length of the side face of the aerodynamic flap (31).

5. Aerodynamic flap (11; 31) according to claim 4, characterized in that the length is configured to move relative to the aerodynamic flap (31) segment (33) of the flap when viewed in the flow direction of air is between 30% and 70% of the chord of the profile of the aerodynamic flap (31).

6. Aerodynamic flap (11; 31) according to claim 1, characterized in that for coupling movement made with the possibility of moving segment (33) of the flap with the movement of the aerodynamic flap (31) provides a mechanism for coupling for coupling the control mechanism of the aerodynamic flap (31) with the control mechanism of the segment (33) of the movable flap.

7. Highly effective is acrylic (41; 51) of the aircraft, containing affecting disruption of the flow device on at least one side face (12; 32) of the aerodynamic flap (21), characterized in that the influencing disruption of the flow device includes:
at least one device for supplying compressed air, and
at least one facing side face (42; 52) of the aerodynamic flap (41; 51) and is connected with at least one device for supplying compressed air channel (43; 54) for blowing compressed air in the surrounding space of the aerodynamic flap (41; 51).

8. High-performance flap (41; 51) of an aircraft according to claim 7, characterized in that the outgoing channel (43; 54) comes to the surface profile of the lateral faces (42; 52).

9. High-performance flap (41; 51) of an aircraft according to claim 7, characterized in that the outgoing channel (43; 54) extends at an angle between 70 and 110 to the contour of the side face (42; 52).

10. High-performance flap (41; 51) of an aircraft according to claim 7, characterized in that the outgoing channel (43; 54) has a connection for interfacing with the system of the aircraft so that is vented through an output channel (43; 54) compressed air can be fed from the system air sampling aircraft engines.

11. High-performance flap (41; 51) of an aircraft according to claim 7, characterized in that the winding is through facing the side surface (52) of the aerodynamic flap (51) channel (54) compressed air generated by the dynamic pressure.

12. High-performance flap (41; 51) of an aircraft according to claim 11, characterized in that the influencing disruption of the flow device includes at least one part facing the flow area of the aerodynamic flap (51) channel (53) and is connected to the incoming channel (53) and facing the side face (42; 52) of the aerodynamic flap (51) channel (43; 54) to be passed through the incident from the aerodynamic flap of the air.

13. Device for influencing the disruption of the flow of highly effective flap of an aircraft (11; 31), characterized in that the influencing breakdown flow device for blowing compressed air in the surrounding space of the aerodynamic flap (41; 51) contains:
at least one device for supplying compressed air, and
- at least one outgoing channel (43; 54) for blowing compressed air in the surrounding space of the aerodynamic flap (41; 51), which is made with the possibility of placing on a side face (42; 52) of the aerodynamic flap (41; 51), and
- connection piece to connect the device to the compressed air output channel.

14. The device according to item 13, wherein the outgoing channel (43; 54) are made so that it can be located in the aerodynamic flap (41; 51) in such a way that he comes to the surface profile of the lateral faces (42; 52).

Way indicated in paragraph 13 characterized in that the outgoing channel (43; 54) are made so that it can be located in the aerodynamic flap (41; 51) in such a way that it comes out at the place of exit at an angle between 70 and 110 to the contour of the side face (42; 52).

16. The device according to item 13, wherein the outgoing channel (43; 54) has a connection for interfacing with the system of the aircraft so that is vented through the discharge channel (43; 54) compressed air can be fed from the system air sampling aircraft engines.

17. The device according to item 13, characterized in that it has a compressed-air through which is fed compressed air can be vented through the opening at the side surface (52) of the aerodynamic flap (51) channel (54).

18. The device according to 17, characterized in that the influencing disruption of the flow device includes:
at least one first incoming channel (53), which can be placed in the reversed flow region of the aerodynamic flap (51), and
- communicated with the first incoming channel (53) and is made with the possibility of placing on a side face (42; 52) of the aerodynamic flap (51) outgoing channel (43; 54) for end-to-end passes resulting from the aerodynamic flap of the air.



 

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9 cl, 2 dwg

FIELD: aviation.

SUBSTANCE: aircraft (10) has fuselage (12) connected with wings, air intake (46), nose section (52) of fuselage of varying cross section and vortex generation control unit (72) located on leading-edge wing extension whose shape makes it possible to make symmetrical break of vortices on said extension and medium and large angles of attack; it is engageable with tail sections (44 and 38) spaced apart so that leading edge (36) of vertical fin (38) gets beyond trailing edges of each wing for maintenance of stability in transversal direction. Ratio of area of leading edge extension and height of vortex generation control unit is equal to 2.35 m and tolerance range changes from +100% to -50% of this magnitude.

EFFECT: improved aerodynamic properties at large angles of attack.

8 cl, 18 dwg

FIELD: aerodynamics; designing of flying vehicles, organization of aircraft motion in water.

SUBSTANCE: proposed method consists in forming regular structures for finding the conditions when axis of natural vortices is directed not in way of flow but at any angle required by conditions of flow. Infinite sequence of artificial vortices is similar to roller bearing located between body and medium. Proposed method provides for creating the lifting force for flying vehicle on base of proposed model of flowing around solid bodies by continuous media. Proposed method consists in forming the determined vortices on upper surface of wing which are directed to overwing flap where they are broken. Vortices rolling over upper surface of wing without sliding increase in size. Their destruction within overwing flap results in increase of pressure, thus creating lifting force for aircraft.

EFFECT: enhanced efficiency.

8 cl, 8 dwg

FIELD: transport.

SUBSTANCE: set of inventions relates to aircraft engineering. Steam generator comprises water tank 5, electrically-driven valves 4, 10, check valves 3, throttle 9, jacket 6, tank 2 and safety valve 1. Water flows from tank 5 via opened electrically-driven valve 4, check valve 3 and throttle 9 into jacket 6 to convert into steam. The latter flows via check valve 3 to tank 2 and, via safety valve 1, to jets on aircraft wing 7. Method of generating steam for blowing aircraft wing surface consists in using steam generator.

EFFECT: increased lifting capacity of aircraft.

2 cl, 1 dwg

FIELD: aircraft engineering.

SUBSTANCE: device to vary aerodynamic characteristics of hypersonic aircraft comprising airframe, engine, fuel system, planes and control surfaces incorporates bled gas source connected, via sealed pipelines, to permeable porous inserts intended for local gas blow-off into boundary layer of airflow. Cross section area of channels arranged in permeable porous inserts makes 30% to 60% of insert area. Distance between adjacent inserts is 6 to 10 times larger than insert width. Said permeable porous inserts are connected, via sealed pipelines, to low-temperature gas source representing a vortex tube. Proposed method consists in bleeding gas from gas source and feeding it to permeable porous inserts arranged on aircraft surfaces, using above described device, bled gas temperature being other than that of ram airflow.

EFFECT: higher lift.

14 cl, 3 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

Transport aircraft // 2287454

FIELD: aviation.

SUBSTANCE: proposed aircraft has fuselage, two half-wings, jet engine, vertical and horizontal stabilizers and landing gear. Each half-wing has through passages of rectangular section which are parallel relative to each other along half-wing span. Each through passage has lower passage whose inlet hole is located on lower surface of half-wing; upper passage is narrower as compared with lower passage and its outlet hole is located on upper surface of half-wing.

EFFECT: increased lifting force of half-wing.

8 dwg

FIELD: aeronautical engineering.

SUBSTANCE: proposed method consists in taking preheated gas from gas source and bringing it to flying vehicle surface followed by blowing-out jet of preheated mixture of air and combustion products of engine plant at subsonic velocity through local blowing-out zones on lower and/or upper surfaces of flying vehicle wing into external incoming air flow. Besides that, air is taken from air intake or from engine plant compressor and is fed over hermetic mains through adjusting members at supersonic velocity through supersonic nozzles which are flat in configuration from leading edge of wing over lower surface in way of wing chord, thus overlapping the subsonic gas jets escaping from local blowing-out zones by high-velocity air flow at Mach number more than 0.7. Device proposed for realization of this method has fuselage, power plant, engine plant, fuel system, wing and control profiles. Engine plant is connected by hermetic lines with local blowing-out zones located on surfaces of wing and control profiles. Mounted on leading edge of wing lower surface are supersonic nozzles whose external surfaces are located at level of wing surface.

EFFECT: increased lifting force.

11 cl, 4 dwg

FIELD: aviation.

SUBSTANCE: the device is designed for a flight vehicle having a fuselage, jet engine, fuel system, carrying planes and control sections. The device has a source of offtaken gas, which through sealed lines is connected to the zones of local blowing-out of gas to the boundary layer of air flow on the surfaces the flight vehicle. Each zone of local blowing-out of gas is made on the surface of the carrying plane or fuselage, or control sections with a penetrable porous insert with a cross-sectional area of the ducts in the porous insert within 50 to 60% of the area of the insert proper by 10-15 times less than the distance between the adjacent inserts, a flat rectangular slot for a break of the boundary layer is made before each insert and in parallel with it.

EFFECT: reduced drag force and fuel consumption.

10 cl, 2 dwg

FIELD: aeronautical engineering.

SUBSTANCE: proposed method includes bleeding part of preheated gas from gas source followed by delivery of bled gas to control surfaces of rudder, upper and lower surface of flying vehicle elevator.

Then, air bled from air intake or air compressor of engine plant is fed via hermetic mains through control members to supersonic nozzles which are flat in configuration from leading edges of said planes in way of chord of each rudder and elevator shutting-off local subsonic gas jets escaping from local blow-off zone in takeoff and landing modes by supersonic air flow. Turn and inclination of flying vehicle are performed by control of subsonic gas jets through local blow-off zones of rudder surfaces. Device is designed for surfaces of flying vehicle including the fuselage, engine plant, fuel system, lifting surfaces, control profiles in form of rudder and elevator; it includes local blow-off zones located on lateral surfaces of rudder, lower and upper surfaces of elevator which are connected with engine plant by means of hermetic mains. External surfaces of blow-off zones are located at level of surface of respective planes of rudders and elevators; mounted on leading edges of rudder and elevator are supersonic nozzles which are flat in configuration.

EFFECT: enhanced efficiency of control surfaces.

11 cl, 1 dwg

FIELD: heavier-than-air flying vehicles.

SUBSTANCE: proposed flying vehicle is provided with jet power plant located in center of flat wing round in plan. Power plant includes turbocompressors 13, bypass valves 14, receiver 15, adjusting valves 16 and four-section jet engine used for forming circular radially diverging air jet. Sections 17 of engine are designed for independent control during operation and are separated from one another by receiver. Upper part of body is designed for performing function of wing round in plan.

EFFECT: enhanced economical efficiency and reliability.

3 cl, 4 dwg

The invention relates to techniques for aircraft
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