CN115195996A - Airborne lightweight dual-channel circulation control unit - Google Patents
Airborne lightweight dual-channel circulation control unit Download PDFInfo
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- CN115195996A CN115195996A CN202210824345.3A CN202210824345A CN115195996A CN 115195996 A CN115195996 A CN 115195996A CN 202210824345 A CN202210824345 A CN 202210824345A CN 115195996 A CN115195996 A CN 115195996A
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- 238000013461 design Methods 0.000 abstract description 18
- 238000005516 engineering process Methods 0.000 description 6
- 230000008602 contraction Effects 0.000 description 4
- 230000009977 dual effect Effects 0.000 description 3
- 230000002411 adverse Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
- B64C21/04—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for blowing
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Abstract
The invention discloses an airborne light-weight double-channel circulation control unit, which at least comprises two independent jet flow channels, wherein the middle wall surface is shared; the jet flow channel at least comprises an air source inlet, a transition section, a rectifying section and jet flow outlets, the air source inlets of the two jet flow channels are in a cross dislocation design, the axes of the air source inlets are in the same plane and pass through the central line of the coanda profile and adopt a reverse external thread design, the transition section is a circular channel torque-shaped channel, a boss is arranged on one side of the transition section outlet, which is far away from the other jet flow channel, a pressure sensor and a temperature sensor are arranged on the boss, flow direction reinforcing ribs are arranged in the rectifying section, adjacent reinforcing ribs adopt an intermittent dislocation structure and are used for rectifying and structurally reinforcing the jet flow channels, the weight and the volume of the structure are reduced as much as possible under the condition of meeting the structural safety, the outer profile of the tail end of the circulation control unit is seamlessly combined with the outer profile of the trailing edge of the wing, and the outer profile of the tail end of the circulation control unit is positioned and fixed on an airplane through mesh supports on two sides.
Description
Technical Field
The invention belongs to the field of circulation control, relates to a double-channel circulation control unit, and particularly relates to an airborne light-weight double-channel circulation control unit.
Background
Most of the existing aircrafts adopt the traditional mechanical control surface to change the aerodynamic force and moment of the aircraft to carry out flight attitude control, but the control mode has some inherent defects: the deflection of the control surface changes the volume appearance of the airplane, destroys the invisible design of the aerodynamic appearance of the airplane and reduces the low observability; gaps, steps, bulges and the like generated between the movable surface and the stabilizing surface as well as between the movable surfaces destroy the seamless and smooth continuous design criteria of the wings and increase the additional aerodynamic resistance; limited by the pressure of the incoming flow speed, the control efficiency is low at low speed, and the control capability is insufficient; complex control link, heavy structure, low space utilization rate, complex maintenance and the like. Therefore, the traditional mechanical control plane control mode cannot meet the higher requirements of the pneumatic/stealth/control/structure integrated design of the airplane in future battles, and a new pneumatic control technology needs to be developed urgently.
The active jet circulation control technology realizes the mechanical control surface-free flight control of the aircraft by generating a virtual control surface through jet, and is an active flow control technology with great potential. The circulation control unit is used as an active jet circulation control exciter and is the key of the application of the active jet circulation control technology. The jet flow seam channel is arranged along the spanwise direction at the trailing edge of the wing, and high-temperature and high-pressure gas is sprayed out from the exciter trailing edge seam channel through the internal flow channel. For the large-width-to-height ratio circulation control unit, the uniformity of jet flow in the spanwise direction is guaranteed, the pressure loss is reduced, the requirement of high-pressure ratio gas on the structural strength is met, the requirement of narrow installation space of a sharp trailing edge wing is met, the weight of an exciter directly influences the engineering applicability of the active jet flow circulation control technology, and therefore the airborne circulation control unit is very much in design constraint and complex.
From the above, the circulation control unit is a key pneumatic component for realizing the jet circulation control technology and is also a very important component for being pushed to engineering application, so that the design of the airborne light-weight dual-channel circulation control unit is needed to be developed.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide an airborne light-weight double-channel circulation control unit which can meet the requirements of high-pressure ratio air source control and narrow wing trailing edge installation space.
The purpose of the invention is realized by the following technical scheme:
an airborne light-weight double-channel circulation control unit comprises a first jet flow channel and a second jet flow channel, wherein the first jet flow channel and the second jet flow channel are respectively and sequentially provided with an air source inlet, a transition section, a rectifying section and a jet flow outlet; the gas source inlets comprise a first gas source inlet and a second gas source inlet which respectively correspond to the first jet flow channel and the second jet flow channel, the first gas source inlet and the second gas source inlet are arranged in a staggered mode, the axes of the two gas source inlets are parallel and are in the same plane, and the plane passes through the tail end of the control unit and is provided with a central line of the coanda profile; the first jet flow channel and the second jet flow channel are arranged in an overlapped mode, and the two jet flow channels share a middle wall surface in the rectifying section; jet flow outlets of the first jet flow channel and the second jet flow channel are respectively provided with a jet flow nozzle, the tail end of the middle wall surface is provided with a coanda profile, the coanda profiles are symmetrically arranged relative to the center line of the middle wall surface, and the coanda profiles are positioned at the downstream of the jet flow nozzles; and the first fluidic channel and the second fluidic channel share the coanda profile.
According to a preferred embodiment, the transition section is located downstream of the air supply inlet and is a circular channel torqued channel.
According to a preferred embodiment, the side wall of the transition section is provided with a pressure sensor mounting boss and a temperature sensor mounting boss, and the pressure sensor mounting boss and the temperature sensor mounting boss are respectively provided with a pressure sensor and a temperature sensor so as to monitor the pressure and the temperature in the flow channel.
According to a preferred embodiment, the fairing section is located downstream of the transition section and the fairing section jet passage increases in the spanwise direction with increasing flow direction distance.
According to a preferred embodiment, the jet channel of the rectifying section is divided into several uniform sub-jet channels at intervals.
According to a preferred embodiment, the jet channels of the fairing sections are evenly arranged with flow direction reinforcing ribs in the spanwise direction. The jet flow channel is divided into a plurality of sub-jet flow channels and structures, and the structure reinforcement of the jet flow channel is realized.
According to a preferred embodiment, each reinforcing rib is arranged in an intermittent staggered structure, and two adjacent sub-jet flow channels are not closed and communicated in the spanwise direction. By adopting the intermittent staggered structure for each reinforcing rib, two adjacent sub-jet flow channels are not closed, the two sub-jet flow channels can be communicated in the spanwise direction, and the flow direction positions are complementary, so that the spanwise flow between the jet flow channels is promoted while the structural strength is ensured, the uniformity of the pressure in the jet flow channels in the spanwise direction is ensured, and the uniformity of the flow of a jet flow outlet is promoted.
According to a preferred embodiment, the end of the jet nozzle is provided with a constriction. The contraction ratio of the contraction section is larger than 10, and the purpose of reducing the jet speed in the channel is achieved.
According to a preferred embodiment, the first air supply inlet and the second air supply inlet are circular pipes, and the outer wall of each pipe is provided with reverse external threads.
According to a preferred embodiment, a step is arranged on the side wall of the tail end of the circulation control unit, the downstream outer profile of the step is consistent with the outer profile of the trailing edge of the wing, the rear part of the circulation control unit is seamlessly combined with the outer profile of the trailing edge of the wing at the step, and the front part of the circulation control unit at the step is arranged in the wing.
According to a preferred embodiment, a plurality of net-shaped supports are arranged on two sides of the circulation control unit to realize positioning, installation and fixation of the circulation control unit.
The aforementioned main aspects of the invention and their respective further alternatives may be freely combined to form a plurality of aspects, all of which are aspects that may be adopted and claimed by the present invention. The skilled person in the art can understand that there are many combinations, which are all the technical solutions to be protected by the present invention, according to the prior art and the common general knowledge after understanding the scheme of the present invention, and the technical solutions are not exhaustive herein.
The invention has the beneficial effects that:
according to the airborne light-weight double-channel circulation control unit provided by the invention, the two channels are mutually independent and can be respectively controlled, and the increase of the drift diameter of the air source inlet is realized under the condition of limited internal space at the rear edge of the wing through the design of the crossed and staggered air source inlets, so that the pressure loss of a pipeline is reduced;
through the reverse thread design of the air source inlet and the external casing, the quick connection and sealing of the annular control unit, the air supply pipeline and the like in a narrow space can be realized;
the flow direction reinforcing rib rectification design is adopted, the adverse stress of the simply supported beam is reduced, the rectangular frame with large width-to-height ratio is changed into a plurality of rectangular frames with small width-to-height ratio, the uniformity of the spanwise jet flow is improved, the wall surface thickness of the jet flow channel is reduced, and the structural weight and the space volume of the circulation control unit are reduced under the condition of meeting the structural strength;
and each reinforcing rib adopts an intermittent staggered structure, the adjacent two sub-jet flow channels are not closed, the spanwise directions can be communicated, and the flow direction positions form complementation, so that the spanwise flow between the jet flow channels is promoted while the structural strength is ensured, the uniformity of the pressure in the jet flow channels along the spanwise direction is ensured, and the uniformity of the flow of a jet flow outlet is promoted;
the structural weight and the space volume of the circulation control unit are further reduced by the design that the two runners share the middle wall surface;
the pressure sensor and the temperature sensor are arranged in the jet flow channel and used as terminal feedback to realize closed-loop control of jet flow control;
seamless integration in the wing is realized through the seamless combination design of the outer profile of the rear part of the circulation control unit and the outer profile of the trailing edge of the wing; the mesh-shaped supports for fixing are arranged on the two sides of the circulation control unit, so that the circulation control unit can be quickly installed and fixed.
Drawings
FIG. 1 is a schematic structural diagram of an airborne lightweight dual channel circulation control unit of the present invention;
FIG. 2 is a sectional view of the onboard lightweight two-channel circulation control unit installed inside a wing;
FIG. 3 is a trailing edge cross-sectional view of the airborne lightweight dual channel ring control unit of the present invention;
FIG. 4 is a cross-sectional view of the internal flow passage of the airborne lightweight dual channel circulation control unit of the present invention;
the device comprises a 0-circulation control unit, a 1-first jet flow channel, a 2-second jet flow channel, a 3-first air source inlet, a 4-second air source inlet, a 5-first air source inlet reverse external thread, a 6-second air source inlet reverse external thread, a 7-first air source inlet axis, a 8-second air source inlet axis, a 9-middle wall surface, a 10-transition section, a 11-pressure sensor mounting boss, a 12-temperature sensor mounting boss, a 13-step, a 14-coanda profile, a 15-mesh bracket, a 16-jet flow nozzle, a 17-contraction section, an 18-circulation control unit outer profile, a 19-wing trailing edge outer profile, a 21-rectification section and a 22-flow direction reinforcing rib.
Detailed Description
The following embodiments of the present invention are provided by way of specific examples, and other advantages and effects of the present invention will be readily apparent to those skilled in the art from the disclosure herein. The invention is capable of other and different embodiments and of being practiced or of being carried out in various ways, and its several details are capable of modification in various respects, all without departing from the spirit and scope of the present invention. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict. It should be noted that, in order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention are clearly and completely described below, and it is obvious that the described embodiments are some embodiments of the present invention, but not all embodiments.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. indicate orientations and positional relationships that are conventionally used in the products of the present invention, and are used merely for convenience in describing the present invention and for simplicity in description, but do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another, and are not to be construed as indicating or implying relative importance.
Furthermore, the terms "horizontal", "vertical", "overhang" and the like do not imply that the components are required to be absolutely horizontal or overhang, but may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in a specific case to those of ordinary skill in the art.
Example 1:
referring to fig. 1 to 4, the invention discloses an airborne light-weight dual-channel circulation control unit 0, wherein the circulation control unit 0 comprises a first jet flow channel 1 and a second jet flow channel 2, and the first jet flow channel 1 and the second jet flow channel 2 are respectively and sequentially provided with an air source inlet, a transition section 10, a rectification section 21 and a jet flow outlet.
Preferably, the gas source inlet comprises a first gas source inlet 3 and a second gas source inlet 4 which respectively correspond to the first fluidic channel 1 and the second fluidic channel 2, and the first gas source inlet 3 and the second gas source inlet 4 are arranged in a staggered mode. The two channels are mutually independent and can be respectively controlled, and the purposes of increasing the drift diameter of the air source inlet and reducing the pressure loss of the pipeline under the condition of limited internal space at the rear edge of the wing are realized through the design of the crossed and staggered air source inlets.
Further, the two source inlet axes are parallel and in the same plane through the mid-line of the coanda profile 14 at the end of the control unit.
Preferably, the first air source inlet 3 and the second air source inlet 4 are circular pipelines, and the outer wall is provided with reverse external threads. Through the reverse thread design of air supply entry, through external sleeve pipe, can realize the high-speed joint and the sealed of ring volume control unit and air supply line etc. in narrow and small space.
Preferably, the transition section 10 is located downstream of the air supply inlet and is a circular channel torqued channel.
Preferably, a pressure sensor mounting boss 11 and a temperature sensor mounting boss 12 are arranged on the side wall of the transition section 10, and a pressure sensor and a temperature sensor are respectively arranged on the pressure sensor mounting boss 11 and the temperature sensor mounting boss 12 to complete pressure and temperature monitoring in the flow channel. A pressure sensor and a temperature sensor are arranged in the jet flow channel and used as terminal feedback to realize closed-loop control of jet flow control.
Preferably, the rectifying section 21 is located downstream of the transition section 10, and the jet passage of the rectifying section 21 gradually increases in the spanwise direction as the distance of the flow direction increases.
Further, the jet flow channel of the rectifying section 21 is gradually divided into a plurality of uniform small jet flow channels by adopting a 2-division method.
Further, a plurality of flow direction reinforcing ribs 22 are uniformly arranged on the jet flow channel of the rectifying section 21 in the spanwise direction, so that the separation and the structural reinforcement of the jet flow channel are completed.
The flow direction reinforcing rib 22 is adopted for rectification, so that the adverse stress of the simply supported beam is reduced, the rectangular frame with a large width-to-height ratio is changed into a plurality of rectangular frames with small width-to-height ratios, the uniformity of the spanwise jet flow is improved, the wall surface thickness of the jet flow channel is reduced, and the structural weight and the space volume of the circulation control unit are reduced under the condition of meeting the structural strength.
Furthermore, each reinforcing rib 22 is arranged in an intermittent staggered structure, and two adjacent sub-jet flow channels are not closed and communicated in the spreading direction. By adopting the intermittent staggered structure of each reinforcing rib, two adjacent sub-jet flow channels are not closed, the two sub-jet flow channels can be communicated in the spanwise direction, and the flow direction positions form complementation, so that the spanwise flow between the jet flow channels is promoted while the structural strength is ensured, the uniformity of the pressure in the jet flow channels in the spanwise direction is ensured, and the uniformity of the flow of jet flow outlets is promoted.
Further, the first jet flow channel 1 and the second jet flow channel 2 are arranged in an overlapped mode, and the two jet flow channels share the middle wall surface 9 in the rectifying section 21. The structural weight and the space volume of the circulation control unit are further reduced by the design that the two flow passages share the middle wall surface.
Preferably, the jet outlets of the first jet channel 1 and the second jet channel 2 are respectively provided with a jet nozzle 16, the end of the middle wall surface 9 is provided with a coanda type, and the coanda profiles are symmetrically arranged relative to the midline of the middle wall surface 9 and are positioned at the downstream of the jet nozzle 16. And the first fluidic channel 1 and the second fluidic channel 2 share the coanda profile.
Preferably, the end of the jet nozzle 16 is provided with a constriction 17. The contraction ratio of the contraction section 17 is larger than 10, and the purpose of reducing the jet speed in the channel is achieved.
Preferably, a step 13 is arranged on the side wall of the tail end of the circulation control unit 0, the downstream outer profile of the step 13 is consistent with the outer profile of the trailing edge of the wing, the rear part of the circulation control unit 0 at the step 13 is seamlessly combined with the outer profile 19 of the trailing edge of the wing, and the front part of the circulation control unit 0 at the step 13 is arranged inside the wing. The seamless integration of the circulation control unit 0 in the wing is realized through the seamless combination design of the outer profile of the rear part of the circulation control unit and the outer profile of the trailing edge of the wing.
Preferably, a plurality of net-shaped supports 15 are arranged on two sides of the circulation control unit 0 to realize positioning, mounting and fixing of the circulation control unit 0. The mesh-shaped supports for fixing are arranged on the two sides of the circulation control unit, so that the circulation control unit can be quickly installed and fixed.
Through the structural design of the circulation control unit, the circulation control unit can meet the requirements of high-pressure-ratio air source control and narrow wing trailing edge installation space.
According to the invention, through the staggered design of the air source inlets, the diameter of the air source inlets is increased under the condition of meeting the requirement of a smaller installation space at the rear edge of the wing, the flowing pressure loss in a pipeline is reduced, the structural weight is reduced through the reinforcing ribs, the flowing uniformity is increased, the pressure and temperature feedback of the terminal is realized by arranging the pressure and temperature sensors, and the pressure and temperature feedback device has the advantages of simple structure, light weight and small volume.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (10)
1. The airborne light-weight double-channel circulation control unit is characterized in that the circulation control unit (0) comprises a first jet flow channel (1) and a second jet flow channel (2), wherein the first jet flow channel (1) and the second jet flow channel (2) are respectively and sequentially provided with an air source inlet, a transition section (10), a rectifying section (21) and a jet flow outlet;
the gas source inlets comprise a first gas source inlet (3) and a second gas source inlet (4) which respectively correspond to the first jet flow channel (1) and the second jet flow channel (2), the first gas source inlet (3) and the second gas source inlet (4) are arranged in a staggered mode, the axes of the two gas source inlets are parallel and in the same plane, and the plane passes through the middle line of the coanda profile (14) arranged at the tail end of the circulation control unit (0);
the first jet flow channel (1) and the second jet flow channel (2) are arranged in an overlapped mode, and the two jet flow channels share a middle wall surface (9) in the rectifying section;
the jet flow outlets of the first jet flow channel (1) and the second jet flow channel (2) are respectively provided with a jet flow nozzle (16), the tail end of the middle wall surface (9) is provided with a coanda profile (14), the coanda profiles (14) are symmetrically arranged relative to the central line of the middle wall surface (9), and the coanda profiles (14) are positioned at the downstream of the jet flow nozzles (16); and the first fluidic channel (1) and the second fluidic channel (2) share said coanda profile (14).
2. The circuit-volume control unit as claimed in claim 1, characterized in that the transition section (10) is located downstream of the gas supply inlet and is a circular-channel torqued channel.
3. The circulation control unit according to claim 2, wherein the side wall of the transition section (10) is provided with a pressure sensor mounting boss (11) and a temperature sensor mounting boss (12), and the pressure sensor mounting boss (11) and the temperature sensor mounting boss (12) are respectively provided with a pressure sensor and a temperature sensor to monitor the pressure and the temperature in the flow passage.
4. A circuit volume control unit according to claim 2, characterized in that the rectifying section (21) is located downstream of the transition section (10) and that the jet passage of the rectifying section (21) increases in the spanwise direction with increasing flow direction distance.
5. A circulation control unit according to claim 4, wherein the fluidic channels of the rectifying section (21) are divided into a number of uniform sub-fluidic channels at intervals.
6. A circulation control unit according to claim 4, wherein the fluidic channels of the rectifying section (21) are arranged with flow direction reinforcing ribs (22) in the spanwise direction.
7. The circulation control unit according to claim 6, wherein each reinforcing rib (22) is arranged in an intermittent staggered structure, and adjacent two sub-jet flow channels are not closed and are communicated in the spanwise direction.
8. A circulation control unit according to claim 1, wherein the jet nozzle (16) is provided with a constriction (17) at its end, the constriction (17) having a constriction ratio greater than 10.
9. A circuit-volume control unit according to claim 1, characterized in that the first (3) and second (4) gas supply inlets are circular pipes, the outer wall of which is provided with counter external threads.
10. The circulation control unit according to claim 1, characterized in that the side wall of the tail end of the circulation control unit (0) is provided with a step (13), the downstream outer profile of the step (13) is consistent with the outer profile (19) of the trailing edge of the wing, the rear part of the circulation control unit (0) is seamlessly combined with the outer profile (19) of the trailing edge of the wing at the step (13), and the front part of the circulation control unit (0) at the step (13) is arranged in the wing;
and a plurality of net-shaped supports (15) are arranged on two sides of the circulation control unit (0) to realize the positioning, installation and fixation of the circulation control unit (0).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210824345.3A CN115195996A (en) | 2022-07-14 | 2022-07-14 | Airborne lightweight dual-channel circulation control unit |
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| CN202210824345.3A CN115195996A (en) | 2022-07-14 | 2022-07-14 | Airborne lightweight dual-channel circulation control unit |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115373451A (en) * | 2022-10-21 | 2022-11-22 | 中国空气动力研究与发展中心低速空气动力研究所 | Method and test platform for obtaining flow control strategy of circular quantity exciter |
| CN115571329A (en) * | 2022-12-09 | 2023-01-06 | 中国空气动力研究与发展中心低速空气动力研究所 | Wing structure, flow control method thereof, aircraft and flow control test model |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115373451A (en) * | 2022-10-21 | 2022-11-22 | 中国空气动力研究与发展中心低速空气动力研究所 | Method and test platform for obtaining flow control strategy of circular quantity exciter |
| CN115571329A (en) * | 2022-12-09 | 2023-01-06 | 中国空气动力研究与发展中心低速空气动力研究所 | Wing structure, flow control method thereof, aircraft and flow control test model |
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