CN115520373A - Jet flow control mechanism for controlling airflow direction of flow field at trailing edge of aircraft wing - Google Patents
Jet flow control mechanism for controlling airflow direction of flow field at trailing edge of aircraft wing Download PDFInfo
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- CN115520373A CN115520373A CN202210989803.9A CN202210989803A CN115520373A CN 115520373 A CN115520373 A CN 115520373A CN 202210989803 A CN202210989803 A CN 202210989803A CN 115520373 A CN115520373 A CN 115520373A
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- jet
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/28—Leading or trailing edges attached to primary structures, e.g. forming fixed slots
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/58—Wings provided with fences or spoilers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C2230/00—Boundary layer controls
- B64C2230/04—Boundary layer controls by actively generating fluid flow
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
Abstract
The invention provides a jet flow control mechanism for controlling the airflow direction of a wing trailing edge flow field of an aircraft, which belongs to the technical field of aircraft control and comprises a leading edge bleed air, a shell, a flow deflector, a flow control sheet, a Coanda trailing edge, a jet flow direction control sheet, a jet flow adjusting system, a transmission system component, an auxiliary jet flow control system and an auxiliary jet flow control valve; the jet flow control mechanism is arranged along the chord line direction of the airfoil of the aircraft, and the leading edge bleed air and the shell are coaxially arranged; the jet flow adjusting system is arranged at one side of the leading edge bleed air close to the shell, and the movable end of the transmission system component is connected with the flow control sheet; the jet flow direction control sheet is connected with the flow deflector, and one end far away from the leading edge bleed air is provided with an air outlet; the secondary jet control system, the secondary jet control valve and the Coanda trailing edge are symmetrically disposed within the interior cavity of the jet direction control segment. The invention solves the problem that the prior art can not realize the control of the virtual control surface, and applies the jet flow control mechanism technology to the wings of the high-speed aircraft.
Description
Technical Field
The invention belongs to the technical field of aircraft control, and particularly relates to a jet flow control mechanism for controlling the airflow direction of a flow field at the trailing edge of an aircraft wing.
Background
In view of the long-term goals of aircraft development, the problems of aircraft stability and maneuverability must be addressed. At present, the performance of the aircraft is to be improved to the utmost extent by the optimal design of the structural layout. Therefore, a feasible method is to seek a solution from the viewpoint of enhancing the control efficiency of the aerodynamic control surface and improving the maneuverability of the aircraft. The blowing and suction control technique can significantly improve the aerodynamic (moment) performance of an aircraft by sucking off inefficient fluid in the boundary layer of the surface of a proximate object and replacing it with a portion of free flow with high momentum.
The technology has good pneumatic advantages in low-speed test verification, is limited by the characteristic that the airfoil of the high-speed aircraft is thin and long, and is greatly limited in the process of popularization and application to high speed.
In conclusion, under the condition of strong geometric constraint, the blowing and air suction control technology is realized, the wing structure of the aircraft needs to be redesigned, the existing jet flow control mechanism technology cannot be applied to the wing of the high-speed aircraft, and improvement is needed.
Disclosure of Invention
The invention provides a jet flow control mechanism for controlling the airflow direction of a flow field at the trailing edge of an aircraft wing, and aims to solve the problem that the existing jet flow control mechanism technology cannot be applied to the wing of a high-speed aircraft.
The purpose of the invention is realized by the following technical scheme:
a jet flow control mechanism for controlling the airflow direction of a wing trailing edge flow field of an aircraft comprises a leading edge bleed air, a shell, a flow deflector, a flow control sheet, a Coanda trailing edge, a jet flow direction control sheet, a jet flow adjusting system, a transmission system component, an auxiliary jet flow control system and an auxiliary jet flow control valve; the jet flow control mechanism is arranged along the chord direction of an airfoil of the aircraft, an opening of the leading edge bleed air is arranged in the middle of the leading edge of the airfoil of the aircraft, the leading edge bleed air and the shell are coaxially arranged, one side of the shell, which is intersected with the leading edge bleed air, is in smooth transition, and one side, which is far away from the leading edge bleed air, is provided with an air outlet; the jet flow adjusting system is arranged on one side, close to the shell, of the leading edge bleed air, the flow deflector comprises an upper piece and a lower piece, one side of the flow deflector is arranged at the corner of the cross section of the shell, one sides far away from the leading edge bleed air are intersected, and the intersection line is positioned in the shell; the flow control sheet comprises an upper sheet and a lower sheet which are respectively arranged in an upper airfoil surface cavity and a lower airfoil surface cavity formed between the flow deflector and the shell; the fixed end of the transmission system component is arranged on one side of the shell facing the flow deflector, and the movable end of the transmission system component is connected with the flow control sheet; the section of the jet flow direction control sheet is streamline, the blunt end is arranged towards one side of the leading edge bleed air and connected with the flow deflector, and the end far away from the leading edge bleed air is provided with an air outlet; the auxiliary jet flow control system, the auxiliary jet flow control valve and the Coanda trailing edge are symmetrically arranged in an inner cavity of the jet flow direction control sheet, the auxiliary jet flow control system is connected with a self-contained gas storage cylinder or shunts leading edge bleed air to form a stable auxiliary jet flow gas with controllable flow, and the stable auxiliary jet flow gas is ejected along the Coanda trailing edge under the control of the auxiliary jet flow control valve; a jet flow outlet is formed between the jet flow direction control sheet and the shell; an auxiliary jet outlet is formed between the jet direction control sheet and the Coanda trailing edge; the Coanda trailing edge is semi-circular with a diameter sized according to the aircraft airfoil, the jet outlet and the secondary jet outlet.
As further optimization, the jet flow adjusting system is arranged on one side, close to the shell, of the leading edge bleed air and is 5-8 mm away from the intersection.
As a further optimization, the Coanda trailing edge adopts an internal hollow structure.
As a further optimization, the drive train assembly includes a drive assembly and a lead screw assembly.
As a further optimization, the jet flow regulating system comprises a pressure increasing valve, a speed regulating valve and a throttle valve.
As a further optimization, the section of the leading edge bleed air is in an isosceles trapezoid shape.
As a further optimization, the cross section of the shell is in a diamond shape, a trapezoid shape or a polygon shape.
The beneficial technical effects obtained by the invention are as follows:
by adopting the technical scheme provided by the invention, the front edge forms the effect of reducing heat flow accumulation by air suction, and the rear edge forms the effect similar to virtual control surface control. Compared with the prior art, the method can realize the effects of reducing heat of the front edge of the wing profile of the aircraft, reducing heat load and pressure load accumulation of a rudder joint, increasing lift of the wing profile and a virtual control surface, successfully applies the jet flow control mechanism technology to the wing of the high-speed aircraft, solves the problems existing in the prior art, and has outstanding substantive characteristics and remarkable progress.
Drawings
FIG. 1 is a schematic mechanical diagram of one embodiment of the present invention;
FIG. 2 is a schematic diagram of the state of the mechanism for forming a Coanda jet according to one embodiment of the present invention;
FIG. 3 is an enlarged view of a portion of FIG. 2 at A;
FIG. 4 is a schematic diagram of the mechanism for forming a free jet according to one embodiment of the present invention;
FIG. 5 is a top view of FIG. 4;
FIG. 6 is a simulated cloud of trailing edge jet control in a high velocity flow field in accordance with one embodiment of the present invention;
FIG. 7 is a graph of the aerodynamic coefficient of the airfoil of the present invention as a function of the total jet pressure ratio at a height H =30 km;
reference numerals: 1. leading edge air entraining; 2. a housing; 3. a flow deflector; 4. a flow control plate; 5. a jet outlet; 6. an auxiliary jet outlet; 7. the Coanda trailing edge; 8. a jet direction control sheet; 11. a jet regulation system; 12. a driveline component; 13. an auxiliary jet control system; 14. an auxiliary jet control valve.
Detailed Description
The technical solution of the present invention will be further described in detail with reference to the accompanying drawings and the detailed description. It is to be understood that the described embodiments are merely a few embodiments of the invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the invention without making any creative effort, shall fall within the scope of the claimed invention.
The jet flow control mechanism comprises a wing section leading edge flow field bleed air part, an inner flow channel flow control part and a wing section trailing edge flow field jet flow and flow direction deflection part, and achieves the effect of aircraft attitude control by adjusting the size and the flow direction of bleed air and jet air according to the requirement of aircraft flight torque. The jet flow control mechanism collects gas required by jet flow by using a front edge air entraining part of the mechanism and realizes vector jet flow by using a rear edge jet flow control system.
As shown in fig. 1 to 5, the jet control mechanism in this embodiment includes a leading edge bleed air (1), a housing (2), a guide vane (3), a flow control vane (4), a Coanda trailing edge (7), a jet direction control vane (8), a jet regulation system (11), a transmission system component (12), an auxiliary jet control system (13), and an auxiliary jet control valve (14).
In this embodiment, the jet control mechanism is disposed along the chord line direction of the airfoil of the aircraft, taking the position in fig. 2 as an example, the left side in the figure is front, i.e., facing the head of the aircraft, and the right side is rear, and the upper and lower sides are correspondingly consistent with the upper and lower sides of the airfoil.
In the embodiment, the leading edge bleed air (1) and the shell (2) are coaxially arranged, and the specific shape and size are determined according to the performance and aerodynamic shape requirements of the airfoil of the high-speed aircraft. The section of the leading edge bleed air (1) in the embodiment is isosceles trapezoid. One side of the shell (2) intersected with the leading edge bleed air (1) is in smooth transition, and one side far away from the leading edge bleed air (1) is provided with an air outlet. The cross section of the shell (2) can be designed into various shapes such as trapezoid, polygon and the like according to the shape of the wing of the aircraft, and the shell is designed into a diamond shape in the specific embodiment, so that the advantage that airflow in the wing profile can flow more uniformly is achieved.
The jet regulating system (11) is arranged in the leading edge bleed air (1) on the side close to the housing (2) in this particular embodiment, preferably at a distance of 5-8 mm from the intersection, and the air flow is relatively stable, in particular at a position related to the total length of the leading edge bleed air (1), in this particular embodiment at a distance of 6mm from the intersection. The jet flow regulating system (11) comprises a pressure increasing valve, a speed regulating valve and a throttle valve and is used for regulating parameters such as flow, air flow pressure and the like.
In the embodiment, the flow deflector (3) comprises an upper piece and a lower piece, wherein one side of the flow deflector is respectively arranged at the corner of the cross section of the shell (2), and one side of the flow deflector, which is far away from the leading edge bleed air (1), is intersected and the intersection line is positioned inside the shell (2).
In the embodiment, the flow control sheet (4) comprises an upper sheet and a lower sheet which are respectively arranged in an upper wing surface cavity and a lower wing surface cavity formed between the flow deflector (3) and the shell (2), the transmission system components (12) comprise two sets, each set comprises a driving component and a screw rod component, a fixed end is arranged on one side, facing the flow deflector (3), of the shell (2), and a movable end is connected with the flow control sheet (4) and used for driving the flow control sheet (4) and the jet flow direction control sheet (8) to rotate and is automatically opened in due time according to regulation requirements, so that airflow smoothly flows to the upper wing surface cavity or the lower wing surface cavity and is matched with the jet flow direction control sheet (8) to realize the flow speed regulation effect in a certain range.
In the embodiment, the cross section of the jet flow direction control sheet (8) is streamline, the blunt end is arranged towards one side of the leading edge bleed air (1) and is connected with the flow deflector (3), and the end far away from the leading edge bleed air (1) is provided with an air outlet.
In the embodiment, the auxiliary jet flow control system (13), the auxiliary jet flow control valve (14) and the Coanda trailing edge (7) are symmetrically arranged in an inner cavity of the jet flow direction control sheet (8), the auxiliary jet flow control system (13) is connected with a self-contained air storage bottle or divides the leading edge bleed air (1) to form a stable auxiliary jet flow gas with controllable flow, and the stable auxiliary jet flow gas is ejected along the Coanda trailing edge (7) under the control of the auxiliary jet flow control valve (14). The Coanda trailing edge (7) in this particular embodiment is of a hollow design in order to reduce the structural mass. Since the auxiliary jet control system (13) is embedded in the wing of a high-speed aircraft, the length of the auxiliary jet control system (13) is determined by the length of the wing of the aircraft, i.e. the distance between the leading edge bleed air (1) and the Coanda trailing edge (7) is determined by the length of the wing of the aircraft, which is an unchangeable precondition.
In the embodiment, a jet flow outlet (5) is formed between the jet flow direction control sheet (8) and the shell (2). An auxiliary jet outlet (6) is formed between the jet direction control sheet (8) and the Coanda trailing edge (7).
In this embodiment, the leading edge bleed air (1), the casing (2), the flow deflector (3), the flow control plate (4), the transmission system component (12), the Coanda trailing edge (7), the jet flow direction control plate (8) and the jet flow regulation system (11) are all improved on the basis of the prior art, and by changing a local structure in the airfoil, the flow direction of the overall airflow in the airfoil is ensured, so that vector jet flow is realized.
The auxiliary jet flow control valve (14) in the embodiment has the function of enabling the auxiliary jet flow to flow out from the upper or lower auxiliary jet flow outlet (6), and mainly aims to be matched with the flow control sheet (4) to achieve disturbance effects of different degrees on the main jet flow, form Coanda trailing edge wall attachment effects of different degrees and adapt to control requirements under multiple working conditions.
Because the high-speed flow field pressure is large, the deflection difficulty of the jet flow vector is large, the Coanda jet flow is not enough to meet the control capability of the virtual rudder effect, and an auxiliary jet flow control system (13) and an auxiliary jet flow control valve (14) are additionally added to achieve the control purpose of the virtual rudder effect.
The opening of the leading edge bleed air (1) is arranged in the middle of the leading edge of the aircraft wing profile, the Coanda trailing edge (7) is semicircular, and the diameter is determined according to the size of the aircraft wing profile, the jet outlet (5) and the auxiliary jet outlet (6).
In the embodiment, the jet control mechanism based on the auxiliary jet is used according to the following method:
s100, extending the chord length of the airfoil profile and increasing the lift force of the airfoil profile
The airfoil profile is in an original state of 0 attack angle, the flow control sheet (4) and the jet flow direction control sheet (8) are maintained in a vertically symmetrical state, the auxiliary jet flow control valve (14) is closed, and the airflow flow rates of the upper flow channel and the lower flow channel are the same.
According to the actual pneumatic control requirement of the wing profile, the flow of bleed air is controlled by a jet flow adjusting system (11) and the flow of jet flow is controlled by a transmission system component (12). When the flow is needed to be large, the jet flow adjusting system (11) and the transmission system assembly (12) are required to be increased, the upper and lower opening degrees of the flow control sheet (4) are kept to be the same, the same airflow of the upper and lower flow channels is ensured, jet flow is ejected up and down symmetrically, a virtual aerodynamic surface is formed, the chord length of the airfoil profile is extended, and the purpose of increasing the lift force is achieved.
S200, when the downward virtual rudder deflection is formed by the wing profile, two basic forms are provided, specifically as follows:
s201, when the wing profile is required to form a downward small virtual rudder deflection
The flow of the air flow passing through the jet flow regulating system (11) is reduced. At the same time, the upper flow control plate (4) is opened, and the lower flow control plate (4) and the lower auxiliary jet control valve (14) are closed. The air flow is induced to form a Coanda jet at the trailing edge of the airfoil by means of an auxiliary jet control system (13). The opening sizes of the upper side flow control sheet (4) and the upper side auxiliary jet flow control valve (14) are utilized to control the flow and the flow velocity of jet flow; changing the flow direction of the Coanda jet by utilizing the jet direction control sheet (8) to realize the purpose of changing the virtual rudder deflection angle;
s202, when the wing profile is required to form a downward large virtual rudder deflection
The flow rate of the air flow passing through the jet flow regulating system (11) is regulated to be large. At the same time, the lower flow control plate (4) is opened, and the upper flow control plate (4) and the upper auxiliary jet control valve (14) are closed. The jet flow adjusting system (11) and the lower side flow control piece (4) are used for adjusting the flow of the jet flow at the tail edge of the wing profile, and the jet flow direction control piece (8) is used for controlling the jet flow direction, so that the purpose of changing the deflection angle of the virtual rudder is achieved.
S300, when the wing profile is required to form an upward virtual rudder deflection
There are also two basic forms, the virtual rudder deflection angle is adjusted through a jet flow adjusting system (11), a flow control sheet (4), an auxiliary jet flow control system (13) and an auxiliary jet flow control valve (14), but the operation direction is opposite to the time when the wing profile is required to form a downward virtual rudder deflection, and the two basic forms are as follows:
s301, when the wing profile is required to form an upward small virtual rudder deflection
The flow of the air flow passing through the jet flow regulating system (11) is regulated to be small. At the same time, the lower flow control plate (4) is opened, and the upper flow control plate (4) and the upper auxiliary jet control valve (14) are closed. The air flow is induced to form a Coanda jet at the trailing edge of the airfoil by means of an auxiliary jet control system (13). The opening size of the lower side flow control sheet (4) and the lower side auxiliary jet flow control valve (14) is utilized to control the flow and the flow speed of jet flow; changing the flow direction of the Coanda jet by utilizing the jet direction control sheet (8) to realize the purpose of changing the virtual rudder deflection angle;
s302, when the wing profile is required to form an upward large virtual rudder deflection
The flow rate of the air flow passing through the jet flow regulating system (11) is regulated to be large. At the same time, the upper flow control plate (4) is opened, and the lower flow control plate (4) and the lower auxiliary jet control valve (14) are closed. The jet flow adjusting system (11) and the upper side flow control piece (4) are used for adjusting the flow of the jet flow at the tail edge of the wing profile, and the jet flow direction control piece (8) is used for controlling the jet flow direction, so that the purpose of changing the deflection angle of the virtual rudder is achieved.
By using an artificial intelligence method and through big data analysis, the flow control sheet (4) and the jet flow direction adjusting sheet (8) can be matched, the directions and the sizes of the upper jet flow and the lower jet flow are matched, and virtual pneumatic rudders with different rudder deflection angles are formed as required.
The beneficial technical effects obtained by the specific embodiment are as follows:
in order to verify the influence of the jet flow of the airfoil trailing edge of the high-speed aircraft on the moment of the aircraft, relevant pneumatic simulation work is carried out. The simulation result is shown in fig. 4, and research shows that jet flow at the tail edge of the aircraft airfoil in a high-speed flow field has stronger aerodynamic force change on the airfoil. As shown in fig. 5, different jet pressure ratios have a greater difference in aerodynamic effect at the same height.
As can be seen in FIG. 4, high-speed jet flows are generated on the upper side of the tail edge of the wing of the high-speed aircraft, under the influence of tail edge gas compression, airflow is ejected out on the upper side along the flow direction, a downward 'virtual control surface' is formed by the compressed gas, and the lift force and the pitching moment formed by jet flows generated by different air pressure ratios are linearly changed, but the resistance is not greatly changed. This concrete embodiment can produce the effect of rudder face deflection control, compares with prior art and has reduced the rudder seam, has reduced heat accumulation and the pressure accumulation that produces in rudder seam department when high-speed aircraft flies for a long time, has solved the problem of aircraft wing thermal-insulated design of preventing.
The embodiment adopts the integrated design from air entraining to jet flow, reduces the redundancy of a carried air source, and realizes the design of a flow mechanism under the condition of stronger geometric constraint of the wing profile of the high-speed aircraft. The secondary distribution of airflow flow in the wing profile is realized by using the auxiliary jet flow control system, and the tail edge jet flow direction control is realized according to the control requirement of the aircraft, so that the attitude of the aircraft is adjusted. The application flow field range of the blowing and air suction technology is expanded, and a new thought is provided for the design of a high-speed aircraft.
By adopting the technical scheme provided by the specific embodiment, the front edge forms the effect of inhaling to reduce heat flow accumulation, and the rear edge forms the effect similar to virtual control surface control. Compared with the prior art, the method can realize the effects of heat reduction of the front edge of the wing profile of the aircraft, reduction of heat load and pressure load accumulation of a rudder joint, high lift of the wing profile and a virtual control surface, successfully applies the jet flow control mechanism technology to the wing of the high-speed aircraft, solves the problems existing in the prior art, and has outstanding substantive characteristics and remarkable progress.
Claims (7)
1. A jet flow control mechanism for controlling the airflow direction of a wing trailing edge flow field of an aircraft comprises a leading edge bleed air (1), a shell (2), a flow deflector (3), a flow control sheet (4), a Coanda trailing edge (7), a jet flow direction control sheet (8), a jet flow adjusting system (11) and a transmission system component (12), and is characterized by further comprising an auxiliary jet flow control system (13) and an auxiliary jet flow control valve (14);
the jet flow control mechanism is arranged along the chord line direction of an aircraft wing profile, an opening of the leading edge bleed air (1) is arranged in the middle of the leading edge of the aircraft wing profile, the leading edge bleed air (1) and the shell (2) are coaxially arranged, one side of the shell (2) intersected with the leading edge bleed air (1) is in smooth transition, and one side far away from the leading edge bleed air (1) is provided with an air outlet;
the jet flow adjusting system (11) is arranged on one side, close to the shell (2), of the leading edge bleed air (1), the flow deflector (3) comprises an upper piece and a lower piece, one side of the flow deflector is arranged at the corner of the cross section of the shell (2), one side far away from the leading edge bleed air (1) is intersected, and the intersection line is positioned inside the shell (2); the flow control sheet (4) comprises an upper sheet and a lower sheet which are respectively arranged in an upper airfoil surface cavity and a lower airfoil surface cavity formed between the flow deflector (3) and the shell (2); the two sets of transmission system components (12) are provided, fixed ends are arranged on one side, facing the flow deflector (3), of the shell (2), and movable ends are connected with the flow control sheet (4); the section of the jet flow direction control sheet (8) is streamline, the blunt end is arranged towards one side of the leading edge bleed air (1) and is connected with the flow deflector (3), and the end far away from the leading edge bleed air (1) is provided with a gas outlet;
the auxiliary jet flow control system (13), the auxiliary jet flow control valve (14) and the Coanda trailing edge (7) are symmetrically arranged in an internal cavity of the jet flow direction control sheet (8), the auxiliary jet flow control system (13) is connected with a self-contained reserve gas cylinder or divides the leading edge bleed gas (1) to form a stable auxiliary jet flow gas with controllable flow, and the stable auxiliary jet flow gas is ejected along the Coanda trailing edge (7) under the control of the auxiliary jet flow control valve (14);
a jet flow outlet is formed between the jet flow direction control sheet (8) and the shell (2); an auxiliary jet outlet is formed between the jet direction control sheet (8) and the Coanda trailing edge (7); the Coanda trailing edge (7) is semicircular, and the diameter is determined according to the sizes of the wing profile, the jet outlet and the auxiliary jet outlet of the aircraft.
2. The jet control mechanism according to claim 1, characterized in that the jet regulation system (11) is arranged in the leading edge bleed air (1) at a distance of 5-8 mm from the intersection, on the side close to the housing (2).
3. The jet control mechanism of claim 1, wherein the Coanda trailing edge (7) is of an internally hollow configuration.
4. The jet control mechanism of claim 1, wherein the drive train assembly (12) comprises a drive assembly and a lead screw assembly.
5. The jet control mechanism according to claim 1, characterized in that the jet regulation system (11) comprises a pressure increase valve, a speed regulation valve and a throttle valve.
6. The jet control mechanism according to any one of claims 1 to 5, wherein the leading edge bleed air (1) is isosceles trapezoidal in cross-section.
7. The fluidic control mechanism of any of claims 1 to 5, wherein the cross-sectional shape of the housing (2) is diamond, trapezoid or polygon.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210989803.9A CN115520373A (en) | 2022-08-18 | 2022-08-18 | Jet flow control mechanism for controlling airflow direction of flow field at trailing edge of aircraft wing |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210989803.9A CN115520373A (en) | 2022-08-18 | 2022-08-18 | Jet flow control mechanism for controlling airflow direction of flow field at trailing edge of aircraft wing |
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| CN115520373A true CN115520373A (en) | 2022-12-27 |
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| CN202210989803.9A Pending CN115520373A (en) | 2022-08-18 | 2022-08-18 | Jet flow control mechanism for controlling airflow direction of flow field at trailing edge of aircraft wing |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115892470A (en) * | 2023-01-09 | 2023-04-04 | 中国空气动力研究与发展中心高速空气动力研究所 | Built-in equipment separation safety protection system |
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2022
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115892470A (en) * | 2023-01-09 | 2023-04-04 | 中国空气动力研究与发展中心高速空气动力研究所 | Built-in equipment separation safety protection system |
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