CN113148148A - Stability augmentation circulation control method of ground effect vehicle and stability augmentation type ground effect vehicle - Google Patents
Stability augmentation circulation control method of ground effect vehicle and stability augmentation type ground effect vehicle Download PDFInfo
- Publication number
- CN113148148A CN113148148A CN202110425215.8A CN202110425215A CN113148148A CN 113148148 A CN113148148 A CN 113148148A CN 202110425215 A CN202110425215 A CN 202110425215A CN 113148148 A CN113148148 A CN 113148148A
- Authority
- CN
- China
- Prior art keywords
- pressure
- blowing
- flap
- wing
- calculating
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C35/00—Flying-boats; Seaplanes
- B64C35/007—Specific control surfaces therefor
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a stability augmentation circulation control method of a ground effect vehicle and the stability augmentation type ground effect vehicle. The control method is applied to the stability-increasing type ground effect aircraft, and the stability-increasing type ground effect aircraft comprises a blowing flap and a first pressure sensor. The first pressure sensor is arranged at the leading edge of the lower wing surface of the main wing of the WIG craft, and the air blowing flap comprises a flap device and an air blowing device. The method comprises the following steps: acquiring the pressure applied to the front edge of the lower airfoil surface of the main wing of the WIG craft, and recording the pressure as a first pressure; calculating the change frequency and amplitude of the first pressure; according to Cμ 1＝C0+ Asin (2 π ft +0.4 π) calculates the first blowing capacity coefficient Cμ 1Wherein f is the variation frequency of the first pressure, A is the amplitude of the first pressure, C0Is the initial blowing momentum coefficient; calculating a first blowing speed according to the first blowing capacity coefficient; and controlling the air blowing device to blow air at a first air blowing speed, and keeping the wing flap surface in a retracted state. The invention can increase the cruising speed of the ground effect vehicle under the condition of wave sea surfaceStability of (2).
Description
Technical Field
The invention relates to the technical field of ground effect aircrafts, in particular to a stability augmentation circulation control method of a ground effect aircraft and a stability augmentation type ground effect aircraft.
Background
The WIG craft is generally a near-ground, surface or offshore craft, particularly a water takeoff and landing craft, which improves lift by the ground effect. When the ground effect vehicle is cruising on the sea surface, the height from the sea surface is lower, and the aerodynamic force of the wings of the aircraft is easily influenced by sea surface waves. The problems of bumping and unstable flying of the aircraft caused by longitudinal floating and sinking response, transverse tilting motion and splashing effect of the aircraft in the opposite action of waves are stressed on the safety of the aircraft in the cruising process. Meanwhile, the flow field around the wing of the WIG craft changes under the condition of a wave sea surface, and the wingtips of the wing are easy to flow and separate, so that the wingtips stall.
Disclosure of Invention
The invention aims to provide a stability augmentation circulation control method of a ground effect vehicle and the stability augmentation type ground effect vehicle, so as to increase the cruising stability of the ground effect vehicle under the wave sea surface condition.
In order to achieve the purpose, the invention provides the following scheme:
a stability augmentation loop amount control method of a WIG craft, the control method being applied to a WIG craft including an air-blowing flap, the air-blowing flap including a flap device and an air-blowing device, the flap device including an actuating cylinder and a flap airfoil, the method comprising:
acquiring the pressure applied to the front edge of the lower airfoil surface of the main wing of the WIG craft, and recording the pressure as a first pressure;
calculating the change frequency and amplitude of the first pressure;
according to Cμ 1＝C0+ Asin (2 π ft +0.4 π) calculates the first blowing capacity coefficient Cμ 1Wherein f is the variation frequency of the first pressure, A is the amplitude of the first pressure, C0Is the initial blowing momentum coefficient;
calculating a first blowing speed according to the first blowing capacity coefficient;
and controlling the air blowing device to blow air at the first air blowing speed, wherein the flap wing surface is kept in a retracted state.
Optionally, the calculating a first air blowing speed according to the first air blowing capacity coefficient specifically includes:
according to
Calculating a first blowing velocity v1Wherein v is∞H is the width of the nozzle of the blowing device for the free incoming flow velocity.
Optionally, the method further includes:
acquiring pressure applied to the upper wing surface of the main wing of the WIG craft close to the wing flap surface and recording the pressure as second pressure;
according to Cμ 2＝F(p-p∞) Calculating a second blowing momentum coefficient Cμ 2Wherein p is the second pressure, p∞Is far field atmospheric pressure, F is the coefficient;
calculating a second blowing speed according to the second blowing momentum coefficient;
and controlling the air blowing device to blow air to the flap wing surface at the second air blowing speed, wherein the flap wing surface is kept in an open state.
Optionally, the calculating a second blowing speed according to the second blowing momentum coefficient specifically includes:
according to
Calculating the blowing speed v of a blowing device2Wherein v is∞H is the width of the nozzle of the blowing device for the free incoming flow speed.
Optionally, the method further includes:
acquiring the internal pressure of the high-pressure gas cylinder of the WIG craft, and recording as a third pressure;
judging whether the third pressure is smaller than a preset pressure threshold value or not;
and when the judgment result shows that the third pressure is smaller than the preset pressure threshold value, controlling the high-pressure gas cylinder to introduce high-pressure gas from the engine or the gas compressor and storing the high-pressure gas.
Optionally, the first pressure is measured by a first sensor mounted on the leading edge of the lower airfoil surface of the main wing of the WIG craft.
Optionally, the second pressure is measured by a second sensor mounted on the upper wing surface of the WIG craft near the flap surface.
Optionally, the third pressure is measured by a third sensor installed inside the high-pressure gas cylinder of the WIG craft.
The invention also provides a stability augmentation type ground effect aircraft, which comprises: the device comprises a flap device, an air blowing device, a flight control system and a first pressure sensor;
the flap device is positioned at the rear edge of the main wing and comprises an actuating cylinder and a flap wing surface;
the blowing device is positioned in the main wing and comprises a gas pipeline, a high-pressure gas cylinder, an electromagnetic valve, a flow regulating device and a blowing port;
the first pressure sensor is arranged on the leading edge of the lower wing surface of the main wing of the WIG craft;
the flight control system includes: the measurement pressure acquisition module is used for acquiring the pressure on the front edge of the lower airfoil surface of the main wing of the WIG craft measured by the first pressure sensor, and recording the pressure as a first pressure; the pressure information calculation module is used for calculating the change frequency and the change amplitude of the first pressure; a first blowing air volume coefficient calculating module for calculating the first blowing air volume coefficient according to Cμ 1＝C0+ Asin (2 π ft +0.4 π) calculates the first blowing capacity coefficient Cμ 1Wherein f is the variation frequency of the first pressure, A is the amplitude of the first pressure, C0Is the initial blowing momentum coefficient; the blowing speed calculation module is used for calculating a first blowing speed according to the first blowing capacity coefficient; and the control module is used for controlling the air blowing device to blow air at the first air blowing speed, and at the moment, the flap wing surface is kept in a retracted state.
Optionally, the flight control system further includes: the second pressure sensor and the second blowing momentum coefficient calculation module;
the second pressure sensor is arranged on the upper wing surface of the main wing of the WIG craft close to the wing surface of the flap;
the second blowing momentum coefficient calculation moduleFor according to Cμ 2＝F(p-p∞) Calculating a second blowing capacity coefficient Cμ 2Wherein p is the second pressure, p∞Is far field atmospheric pressure, F is the coefficient;
the measurement pressure acquisition module is further used for acquiring pressure, measured by the second pressure sensor, on the upper wing surface of the main wing of the WIG craft close to the wing flap surface, and recording the pressure as second pressure;
the blowing speed calculating module is also used for calculating a second blowing speed according to the second blowing momentum coefficient;
the control module is further used for controlling the air blowing device to blow air to the flap surface at the second air blowing speed, and at the moment, the flap surface is kept in an open state.
According to the specific embodiment provided by the invention, the invention discloses the following technical effects: according to the stability augmentation circulation control method of the ground effect vehicle and the stability augmentation type ground effect vehicle, the relative stability of the surface lift force of the wing is ensured by controlling the blowing device to blow air, and the instability problem and the insufficient lift force problem in the relative action of the vehicle and waves are solved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a first flowchart of a method for controlling a stability augmentation loop amount of a WIG craft according to embodiment 1 of the present invention;
FIG. 2 is a schematic view showing the cruise condition of the wing in embodiment 1 of the present invention;
FIG. 3 is a lift coefficient curve before controlling the cyclic quantity and a lift coefficient curve after controlling the cyclic quantity under the condition of a wave wall surface;
FIG. 4 is a second flowchart of a stability augmentation loop amount control method of a WIG craft according to embodiment 2 of the present invention;
FIG. 5 is a schematic view showing a take-off and landing state of an airfoil according to embodiment 2 of the present invention;
FIG. 6(a) is a wing flow chart of the invention in example 2 without applying the circulation control, and FIG. 6(b) is a wing flow chart of the invention in example 2 after applying the circulation control;
fig. 7(a) is a graph of a lift force curve of an airfoil profile (x-axis is a blowing momentum coefficient and y-axis is a lift force coefficient) under the application of different blowing momentum coefficients in embodiment 2 of the present invention, and fig. 7(b) is a graph of a drag coefficient of an airfoil profile (x-axis is a blowing momentum coefficient and y-axis is a drag coefficient) under the application of different blowing momentum coefficients in embodiment 2 of the present invention;
fig. 8(a) is a lift curve diagram of different wing flap deflection angles of a wing under cyclic control in embodiment 2 of the present invention (x-axis is a flap deflection angle, y-axis is a lift coefficient), and fig. 8(b) is a drag coefficient curve diagram of different wing flap deflection angles of a wing under cyclic control in embodiment 2 of the present invention (x-axis is a flap deflection angle, y-axis is a drag coefficient);
fig. 9 is a third flow chart of the stability augmentation loop quantity control method for the WIG craft according to embodiment 3 of the present invention.
1. A high pressure gas cylinder; 2. a bleed air line; 3. an actuator cylinder; 4. a flap surface; 5. a flow regulating device; 6. a blowing nozzle; 7. an electromagnetic valve; 8. a first pressure sensor; 9. a third pressure sensor; 10. a second pressure sensor.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
Example 1
The embodiment provides a stability augmentation circulation control method of a WIG craft, which is applied to a WIG craft with an air blowing flap, wherein the air blowing flap comprises a flap device and an air blowing device, and the flap device comprises an actuating cylinder 3 and a flap wing surface 4.
Controlling the circulation quantity: a jet hole is formed on the flap airfoil surface close to the trailing edge, high-pressure airflow is formed in an internal cavity of the airfoil, jet flow is generated through the jet hole along the object plane in a tangential direction, and the jet flow and outflow flow are mixed to form a coanda effect along the curved circular trailing edge surface.
Referring to fig. 1, the method for controlling the augmentation stability loop quantity of the WIG craft provided by the embodiment includes the following steps:
step 101: acquiring the pressure applied to the front edge of the lower airfoil surface of the main wing of the WIG craft, and recording the pressure as a first pressure;
step 102: calculating the change frequency and amplitude of the first pressure;
step 103: according to Cμ 1＝C0+ Asin (2 π ft +0.4 π) calculates the first blowing capacity coefficient Cμ 1Wherein f is the variation frequency of the first pressure, A is the amplitude of the first pressure, C0Is the initial blowing momentum coefficient;
step 104: calculating a first blowing speed according to the first blowing capacity coefficient;
step 105: and controlling the air blowing device to blow air at a first air blowing speed, wherein the flap wing surface is kept in a retracted state.
As an implementation manner of this embodiment, step 104 specifically includes:
according to
Calculating a first blowing velocity v1Wherein v is∞H is the width of the nozzle of the blowing device for the free incoming flow velocity.
As an embodiment of the embodiment, a first sensor is installed at the front edge of the lower wing surface of the main wing of the WIG craft, and the first pressure is measured by the first pressure sensor 8.
The method for controlling the stability augmentation circulation quantity of the WIG craft provided by the embodiment is applied to the sea surface cruising state of the WIG craft, and the frequency and the air blowing quantity of the air blowing device are controlled by monitoring the pressure fluctuation of the lower wing surface under the condition of a wave sea surface, so that the stability of the WIG craft under the complex sea condition is enhanced. And the blowing stability augmentation instruction detects the state of the flap through a flight control system to ensure that the flap surface 4 is kept in a retracted state. The pressure on the lower surface of the wing is oscillated by the relative action of sea surface waves and the aircraft, so that the lift force of the WIG craft is correspondingly oscillated. The first pressure sensor 8 at the leading edge of the main wing is positioned at the front position of the lower wing surface, transmits the oscillating pressure information (frequency f, amplitude A) to a flight control system and combines the airspeed head speed information (speed v)∞) Judging the wavelength and wave height of sea surface waves by a flight control system, and calculating to obtain a blowing momentum coefficient change curve C of periodic circulation controlμ 1＝C0+ Asin (2 π ft +0.4 π). The flow regulating device 5 controls the air blowing port to blow air periodically to counteract aerodynamic oscillation in the opposite action of waves, so that the stability of the WIG craft is improved. During cruising, the flap airfoil 4 and the blowing conditions are as shown in fig. 2.
Fig. 3 shows the aerodynamic changes of the WIG craft wing during the wave cruise in two wave periods. Wherein the wing chord length is 1m, the wavelength is 5m, the wave height is 0.5m, and the cruising speed is 100 m/s. It can be seen that the amplitude of the wing lift is about 7%. After the cyclic control is applied, the lift coefficient of the wing is obviously increased, the change tends to be smooth, and the amplitude of the lift is about 3.3%.
Example 2
Referring to fig. 4, the method for controlling the augmentation stability loop amount of the WIG craft provided by this embodiment further includes the following steps based on embodiment 1:
step 401: acquiring pressure applied to the upper wing surface of the main wing of the WIG craft close to the flap wing surface 4, and recording the pressure as second pressure;
step 402: according to Cμ 2＝F(p-p∞) Calculating a second blowing momentum coefficient Cμ 2Wherein p is a second pressure, p∞The pressure is far-field atmospheric pressure, and F is a coefficient and can be obtained through a simulation experiment;
step 403: calculating a second blowing speed according to the second blowing momentum coefficient;
step 404: and controlling an air blowing device to blow air to the flap wing surface at a second air blowing speed.
As an implementation manner of this embodiment, step 403 specifically includes:
according to
Calculating the blowing speed v of a blowing device2Wherein v is∞H is the width of the nozzle of the blowing device for the free incoming flow speed.
As an embodiment of the present embodiment, a second pressure is installed on the upper wing surface of the WIG craft main wing near the flap surface 4, and the second pressure is measured by the second sensor.
The embodiment is applied to the ground effect aircraft in the take-off and landing state, the flap deflects downwards, the wall attachment effect is generated through blowing, the flow separation area on the surface of the flap is reduced, and the annular volume of the wing and the lift force of the ground effect aircraft are increased. In a take-off and landing state, the take-off, landing and lift-increasing instruction controls the actuating cylinder through the flight control system to enable the flap airfoil surface 4 to deflect downwards by a corresponding angle, and the flap airfoil surface 4 flows and is separated due to flap deflection downwards, so that the lift force is reduced. The second flap pressure sensor 10 detects the increase of the upper airfoil surface pressure and outputs the pressure information to the flight control system, and judges the degree of flap surface separation flow and the second blowing momentum coefficient C of the circulation controlμ 2＝F(p-p∞) The flow regulating device 5 controls the blowing flow of the high-pressure gas bottle 11, and the gas is blown to the flap wing surface 4 through the blowing nozzle 6, so that the flow separation of the flap wing surface 4 is controlled, the annular volume is increased, and the lift force is increased. In the taking-off and landing process, the wing attitude and the blowing state are shown in fig. 5.
In the embodiment, NASALANGLEY LS (1) -0417MOD airfoil profiles are numerically simulated by a computational fluid dynamics method, the chord length is 1m, the flap is 0.3m, the flying height is 0.3m, the simulated incoming flow is 40m/s, the main wing has an attack angle of 10 degrees, and the flap drift angle is 40 degrees. As can be seen from comparison of flow lines of flow fields around the wings under two working conditions of no cyclic control and 0.037 aerodynamic coefficient, the degree of flow separation of the flap surface is obviously reduced after cyclic control is applied, and the flow separation of the flap surface in a take-off and landing state can be effectively controlled. FIG. 7 is a lift-drag coefficient curve of an airfoil under the same working condition and different blowing momentum coefficients. Under the condition of applying a certain blowing aerodynamic coefficient, the wing profile lift coefficient is obviously increased, and the resistance is obviously reduced. FIG. 8 is a curve of lift and drag coefficients of the wing at different flap angles under the circular control with the blowing momentum coefficient of 0.054. It can be seen that when the flap deflection angle is greater than 40 °, the effect of cyclic control is significantly reduced, the lift coefficient of the wing sharply decreases, and the drag coefficient significantly increases.
Example 3
Referring to fig. 9, the method for controlling the augmentation stability loop amount of the WIG craft provided by this embodiment further includes the following steps based on embodiment 1 or embodiment 2:
step 901: acquiring the internal pressure of a high-pressure gas cylinder 1 of the WIG craft, and recording as a third pressure;
step 902: judging whether the third pressure is smaller than a preset pressure threshold value or not;
step 903: and when the judgment result shows that the third pressure is smaller than the preset pressure threshold value, controlling the high-pressure gas bottle 1 to introduce high-pressure gas from the engine or the gas compressor and storing the high-pressure gas.
As an embodiment of the embodiment, a third pressure sensor 9 is installed inside the high-pressure gas cylinder 1 of the WIG craft, and the third pressure is measured by the third pressure sensor.
When the gas cylinder pressure detected by the third pressure sensor 9 is smaller than a certain value, for example, smaller than 40MPa, the flight control system controls the electromagnetic valve 7 to open, and the high-pressure gas cylinder 1 introduces high-pressure gas from the engine or the gas compressor at a certain flow rate through the gas introduction pipeline 2 and stores the high-pressure gas.
Example 4
The embodiment provides a stability augmentation type WIG craft, which corresponds to embodiments 1, 2 and 3, and the methods provided by embodiments 1, 2 and 3 can be applied to the WIG craft provided by the embodiment, and the WIG craft comprises: flap arrangements, airspeed head tubes, air-blowing devices, flight control systems, first pressure sensors, and, of course, other structural components necessary for the WIG craft.
The flap device is positioned at the rear edge of the main wing and comprises an actuating cylinder and a flap wing surface; the blowing device is positioned in the main wing and comprises a gas pipeline, a high-pressure gas cylinder, an electromagnetic valve, a flow regulating device and a blowing port; the first pressure sensor is arranged on the front edge of the lower wing surface of the main wing of the WIG craft; the flight control system includes: the measurement pressure acquisition module is used for acquiring the pressure on the front edge of the lower wing surface of the main wing of the WIG craft measured by the first pressure sensor and recording the pressure as the first pressure; the pressure information calculation module is used for calculating the change frequency and amplitude of the first pressure; a first blowing air volume coefficient calculating module for calculating the first blowing air volume coefficient according to Cμ 1＝C0+ Asin (2 π ft +0.4 π) calculates the first blowing capacity coefficient Cμ 1Wherein f is the variation frequency of the first pressure, A is the amplitude of the first pressure, C0Is the initial blowing momentum coefficient; the blowing speed calculating module is used for calculating a first blowing speed according to the first blowing momentum coefficient; and the control module is used for controlling the air blowing device to blow air at a first air blowing speed, and the flap wing surface is kept in a retracted state.
When the sea surface cruises, the flap is retracted, the air blowing device is controlled by the flight control system to blow air periodically, the relative stability of the lift force of the wing surface is ensured, and the problem of instability in the relative action of the aircraft and waves is solved.
As an implementation manner of this embodiment, this embodiment provides a flight control system further including: the second pressure sensor and the second blowing momentum coefficient calculation module; a second pressure sensor arranged on the upper wing surface of the main wing of the WIG craft near the wing surface of the flap(ii) a A second blowing momentum coefficient calculation module for calculating the second blowing momentum coefficient according to Cμ 2＝F(p-p∞) Calculating a second blowing momentum coefficient Cμ 2Wherein p is a second pressure, p∞Is far field atmospheric pressure, and F is a coefficient; the measurement pressure acquisition module is also used for acquiring pressure on the upper wing surface of the main wing of the WIG craft close to the wing flap surface, which is measured by the second pressure sensor, and recording the pressure as second pressure; the blowing speed calculation module is also used for calculating a second blowing speed according to the second blowing momentum coefficient; and the control module is also used for controlling the air blowing device to blow air to the flap wing surface at a second air blowing speed, and at the moment, the flap wing surface is kept in an open state.
The invention controls the flow separation of the surface of the flap by blowing air from the deflecting flap and the blowing device in the lifting process, and increases the loop quantity of the flap, thereby improving the maximum lift coefficient in the lifting process.
As an implementation manner of this embodiment, this embodiment provides a flight control system further including: a third pressure sensor and a pressure judgment module. The device comprises a ground effect aircraft high-pressure gas cylinder, a measured pressure acquisition module, a pressure judgment module and a control module, wherein the third pressure sensor is installed inside the ground effect aircraft high-pressure gas cylinder, the measured pressure acquisition module is further used for acquiring the pressure inside the ground effect aircraft high-pressure gas cylinder, namely third pressure, measured by the third pressure sensor, the pressure judgment module is used for judging whether the third pressure is smaller than a preset pressure threshold value, and the control module is further used for controlling the high-pressure gas cylinder to introduce high-pressure gas from an engine or a gas compressor and store the high-pressure gas when the judgment result shows that the third pressure is smaller than the preset pressure threshold value.
Specifically, the flight control system receives information of pressure, speed and pilot instructions, and obtains control instructions of the blowing device and the flap device through calculation of a control algorithm. The flap device is located at the trailing edge of the wing and includes but is not limited to simple flaps, split flaps, slotted flaps and fuller flaps, and the actuator cylinder can control the folding and unfolding of the flaps. The flap surface can deflect downwards by about 40 degrees in the taking-off and landing processes of the WIG craft to increase lift force, and the wing spoiler can be matched with the trailing edge flap to deflect downwards; and when in a cruising state, the flap is retracted, so that the resistance of the ground effect aircraft is reduced. The air-entraining pipeline is connected with a high-pressure gas cylinder or an air-entraining device, and an air source can entrain air by an engine or can be from an air compressor and is controlled to open and close by an electromagnetic valve. And the high-pressure gas cylinder stores the gas of the bleed gas pipeline, and receives an instruction from the flight control system through the flow regulating device to control the gas blowing port to blow gas. The blowing device is arranged at the position close to the back in the wing, the blowing nozzle is positioned in front of the flap, and the blowing direction of the blowing nozzle can be adjusted according to the deflection angle of the flap.
The invention has simple structure, is suitable for taking off, landing and cruising states of the WIG craft under different complex sea conditions, and can greatly increase the lift force, stability and safety of the WIG craft. The invention controls the flow separation of the surface of the flap by blowing air from the deflecting flap and the blowing device in the lifting process, and increases the loop quantity of the flap, thereby improving the maximum lift coefficient in the lifting process. When the aircraft is in a cruising state, the flap is retracted, the air blowing device is controlled by the flight control system to blow air periodically, the surface lift force of the wing is ensured to be relatively stable, and the problem of instability in the relative action of the aircraft and waves is solved.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. For the system disclosed by the embodiment, the description is relatively simple because the system corresponds to the method disclosed by the embodiment, and the relevant points can be referred to the method part for description.
The principles and embodiments of the present invention have been described herein using specific examples, which are provided only to help understand the method and the core concept of the present invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In summary, this summary should not be construed to limit the present invention.
Claims (10)
1. A method for controlling a stability augmentation loop amount of a WIG craft, the method being applied to a WIG craft including an air-blowing flap, the air-blowing flap including a flap device and an air-blowing device, the flap device including an actuator and a flap airfoil, the method comprising:
acquiring the pressure applied to the front edge of the lower airfoil surface of the main wing of the WIG craft, and recording the pressure as a first pressure;
calculating the change frequency and amplitude of the first pressure;
according to Cμ 1＝C0+ Asin (2 π ft +0.4 π) calculates the first blowing capacity coefficient Cμ 1Wherein f is the variation frequency of the first pressure, A is the amplitude of the first pressure, C0Is the initial blowing momentum coefficient;
calculating a first blowing speed according to the first blowing capacity coefficient;
and controlling the air blowing device to blow air at the first air blowing speed, and keeping the flap wing surface in a retracted state at the moment.
2. The method for controlling the augmentation stability loop quantity of the WIG craft according to claim 1, wherein the calculating the first blowing speed according to the first blowing capacity coefficient specifically comprises:
according to
Calculating a first blowing velocity v1Wherein v is∞H is the width of the nozzle of the blowing device for the free incoming flow speed.
3. The augmentation loop amount control method of a WIG craft according to claim 1, wherein the method further comprises:
acquiring pressure applied to the upper wing surface of the main wing of the WIG craft close to the wing flap surface and recording the pressure as second pressure;
according to Cμ 2＝F(p-p∞) Calculating a second blowing momentum coefficient Cμ 2Wherein p is the second pressure, p∞Is far field atmospheric pressure, F is the coefficient;
calculating a second blowing speed according to the second blowing momentum coefficient;
and controlling the air blowing device to blow air to the flap wing surface at the second air blowing speed, wherein the flap wing surface is kept in an open state.
4. The method for controlling the augmentation stability loop quantity of the WIG craft according to claim 3, wherein the calculating of the second blowing speed according to the second blowing momentum coefficient specifically comprises:
according to
Calculating the blowing speed v of a blowing device2Wherein v is∞H is the width of the nozzle of the blowing device for the free incoming flow speed.
5. The augmentation loop amount control method of a WIG craft according to claim 1, wherein the method further comprises:
acquiring the internal pressure of the high-pressure gas cylinder of the WIG craft, and recording as a third pressure;
judging whether the third pressure is smaller than a preset pressure threshold value or not;
and when the judgment result shows that the third pressure is smaller than the preset pressure threshold value, controlling the high-pressure gas cylinder to introduce high-pressure gas from the engine or the gas compressor and storing the high-pressure gas.
6. The augmentation loop quantity control method of the WIG craft of claim 1, wherein said first pressure is measured by a first sensor installed at a leading edge of a lower wing surface of a main wing of said WIG craft.
7. The augmentation loop quantity control method of the WIG craft of claim 1, wherein the second pressure is measured by a second sensor installed on the upper wing surface of the main wing of the WIG craft near the flap surface.
8. The augmentation loop quantity control method of the WIG craft of claim 1, wherein said third pressure is measured by a third sensor installed inside a high pressure gas cylinder of the WIG craft.
9. A stability augmentation type WIG craft, comprising: the system comprises a flap device, an air blowing device, a flight control system and a first pressure sensor;
the flap device is positioned at the rear edge of the main wing and comprises an actuating cylinder and a flap wing surface;
the blowing device is positioned in the main wing and comprises a gas pipeline, a high-pressure gas cylinder, an electromagnetic valve, a flow regulating device and a blowing port;
the first pressure sensor is arranged on the leading edge of the lower wing surface of the main wing of the WIG craft;
the flight control system includes: the measurement pressure acquisition module is used for acquiring the pressure on the front edge of the lower airfoil surface of the main wing of the WIG craft measured by the first pressure sensor, and recording the pressure as a first pressure; the pressure information calculation module is used for calculating the change frequency and the change amplitude of the first pressure; a first blowing air volume coefficient calculating module for calculating the first blowing air volume coefficient according to Cμ 1＝C0+ Asin (2 π ft +0.4 π) calculates the first blowing capacity coefficient Cμ 1Wherein f is the variation frequency of the first pressure, A is the amplitude of the first pressure, C0Is the initial blowing momentum coefficient; the blowing speed calculation module is used for calculating a first blowing speed according to the first blowing capacity coefficient; and the control module is used for controlling the air blowing device to blow air at the first air blowing speed, and at the moment, the flap wing surface is kept in a retracted state.
10. The stability-augmenting WIG craft of claim 1, wherein said flight control system further comprises: the second pressure sensor and the second blowing momentum coefficient calculation module;
the second pressure sensor is arranged on the upper wing surface of the main wing of the WIG craft close to the wing flap surface;
the second blowing momentum coefficient calculation module is used for calculating the second blowing momentum coefficient according to Cμ 2＝F(p-p∞) Calculating a second blowing momentum coefficient Cμ 2Wherein p is the second pressure, p∞Is far field atmospheric pressure, F is the coefficient;
the measurement pressure acquisition module is further used for acquiring pressure, measured by the second pressure sensor, on the upper wing surface of the main wing of the WIG craft close to the wing flap surface, and recording the pressure as second pressure;
the blowing speed calculating module is also used for calculating a second blowing speed according to the second blowing momentum coefficient;
the control module is further used for controlling the air blowing device to blow air to the flap surface at the second air blowing speed, and at the moment, the flap surface is kept in an open state.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110425215.8A CN113148148B (en) | 2021-04-20 | 2021-04-20 | Stability augmentation circulation control method of ground effect vehicle and stability augmentation type ground effect vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110425215.8A CN113148148B (en) | 2021-04-20 | 2021-04-20 | Stability augmentation circulation control method of ground effect vehicle and stability augmentation type ground effect vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113148148A true CN113148148A (en) | 2021-07-23 |
| CN113148148B CN113148148B (en) | 2022-03-29 |
Family
ID=76867554
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110425215.8A Active CN113148148B (en) | 2021-04-20 | 2021-04-20 | Stability augmentation circulation control method of ground effect vehicle and stability augmentation type ground effect vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113148148B (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1158312A (en) * | 1965-07-21 | 1969-07-16 | Hawker Siddeley Aviation Ltd | Improvements in or relating to Aircraft Controls. |
| US3974987A (en) * | 1975-05-07 | 1976-08-17 | Northrop Corporation | Cascade effect blown flap |
| CN1974323A (en) * | 2006-12-15 | 2007-06-06 | 中国科技开发院 | Ground effect flyer |
| CN101423116A (en) * | 2008-11-12 | 2009-05-06 | 北京航空航天大学 | High incidence dissymmetry eddy single-hole site micro-blowing disturbance active control method and device |
| US20100270434A1 (en) * | 2005-12-20 | 2010-10-28 | Adrianus Stefanus Jonker | Controlling the boundary layer of an airfoil |
| EP2955105A1 (en) * | 2014-06-10 | 2015-12-16 | Instytut Lotnictwa | Autonomous active flow control system |
| CN108860597A (en) * | 2018-06-22 | 2018-11-23 | 上海理工大学 | A kind of flapping wings type capacitation device using circulation control lift-rising |
-
2021
- 2021-04-20 CN CN202110425215.8A patent/CN113148148B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1158312A (en) * | 1965-07-21 | 1969-07-16 | Hawker Siddeley Aviation Ltd | Improvements in or relating to Aircraft Controls. |
| US3974987A (en) * | 1975-05-07 | 1976-08-17 | Northrop Corporation | Cascade effect blown flap |
| US20100270434A1 (en) * | 2005-12-20 | 2010-10-28 | Adrianus Stefanus Jonker | Controlling the boundary layer of an airfoil |
| CN1974323A (en) * | 2006-12-15 | 2007-06-06 | 中国科技开发院 | Ground effect flyer |
| CN101423116A (en) * | 2008-11-12 | 2009-05-06 | 北京航空航天大学 | High incidence dissymmetry eddy single-hole site micro-blowing disturbance active control method and device |
| EP2955105A1 (en) * | 2014-06-10 | 2015-12-16 | Instytut Lotnictwa | Autonomous active flow control system |
| CN108860597A (en) * | 2018-06-22 | 2018-11-23 | 上海理工大学 | A kind of flapping wings type capacitation device using circulation control lift-rising |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113148148B (en) | 2022-03-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US11440645B2 (en) | Adjustable lift modification wingtip | |
| US7748958B2 (en) | Vortex generators on rotor blades to delay an onset of large oscillatory pitching moments and increase maximum lift | |
| Stanewsky | Adaptive wing and flow control technology | |
| US6634594B1 (en) | Hypersonic waverider variable leading edge flaps | |
| US20060027711A1 (en) | Vernier active flow control effector | |
| US8152109B2 (en) | Method and system for controlling fluid flow in relation to a foil and harnessing energy therefrom | |
| US7357358B2 (en) | Aircraft leading edge device systems and corresponding sizing methods | |
| CN109911216B (en) | System and method for correcting the position of water impingement limits on an airfoil | |
| US20020014555A1 (en) | Method for altitude control and/or pitch angle control of airships, and an airship having a device for altitude control and/or pitch angle trimming | |
| US4643376A (en) | Shock inducing pod for causing flow separation | |
| US4176813A (en) | Shark nose for aircraft | |
| US5366180A (en) | High-lift device for aircraft | |
| CN104477376A (en) | Combined pneumatic control method for aerodynamic rudder/reaction control system of hypersonic flight vehicle | |
| McManus et al. | Airfoil performance enhancement using pulsed jet separation control | |
| US20230024601A1 (en) | Aircraft wing with trailing edge flight control surface | |
| US4705240A (en) | Passive vortex lift control | |
| CN111003160A (en) | Self-adaptive high-speed aircraft layout based on wing tip deformation | |
| CN113148148B (en) | Stability augmentation circulation control method of ground effect vehicle and stability augmentation type ground effect vehicle | |
| JPS595777B2 (en) | Air suction device for aircraft-mounted gas turbine engine | |
| Linehan et al. | Aerodynamics and lateral stability of low-aspect-ratio wings with dihedral at low Reynolds numbers | |
| Huffman et al. | Aerodynamic effects of distributed spanwise blowing on a fighter configuration | |
| Phelps III et al. | Summary of low-speed aerodynamic characteristics of upper-surface-blown jet-flap configurations | |
| Rozbytskyi et al. | The Influence of Leading Edge Vortex Generators on the Efficiency of Lateral Control Surfaces | |
| RU2785230C1 (en) | Aircraft and method for its manufacture | |
| CN112810800A (en) | Laminar flow separation control method based on local vibration of wing surface |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |