CN117622464A - A technology for distributed variable diversion and drag reduction and vector jet flow field control at the wing leading edge stagnation point and high-pressure area - Google Patents

Abstract

The invention discloses a technology for distributed variable diversion and drag reduction and vector jet flow field control of wing leading edge stagnation points and high-pressure areas, and belongs to the technical field of aviation equipment. The wing includes spar, skin, edge strips, honeycomb air inlet, pressure switch, air duct, vector exhaust plate, linear servo, mounting base, etc. Structure 1 is the honeycomb air inlet, structure 2 is the pressure switch, structure 3 is the air intake duct, structure 4-10 is the spar skin and other structural parts, structure 11 is the linear steering gear assembly, and structure 12 is the vector exhaust plate. Structure 13 is the steering gear mounting base. During flight, when the pressure at the stagnation point of the wing's leading edge and the high-pressure zone exceeds the set value, the pressure switch controls the opening of the honeycomb air inlet, introducing the high-pressure airflow through the bleed air duct and discharging it at the upper part of the trailing edge of the wing. The gas exhaust port is controlled by a linear servo to open and close the vector exhaust plate. When the vector exhaust plate is closed downward, the gas introduced from the leading edge can be discharged at the rear of the air duct, which can accelerate the flow field on the upper surface of the wing and increase the lift of the wing. When the vector exhaust plate is opened upward at a certain angle, it can disturb the airflow on the upper wing surface, increase the wing resistance, and serve as a speed brake.

Description

A kind of distributed variable diversion and drag reduction and vector jet at the wing leading edge stagnation point and high pressure area Flow field control technology

Technical field

The invention relates to a technology for distributed variable diversion and drag reduction and vector jet flow field control of wing leading edge stagnation points and high-pressure areas, and belongs to the field of aviation.

Background technique

Distributed variable induction drag reduction and vector jet flow field control technology at the wing's leading edge stagnation point and high-pressure area is a technology that arranges honeycomb air inlets at the wing's leading edge stagnation point and high-pressure area. The airfoil opening exhaust technology on the trailing edge. The pressure of the airflow on the leading edge of the wing during flight is transmitted to the pressure switch component at the rear of the honeycomb air inlet. After measurement by the pressure switch, the opening of the honeycomb air inlet is determined, thereby controlling the amount of air intake. A vector exhaust plate is installed on the upper wing surface on the trailing edge of the wing. The linear steering gear telescopically controls the opening and closing of the vector exhaust plate as required. When contracted and closed, the air introduced at the leading edge can be discharged at high speed through the bleed duct, thus accelerating the wing. The speed of the airflow above achieves the effect of increasing the lift of the wing. Opening the vector exhaust plate upward can disrupt the direction of the airflow above the wing, thereby achieving the effect of reducing lift and increasing drag. It can be used as a brake in the air or as a speed brake during ground taxiing. Taken together, this technology can increase wing lift and improve fuel economy.

Contents of the invention

In order to solve the problem of current fixed-wing aircraft wings having a large leading edge stagnation point pressure and forming a large drag during high-speed flight, the present invention provides a distributed variable diversion drag reduction and vector control system for the wing leading edge stagnation point and high-pressure zone. Jet flow field control technology is designed to reduce drag during high-speed flight, especially at supersonic and hypersonic speeds.

The present invention adopts the following technical solutions to solve the above technical problems:

The invention provides a honeycomb air inlet with distributed controllable opening. A pressure switch with integrated heating and anti-icing function is used to control the opening of the air inlet and linearly control the air intake volume. The airflow entering the leading edge is compressed into high-pressure airflow through the air intake duct and discharged on the upper surface of the trailing edge of the wing. The angle of the vector exhaust plate can be adjusted to increase lift or drag.

The number of honeycomb air inlets can be determined according to the actual size of the wing. In this example, two rows on the upper wing surface, one row on the leading edge, and three rows on the lower wing surface are used.

The pressure switch is used in combination with the honeycomb air inlet. The pressure switch is equipped with the same number of pressure sensors as the honeycomb air inlet and is used to measure and open and close the honeycomb air inlet.

The ratio of the inlet area to the outlet area of the air induction duct is 9, and the introduced low-speed airflow can be compressed to form a high-speed airflow for discharge.

Description of drawings

Figure 1 is a schematic diagram of the appearance of the present invention.

Figure 2 is a schematic diagram of the honeycomb air inlet assembly.

Figure 3 is a schematic diagram of the combination of the pressure sensor and honeycomb valve.

Figure 4 is a schematic diagram of the air duct inside the wing.

Figure 5 is a schematic diagram of the air duct and pressure switch.

Figure 6 is a schematic diagram of the vector exhaust plate on the wing.

Figure 7 is a schematic diagram of the deflection work of the vector exhaust plate.

Figure 8 is a schematic diagram of the exhaust state of the vector exhaust plate in the air duct.

Figure 9 is a schematic diagram of a vector exhaust plate used as an air speed brake or a ground spoiler.

Figure 10 is a summary drawing of the description of the present invention.

Detailed ways

The technical solution of the present invention will be further described in detail below in conjunction with the accompanying drawings:

The present invention is a distributed variable airflow drag reduction and vector jet flow field control technology for the wing leading edge stagnation point and high-pressure area. Its neutral state appearance is schematically shown in Figure 1. The enlargement of the honeycomb air inlet at the leading edge stagnation point and the high-pressure area is shown in schematic diagram 2, in which the honeycomb valve (14) and the pressure sensor (15) are enlarged as shown in figure 3. The arrangement of the air duct (3) in the wing is shown in Figure 4; the installation of the air duct (3), the honeycomb air inlet (1) and the pressure switch (2) is as shown in the schematic diagram 5. The position of the vector exhaust plate (12) on the wing is shown in schematic diagram 6, and the deflection working range of the vector exhaust plate is shown in schematic diagram 7.

The working principle of the present invention is as follows:

During the air intake process, the honeycomb air inlet (1) receives the aerodynamic pressure from the leading edge stagnation point and the high-pressure area, and transmits it to the rear pressure switch (2). The pressure sensor (15) in the pressure switch measures the aerodynamic pressure. According to Pneumatic pressure automatically adjusts the opening of the honeycomb air inlet to keep the air intake within a reasonable range. The opening of the honeycomb air inlet is shown in Figure 2. The combination of the honeycomb valve (14) and the pressure sensor (15) is shown in Figure 3. The pressure sensor uses a spring to support the honeycomb valve to keep its valve opening and closing process linear.

During the exhaust process, the vector exhaust plate is retracted into the wing under the action of the linear servo, as shown in Figure 8. At this time, the gas can be discharged from the rear of the air duct to accelerate the airflow above the wing.

When in the air speed brake or ground spoiler state, the vector exhaust plate rotates around the rotation axis toward the trailing edge of the wing under the action of the linear steering gear, blocking part of the airflow above the wing, slowing down the airflow speed, and reducing lift and increasing drag, such as As shown in Figure 9.

Claims (3)

1. The present invention discloses a technology for distributed variable diversion and drag reduction and vector jet flow field control of the wing leading edge stagnation point and high-pressure zone, which is characterized by including a honeycomb air inlet (1) and a pressure switch (2) , air duct (3), rib (4), skin (5), edge strips (6, 7), carbon tube spars (8, 9), mounting plate (10), linear servo (11) , vector exhaust plate (12), steering gear mounting base (13); among them: The honeycomb air inlet (1), pressure switch (2), air intake duct (3), wing rib (4), and vector exhaust plate (12) are designed according to the size of the wing section to which they are applied. 2. According to the distributed variable diversion and drag reduction and vector jet flow field control technology at the leading edge stagnation point and high-pressure area of the wing according to claim 1, the honeycomb air inlet (1) is distributed at the leading edge stagnation point and the high-pressure area. The pneumatic load it bears is transmitted to the pressure switch (2). After the set pressure is exceeded, the pressure switch will open the honeycomb air inlet (1), and its opening is controlled according to the pressure. The airflow entering through the honeycomb air inlet (1) is transmitted to the upper part of the trailing edge of the wing through the air intake duct (3). The air intake duct (3) adopts a design with a large front and a small rear, which accelerates the airflow at the exhaust port. 3. According to claim 1, a vector exhaust plate (12) is provided on the upper part of the trailing edge of the wing, which can be controlled to move up and down by a linear servo (11) articulated with the mounting base (13). When the linear servo (11) retracts the actuating rod, the vector exhaust plate (12) can be pulled down to the preset position. At this time, the rear of the air intake duct (3) can be exhausted to accelerate the airflow above the wing, thereby increasing lift. ; Pushing the vector exhaust plate (12) upward can disturb part of the airflow on the upper part of the wing, increase resistance, and can be used as an air brake or a ground spoiler.