Air entraining structure

Abstract

The invention provides an air entraining structure which comprises a surface sensor assembly and an air entraining transmission channel, the surface sensor assembly comprises an air entraining cover, a base and a pagoda head air tap, a plurality of through pressure measuring holes are formed in the air entraining cover, through holes in butt joint with the pressure measuring holes are formed in the base, the rear ends of the through holes are communicated, and after the air entraining cover and the base are fixedly connected, the air entraining transmission channel is formed in the air entraining cover. The pagoda head air nozzle is fixedly connected with the rear end of the base, and the inner cavity is communicated with the air entraining inner cavity; one end of the air entraining transmission channel is connected with the pagoda head of the pagoda head air tap, and the other end of the air entraining transmission channel is connected with an external pressure tapping port of the atmosphere measurement system. The air entraining path and the layout of the sensor are optimized, and efficient pressure transmission from the surface of the aircraft to internal atmosphere measurement system equipment is achieved.

Description

TECHNICAL FIELD

[0001] The application relates to an air induction structure and belongs to the technical field of aerospace. BACKGROUND

[0002] With the rapid development of low-altitude economy, the economic benefits of short-distance aircraft such as eVTOL (tilt rotor) are increasingly prominent. Such aircraft adopts a fixed-wing mode during cruising, and accurate true airspeed must be obtained to participate in the attitude control of the flight path in order to ensure flight quality. An embedded atmospheric measurement system senses surface pressure through pressure measuring holes distributed on the surface of the aircraft, and then solves key flight parameters. Traditional air induction schemes use metal or special composite material pipes. Such air induction schemes have problems such as large system weight, blocked pressure measuring holes, complex system structure, and high cost.

[0003] Specifically, the direct opening air induction structure is prone to failure of the pressure measuring point due to particle intrusion or thermal deformation in a high-temperature and high-pressure environment; the metal air induction pipeline is relatively heavy, which increases the overall weight of the aircraft, and the complex curved shape of the metal pipeline needs to be precisely machined, which increases the manufacturing cost. SUMMARY

[0004] The purpose of the present application is to overcome the shortcomings of the prior art and provide an air induction structure with simple structure, high reliability and low cost to realize efficient sensing of the surface pressure of the aircraft.

[0005] The technical solution of the present application is an air induction structure, which comprises a surface sensor assembly and an air induction transmission channel. The surface sensor assembly comprises an air induction cover, a base and a pagoda head gas nozzle. The air induction cover is internally provided with a plurality of through pressure measuring holes. The base is internally provided with through holes that are connected to the pressure measuring holes. The through holes are connected at the rear end. After the air induction cover and the base are fixed, an air induction inner cavity is formed inside. The pagoda head gas nozzle is fixed to the rear end of the base, and the internal cavity is connected to the air induction inner cavity. The air induction transmission channel adopts a flexible hose, one end of which is connected to the pagoda head of the pagoda head gas nozzle, and the other end is connected to the external pressure tapping port of the atmospheric measurement system.

[0006] The beneficial effects of the present application compared with the prior art are as follows:

[0007] (1) The air induction path and sensor layout of the present application are optimized to realize efficient pressure transmission from the surface of the aircraft to the internal atmospheric measurement system equipment.

[0008] (2) The air induction structure of the present application combines the surface porous redundancy design with the internal silicone rubber hose air induction channel, has the characteristics of light weight, convenient installation and maintenance, good environmental adaptability, high reliability, etc., and significantly reduces the cost.

[0009] (3) The present invention adopts a combination of surface porous redundancy design and internal silicone rubber hose air duct, which significantly reduces system complexity and manufacturing cost, while improving the reliability of the air duct system. Attached Figure Description

[0010] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0011] Figure 1 This is a cross-sectional view showing the connection between the aircraft bulkhead and the surface sensor assembly of the present invention.

[0012] Figure 2 This is a schematic diagram of the silicone rubber hose of the present invention being laid along with the aircraft structure.

[0013] Among them, 1 is the bleed air cover; 2 is the base; 3 is the inner cavity; 4 is the flange; 5 is the pagoda-shaped air nozzle; 6 is the silicone rubber hose; 7 is the lightweight clamp; and 8 is the aircraft bulkhead. Detailed Implementation

[0014] This invention provides a low-cost air bleed structure. By installing a sensor assembly on the aircraft wall and bleeding air through an internal pipe at the end of the sensor, the pressure value on the aircraft surface is transmitted to an internal pressure sensor. Through a combination of a porous redundant design on the surface and a silicone rubber flexible air bleed channel, system complexity and manufacturing costs are significantly reduced, while the reliability of the air bleed system is improved. This contributes to the miniaturization and cost reduction of low-altitude short-range fixed-wing aircraft. This invention is particularly suitable for embedded atmospheric measurement systems in high subsonic / sonic aircraft, maintaining stable pressure transmission performance in the aircraft environment.

[0015] This invention discloses an air intake structure, comprising a surface sensor assembly and an air intake transmission channel. The surface sensor assembly includes an air intake cover, a base, and a pagoda-shaped nozzle. The air intake cover has multiple through-holes with inverted conical front ends and straight rear ends. The base has through holes that mate with the pressure holes, and the rear ends of the through holes are connected. After the air intake cover and the base are fixedly connected, the pressure holes and through holes form an air intake cavity. The pagoda-shaped nozzle is fixedly connected to the rear end of the base, and its internal cavity is connected to the air intake cavity. The air intake transmission channel is a flexible hose, with one end connected to the pagoda head of the pagoda-shaped nozzle and the other end connected to the external pressure tap of the atmospheric measurement system.

[0016] The surface sensor assembly of this invention is the front-end pressure sensing part of the air intake system, and is usually embedded in the surface of key areas such as the nose or leading edge of an aircraft.

[0017] Furthermore, the outer surface of the bleed air cover conforms to the local outer surface of the aircraft, ensuring that it does not significantly interfere with the original aerodynamic shape. The bleed air cover contains multiple through-hole pressure measuring holes, with the front end of each hole featuring an inverted conical design, smaller at the front and larger at the back. More preferably, the diameter of the straight section of the pressure measuring hole is no greater than 1.5 mm, and the preferred inverted cone angle is within the range of 90° to 110°, effectively preventing particulate matter blockage.

[0018] Furthermore, the air duct cavity formed by the air duct cover and the base acts as a pressure stagnation chamber, converting the dynamic pressure on the aircraft surface into static pressure and collecting airflow from multiple pressure measuring holes to achieve redundancy backup. Even if a single pressure measuring hole is blocked, the system can still obtain pressure through other pressure measuring holes.

[0019] Furthermore, the base and the air vent cover are welded together to form a cylindrical structure with a flange at the rear end. The material is usually a high-temperature resistant nickel-based alloy to ensure structural strength and reliability under high-temperature conditions.

[0020] Furthermore, one end of the pagoda-shaped nozzle has a multi-stage expansion-contraction structure that fits into the flexible hose, while the other end has an external thread structure that fits into the internal thread at the rear end of the base.

[0021] This invention utilizes a flexible silicone rubber hose as the bleed air transmission channel, which efficiently transmits the gas pressure collected within the surface sensor cavity to the aircraft interior. The silicone rubber hose is flexible, heat-resistant, and stable, with a continuous operating temperature range of -60℃ to 200℃. The silicone rubber hose is non-toxic, odorless, and exhibits excellent chemical stability.

[0022] Furthermore, the flexible hose needs to be secured to the inner wall of the aircraft cabin to prevent its vibration from interfering with other equipment inside. Stainless steel hose clamps are used to fasten the flexible hose to the pagoda-shaped structure to prevent leakage. The flexible hose is laid along the internal structure of the aircraft and secured with lightweight clamps to avoid interference with moving parts.

[0023] Compared to metal tubing, the silicone rubber hose of this invention significantly reduces manufacturing costs and is easier to install, reducing labor costs and the need for specialized tools. Its modular design further lowers maintenance costs. The silicone rubber hose is also significantly lighter than metal tubing, which is beneficial for aircraft weight reduction and improved overall performance.

[0024] The flexibility of the silicone rubber hose of this invention allows it to adapt to complex installation paths without the need for precise bending, greatly simplifying the installation process. Installation and maintenance are convenient; during maintenance, simply loosening the connecting clamp is sufficient to replace the hose. The silicone rubber hose can operate for extended periods between -60℃ and 200℃, and can withstand temperatures up to 310℃ for short periods, meeting the environmental requirements of aircraft interiors and demonstrating excellent environmental adaptability.

[0025] The multi-hole redundant design of this invention effectively prevents single-point failure of the pressure measurement point, and the flexibility of the silicone rubber tube can play a shock-absorbing role, reducing the risk of joint loosening, and the overall system reliability is high.

[0026] A preferred embodiment of the present invention will now be described with reference to the accompanying drawings.

[0027] like Figure 1 As shown, the diameter of the straight section of the bleed air cover 1 is slightly smaller than the diameter of the opening on the aircraft cabin wall, and the two are fixed together by bolts through the flange 4. The silicone rubber hose 6 is sleeved on the expansion-contraction structure of the pagoda-head air nozzle 5, and the inner diameter of the silicone rubber hose 6 is slightly smaller than the outer diameter of the expansion section of the pagoda-head air nozzle 5 to ensure the airtightness of the connection.

[0028] like Figure 2 As shown, the silicone rubber hose 6 is fixed along the shape of the aircraft's inner cabin wall 8 using lightweight clamps 7, following the actual installation direction.

[0029] During flight, the airflow on the surface of the aircraft enters the inner cavity 3 through multiple inverted conical pressure measuring holes on the sensor bleed cover 1. After the pressure is balanced in the inner cavity 3, it is transferred to the silicone rubber hose 6 through the pagoda-shaped air nozzle 5 on the base, and finally guided to the external pressure tap of the atmospheric measurement system inside the aircraft, ensuring efficient, low-cost and highly reliable extraction of the aircraft surface pressure.

[0030] The parts of this invention not described in detail are techniques known to those skilled in the art.

Claims

1. An air-entraining structure, characterized in that: It includes a surface sensor assembly and a bleed air transmission channel. The surface sensor assembly includes a bleed air cover, a base, and a pagoda-shaped nozzle. The bleed air cover has multiple through-holes for measuring pressure. The base has through holes that connect to the pressure holes. The rear end of the through holes is open. After the bleed air cover and the base are fixed together, an internal bleed air cavity is formed. The pagoda-shaped nozzle is fixed to the rear end of the base, and its internal cavity is connected to the bleed air cavity. The bleed air transmission channel uses a flexible hose. One end is connected to the pagoda head of the pagoda-shaped nozzle, and the other end is connected to the external pressure tap of the atmospheric measurement system.

2. The air-entraining structure according to claim 1, characterized in that: The air vent cover is embedded in the surface of the aircraft's head or leading edge region, and its outer surface is conformal to the local outer surface of the aircraft.

3. The air-entraining structure according to claim 2, characterized in that: The front end of the pressure measuring hole is inverted conical, and the rear end is straight.

4. The air-entraining structure according to claim 3, characterized in that: The diameter of the straight section of the pressure measuring hole is no greater than 1.5 mm, and the inverted cone angle ranges from 90° to 110°.

5. The air-entraining structure according to claim 4, characterized in that: The air duct cover and the base together form an air duct cavity, which acts as a pressure stagnation cavity, converting the dynamic pressure on the aircraft surface into static pressure and collecting airflow from multiple pressure measuring holes to achieve redundancy backup.

6. The air-entraining structure according to claim 5, characterized in that: The base and the air vent cover are welded together to form a cylindrical structure with a flange at the rear end.

7. The air-entraining structure according to claim 6, characterized in that: The pagoda-shaped air nozzle has a multi-stage expansion-contraction structure at one end, which fits into the flexible hose. The other end has an external thread structure that fits into the internal thread at the rear end of the base.

8. The air-entraining structure according to claim 7, characterized in that: The flexible hose is made of silicone rubber.

9. The air-entraining structure according to claim 7, characterized in that: The connection between the flexible hose and the pagoda-shaped air nozzle is secured with a stainless steel hose clamp. The flexible hose is laid along the internal structure of the aircraft and fixed to the inner wall of the aircraft cabin using clamps.

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