Low-cost atmospheric sensing system sand shield design method and related devices

Abstract

This invention provides a low-cost design method and related apparatus for a sand shield of an atmospheric sensing system, comprising: setting a total pressure bleed air vent sand shield at the top of the total pressure bleed air vent, the total pressure bleed air vent sand shield being made of sintered porous metal material, the aircraft substrate where the total pressure bleed air vent is located and the total pressure bleed air vent sand shield being made of the same metal material and connected by fusion welding, the outer surface of the total pressure bleed air vent sand shield having the same curvature as the aircraft skin at its location; when the static pressure bleed air vent substrate material is non-metallic, setting an umbrella-shaped sand shield at the upper end of the static pressure bleed air vent, the umbrella-shaped sand shield being fixedly bonded to the upper end of the static pressure bleed air vent substrate with low-temperature adhesive; when the static pressure bleed air vent substrate material is metallic, the sand shield scheme adopts a sintered porous metal sand shield being the same as the total pressure bleed air vent sand shield. The technical solution of this invention solves the technical problems of complex manufacturing processes and significant impact on aerodynamic performance associated with traditional sand shields.

Description

Technical Field

[0001] This invention relates to the field of aircraft measurement technology, and in particular to a low-cost design method and related device for a sand shield for an atmospheric sensing system. Background Technology

[0002] As an advanced flight parameter sensing system, the flush air data sensing (FADS) system has been continuously developed and improved. Currently, the technology is relatively mature abroad. In particular, the FADS system for blunt-nosed aircraft has been successfully industrialized and has been widely tested and applied to various types of aircraft. Its basic principle is to obtain the surface pressure through pressure measurement holes configured on the leading edge surface of the aircraft, and to deduce the flight parameters of the aircraft based on the established aerodynamic model.

[0003] Because FADS (Flight Analysis and Control System) is crucial for aircraft flight safety, its reliability inevitably suffers from problems such as pressure port malfunctions, pressure sensor failures, or circuit system failures during flight, which can significantly impact flight safety. For example, in 2008, a B-2 bomber experienced a pressure measurement failure due to moisture blockage in its pressure port, leading to incorrect atmospheric data. These erroneous atmospheric parameters caused the flight control system to miscalculate the required takeoff speed and climb angle, resulting in the aircraft rolling to the left and subsequently crashing. Therefore, the development of fault diagnosis and redundancy configuration methods related to FADS systems is of paramount importance.

[0004] As the sensor in an atmospheric sensing system, the bleed air structure is one of the key components. To ensure the normal operation of the atmospheric sensing system, it is necessary to ensure that the total pressure port and static pressure port of the aircraft or weapon system are not blocked by sand and dust during ground storage and airborne flight. Therefore, sand shields need to be designed to ensure smooth airflow to each bleed air structure. Existing sand protection methods mainly include the following:

[0005] (1) Pitot tube: The risk of blockage is reduced by increasing the inner diameter of the orifice. Since 2012, several pitot tube blockage incidents have occurred on Cessna 172R aircraft. Analysis suggests that the 3mm inner diameter of the pitot tube orifice is too small. When the aircraft is parked on the ground, dust or sediment in the air can be carried into the orifice by insects or splashed into the orifice during taxiing, causing blockage of the main pressure tube. After comprehensive research, the preliminary improvement plan is to replace the pitot tube of the Cessna 172R aircraft with a 7.5mm inner diameter TB aircraft pitot tube. However, embedded atmospheric sensors are usually used in high-speed aircraft. An excessively large inner diameter would disrupt the aerodynamic shape of the aircraft surface and introduce additional thermal protection pressure, making it unsuitable.

[0006] (2) Mechanical Seal Structure: Patent CN111846251B discloses a sand protection device for engine air intake, exhaust, and tail nozzle. The sand seal is made of rubber material, with supports at both ends, and is fixed to the front of the engine using a mechanical structure. This sand protection device is suitable for scenarios such as engine air intakes where the size is relatively large and there is enough space to arrange the mechanical structure. The structure is relatively complex, but the embedded atmospheric sensor is small and needs to maintain the integrity of the aerodynamic profile, making it difficult to arrange a mechanical seal structure.

[0007] (3) Sand prevention in the stagnation cavity: Patent CN119509615A provides a design method for a total pressure sensor, in which the design of the inner cavity between the stagnation cover and the base increases the deposition of redundant materials and reduces the risk of blockage in the stagnation pipe. However, this structure involves multiple mechanical structures such as the stagnation cover, the base, and the flange, and the process is relatively complex. Summary of the Invention

[0008] This invention provides a low-cost design method and related device for sand cover of atmospheric sensing system, which can solve the technical problems of complex process and large impact on aerodynamic performance of traditional sand cover.

[0009] According to one aspect of the present invention, a low-cost sand shield design method for an atmospheric sensing system is provided. The low-cost sand shield design method includes: setting a total pressure bleed air vent sand shield at the top of the total pressure bleed air vent; the total pressure bleed air vent sand shield is made of sintered porous metal material; the aircraft substrate where the total pressure bleed air vent is located and the total pressure bleed air vent sand shield are made of the same metal material and are fused and welded together; the outer surface of the total pressure bleed air vent sand shield has the same curvature as the aircraft skin at its location, maintaining the integrity of the aerodynamic shape; the total pressure bleed air vent sand shield plays a sand-proof role through the pores of the sintered porous metal material; when the static pressure bleed air vent substrate material is non-metallic, an umbrella-shaped sand shield is set at the upper end of the static pressure bleed air vent, the umbrella-shaped sand shield having a smaller cross-sectional diameter. The end of the umbrella-shaped sand shield is fixedly bonded to the upper end of the static pressure bleed hole substrate with low-temperature adhesive. During the takeoff of the weapon equipment, the edge of the umbrella-shaped sand shield is subjected to separation force, and the low-temperature adhesive is melted by aerodynamic heating, causing the umbrella-shaped sand shield to fly away from the aircraft, and the static pressure bleed hole can be vented normally. When the static pressure bleed hole substrate material is metal, a static pressure bleed hole sand shield is set at the top of the static pressure bleed hole. The static pressure bleed hole sand shield is made of sintered metal porous material. The aircraft substrate where the static pressure bleed hole is located and the static pressure bleed hole sand shield are made of the same metal material and are fused and welded together. The outer surface of the static pressure bleed hole sand shield has the same curvature as the aircraft skin at its location, maintaining the integrity of the aerodynamic shape. The static pressure bleed hole sand shield plays a sand-proof role through the pores of the sintered metal porous material.

[0010] Furthermore, the thickness of the sand cover for the total pressure vent is 0.1mm to 0.15mm.

[0011] Furthermore, the grade of the sintered metal porous material selected for the total pressure vent sand cover is chosen based on the size of the filterable particles.

[0012] Furthermore, when the substrate material of the static pressure air intake is non-metallic, the umbrella-shaped sand shield uses rubber or lightweight heat-insulating tile material to prevent it from impacting the substrate when it flies away.

[0013] Furthermore, the choice of low-temperature adhesive is based on the temperature that can be achieved by aerodynamic heating. The lower the temperature of the aircraft substrate where the static pressure bleed hole is located during actual flight, the lower the melting point of the low-temperature adhesive.

[0014] Furthermore, the tilt angle of the edge of the umbrella-shaped sand shield is calculated and determined according to the flight conditions to ensure that the umbrella-shaped sand shield can be detached smoothly.

[0015] Furthermore, the thickness of the static pressure air vent sand cover is 0.1mm to 0.15mm.

[0016] Furthermore, the grade of the sintered metal porous material selected for the static pressure air intake sand cover is chosen based on the size of the filterable particles.

[0017] According to another aspect of the present invention, a low-cost atmospheric sensing system sand cover is provided, which is designed using the low-cost atmospheric sensing system sand cover design method described above.

[0018] According to another aspect of the present invention, an aircraft is provided, the aircraft including an atmospheric sensing system and an atmospheric sensing system sand shield, the atmospheric sensing system sand shield being a low-cost atmospheric sensing system sand shield as described above.

[0019] This invention provides a low-cost sand shield design method for atmospheric sensing systems. It replaces existing mechanical seal sand shields with sintered porous metal sand shields, connected via fusion welding, resulting in a simple, low-cost, and highly reliable process. For non-weldable non-metallic materials, this invention proposes a low-cost hydrostatic sand shield solution utilizing the separation force generated during flight of the umbrella-shaped structure and low-temperature adhesive melting separation. This eliminates the need for additional mechanical structures, resulting in a simple, low-cost, and highly reliable process. Furthermore, this invention proposes low-cost sand shield solutions for both the total pressure port and the hydrostatic pressure port, effectively protecting against sand and dust blockage problems that FADS systems may encounter, significantly improving system reliability. Therefore, compared to existing technologies, the low-cost atmospheric sensing system sand shield design method provided by this invention is simpler, lower in cost, and more reliable, effectively protecting FADS systems from sand and dust blockage problems and effectively solving the problems of complex traditional sand shield processes and significant impact on aerodynamic performance. Attached Figure Description

[0020] The accompanying drawings, which form part of this specification, are provided to further illustrate embodiments of the invention and, together with the textual description, explain the principles of the invention. It is obvious that the drawings described below are merely some embodiments of the invention, and those skilled in the art can obtain other drawings based on these drawings without any creative effort.

[0021] Figure 1 This diagram illustrates the structure of a sand shield for the total pressure bleed air vent, provided according to a specific embodiment of the present invention, installed on the aircraft substrate where the total pressure bleed air vent is located;

[0022] Figure 2 A schematic diagram of the structure of the total pressure air vent sand cover provided according to a specific embodiment of the present invention is shown;

[0023] Figure 3 A schematic diagram of the structure of the umbrella-shaped sand shield provided according to a specific embodiment of the present invention is shown;

[0024] Figure 4 A schematic diagram of the structure of the umbrella-shaped sand shield provided according to a specific embodiment of the present invention, installed on a static pressure air vent substrate, is shown.

[0025] The above figures include the following reference numerals:

[0026] 10. Sand shield for total pressure bleed air vent; 20. Aircraft base where total pressure bleed air vent is located; 30. Umbrella-shaped sand shield; 40. Static pressure bleed air vent base; 40a. Static pressure bleed air vent. Detailed Implementation

[0027] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the present invention or its application or use. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0028] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this application. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0029] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these embodiments do not limit the scope of the invention. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following figures denote similar items; therefore, once an item is defined in one figure, it need not be further discussed in subsequent figures.

[0030] like Figures 1 to 4As shown, a low-cost sand shield design method for an atmospheric sensing system is provided according to a specific embodiment of the present invention. This low-cost sand shield design method includes: setting a total pressure bleed air vent sand shield 10 at the top of the total pressure bleed air vent; the total pressure bleed air vent sand shield 10 is made of sintered porous metal material; the aircraft substrate 20 where the total pressure bleed air vent is located and the total pressure bleed air vent sand shield 10 are made of the same metal material and are fused and welded together; the outer surface of the total pressure bleed air vent sand shield has the same curvature as the aircraft skin at its location, maintaining the integrity of the aerodynamic shape; the total pressure bleed air vent sand shield plays a sand-proof role through the pores of the sintered porous metal material; when the static pressure bleed air vent substrate material is non-metallic, an umbrella-shaped sand shield is set at the upper end of the static pressure bleed air vent; the horizontal... The smaller diameter end is fixedly bonded to the upper end of the static pressure bleed air vent substrate using low-temperature adhesive. During the takeoff of the weapon system, the edge of the umbrella-shaped sand shield is subjected to separation force, and the low-temperature adhesive is melted by aerodynamic heating, causing the umbrella-shaped sand shield to fly away from the aircraft, allowing the static pressure bleed air vent to breathe normally. When the static pressure bleed air vent substrate material is metal, a static pressure bleed air vent sand shield is installed at the top of the static pressure bleed air vent. The static pressure bleed air vent sand shield is made of sintered porous metal material. The aircraft substrate where the static pressure bleed air vent is located and the static pressure bleed air vent sand shield are made of the same metal material and are fused and welded together. The outer surface of the static pressure bleed air vent sand shield has the same curvature as the aircraft skin at its location, maintaining the integrity of the aerodynamic shape. The static pressure bleed air vent sand shield plays a sand-proof role through the pores of the sintered porous metal material.

[0031] This configuration provides a low-cost sand shield design method for atmospheric sensing systems. It replaces existing mechanical seal sand shields with sintered porous metal sand shields, connected via fusion welding, resulting in a simple, low-cost, and highly reliable process. For non-weldable non-metallic materials, this invention proposes a low-cost hydrostatic sand shield solution utilizing the separation force generated during flight of the umbrella-shaped structure and low-temperature adhesive melting separation. This eliminates the need for additional mechanical structures for self-separation, resulting in a simple, low-cost, and highly reliable process. Furthermore, this invention proposes low-cost sand shield solutions for both the total pressure port and the hydrostatic pressure port, effectively protecting against sand and dust blockage problems that FADS systems may encounter, significantly improving system reliability. Therefore, compared to existing technologies, the low-cost atmospheric sensing system sand shield design method provided by this invention is simpler, lower in cost, and more reliable, effectively protecting FADS systems from sand and dust blockage problems and effectively solving the problems of complex traditional sand shield processes and significant impact on aerodynamic performance.

[0032] Furthermore, in this invention, the thickness of the total pressure vent sand cover is preferably 0.1mm to 0.15mm. The grade of the sintered metal porous material selected for the total pressure vent sand cover is chosen based on the size of the filterable particles. National standards such as GB / T6886, GB / T6887, and GB / T2586 provide particle size values ​​corresponding to the filtration efficiency of sintered metal porous materials.

[0033] When designing sand covers for static pressure holes, there are two technical solutions based on whether the static pressure hole matrix material is metal or non-metal.

[0034] When the static pressure air intake vent matrix material 40 is non-metallic, the umbrella-shaped sand cover 30 scheme is as follows: Figure 2 As shown, the umbrella-shaped sand shield 30 is made of rubber or lightweight heat-insulating tile material and is a frustum-shaped structural component to prevent impact to the substrate during takeoff. The end of the umbrella-shaped sand shield 30 with a smaller cross-sectional diameter is fixedly bonded to the upper end of the static pressure bleed air vent substrate using low-temperature adhesive. During the takeoff of the weapon system, the edge of the umbrella-shaped sand shield is subjected to separation force, and the low-temperature adhesive is melted by aerodynamic heating, allowing the umbrella-shaped sand shield to detach from the aircraft, and the static pressure bleed air vent can be vented normally. The low-temperature adhesive is selected based on the temperature that can be achieved by aerodynamic heating; the lower the temperature of the aircraft substrate where the static pressure bleed air vent is located during actual flight, the lower the melting point of the low-temperature adhesive. The tilt angle of the edge of the umbrella-shaped sand shield is determined according to flight conditions to ensure that the umbrella-shaped sand shield can detach smoothly.

[0035] When the substrate material 40 of the static pressure vent is non-metallic, the sand shield scheme adopts a sintered metal porous material sand shield consistent with the total pressure vent sand shield, which includes the static pressure vent and the sintered metal porous material sand shield. The sand shield and the vent are made of the same metal material and are welded together. The outer surface of the sand shield has the same curvature as the aircraft skin to maintain the integrity of the aerodynamic shape. The thickness of the static pressure vent sand shield is 0.1mm to 0.15mm. The grade of the sintered metal porous material selected for the static pressure vent sand shield is selected according to the filterable particle size. National standards such as GB / T6886-2008, GB / T6887-2007, and GB / T2586-2010 give the particle size values ​​corresponding to the filtration efficiency of sintered metal porous materials.

[0036] According to another aspect of the present invention, a low-cost atmospheric sensing system sand cover is provided, which is designed using the low-cost atmospheric sensing system sand cover design method described above.

[0037] This configuration provides a low-cost sand shield for an atmospheric sensing system. The sand shield is designed using the aforementioned low-cost sand shield design method, replacing the existing mechanical seal structure sand shield with a sintered porous metal material sand shield. The connection is achieved through fusion welding, resulting in a simple, low-cost, and highly reliable process. For non-weldable non-metallic materials, this invention proposes a low-cost hydrostatic sand shield solution utilizing the separation force generated during flight of the umbrella-shaped structure and low-temperature adhesive melting separation. This solution eliminates the need for additional mechanical structures, resulting in a simple, low-cost, and highly reliable process. Furthermore, this invention proposes low-cost sand shield solutions for both the total pressure port and the hydrostatic pressure port, effectively protecting the FADS system from potential sand and dust blockage issues and significantly improving system reliability.

[0038] According to another aspect of the present invention, an aircraft is provided, the aircraft including an atmospheric sensing system and an atmospheric sensing system sand shield, the atmospheric sensing system sand shield being a low-cost atmospheric sensing system sand shield as described above.

[0039] This configuration provides an aircraft. Compared with existing technologies, the low-cost atmospheric sensing system sand cover design method provided by this invention is simple in process, low in cost, and highly reliable. It can effectively protect against sand and dust blockage problems that the FADS system may encounter. Therefore, its application in aircraft can effectively improve the aircraft's working performance.

[0040] like Figures 1 to 4 As shown in the figure, a low-cost sand cover design method for an atmospheric sensing system is provided according to a specific embodiment of the present invention, including the following steps:

[0041] Step 1: Design the sand cover for the main pressure hole;

[0042] A low-cost total pressure hole sand cover design is provided, such as... Figure 1 As shown, it includes a total pressure vent and a sand cover made of sintered metal porous material.

[0043] The sand shield is installed at the top of the air intake hole and plays a sand-proof role through the pores of the sintered metal porous material.

[0044] Step 2: Design of sand cover for static pressure hole;

[0045] A low-cost design scheme for a hydrostatic pore sand cover is provided. Based on the classification of the hydrostatic pore matrix material as metal / non-metal, there are two technical solutions.

[0046] When the substrate material of the static pressure vent is non-metallic, the sand cover solution includes a static pressure vent, an umbrella-shaped sand cover, and a low-temperature adhesive.

[0047] During the takeoff of an aircraft or weapon system, the edge of the umbrella-shaped sand shield is subjected to separation force, and the low-temperature adhesive is melted by aerodynamic heating, causing the umbrella-shaped sand shield to fly away from the aircraft or weapon system, and the static pressure vent can be vented normally.

[0048] When the substrate material of the static pressure hole is metal, the sand cover scheme adopts the same sintered metal porous material sand cover as the total pressure hole sand cover, which includes static pressure air vents and sintered metal porous material sand cover.

[0049] To gain a better understanding of the low-cost atmospheric sensing system sand cover solution provided by this invention, a detailed description is provided below with reference to specific examples and accompanying drawings.

[0050] Step 1: Design the sand cover for the main pressure hole;

[0051] A low-cost total pressure hole sand cover design is provided, which includes a total pressure vent hole and a sand cover made of sintered metal porous material.

[0052] The sand shield is installed at the top of the air intake hole and plays a sand-proof role through the pores of the sintered metal porous material.

[0053] In this example, the air intake vent substrate material is high-temperature nickel-based metal material GH4099, so the sand shield is also made of GH4099 and is welded by melting. The outer surface of the sand shield has the same curvature as the aircraft skin and is a blunt ball head to maintain the integrity of the aerodynamic shape.

[0054] In this example, the thickness of the sand cover is 0.1 mm;

[0055] In this example, since the material selected is high-temperature nickel-based metal material GH4099, referring to GB / T6887-2019, a sheet-like sintered metal porous material filter element of grade NG022-B1-10-1 was selected according to the diameter of the sand and gravel blocking 60μm and the diameter of the total pressure air intake 2mm. After being processed according to the actual size, it was welded to the head of the total pressure air intake.

[0056] Step 2: Design of sand cover for static pressure hole;

[0057] A low-cost design scheme for a hydrostatic pore sand cover is provided. Based on the classification of the hydrostatic pore matrix material as metal / non-metal, there are two technical solutions.

[0058] In this example, the substrate material of the static pressure hole is high-temperature nickel-based metal material GH4099. Therefore, the sand cover scheme adopts the same sintered metal porous material sand cover as the total pressure hole sand cover, which includes static pressure air vents and sintered metal porous material sand cover.

[0059] In this example, the sand shield and the air vent are made of the same metal material, namely high-temperature nickel-based metal material GH4099, and are welded by melting. The outer surface of the sand shield has the same curvature as the aircraft skin, maintaining the integrity of the aerodynamic shape.

[0060] In this example, the thickness of the sand cover is selected as 0.1mm;

[0061] In this example, since the material selected is high-temperature nickel-based metal material GH4099, referring to GB / T6887-2019, a sheet-like sintered metal porous material filter element of grade NG022-B1-10-1 was selected according to the diameter of the sand and gravel blocking 60μm and the diameter of the static pressure air intake hole 2mm. After being processed according to the actual size, it was welded to the head of the static pressure air intake port.

[0062] In summary, the low-cost sand cover solution for an atmospheric sensing system provided by this invention has at least the following advantages compared to existing technologies:

[0063] (1) This invention proposes a low-cost sand cover solution for an atmospheric sensing system. The existing mechanical seal structure sand cover is replaced by a sand cover made of sintered metal porous material and connected by melting welding. The process is simple, low-cost and highly reliable.

[0064] (2) For non-metallic materials that cannot be welded, this invention proposes a low-cost static pressure sand cover solution that utilizes the separation force generated during the flight of the umbrella-shaped structure and the low-temperature adhesive melting separation. It does not require additional mechanical structures to separate on its own, and the process is simple, low-cost, and highly reliable.

[0065] (3) The present invention proposes low-cost sand cover solutions for the total pressure hole and static pressure hole respectively, which can effectively protect the FADS system from sand and dust blockage problems that may be encountered, and greatly improve the reliability of the system.

[0066] For ease of description, spatial relative terms such as "above," "on top of," "on the upper surface of," "above," etc., are used herein to describe the spatial positional relationship of a device or feature as shown in the figures to other devices or features. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation beyond the orientation of the device as described in the figures. For example, if the device in the figures were inverted, a device described as "above" or "on top of" other devices or structures would subsequently be positioned as "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below." The device may also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatial relative descriptions used herein will be interpreted accordingly.

[0067] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore should not be construed as limiting the scope of protection of this invention.

[0068] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A low-cost sand cover design method for an atmospheric sensing system, characterized in that, The low-cost atmospheric sensing system sand cover design method includes: A sand shield is installed at the top of the total pressure bleed air vent. The sand shield is made of sintered metal porous material. The aircraft substrate where the total pressure bleed air vent is located and the sand shield are made of the same metal material and are connected by melting and welding. The outer surface of the sand shield has the same curvature as the skin of the aircraft at its location to maintain the integrity of the aerodynamic shape. The sand shield plays a sand-proof role through the pores of the sintered metal porous material. When the substrate material of the static pressure air vent is non-metallic, an umbrella-shaped sand shield is installed at the upper end of the static pressure air vent. The end of the umbrella-shaped sand shield with a smaller cross-sectional diameter is fixedly bonded to the upper end of the static pressure air vent substrate with low-temperature adhesive. During the take-off process of the weapon equipment, the edge of the umbrella-shaped sand shield is subjected to separation force, and the low-temperature adhesive is melted by aerodynamic heating, which causes the umbrella-shaped sand shield to fly away from the aircraft, and the static pressure air vent can be vented normally. When the substrate material of the static pressure blew hole is metal, a static pressure blew hole sand shield is installed at the top of the static pressure blew hole. The static pressure blew hole sand shield is made of sintered metal porous material. The aircraft substrate where the static pressure blew hole is located and the static pressure blew hole sand shield are made of the same metal material and are connected by melting and welding. The outer surface of the static pressure blew hole sand shield has the same curvature as the aircraft skin at its location to maintain the integrity of the aerodynamic shape. The static pressure blew hole sand shield plays a sand-proof role through the pores of the sintered metal porous material.

2. The low-cost sand cover design method for an atmospheric sensing system according to claim 1, characterized in that, The thickness of the sand cover for the total pressure vent is 0.1mm to 0.15mm.

3. The low-cost sand cover design method for an atmospheric sensing system according to claim 2, characterized in that, The grade of the sintered metal porous material selected for the total pressure air vent sand cover is chosen based on the size of the filterable particles.

4. The low-cost sand cover design method for an atmospheric sensing system according to any one of claims 1 to 3, characterized in that, When the substrate material of the static pressure air intake hole is non-metallic, the umbrella-shaped sand shield is made of rubber or lightweight heat-insulating tile material to prevent it from impacting the substrate when it flies away.

5. The low-cost sand cover design method for an atmospheric sensing system according to claim 4, characterized in that, The choice of low-temperature adhesive is based on the temperature that can be achieved by aerodynamic heating. The lower the temperature of the aircraft substrate where the static pressure air vent is located during actual flight, the lower the melting point of the low-temperature adhesive.

6. The low-cost sand cover design method for an atmospheric sensing system according to claim 5, characterized in that, The tilt angle of the umbrella-shaped sand shield's edge is calculated and determined according to flight conditions to ensure that the umbrella-shaped sand shield can be detached smoothly.

7. The low-cost sand cover design method for an atmospheric sensing system according to claim 1, characterized in that, The thickness of the static pressure air vent sand cover is 0.1mm to 0.15mm.

8. The low-cost sand cover design method for an atmospheric sensing system according to claim 7, characterized in that, The grade of the sintered metal porous material selected for the static pressure air vent sand cover is chosen based on the size of the filterable particles.

9. A low-cost sand cover for an atmospheric sensing system, characterized in that, The low-cost atmospheric sensing system sand cover is designed using the low-cost atmospheric sensing system sand cover design method as described in any one of claims 1 to 8.

10. An aircraft, characterized in that, The aircraft includes an atmospheric sensing system and an atmospheric sensing system sand shield, wherein the atmospheric sensing system sand shield is the low-cost atmospheric sensing system sand shield as described in claim 9.

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