An aircraft embedded pitot-static system pressure port adapter

Abstract

The application discloses an aircraft embedded atmospheric data system pressure hole adapter and belongs to the technical field of aircraft ground test support equipment. The adapter is used for connecting pressure output pipelines of an atmospheric data tester with pressure holes on the surface of an aircraft body to verify the function and precision of the embedded atmospheric data system. The adapter comprises a fuselage reverse mold assembly matched with the shape of a nose and fixed on a nose shell, and a plurality of pressure hole butt joint assemblies independently fixed on the fuselage reverse mold assembly. The pressure hole butt joint assembly comprises a pressure lead steel pipe-pressure bearing surface assembly, a silica gel pad, a through hole hexagonal screw and a positioning base. The fuselage reverse mold assembly is used for realizing overall rapid positioning and clamping, and the position fine adjustment function of the threaded mechanical pressing mechanism and the positioning base in each pressure hole butt joint assembly is used for realizing accurate butt joint and long-term stable sealing of each pressure hole.

Description

Technical Field

[0001] This invention belongs to the technical field of aircraft atmospheric data testing system equipment, and specifically relates to an adapter for a pressure measurement port of an aircraft embedded atmospheric data system. Background Technology

[0002] With the increasing demands for stealth performance and integrated aerodynamic design in modern aircraft, embedded air data systems have gradually replaced traditional air data probes, becoming standard equipment for next-generation fighter jets and high-end civilian aircraft. These systems typically have multiple pressure measurement ports arranged around the nose of the aircraft. By measuring local aerodynamic pressure, the embedded air data computer calculates key flight parameters such as airspeed, altitude, Mach number, angle of attack, and sideslip angle in real time.

[0003] Ground testing is a critical step before aircraft takeoff, and ground testing of the embedded air data system is essential. It is the final safety checkpoint to verify the proper functioning of the system's sensors, computers, and algorithms. Only through effective ground testing can it be confirmed that the system is in normal working order before takeoff, thus ensuring flight safety. During ground testing, the pressure output lines of the air data testing instrument must be reliably connected to the pressure measurement ports on the aircraft surface to verify the system's functionality and accuracy. However, the pressure measurement ports of the embedded air data system are typically located on highly smooth curved surfaces with numerous and densely distributed ports. Traditional connection methods generally involve manual hand-pressing or using vacuum pump-assisted suction cup fixation.

[0004] Traditional connection methods face two major challenges: manual pressure connection is inefficient and unreliable. Relying on testers to hold the tubing and align and press it against a single pressure test hole can lead to fatigue during long-term operation, resulting in poor sealing and pressure leakage, and making it impossible to achieve long-term testing of multiple holes. Using a vacuum pump-assisted suction cup fixation can achieve the testing function, but it requires external vacuum pumps and other auxiliary equipment, which not only increases test preparation time and equipment costs, but also places higher demands on the skills of operators, making it unfavorable for rapid field support.

[0005] Therefore, there is an urgent need for a ground test adapter that is suitable for the multi-position characteristics of embedded atmospheric data systems, has the ability to be quickly installed and has long-term stable sealing capabilities, in order to improve testing efficiency, ensure data accuracy, and ultimately serve flight safety. Summary of the Invention

[0006] The purpose of this invention is to overcome the shortcomings of existing connection technologies and provide an aircraft embedded atmospheric data system pressure measurement port adapter that is easy to install, has a stable connection, and has long-term airtight performance, especially suitable for high-precision pressure transmission under complex curved surface shapes.

[0007] The technical solution of the present invention is as follows: An adapter for a pressure measurement port in an aircraft embedded atmospheric data system, comprising a fuselage molding assembly and a pressure measurement port docking assembly; wherein, the fuselage molding assembly comprises two detachably connected fuselage molding structures, the two fuselage molding structures being rigidly connected in the non-clamping area by internal reinforcing ribs or connectors; the inner surface of the fuselage molding assembly conforms to the outer skin shape of the section of the aircraft nose where the pressure measurement port is located, and is fixedly connected to the nose by a detachable lateral clamping mechanism; the pressure measurement port docking assembly comprises a pressure-feeding steel pipe-pressure-bearing surface assembly, a silicone pad, a through-hole hexagonal screw, and a positioning base; wherein, the pressure-feeding steel pipe-pressure-bearing surface assembly consists of a pressure-feeding steel pipe and a... The pressure-bearing surfaces are welded to form an integrated airtight structure; the silicone pad is fixedly bonded to the bottom of the pressure-bearing surface; the through-hole hexagonal screw passes through the positioning base and engages with its threaded insert, and the screw shaft has a through hole for the pressure-guiding steel pipe to pass through, with its lower end acting on the upper surface of the pressure-bearing surface; the positioning base includes a lower rectangular positioning part, an upper boss, and a threaded insert embedded in the center; multiple pressure-measuring hole docking assemblies can be adjusted in position on the body molding assembly, and are installed one-to-one at the respective pressure-measuring hole positioning positions of the body molding assembly, to establish independent sealed connection channels between the pressure output pipelines of the atmospheric data tester and the pressure-measuring holes on the body surface.

[0008] Optionally, the lateral clamping mechanism includes clamping lugs arranged in pairs on the two body molding structures, each with a through hole; the upper and lower body molding structures are locked together by screws and nuts. As the screws are screwed in, the clamping force on both sides forces the entire assembly to retract toward the center of the machine head. Finally, through the friction between the inner surface of the assembly and the skin surface, as well as the support of the local structure, the body molding assembly is firmly fixed to the machine head.

[0009] Optionally, the body molding assembly is provided with a double-layer guide and mounting structure corresponding to each pressure test hole. The structure includes an upper rectangular limiting hole and a lower square observation window, forming a sandwich space of a certain height between the two layers.

[0010] Optionally, the pressure testing hole docking assembly includes: a pressure-applying steel pipe-pressure-bearing surface assembly, which is formed by welding the pressure-applying steel pipe and the pressure-bearing surface to form an integrated airtight structure; a silicone pad, which is fixedly bonded to the bottom of the pressure-bearing surface; a positioning base, which includes a lower rectangular positioning part, an upper boss and a threaded insert embedded in the center; and a through-hole hexagonal screw, which passes through the positioning base and is screwed into the threaded insert therein, with a through hole in the screw shaft for the pressure-applying steel pipe to pass through, and its lower end acting on the upper surface of the pressure-bearing surface.

[0011] Optionally, the dimensions of the lower cuboid positioning part of the positioning base are adapted to the upper rectangular limiting hole and the height of the interlayer of the body molding assembly, so that it can move in a two-dimensional plane and rotate 360° around the normal of the plane within the interlayer.

[0012] Optionally, the diameter of the through hole of the external hexagonal screw is 0.1 mm to 0.8 mm larger than the outer diameter of the pressure-guiding steel pipe, and the length of the screw is greater than the sum of the total thickness of the positioning base, the lower wall thickness of the body mold assembly, and the compression stroke of the pressure-bearing surface.

[0013] Optionally, the silicone pad is an elastic silicone rubber component. Its bottom surface, which is bonded to the pressure-bearing surface, is flat, and its top surface, which is in contact with the machine body, is flat or curved. It has an annular sealing area around the central through hole in its middle part, which can automatically adapt and stick to the surface of the machine body after being subjected to the pressure of the pressure-bearing steel pipe-pressure-bearing surface assembly.

[0014] Optionally, the positioning base is made of transparent or semi-transparent engineering plastic, and the outer contour of its upper boss is quadrilateral or polygonal.

[0015] Optionally, the long side of the upper rectangular limiting hole of the double-layer guide and mounting structure of the body molding assembly is parallel to the longitudinal axis of the machine head, and its size is 0.5mm to 2mm larger on one side than the corresponding size of the lower cuboid positioning part of the positioning base.

[0016] The working principle of this invention is as follows: The body molding assembly is fastened to the machine head by a screw mechanism, forming an overall support and initial positioning reference; the pressure testing hole docking assembly is placed inside the double-layer guide structure of the molding assembly, first moving within the double-layer guide structure to achieve precise positioning, and then the silicone pad is gradually pressed against the surface of the machine body by tightening the external hexagonal screws of the through hole; when tightening continues, the positioning base moves upward under the reaction force, abutting against the upper structure of the molding assembly, thereby achieving mechanical self-locking and stable sealing of the pressure testing hole unit. This process realizes a reliable connection mechanism of overall positioning - hole-by-hole pressurization - point-by-point locking.

[0017] The beneficial effects of this invention are reflected in: (1) Improve the efficiency and reliability of multi-hole testing: By combining overall molding and split locking, the installation and sealing of multiple pressure test holes can be completed at one time, overcoming the shortcomings of traditional manual manual pressing and docking, which cannot achieve the function of long-term testing of multiple holes; (2) Adaptable to complex curved surfaces: Abandoning the traditional overall full-fit approach, a local compression and sealing strategy is adopted to overcome the matching problems caused by manufacturing errors and deformation of large curved parts. It has good adaptability and can be applied to multiple flights of the same type of machine. (3) Pure mechanical compression seal: No external auxiliary equipment such as vacuum pump is required. The seal is achieved by relying on the mechanical pressure of the thread. It is suitable for both positive and negative pressure tests, and the sealing performance does not decay during long-term testing. (4) Easy to operate and highly reliable: The structure is intuitive and the installation process is simple, making it easy for ground staff to master and implement, greatly reducing the dependence on field testing equipment and personnel; (5) Good maintainability and reusability: easy to disassemble, each part can be replaced independently, and easily damaged parts such as silicone pads are easy to maintain. The whole device can be repeatedly used for multiple flights of the same type of machine. Attached Figure Description

[0018] To more clearly illustrate the technical solution of the present invention, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this disclosure. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. Figure 1 This is a schematic diagram of the pressure port adapter structure for the aircraft embedded air data system of the present invention; Figure 2 This is a schematic diagram of the structure of the present invention installed on an embedded atmospheric data system; Figure 3 This is a schematic diagram of the fuselage molding assembly structure of the present invention; Figure 4 This is a schematic diagram of the pressure testing hole docking assembly of the present invention; Figure 5 yes Figure 4 A cross-sectional view of the AA plane; Figure 6 Partial cross-sectional view of a single hole mounting position of the present invention. The components include: 1. Body molding assembly; 11. Rectangular limiting hole; 12. Square observation window; 2. Pressure testing hole docking assembly; 21. Pressure-applying steel pipe-pressure-bearing surface assembly; 22. Silicone pad; 23. Through-hole external hexagonal screw; 24. Positioning base; 3. Machine head; 4. Pressure testing hole. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of this application clearer, the following detailed description of this application will be provided in conjunction with the accompanying drawings. The described embodiments should not be considered as limitations on this application. All other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0020] In the following description, references to "some embodiments" describe a subset of all possible embodiments. However, it is understood that "some embodiments" can be the same or different subsets of all possible embodiments and can be combined with each other without conflict. The terms "first" and "second" are used merely to distinguish similar objects and do not represent a specific ordering of objects. The terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion. For example, a process, method, apparatus, product, or server that includes a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or modules not explicitly listed or inherent to these processes, methods, products, or apparatuses. Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used herein is for the purpose of describing embodiments of this application only.

[0021] This embodiment provides an adapter for the pressure measurement port of an aircraft embedded air data system. Its function is to connect the pressure output lines of an air data testing instrument to the pressure measurement ports on the aircraft surface to verify the functionality and accuracy of the embedded air data system. Figures 1 to 5 As shown, the aircraft embedded air data system pressure port adapter includes: a fuselage molding assembly 1 that conforms to the shape of the nose 3 and is fixed to the nose shell, and multiple independent pressure port docking assemblies 2 fixed to the fuselage molding assembly 1. The pressure port docking assembly 2 includes a pressure-bearing steel pipe-pressure-bearing surface assembly 21, a silicone pad 22, a through-hole hexagonal screw 23, and a positioning base 24.

[0022] like Figure 2 As shown, using the aircraft embedded air data system pressure port adapter, the pressure output lines of the air data tester can be reliably connected to the pressure ports on the aircraft fuselage surface. This satisfies the ground testing function of the embedded air data system and simplifies the connection process between the air data tester and the nose pressure port. The fuselage molding assembly 1 is fixedly connected to the aircraft shell, and the pressure port docking assembly 2 docks with the pressure port to ensure that the pressure output lines of the air data tester and the pressure ports of the aircraft do not detach, maintaining a stable connection for a long time. This prevents foreign objects from entering the static pressure port, avoiding contamination of the aircraft and blockage of the lines.

[0023] The following detailed description of the specific structure, assembly relationship, and workflow of the aircraft embedded atmospheric data system pressure port adapter, in conjunction with preferred embodiments of the present invention, is provided so that those skilled in the art can accurately understand and implement this solution.

[0024] This embodiment designs a typical layout for an embedded atmospheric data system of a certain type of aircraft. The system has ten pressure measurement ports 4 evenly distributed circumferentially at the front of the nose for collecting local static pressure signals. The adapter needs to achieve a synchronous, reliable, and sealed connection with these ten pressure measurement ports, ensuring the stability and airtightness of the connection throughout the entire ground testing period.

[0025] like Figure 3 As shown, the fuselage molding assembly 1 serves as the basic support and macroscopic positioning mechanism for the adapter, with its core design concept being contour-following clamping. This fuselage molding assembly 1 is designed and manufactured based on the three-dimensional shape data of the front section of the specific aircraft head. The inner wall maintains the shape of the surface skin of the head 3, ensuring lightweight design and sufficient structural rigidity. To accommodate the curvature of the head, the fuselage molding assembly 1 includes two detachably connected fuselage molding structures. These two structures are rigidly connected in the non-clamping area via internal reinforcing ribs or connectors, forming an integral frame. To achieve a non-damaging, detachable, rigid connection with the head 3, the fuselage molding assembly 1 is symmetrically equipped with screw clamping mechanisms on both sides. Specifically, a clamping lug is designed at the upper and lower positions on the left and right sides of the fuselage molding assembly 1, with through holes on the lugs. Correspondingly, approximately 5mm of clamping travel space is reserved on both sides between the inner side of the fuselage molding assembly 1 and the skin of the head 3. The upper and lower parts can be locked together with screws and nuts. As the screws are screwed in, the clamping force on the left and right sides forces the fuselage molding assembly 1 to retract towards the center of the machine head. Finally, through the friction between the inner surface of the fuselage molding assembly 1 and the skin surface, as well as the support of the local structure, the fuselage molding assembly 1 is firmly fixed to the machine head 3.

[0026] Positioning and docking interface for pressure testing holes 4: A double-layer guide structure is precisely machined on the fuselage molding assembly 1, corresponding to the positions of the ten nose pressure testing holes 4. This is crucial for achieving precise docking of the holes. A large square observation window 12 is provided in the lower layer, serving three main functions: first, to provide operators with a clear view during initial installation, allowing direct visual observation and preliminary alignment of the pressure testing holes 4 on the fuselage below; second, to provide operational space for inserting the pressure-bearing steel pipe-pressure-bearing surface assembly 21 and the silicone pad 22 in the pressure testing hole docking assembly 2, and to allow the pressure-bearing steel pipe-pressure-bearing surface assembly 21 to move within this double-layer guide structure for precise positioning; and third, to serve as an auxiliary observation window during testing. A rectangular limiting hole 11 is provided in the upper layer. The length of this hole is typically aligned with the longitudinal axis of the aircraft, and its dimensions are carefully designed: the length is slightly larger than the corresponding length of the cuboid positioning part under the positioning base 24, while the width is slidably fitted to the width of the base. The design of the rectangular hole is the core of its ingenious insertion and locking functionality. A space with a defined height is formed between the upper and lower layers. The height of this space is 1mm to 1.5mm greater than the thickness of the lower cuboid positioning part of the positioning base 24. This dimensional difference is crucial, ensuring that when the positioning base 24 is initially placed in the space, it not only has room to move along the length of the rectangular hole for fine-tuning, but also has sufficient vertical space to provide travel for subsequent locking actions. Considering that this area will bear significant concentrated pressure during locking, reinforcing ribs are designed on both sides of the component body of each double-layer structure, significantly improving the rigidity and compressive strength of this local structure and preventing deformation or damage under long-term use or excessive locking force.

[0027] like Figure 4 and Figure 5As shown, the pressure test port assembly 2 comprises four parts: a pressure-applying steel pipe-pressure-bearing surface assembly 21, a silicone pad 22, a through-hole hexagonal screw 23, and a positioning base 24. The pressure-applying steel pipe-pressure-bearing surface assembly 21 is the base for pressure transmission and sealing. The pressure-applying steel pipe and the pressure-bearing surface are connected by welding, ensuring a secure and leak-proof connection. The upper surface of the pressure-bearing surface is finely ground smooth. One end of the pressure-applying steel pipe is welded perpendicularly to the center of the pressure-bearing surface, while the other end serves as an external interface. Its length is designed so that, when the assembly is fully installed, it can completely pass through the center through-hole of the through-hole hexagonal screw 23 and extend an additional length, typically 15-25mm, to reliably connect to the pressure output pipeline of the atmospheric data testing instrument. The silicone pad 22 is a key elastic element that directly contacts the aircraft skin and forms a seal. Its bottom is firmly bonded to the bottom surface of the pressure-bearing surface using adhesive. The sealing surface of the silicone gasket is designed with a concentric circle structure: the central area is a through hole, and its outer diameter is determined by the principle that it must completely cover and extend beyond the edge of the pressure measuring hole 4 on the fuselage. Typically, the diameter of the effective sealing inner ring of the silicone gasket 22 is designed to be 2 to 3 times the diameter of the pressure measuring hole 4, providing sufficient tolerance for installation alignment. The thickness of the silicone gasket 22 is optimized to ensure sufficient elastic deformation under reasonable locking force, both conforming to any minor surface undulations to form a continuous and reliable annular sealing band, and preventing damage or excessive stress due to over-compression. The through-hole external hexagonal screw 23, as the driving component for providing and transmitting locking force, has a through hole in its center. The diameter of the through hole is slightly larger than that of the pressure-applying steel pipe, allowing the pipe to pass through without causing it to wobble. The positioning base 24 is divided into upper and lower parts. The lower part is a cuboid structure whose dimensions precisely match the rectangular limiting hole 11 and the interlayer height on the fuselage molding assembly 1. After the interlayer is inserted, it can move along the length of the rectangular limiting hole 11 to achieve initial alignment of the pressure measuring hole 4; its thickness is less than the height of the interlayer, leaving room for movement. The upper part is a square structure that protrudes upwards, making it easy to clamp with a wrench during installation to prevent the entire positioning base 24 from rotating or moving when tightening the through-hole hexagonal screw 23. The positioning base 24 has a through hole in the center for inserting a copper nut. Then, the through-hole hexagonal screw 23 is tightened downwards from the copper nut, pressing the bottom against the pressure-bearing surface part of the pressure-applying steel pipe-pressure-bearing surface assembly 21. When the pressure-bearing surface is pressed down to make the silicone pad press against the surface of the machine body, the positioning base 24 will move upwards as the through-hole hexagonal screw 23 is tightened further. The cuboid part will then press against the upper layer of the interlayer of the machine body molding assembly 1 to achieve fixation and pressurize the silicone pad to achieve airtightness.

[0028] The installation and connection process is as follows: Overall positioning: Place the entire body molding assembly 1 onto the test section of the machine head 3, and visually align each double-layer structure roughly with the corresponding pressure test hole. Then, use tools to evenly tighten the four clamping screws on the left and right sides until the assembly is firmly and securely fixed to the machine head.

[0029] Separate placement: For each pressure test hole 4, take a set of pressure test hole docking components 2. First, put the pressure-bearing steel pipe-pressure-bearing surface component 21 together with its bottom silicone pad 22 into the lower square window 12 of the body molding component 1, so that the silicone pad 22 roughly covers the corresponding pressure test hole 4.

[0030] Base Placement: With the lower cuboid positioning part of the positioning base aligning with the upper rectangular hole, place the positioning base 24 into the corresponding interlayer. At this time, the base can slide within a small range within the interlayer.

[0031] Initial alignment: Pass the through-hole hexagonal screw 23 through the center copper nut of the positioning base 24 from above, and continue downwards until its lower end makes slight contact with the upper surface of the pressure-bearing surface of the pressure-applying steel pipe-pressure-bearing surface assembly 21. At this time, the operator can fine-tune the position of each component through the transparent base or the lower window to ensure that the center of the pressure-applying steel pipe and the silicone pad below are basically aligned with the pressure measuring hole of the machine body.

[0032] Locking and Sealing: Use a wrench to hold the upper boss of the positioning base 24 in place, preventing it from rotating. Use another wrench to tighten the through-hole hexagonal screw 23 clockwise. As the screw rotates downwards, its bottom presses against the bearing surface, which is blocked by the lower body skin. Therefore, the rotational motion of the screw is converted into a downward linear pressure on the bearing surface and the silicone pad 22. The silicone pad 22 is pressed against the body surface and undergoes elastic deformation, tightly adhering to the skin and gradually forming a seal. After the silicone pad 22 is compacted, continue to tighten the screw. Since the bearing surface-silicone pad 22 system cannot continue to move downwards, the reaction force will cause the positioning base 24 to move upwards relative to the screw. Finally, the upper surface of the lower cuboid positioning part of the positioning base 24 will be tightly pressed against the upper inner wall of the body molding assembly 1, achieving mechanical self-locking. At this point, the tightening force of the screw is converted into two parts: one part is transmitted through the base to the molding assembly 1 of the machine body, forming a reverse support; the other part continues to act on the bearing surface, maintaining the sealing and clamping force of the silicone gasket 22. This structure cleverly transforms a single tightening action into two results: sealing and locking. The final installation result is shown in the figure below. Figure 6 As shown.

[0033] Pipeline connection: After all ten pressure test hole docking components 2 are installed and locked, the pressure output pipelines of the ten corresponding channels of the atmospheric data tester are respectively connected to the protruding ends of the pressure-testing steel pipes of each pressure-testing steel pipe-pressure-bearing surface component 21 to complete all air circuit connections.

[0034] The atmospheric data testing instrument is activated, applying precise positive or negative pressure signals to each channel according to a preset program. The pressure travels through pipes, pressure-sensing steel pipes, and channels within the pressure-bearing surface (or directly through if the silicone pad 22 has a through hole in the center), acting on the sealed cavity formed by the silicone pad 22, and ultimately being transmitted equivalently to the fuselage pressure measurement port and the embedded atmospheric data sensor inside. The flight control computer collects these pressure signals and calculates atmospheric parameters such as airspeed, altitude, Mach number, angle of attack, and sideslip angle. By comparing and analyzing these parameters with the standard values ​​set by the testing system, the functional verification, accuracy calibration, and health status assessment of the embedded atmospheric data system can be completed.

[0035] After the test, disconnect all external pressure testing hoses. For each pressure testing port assembly 2, loosen the external hexagonal screws 23 counterclockwise with a wrench. As the screws loosen, the upward clamping force acting on the positioning base 24 is first eliminated, and the base returns to its free state in the interlayer; subsequently, the downward pressure acting on the pressure-bearing surface decreases until it disappears, and the silicone pad rebounds under its own elasticity, detaching from the tight contact with the machine body. Rotate the positioning base 24 about 90 degrees so that the long side of its lower cuboid positioning part is aligned with the length direction of the rectangular hole on the upper layer of the machine body molding assembly. At this time, the base size matches the rectangular hole, and the entire pressure testing port 2 assembly can be removed upward from the interlayer. Finally, completely loosen and remove the four clamping screws on the left and right sides of the machine body molding assembly 1, and the assembly will naturally detach from the machine head, completing the disassembly work.

[0036] Note that the above description is merely a preferred embodiment of the present invention and the technical principles employed. Those skilled in the art will understand that the present invention is not limited to the specific embodiments described herein, and various obvious changes, readjustments, and substitutions can be made without departing from the scope of protection of the present invention. Therefore, although the present invention has been described in detail through the above embodiments, the present invention is not limited to the above embodiments, and may include many other equivalent embodiments without departing from the concept of the present invention, the scope of which is determined by the scope of the appended claims.

Claims

1. A pressure port adapter for an aircraft embedded atmospheric data system, characterized in that, Includes fuselage molding assembly (1) and pressure testing hole docking assembly (2); The fuselage molding assembly (1) includes two detachably connected fuselage molding structures. The two fuselage molding structures are rigidly connected in the non-clamping area by internal reinforcing ribs or connectors. The inner surface of the fuselage molding assembly (1) is matched with the outer skin of the section where the pressure test hole is located on the nose of the aircraft, and is fixedly connected to the nose through a detachable lateral clamping mechanism. The pressure testing hole docking assembly (2) includes a pressure-feeding steel pipe-pressure-bearing surface assembly (21), a silicone pad (22), a through-hole hexagonal screw (23), and a positioning base (24); wherein, the pressure-feeding steel pipe-pressure-bearing surface assembly (21) is formed by welding the pressure-feeding steel pipe and the pressure-bearing surface to form an integrated airtight structure; the silicone pad (22) is fixedly bonded to the bottom of the pressure-bearing surface; the through-hole hexagonal screw (23) passes through the positioning base (24) and engages with its threaded insert, the through-hole hexagonal screw (23) has a through hole in the screw shaft for the pressure-feeding steel pipe to pass through, and its lower end acts on the upper surface of the pressure-bearing surface; the positioning base (24) includes a lower rectangular positioning part, an upper boss, and a threaded insert embedded in the center; Multiple pressure testing hole docking components (2) can be adjusted in position on the fuselage molding component (1) and installed one by one at the pressure testing hole positioning positions of the fuselage molding component (1) to establish an independent sealed connection channel between each pressure output pipeline of the atmospheric data tester and the pressure testing hole on the fuselage surface.

2. The pressure port adapter for an aircraft embedded atmospheric data system according to claim 1, characterized in that: The lateral clamping mechanism includes clamping lugs that are set in pairs on the two body molding structures respectively, and the clamping lugs have through holes; the upper and lower body molding structures are locked by screws and nuts. As the screws are screwed in, the clamping force on both sides forces the entire assembly to retract towards the center of the machine head. Finally, the friction between the inner surface of the assembly and the skin surface, as well as the local structural support, firmly fix the body molding assembly (1) to the machine head.

3. The pressure port adapter for an aircraft embedded air data system according to claim 1, characterized in that: The fuselage molding assembly (1) is provided with a double-layer guide and installation structure corresponding to each pressure test hole. The structure includes an upper rectangular limiting hole (11) and a lower square observation window (12), forming a sandwich space of a certain height between the two layers.

4. The pressure port adapter for an aircraft embedded atmospheric data system according to claim 1, characterized in that: The dimensions of the lower cuboid positioning part of the positioning base (24) are adapted to the upper rectangular limiting hole and the height of the interlayer of the fuselage molding assembly (1), so that it can move in a two-dimensional plane and rotate 360° around the normal of the plane within the interlayer.

5. The pressure port adapter for an aircraft embedded atmospheric data system according to claim 1, characterized in that: The diameter of the through hole of the external hexagonal screw (23) is 0.1 mm to 0.8 mm larger than the outer diameter of the pressure-guiding steel pipe, and its screw length is greater than the sum of the total thickness of the positioning base (24), the lower wall thickness of the body mold assembly (1), and the compression stroke of the pressure-bearing surface.

6. The pressure port adapter for an aircraft embedded atmospheric data system according to claim 1, characterized in that: The silicone pad (22) is an elastic silicone rubber component. Its bottom surface, which is bonded to the pressure bearing surface, is flat, and its top surface, which is in contact with the machine body, is flat or curved. The middle part is provided with an annular sealing area surrounding the central through hole. After being subjected to the pressure of the pressure-bearing steel pipe-pressure bearing surface assembly (21), it can automatically adapt and stick to the surface of the machine body.

7. The pressure port adapter for an aircraft embedded atmospheric data system according to claim 1, characterized in that: The positioning base (24) is made of transparent or semi-transparent engineering plastic, and the outer contour of its upper boss is quadrilateral or polygonal.

8. The pressure port adapter for an aircraft embedded atmospheric data system according to claim 1, characterized in that: The upper rectangular limiting hole of the double-layer guide and mounting structure of the fuselage molding assembly (1) has its long side parallel to the longitudinal axis of the machine head, and its size is 0.5mm to 2mm larger on one side than the corresponding size of the lower cuboid positioning part of the positioning base (24).

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