Pressure guiding device for embedded atmosphere data sensing system and use method of pressure guiding device

Abstract

The invention relates to the technical field of embedded atmosphere data sensing of aircrafts, in particular to a pressure guiding device for an embedded atmosphere data sensing system and a using method of the pressure guiding device. One end of the pressure guiding pipeline is communicated with the heat sink unit, and the other end of the pressure guiding pipeline is connected with a pressure sensor; the heat sink unit is mounted at a pressure guide hole of the aircraft heat-proof structure; the heat sink unit is internally provided with a leakproof assembly, the leakproof assembly comprises a phase-change material, when the temperature is too high due to leakage, the phase-change material is converted into liquid from solid to block the heat sink unit, and external high-temperature airflow is prevented from entering the heat-proof structure. The anti-leakage assembly is arranged in the heat sink unit, the anti-leakage assembly comprises the phase change material, when the temperature is too high due to pipeline leakage, the phase change material is converted into liquid from solid to block the heat sink unit, and external high-temperature airflow is prevented from entering the heat-proof structure; and the measurement precision and reliability of the FADS system in the hypersonic flight vehicle are ensured.

Description

Technical Field

[0001] This invention relates to the field of measurement technology for embedded atmospheric data sensing systems for aircraft, and in particular to a pressure-inducing device for embedded atmospheric data sensing systems and its usage method, mainly used for measuring flight atmospheric parameters under high-temperature ablation conditions in the return capsule. Background Technology

[0002] The Flush Air Data Sensing (FADS) system uses an array of pressure sensors to measure the pressure distribution on the surface of an aircraft and indirectly obtains atmospheric data such as static pressure, Mach number, angle of attack, and sideslip angle through specific algorithms. The FADS system is the primary means for aircraft to acquire atmospheric data as input for flight control, and it is particularly important for hypersonic aircraft, as its reliability directly affects flight safety and control accuracy.

[0003] During hypersonic flight, the surface of a hypersonic vehicle generates extreme temperatures of 500-600°C due to aerodynamic friction, placing stringent requirements on the pressure tapping lines of the FADS system. Existing pressure tapping line connections are simple and often fail to balance high-temperature resistance with pressure transmission stability, making them prone to leakage in high-temperature environments. This results in potential problems such as insufficient measurement accuracy and poor reliability of the FADS system in hypersonic vehicles.

[0004] Therefore, in order to address the shortcomings of existing technologies, designing a high-temperature pressure-sensing pipeline that can adapt to the high-temperature operating conditions of hypersonic vehicles and ensure the accuracy of pressure measurement has become a key requirement for the current development of FADS system technology. Summary of the Invention

[0005] The purpose of this invention is to provide a pressure tapping device and its usage method for an embedded atmospheric data sensing system, which can avoid leakage problems caused by pressure tapping pipeline under high temperature conditions, ensure the accuracy of pressure signal transmission under high temperature environment, and improve the reliability of embedded atmospheric data sensing system.

[0006] This invention provides a pressure-sensing device for an embedded atmospheric data sensing system, comprising a pressure-sensing pipeline, one end of which is connected to a heat sink unit and the other end to a pressure sensor; the heat sink unit is installed at a pressure-sensing port on the heat shield structure of an aircraft, the pressure-sensing port being perpendicular to the surface of the heat shield structure; the heat sink unit is equipped with an anti-leakage component, which includes a phase change material. When a leak occurs and the temperature becomes too high, the phase change material changes from solid to liquid, blocking the heat sink unit and preventing external high-temperature airflow from entering the interior of the heat shield structure.

[0007] Furthermore, the heat sink unit includes a fixing block, one end of which is connected to the pressure-feeding pipeline, and the other end of which is provided with a connecting pipe, which is connected to the pressure-feeding pipeline; a sealing plate is provided at the end of the connecting pipe away from the fixing block, and honeycomb holes are provided through the sealing plate; the anti-leakage component is provided inside the connecting pipe; the fixing block, the connecting pipe and the sealing plate are integrally formed.

[0008] Furthermore, the leak-proof component includes the phase change material, and porous materials are respectively provided on both sides of the phase change material. When the internal temperature of the connecting pipe exceeds the phase change temperature of the phase change material, the phase change material melts into a liquid state and flows into the pores of the porous materials on both sides, filling and accumulating in the pores of the porous materials to form a sealing layer, thereby blocking the connecting pipe.

[0009] Furthermore, the phase change material is a tin block, the porous material is copper foam, there is a gap between the tin block and the inner wall of the connecting pipe, and the copper foam is fixedly connected to the inside of the connecting pipe.

[0010] Furthermore, the pressure sensor includes a medium-pressure sensor and an atmospheric pressure sensor; the medium-pressure sensor has a range of 0-15 kPa and an accuracy class of 0.1%FS; the atmospheric pressure sensor has a range of 0-100 kPa and an accuracy class of 0.1%FS.

[0011] Furthermore, the pressure-sensing pipeline includes a main connecting pipe, one end of which is connected to the heat sink unit, and the other end of which is connected to the inlet of a three-way valve. The two outlets of the three-way valve are respectively connected to a first branch pipe and a second branch pipe. The first branch pipe is connected to the medium-pressure sensor, and the second branch pipe is connected to the atmospheric pressure sensor.

[0012] Furthermore, the heat sink unit is connected to the heat-resistant structure by screws.

[0013] Furthermore, the heat sink unit and the heat-resistant structure are sealed with heat-resistant putty; the heat sink unit, the connecting main pipe, the first branch pipe and the second branch pipe are all made of 304 stainless steel.

[0014] Furthermore, the diameter of the pressure-guiding hole is 3-5 mm, and the diameter of the honeycomb hole on the sealing plate is 0.5 mm.

[0015] This invention provides a method of using the above-mentioned pressure-applying device, comprising the following steps: S1. Open pressure tapping holes at the measuring points of the heat protection structure of the aircraft to be tested, and install the heat sink unit at the pressure tapping holes; S2. Take a stainless steel pipe, apply high-temperature resistant adhesive to the outer wall of the stainless steel pipe, and insert it into the pressure hole from the bottom of the heat-proof structure until it is connected to the heat sink unit. S3. When the high-temperature resistant adhesive is in a semi-cured state, perform the first airtightness measurement to ensure that the leakage rate is ≤10Pa / s; S4. After the first air tightness measurement is completed, rotate the stainless steel pipe and pull it out of the pressure hole. After the high temperature resistant adhesive has completely cured, perform the air tightness measurement again to ensure that the leakage rate is ≤10Pa / s. S5. Finally, pneumatic pressure detection is performed. The pressure of the flow field at the measuring point is transmitted to the inside of the pressure sensor through the heat sink unit and pressure tapping pipeline. The pressure sensor converts the pressure into a standard voltage signal for the system to collect.

[0016] Furthermore, the high-temperature resistant adhesive is made of phenolic resin adhesive.

[0017] In summary, compared with the prior art, the present invention has the following advantages: The technical solution provided by this invention sets a pressure-inducing hole perpendicular to the surface of the pressure measuring point at the pressure measuring point of the aircraft's heat protection structure. The pressure of the flow field at the measuring point is introduced into the pressure-inducing pipeline through the heat sink unit and transmitted to the pressure sensor. After being converted by the pressure sensor, the output is a standard voltage signal for the system to collect. The system has a simple structure, high reliability, and low cost.

[0018] The pressure-reducing device provided by the present invention sets up an anti-leakage component inside the heat sink unit. The anti-leakage component includes a phase change material. When the temperature is too high due to a leak in the pipeline, the phase change material changes from solid to liquid, blocking the heat sink unit and preventing the external high-temperature airflow from entering the heat protection structure. It can also prevent the pressure sensor from being damaged by high temperature, thus ensuring the measurement accuracy and reliability of the FADS system in hypersonic vehicles.

[0019] The pressure-reducing device provided by this invention is suitable for measuring Mach number in the range of 1.5-25, static pressure altitude in the range of 10-85km, and angle of attack and sideslip angle in the range of -5° to 25°. It can meet most hypersonic flight speed ranges and has high measurement accuracy in both low and high Mach number ranges. Attached Figure Description

[0020] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0021] Figure 1This is a front view of the pressure-applying device in an embodiment of the present invention; Figure 2 This is a top view of the pressure-applying device in an embodiment of the present invention; Figure 3 This is a three-dimensional structural diagram of the pressure-applying device in an embodiment of the present invention; Figure 4 This is a cross-sectional view of the pressure-applying device in an embodiment of the present invention; Figure 5 This is a schematic diagram of the heat sink unit in an embodiment of the present invention; Figure 6 This is a schematic diagram of the installation of the pressure-applying device in an embodiment of the present invention.

[0022] Explanation of reference numerals in the attached drawings: 1-Heat sink unit; 101-Fixing block; 1011-First threaded hole; 102-Connecting pipe; 103-Sealing plate; 1031-Honeycomb hole; 104-Tin block; 105-Foamed copper; 2-Connecting main pipe; 3-First branch pipe; 301-First pipe joint; 302-First fastening nut; 4-Second branch pipe; 401-Second pipe joint; 402-Second fastening nut; 5-Three-way valve; 6-Medium pressure sensor; 7-Normal pressure sensor; 8-Heatproof structure; 801-Outer heatproof layer; 802-Inner composite material layer; 803-Pressure tapping hole. Detailed Implementation

[0023] The technical solution of the present invention will be clearly and completely described below with reference to the embodiments. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. 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.

[0024] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting this invention.

[0025] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the stated features. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified. Furthermore, the terms "installed," "connected," and "linked" should be interpreted broadly; for example, they may refer to a fixed connection, a detachable connection, or an integral connection; they may refer to a mechanical connection or an electrical connection; they may refer to a direct connection or an indirect connection through an intermediate medium; and they may refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0026] Example A pressure-sensing device for an embedded atmospheric data sensing system, such as Figures 1-4 As shown, it includes heat sink unit 1, pressure tapping pipeline, and pressure sensor, the details of which are as follows: Heat sink unit 1 is used to connect the pressure vents and pressure pipes of the aircraft's heat shield structure, and to cool any high-temperature gases that may enter. For example... Figure 4 ( Figure 4 (The structure of the honeycomb pore 1031 is not shown in the figure) and Figure 5 As shown, the device includes a fixing block 101, one end of which is connected to a pressure-feeding pipeline, and a connecting pipe 102 fixed to the other end of the fixing block 101, which is also connected to the pressure-feeding pipeline. A sealing plate 103 is provided at the end of the connecting pipe 102 away from the fixing block 101, and honeycomb holes 1031 with a diameter of 0.5 mm are provided through the sealing plate 103. The fixing block 101, connecting pipe 102, and sealing plate 103 are integrally formed and made of 304 stainless steel.

[0027] A leak-proof component is installed inside the connecting pipe 102. This component includes a phase change material, with porous material on both sides. In this embodiment, the phase change material is a tin block 104, and the porous material is copper foam 105. Both the tin block 104 and the copper foam 105 are cylindrical. The outer peripheral wall of the copper foam 105 is tightly fitted and fixed to the inner wall of the connecting pipe 102. A gap exists between the tin block 104 and the inner wall of the connecting pipe 102 to facilitate gas passage. When the internal temperature of the connecting pipe 102 exceeds the phase change temperature of the tin block 104 (232°C), the tin block 104 melts into a liquid state and flows into the pores of the copper foam 105 on both sides. The liquid tin fills and accumulates in the pores of the copper foam 105, forming a tight-fitting sealing layer, thereby blocking the connecting pipe 102 and preventing external high-temperature gas from entering the heat-resistant structure. This also prevents high-temperature gas from entering the pressure sensor. Simultaneously, the tin block 104 absorbs heat from the surrounding environment during the phase change process, which can also cool some of the high-temperature gas that enters the heat-resistant structure.

[0028] The pressure sensors include a medium-pressure sensor 6 and an atmospheric pressure sensor 7; the medium-pressure sensor 6 has a range of 0-15 kPa and an accuracy class of 0.1%FS; the atmospheric pressure sensor 7 has a range of 0-100 kPa and an accuracy class of 0.1%FS.

[0029] like Figure 1 , Figure 2 and Figure 3 As shown, the pressure-sensing pipeline includes a main connecting pipe 2, a first branch pipe 3, and a second branch pipe 4. One end of the main connecting pipe 2 is fixedly connected to the fixing block 101 of the heat sink unit 1. The centerline of the main connecting pipe 2 is perpendicularly aligned with the centerline of the sealing plate 103 and the centerline of the pressure-sensing hole. The other end of the main connecting pipe 2 is connected to the inlet of a three-way valve 5. The two outlets of the three-way valve 5 are respectively connected to the first branch pipe 3 and the second branch pipe 4. The end of the first branch pipe 3 away from the three-way valve 5 is provided with a first pipe connector 301, and a first fastening nut 302 is fitted on the outside of the first pipe connector 301. The first pipe connector 301 is connected to the medium-pressure sensor 6. The end of the second branch pipe 4 away from the three-way valve 5 is provided with a second pipe connector 401, and a second fastening nut 402 is fitted on the outside of the second pipe connector 401. The second pipe connector 401 is connected to the atmospheric pressure sensor 7. The main connecting pipe 2, the first branch pipe 3, and the second branch pipe 4 are all made of 304 stainless steel. The mass of a single-point pressure tapping line is approximately 90g, and the total mass including the pressure sensor is no more than 220g.

[0030] The shape of the connecting main pipe 2 is an inverted L-shape, with a bend angle of 92°.

[0031] like Figure 6As shown, the heat shield structure 8 of the aircraft consists of an outer heat shield layer 801 and an inner composite material layer 802. A pressure-injecting hole 803 penetrates both the outer heat shield layer 801 and the inner composite material layer 802, and the diameter of the pressure-injecting hole 803 is 3-5 mm. The outer heat shield layer 801 is made of carbon fiber composite heat shield material, which has poor sealing performance and a surface temperature that can reach 2500℃, causing partial ablation. The inner composite material layer 802 has better sealing performance and can be machined with threaded holes for installation and fixation. Four first threaded holes 1011 are provided through the edge of the fixing block 101, and these four first threaded holes 1011 are evenly distributed around the connecting pipe 102. The heat shield structure 8 has four second threaded holes corresponding to the first threaded holes 1011, which penetrate from the outer heat shield layer 801 to the interior of the inner composite material layer 802, and the length of the second threaded holes is 10 mm. Both the first threaded hole 1011 and the second threaded hole are M4 threaded holes. The first threaded hole 1011 and the second threaded hole are connected by a screw, which is an M4×10mm stainless steel screw. At the same time, the heat sink unit 1 and the heat protection structure 8 are sealed with heat-resistant putty.

[0032] When installing the heat sink unit 1, it is also necessary to provide an installation hole on the outer heat insulation layer 801 of the heat insulation structure 8 that communicates with the pressure hole 803 for fixing the installation connecting pipe 102.

[0033] The specific steps of the method using the aforementioned pressure-applying device are as follows: S1. A pressure-applying hole 803 with a diameter of 3-5mm is opened at the measuring point of the heat protection structure 8 of the aircraft to be tested, and a mounting hole communicating with the pressure-applying hole 803 is opened on the outer heat protection layer 801. The connecting pipe 102 of the heat sink unit 1 is fixed in the mounting hole, and the fixing block 101 is fixed to the heat protection structure 8 with screws (e.g., Figure 6 (as shown), and sealed with heat-resistant putty; S2. Take a stainless steel pipe (outer diameter 2-4mm, inner diameter 1mm), apply high-temperature resistant adhesive to the outer wall of the stainless steel pipe, the high-temperature resistant adhesive is phenolic resin adhesive, insert it into the pressure hole 803 from the bottom of the heat protection structure 8 until it is connected to the honeycomb hole 1031 of the heat sink unit 1. After 30 minutes, the high-temperature resistant adhesive is in a semi-cured state. The first airtightness measurement is then performed to ensure that the leakage rate is ≤10Pa / s. S4. After the first air tightness measurement, rotate the stainless steel pipe at a speed of 2 rpm / s and pull the stainless steel pipe out of the pressure hole 803. Wait 12 hours for the high temperature resistant adhesive to fully cure, and then perform the air tightness measurement again to ensure that the leakage rate is ≤10Pa / s. S5. Finally, pneumatic pressure is tested according to conventional testing requirements in this field. The pressure of the flow field at the measuring point is transmitted to the inside of the pressure sensor through the heat sink unit 1 and the pressure tapping pipeline. The pressure sensor converts the pressure into a standard voltage signal for the system to collect.

[0034] The pressure-applying device provided by this invention has the following advantages: I. The pressure-sensing device for an embedded atmospheric data sensing system provided by this invention is mainly designed for measuring flight atmospheric parameters under the high-temperature ablation environment of the return capsule needle. The anti-leakage component installed inside the heat sink unit can block the pipeline when the temperature becomes too high due to a leak in the pipeline, preventing the external high-temperature airflow from entering the heat protection structure. At the same time, the phase change material absorbs heat from the surrounding environment during the phase change process, which can also cool down some of the high-temperature gas that has entered the heat protection structure. It has unique anti-blocking and high-temperature resistance effects. The entire device has a simple structure, high reliability, and low cost.

[0035] Second, the pressure-reducing device provided by this invention measures Mach numbers in the range of 1.5-25, which can meet most hypersonic flight speed ranges. The angle of attack and sideslip angle measurement ranges are both -5° to 25°, and it has high measurement accuracy in both low and high Mach number ranges.

[0036] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A pressure-applying device for an embedded atmospheric data sensing system, characterized in that, The system includes a pressure-sensing pipeline, one end of which is connected to a heat sink unit and the other end to a pressure sensor. The heat sink unit is installed at the pressure-sensing port of the aircraft's heat shield structure, and the pressure-sensing port is perpendicular to the surface of the heat shield structure. The heat sink unit is equipped with an anti-leakage component, which includes a phase change material. When a leak causes the temperature to become too high, the phase change material changes from solid to liquid, blocking the heat sink unit and preventing external high-temperature airflow from entering the interior of the heat shield structure.

2. The pressure-applying device according to claim 1, characterized in that, The heat sink unit includes a fixing block, one end of which is connected to the pressure-feeding pipeline, and the other end of which is provided with a connecting pipe, which is connected to the pressure-feeding pipeline; a sealing plate is provided at the end of the connecting pipe away from the fixing block, and honeycomb holes are provided through the sealing plate; the anti-leakage component is provided inside the connecting pipe; the fixing block, the connecting pipe and the sealing plate are integrally formed.

3. The pressure-applying device according to claim 2, characterized in that, The leak-proof component includes the phase change material, and porous materials are respectively provided on both sides of the phase change material. When the internal temperature of the connecting pipe exceeds the phase change temperature of the phase change material, the phase change material melts into a liquid state and flows into the pores of the porous materials on both sides, filling and accumulating in the pores of the porous materials to form a tight sealing layer, thereby blocking the connecting pipe.

4. The pressure-applying device according to claim 3, characterized in that, The phase change material is a tin block, the porous material is copper foam, there is a gap between the tin block and the inner wall of the connecting pipe, and the copper foam is fixedly connected to the inside of the connecting pipe.

5. The pressure-applying device according to claim 1, characterized in that, The pressure sensor includes a medium-pressure sensor and an atmospheric pressure sensor; the medium-pressure sensor has a range of 0-15 kPa and an accuracy class of 0.1%FS; the atmospheric pressure sensor has a range of 0-100 kPa and an accuracy class of 0.1%FS.

6. The pressure-applying device according to claim 5, characterized in that, The pressure-sensing pipeline includes a main connecting pipe, one end of which is connected to the heat sink unit, and the other end of which is connected to the inlet of a three-way valve. The two outlets of the three-way valve are respectively connected to a first branch pipe and a second branch pipe. The first branch pipe is connected to the medium-pressure sensor, and the second branch pipe is connected to the atmospheric pressure sensor.

7. The pressure-applying device according to claim 6, characterized in that, The heat sink unit is connected to the heat-resistant structure by screws.

8. The pressure-applying device according to claim 7, characterized in that, The heat sink unit and the heat protection structure are sealed with heat-resistant putty; the heat sink unit, the connecting main pipe, the first branch pipe and the second branch pipe are all made of 304 stainless steel.

9. The pressure-applying device according to claim 2, characterized in that, The diameter of the pressure-guiding hole is 3-5 mm, and the diameter of the honeycomb hole on the sealing plate is 0.5 mm.

10. A method of using the pressure-applying device according to any one of claims 1-9, characterized in that, Includes the following steps: S1. Open pressure tapping holes at the measuring points of the heat protection structure of the aircraft to be tested, and install the heat sink unit at the pressure tapping holes; S2. Take a stainless steel pipe, apply high-temperature resistant adhesive to the outer wall of the stainless steel pipe, and insert it into the pressure hole from the bottom of the heat-proof structure until it is connected to the heat sink unit. S3. When the high-temperature resistant adhesive is in a semi-cured state, perform the first airtightness measurement to ensure that the leakage rate is ≤10Pa / s; S4. After the first air tightness measurement is completed, rotate the stainless steel pipe and pull it out of the pressure hole. After the high temperature resistant adhesive has completely cured, perform the air tightness measurement again to ensure that the leakage rate is ≤10Pa / s. S5. Finally, pneumatic pressure detection is performed. The pressure of the flow field at the measuring point is transmitted to the inside of the pressure sensor through the heat sink unit and pressure tapping pipeline. The pressure sensor converts the pressure into a standard voltage signal for the system to collect.

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