An airborne atmospheric temperature acquisition device

Abstract

This specification provides an airborne atmospheric temperature acquisition device, comprising: a deflector cover disposed along the flight direction of an atmospheric data acquisition pod; a first deflector hole and a second deflector hole, which are connected and disposed on the deflector cover, through which air flows into the interior of the deflector cover and out through the first and second deflector holes; and a temperature sensor disposed inside the deflector cover. By integrating the atmospheric temperature sensor into the pod of the airborne mission system, the environment of the acquisition area meets the requirements for atmospheric temperature acquisition, satisfying the requirements for atmospheric temperature acquisition and measurement of the airborne mission system of an artificial influence operation aircraft. It offers advantages such as no wind resistance, low power consumption, high integration, good overall performance, and high economy.

Description

Technical Field

[0001] This specification relates to the field of airborne equipment technology, specifically to an airborne atmospheric temperature acquisition device. Background Technology

[0002] Atmospheric temperature is a crucial parameter for airborne missions in weather modification operations, directly determining the timing and amount of catalyst dispersal. Currently, atmospheric temperature measurement for these missions primarily relies on atmospheric temperature sensors, typically mounted as separate components external to the aircraft or equipment. However, using independently mounted atmospheric temperature sensors in airborne weather modification mission systems presents three main problems: 1. The protruding temperature sensor, mounted as a separate component external to the equipment or aircraft skin, increases drag. 2. Such protruding sensors require anti-icing and de-icing designs, and the heaters used for these processes consume significant power, increasing the aircraft's power load. 3. If the airborne mission system receives atmospheric temperature data from the aircraft's flight control system, the interconnection between the two systems increases the complexity of the flight control system.

[0003] With the development of weather modification technology, the demand for integrated and highly integrated atmospheric parameter acquisition equipment for airborne mission systems is becoming increasingly prominent. Therefore, integrated and highly integrated atmospheric parameter acquisition systems have become a research direction. Atmospheric temperature, as one of the atmospheric parameters of airborne mission systems, should also have its various parameter acquisition devices integrated into the atmospheric parameter acquisition system, becoming part of the integrated atmospheric parameter acquisition system, thus meeting the requirements of integrated, independent, and highly integrated systems. Summary of the Invention

[0004] In view of this, embodiments of this specification provide an airborne atmospheric temperature acquisition device to achieve the purpose of accurately measuring atmospheric temperature using an integrated temperature acquisition device.

[0005] The embodiments in this specification provide the following technical solutions:

[0006] An airborne atmospheric temperature acquisition device, comprising:

[0007] A deflector is positioned in the direction of flight of the atmospheric data acquisition pod;

[0008] The first guide hole and the second guide hole are connected to each other on the guide cover. Air flows into the interior of the guide cover from the second guide hole and flows out from the first guide hole and the second guide hole.

[0009] Temperature sensor, which is located inside the flow guide cover.

[0010] Furthermore, the airborne atmospheric temperature acquisition device is fixed to the tail of the atmospheric data acquisition pod. The deflector is a hollow shell structure, which includes a cylindrical section and an ellipsoidal section. One end of the cylindrical section is fixedly connected to the body of the atmospheric data acquisition pod.

[0011] Multiple first guide holes are evenly arranged on the outer circumferential surface of the cylindrical section of the guide cover;

[0012] The second guide hole is located at the tail of the central axis of the ellipsoidal section.

[0013] Furthermore, the temperature sensor is positioned on the central axis of the housing structure of the flow guide cover, with the sensing element of the temperature sensor facing the airflow direction between the first flow guide hole and the second flow guide hole.

[0014] Furthermore, the minor axis diameter of the ellipsoidal segment is the same as the diameter of the atmospheric data acquisition pod, and the major axis length of the ellipsoidal segment is 1.9 to 2 times the minor axis diameter.

[0015] Furthermore, the cylindrical and ellipsoidal sections of the shell structure have the same thickness.

[0016] Furthermore, the diameter of the first guide hole is 2.8 mm to 3.0 mm.

[0017] Furthermore, the diameter of the second guide hole is 13.5 mm to 14.5 mm.

[0018] Furthermore, the airborne atmospheric temperature acquisition device also includes a fixing ring and a protective net, with the protective net fixed to the second guide hole by the fixing ring.

[0019] Furthermore, the airborne atmospheric temperature acquisition device also includes a sensor cover that surrounds the temperature sensor.

[0020] Furthermore, the temperature sensor is a thermistor.

[0021] Compared with the prior art, the beneficial effects that at least one technical solution adopted in the embodiments of this specification can achieve include at least:

[0022] The airborne atmospheric temperature acquisition device of this invention integrates an atmospheric temperature sensor into a pod within the airborne mission system. The environment of the acquisition area meets the requirements for atmospheric temperature acquisition, satisfying the requirements for atmospheric temperature acquisition and measurement in the airborne mission system of an artificial influence operation aircraft. As a parameter acquisition device within the airborne mission system, the built-in atmospheric temperature acquisition device's measurement method does not affect the overall flow field of the aircraft. Since there are no protrusions exposed to the air on the outer surface of the airborne atmospheric temperature acquisition device, no anti-icing or de-icing design is needed, reducing the overall power consumption of the airborne mission system. Independent acquisition, without interoperation with the aircraft's flight control system, reduces the possibility of malfunctions. Therefore, the airborne atmospheric temperature acquisition device of this embodiment has advantages such as zero wind resistance, low power consumption, high integration, good overall performance, and high economy. Attached Figure Description

[0023] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0024] Figure 1 This is a schematic diagram of the aerodynamic flow field according to an embodiment of the present invention;

[0025] Figure 2 yes Figure 1 A schematic diagram of the pneumatic principle of the internal cavity of part I;

[0026] Figure 3 This is a schematic diagram of the overall structure of the airborne atmospheric temperature acquisition device according to an embodiment of the present invention;

[0027] Figure 4 This is a pressure distribution cloud map calculated by simulation in an embodiment of the present invention.

[0028] Explanation of reference numerals in the attached drawings: 1. Cabin; 2. First flow guide hole; 3. Temperature sensor; 4. Sensor cover; 5. Flow guide cover; 6. Fixing ring; 7. Protective net; 8. Second flow guide hole; 9. Atmospheric data acquisition pod. Detailed Implementation

[0029] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0030] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0031] It should be noted that various aspects of embodiments within the scope of the appended claims are described below. It will be apparent that the aspects described herein can be embodied in a wide variety of forms, and any particular structure and / or function described herein is merely illustrative. Based on this application, those skilled in the art will understand that one aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number and aspects set forth herein can be used to implement the device and / or practice the method. Additionally, this device and / or method can be implemented using structures and / or functionalities other than one or more of the aspects set forth herein.

[0032] It should also be noted that the illustrations provided in the following embodiments are only schematic representations of the basic concept of this application. The drawings only show the components related to this application and are not drawn according to the actual number, shape and size of the components in the actual implementation. In the actual implementation, the form, quantity and proportion of each component can be arbitrarily changed, and the layout of the components may also be more complex.

[0033] Furthermore, specific details are provided in the following description to facilitate a thorough understanding of the examples. However, those skilled in the art will understand that the described aspects can be practiced without these specific details.

[0034] The original method of atmospheric temperature acquisition in the airborne mission system was innovated by either receiving data from the aircraft flight control system or placing an independent atmospheric temperature sensor on the surface of the equipment. By combining the structural characteristics of the atmospheric data acquisition pod in the airborne mission system of the artificial influence operation aircraft, the atmospheric temperature acquisition device is set at the tail of the atmospheric data acquisition pod.

[0035] The technical solutions provided by the various embodiments of this application are described below with reference to the accompanying drawings.

[0036] The atmospheric data acquisition pod 9 is the data acquisition and processing equipment of the airborne mission system of the weather modification operation aircraft. It is installed under the wing of the aircraft and has a cabin 1 on the outside.

[0037] like Figure 1 As shown in the airflow diagram, the main body of the atmospheric data acquisition pod 9 is cylindrical. After takeoff, airflow is generated outside the atmospheric data acquisition pod 9 from position 901 to position 902 (in the flight direction). According to aerodynamic characteristics, during flight, in the rear region of the atmospheric data acquisition pod 9, the surface pressure at position 903 is lower than that at position 904. The airflow passing through the rear region of the atmospheric data acquisition pod 9 will create a pressure difference between positions 903 and 904.

[0038] Figure 2 yes Figure 1 An enlarged schematic diagram of section I. Here, after the gas flows into the rear region, a stable flow field suitable for measuring atmospheric temperature is formed in region 905. Therefore, this pressure difference can be used to construct an internally hollow shell structure in the rear region, with inlet and outlet guide holes.

[0039] The measurement principle of this invention is to utilize the pressure difference formed on the surface of the atmospheric data acquisition pod 9 in the onboard mission system during flight. Through two guide holes, the gas in the inner cavity of the tail of the atmospheric data acquisition pod 9 exchanges with the external atmosphere, forming a flow field suitable for atmospheric temperature measurement in the inner cavity of the atmospheric data acquisition pod 9. The temperature sensor 3 is then built into this cavity to collect the atmospheric temperature.

[0040] The measurement principle of this invention is the same as that of the atmospheric total temperature sensor. When the airflow is completely still during the adiabatic process, its kinetic energy will be converted into internal energy and reflected. During actual flight, the airflow flows through the atmospheric data acquisition pod 9 at a speed of 50m / s to 150m / s. After undergoing an adiabatic process in the cavity of the flow guide cover 5, it becomes still, and its kinetic energy will be converted into internal energy. The position of the temperature sensor 3 is verified by simulation and experiment to be placed at a position where the airflow velocity is basically zero. The temperature measured at this position can be used to calculate the atmospheric temperature.

[0041] like Figure 2 and Figure 3As shown, a flow deflector 5 is located at the rear of the atmospheric data acquisition pod 9. A first flow deflector 2 is positioned at position 903, and a second flow deflector 8 is positioned at position 904. This allows airflow between the two locations with a pressure difference to occur through the first and second flow deflectors 2 and 8. An element for measuring atmospheric temperature is installed at position 905 to achieve temperature testing. Airflow enters through the second flow deflector 8 and exits through the first and second flow deflectors 2 and 8. Based on the aircraft's flight speed (100 m / s), a flow field with a velocity below 1 m / s is formed within the cavity of the tail flow deflector 5. Real-time air exchange occurs between the inside and outside of the flow deflector 5, and this airflow environment meets the conditions for atmospheric temperature acquisition.

[0042] like Figure 3 As shown, the airborne atmospheric temperature acquisition device of this embodiment includes: a first guide hole 2, a temperature sensor 3, a sensor cover 4, a guide cover 5, a fixed protective net 7, and a second guide hole 8.

[0043] according to Figure 1 and Figure 2 Airflow field diagram and such Figure 3 The diagram shows the structure of the airborne atmospheric temperature acquisition device. Due to the pressure difference between positions 903 and 904, the air deflector 5, the first air deflector 2, and the second air deflector 8 are all located between positions 903 and 904. Simultaneously, due to the pressure difference between positions 903 and 904, airflow enters through the second air deflector 8 and exits through the first air deflector 2, resulting in air exchange between the inside and outside of the air deflector 5. The temperature sensor 3 is integrated into the airflow within the air deflector 5 and measures the atmospheric temperature during flight.

[0044] The flow guide cover 5, connected to the cabin body 1 of the atmospheric data acquisition pod 9, is a hollow shell-like structure. The shell includes a cylindrical section and an ellipsoidal section, with one end of the cylindrical section fixedly connected to the cabin body 1. Both the inner and outer surfaces of the ellipsoidal section are ellipsoidal surfaces formed by elliptical curves around an axis. The first flow guide hole 2 consists of multiple radially distributed annular through holes on the cylindrical surface of the tail section of the flow guide cover 5, each with a diameter ranging from Φ2.8mm to Φ3.0mm. The second flow guide hole 8, located at position 904, is an axial through hole on the axial end face of the tail section of the ellipsoidal section of the flow guide cover 5, with a through hole size ranging from Φ13.5mm to Φ14.5mm.

[0045] The minor axis diameter of the ellipsoidal section is consistent with the diameter of the cylindrical surface of the pod (Φ80mm~Φ82mm), while the major axis is approximately 1.9 to 2 times the minor axis diameter (major axis size is 150mm~152mm). The ratio of the major and minor axes of the deflector 5 and the size and number of deflector holes were optimized based on experience from previous similar products through simulation calculations and experimental results. Flight verification has shown that the design is feasible and largely consistent with the design expectations.

[0046] The inner and outer surfaces of the flow deflector 5 have uniform wall thickness, and the smooth surface of the inner cavity facilitates smooth airflow. The uniform wall thickness maintains structural strength while controlling weight. The outer wall of the flow deflector 5 has no protruding structures from the main body of the equipment, thus eliminating additional flight drag. Furthermore, the outer wall of the flow deflector 5 has no stagnation points, meaning there are no protrusions on its outer surface, eliminating the need for a separate heating module for anti-icing and de-icing.

[0047] Inside the second guide hole 8, there is a fixing ring 6 and a protective net 7. The protective net 7 is fixed to the second guide hole 8 by the fixing ring 6. The protective net 7 can prevent large particles of sand and gravel and other foreign objects from entering the guide cover 5.

[0048] Temperature sensor 3 is positioned in region 905, where a stable flow field suitable for measuring atmospheric temperature is formed. One end of temperature sensor 3 is fixed to one side of the cabin 1, and the other end of temperature sensor 3 is equipped with a sensing element, which faces the airflow direction between the first guide hole 2 and the second guide hole 8. A sensor cover 4 is provided on the outside of temperature sensor 3 to protect temperature sensor 3 from rainwater and other contaminants.

[0049] Temperature sensor 3 uses a thermistor as the temperature sensing element, and outputs a digital signal after signal processing. Thermistors have high sensitivity, with a temperature coefficient of resistance 10 to 100 times greater than that of metals, and can detect temperature changes of 10⁻⁶℃. They also have a wide operating temperature range, with room-temperature devices suitable for -55℃ to 315℃. The thermistor alloy temperature sensor 3 is placed in a stable environment and is widely used in high-performance aircraft atmospheric temperature sensors and large passenger aircraft temperature sensors.

[0050] like Figure 4 As shown, P is the pressure unit Pascal, and the values ​​are only pressure values, not component markings. Based on the assumed aircraft speed (100 m / s), calculations show that the pressure difference between position 903 (where the first guide hole 2 is located) and position 904 (where the second guide hole 8 is located) is approximately 400 Pa to 500 Pa. Under this pressure, air exchange occurs between the inside and outside of the guide cover 5.

[0051] pass Figure 4 The simulation calculations show that external air flows in from the second guide hole 8, flows out from the first guide hole 2 and the second guide hole 8 through the guide cover 5, and forms a stable flow field suitable for measuring atmospheric temperature in region 905 inside the cavity of the guide cover 5. The temperature sensor 3 is placed in this region to collect atmospheric temperature parameters and provide them to the airborne mission system.

[0052] The airborne atmospheric temperature acquisition device of this invention is an embedded atmospheric temperature measurement device applied to the airborne mission system of an aircraft used for weather modification operations. Employing embedded airborne atmospheric temperature measurement technology eliminates the need for an additional anti-icing and heating module, significantly reducing equipment power consumption while meeting measurement requirements. Utilizing the pressure difference formed on the surface of the pod within the onboard mission system during aircraft flight, the gas in the pod's tail cavity exchanges with the external atmosphere through two guide holes, creating a flow field suitable for atmospheric temperature measurement within the pod cavity. A temperature sensor is then embedded within this cavity to collect atmospheric temperature data. The inner and outer surface structures of the pod's tail section guide cover, along with the size and placement of the two guide holes, ensure effective utilization of the pressure difference formed on the surface of the pod's tail section guide cover during aircraft flight.

[0053] The various embodiments in this specification are described in a progressive manner. Similar or identical parts between embodiments can be referred to interchangeably. Each embodiment focuses on describing the differences from other embodiments. In particular, the method embodiments described later are relatively simple in description because they correspond to the system; relevant parts can be referred to the descriptions in the system embodiments.

[0054] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. An airborne atmospheric temperature acquisition device, characterized in that, include: A flow deflector (5) is positioned in the same direction as the atmospheric data acquisition pod (9); The first guide hole (2) and the second guide hole (8) are connected to the guide cover (5). Air flows into the interior of the guide cover (5) from the second guide hole (8) and flows out from the first guide hole (2) and the second guide hole (8). Temperature sensor (3) is installed inside the flow guide cover (5); The airborne atmospheric temperature acquisition device is fixed to one side of the cabin (1) of the atmospheric data acquisition pod (9). The guide cover (5) is a hollow shell structure. The shell structure includes a cylindrical section and an ellipsoidal section. One end of the cylindrical section is fixedly connected to the cabin (1) of the atmospheric data acquisition pod (9). Multiple first guide holes (2) are evenly arranged on the outer circumferential surface of the cylindrical section of the guide cover (5); The second guide hole (8) is located at the tail of the central axis of the ellipsoidal section; The temperature sensor (3) is located on the central axis of the housing structure of the flow guide cover (5), and the sensing element of the temperature sensor (3) is oriented towards the airflow direction between the first flow guide hole (2) and the second flow guide hole (8). The diameter of the first guide hole (2) is 2.8 mm to 3.0 mm; The diameter of the second guide hole (8) is 13.5 mm to 14.5 mm.

2. The airborne atmospheric temperature acquisition device according to claim 1, characterized in that, The minor axis diameter of the ellipsoidal segment is the same as the diameter of the atmospheric data acquisition pod (9), and the major axis length of the ellipsoidal segment is 1.9 to 2 times the minor axis diameter.

3. The airborne atmospheric temperature acquisition device according to claim 1, characterized in that, The cylindrical and ellipsoidal sections of the shell structure have the same thickness.

4. The airborne atmospheric temperature acquisition device according to claim 1, characterized in that, The airborne atmospheric temperature acquisition device also includes a fixing ring (6) and a protective net (7), with the protective net (7) fixed on the second guide hole (8) by the fixing ring (6).

5. The airborne atmospheric temperature acquisition device according to claim 1, characterized in that, The airborne atmospheric temperature acquisition device also includes a sensor cover (4), which is wrapped around the temperature sensor (3).

6. The airborne atmospheric temperature acquisition device according to claim 1, characterized in that, The temperature sensor (3) is a thermistor.

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