Airship internal temperature acquisition device and airship

Abstract

The application relates to the technical field of aerostat, and provides an aerostat internal temperature acquisition device and an aerostat. The aerostat internal temperature acquisition device comprises a temperature acquisition and storage module, a cable releasing unit and temperature sensors. The temperature acquisition and storage module and the cable releasing unit are arranged in a ball of the aerostat, the temperature acquisition and storage module is arranged at the top end of the ball, and the cable releasing unit is arranged at the bottom end of the ball. The cable releasing unit comprises a shell, a winding drum and a cable, the winding drum is rotatably arranged in the shell, one end of the cable is wound on the winding drum, and the other end is connected with the top end of the ball. A plurality of temperature sensors are sequentially and spacedly arranged along the extension direction of the cable, and the signal lead lines of the temperature sensors are connected with the temperature acquisition and storage module. According to the shape change of the ball, the plurality of temperature sensors can be adaptively distributed at different positions in the ball, so that the temperature at different positions in the ball can be conveniently acquired.

Description

Technical Field

[0001] This invention relates to the field of airship technology, and in particular to an internal temperature acquisition device for an airship and an airship. Background Technology

[0002] An aerostat is a lighter-than-air aircraft that relies on atmospheric buoyancy to ascend. It can remain in the stratosphere for extended periods, enabling it to perform various observation missions within the stratosphere. During its ascent to the stratosphere, the aerostat traverses a complex troposphere, where the surrounding environment and atmospheric parameters change with altitude, affecting its kinematic and thermal characteristics.

[0003] However, most existing airships can only detect their altitude and speed during ascent, making it difficult to collect temperature data at different locations inside the airship during ascent, which directly affects the study of the airship's state during ascent. Summary of the Invention

[0004] This invention provides an internal temperature acquisition device and an airship to solve the problem that it is difficult to acquire the temperature at different locations inside the airship during the airship's ascent.

[0005] In a first aspect, the present invention provides an internal temperature acquisition device for an airship, comprising: a temperature acquisition and storage module, a cable deployment unit, and a temperature sensor;

[0006] Both the temperature acquisition and storage module and the cable-laying unit are installed inside the sphere of the airship. The temperature acquisition and storage module is located at the top of the sphere, and the cable-laying unit is located at the bottom of the sphere.

[0007] The cable-laying unit includes a housing, a drum, and a cable. The drum is rotatably mounted on the housing. One end of the cable is wound around the drum, and the other end is connected to the top of the sphere.

[0008] The temperature sensor is provided in multiple ways, and the multiple temperature sensors are arranged at intervals along the extension direction of the cable. The signal lead of each temperature sensor is connected to the temperature acquisition and storage module.

[0009] According to the present invention, an airship internal temperature acquisition device, the cable-laying unit further includes a brake shaft, a linkage arm, and a guide assembly;

[0010] The drum is sleeved on the peripheral wall of the brake shaft. The brake shaft includes a fixed brake shaft, a floating brake shaft, and an elastic support member. The fixed brake shaft and the floating brake shaft are arranged side by side. The elastic support member is disposed between the fixed brake shaft and the floating brake shaft. The fixed brake shaft is fixedly connected to the housing. Frictional contact is formed between the peripheral wall of the fixed brake shaft and the inner wall of the drum and / or between the peripheral wall of the floating brake shaft and the inner wall of the drum.

[0011] The guiding assembly includes a fixed guide shaft and a floating guide shaft, which are arranged side by side. The fixed guide shaft is connected to the housing. One end of the linkage arm is rotatably connected to the fixed guide shaft, and the other end is fixedly connected to the floating shaft. The floating guide shaft is rotatably mounted on the linkage arm.

[0012] The cable on the drum first passes around the floating guide shaft, then through the gap between the fixed guide shaft and the floating guide shaft, then passes around the fixed guide shaft, and finally connects to the top of the sphere.

[0013] According to the present invention, an internal temperature acquisition device for an airship is provided, wherein the fixed brake shaft has a first plane and a first arc-shaped friction surface, and the floating brake shaft has a second plane and a second arc-shaped friction surface;

[0014] The first plane and the second plane are parallel, and the elastic support is disposed between the first plane and the second plane;

[0015] Both the first arc-shaped friction surface and the second arc-shaped friction surface are in contact with the inner wall of the drum.

[0016] According to the present invention, an internal temperature acquisition device for an airship is provided, wherein multiple elastic support members are provided, and the multiple elastic support members are arranged sequentially at intervals along the extension direction of the fixed brake shaft or the floating brake shaft.

[0017] According to the present invention, an airship internal temperature acquisition device is provided, wherein there are two linkage arms, which are spaced apart, and the drum, the brake shaft and the guide assembly are disposed between the two linkage arms.

[0018] According to the present invention, an internal temperature acquisition device for an airship is provided, wherein the housing has a receiving cavity and a guide port communicating with the receiving cavity;

[0019] The drum, the brake shaft, the linkage arm, and the guide assembly are respectively disposed in the receiving cavity. After passing through the guide assembly, the cable is led out from the guide port and then connected to the top of the sphere.

[0020] According to the present invention, an internal temperature acquisition device for an airship further includes: a thermal insulation chamber; the thermal insulation chamber is located at the top of the sphere, the thermal insulation chamber includes an inner chamber and a thermal insulation shell, the thermal insulation shell covers the outside of the inner chamber, and the temperature acquisition and storage module is located in the inner chamber.

[0021] According to the present invention, an internal temperature acquisition device for an airship is provided, wherein the cable is further provided with multiple light shields;

[0022] Multiple light shields and multiple temperature sensors are arranged opposite to each other, with the temperature sensors housed within the light shields.

[0023] In a second aspect, the present invention also provides an airship, including a sphere and an internal temperature acquisition device for the airship as described above.

[0024] An airship provided by the present invention further includes: a pod;

[0025] The pod is located at the bottom of the sphere and is equipped with an environmental data acquisition module, a solar irradiance meter, a long-wave infrared radiation meter, a flight status recording module, and a data processing and storage module.

[0026] The environmental data acquisition module, the solar irradiance meter, the long-wave infrared radiation meter, and the flight status recording module are respectively connected to the data processing and storage module.

[0027] The present invention provides an internal temperature acquisition device for an airship and an airship. By arranging temperature acquisition and storage modules and a cable-laying unit arranged vertically within the sphere of the airship, and connecting the cable of the cable-laying unit to the top of the sphere, the airship can utilize the characteristic of the sphere continuously expanding due to the increasing internal and external pressure difference during its ascent. The sphere drives the cable on the drum to continuously unwind, and the unwinding cable then unfolds and sets up each temperature sensor attached to it one by one along the height direction of the sphere. This achieves adaptive distribution of multiple temperature sensors at different positions within the sphere according to the shape changes of the sphere, facilitating the acquisition of temperature at different locations within the sphere and thus achieving better temperature measurement. Attached Figure Description

[0028] To more clearly illustrate the technical solutions in this invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0029] Figure 1 This is a schematic diagram of the structure of the airship provided by the present invention;

[0030] Figure 2 This is one of the schematic diagrams of the internal temperature acquisition device of the airship provided by the present invention;

[0031] Figure 3 This is the second schematic diagram of the airship internal temperature acquisition device provided by the present invention;

[0032] Figure 4 This is a comparative schematic diagram showing the shape changes of the sphere during the ascent of the airship, provided by the present invention.

[0033] Figure 5 This is a schematic diagram of the cable-laying unit provided by the present invention;

[0034] Figure 6 This is a schematic diagram of the assembly structure of the drum, brake shaft, linkage arm and guide assembly in the cable laying unit provided by the present invention;

[0035] Figure 7 This invention provides Figure 6 A schematic diagram of the side view structure;

[0036] Figure 8 This invention provides Figure 7 A schematic diagram of the AA section.

[0037] Figure label:

[0038] 10. Sphere; 20. Pod;

[0039] 1. Temperature acquisition and storage module;

[0040] 2. Cable laying unit; 21. Housing; 211. Receiving cavity; 212. Guide port; 22. Drum; 23. Cable; 231. Sunshade; 24. Brake shaft; 241. Fixed brake shaft; 242. Floating brake shaft; 243. Elastic support; 25. Linkage arm; 26. Guide assembly; 261. Fixed guide shaft; 262. Floating guide shaft;

[0041] 3. Temperature sensor;

[0042] 4. Insulated chamber; 41. Inner chamber; 42. Insulated shell;

[0043] 101. Flange plate; 201. Environmental data acquisition module; 202. Solar irradiance meter; 203. Long-wave infrared radiation meter; 204. Flight status recording module; 205. Data processing and storage module. Detailed Implementation

[0044] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of this invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this invention. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0045] The following is combined with Figures 1-8 The present invention will provide a detailed description of the airship internal temperature acquisition device and airship provided in the embodiments of the present invention through specific implementation methods and application scenarios.

[0046] In the first aspect, such as Figures 1 to 3 As shown, an embodiment of the present invention provides a temperature acquisition device for an airship, including: a temperature acquisition and storage module 1, a cable laying unit 2, and a temperature sensor 3.

[0047] The temperature acquisition and storage module 1 and the cable-laying unit 2 are both installed inside the sphere 10 of the airship. The temperature acquisition and storage module 1 is located at the top of the sphere 10, and the cable-laying unit 2 is located at the bottom of the sphere 10.

[0048] The cable laying unit 2 includes a housing 21, a drum 22 and a cable 23. The drum 22 is rotatably disposed on the housing 21. One end of the cable 23 is wound on the drum 22, and the other end is connected to the top of the sphere 10.

[0049] Multiple temperature sensors 3 are provided, and the multiple temperature sensors 3 are arranged sequentially at intervals along the extension direction of the cable 23. The signal lead of each temperature sensor 3 is connected to the temperature acquisition and storage module 1.

[0050] Understandably, the sphere 10 of the aerostat can be made of an elastic membrane, and helium can be filled into the sphere 10 when it is launched.

[0051] Before the sphere 10 of the airship is launched, the sphere 10 is not fully extended, and its volume can be marked as the first volume. When the sphere 10 of the airship rises to the stratosphere, the sphere 10 is fully formed, and its volume can be marked as the second volume, which is larger than the first volume.

[0052] During the ascent of the aerostat, as the height of the aerostat's sphere 10 increases, this embodiment utilizes... Figure 4 (a), (b), (c) and (d) in the figure illustrate the successively increasing trend of the shape (volume) of sphere 10.

[0053] exist Figure 4In the process, the sphere 10 of the airship is in a fully formed state. Under the action of the gravity of the cable laying unit 2, the unwound cable 23 on the drum 22 is distributed in the vertical direction, and the extension direction of this part of the cable 23 is arranged along the line connecting the top and bottom of the sphere 10.

[0054] At this time, there are a total of five temperature sensors 3 distributed on the unwound cable 23 on the drum 22. The height difference between two adjacent temperature sensors 3 can be 0.2L, and the height difference between the topmost temperature sensor 3 and the top of the sphere 10 is 0.1L. Wherein, L is the height difference between the top and bottom of the sphere 10.

[0055] Thus, when the sphere 10 of the airship is fully formed, the present invention can collect the temperature at different heights inside the sphere 10 by using multiple temperature sensors 3 distributed on the unwound cable 23. The signals collected by each temperature sensor 3 can be uniformly transmitted to the temperature acquisition and storage module 1, which collects and stores the signals fed back by each temperature sensor 3.

[0056] The temperature acquisition and storage module 1 can be configured to include a sampling circuit, a processing module, and a storage module. Each temperature sensor 3 is connected to the sampling circuit, the sampling circuit is connected to the processing module, and the processing module is connected to the storage module.

[0057] Of course, in this embodiment, the processing module and the wireless communication module can also be connected. The temperature signals collected by each temperature sensor 3 can be transmitted to the terminal device through the wireless communication module, and the user can view this information through the terminal device. The terminal device can be a mobile phone, tablet computer, or smart wearable device, etc., and is not specifically limited thereto.

[0058] The airship internal temperature acquisition device of the present invention arranges a temperature acquisition and storage module 1 and a cable-laying unit 2 arranged vertically opposite each other inside the sphere 10 of the airship. The cable 23 of the cable-laying unit 2 is connected to the top of the sphere 10. During the airship's ascent, the sphere 10 expands continuously due to the increasing internal and external pressure difference. The cable 23 on the drum 22 is continuously unwound by the sphere 10. The unwound cable 23 then unfolds each temperature sensor 3 attached to it along the height direction of the sphere 10. This allows multiple temperature sensors 3 to be adaptively distributed in different positions inside the sphere 10 according to the shape changes of the sphere 10, facilitating the acquisition of temperature at different locations inside the sphere 10 and thus achieving better temperature measurement.

[0059] In some embodiments, such as Figures 5 to 8 As shown, the cable-laying unit 2 also includes a brake shaft 24, a linkage arm 25, and a guide assembly 26.

[0060] The drum 22 is sleeved on the peripheral wall of the brake shaft 24. The brake shaft 24 includes a fixed brake shaft 241, a floating brake shaft 242, and an elastic support member 243. The elastic support member 243 can be a spring or an elastic rod. The fixed brake shaft 241 and the floating brake shaft 242 are arranged side by side. The elastic support member 243 is located between the fixed brake shaft 241 and the floating brake shaft 242. The fixed brake shaft 241 is fixedly connected to the housing 21. Frictional contact is formed between the peripheral wall of the fixed brake shaft 241 and the inner wall of the drum 22 and / or between the peripheral wall of the floating brake shaft 242 and the inner wall of the drum 22.

[0061] The guide assembly 26 includes a fixed guide shaft 261 and a floating guide shaft 262, which are arranged side by side. The fixed guide shaft 261 is connected to the housing 21. One end of the linkage arm 25 is rotatably connected to the fixed guide shaft 261, and the other end is fixedly connected to the floating shaft. The floating guide shaft 262 is rotatably mounted on the linkage arm 25.

[0062] The cable 23 on the drum 22 first passes around the floating guide shaft 262, then passes through the gap between the fixed guide shaft 261 and the floating guide shaft 262, then passes around the fixed guide shaft 261, and then connects to the top of the ball 10.

[0063] Understandably, in the initial stage of the airship's ascent, the cable 23 on the drum 22 has a relatively large weight because it has not yet been unwound, and the tension on the unwound cable 23 is relatively large. At this time, the cable 23 will exert a relatively large lateral force on the floating guide shaft 262. The floating guide shaft 262 tends to swing laterally through the linkage arm 25, which increases the pressure of the floating brake shaft 242 on the inner wall of the drum 22. This increases the contact friction between the drum 22 and the brake shaft 24, thereby slowing down the rotation speed of the drum 22 and slowing down the unwinding speed of the cable 23.

[0064] As the sphere 10 of the airship continues to rise, the drum 22 continuously unwinds the cable 23. The weight on the drum 22 gradually decreases, thereby reducing the tension on the unwound cable 23. This reduces the contact friction between the drum 22 and the brake shaft 24, increasing the unwinding speed of the drum 22 on the cable 23.

[0065] Therefore, the cable-laying unit 2 of the present invention can automatically adjust the resistance of the cable 23 on the drum 22 to unwinding according to the gravity on the drum 22 inside the housing 21. As the gravity on the drum 22 decreases, the resistance of the drum 22 to unwinding the cable 23 is automatically reduced. This not only enables the rapid deployment of various temperature sensors 3 inside the sphere 10, but also ensures that the entire cable-laying unit 2 slowly descends to the bottom of the sphere 10 during the ascent of the airship.

[0066] In some embodiments, such as Figure 8 As shown, the fixed brake shaft 241 has a first plane and a first arc-shaped friction surface, and the floating brake shaft 242 has a second plane and a second arc-shaped friction surface.

[0067] The first plane and the second plane are parallel, and the elastic support 243 is located between the first plane and the second plane; the first arc-shaped friction surface and the second arc-shaped friction surface are both in contact with the inner wall of the drum 22.

[0068] Understandably, the cross-sectional shape of the fixed brake shaft 241 along the plane perpendicular to its axis is semi-circular, and the cross-sectional shape of the floating brake shaft 242 along the plane perpendicular to its axis is also semi-circular.

[0069] The first plane on the fixed brake shaft 241 and the second plane on the floating brake shaft 242 are arranged opposite to each other, and the first arc-shaped friction surface on the fixed brake shaft 241 and the second arc-shaped friction surface on the floating brake shaft 242 are arranged in opposite directions.

[0070] Supported by the elastic support 243, the fixed brake shaft 241 and the floating brake shaft 242 are connected, but they are always far apart from each other. Both the first arc-shaped friction surface and the second arc-shaped friction surface abut against the inner wall of the drum 22, thereby achieving braking of the drum 22. In order to increase the braking effect of the brake shaft 24 on the drum 22, the inner wall of the drum 22 can also be configured with a rough surface structure.

[0071] Furthermore, in order to ensure the braking capacity and service life of the fixed brake shaft 241 and the floating brake shaft 242, a first friction plate can be attached to the position corresponding to the first arc-shaped friction surface on the fixed brake shaft 241, and a second friction plate can be attached to the position corresponding to the second arc-shaped friction surface on the floating brake shaft 242, so as to adhere to the wall surface corresponding to the first friction plate and the second friction plate and the inner wall of the drum 22.

[0072] In some embodiments, such as Figure 7 and Figure 8 As shown, multiple elastic support members 243 are provided, and the multiple elastic support members 243 are arranged sequentially at intervals along the extension direction of the fixed brake shaft 241 or the floating brake shaft 242.

[0073] Thus, by setting multiple elastic support members 243, this embodiment can provide stable support for the floating brake shaft 242 based on the multiple elastic support members 243. During the process of the linkage arm 25 driving the floating brake shaft 242 to swing relative to the fixed brake shaft 241, it is ensured that the fixed brake shaft 241 and the floating brake shaft 242 always remain parallel. Therefore, based on the cooperation of the fixed brake shaft 241 and the floating brake shaft 242, the braking effect on the drum 22 is ensured.

[0074] In some embodiments, such as Figure 5 and Figure 6 As shown, there are two linkage arms 25, which are spaced apart. The drum 22, brake shaft 24 and guide assembly 26 are located between the two linkage arms 25.

[0075] Specifically, the upper end of one of the two linkage arms 25 is rotatably disposed at one end of the fixed guide shaft 261, and the upper end of the other arm is rotatably disposed at the other end of the fixed guide shaft 261.

[0076] One end of the floating guide shaft 262 is rotatably connected to one of the two linkage arms 25, and the other end of the floating guide shaft 262 is rotatably connected to the other of the two linkage arms 25.

[0077] Two linkage arms 25 are respectively located on both sides of the drum 22, and the lower end of one of the two linkage arms 25 is connected to one end of the floating brake shaft 242, and the lower end of the other linkage arm 25 is connected to the other end of the floating brake shaft 242.

[0078] Obviously, by setting two linkage arms 25, this embodiment can not only achieve stable installation of the floating guide shaft 262 and the floating brake shaft 242 based on the two linkage arms 25, but also ensure the stability of force transmission between the floating guide shaft 262 and the floating brake shaft 242.

[0079] In some embodiments, such as Figure 5 As shown, the housing 21 has a receiving cavity 211 and a guide port 212 communicating with the receiving cavity 211. The drum 22, brake shaft 24, linkage arm 25 and guide assembly 26 are respectively disposed in the receiving cavity 211. After passing through the guide assembly 26, the cable 23 is led out from the guide port 212 and then connected to the top of the ball 10.

[0080] The guide port 212 is located at the upper end of the housing 21, and the drum 22 is located at the lower end of the housing 21. The size of the upper end of the housing 21 is smaller than the size of the lower end of the housing 21.

[0081] In some embodiments, such as Figure 3 As shown, the airship internal temperature acquisition device in this embodiment also includes: a heat preservation chamber 4; the heat preservation chamber 4 is located at the top of the sphere 10, the heat preservation chamber 4 includes an inner chamber 41 and a heat preservation shell 42, the heat preservation shell 42 covers the outside of the inner chamber 41, and the temperature acquisition and storage module 1 is located in the inner chamber 41.

[0082] Understandably, the insulated chamber 4 not only provides a mounting base for the temperature acquisition and storage module 1, but also provides thermal insulation protection for the temperature acquisition and storage module 1 to prevent damage to the temperature acquisition and storage module 1 in low-temperature environments.

[0083] The insulation shell 42 corresponding to the insulation chamber 4 can be configured as a foam shell to reduce the weight occupied by the insulation shell 42 while achieving protection.

[0084] The foam shell can be configured to include a top, a sleeve, and a bottom. The top covers the top of the inner compartment 41, the top and the upper end of the sleeve are connected, the sleeve is fitted onto the periphery of the inner compartment 41, and the bottom is embedded in the lower port of the inner compartment 41.

[0085] Meanwhile, the inner cabin 41 can be made of materials with high hardness such as stainless steel and plastic. The lower end of the inner cabin 41 and the flange plate 101 set at the top of the sphere 10 are connected by corresponding flange structures. The lower end of the shell and the flange plate 101 are fitted together, and the joint between the lower end of the shell and the flange plate 101 is sealed with aviation sealant.

[0086] A partition is provided inside the inner compartment 41, and an accommodating space is formed between the top of the inner compartment 41 and the partition. The temperature acquisition and storage module 1 is located in the accommodating space. An aircraft carrier head connected to the temperature acquisition and storage module 1 can be installed on the partition. The signal lead wires of multiple temperature sensors 3 can be connected to the aircraft male connector. The aircraft male connector and the aircraft carrier head are plugged in.

[0087] In practical applications, multiple aircraft head and aircraft carrier head can be configured one-to-one according to actual needs.

[0088] In some embodiments, the cable 23 is further provided with a plurality of light shields 231. The plurality of light shields 231 and the plurality of temperature sensors 3 are arranged opposite to each other, and the temperature sensors 3 are housed in the light shields 231.

[0089] Understandably, by configuring a sunshade 231 on the temperature sensor 3, this application can reduce the direct heating effect of solar radiation on the probe of the temperature sensor 3. Adding a sunshade 231 to the upper part of the probe of the temperature sensor 3 can isolate radiation and prevent the probe from contacting the spherical membrane, thus ensuring that the probe of the temperature sensor 3 can normally and effectively measure the temperature change of the gas inside the sphere 10.

[0090] In a second aspect, the present invention also provides an airship, including a sphere 10 and an airship internal temperature acquisition device as described above.

[0091] It is understood that since the airship includes an internal temperature acquisition device, and the specific structure of the internal temperature acquisition device can be referred to in the above embodiments, the airship of this embodiment includes all the technical solutions of the above embodiments. Therefore, it has at least all the beneficial effects achieved by all the technical solutions of the above embodiments, which will not be described in detail here.

[0092] In some embodiments, such as Figure 1As shown, the airship also includes a pod 20. The pod 20 is located at the bottom of the sphere 10. The pod 20 is equipped with an environmental data acquisition module 201, a solar irradiance meter 202, a long-wave infrared radiation meter 203, a flight status recording module 204, and a data processing and storage module 205. The environmental data acquisition module 201, the solar irradiance meter 202, the long-wave infrared radiation meter 203, and the flight status recording module 204 are respectively connected to the data processing and storage module 205.

[0093] Understandably, the environmental data acquisition module 201 can be used to collect environmental parameters such as temperature, air pressure, humidity, and altitude of the environment in which the airship is located. Specifically, the environmental data acquisition module 201 may include a temperature and humidity sensor, an air pressure sensor, and an altitude measuring instrument.

[0094] The flight status recording module 204 is used to detect the current speed, attitude, etc. of the airship. Specifically, the flight status recording module 204 may include a speed detector, a gyroscope, etc.

[0095] Meanwhile, the data processing and storage module 205 can be configured based on a circuit board, including a processor and a memory card. The environmental data acquisition module 201, the solar irradiance meter 202, the long-wave infrared radiation meter 203, and the flight status recording module 204 are respectively connected to the processor, and the processor and the memory card are connected.

[0096] When controlling the airship to conduct flight tests, helium can be filled into the sphere 10 of the airship first. As the sphere 10 is inflated and unfolded, the cable 23 on the drum 22 gradually unwinds. Driven by the cable 23, the temperature sensors 3 on the unwinding cable 23 gradually unfold and are distributed at different temperature measurement positions along the height direction inside the sphere 10, so as to collect the gas temperature at different positions inside the sphere 10.

[0097] Next, the control environment data acquisition module 201, solar irradiance meter 202, long-wave infrared radiation meter 203, and flight status recording module 204 are started to operate, collecting environmental parameters of the environment where the airship is located and flight data parameters of the airship. The data processing and storage module 205 then processes and stores the collected data.

[0098] After the airship completes its flight and recovery, the data collected during the flight is retrieved.

[0099] After the experiment was completed, the data collected during the flight of the airship were analyzed and processed, and the flight calculation model of the airship was verified and improved.

[0100] 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 they can still modify the technical solutions described in the foregoing embodiments, or make equivalent substitutions for some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A temperature acquisition device for the interior of an airship, characterized in that, include: Temperature acquisition and storage module, cable laying unit, and temperature sensor; Both the temperature acquisition and storage module and the cable-laying unit are installed inside the sphere of the airship. The temperature acquisition and storage module is located at the top of the sphere, and the cable-laying unit is located at the bottom of the sphere. The cable-laying unit includes a housing, a drum, and a cable. The drum is rotatably mounted on the housing. One end of the cable is wound around the drum, and the other end is connected to the top of the sphere. The temperature sensor is provided in multiple ways, and the multiple temperature sensors are arranged at intervals along the extension direction of the cable. The signal lead of each temperature sensor is connected to the temperature acquisition and storage module. The cable-laying unit also includes a brake shaft, a linkage arm, and a guide assembly; The drum is sleeved on the peripheral wall of the brake shaft. The brake shaft includes a fixed brake shaft, a floating brake shaft, and an elastic support member. The fixed brake shaft and the floating brake shaft are arranged side by side. The elastic support member is disposed between the fixed brake shaft and the floating brake shaft. The fixed brake shaft is fixedly connected to the housing. Frictional contact is formed between the peripheral wall of the fixed brake shaft and the inner wall of the drum and / or between the peripheral wall of the floating brake shaft and the inner wall of the drum. The guiding assembly includes a fixed guide shaft and a floating guide shaft, which are arranged side by side. The fixed guide shaft is connected to the housing. One end of the linkage arm is rotatably connected to the fixed guide shaft, and the other end is fixedly connected to the floating brake shaft. The floating guide shaft is rotatably mounted on the linkage arm. The cable on the drum first passes around the floating guide shaft, then through the gap between the fixed guide shaft and the floating guide shaft, then passes around the fixed guide shaft, and finally connects to the top of the sphere.

2. The airship internal temperature acquisition device according to claim 1, characterized in that, The fixed brake shaft has a first plane and a first arc-shaped friction surface, and the floating brake shaft has a second plane and a second arc-shaped friction surface; The first plane and the second plane are parallel, and the elastic support is disposed between the first plane and the second plane; Both the first arc-shaped friction surface and the second arc-shaped friction surface are in contact with the inner wall of the drum.

3. The airship internal temperature acquisition device according to claim 2, characterized in that, The elastic support is provided in multiple ways, and the multiple elastic support are arranged sequentially at intervals along the extension direction of the fixed brake shaft or the floating brake shaft.

4. The airship internal temperature acquisition device according to claim 1, characterized in that, The linkage arm is provided with two arms, which are spaced apart. The drum, the brake shaft and the guide assembly are located between the two linkage arms.

5. The airship internal temperature acquisition device according to claim 1, characterized in that, The housing has a receiving cavity and a guide port communicating with the receiving cavity; The drum, the brake shaft, the linkage arm, and the guide assembly are respectively disposed in the receiving cavity. After passing through the guide assembly, the cable is led out from the guide port and then connected to the top of the sphere.

6. The airship internal temperature acquisition device according to any one of claims 1 to 5, characterized in that, Also includes: Insulated compartment; The insulated chamber is located at the top of the sphere. The insulated chamber includes an inner chamber and an insulated shell. The insulated shell covers the outside of the inner chamber. The temperature acquisition and storage module is located inside the inner chamber.

7. The airship internal temperature acquisition device according to any one of claims 1 to 5, characterized in that, The cable is also equipped with multiple light shields; Multiple light shields and multiple temperature sensors are arranged opposite to each other, with the temperature sensors housed within the light shields.

8. An airship, characterized in that, It includes a sphere and an internal temperature acquisition device for an airship as described in any one of claims 1 to 7.

9. The airship according to claim 8, characterized in that, Also includes: pod; The pod is located at the bottom of the sphere and is equipped with an environmental data acquisition module, a solar irradiance meter, a long-wave infrared radiation meter, a flight status recording module, and a data processing and storage module. The environmental data acquisition module, the solar irradiance meter, the long-wave infrared radiation meter, and the flight status recording module are respectively connected to the data processing and storage module.

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