Thermal layer atmosphere in-situ measurement detector

Abstract

The invention relates to the technical field of thermal layer atmosphere in-situ measurement, in particular to a thermal layer atmosphere in-situ measurement detector which comprises a detector body and a baffle, and a first atmosphere particle inlet is formed in one end of the detector body. A preset distance is reserved between the baffle and the end face of the detector body. A second atmospheric particle inlet right opposite to the first atmospheric particle inlet is formed in the baffle. On one hand, a gas high-density accumulation area is transferred to the side, away from the detector body, of the baffle by means of the baffle, and the gas high-density accumulation area is prevented from being formed at the first atmospheric particle inlet of the detector body. On the other hand, the baffle is used for replacing a collimator, one part of the atmospheric particles penetrating through the second atmospheric particle inlet are diffused into the space, the other part of the atmospheric particles flow into the first atmospheric particle inlet, the particles moving in the unexpected direction are limited from flowing into the first atmospheric particle inlet, and the thermal layer atmospheric density measurement precision is greatly improved on the whole.

Description

Technical Field

[0001] The invention relates to the technical field of thermospheric atmosphere in-situ measurement, and in particular to a thermospheric atmosphere in-situ measurement detector. Background Art

[0002] The thermosphere usually refers to the atmosphere at an altitude of about 100km to 800km above sea level, covering part of near-space and low-Earth orbit. Compared with the atmosphere near sea level, the thermosphere is very thin, with a pressure range of about 10 -8 ~10 -1 Pa, the gas composition is also different from that on the ground, and atomic components such as O, H, He, etc. appear. The atmospheric environment in this interval is affected by multiple factors such as space weather events, the movement of the lower dense atmosphere, geomagnetism, and geographical latitude, and the temporal and spatial changes are very complex. The thermosphere has an important impact on satellites, space stations, or aircraft flying in this space.

[0003] Traditional thermospheric in-situ atmospheric measurement detectors are carried on carriers such as satellites, space stations or aircraft. Traditional thermospheric in-situ atmospheric measurement detectors have an atmospheric particle inlet, through which thermospheric atmospheric particles are collected, and then information such as atmospheric density and composition are identified through operations such as ionization, energy analysis or mass spectrometry. However, before entering the atmospheric particle inlet of the detector, the atmospheric particles will interact with the external structure of the carrier / detector. The atmospheric particles are densely accumulated at the atmospheric particle inlet, and the collected gas parameters are no longer exactly the same as the gas parameters in the real environment, which brings errors to the atmospheric density measurement.

[0004] Therefore, how to improve the measurement accuracy of thermospheric atmospheric density has become a technical problem that needs to be urgently solved by technicians in this field. Summary of the invention

[0005] The present invention provides a thermospheric atmosphere in-situ measurement detector, which is used to solve the problem of how to improve the measurement accuracy of thermospheric atmosphere density.

[0006] The present invention provides a thermospheric atmosphere in-situ measurement detector, comprising:

[0007] The detector body has a first atmospheric particle inlet formed at one end;

[0008] The baffle is arranged at one end of the detector body and has a preset distance from the end surface of the detector body; a second atmospheric particle inlet is formed on the baffle and is directly opposite to the first atmospheric particle inlet.

[0009] In some embodiments, the diameter d3 of the second atmospheric particle inlet is equal to the diameter d1 of the first atmospheric particle inlet.

[0010] In some embodiments, the baffle is circular / square, and the ratio of its diameter / side length to the aperture d1 of the first atmospheric particle inlet is greater than or equal to 15.

[0011] In some embodiments, the preset distance is D:

[0012] D=(d l / 2) / tan(a * )=(d l / 2) / tan[ arcsin (c′ s / V vehicle =(d l / 2) / ran[ arcsin ((3kT / m) 1 / 2 / V vehicle )];

[0013] Among them, α * is the maximum deflection angle that the combined velocity V of atmospheric particles can reach; c' s is the root mean square thermal motion velocity; V vehicle is the speed of the carrier carrying the thermospheric atmosphere in-situ measurement detector; k is the Boltzmann constant; T is the gas temperature; m is the mass of the molecule or atom;

[0014] The thickness of the baffle is less than or equal to 2 mm.

[0015] In some embodiments, it also includes:

[0016] The supporting structure is used to connect one end of the detector body with the baffle.

[0017] In some of the embodiments, the detector body is provided with an ionization chamber; a first atmospheric particle inlet is formed at one end of the ionization chamber close to the baffle; and the ionization chamber is used to convert a neutral gas molecule / atom beam into an ion beam.

[0018] In some of the embodiments, the detector body is further provided with an acceleration chamber; the acceleration chamber is used to increase the kinetic energy of the ion beam.

[0019] In some of the embodiments, the detector body is further provided with an energy analysis unit; the energy analysis unit is used to perform energy analysis on the ion beam.

[0020] In some of the embodiments, the detector body is further provided with a particle counting unit; the particle counting unit is used to measure the number of particles.

[0021] In some embodiments, it also includes:

[0022] The control system is respectively connected with the ionization chamber, the acceleration chamber, the energy analysis unit and the particle counting unit.

[0023] The beneficial effects of the present invention are as follows: The thermospheric atmosphere in-situ measurement detector of the present invention is provided with a first atmospheric particle inlet at one end of the detector body by setting a detector body and a baffle. A preset distance is left between the baffle and the end face of the detector body. A second atmospheric particle inlet is formed on the baffle, which is directly opposite to the first atmospheric particle inlet. On the one hand, the gas high-density accumulation area is transferred to the side of the baffle away from the detector body with the aid of the baffle, thereby preventing the formation of a gas high-density accumulation area at the first atmospheric particle inlet of the detector body. On the other hand, the baffle is used instead of the collimator, so that a part of the atmospheric particles passing through the second atmospheric particle inlet diffuses into the space, and the other part flows into the first atmospheric particle inlet, thereby limiting the particles moving in an unexpected direction from flowing into the first atmospheric particle inlet. On the whole, the measurement accuracy of the thermospheric atmosphere density is greatly improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is the result of the two-dimensional axisymmetric direct Monte Carlo method flow field simulation after the thermospheric atmosphere interacts with the traditional thermospheric atmosphere in-situ measurement detector;

[0025] Figure 2 It is a schematic structural diagram of some specific embodiments of a thermospheric atmosphere in-situ measurement detector of the present invention;

[0026] Figure 3 yes Figure 2 The schematic diagram of the structure of the detector body in the thermospheric atmosphere in-situ measurement detector shown;

[0027] Figure 4 It is a schematic diagram of the composite velocity of the atmospheric particle incident velocity and the atmospheric particle thermal motion velocity;

[0028] Figure 5 It is a schematic diagram of the composite velocity of the atmospheric particle incident velocity and the root mean square thermal motion velocity of the atmospheric particles;

[0029] Figure 6 This is a test comparison diagram of a conventional thermosphere atmosphere in-situ measurement detector and a thermosphere atmosphere in-situ measurement detector of the present invention when they are in a 150km orbit;

[0030] Figure 7 It is a test comparison diagram of a conventional thermospheric atmosphere in-situ measurement detector and the thermospheric atmosphere in-situ measurement detector of the present invention when they are in a 400 km orbit.

[0031] In the attached drawings, 110 is the detector body; 111 is the ionization chamber; 112 is the acceleration chamber; 113 is the energy analysis unit; 114 is the particle counting unit; 115 is the electron source; 116 is the atmospheric particle inflow channel; 120 is the baffle; and 130 is the control system. DETAILED DESCRIPTION

[0032] The technical solution of the present invention will be clearly and completely described below in conjunction with the embodiments. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0033] As described in the background technology, the traditional thermospheric atmosphere in-situ measurement detector is carried on a carrier such as a satellite, space station or aircraft. The traditional thermospheric atmosphere in-situ measurement detector has an atmospheric particle inlet, through which the thermospheric atmospheric particles are collected, and then the atmospheric density and composition and other information are identified through ionization, energy analysis or mass spectrometry analysis. However, before entering the atmospheric particle inlet of the detector, the atmospheric particles will interact with the external structure of the carrier / detector. The atmospheric particles are densely accumulated at the atmospheric particle inlet, and the collected gas parameters are no longer exactly the same as the gas parameters in the real environment, which introduces errors in the atmospheric density measurement. For ease of understanding, Figure 1 It shows that the orbital altitude of the conventional thermospheric atmosphere in-situ measurement detector is about 150 km, and the atmospheric density is 2×10 -9 kg / m 3 When the gas velocity is 8000m / s, the two-dimensional axisymmetric direct Monte Carlo method flow field simulation results after the thermosphere atmosphere interacts with the traditional thermosphere atmosphere in-situ measurement detector can be considered as the cross section of the flow field. Figure 1 It can be seen that a high-density area is generated in front of the detector body 110 of the conventional thermosphere atmosphere in-situ measurement detector, and the atmospheric density at the highest density position is even about 35 times the density of the incoming gas. The local enlarged figure shows the gas density in the atmospheric particle inflow channel 116 of the detector body 110 of the conventional thermosphere atmosphere in-situ measurement detector. It can be seen that the gas density at the atmospheric particle inlet of the conventional thermosphere atmosphere in-situ measurement detector is 4×10 -9 kg / m 3 , which is twice the density of the ambient gas. In this case, the measurement of the thermospheric atmospheric density will introduce a relatively large error. Therefore, how to improve the measurement accuracy of the thermospheric atmospheric density has become a technical problem that needs to be solved urgently by those skilled in the art.

[0034] To solve the above problems, refer to Figure 2The present invention provides a thermospheric atmosphere in-situ measurement detector, including a detector body 110 and a baffle 120. A first atmospheric particle inlet is formed at one end of the detector body 110. The baffle 120 is disposed at one end of the detector body 110. A preset distance is left between the baffle 120 and the end face of the detector body 110. A second atmospheric particle inlet is formed on the baffle 120, which is directly opposite to the first atmospheric particle inlet. On the one hand, the gas high-density accumulation area is transferred to the side of the baffle 120 away from the detector body 110 by means of the baffle 120, so as to prevent the formation of a gas high-density accumulation area at the first atmospheric particle inlet of the detector body 110. On the other hand, the baffle 120 is used instead of the collimator, so that part of the atmospheric particles passing through the second atmospheric particle inlet diffuses into the space, and the other part flows into the first atmospheric particle inlet, thereby limiting the particles moving in an unexpected direction from flowing into the first atmospheric particle inlet. On the whole, the measurement accuracy of the thermospheric atmosphere density is greatly improved.

[0035] Specifically, in the example, Figure 2 and Figure 3 As shown, the detector body 110 is provided with an ionization chamber 111, an acceleration chamber 112, an energy analysis unit 113 and a particle counting unit 114. A first atmospheric particle inlet is formed at one end of the ionization chamber 111 close to the baffle 120. The ionization chamber 111 is used to convert the neutral gas molecule / atom beam into an ion beam. The acceleration chamber 112 is used to increase the kinetic energy in the ion beam. The energy analysis unit 113 is used to perform energy analysis on the ion beam. The particle counting unit 114 is used to measure the number of particles. The thermosphere atmosphere in-situ measurement detector also includes a control system 130. The control system 130 is electrically connected to the ionization chamber 111, the acceleration chamber 112, the energy analysis unit 113, the particle counting unit 114, and the main controller on the carrier. The control system 130 controls the electron source 115 through a voltage, so that the electron source 115 generates an electron beam. The electron beam acts on the neutral gas molecule / atom beam flowing into the ionization chamber 111 to convert the neutral gas molecule / atom beam into an ion beam. The control system 130 controls the accelerating electrodes in the accelerating chamber 112 by voltage, and accelerates the ion beam by voltage difference. The control system 130 works by voltage controlling the energy analysis unit 113. The control system 130 controls the particle counting unit 114 by voltage. The particle count is converted into a pulse electrical signal and transmitted to the control system 130. The master controller can supply power and control the control system 130 to work. The master controller and the control system 130 can transmit data to each other.

[0036] Preferably, if Figure 2As shown, the aperture d3 of the second atmospheric particle inlet is equal to the aperture d1 of the first atmospheric particle inlet. The second atmospheric particle inlet and the first atmospheric particle inlet can be square or circular. The baffle 120 can be circular or square. For the circular baffle 120 and the circular first atmospheric particle inlet, the ratio of the diameter d2 of the baffle 120 to the aperture d1 of the first atmospheric particle inlet is greater than or equal to 15. For the square baffle 120 and the square first atmospheric particle inlet, the ratio of the side length of the baffle 120 to the aperture d1 of the first atmospheric particle inlet is greater than or equal to 15. In this way, the accuracy of thermospheric atmospheric density measurement can be effectively improved.

[0037] It should be noted that it is necessary to analyze the density of the orbital atmosphere at the altitude to be measured to determine whether the thermospheric atmosphere in-situ measurement detector of the present invention is applicable. Through rarefied gas simulation, it can be seen that if the gas particles collide with the carrier / detector structure at the normal flight speed of 8000m / s of the low-orbit carrier, a high-density area about 40 times higher than the ambient gas density is formed in front of the detector. In order to ensure that the gas is still in a free particle flow state even after the high-density area is formed, the judgment criterion is to calculate the dimensionless parameter Kn that characterizes the rarefaction of the gas after it is 40 times higher than the atmospheric density of the area to be detected. * Is the number greater than 0.5? * Defined as:

[0038] K * =(λ / 40) / L;

[0039] Where λ is the mean free path of molecules in the area to be detected, λ / 40 represents the mean free path of molecules 40 times higher than the atmospheric density in the area to be detected; L is the characteristic size of the carrier such as satellite, space station or aircraft. * Greater than 0.5, the thermospheric atmosphere in-situ measurement detector of the present invention is suitable for thermospheric atmosphere in-situ measurement; if Kn * If it is less than or equal to 0.5, the thermospheric atmosphere in-situ measurement detector of the present invention is no longer suitable for thermospheric atmosphere in-situ measurement.

[0040] like Figure 4 As shown in the figure, the velocity of the atmospheric particles arriving at the detector entrance is determined by the vector synthesis of the aircraft motion velocity and the thermal motion velocity of the atmospheric particles. vehicle is the speed of the carrier carrying the thermospheric atmosphere in-situ measurement probe. Without considering the atmospheric wind speed, if the carrier carrying the thermospheric atmosphere in-situ measurement probe is considered to be stationary, the atmospheric particles are measured at V atmosphere The speed of V atmosphere With Flying V vehicle Equal. thermalIt represents the thermal motion speed of atmospheric particles. It is the speed superimposed on the macroscopic motion speed. After synthesis, it forms the speed V of atmospheric particles reaching the detector entrance. The combined speed V is equal to the atmospheric particle speed V atmosphere The angle is α.

[0041] Usually, the thermal motion speed of atmospheric particles V thermal It is a random number that conforms to the Maxwell distribution. Its distribution function is related to temperature. According to the kinetic theory of rarefied gases, its distribution function has three special speed values, namely the most probable thermal motion speed, the average thermal motion speed and the root mean square thermal motion speed, which respectively represent the speed values ​​with a higher probability of appearing in the random distribution from the perspective of certain characteristics.

[0042] If the root mean square thermal motion velocity c' is selected s As the speed that characterizes its overall thermal motion speed, then:

[0043] c′ s =(3kT / m) 1 / 2 ;

[0044] Where k is the Boltzmann constant, which is 1.380658×10 -23 , T is the gas temperature, m is the molecular or atomic mass. In this case, the velocity V of the atmospheric particles reaches the maximum deflection α * When the root mean square thermal motion speed c' s The velocity V of the atmospheric particles should be perpendicular to each other, such as Figure 5 shown.

[0045] α * = arcsin ( c′ s / V vehicle );

[0046] Therefore, the preset distance D between the baffle 120 and the end surface of the detector body 110 is:

[0047] D=(d l / 2 ) / tan(a * )=(d l / 2) / tan[ arcsin ( c′ s / V vehicle =(d l / 2) / ran[ arcsin ((3kT / m) 1 / 2 / V vehicle )];

[0048] Among them, α * is the maximum deflection angle that the combined velocity V of atmospheric particles can reach; c' s is the root mean square thermal motion velocity; V vehicleis the speed of the carrier carrying the thermosphere atmosphere in-situ measurement detector; k is the Boltzmann constant; T is the gas temperature; m is the mass of the molecule or atom. The thickness of the baffle 120 should be less than or equal to 2 mm. Considering that the error of the gas temperature T will not cause a particularly large error in the calculation of the preset distance D, the atmospheric temperature distribution in the atmospheric environment model can usually meet the current calculation needs. Here, the American standard atmospheric model can be selected to obtain the atmospheric environment temperature parameters. At the current temperature, the deflection angle is greater than α * Particles cannot enter the first atmospheric particle inlet.

[0049] Specifically, in the exemplary embodiment, the thermospheric atmosphere in-situ measurement probe further includes a support structure having a certain rigidity and strength and used to connect one end of the probe body 110 with the baffle 120 to limit the relative position of the baffle 120 and the probe body 110 .

[0050] Preferably, the support structure is a tripod or other structure, which should not only have high structural strength and rigidity, but also be as small as possible to ensure that the space between the baffle 120 of the plate-shaped structure and the detector body 110 is in a hollow state as much as possible, so as to achieve the purpose of smoothly discharging atmospheric particles from unexpected directions. At the same time, the small-volume support structure can effectively reduce the probability of atmospheric particles from unexpected directions colliding and changing directions with the support structure, and further prevent atmospheric particles from unexpected directions from flowing into the first atmospheric particle inlet.

[0051] For example, Figure 6 As shown, when the orbital altitude is 150km, according to the US standard atmospheric model, the atmospheric density is 2×10 -9 km / m 3 , the gas temperature T is 635K, and the molecular mean free path λ is 32.5m. Assuming that the carrier is a micro-nano satellite, the characteristic size L is 1m. The first atmospheric particle inlet is circular, and the diameter d1 is 4mm. After calculation, Kn * =0.8125>0.5, the thermosphere in-situ measurement detector of the present invention is suitable for thermosphere in-situ measurement. The baffle 120 is circular, and the diameter d2 is 60 mm. The second atmospheric particle inlet is circular, and the diameter d3 is 4 mm. The Boltzmann constant k is 1.380658×10 -23 , the gas temperature T is 635K, and m is the molecular mass of nitrogen 4.65×10 -26 kg,V vehicle Take 8000m / s, then the preset distance D is 21.18mm. A two-dimensional axisymmetric simulation analysis was conducted on the interaction between the conventional thermosphere atmosphere in-situ measurement detector / the thermosphere atmosphere in-situ measurement detector of the present invention and the incoming gas. Since the influence of the support structure on the flow field can be ignored, it is not modeled. The comparison results are shown in Figure 6As shown in the figure, the density of the gas in the atmospheric particle inflow channel 116 of the detector body 110 of the conventional thermosphere atmosphere in-situ measurement detector is obviously high, close to 5×10 -9 km / m 3 , and the thermosphere atmosphere in-situ measurement detector of the present invention uses the baffle 120 to make the atmospheric particles of the detector body 110 flow into the gas density in the channel 116 to be 2×10 -9 kg / m 3 The density of the gas in the rear section gradually decreases due to the simplified detector model used in the current simulation. The gas particles in the rear section of the gas channel directly enter the high vacuum area, resulting in a decrease in density. However, the gas exhaust channel of the actual detection structure is not directly connected to the external environment like the simplified model, so the gas density will not decrease rapidly.

[0052] like Figure 7 As shown in Figure 2, when the orbital altitude is 400 km, according to the US standard atmospheric model, the atmospheric density is 2.8×10 -12 kg / m 3 , gas temperature T is 996K, molecular mean free path λ is 15997m. Assuming the carrier is a micro-nano satellite, the characteristic size L is 1m. The first atmospheric particle inlet is circular, with a diameter d1 of 4mm. After calculation, Kn * =0.8125>0.5, the thermosphere in-situ measurement detector of the present invention is suitable for thermosphere in-situ measurement. The baffle 120 is circular, and the diameter d2 is 60 mm. The second atmospheric particle inlet is circular, and the diameter d3 is 4 mm. The Boltzmann constant k is 1.380658×10 -23 , the gas temperature T is 996K, and m is the molecular mass of nitrogen 4.65×10 -26 kg,V vehicle Take 8000m / s, then the preset distance D is 16.87mm. A two-dimensional axisymmetric simulation analysis was conducted on the interaction between the conventional thermosphere atmosphere in-situ measurement detector / the thermosphere atmosphere in-situ measurement detector of the present invention and the incoming gas. Since the influence of the support structure on the flow field can be ignored, it is not modeled. The comparison results are shown in Figure 2. Figure 7 As shown in the figure, the density of the gas in the atmospheric particle inflow channel 116 of the detector body 110 of the conventional thermosphere atmosphere in-situ measurement detector is obviously high, close to 3.3×10 -12 kg / m 3 , and the thermosphere atmosphere in-situ measurement detector of the present invention uses the baffle 120 to make the atmospheric particles of the detector body 110 flow into the gas density in the channel 116 to be 2.8×10 -12 kg / m 3 It is about 2.3777 W, which is very close to the density of the incoming gas.

[0053] In the description of the present invention, it is to be understood that the terms “center”, “longitudinal”, “lateral”, “length”, “width”, “thickness”, “up”, “down”, “front”, “back”, “left”, “right”, “vertical”, “horizontal”, “top”, “bottom”, “inside”, “outside”, “clockwise”, “counterclockwise”, “axial”, “radial”, “circumferential”, etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0054] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0055] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral one; it can be a mechanical connection, an electrical connection, or communication with each other; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0056] In the present invention, the terms "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" etc. mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the described specific features, structures, materials or characteristics may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0057] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations of the present invention. A person skilled in the art may change, modify, replace and vary the above embodiments within the scope of the present invention.

Claims

1. A thermospheric atmosphere in-situ measurement detector, characterized in that: include: The detector body has a first atmospheric particle inlet formed at one end; A baffle is arranged at one end of the detector body and has a preset distance from the end surface of the detector body; a second atmospheric particle inlet is formed on the baffle and is directly opposite to the first atmospheric particle inlet.

2. The thermospheric atmosphere in-situ measurement probe according to claim 1, characterized in that: The diameter d3 of the second atmospheric particle inlet is equal to the diameter d1 of the first atmospheric particle inlet.

3. The thermospheric atmosphere in-situ measurement probe according to claim 1, characterized in that: The baffle is circular / square, and the ratio of its diameter / side length to the aperture d1 of the first atmospheric particle inlet is greater than or equal to 15.

4. The thermospheric atmosphere in-situ measurement probe according to claim 1, characterized in that: The preset distance is D: D=(d1 / 2) / tan(α * )=(d1 / 2) / tan[ arcsin ( c' s / V vethcle )]=(d1 / 2) / tan[ arcsin ((3kT / m) 1 / 2 / V vehicle )]; Among them, α * is the maximum deflection angle that the combined velocity V of atmospheric particles can reach; c ' s is the root mean square thermal motion velocity; V vehicle is the speed of the carrier carrying the thermospheric atmosphere in-situ measurement probe; k is the Boltzmann constant; T is the gas temperature; m is the mass of a molecule or atom; The thickness of the baffle is less than or equal to 2 mm.

5. The thermospheric atmosphere in-situ measurement probe according to any one of claims 1 to 4, characterized in that: Also includes: A supporting structure is used to connect one end of the detector body with the baffle.

6. The thermospheric atmosphere in-situ measurement probe according to any one of claims 1 to 4, characterized in that: The detector body is provided with an ionization chamber; the first atmospheric particle inlet is formed at one end of the ionization chamber close to the baffle; the ionization chamber is used to convert a neutral gas molecule / atom beam into an ion beam.

7. The thermospheric atmosphere in-situ measurement probe according to claim 6, characterized in that: The detector body is also provided with an acceleration chamber; the acceleration chamber is used to increase the kinetic energy of the ion beam.

8. The thermospheric atmosphere in-situ measurement probe according to claim 7, characterized in that: The detector body is also provided with an energy analysis unit; the energy analysis unit is used to perform energy analysis on the ion beam.

9. The thermospheric atmosphere in-situ measurement probe according to claim 8, characterized in that: The detector body is also provided with a particle counting unit; the particle counting unit is used to measure the number of particles.

10. The thermospheric atmosphere in-situ measurement probe according to claim 9, characterized in that: Also includes: A control system is connected to the ionization chamber, the acceleration chamber, the energy analysis unit, and the particle counting unit respectively.

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