An apparatus and method for measuring the spatial atmospheric wind field of a spacecraft's operating orbit

Abstract

The present invention belongs to the technical field of space environment detection equipment, and in particular, relates to a device for measuring the atmospheric wind field in a spacecraft orbit, characterized in that the device comprises: a gas sampling and collimating sub-device (1), a cold cathode electron emitting and focusing sub-device (2), an ionization zone electric field control sub-device (3), an ion velocity analysis and collection sub-device (4) and a device shell (5); the gas sampling and collimating sub-device (1), the cold cathode electron emitting and focusing sub-device (2), the ionization zone electric field control sub-device (3) and the ion velocity analysis and collection sub-device (4) are arranged in the device shell (5); the gas sampling and collimating sub-device (1) is arranged on the cold cathode electron emitting and focusing sub-device (2), and one side of the two is sequentially connected to the ion velocity analysis and collection sub-device (4); and the ionization zone electric field control sub-device (3) is arranged in the cold cathode electron emitting and focusing sub-device (2).

Description

Technical Field

[0001] The present invention belongs to the technical field of space environment detection equipment. Specifically, it relates to a device and method for measuring the spatial atmospheric wind field of a spacecraft's operating orbit. Background Art

[0002] The upper atmosphere of a planet is one of the key regions for studying the planet's space environment and evolution. The upper atmosphere wind field plays an important role in the magnetosphere-ionosphere-atmosphere coupling, and is an important atmospheric parameter for studying the dynamics of the planet's upper atmosphere and ionosphere. It is also of great significance for the study of the evolution process of the planet's climate and atmosphere. However, since the gas in the planet's upper atmosphere belongs to a rarefied gas free molecular flow, the continuum hypothesis no longer applies to this region. Therefore, the in-situ wind measurement devices used on the ground are not suitable for measuring the upper atmosphere wind field of a planet. In addition, the relative speed between the spacecraft operating in the planet's upper atmosphere and the atmosphere can reach several kilometers per second, which is much greater than the wind speed to be measured, making it very difficult to conduct in-situ detection of the spatial atmospheric wind field of the spacecraft's operating orbit. Therefore, realizing the in-situ measurement of the spatial atmospheric wind field of the spacecraft's operating orbit is an important development direction.

[0003] The basic principle of conducting in-situ measurement of the spatial atmospheric wind field of a spacecraft's operating orbit is to obtain parameters such as its velocity and temperature by measuring the distribution of neutral particles in the planet's upper atmosphere. Since the energy of neutral particles in the atmosphere is very low and it is difficult to directly measure and obtain their energy spectra, after ionizing the neutral particles, the energy spectrum distribution of the ions is measured, and thus the energy spectrum distribution of the neutral particles is indirectly obtained.

[0004] However, after the conventional gas neutral particles are ionized, the method of measuring the energy spectrum distribution of the ionized ions is interfered by a strong residual electric field, with poor measurement accuracy and it is difficult to directly reflect the true energy spectrum distribution of the neutral particles. Summary of the Invention

[0005] To solve the above-mentioned defects existing in the prior art, the present invention proposes a device and method for measuring the spatial atmospheric wind field of a spacecraft's operating orbit. The measuring device of the present invention is embedded on the surface of the satellite, with the air inlet pointing to the measuring direction of the wind speed vector, and the upper part of the sensor protruding from the surface of the satellite, and the detection window is kept as far away from the surface of the satellite as possible to reduce the interference of the satellite surface plume on the measurement of neutral gas molecules.

[0006] The present invention provides a device for measuring the spatial atmospheric wind field of a spacecraft's operating orbit. The device includes: a gas sampling and collimation sub-device, a cold cathode electron emission and focusing sub-device, an ionization region electric field control sub-device, an ion velocity analysis and collection sub-device, and a device housing;

[0007] The gas sampling and collimation sub-device, the cold cathode electron emission and focusing sub-device, the ionization region electric field control sub-device, and the ion velocity analysis and collection sub-device are arranged inside the device housing;

[0008] The gas sampling and collimation sub-device is arranged on the cold cathode electron emission and focusing sub-device, and the ion velocity analysis and collection sub-device is sequentially connected to one side of the two; the ionization region electric field control sub-device is arranged inside the cold cathode electron emission and focusing sub-device.

[0009] As one of the improvements of the above technical solution, the gas sampling and collimation sub-device includes: an air inlet, an air outlet, and a collimation chamber;

[0010] The collimation chamber is a cylindrical cavity, and the air inlet and the air outlet are respectively arranged at both ends of the cylindrical cavity.

[0011] As one of the improvements of the above technical solution, the cold cathode electron emission and focusing sub-device includes: a cold cathode electron emitter, an electron modulation electrode assembly, and an anode plate;

[0012] The electron modulation electrode assembly is arranged above the cold cathode electron emitter; the anode plate is arranged above the electron modulation electrode assembly; the electron modulation electrode assembly is located between the cold cathode electron emitter and the anode plate, and the three are arranged in parallel.

[0013] As one of the improvements of the above technical solution, the cold cathode electron emitter includes: a cold cathode electron emission body and a frame support;

[0014] The cold cathode electron emission body has a cylindrical structure, the cross-section of the frame support has an I-shaped structure, and the cold cathode electron emission body is arranged inside the frame support.

[0015] As one of the improvements of the above technical solution, the electron modulation electrode assembly includes: a first cylindrical hollow structure electrode and a second cylindrical hollow structure electrode;

[0016] The first cylindrical hollow structure electrode is arranged below the second cylindrical hollow structure electrode, and the central axes of the first cylindrical hollow structure electrode and the second cylindrical hollow structure electrode coincide with the central axis of the cold cathode electron emitter.

[0017] As one of the improvements of the above technical solution, the ionization region electric field control sub-device includes: a first ionization region shielding grid and a second ionization region shielding grid;

[0018] The second ionization region shielding grid is arranged in parallel on the inner wall at the top of the electron modulation electrode assembly, and the first ionization region shielding grid is arranged in parallel on the inner wall between the electron modulation electrode assembly and the second ionization region shielding grid.

[0019] As one of the improvements to the above technical solution, the ion velocity analysis and collection sub-device includes at least two analysis area shielding grids, at least four analysis area scanning grids, and a collector electrode arranged in sequence;

[0020] The at least two analysis area shielding grids, the at least four analysis area scanning grids, and the collector electrode are arranged in parallel.

[0021] The present invention also provides a method for measuring the space atmospheric wind field of a spacecraft's operating orbit, and the method includes:

[0022] The neutral gas molecules of the planetary upper atmosphere incident at high speed on the spacecraft's operating orbit enter the air inlet of the collimation chamber, and the neutral gas molecules of the planetary upper atmosphere enter the ionization area in the collimation chamber;

[0023] The cold cathode electron emitter emits an electron beam, and through the electron modulation electrode assembly and the ionization area electric field control sub-device, the incident direction of the electron beam is adjusted, and the electron beam is vertically incident on the ionization area;

[0024] The electron beam is used to ionize the neutral gas molecules of the planetary upper atmosphere, and the ionized ions are emitted while maintaining the distribution state of the incident neutral gas. The emitted ions pass through the analysis area shielding grid, enter the analysis area scanning grid, and through the analysis area scanning grid, an ion current I is obtained, and the velocity V is calculated using the scanning voltage g , and then combined with formulas (1) and (2), the central velocity V of the neutral gas molecules is inversely calculated c and the thermal velocity V m :

[0025]

[0026] I = GeN i F(v) (2)

[0027] where F(v) is the distribution function related to the velocity V c of the neutral gas molecules and the thermal velocity V m of the neutral gas molecules; Ge is a constant factor; N i is the density of the neutral gas;

[0028] According to the calculated thermal velocity V m of the neutral gas molecules, the temperature of the neutral gas molecules can be obtained.

[0029] The beneficial effects of the present invention compared with the prior art are:

[0030] 1. The measuring device of the present invention realizes the sampling and collimation of the neutral gas molecular inflow in the upper atmosphere of the planet through the gas sampling and collimation sub-device; through the collimation function of the gas sampling and collimation sub-device, the main direction of the gas inflow incident at high speed along the spacecraft operation orbit is selected, realizing the selective measurement of different inflow directions.

[0031] 2. In the measuring device of the present invention, after the gas inflow is ionized in the ionization region, through the cold cathode electron emission and focusing sub-device and the ionization region electric field control sub-device, the emitted electrons are focused into an approximately parallel electron beam, improving the ionization efficiency and ensuring the consistency of electron energy. At the same time, the electric field in the ionization region is adjusted to greatly reduce the interference of the leakage electric field on the ion distribution state generated after the ionization of the incident neutral gas molecular inflow, so that the ions generated by ionization are as consistent as possible with the initial state of the incident neutral gas distribution, thus solving the problem of interference from the residual electric field. And through the ion velocity analysis and collection sub-device, the ions in the ionization region are scanned, extracted and collected to obtain the ion energy distribution curve, and parameters such as the velocity and temperature of the incident neutral gas are obtained; and the interference of background noise is greatly reduced, and the wind speed measurement accuracy can reach better than 10 m / s, realizing the high-precision measurement of the space atmospheric wind field along the spacecraft operation orbit.

[0032] 3. The measuring device of the present invention has the function of detecting the space atmospheric wind field, solves the problem of interference from the residual electric field, and realizes the high-precision measurement of the space atmospheric wind field along the spacecraft operation orbit. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 is a schematic structural diagram of a device for measuring the space atmospheric wind field along a spacecraft operation orbit according to the present invention;

[0034] Figure 2 is Figure 1 a longitudinal sectional structural diagram of the gas sampling and collimation sub-device and the cold cathode electron emission and focusing sub-device in a device for measuring the space atmospheric wind field along a spacecraft operation orbit according to the present invention;

[0035] Figure 3 is Figure 1 a sectional structural diagram of the ion velocity analysis and collection sub-device in a device for measuring the space atmospheric wind field along a spacecraft operation orbit according to the present invention.

[0036] Reference Signs:

[0037] 1. Gas sampling and collimation sub-device 2. Cold cathode electron emission and focusing sub-device

[0038] 3. Ionization region electric field control sub-device 4. Ion velocity analysis and collection sub-device

[0039] 5. Device housing

[0040] 1.1, Intake port 1.2, Outlet port 1.3, Collimation chamber

[0041] 2.1, Electron-emitting cold cathode 2.2, Electron modulation electrode assembly 2.3, Anode plate

[0042] 2.1.1, Cold cathode electron emitter 2.1.2, Frame support

[0043] 2.2.1, First cylindrical hollow structure electrode 2.2.2, Second cylindrical hollow structure electrode

[0044] 3.1, First ionization region shielding grid 3.2, Second ionization region shielding grid

[0045] 4.1, Analysis region shielding grid 4.2, Analysis region scanning grid

[0046] 4.3, Collector Detailed implementation mode

[0047] The present invention will be further described in conjunction with the accompanying drawings.

[0048] As Figure 1 shown, the present invention provides a device for measuring the spatial atmospheric wind field of a spacecraft operating orbit. The device includes: a gas sampling and collimation sub-device 1, a cold cathode electron emission and focusing sub-device 2, an ionization region electric field control sub-device 3, an ion velocity analysis and collection sub-device 4, and a device housing 5;

[0049] The gas sampling and collimation sub-device 1, the cold cathode electron emission and focusing sub-device 2, the ionization region electric field control sub-device 3, and the ion velocity analysis and collection sub-device 4 are arranged inside the device housing 5;

[0050] The gas sampling and collimation sub-device 1 is arranged on the cold cathode electron emission and focusing sub-device 2, and the ion velocity analysis and collection sub-device is sequentially connected to one side of the two; the ionization region electric field control sub-device 3 is arranged inside the cold cathode electron emission and focusing sub-device 2;

[0051] The gas sampling and collimation sub-device 1 is used for sampling neutral gas molecules and collimating the gas movement direction;

[0052] The cold cathode electron emission and focusing sub-device 2 is used for emitting electrons and realizing the focusing of the electron beam in the ionization region. The electrons enter the ionization region under the guidance of the electron emission and focusing system to ionize gas molecules;

[0053] The ionization region electric field control sub-device 3 is used for controlling the penetration of the surrounding electrode voltage, so that the ionized ions maintain the distribution state of the neutral gas incident;

[0054] The ion velocity analysis and collection sub-device 4 is used to extract and collect ions in the ionization region, obtain the energy distribution curve of the ions, and obtain the corresponding ion current according to the energy distribution curve.

[0055] The device housing 5 provides an installation platform for the entire measuring device and shields the internal and external electric fields.

[0056] As Figure 1 shown, the gas sampling and collimation sub-device 1 includes: an air inlet 1.1, an air outlet 1.2, and a collimation chamber 1.3; the collimation chamber 1.2 is a cylindrical cavity, and the air inlet 1.1 and the air outlet 1.2 are respectively arranged at both ends of the cylindrical cavity; among them, the air inlet 1.1 and the air outlet 1.2 are two circular openings of the same size, and the neutral gas molecules in the planetary upper atmosphere enter from the air inlet 1.1 in the gas sampling and collimation sub-device 1, are collimated by the collimation 1.3, and then are emitted from the air outlet 1.2 and enter the ionization region for ionization, and then enter the analysis region in the ion velocity analysis and collection sub-device.

[0057] As Figure 1 and 2 shown, the cold cathode electron emission and focusing sub-device 2 includes: an electron emission cold cathode 2.1, an electron modulation electrode assembly 2.2, and an anode plate 2.3;

[0058] The electron modulation electrode assembly 2.2 is arranged above the electron emission cold cathode 2.1, and the anode plate 2.3 is arranged above the electron modulation electrode assembly 2.2; the electron modulation electrode assembly 2.2 is located between the electron emission cold cathode 2.1 and the anode plate 2.3, and the three are arranged in parallel, which can focus the electron beam current emitted by the electron emission cold cathode 2.1. The electron emission cold cathode 2.1 and the anode plate 2.3 have the same size and are respectively located on both sides of the ionization region; the anode plate 2.3 can receive the electron beam current emitted by the electron emission cold cathode 2.1.

[0059] Specifically, as Figure 1 and 2 shown, the electron emission cold cathode 2.1 includes: a cold cathode electron emitter 2.1.1 and a frame support 2.1.2;

[0060] The cold cathode electron emitter 2.1.1 has a thin cylindrical structure, the cross-section of the frame support 2.1.2 has an I-shaped structure, and the cold cathode electron emitter 2.1.1 is arranged inside the frame support 2.1.2, aiming to emit electrons so that the neutral gas molecules in the collimation chamber 1.3 are ionized in the ionization region. Among them, the region formed between the electron emission cold cathode assembly 2.2 and the anode plate 2.3 is the ionization region.

[0061] Among them, the cold cathode electron emitter 2.1.1 is a carbon nanotube electron emitter;

[0062] The electron-emitting cold cathode 2.1 can also adopt a planar or hemispherical structure; among them, the hemispherical structure can greatly enhance the electron focusing effect; a deflection voltage can be added between the collector 4.3 and the scanning grid 4.2, so that the movement direction of the emitted ions deflects by a certain fixed angle value between 0 degrees and 90 degrees, thereby further reducing the influence of background noise and expanding the detection lower limit. The field of view after gas collimation by the gas sampling and collimation sub-device is adjustable according to the detection requirements of the gas inflow.

[0063] As Figure 1 and 2 shown, the electron modulation electrode assembly 2.2 includes: a first cylindrical hollow structure electrode 2.2.1 and a second cylindrical hollow structure electrode 2.2.2;

[0064] The first cylindrical hollow structure electrode 2.2.1 is arranged below the second cylindrical hollow structure electrode 2.2.2, and the central axes of the first cylindrical hollow structure electrode 2.2.1 and the second cylindrical hollow structure electrode 2.2.2 coincide with the central axis of the electron-emitting cold cathode 2.1.

[0065] The cross-sections of the first cylindrical hollow structure electrode 2.2.1 and the second cylindrical hollow structure electrode 2.2.2 are both hollow rings, which can focus the electron beam current emitted by the cold cathode electron emitter 2.1.1.

[0066] The anode plate 2.3 is used to receive the electron beam current.

[0067] As Figure 1 and 2 shown, the ionization region electric field control sub-device 3 includes: a first ionization region shielding grid 3.1 and a second ionization region shielding grid 3.2;

[0068] The second ionization region shielding grid 3.2 is arranged in parallel on the inner wall of the top of the electron modulation electrode assembly 2.2, and the first ionization region shielding grid 3.1 is arranged in parallel on the inner wall between the electron modulation electrode assembly 2.2 and the second ionization region shielding grid 3.2;

[0069] The first ionization region shielding grid 3.1 and the second ionization region shielding grid 3.2 form a set of parallel shielding grids; shielding the electric field leaking from the electron-emitting cold cathode assembly into the ionization region, so that the initial state of the ionized ions and the incident neutral gas distribution is kept as consistent as possible.

[0070] The potentials of the first ionization region shielding grid 3.1 and the second ionization region shielding grid 3.2 are both set to 0V, and the electric potential at any point in the ionization region should be ≤ 0.005V;

[0071] As Figure 1 and 3As shown, the ion velocity analysis and collection sub-device 4 includes at least two analysis area shielding grids 4.1, at least four analysis area scanning grids 4.2, and a collector 4.3 arranged in sequence;

[0072] The at least two analysis area shielding grids 4.1, the at least four analysis area scanning grids 4.2, and the collector 4.3 are arranged in parallel;

[0073] Among them, the analysis area shielding grids 4.1 are arranged in parallel with each other, the analysis area scanning grids 4.2 are arranged in parallel with each other, and the collector 4.3 is arranged in parallel with each analysis area shielding grid 4.1 and each analysis area scanning grid 4.2 respectively.

[0074] The analysis area shielding grid 4.1 is used to block the leakage of the scanning voltage, make the electric field uniform, and shield the electrons incident from the outside; the analysis area scanning grid 4.2 obtains the energy distribution of the incident ions by changing the voltage; the collector 4.3 is used to collect ions.

[0075] Among them, the potential of the analysis area shielding grid 4.1 is set to 0V; the voltage change of the analysis area scanning grid 4.2 is 0 - 22V; the collector 4.3 is grounded.

[0076] The cold cathode electron emitter 2.1.1, the first cylindrical hollow structure electrode 2.2.1, the second cylindrical hollow structure electrode 2.2.2, the anode plate 2.3, the first ionization area shielding grid 3.1, the second ionization area shielding grid 3.2, the analysis area shielding grid 4.1, the analysis area scanning grid 4.2, and the collector 4.3 are all insulated with alumina ceramics, and an antioxidant film is plated on the inner wall of the cavity.

[0077] In the present invention, the central axes of the collimation chamber 1.3, the ionization area, and the ion velocity analysis and collection sub-device in the gas sampling and collimation sub-device 1 are located on the same straight line.

[0078] The present invention also provides a method for measuring the space atmospheric wind field of a spacecraft operating orbit, and this method includes:

[0079] The neutral gas molecules of the planetary upper atmosphere incident at high speed in the spacecraft operating orbit enter the air inlet 1.1 of the collimation chamber 1.3, and the neutral gas molecules of the planetary upper atmosphere enter the ionization area in the collimation chamber 1.3;

[0080] The cold cathode electron emitter 2.1.1 emits an electron beam, and through the electron modulation pole assembly 2.2 and the ionization area electric field control sub-device 3, adjusts the incident direction of the electron beam and vertically irradiates the electron beam into the ionization area;

[0081] Ionize the neutral gas molecules in the upper atmosphere of a planet using an electron beam. The ions after ionization are emitted while maintaining the distribution state of the incident neutral gas. The emitted ions pass through the analysis area shielding grid 4.1 and enter the analysis area scanning grid 4.2. By passing through the analysis area scanning grid 4.2, an ion current I is obtained, and the velocity V converted from the scanning voltage is used. g Then, by combining formulas (1) and (2), the central velocity V of the neutral gas molecules is inversely calculated. c and the thermal velocity V m :

[0082]

[0083] I = GeN i F(v) (2)

[0084] where F(v) is the distribution function related to the velocity V c of the neutral gas molecules and the thermal velocity V m of the neutral gas molecules; Ge is a constant factor; N i is the density of the neutral gas;

[0085] According to the calculated thermal velocity V m of the neutral gas molecules, the temperature of the neutral gas molecules can be obtained.

[0086] The neutral gas molecules in the upper atmosphere of a planet incident at high speed along the spacecraft's orbit enter the ionization region in the ionization region electric field control sub-device after passing through the gas sampling and collimation sub-device, and are ionized in the ionization region through the cold cathode electron emission and focusing sub-device. The ions after ionization are emitted while maintaining the distribution state of the incident neutral gas. The emitted ions are measured in the ion velocity analysis and collection sub-device to obtain parameters such as the velocity and temperature of the incident neutral gas molecules.

[0087] By setting the cold cathode electron emission and focusing sub-device and the ionization region electric field control sub-device, the present invention reduces the intensity and gradient of the ionization region electric field, greatly reduces the influence of the remaining electric field in the ionization region on the ion distribution after neutral gas ionization, and solves the problem of the remaining electric field; by collecting ions through the ion velocity analysis and collection sub-device and obtaining the distribution of ions and reducing the interference of background noise, the accuracy of the measurement of the spatial atmospheric wind field is greatly increased, thereby obtaining parameters such as the atmospheric wind speed and temperature in the space of the spacecraft's orbit, and realizing the high-precision measurement of the spatial atmospheric wind field in the spacecraft's orbit; the measurement device of the present invention has a wide range of application requirements in the field of the Earth's space and the exploration of extraterrestrial planets.

[0088] 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 embodiments, those of ordinary skill in the art should understand that any modification or equivalent replacement of the technical solutions of the present invention does not depart from the spirit and scope of the technical solutions of the present invention, and they should all be covered within the scope of the claims of the present invention.

Claims

1. A device for measuring the spatial atmospheric wind field of a spacecraft's operating orbit, characterized in that, the device includes: a gas sampling and collimation sub-device (1), a cold cathode electron emission and focusing sub-device (2), an ionization region electric field control sub-device (3), an ion velocity analysis and collection sub-device (4), and a device housing (5); The gas sampling and collimation sub-device (1), the cold cathode electron emission and focusing sub-device (2), the ionization region electric field control sub-device (3), and the ion velocity analysis and collection sub-device (4) are arranged inside the device housing (5); The gas sampling and collimation sub-device (1) is arranged on the cold cathode electron emission and focusing sub-device (2), and the ion velocity analysis and collection sub-device (4) is sequentially connected to one side of the two; The ionization region electric field control sub-device (3) is arranged inside the cold cathode electron emission and focusing sub-device (2); The cold cathode electron emission and focusing sub-device (2) includes: an electron emission cold cathode (2.1), an electron modulation electrode assembly (2.2), and an anode plate (2.3); The electron emission cold cathode (2.1) adopts a planar or hemispherical structure; The electron modulation electrode assembly (2.2) is arranged above the electron emission cold cathode (2.1); the anode plate (2.3) is arranged above the electron modulation electrode assembly (2.2); the electron modulation electrode assembly (2.2) is located between the electron emission cold cathode (2.1) and the anode plate (2.3), and the three are arranged in parallel; The ion velocity analysis and collection sub-device (4) includes two analysis region shielding grids (4.1), four analysis region scanning grids (4.2), and a collection electrode (4.3) arranged in sequence; The two analysis region shielding grids (4.1), the four analysis region scanning grids (4.2), and the collection electrode (4.3) are arranged in parallel; The potential of the analysis region shielding grid (4.1) is set to 0V; the voltage of the analysis region scanning grid (4.2) varies from 0 to 22V; the collection electrode (4.3) is grounded; There is a deflection voltage between the collection electrode (4.3) and the scanning grid (4.2), so that the movement direction of the outgoing ions deflects by a set angle value between 0 degrees and 90 degrees.

2. The device for measuring the spatial atmospheric wind field of a spacecraft's operating orbit according to claim 1, characterized in that, the gas sampling and collimation sub-device (1) includes: an air inlet (1.1), an air outlet (1.2), and a collimation chamber (1.3); The collimation chamber (1.3) is a cylindrical cavity, and the air inlet (1.1) and the air outlet (1.2) are respectively arranged at both ends of the cylindrical cavity.

3. The device for measuring the spatial atmospheric wind field of a spacecraft's operating orbit according to claim 1, characterized in that, the electron emission cold cathode (2.1) includes: a cold cathode electron emitter (2.1.1) and a frame support (2.1.2); The cold cathode electron emitter (2.1.1) has a cylindrical structure, the cross-section of the frame support (2.1.2) has an I-shaped structure, and the cold cathode electron emitter (2.1.1) is arranged inside the frame support (2.1.2).

4. The device for measuring the spatial atmospheric wind field of a spacecraft's operating orbit according to claim 1, characterized in that, The electronic modulation electrode assembly (2.2) includes: a first cylindrical hollow structure electrode (2.2.1) and a second cylindrical hollow structure electrode (2.2.2); The first cylindrical hollow structure electrode (2.2.1) is disposed below the second cylindrical hollow structure electrode (2.2.2), and the central axes of the first cylindrical hollow structure electrode (2.2.1) and the second cylindrical hollow structure electrode (2.2.2) coincide with the central axis of the electron emission cold cathode (2.1).

5. The spacecraft operating orbit space atmospheric wind field measuring device according to claim 1, characterized in that the ionization region electric field control sub-device (3) includes: a first ionization region shielding grid (3.1) and a second ionization region shielding grid (3.2); The second ionization region shielding grid (3.2) is disposed parallel to the inner wall at the top end of the electronic modulation electrode assembly (2.2), and the first ionization region shielding grid (3.1) is disposed parallel to the inner wall between the electronic modulation electrode assembly (2.2) and the second ionization region shielding grid (3.2).

6. A method for measuring the space atmospheric wind field of a spacecraft operating orbit, which is implemented based on the spacecraft operating orbit space atmospheric wind field measuring device according to any one of claims 1-5 above, and the method includes: The neutral gas molecules of the planetary upper atmosphere incident at high speed in the spacecraft operating orbit enter the air inlet (1.1) of the collimation chamber (1.3), and the neutral gas molecules of the planetary upper atmosphere enter the ionization region in the collimation chamber (1.3); The cold cathode electron emitter (2.1.1) emits an electron beam, and adjusts the incident direction of the electron beam through the electronic modulation electrode assembly (2.2) and the ionization region electric field control sub-device (3), and vertically irradiates the electron beam into the ionization region; Ionize neutral gas molecules in the upper atmosphere of a planet using an electron beam. After ionization, the ions are emitted while maintaining the distribution state of the incident neutral gas. The emitted ions pass through the analysis area shielding grid (4.1) and enter the analysis area scanning grid (4.2). By passing through the analysis area scanning grid (4.2), an ion current I is obtained, and the velocity V converted from the scanning voltage is used g , and then, in combination with formulas (1) and (2), the central velocity V of the neutral gas molecules is inversely calculated c and the thermal velocity V m : I = GeN i F(v) (2) where F(v) is the distribution function related to the velocity V of neutral gas molecules c and the thermal velocity V of neutral gas molecules m ; Ge is a constant factor; N i is the density of the neutral gas; According to the calculated thermal velocity V of the neutral gas molecules m , the temperature of the neutral gas molecules can be obtained.

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