Aviation absolute gravity measuring device with common-base sensing multiplexing cooperative stability

Abstract

The invention relates to an aviation absolute gravity measuring device with co-base sensing multiplexing cooperative stabilization. The aviation absolute gravity measuring device comprises a quantum gravity system controller, an inertial stabilization platform and a gravimeter probe mounted on the inertial stabilization platform, the gravimeter probe captures rubidium atoms and performs gravity measurement, the inertial stabilization platform corrects the measurement result of the gravimeter probe according to the acceleration and the attitude position of the aircraft in real time, and the quantum gravity system controller corrects the measurement result of the gravimeter probe according to the attitude position and the acceleration of the aircraft, so that the gravity is accurately measured in an aviation environment.

Description

Technical Field

[0001] The present invention belongs to the field of quantum sensing technology, and in particular relates to an aviation absolute gravity measurement device with common base sensing multiplexing and collaborative stability. Background Art

[0002] Airborne geophysical surveys use aircraft and other aerial vehicles as physical exploration instruments to measure, collect, and process dynamic geophysical field information while in flight. Compared to traditional ground-based surveys, this method is faster, more efficient, and less affected by topography, making it particularly suitable for surveys over large areas with complex terrain.

[0003] The Earth's gravity field directly reflects environmental characteristics such as geological structure, crustal composition, and topography, providing crucial fundamental and strategic geophysical information. Therefore, airborne gravity measurement is a key measurement method in airborne geophysical exploration. Measuring the Earth's gravity field through airborne gravity measurement provides crucial supporting data for resource exploration, energy security, deep earth exploration, ocean monitoring, and national defense development, and holds significant strategic significance.

[0004] Currently, the most practical airborne gravity measurement instruments in China are relative gravity instruments, represented by the SGA-WZ02 strapdown airborne gravity measurement system. At a spatial resolution of 3 km, their internal accuracy reaches ±0.6 mGal. Because relative gravity instruments rely on base point calibration and cannot instantly measure the absolute value of gravitational acceleration, long-term static observations and evaluations are required before and after test flights to eliminate the inevitable static drift of relative gravity instruments, which significantly limits the efficiency of airborne gravity measurements.

[0005] The quantum absolute gravimeter is a new type of gravity measurement instrument that has developed rapidly over the past three decades. Based on the quantum properties of microscopic particles, it exploits the interference phenomenon of cold atomic matter waves to achieve high-precision absolute gravity measurements. Its theoretical upper limit for measurement resolution far exceeds that of traditional instruments. Furthermore, compared to traditional relative gravity measurement techniques, the quantum absolute gravimeter can measure the absolute value of gravitational acceleration in real time, significantly reducing the impact of instrument drift. This allows for efficient and accurate measurement of the Earth's gravitational field distribution. Therefore, the cold atom absolute gravimeter is widely considered to be a representative example of the next generation of quantum precision measurement instruments, and its technological development has garnered widespread attention.

[0006] However, most quantum gravimeters are limited to operating in specific static laboratory environments and are unable to meet the requirements of dynamic aviation measurements. To realize absolute gravity measurement applications in aviation environments, innovative technologies and structural designs are urgently needed to control the direction of gravity sensing in dynamic environments and extract gravity signals in high-vibration environments. This will not only expand the application range of cold atom absolute gravimeters but also open up the possibility of high-precision gravity measurements in more fields. The airborne quantum gravimeter systems developed by NASA, ONERA, and Exail in France have achieved this goal to a certain extent, but due to technical sensitivity, further disclosure of the working mechanism and specific structure has been kept. Summary of the Invention

[0007] In response to the above-mentioned problems, the present invention proposes an aviation absolute gravity measurement device with co-base sensing multiplexing and collaborative stability. The concept is to add a stabilizing platform and a quantum gravity system controller to the existing cold atom gravimeter to correct the gravity measurement results according to the aircraft's attitude position and acceleration, thereby accurately measuring gravity in an aviation environment.

[0008] The common base sensing multiplexing and collaboratively stabilized aviation absolute gravity measurement device of the present invention comprises a quantum gravity system controller 300, an inertial stabilization platform 200, and a gravimeter probe 100 mounted on the inertial stabilization platform 200;

[0009] The gravimeter probe 100 includes a magnetic shielding layer 161, and a gravimeter optical path and a vertical vacuum chamber 101 are arranged inside the magnetic shielding layer 161; the vacuum chamber 101 is wrapped with a directional magnetic field coil 151; the gravimeter optical path is connected to the probe input and output bus 181 outside the magnetic shielding layer, and emits initial Raman light 131 downward from the top of the vacuum chamber 101 along the longitudinal center axis of the vacuum chamber 101; the gravimeter optical path emits cooling light 111 from the side of the vacuum chamber to the vacuum chamber 101, which intersects at a point in the vacuum chamber 101; the cooling light 111 includes a first cooling light 111a, a second cooling light 111b, a third cooling light 111c, a fourth cooling light 111d, a fifth cooling light 111e and a sixth cooling light 111f; the definition of the The intersection of the cooling light is the center of the MOT; a first magnetic field coil 112a and a second magnetic field coil 112d are installed on either side of the MOT center in the longitudinal direction, forming a MOT for cooling atoms; a clearing light 121 and a microwave radiating device 122 are provided laterally below the MOT center; a first fluorescence collecting device 142a and a second fluorescence collecting device 142b are provided on one longitudinal side of the vacuum chamber 101, located below the microwave radiating device 122; a single-state detection light 141a and a binary detection light 141b emitted by the gravimeter optical path pass laterally through the vacuum chamber 101 from the same height as the first fluorescence collecting device 142a and the second fluorescence collecting device 142b; a through hole is provided at the bottom of the magnetic shielding layer 161 for the initial Raman light 131a to pass through;

[0010] The inertial stabilization platform 200 includes a platform mounting frame 211, an outer frame rotation motor 212a is provided on the inner wall of the platform mounting frame 211; the outer frame rotation motor 212a is connected to the platform outer rotating frame 213a and can rotate the platform outer rotating frame 213a along a transverse rotation axis; the inner wall of the platform outer rotating frame 213a is fixedly connected to the inner frame rotation motor 212b; the inner frame rotation motor 212b is connected to the platform inner rotating frame 213b and can rotate the platform inner rotating frame 213b along a longitudinal rotation axis; the inner wall of the platform inner rotating frame 213b is fixedly connected to the base 214, the lower part of the base 214 is connected to the integrated sensor module 220, and the upper part of the base 214 is connected to the magnetic shielding layer 161 of the gravimeter probe 100;

[0011] The integrated sensor module 220 includes a high-precision accelerometer 221. A polarization reflection device 132 is provided on the top of the high-precision accelerometer 221. The bottom of the high-precision accelerometer 221 is connected to a conventional IMU unit 222. The polarization reflection device 132 reflects the initial Raman light 131a along the original path to form a reverse Raman light 131b opposite to the initial Raman light 131a.

[0012] The gravity measurement process of the gravimeter probe 100 is as follows:

[0013] 1. Atom capture: Rubidium atoms are contained in the vacuum chamber 101. A magneto-optical trap consisting of six beams of cooling light 111, a first magnetic field coil 112a, and a second magnetic field coil 112b is continuously turned on for a period of time to capture a sufficient number of rubidium atomic clusters 113 from the vacuum background.

[0014] 2. Atom cooling: After the capture is completed, the power supply of the first magnetic field coil 112a and the second magnetic field coil 112b is turned off, and the detuning and power of the six cooling beams 111 are reduced to perform polarization gradient cooling, cooling the temperature of the trapped atomic cluster to the microkelvin level, completing the cooling process of the atomic cluster;

[0015] 3. Energy state selection: The six cooling beams 111 are turned off, allowing the rubidium atoms to fall freely. Current is passed through the directional magnetic field coil 151 to generate a quantized axial magnetic field. Microwaves are then applied to select the target atomic state, and the purge beam 121 is turned on to purge atoms from the remaining energy states, completing the atomic energy state selection.

[0016] 4. Matter wave interference: After the energy state selection is completed, the rubidium atoms open the vertical initial Raman light 131a and the reflected Raman light 131b during their continuous free fall, interacting with the rubidium atoms to carry out matter wave interference.

[0017] 5. Normalized detection: After the interference is completed, the binary detection light 141b and the single-state detection light 141a are turned on in sequence to make the falling atoms emit fluorescence. The binary and single-state fluorescence signals are collected respectively by the binary detection light 141b and the single-state detection light 141a to obtain the trend signal of the atomic population change in the two energy states during the interference process.

[0018] 6. Obtaining the initial value of gravity acceleration: Obtain the initial value signal of gravity acceleration based on the detected population phase information.

[0019] The quantum gravity system controller 300 is connected to the absolute gravimeter probe 100 via the probe input / output bus 181 and to the inertial stabilization platform 200 via the platform input / output bus 231. The quantum gravity system controller 300 includes a control host computer 311, a laser control module 321, a laser light source module 331, a digital acquisition and recording module 341, a frequency generation and control module 361, an electronic control module 371, and a platform control module 381. The platform control module 381 and the control host computer 311 are connected to a satellite navigation system 241 via a satellite signal line 242. The satellite navigation system 241 is installed on the top of the external aircraft shell 600. The high-precision accelerometer 221 collects the three-axis acceleration of the gravimeter probe 100, and the conventional IMU unit 222 collects the three-axis angular velocity of the gravimeter probe 100.

[0020] The control host computer 311 is used to operate and control different modules, process information from each module, and ultimately output the gravity value; the laser control module 321 is used to implement the optical path and obtain the required frequency and power; the laser light source module 331 is used to provide one or two lasers, which are directly input into the laser control module 321; the analog / digital acquisition and recording module 341 is used to receive and record various signals; the temperature feedback controller 351 is used to maintain the temperature of the laser control module 321, ensure the stability of its working environment, and prevent drift; the frequency generation and control module 361 is used to provide all the reference frequencies required to implement the physical process; and the electronic control module 371 is used to provide power and implement timing control.

[0021] The platform control module 381 is connected to the integrated sensor module 220 via the platform input / output bus 231 and receives the three-axis acceleration signal from the high-precision accelerometer 221 and the three-axis angular velocity signal from the conventional IMU unit 222. The platform control module 381 is connected to the satellite navigation system 241 via the satellite signal line 242 and receives the aircraft position information sent by the satellite navigation system 241. After the platform control module 381 calculates the acceleration signal, rotation signal, and aircraft position information, it outputs control instructions to the outer frame rotation motor 212a and the inner frame rotation motor 212b via the platform input / output bus 231, thereby rotating the platform outer rotating frame 213a and the platform inner rotating frame 213b to keep the direction of the gravimeter probe 100 consistent with the direction of gravity acceleration.

[0022] More specifically, the laser control module 321 is connected to the temperature feedback controller 351 , which receives an ambient temperature signal of the laser control module 321 and inputs a feedback value to the laser control module 321 to keep the ambient temperature of the laser control module 321 stable.

[0023] More specifically, a plurality of passive vibration isolation devices 401 are installed at the bottom of the quantum gravity system controller 300 , and the passive vibration isolation devices 401 are fixedly connected to the bottom 500 of the cabin.

[0024] During operation, the laser light source module 331 transmits several paths of initial laser light to the laser control module 321, the frequency generation and control module 361 inputs a reference frequency to the laser control module 321 and the digital acquisition and recording module 341, and the electronic control module 371 supplies power to the laser control module 321 and the digital acquisition and recording module 341 and transmits a timing control signal; the laser control module 321 splits the initial laser light according to the reference frequency and the timing control signal and performs frequency and phase locking to generate the first cooling light 111a, the second cooling light 111b, the third cooling light 111c, the fourth cooling light 111d, the fifth cooling light 111e, the sixth cooling light 111f, the clearing light 121, the initial Raman light 131a, the first-state detection light 141a and the second-state detection light 141b and transmits them to the gravimeter optical path through the probe input and output bus 181; the electronic control module 371 transmits the initial Raman light to the gravimeter optical path through the probe input and output bus 181; the electronic control module 371 transmits the initial Raman light to the gravimeter optical path through the probe input and output bus 181; the electronic control module 371 transmits the initial Raman light to the gravimeter optical path through the probe input and output bus 181 Line 181 supplies power to the first magnetic field coil 112a and the second magnetic field coil 112d, causing the first magnetic field coil 112a and the second magnetic field coil 112d to generate a magnetic field; the electronic control module 371 supplies power to the directional magnetic field coil 151 through the probe input and output bus 181, causing the directional magnetic field coil 151 to generate a quantized axial magnetic field; the first fluorescence collection device 142a and the second fluorescence collection device 142b transmit the atomic interference signal to the digital acquisition and recording module 341 through the probe input and output bus 181; the host computer 311 is controlled to receive the three-axis acceleration signal, three-axis angular velocity signal collected by the platform control module 381 and the aircraft position information collected by the satellite navigation system 241, as well as the atomic interference signal recorded by the digital acquisition and recording module 341, and the atomic interference signal is corrected according to the three-axis acceleration signal, three-axis angular velocity signal and aircraft position information to calculate the aviation absolute gravitational acceleration.

[0025] The beneficial effects produced by the present invention are:

[0026] 1. Through the combined action of the inertial stabilization platform 200 and the passive vibration isolation device 401, the quantum absolute gravity measurement system can perform absolute gravity acceleration measurement in an aviation environment, ensuring that the gravity measurement direction maintains a high degree of consistency with the Earth's gravity acceleration direction under dynamic conditions, overcoming the measurement reference offset caused by aircraft attitude disturbances and achieving stable capture of the gravity vector under flight conditions.

[0027] 2. An integrated sensing module: one channel implements attitude control of the inertial stabilization platform where the gravimeter probe is located, and the other channel transmits aircraft position information, the gravimeter probe's three-axis acceleration, and three-axis angular velocity to the host computer, thereby performing vibration compensation when calculating the absolute gravity acceleration of aviation, thereby solving the parameter asynchrony problem inherent in the split design.

[0028] 3. The integrated mounting structure on a common base effectively reduces the consistency error in carrier inclination measurement. This simplifies the complex transfer function modeling required to compensate for mounting offset in traditional solutions, unifies the solution model, and through the spatiotemporal alignment and fusion of motion parameters and vibration data, reduces the number of levels in the error transmission chain and improves signal and data authenticity. Ultimately, a common base, sensor-reuse, and collaboratively stable airborne absolute gravity measurement system is achieved. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 This is a structural diagram of an aviation absolute gravity measurement device with common base sensing multiplexing and collaborative stability according to the present invention.

[0030] Figure 2a It is a front view of the gravimeter probe of the present invention.

[0031] Figure 2b It is a side view of the gravimeter probe of the present invention.

[0032] Figure 3a It is a structural diagram of the inertial stabilization platform of the present invention.

[0033] Figure 3b This is a detailed diagram of the integrated sensing module of the present invention.

[0034] Figure 4 It is a timing diagram of the operation of the gravimeter probe of the present invention.

[0035] Figure 5 It is a schematic flow chart of the initial gravity value measurement of the gravimeter probe of the present invention.

[0036] Figure 6 This is a complete flow chart of the present invention for measuring aviation absolute gravitational acceleration.

[0037] Figure 7 This is a control flow chart of a common base sensing multiplexing and collaboratively stable aviation absolute gravity measurement device of the present invention. DETAILED DESCRIPTION

[0038] The following describes the specific implementation of the embodiment of the present invention in detail with reference to the accompanying drawings. It should be understood that the specific implementation described herein is only used to illustrate and explain the embodiment of the present invention and is not used to limit the embodiment of the present invention.

[0039] In the description of the present invention, it should 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" and the like to indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying 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.

[0040] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "plurality" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0041] In the present invention, unless otherwise specified or limited, the terms "installed," "connected," "connect," "fixed," etc. should be understood in a broad sense. For example, they can refer to fixed connection, detachable connection, or integration; mechanical connection, electrical connection, or communication; direct connection or indirect connection through an intermediate medium; internal communication between two elements or interaction between two elements, unless otherwise specified. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0042] In the present invention, unless otherwise expressly specified or limited, when a first feature is "above" or "below" a second feature, it may mean that the first and second features are in direct contact, or that the first and second features are in indirect contact through an intermediary. Furthermore, when a first feature is "above," "above," or "above" a second feature, it may mean that the first feature is directly above or diagonally above the second feature, or simply means that the first feature is at a higher level than the second feature. When a first feature is "below," "below," or "below" a second feature, it may mean that the first feature is directly below or diagonally below the second feature, or simply means that the first feature is at a lower level than the second feature.

[0043] In the description of this specification, the reference terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" 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 specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and features of different embodiments or examples without contradiction.

[0044] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with exemplary embodiments.

[0045] according to Figure 1 The common base sensing multiplexing and collaboratively stabilized aviation absolute gravity measurement device of the present invention comprises a quantum gravity system controller 300, an inertial stabilization platform 200, and a gravimeter probe 100 mounted on the inertial stabilization platform 200;

[0046] according to Figure 2a-2b The gravimeter probe 100 includes a magnetic shielding layer 161, and a gravimeter optical path and a vertical vacuum chamber 101 are arranged inside the magnetic shielding layer 161; the vacuum chamber 101 is wrapped with a directional magnetic field coil 151; the gravimeter optical path is connected to the probe input and output bus 181 outside the magnetic shielding layer, and emits an initial Raman light 131 downward from the top of the vacuum chamber 101 along the longitudinal center axis of the vacuum chamber 101; the gravimeter optical path emits cooling light (111) from the side of the vacuum chamber to the vacuum chamber 101, which intersects at a point in the vacuum chamber 101; the cooling light (111) includes a first cooling light 111a, a second cooling light 111b, a third cooling light 111c, a fourth cooling light 111d, a fifth cooling light 111e and a sixth cooling light 111f; the directional magnetic field coil 151 is wrapped outside the vacuum chamber 10 ... The intersection of the cooling light is the center of the magneto-optical trap; a first magnetic field coil 112a and a second magnetic field coil 112d are respectively installed on both longitudinal sides of the center of the magneto-optical trap to form a magneto-optical trap for cooling atoms; a clearing light 121 and a microwave radiating device 122 are provided laterally below the center of the magneto-optical trap; a first fluorescence collecting device 142a and a second fluorescence collecting device 142b are provided on one longitudinal side of the vacuum cavity 101 and are located below the microwave radiating device 122; a single-state detection light 141a and a binary detection light 141b emitted by the gravimeter optical path respectively pass through the vacuum cavity 101 laterally from the same height as the first fluorescence collecting device 142a and the second fluorescence collecting device 142b; a through hole is provided at the bottom of the magnetic shielding layer 161 for the initial Raman light 131a to pass through;

[0047] according to Figure 3aThe inertial stabilization platform 200 includes a platform mounting frame 211, and an outer frame rotation motor 212a is provided on the inner wall of the platform mounting frame 211; the outer frame rotation motor 212a is connected to the platform outer rotation frame 213a and can rotate the platform outer rotation frame 213a along a transverse rotation axis; the inner wall of the platform outer rotation frame 213a is fixedly connected to the inner frame rotation motor 212b; the inner frame rotation motor 212b is connected to the platform inner rotation frame 213b and can rotate the platform inner rotation frame 213b along a longitudinal rotation axis; the inner wall of the platform inner rotation frame 213b is fixedly connected to the base 214, the lower part of the base 214 is connected to the integrated sensor module 220, and the upper part of the base 214 is connected to the magnetic shielding layer 161 of the gravimeter probe 100;

[0048] according to Figure 3b The integrated sensing module 220 includes a high-precision accelerometer 221. A polarization reflection device 132 is provided on the top of the high-precision accelerometer 221. The bottom of the high-precision accelerometer 221 is connected to a conventional IMU unit 222. The polarization reflection device 132 reflects the initial Raman light 131a along the original path to form a reverse Raman light 131b opposite to the initial Raman light 131a.

[0049] according to Figure 4-Figure 5 , the gravity measurement process of the gravimeter probe 100 is as follows:

[0050] 1. Atom capture: Rubidium atoms are contained in the vacuum chamber 101. A magneto-optical trap consisting of six beams of cooling light 111, a first magnetic field coil 112a, and a second magnetic field coil 112b is continuously turned on for a period of time to capture a sufficient number of rubidium atomic clusters 113 from the vacuum background.

[0051] 2. Atom cooling: After the capture is completed, the power supply of the first magnetic field coil 112a and the second magnetic field coil 112b is turned off, and the detuning and power of the six cooling beams 111 are reduced to perform polarization gradient cooling, cooling the temperature of the trapped atomic cluster to the microkelvin level, completing the cooling process of the atomic cluster;

[0052] 3. Energy state selection: The six cooling beams 111 are turned off, allowing the rubidium atoms to fall freely. Current is passed through the directional magnetic field coil 151 to generate a quantized axial magnetic field. Microwaves are then applied to select the target atomic state, and the purge beam 121 is turned on to purge atoms from the remaining energy states, completing the atomic energy state selection.

[0053] 4. Matter wave interference: After the energy state selection is completed, the rubidium atoms open the vertical initial Raman light 131a and the reflected Raman light 131b during their continuous free fall, interacting with the rubidium atoms to carry out matter wave interference.

[0054] 5. Normalized detection: After the interference is completed, the binary detection light 141b and the single-state detection light 141a are turned on in sequence to make the falling atoms emit fluorescence. The binary and single-state fluorescence signals are collected respectively by the binary detection light 141b and the single-state detection light 141a to obtain the trend signal of the atomic population change in the two energy states during the interference process.

[0055] 6. Obtaining the initial value of gravity acceleration: Obtain the initial value signal of gravity acceleration based on the detected population phase information.

[0056] The quantum gravity system controller 300 is connected to the absolute gravimeter probe 100 via the probe input / output bus 181 and to the inertial stabilization platform 200 via the platform input / output bus 231. The quantum gravity system controller 300 includes a control host computer 311, a laser control module 321, a laser light source module 331, a digital acquisition and recording module 341, a frequency generation and control module 361, an electronic control module 371, and a platform control module 381. The platform control module 381 and the control host computer 311 are connected to a satellite navigation system 241 via a satellite signal line 242. The satellite navigation system 241 is installed on the top of the external aircraft shell 600. The high-precision accelerometer 221 collects the three-axis acceleration of the gravimeter probe 100, and the conventional IMU unit 222 collects the three-axis angular velocity of the gravimeter probe 100.

[0057] according to Figure 6-Figure 7 The platform control module 381 is connected to the integrated sensor module 220 through the platform input / output bus 231, and receives the three-axis acceleration signal of the high-precision accelerometer 221 and the three-axis angular velocity signal recorded by the conventional IMU unit 222; the platform control module 381 is connected to the satellite navigation system 241 through the satellite signal line 242, and receives the aircraft position information sent by the satellite navigation system 241; after the platform control module 381 calculates the three-axis acceleration signal, the three-axis angular velocity signal and the aircraft position information together, it outputs a control instruction to the outer frame rotation motor 212a and the inner frame rotation motor 212b through the platform input / output bus 231, thereby rotating the platform outer rotating frame 213a and the platform inner rotating frame 213b, so that the direction of the gravimeter probe 100 remains the same as the direction of gravity acceleration;

[0058] In some embodiments, the laser control module 321 is connected to a temperature feedback controller 351 , which receives an ambient temperature signal from the laser control module 321 and inputs a feedback value to the laser control module 321 to keep the ambient temperature of the laser control module 321 stable.

[0059] In some embodiments, a plurality of passive vibration isolation devices 401 are installed at the bottom of the quantum gravity system controller 300 , and the passive vibration isolation devices 401 are fixedly connected to the bottom 500 of the cabin.

[0060] During operation, the laser light source module 331 transmits several paths of initial laser light to the laser control module 321, the frequency generation and control module 361 inputs a reference frequency to the laser control module 321 and the digital acquisition and recording module 341, and the electronic control module 371 supplies power to the laser control module 321 and the digital acquisition and recording module 341 and transmits a timing control signal; the laser control module 321 splits the initial laser light according to the reference frequency and the timing control signal and performs frequency and phase locking to generate the first cooling light 111a, the second cooling light 111b, the third cooling light 111c, the fourth cooling light 111d, the fifth cooling light 111e, the sixth cooling light 111f, the clearing light 121, the initial Raman light 131a, the first-state detection light 141a and the second-state detection light 141b and transmits them to the gravimeter optical path through the probe input and output bus 181; the electronic control module 371 transmits the initial Raman light to the gravimeter optical path through the probe input and output bus 181; the electronic control module 371 transmits the initial Raman light to the gravimeter optical path through the probe input and output bus 181; the electronic control module 371 transmits the initial Raman light to the gravimeter optical path through the probe input and output bus 181 Line 181 supplies power to the first magnetic field coil 112a and the second magnetic field coil 112d, causing the first magnetic field coil 112a and the second magnetic field coil 112d to generate a magnetic field; the electronic control module 371 supplies power to the directional magnetic field coil 151 through the probe input and output bus 181, causing the directional magnetic field coil 151 to generate a quantized axial magnetic field; the first fluorescence collection device 142a and the second fluorescence collection device 142b transmit the atomic interference signal to the digital acquisition and recording module 341 through the probe input and output bus 181; the host computer 311 is controlled to receive the three-axis acceleration signal, three-axis angular velocity signal collected by the platform control module 381 and the aircraft position information collected by the satellite navigation system 241, as well as the atomic interference signal recorded by the digital acquisition and recording module 341, and the atomic interference signal is corrected according to the three-axis acceleration signal, three-axis angular velocity signal and aircraft position information to calculate the aviation absolute gravitational acceleration.

[0061] The above embodiments are only preferred embodiments of the technical solution of the present invention and are not intended to limit the scope of protection of the present invention. Any equivalent modifications or adjustments based on the design gist and principles of the present invention fall within the scope of the claims of the present invention.

Claims

1. An aviation absolute gravity measurement device with shared base sensor multiplexing and collaborative stability, characterized by: It comprises a quantum gravity system controller (300), an inertial stabilization platform (200), and a gravimeter probe (100) mounted on the inertial stabilization platform (200); The gravimeter probe (100) comprises a magnetic shielding layer (161), wherein a gravimeter optical path and a vertical vacuum chamber (101) are provided inside the magnetic shielding layer (161); a directional magnetic field coil (151) is wrapped outside the vacuum chamber (101); the gravimeter optical path is connected to a probe input / output bus (181) outside the magnetic shielding layer, and emits initial Raman light (131a) downward from the top of the vacuum chamber (101) along the longitudinal center axis of the vacuum chamber (101); The gravimeter optical path emits cooling light (111) from the side of the vacuum chamber to the vacuum chamber (101) and converges at a point of the vacuum chamber (101); the cooling light (111) includes a first cooling light (111a), a second cooling light (111b), a third cooling light (111c), a fourth cooling light (111d), a fifth cooling light (111e) and a sixth cooling light (111f); the intersection point of the cooling light (111) is defined as the center of the magneto-optical trap; a first magnetic field coil (112a) and a second magnetic field coil (112d) are respectively installed on both longitudinal sides of the center of the magneto-optical trap to form a magneto-optical trap for cooling atoms; the magneto-optical trap is provided with a plurality of cooling light beams, each of which is a plurality of cooling light beams. A clearing light (121) and a microwave radiating device (122) are provided laterally below the center of the well; a first fluorescence collecting device (142a) and a second fluorescence collecting device (142b) are provided on a longitudinal side of the vacuum cavity (101) and are located below the microwave radiating device (122); a single-state detection light (141a) and a second-state detection light (141b) emitted by the gravimeter optical path respectively pass through the vacuum cavity (101) laterally from the same height as the first fluorescence collecting device (142a) and the second fluorescence collecting device (142b); and a through hole for the initial Raman light (131a) to pass through is provided at the bottom of the magnetic shielding layer (161); The inertial stabilization platform (200) comprises a platform installation frame (211), an outer frame rotating motor (212a) is provided on the inner wall of the platform installation frame (211); the outer frame rotating motor (212a) is connected to the platform outer rotating frame (213a) and can rotate the platform outer rotating frame (213a) along a transverse rotating axis; the inner wall of the platform outer rotating frame (213a) is fixedly connected to the inner frame rotating motor (212b); the inner frame rotating motor (212b) is connected to the platform inner rotating frame (213b) and can rotate the platform inner rotating frame (213b) along a longitudinal rotating axis; the inner wall of the platform inner rotating frame (213b) is fixedly connected to a base (214); the lower part of the base (214) is connected to an integrated sensor module (220), and the upper part of the base (214) is connected to a magnetic shielding layer (161) of a gravimeter probe (100); The integrated sensing module (220) includes a high-precision accelerometer (221), a polarization reflection device (132) is provided on the top of the high-precision accelerometer (221), and a conventional IMU unit (222) is connected to the bottom of the high-precision accelerometer (221); the polarization reflection device (132) reflects the initial Raman light (131a) along the original path to form reverse Raman light (131b) opposite to the initial Raman light (131a); The quantum gravity system controller (300) is connected to the absolute gravimeter probe (100) via a probe input / output bus (181) and is connected to the inertial stabilization platform (200) via a platform input / output bus (231); the quantum gravity system controller (300) comprises a control host computer (311), a laser control module (321), a laser light source module (331), a digital acquisition and recording module (341), a frequency generation and control module (361), an electronic control module (371) and a platform control module (381); the platform control module (381) and the control host computer (311) are connected to a satellite navigation system (241) via a satellite signal line (242); the satellite navigation system (241) is installed on the top of an external aircraft shell (600); The high-precision accelerometer (221) collects the three-axis acceleration of the gravimeter probe (100), and the conventional IMU unit (222) collects the three-axis angular velocity of the gravimeter probe (100); The platform control module (381) is connected to the integrated sensor module (220) via the platform input / output bus (231), and receives the three-axis acceleration signal of the high-precision accelerometer (221) and the three-axis angular velocity signal of the conventional IMU unit (222); the platform control module (381) is connected to the satellite navigation system (241) via the satellite signal line (242), and receives the aircraft position information sent by the satellite navigation system (241); the platform control module (381) calculates the acceleration signal, the rotation signal and the aircraft attitude position information together, and outputs a control instruction to the outer frame rotation motor (212a) and the inner frame rotation motor (212b) via the platform input / output bus (231), thereby rotating the platform outer rotation frame (213a) and the platform inner rotation frame (213b), so that the direction of the gravimeter probe (100) remains the same as the direction of gravity acceleration; The laser light source module (331) transmits a plurality of initial laser beams to the laser control module (321); the frequency generation and control module (361) inputs a reference frequency to the laser control module (321) and the digital acquisition and recording module (341); the electronic control module (371) supplies power to the laser control module (321) and the digital acquisition and recording module (341) and transmits a timing control signal; the laser control module (321) splits the initial laser beam and performs frequency control according to the reference frequency and the timing control signal. The first cooling light (111a), the second cooling light (111b), the third cooling light (111c), the fourth cooling light (111d), the fifth cooling light (111e), the sixth cooling light (111f), the cleaning light (121), the initial Raman light (131a), the first-state detection light (141a) and the second-state detection light (141b) are generated and transmitted to the gravimeter optical path through the probe input and output bus (181); the electronic control module (371) generates the first cooling light (111a), the second cooling light (111b), the third cooling light (111c), the fourth cooling light (111d), the fifth cooling light (111e), the sixth cooling light (111f), the cleaning light (121), the initial Raman light (131a), the first-state detection light (141a) and the second-state detection light (141b) through the probe input and output bus (181); The output bus (181) supplies power to the first magnetic field coil (112a) and the second magnetic field coil (112d), so that the first magnetic field coil (112a) and the second magnetic field coil (112d) generate a magnetic field; the electronic control module (371) supplies power to the directional magnetic field coil (151) through the probe input and output bus (181), so that the directional magnetic field coil (151) generates a quantized axial magnetic field; the first fluorescence collection device (142a) and the second fluorescence collection device (142b) transmit the atomic interference signal to the digital acquisition and recording module (341) through the probe input and output bus (181); the host computer (311) is controlled to receive the three-axis acceleration signal and the three-axis angular velocity signal collected by the platform control module (381) and the aircraft position information collected by the satellite navigation system (241) as well as the atomic interference signal recorded by the digital acquisition and recording module (341), and the atomic interference signal is corrected according to the three-axis acceleration signal, the three-axis angular velocity signal and the aircraft position information to calculate the aviation absolute gravity acceleration.

2. The common-base sensing multiplexing and collaboratively stable aviation absolute gravity measurement device according to claim 1, characterized in that: The laser control module (321) is connected to a temperature feedback controller (351), which receives an ambient temperature signal of the laser control module (321) and inputs a feedback value to the laser control module (321) to maintain the ambient temperature of the laser control module (321) stable.

3. The common-base sensing multiplexing and collaboratively stable aviation absolute gravity measurement device according to claim 1, characterized in that: A plurality of passive vibration isolation devices (401) are installed at the bottom of the quantum gravity system controller (300), and the passive vibration isolation devices (401) are fixedly connected to the bottom (500) of the cabin.

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