CN112698417A - Cold atom absolute gravimeter capable of being used for dynamic measurement - Google Patents
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Abstract
The invention relates to a cold atom absolute gravimeter capable of being used for dynamic measurement, which comprises a gravimeter sensitive unit, a stable platform assembly, a laser and a control assembly, wherein the gravimeter sensitive unit is arranged in the middle of the stable platform assembly, the laser is connected with the gravimeter sensitive unit through an optical cable, and the control assembly is respectively in signal connection with the laser, the gravimeter sensitive unit and the stable platform assembly; the laser is used for generating laser with specific frequency and power; the gravimeter sensing unit is used for realizing trapping, cooling and interference of atoms and detecting the state and the number of the atoms; the stable platform assembly is used for compensating the inclination angle of the sensitive unit of the gravimeter in real time so as to maintain the posture of the sensitive unit of the gravimeter; the control assembly is used for controlling the laser, the gravity meter sensitive unit and the stable platform assembly to operate, and calculating the gravity acceleration according to the atomic state and the number of the gravity meter sensitive units. The invention can realize accurate measurement of absolute gravity in a dynamic environment.
Description
Technical Field
The invention relates to the field of quantum precision measurement, in particular to a cold atom absolute gravimeter capable of being used for dynamic measurement.
Background
The gravity environment is an important component of a battlefield environment, and directly influences the navigation positioning performance of a battlefield operation platform and the attack precision of battlefield guided weapons. In the process of executing a combat mission by a battlefield combat platform, high-precision, long-endurance and autonomous navigation and positioning are required to be realized on the premise of ensuring the concealment, so that the means such as satellites, radio, astronomy and the like are difficult to be used for navigation and positioning. The gravity information is used for assisting navigation in a battlefield gravity environment, so that error divergence of inertial navigation is inhibited, and the hidden autonomous navigation capability in long voyage is obviously improved. Meanwhile, when the inertial guidance remote striking weapon is launched, the sea battlefield gravity environment is used as the necessary input of the inertial navigation system, and the accuracy of the sea battlefield gravity environment is directly related to the initial alignment and navigation resolving precision of the inertial navigation system, so that the accuracy and effect of military striking are directly influenced.
Besides military applications, marine gravity measurement has very important significance for fundamental and frontier scientific researches such as resource exploration, space science, marine science, geodetic surveying, geophysics, geodynamics and the like. Such as: by measuring the gravity field distribution, the underground material distribution is reversely derived, the oil and gas mineral resource condition in the deep part of the earth is efficiently explored, and the perspective and illumination of the deep part of the earth are realized; the earth gravity parameters are measured with high precision, a gravity basic network is established, accurate gravity parameters are provided for rocket launching, manned space flight, lunar exploration engineering and the like, and space science can be effectively served; by monitoring the abnormal change condition of the earth gravity field, the earthquake, tsunami, volcano eruption and the like can be warned in time.
Aiming at the requirement of absolute gravity measurement, a novel gravimeter, namely a cold atom gravimeter, appears in recent years. The gravity meter adopts a novel technical system of atom interference measurement, and obtains gravity information through interference fringe phases according to free fall of atoms in a gravity field. Because the cold atoms in the ultrahigh vacuum system adopted by the atomic gravimeter are the research objects, the atomic level structure is very stable, so that the atomic gravimeter has the advantages of high precision, good stability, high repetition rate and the like, and the defects of mechanical abrasion and reduction of service life of the free-fall absolute gravimeter are overcome.
Disclosure of Invention
Aiming at the technical problems in the prior art, the invention provides a cold atom absolute gravimeter which can be used for dynamic measurement, has high precision, good stability and high repetition rate, does not have the defects of mechanical abrasion of a laser interference absolute gravimeter and reduced service life, and can realize the attitude maintenance of a sensitive unit of the absolute gravimeter in a dynamic environment so as to realize the accurate measurement of absolute gravity in the dynamic environment.
The technical scheme for solving the technical problems is as follows:
a cold atom absolute gravimeter capable of being used for dynamic measurement comprises a gravimeter sensitive unit, a stable platform assembly, a laser and a control assembly, wherein the gravimeter sensitive unit is fixedly arranged in the middle of the stable platform assembly, the laser is connected with the gravimeter sensitive unit through an optical cable, and the control assembly is respectively in signal connection with the laser, the gravimeter sensitive unit and the stable platform assembly;
the laser is used for generating laser with specific frequency and power;
the gravimeter sensing unit is used for trapping, cooling and interfering atoms and detecting the states and the number of the atoms;
the stable platform assembly is used for compensating the inclination angle of the sensitive unit of the gravimeter in real time so as to maintain the posture of the sensitive unit of the gravimeter;
the control assembly is used for controlling the laser, the gravity meter sensitive unit and the stable platform assembly to operate, and calculating the gravity acceleration according to the atomic state and the number of the gravity meter sensitive units.
Preferably, the stable platform assembly comprises an inner ring fixing support, an outer ring fixing support and a base which are connected in sequence, the gravity meter sensing unit is fixedly arranged on the inner ring fixing support, a first servo motor is arranged between the inner ring fixing support and the outer ring fixing support, a fixing part of the first servo motor is arranged on the outer ring fixing support, and a movable part of the first servo motor is fixedly connected with the inner ring fixing support; a second servo motor is arranged between the outer ring fixing support and the base, a fixing part of the second servo motor is installed on the base, and a movable part of the second servo motor is fixedly connected with the outer ring fixing support; the output shafts of the first servo motor and the second servo motor are vertically arranged; first servo motor with the shaft end of second servo motor all installs the circle grating encoder, still be equipped with attitude sensor IMU on the inner ring fixed bolster, still be equipped with IMU on the base and solve the module, IMU solve the module with attitude sensor IMU signal connection, control assembly sets up on the base, circle grating encoder the IMU solve the module respectively with control assembly signal connection.
Preferably, the base is further provided with an inertial navigation calibration assembly, the inertial navigation calibration assembly is in signal connection with the control assembly, and the inertial navigation calibration assembly is a GNSS/GPS module.
Preferably, two first servo motors are symmetrically arranged between the outer ring fixing support and the inner ring fixing support.
Preferably, two second servo motors are symmetrically arranged between the outer ring fixing support and the base.
Preferably, the gravity meter sensing unit comprises a magnetic shield and a vacuum cavity, the magnetic shield is arranged outside the vacuum cavity, a magnetic field coil is arranged between the magnetic shield and the vacuum cavity, and the magnetic field coil is in signal connection with the control component; the vacuum cavity is provided with a vacuum pump, the inner side of the vacuum cavity is fixedly provided with a Raman light/detection light/back-pumping light collimation head, an all-solid-state cooling light module, a blowing light module and a fluorescence lens, the Raman light/detection light/back-pumping light collimation head is coupled with the laser through an optical fiber, and the vacuum pump and the fluorescence lens are respectively in signal connection with the control assembly.
Preferably, an accelerometer is further arranged on the gravity meter sensitive unit and is in signal connection with the control assembly, so that interference of environmental vibration noise on the gravity meter sensitive unit is inhibited.
Preferably, the control assembly comprises a data acquisition and processing unit, a laser control unit and a magnetic field control unit, wherein the data acquisition and processing unit is in signal connection with the stable platform assembly and the gravimeter sensitive unit respectively, and is used for acquiring and processing various signals of the stable platform assembly and the gravimeter sensitive unit and outputting control signals; the laser control unit is in signal connection with the laser and is used for completing laser frequency shift and laser switch control; the magnetic field control unit is in signal connection with the magnetic field coil and is used for providing stable constant current source driving for the magnetic field coil in the magnetic shielding cover.
Preferably, a load layer gyroscope is further arranged on the inner ring fixing support and is in signal connection with the control assembly.
Preferably, the laser is a narrow linewidth laser.
The invention has the beneficial effects that: the invention adopts the cold atom absolute gravimeter as the gravity sensor, has the advantages of high precision, good stabilization, high repetition rate and the like, and does not have the defects of mechanical abrasion of the laser interference absolute gravimeter and reduction of the service life. The attitude of the sensitive unit of the absolute gravimeter is maintained by adopting the stable platform in a dynamic environment, and then the accurate measurement of the absolute gravity is realized in the dynamic environment.
Drawings
FIG. 1 is a schematic structural diagram of an embodiment of the present invention;
FIG. 2 is a schematic diagram of the working principle of the present invention;
FIG. 3 is a flowchart illustrating the stabilized platform attitude calculation and compensation process according to an embodiment of the present invention.
In the drawings, the components represented by the respective reference numerals are listed below:
1. the system comprises an IMU resolving module, 2, a control assembly, 3, a first servo motor, 4, a second servo motor, 5, a gravity meter sensitive unit, 6, an attitude sensor IMU, 7, a GNSS/GPS module, 8, an inner ring fixing support, 9, a base, 10, an outer ring fixing support, 11 and a load layer gyroscope.
Detailed Description
The principles and features of this invention are described below in conjunction with the following drawings, which are set forth by way of illustration only and are not intended to limit the scope of the invention.
As shown in fig. 1, the cold atom absolute gravimeter capable of being used for dynamic measurement provided by this embodiment includes a gravimeter sensing unit 5, a stable platform assembly, a laser, and a control assembly 2, the gravimeter sensing unit 5 is fixedly disposed in the middle of the stable platform assembly, and the control assembly 2 is mounted at the lower end of the stable platform assembly. The laser of this embodiment adopts narrow linewidth laser, its with the sensitive unit of gravity appearance 5 passes through the optical cable connection, control assembly 2 with the laser, the sensitive unit of gravity appearance 5 the stable platform subassembly passes through cable signal connection respectively.
The laser is used for generating laser light with specific frequency and power.
The gravimeter sensing unit 5 is used for trapping, cooling and interfering atoms and detecting the states and the number of the atoms.
The stable platform assembly is used for compensating the inclination angle of the sensitive gravity meter unit 5 in real time so as to maintain the posture of the sensitive gravity meter unit 5.
The control assembly 2 is used for controlling the laser, the gravimeter sensing unit 5 and the stable platform assembly to operate, and calculating the gravity acceleration according to the atomic state and the number of the gravimeter sensing unit 5.
In this embodiment, the gravity meter sensing unit 5 includes a magnetic shielding cover and a vacuum cavity, the magnetic shielding cover is disposed outside the vacuum cavity, a magnetic field coil is disposed between the magnetic shielding cover and the vacuum cavity, and the magnetic field coil is in signal connection with the control component 2. The control component 2 controls the magnetic field coil to generate a stable magnetic field to meet the requirement of the sensitive unit 5 of the gravimeter, and the magnetic shielding cover isolates the interference of an environmental magnetic field to equipment to establish a stable magnetic field environment. The vacuum cavity provides a vacuum environment for the processes of atom cooling, state selection, interference, end state detection and the like, and eliminates the interference of impurity particles on equipment.
The vacuum cavity is provided with a vacuum pump for maintaining a vacuum environment in the vacuum cavity. The Raman light/probe light/back-pumping light collimation head, the all-solid-state cooling light module, the blowing light module and the fluorescence lens are fixedly arranged on the inner side of the vacuum cavity, the Raman light/probe light/back-pumping light collimation head is coupled with the laser through an optical fiber, and the vacuum pump and the fluorescence lens are respectively in signal connection with the control assembly 2. Emergent light of the Raman light/detection light/back-pumping light collimation head passes through the vacuum cavity, then passes through the quarter-wave plate, and then returns through the reflector module in the original path to form opposite Raman light/detection light/back-pumping light, and the opposite Raman light/detection light/back-pumping light is used for providing back-pumping light in the atomic group cooling process, pi/2-pi/2 Raman pulse laser in the interference process and detection light in the final state detection process. The all-solid-state cooling optical module equally divides a beam of incident cooling light into three pairs of opposite-emission cooling light with equal intensity through the spectroscope, the polaroid and the reflector, and the three pairs of opposite-emission cooling light are used for cooling radicals in the vacuum cavity. And the blowing light module is used for providing blowing light needed in the atomic state selection process. The fluorescence lens is used for collecting fluorescence signals emitted in the detection of the end state of the atomic group.
The cold atom absolute gravimeter of the present embodiment87Rb atoms are used as proof masses, the techniques of radical cooling and trapping, polarization gradient cooling, state preparation, atom interference, end state detection and the like are adopted to measure the gravity acceleration, and the working principle of cold atom absolute gravimeter measurement is shown in figure 2.
The work flow of atomic interference is as follows: firstly, cooling and trapping rubidium atoms from hot steam by using cooling laser emitted from an all-solid-state cooling optical module and pumpback light emitted from a Raman light/probe light/pumpback light collimation head by using an MOT (magneto optical trapping) technology to form cold atomic groups; secondly, changing the detuning quantity of the cooling laser emitted from the all-solid-state cooling optical module, and further reducing the temperature of atomic groups; thirdly, removing background atoms from the falling atoms through microwave state selection and blowing light emitted by a blowing light module to obtain single quantum state atomic groups; fourthly, in the atom falling process, carrying out two-photon Raman transition on three beams of pi/2-pi/2 pulse laser emitted in a time-sharing manner by using a Raman light/probe light/back pump light collimation head and atoms to form interference; and fifthly, detecting the number of atoms in different states by using detection light emitted from the Raman light/detection light/back pump light collimation head, collecting fluorescence signals emitted by the atoms under the irradiation of the detection light by using a fluorescence lens, and calculating interference fringes and phases of the substance wave by using the fluorescence signals to obtain the gravitational acceleration.
Preferably, an accelerometer (not shown in fig. 1, refer to the flowchart in fig. 3) is further disposed on the vacuum chamber of the gravity meter sensing unit 5, and the accelerometer is in signal connection with the control component 2, and is configured to suppress interference of ambient vibration noise on the gravity meter sensing unit 5.
In this embodiment, the control assembly 2 includes a data acquisition processing unit, a laser control unit, and a magnetic field control unit, the data acquisition processing unit is in signal connection with the stable platform assembly and the sensitive unit of the gravimeter 5 respectively, and is used for acquiring various signals of the stable platform assembly and the sensitive unit of the gravimeter 5, performing signal processing, and outputting a control signal. And the laser control unit is in signal connection with the laser and is used for finishing laser frequency shift and laser switch control. The magnetic field control unit is in signal connection with the magnetic field coil and is used for providing stable constant current source driving for the magnetic field coil in the magnetic shielding cover.
As shown in fig. 1, the stabilized platform assembly includes an inner ring fixing support 8, an outer ring fixing support 10, and a base 9, which are connected in sequence, the gravity meter sensing unit 5 is fixedly disposed on the inner ring fixing support 8, and the control assembly 2 is mounted on the base 9. A first servo motor 3 is arranged between the inner ring fixing support 8 and the outer ring fixing support 10, a fixing part of the first servo motor 3 is installed on the outer ring fixing support 10, and a movable part of the first servo motor 3 is fixedly connected with the inner ring fixing support 8. When the first servo motor 3 rotates, the outer ring fixing support 10 and the inner ring fixing support 8 can rotate relatively. A second servo motor 4 is arranged between the outer ring fixing support 10 and the base 9, a fixing part of the second servo motor 4 is installed on the base 9, and a moving part of the second servo motor 4 is fixedly connected with the outer ring fixing support 10. The first servo motor 3 and the second servo motor 4 are provided with corresponding motor driving modules, and the motor driving modules are in signal connection with the control component 2. When the second servo motor 4 rotates, the outer ring fixing bracket 10 and the base 9 can rotate relatively. The posture of the gravimeter sensing unit 5 on the stabilized platform assembly can be adjusted by matching the operation of the first servo motor 3 and the second servo motor 4.
The output shafts of the first servo motor 3 and the second servo motor 4 are vertically arranged so as to adjust the gravity meter sensitive unit 5 to roll or pitch. First servo motor 3 with the circle grating encoder is all installed to the axle head of second servo motor 4, still be equipped with attitude sensor IMU6 on the inner ring fixed bolster 8, still be equipped with IMU on the base 9 and solve module 1, IMU solve module 1 with attitude sensor IMU6 signal connection, control assembly 2 sets up on the base 9, circle grating encoder IMU solve module 1 respectively with control assembly 2 signal connection. The circular grating encoder is used for feeding back the angular velocities of the first servo motor 3 and the second servo motor 4 to the control assembly 2, the attitude sensor IMU6 is used for transmitting the attitude signal of the gravimeter sensitive unit 5 to the IMU resolving module 1, the attitude signal of the gravimeter sensitive unit 5 is fed back to the control assembly 2 after the IMU resolving module 1 resolves, and the control assembly 2 controls the operation of the first servo motor 3 and the second servo motor 4, so that the attitude of the gravimeter sensitive unit 5 is adjusted.
As shown in fig. 1, an inertial navigation calibration assembly is further mounted on the base 9, and the inertial navigation calibration assembly is in signal connection with the control assembly 2, and is a GNSS/GPS module 7. The GNSS/GPS module 7 is used to calibrate the attitude sensor IMU6 in the motion environment of a ship, an automobile, or the like, and to improve the accuracy of attitude control.
Preferably, a load layer gyroscope 11 is further arranged on the inner ring fixing support 8, and the load layer gyroscope 11 is in signal connection with the control component 2. The load layer gyroscope 11 is used for directly measuring the rotation angular velocity of the absolute gravimeter sensitive unit 5, transmitting the measured rotation angular velocity of the absolute gravimeter to the control assembly 2, serving as a reference factor for controlling the operation of the motor, further inhibiting the interference of rotation on the absolute gravimeter, and improving the control precision and the effective bandwidth of the stable platform.
Preferably, two first servo motors 3 are symmetrically arranged between the outer ring fixing support 10 and the inner ring fixing support 8. Two first servo motors 3 are symmetrically arranged, and the control precision of posture adjustment is improved.
Preferably, two second servo motors 4 are symmetrically arranged between the outer ring fixing support 10 and the base 9. Similarly, the two second servo motors 4 are symmetrically arranged, so that the control precision of the posture adjustment is improved.
The stable platform assembly guarantees the posture of the gravity meter sensitive unit 5 and provides course information when the system error of the gravity meter needs to be evaluated. The scheme of the stable platform is shown in fig. 1, the main structure of the stable platform is divided into three parts, namely an inner ring fixing support 8, an outer ring fixing support 10 and a base 9 in sequence. The base 9 is used as a stable platform base, is in contact with the ground, a ship body or an automobile, and realizes initial posture adjustment and high-frequency vibration isolation through a plurality of supporting legs with rubber spacers. Outer loop fixed bolster 10 and base 9, the servo motor that is set up by two pairs of symmetries respectively between inner ring fixed bolster 8 and outer loop fixed bolster 10 is connected, and torque motor is chooseed for use to servo motor, breaks through the restriction problem of output torque to the stabilized platform control speed, realizes every single move and roll gesture and adjusts. The effective load (i.e. the gravity meter sensitive unit 5) is rigidly connected with the inner ring fixing support 8, and the stability of the load is kept along with the posture adjustment of the inner ring fixing support 10 and the outer ring fixing support 10, so that the function of stabilizing the platform is realized.
An implementation flow chart of the attitude feedback control system of the stabilized platform assembly is shown in fig. 3, and the attitude feedback control system is composed of an attitude sensor IMU6 installed on an inner ring fixing support 8, a circular grating installed at output shaft ends of a first servo motor 3 and a second servo motor 4, an IMU resolving module 1 and a control assembly 2, and is used for implementing a double-ring control system of a position ring and a speed ring. The IMU is used as an attitude sensor, measures attitude information of the inner ring fixing support 8 and the load, and transmits the attitude information to the IMU resolving module 1. After the IMU resolving module 1 resolves the position and attitude information, the position and attitude information is provided for the control component 2 to further perform feedback control on the movement of the first servo motor 3 and the second servo motor 4, so that attitude stability control is realized. The GNSS/GPS module 7 is used to calibrate the attitude sensor IMU6 in the motion environment of a ship, an automobile, or the like, and to improve the accuracy of attitude control. The accelerometer is used to suppress the interference of ambient vibration noise on the gravimeter-sensitive unit 5.
The invention adopts the cold atom absolute gravimeter as the gravity sensor, has the advantages of high precision, good stabilization, high repetition rate and the like, and does not have the defects of mechanical abrasion of the laser interference absolute gravimeter and reduction of the service life. The attitude of the absolute gravimeter sensitive unit 5 is maintained by adopting a stable platform in a dynamic environment, and then the accurate measurement of absolute gravity is realized in the dynamic environment.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (10)
1. A cold atom absolute gravimeter capable of being used for dynamic measurement is characterized by comprising a gravimeter sensitive unit (5), a stable platform assembly, a laser and a control assembly (2), wherein the gravimeter sensitive unit (5) is fixedly arranged in the middle of the stable platform assembly, the laser is connected with the gravimeter sensitive unit (5) through an optical cable, and the control assembly (2) is in signal connection with the laser, the gravimeter sensitive unit (5) and the stable platform assembly respectively;
the laser is used for generating laser with specific frequency and power;
the gravimeter sensing unit (5) is used for trapping, cooling and interfering atoms and detecting the states and the number of the atoms;
the stable platform assembly is used for compensating the inclination angle of the sensitive gravity meter unit (5) in real time so as to maintain the posture of the sensitive gravity meter unit (5);
the control assembly (2) is used for controlling the laser, the gravity meter sensitive unit (5) and the stable platform assembly to operate, and calculating the gravity acceleration according to the atomic state and the number of the gravity meter sensitive unit (5).
2. The cold atom absolute gravimeter capable of being used for dynamic measurement according to claim 1, wherein the stable platform assembly comprises an inner ring fixed support (8), an outer ring fixed support (10) and a base (9) which are connected in sequence, the gravimeter sensing unit (5) is fixedly arranged on the inner ring fixed support (8), a first servo motor (3) is arranged between the inner ring fixed support (8) and the outer ring fixed support (10), a fixed part of the first servo motor (3) is mounted on the outer ring fixed support (10), and a movable part of the first servo motor (3) is fixedly connected with the inner ring fixed support (8); a second servo motor (4) is arranged between the outer ring fixing support (10) and the base (9), a fixing part of the second servo motor (4) is installed on the base (9), and a movable part of the second servo motor (4) is fixedly connected with the outer ring fixing support (10); the output shafts of the first servo motor (3) and the second servo motor (4) are vertically arranged; first servo motor (3) with the circle grating encoder is all installed to the axle head of second servo motor (4), still be equipped with attitude sensor IMU (6) on inner ring fixed bolster (8), still be equipped with IMU on base (9) and solve module (1), IMU solve module (1) with attitude sensor IMU (6) signal connection, control assembly (2) set up on base (9), circle grating encoder IMU solve module (1) respectively with control assembly (2) signal connection.
3. Cold atom absolute gravimeter according to claim 2, characterized in that the base (9) also has an inertial navigation calibration module, which is a GNSS/GPS module (7), mounted thereon and is in signal connection with the control module (2).
4. Cold atom absolute gravimeter according to claim 2, characterized in that two first servomotors (3) are symmetrically arranged between the outer ring (10) and the inner ring (8) fixed supports.
5. Cold atom absolute gravimeter according to claim 2, characterized in that two second servomotors (4) are symmetrically arranged between the outer ring fixed support (10) and the base (9).
6. Cold atom absolute gravimeter according to claim 1, characterized in that the gravimeter-sensitive unit (5) comprises a magnetic shield, a vacuum chamber, the magnetic shield being arranged outside the vacuum chamber, a magnetic field coil being arranged between the magnetic shield and the vacuum chamber, the magnetic field coil being in signal connection with the control assembly (2); the vacuum cavity is provided with a vacuum pump, the inner side of the vacuum cavity is fixedly provided with a Raman light/detection light/back-pumping light collimation head, an all-solid-state cooling light module, a blowing light module and a fluorescence lens, the Raman light/detection light/back-pumping light collimation head is coupled with the laser through an optical fiber, and the vacuum pump and the fluorescence lens are respectively in signal connection with the control component (2).
7. Cold atom absolute gravimeter according to claim 1, characterized in that the sensitive gravimeter unit (5) is further provided with an accelerometer, which is in signal connection with the control unit (2) for suppressing the interference of ambient vibration noise to the sensitive gravimeter unit (5).
8. The cold atom absolute gravimeter capable of being used for dynamic measurement according to claim 6, wherein the control assembly (2) comprises a data acquisition and processing unit, a laser control unit, and a magnetic field control unit, the data acquisition and processing unit is respectively in signal connection with the stable platform assembly and the gravimeter sensing unit (5), and is used for acquiring and processing signals of the stable platform assembly and the gravimeter sensing unit (5), and outputting a control signal; the laser control unit is in signal connection with the laser and is used for completing laser frequency shift and laser switch control; the magnetic field control unit is in signal connection with the magnetic field coil and is used for providing stable constant current source driving for the magnetic field coil in the magnetic shielding cover.
9. Cold atom absolute gravimeter according to claim 2, characterized in that a load layer gyroscope (11) is also provided on the inner ring fixed support (8), the load layer gyroscope (11) being in signal connection with the control module (2).
10. A cold atom absolute gravimeter according to claim 1, characterized in that the laser is a narrow line width laser.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113672002A (en) * | 2021-08-23 | 2021-11-19 | 九江学院 | Cold atom gravimeter active vibration isolation control method based on nominal model |
| CN116184616A (en) * | 2022-12-06 | 2023-05-30 | 中国科学院空间应用工程与技术中心 | Method and system for controlling pose of prism of gravity meter |
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| CN113672002A (en) * | 2021-08-23 | 2021-11-19 | 九江学院 | Cold atom gravimeter active vibration isolation control method based on nominal model |
| CN116184616A (en) * | 2022-12-06 | 2023-05-30 | 中国科学院空间应用工程与技术中心 | Method and system for controlling pose of prism of gravity meter |
| CN116184616B (en) * | 2022-12-06 | 2023-11-14 | 中国科学院空间应用工程与技术中心 | Method and system for controlling pose of prism of gravity meter |
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