CN114814968B - Space gravitational wave detection device based on single inspection quality - Google Patents
Space gravitational wave detection device based on single inspection quality Download PDFInfo
- Publication number
- CN114814968B CN114814968B CN202210466111.6A CN202210466111A CN114814968B CN 114814968 B CN114814968 B CN 114814968B CN 202210466111 A CN202210466111 A CN 202210466111A CN 114814968 B CN114814968 B CN 114814968B
- Authority
- CN
- China
- Prior art keywords
- spacecraft
- laser
- inter
- beam splitter
- optical
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000007689 inspection Methods 0.000 title claims abstract description 62
- 238000001514 detection method Methods 0.000 title claims abstract description 45
- 230000003287 optical effect Effects 0.000 claims abstract description 90
- 238000005305 interferometry Methods 0.000 claims abstract description 59
- 238000006073 displacement reaction Methods 0.000 claims abstract description 20
- 238000005259 measurement Methods 0.000 claims abstract description 15
- 230000015572 biosynthetic process Effects 0.000 claims description 12
- 239000013307 optical fiber Substances 0.000 claims description 8
- 239000000835 fiber Substances 0.000 claims description 4
- 230000008859 change Effects 0.000 abstract description 10
- 238000011217 control strategy Methods 0.000 abstract description 8
- 230000003068 static effect Effects 0.000 abstract 1
- 238000005755 formation reaction Methods 0.000 description 10
- 238000000034 method Methods 0.000 description 7
- 238000010586 diagram Methods 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000029058 respiratory gaseous exchange Effects 0.000 description 2
- 238000006880 cross-coupling reaction Methods 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01V—GEOPHYSICS; GRAVITATIONAL MEASUREMENTS; DETECTING MASSES OR OBJECTS; TAGS
- G01V7/00—Measuring gravitational fields or waves; Gravimetric prospecting or detecting
Landscapes
- Physics & Mathematics (AREA)
- Life Sciences & Earth Sciences (AREA)
- General Life Sciences & Earth Sciences (AREA)
- General Physics & Mathematics (AREA)
- Geophysics (AREA)
- Length Measuring Devices By Optical Means (AREA)
Abstract
The invention discloses a space gravitational wave detection device based on single inspection quality, which comprises three spacecrafts, wherein a spacecraft platform in each spacecraft comprises an inertial sensing part, a driving part and two optical parts, the inertial sensing part comprises a polygonal columnar inspection quality, and the inspection quality comprises two groups of side surfaces with an included angle of 60 DEG in the normal direction and four side surfaces which are perpendicular to each other or parallel to each other and used for detecting displacement sensing and static feedback control; the optical component comprises a local interferometry unit and an inter-satellite long-arm interferometry unit, the local interferometry unit measures the relative displacement change of the spacecraft platform relative to the inspection mass, and a driving component in the local interferometry unit is controlled by a drag-free control algorithm to drive the spacecraft platform to move along with the inspection mass in an orbit plane; the inter-satellite long-arm interferometer measures the relative displacement change between the optical platforms in the two spacecrafts, thereby realizing the measurement of gravitational wave signals. The invention can effectively simplify the traditional control strategy of space gravitational wave detection without dragging.
Description
Technical Field
The invention belongs to the technical field of space gravitational wave detection, and particularly relates to a space gravitational wave detection device based on single inspection quality.
Background
Gravitational wave detection has important significance in the fields of generalized relativity, astrophysics, astronomy and the like. The space gravitational wave detection refers to a method for constructing a large-scale laser interferometer by utilizing spacecraft formation or constellation in space to detect gravitational waves. The spacecraft for space gravitational wave detection mainly comprises an inertial sensor, an optical measurement system, a spacecraft platform and other systems. The basic principle of space gravitational wave detection is to ensure that the inspection quality follows the motion of the geodesic wire in the direction of the laser interferometer by using a non-dragging control technology, and to measure the optical path change between two inspection qualities in space caused by gravitational waves by using the laser interferometer.
Currently, international space gravitational wave detection spacecraft formations are mainly in equilateral triangle configurations, such as LISA (Laser Interferometer SPACE ANTENNA), harmonica scheme, tai chi scheme and the like. In these schemes, a spacecraft formation consists of three spacecraft, each having two proof masses within it, each proof mass providing a face as an end mirror of a laser interferometer. The drag-free control needs to ensure that the two inspection masses respectively move along the geodesic line in the direction of the sensitive axis (the measuring direction of the interferometer) with an included angle of 60 degrees. When one inspection mass has relative displacement relative to the spacecraft in the sensitive axis direction, the micro-bovine-level propeller is required to push the spacecraft along the non-sensitive axis direction of the other inspection mass to compensate the relative displacement, and meanwhile, the electrostatic actuator is required to pull the two inspection masses back to the central position in the non-sensitive axis direction. Therefore, the drag-free control strategy of the traditional double-inspection-quality scheme is very complex, and the micro-bovine-level propeller and the electrostatic feedback actuator are required to be matched to realize drag-free control.
Disclosure of Invention
In order to achieve the above object, the invention provides a space gravitational wave detection device based on single inspection quality, comprising a main control system and an equilateral triangle spacecraft formation, wherein the spacecraft formation comprises three spacecraft with identical configuration and different working modes, the three spacecraft are divided into a main spacecraft and two slave spacecraft according to the working modes, and an inertial sensing component, a control component, a driving component and two optical components are arranged in spacecraft platforms in each spacecraft,
The inertial sensing component comprises a polygonal columnar inspection mass, wherein the inspection mass comprises two groups of first side surfaces with normal direction included angles of 60 degrees and four second side surfaces which are perpendicular or parallel to each other, and polar plates for detecting displacement sensing and controlling electrostatic feedback are arranged around the four second side surfaces;
The optical component comprises a laser, a local interferometry unit, an inter-satellite long-arm interferometry unit and an optical phase-locking unit, and the laser is used for emitting laser in the same spacecraft; the local interferometry unit is used for emitting local laser to one first side surface of the inspection quality and the inter-satellite long-arm interferometry unit by utilizing the laser, and obtaining first optical path information of a spacecraft platform of the spacecraft relative to the inspection quality in the spacecraft platform by utilizing interferometry generated by the local laser reflected by the first side surface and the emitted local laser; the control component in each spacecraft is used for controlling the driving component in the spacecraft to drive the spacecraft platform of the spacecraft to move along with the inspection mass in the orbit plane according to the first optical path information measured by the local interferometry unit in the spacecraft by using a drag-free algorithm;
The two inter-satellite long-arm interferometry units in each spacecraft are used for respectively transmitting inter-satellite long-arm laser to one inter-satellite long-arm interferometry unit in the two adjacent spacecraft; the optical phase locking unit in the slave spacecraft is used for carrying out phase locking on the inter-satellite long-arm laser emitted by the optical phase locking unit and the phase of the inter-satellite long-arm laser emitted by the master spacecraft, and emitting the inter-satellite long-arm laser after phase locking back to the inter-satellite long-arm interferometry unit in the master spacecraft through the inter-satellite long-arm interferometry unit in the spacecraft, and obtaining second optical path information of a spacecraft platform in the master spacecraft and a spacecraft platform in two slave spacecraft from interferometry generated by local laser emitted by the local interferometry unit in the master spacecraft;
the main control system is used for obtaining space gravitational wave signals on the ground through data processing according to the second optical path information and the first optical path information obtained by measurement of the local interferometry units in the spacecrafts.
Compared with the traditional gravitational wave detection device adopting double inspection masses, the spatial gravitational wave detection device based on single inspection masses provided by the invention is characterized in that a single polygonal columnar inspection mass which is easy to process is arranged in each spacecraft, and the polygonal columnar inspection mass has two groups of side faces with an included angle of 60 DEG in the normal direction, so that a complex dragging-free control strategy in a traditional orbit plane can be simplified into a spacecraft platform which completely follows the movement of the inspection masses through a driving part, the cooperation of an electrostatic feedback actuator is not needed, and the traditional spatial gravitational wave detection dragging-free control strategy can be effectively simplified; meanwhile, the polygonal columnar detection quality is also provided with four side faces which are perpendicular or parallel in pairs, and the polar plates are arranged on the periphery of the four side faces, so that compared with the spherical detection quality, the accuracy of polar plate displacement measurement can be effectively improved; compared with the traditional method adopting double inspection quality, the method adopts single inspection quality, and can effectively reduce the overall quality of the spacecraft.
In one embodiment, the drive member is a micro-bovine propeller.
In one embodiment, the local interferometry unit includes a first beam splitter, a second beam splitter, a third beam splitter, a fourth beam splitter, a fifth beam splitter, a first fast deflector, a first mirror, a first four-quadrant photodetector, a first acousto-optic modulator, and a second acousto-optic modulator;
in the same spacecraft, laser emitted by the laser is divided into two laser beams C through the first beam splitter, one laser beam C is divided into two laser beams C through the second beam splitter, and the two laser beams are subjected to frequency shift through the first acousto-optic modulator and the second acousto-optic modulator respectively; the laser of the first acousto-optic modulator frequency shift is emitted to the first side surface of the inspection quality through the first reflecting mirror and the first rapid deflecting mirror in sequence, and the laser reflected by the first side surface of the inspection quality is irradiated to the first four-quadrant photoelectric detector after passing through the first rapid deflecting mirror and the third beam splitter in sequence; and the laser of the second acoustic optical modulator frequency shift irradiates on a first four-quadrant photoelectric detector after passing through the fifth beam splitter and the fourth beam splitter.
In one embodiment, the inter-satellite long-arm interferometry unit includes an on-satellite telescope and an inter-satellite long-arm interferometer, the inter-satellite long-arm interferometer including a sixth beam splitter, a seventh beam splitter, an eighth beam splitter, a second mirror, and a second four-quadrant photodetector;
In an optical platform in a spacecraft, after the laser frequency-shifted by the second optical modulator is divided into two beams of laser D by the sixth beam splitter, one beam of laser D emits inter-satellite long-arm laser by the satellite-borne telescope, the other beam of laser D forms interference laser by the eighth beam splitter, and the interference laser irradiates on the second four-quadrant photoelectric detector; and inter-satellite long-arm laser B emitted by a spacecraft adjacent to the spacecraft sequentially passes through the spaceborne telescope, the seventh beam splitter, the second reflector and the eighth beam splitter, and irradiates on the second four-quadrant photoelectric detector to form interferometry with the interference laser so as to obtain second optical path information of a spacecraft platform in the main spacecraft and a spacecraft platform in the two slave spacecraft.
In one embodiment, the satellite telescope includes a satellite telescope primary mirror and a second quick-deflecting mirror.
In one embodiment, the optical phase locking unit comprises a ninth beam splitter, a tenth beam splitter, a third four-quadrant photoelectric detector, a first optical fiber coupler, a second optical fiber coupler, a phase meter and an optical phase locking loop;
In one optical platform of the main spacecraft, the other beam of laser C is divided into two beams of laser E through the ninth beam splitter, one beam of laser E is emitted into the other optical platform of the main spacecraft through the first optical fiber coupler, the other beam of laser E interferes with the laser emitted by the laser in the other optical platform of the main spacecraft through the second optical fiber coupler on the third quadrant photoelectric detector, and the phase difference of the laser emitted by the two lasers in the main spacecraft is obtained after the detection signal of the third quadrant photoelectric detector passes through the phase meter; the optical phase-locked loop is used for adjusting the phase of laser emitted by one laser in the main spacecraft according to the phase difference information so as to keep the phases of the laser emitted by the two lasers in the main spacecraft consistent;
In the slave spacecraft, second optical path information of a spacecraft platform in the master spacecraft and second optical path information of spacecraft platforms in the two slave spacecraft are measured by using the second four-quadrant photoelectric detector, and an inter-satellite long-arm laser phase difference which is received by the on-board telescope in the spacecraft and is emitted by the inter-satellite long-arm interferometry unit is calculated by using the phase meter; the optical phase-locked loop adjusts the laser phase emitted by the laser in the spacecraft according to the phase difference information, so that the laser phase is consistent with the inter-satellite long-arm laser phase received by the spaceborne telescope.
In one embodiment, the proof mass is in the form of a straight octagon.
In one embodiment, the inspection quality is in a cuboid shape with four corners in an arc shape.
In one embodiment, the inspection mass has a rectangular parallelepiped shape with a pair of side end portions cut out respectively in a specific structure, which is a rectangular parallelepiped shape with a triangular prism cut out at one corner.
Drawings
FIG. 1 is a block diagram of a spatial gravitational wave detection device based on a single proof mass according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a spacecraft formation according to an embodiment of the present invention;
FIG. 3 is a schematic view of an optical component according to an embodiment of the present invention;
FIG. 4 is a schematic diagram of a proof mass provided by an embodiment of the present invention;
FIG. 5 is a schematic diagram of a proof mass provided by another embodiment of the present invention;
fig. 6 is a schematic structural view of a proof mass according to still another embodiment of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
The fundamental principle of the spatial gravitational wave detection in the field is that gravitational waves are utilized to cause the optical path between two inspection masses moving along the geodesic to change, and the gravitational wave signal is extracted by processing data of the optical path change.
As shown in fig. 1 and fig. 2, the spatial gravitational wave detection device based on the single inspection quality provided by the invention comprises a main control system and an equilateral triangle spacecraft formation, wherein the spacecraft formation comprises three spacecrafts with identical configurations and different working modes, and the spacecraft formation can be divided into a main spacecraft and two slave spacecrafts according to the working modes. Within the spacecraft platform 50 in each spacecraft are disposed control components, inertial sensing components, drive components, and two optical components.
In this embodiment, the inertial sensing unit comprises a proof mass 10 for providing an inertial reference for gravitational wave detection along a ground line, the presence of a spatial gravitational wave causing a change in the relative distance of two proof masses in each spacecraft, and accordingly, the spatial gravitational wave detection provided by the present invention is based on the basic principle of spatial gravitational wave detection in the art by measuring the optical path change between the proof mass 10 in the master spacecraft and the proof mass 10 in the two slave spacecraft, respectively.
In the measurement of the space gravitational wave, it is necessary to ensure that the spacecraft platform 50 follows the movement of the proof mass 10 in order to ensure that the proof mass 10 moves along the geodesic line. Therefore, when the space gravitational wave is measured by using the proof mass 10 in each spacecraft, the relative displacement between the spacecraft platform 50 of each spacecraft and the proof mass 10 in each spacecraft is also required to be maintained, and when the displacement between the spacecraft platform of a certain spacecraft and the proof mass 10 in each spacecraft is changed, the spacecraft platform is required to be controlled to move along with the proof mass 10 in each spacecraft by adopting a proper control strategy. In particular, the states of motion of proof mass 10 include states of motion of 3 translational degrees of freedom (2 translational degrees of freedom in the orbital plane and 1 translational degree of freedom perpendicular to the orbital plane) and 3 rotational degrees of freedom.
Combining the basic principle of space gravitational wave detection in the field. In this regard, the structure of the proof mass 10 and the optical components in each spacecraft provided by the invention is specifically as follows:
The inspection mass 10 provided in this embodiment adopts a polygonal column structure, the polygonal column structure includes four sides 10b perpendicular or parallel to each other, a polar plate 11 for detecting displacement sensing and electrostatic feedback control is disposed around the four sides 10b, the polar plate 11 is used for realizing displacement sensing measurement of the inspection mass 10 by the polar plate 11 in 1 translational degree of freedom and 3 rotational degrees of freedom perpendicular to the orbit plane, and the control component 60 controls electrostatic feedback control to enable the inspection mass 10 to move according to the spacecraft platform where it is located. In this embodiment, the polar plates 11 are disposed on four sides of the polygonal column-shaped inspection mass 10, which are perpendicular or parallel to each other, so that compared with the spherical inspection mass, the linearity of the polar plate displacement detection can be effectively improved, the cross coupling coefficient can be reduced, and the measurement accuracy can be ensured.
For displacement detection of the proof mass 10 in 2 translational degrees of freedom in the orbital plane, the present embodiment is implemented by using the other set of sides of the proof mass 10 in cooperation with an optical platform. Specifically, the inspection quality provided in this embodiment further includes two sets of side surfaces 10a (only one of which is indicated in the figure) having an angle of 60 ° in the normal direction, wherein one set of side surfaces 10a is used as an end mirror for the local laser light a emitted in the front-end optical component.
Specifically, the optical components provided in this embodiment include a laser 51, a local interferometry unit 20, an inter-satellite long arm interferometry unit 21, and an optical phase lock unit. In the same spacecraft, a laser 51 is used to emit laser light; the local interferometry unit 20 is configured to emit local laser light a to one of the side surfaces 10a of the proof masses 10 and the inter-satellite long-arm interferometry unit 21, respectively, by using the laser light, and obtain first optical path information of the spacecraft platform 50 of the spacecraft relative to the proof masses 10 therein by using interferometry generated by the local laser light reflected from the side surface 10a and the emitted local laser light.
The control part 60 in each spacecraft is used for obtaining first optical path information according to the measurement of the local interferometry unit 20 in the spacecraft, calculating the relative displacement change of the spacecraft platform 50 of the spacecraft relative to the inspection mass 10 in the spacecraft through an optical path-displacement conversion formula, and then controlling the driving part in the spacecraft platform 50 to drive the spacecraft platform 50 of the spacecraft to move along the inspection mass 10 in the orbit plane according to the drag-free control algorithm by the control part 60, so that a drag-free control strategy of the traditional gravitational wave detection device in the orbit plane can be effectively simplified without matching with an electrostatic feedback actuator. In particular, the drive member may employ a micro-bovine propeller.
The two inter-satellite long-arm interferometry units 21 in each spacecraft provided in this embodiment are configured to emit inter-satellite long-arm laser light B to one inter-satellite long-arm interferometry unit 21 in each of two adjacent spacecraft. The optical phase locking unit in the slave spacecraft is used for phase locking the phase of the inter-satellite long-arm laser emitted by the slave spacecraft and the inter-satellite long-arm laser emitted by the slave spacecraft, transmitting the phase-locked inter-satellite long-arm laser back to the inter-satellite long-arm interferometry unit in the master spacecraft through the inter-satellite long-arm interferometry unit in the spacecraft, and obtaining second optical path information of the spacecraft platform 50 in the master spacecraft and the spacecraft platforms 50 in the two slave spacecraft through interferometry generated by local laser emitted by the local interferometry unit in the master spacecraft.
On the ground, the master control system measures inter-satellite long-arm interferometry units 21 in the master spacecraft to obtain second optical path information of a spacecraft platform 50 in the master spacecraft and spacecraft platforms 50 in the two slave spacecraft, calculates relative displacement changes of the spacecraft platforms 50 of the master spacecraft and the spacecraft platforms 50 of the slave spacecraft through an optical path-displacement conversion formula, combines the relative displacement changes of the spacecraft platforms 50 of the two sections of respective spacecraft measured by the local interferometry units 20 of the master spacecraft and the slave spacecraft, adds the three sections of measurement data, and can extract a gravitational wave signal through data processing, and particularly, the data processing mode is a processing mode commonly used in the art, such as a matched filtering processing mode, and the embodiment is not limited.
Compared with the traditional gravitational wave detection device adopting double inspection masses, the spatial gravitational wave detection device based on the single inspection mass, provided by the embodiment, is internally provided with a single polygonal columnar inspection mass 10 which is easy to process, and the polygonal columnar inspection mass 10 has two groups of side surfaces 10a with the included angle of 60 degrees in the normal direction, so that the complex non-dragging control strategy in the traditional orbit plane can be simplified into that the spacecraft platform completely follows the inspection mass to move through the driving part, the cooperation of an electrostatic feedback actuator is not needed any more, and the traditional spatial gravitational wave detection non-dragging control strategy can be effectively simplified; meanwhile, the polygonal columnar detection mass 10 also has four side surfaces 10b which are perpendicular or parallel in pairs, and the polar plates 11 are arranged around the four side surfaces, so that the accuracy of polar plate displacement measurement can be effectively improved; compared with the traditional method adopting double inspection quality, the method adopts single inspection quality, and can effectively reduce the overall quality of the spacecraft.
In one embodiment, as shown in FIG. 3, the local interferometry unit 20 includes a laser 51, a first beam splitter 531, a second beam splitter 532, a third beam splitter 533, a fourth beam splitter 534, a fifth beam splitter 535, a first fast deflector mirror 55, a first mirror 542, a first four-quadrant photodetector 522, a first acousto-optic modulator 561, and a first acousto-optic modulator 562.
The working principle of the local interferometry unit 20 provided in this embodiment is as follows: in an optical platform 20 in a spacecraft, laser light emitted by a laser 51 is split into two beams of laser light C through a first beam splitter 531, wherein one beam of laser light C is split into two beams through a second beam splitter 532, and the two beams are frequency shifted through a first acoustic optical modulator 561 and a second acoustic optical modulator 562 respectively. The laser light frequency shifted by the first acoustic optical modulator 561 is measurement laser light, and the laser light frequency shifted by the second acoustic optical modulator 562 is reference laser light. The measuring laser is emitted to the inspection mass 10 after passing through the first reflecting mirror 542 and the first fast deflecting mirror 55, and the laser reflected by the group of sides 10a of the inspection mass 10 is irradiated on the first four-quadrant photodetector 522 after passing through the first fast deflecting mirror 55 and the third beam splitter 533. The reference laser light passes through the fifth beam splitter 535 and the fourth beam splitter 534 and then irradiates the first four-quadrant photodetector 522. Finally, the measurement laser and the reference laser form interference at the first four-quadrant photodetector 522, and first optical path information of the spacecraft platform of the spacecraft relative to the inspection quality therein is measured.
In one embodiment, as shown in FIG. 3, the inter-satellite long-arm interferometry unit 21 comprises an on-board telescope and an inter-satellite long-arm interferometer, wherein the on-board telescope comprises a second fast deflecting mirror 42 and a primary mirror 41. The inter-satellite long-arm interferometer includes a sixth beam splitter 536, a seventh beam splitter 537, an eighth beam splitter 538, a second mirror 543, and a second four-quadrant photodetector 521.
The working principle of the inter-satellite long arm interferometry unit 21 provided in this embodiment is as follows: in an optical platform 20 in a spacecraft, the reference laser (the laser shifted in frequency by the second optical modulator 562) is split into two beams of laser light D by the sixth beam splitter 536, one beam of laser light D emits inter-satellite long-arm laser light B by the satellite telescope (the second fast deflector 42 and the primary mirror 41), and the other beam of laser light D forms interference laser light by the eighth beam splitter 538, and irradiates on the second four-quadrant photodetector 521. The inter-satellite long-arm laser B emitted by the spacecraft adjacent to the spacecraft is converged by the satellite-borne telescope primary mirror 41 in the optical platform 20 in the spacecraft, sequentially passes through the second fast deflector 42, the seventh beam splitter 537, the second reflector 543 and the eighth beam splitter 538, irradiates on the second four-quadrant photoelectric detector 521 to interfere with the interference laser, and is combined with the measurement of the optical phase-locking unit to obtain the second optical path information of the spacecraft platform of the spacecraft relative to the spacecraft platform of the remote adjacent spacecraft.
In this embodiment, the spaceborne telescope provided in the present invention is fixed on the spacecraft platform of each spacecraft, and because the formation configuration of the spacecraft is changed, the breathing angle is easy to generate, and in order to compensate the breathing angle, the embodiment can perform coarse adjustment by rotating the spaceborne telescope, and then perform fine adjustment by the second fast deflecting mirror 42 inside the spaceborne telescope or the first fast deflecting mirror 55 in the local interferometry unit 20. When the inter-satellite long-arm laser B-direction deviates from the satellite telescope direction, the change can be monitored by measuring with the second four-quadrant photodetector 521 and compensated by rotating the satellite telescope and the second fast-deflecting mirror 42 inside it. The optical stage is fixedly coupled to the satellite telescope, and when the satellite telescope rotates, the local laser a will deviate from the normal direction of the proof mass 10, and the change is detected by the measurement of the first four-quadrant photodetector 522 and compensated by the first fast deflecting mirror 55 in the local interferometry unit 20.
In one embodiment, as shown in fig. 3, the optical phase lock unit includes a ninth beam splitter 539, a tenth beam splitter 530, a third four-quadrant photodetector 523, a first fiber coupler 571, a second fiber coupler 572, a phase meter 58, and an optical phase lock loop 59.
The working principle of the optical phase-locking unit provided by the embodiment is as follows: in the first optical platform 20 of the main spacecraft, the laser light emitted by the laser 51 is split into two laser beams C through the first beam splitter 531, the other laser beam C is split into two laser beams E through the ninth beam splitter 539, one laser beam E is emitted into the other optical platform 20 of the main spacecraft through the first optical fiber coupler 571, and the other laser beam E interferes with the laser light emitted from the laser in the other optical platform of the main spacecraft through the second optical fiber coupler 572 on the third four-quadrant photodetector 523. The detection signal of the third four-quadrant photodetector 523 passes through the phase meter 58 to obtain the phase difference of the two laser beams. The optical phase-locked loop 59 adjusts the phase of the laser emitted by the laser in one of the optical platforms according to the phase difference information, so that the phases of the laser emitted by the two lasers in the main spacecraft are kept consistent.
In the slave spacecraft, the optical path information of the spacecraft platform of the slave spacecraft relative to the spacecraft platform of the remote main spacecraft, which is measured by using the second four-quadrant photoelectric detector 521, is calculated by using the phase meter 58, so as to obtain the inter-satellite long-arm laser phase difference which is received by the spaceborne telescope in the slave spacecraft and is emitted by the inter-satellite long-arm interferometry unit. The optical phase-locked loop 59 adjusts the phase of the laser light emitted from the laser 51 in the spacecraft according to the phase difference information so as to keep the same with the phase of the inter-satellite long-arm laser light received by the satellite telescope.
In one embodiment, the polygonal column-shaped proof mass provided by the present invention may employ a straight octagon column shape, as shown in fig. 4. Four rectangular parallelepiped shapes with rounded corners may also be used, as shown in fig. 5, where four rounded sides may act as mirrors for the local laser and plates may be placed around the remaining four sides.
Of course, a pair of rectangular parallelepiped shapes with specific structures cut out at both end portions of the side may be employed, respectively, the specific structures being rectangular parallelepiped shapes with triangular prisms cut out at one corner, as shown in fig. 6. Specifically, the actual shape of the polygonal columnar inspection mass 10 provided by the invention can be correspondingly designed according to the detection requirement of the actual space gravitational wave, and only two groups of sides with the normal direction included angle of 120 degrees and four sides which are perpendicular or parallel to each other need to be met for the polygonal columnar inspection mass 10, and the embodiment is not limited.
In one embodiment, the invention also adjusts the barycenter of the spacecraft platform 50 to coincide with the barycenter of the inspection mass 10 through a barycenter adjustment technology, such as least square estimation of the on-orbit barycenter position of the electrostatic suspension accelerometer, so as to reduce the influence of inertia force caused by barycenter misalignment, thereby effectively improving the accuracy of space gravitational wave detection.
It will be readily appreciated by those skilled in the art that the foregoing description is merely a preferred embodiment of the invention and is not intended to limit the invention, but any modifications, equivalents, improvements or alternatives falling within the spirit and principles of the invention are intended to be included within the scope of the invention.
Claims (9)
1. The space gravitational wave detection device based on single inspection quality is characterized by comprising a main control system and an equilateral triangle spacecraft formation, wherein the spacecraft formation comprises three spacecrafts with identical configuration and different working modes, the three spacecrafts are divided into a main spacecraft and two slave spacecrafts according to the working modes, an inertial sensing component, a control component, a driving component and two optical components are arranged in a spacecraft platform in each spacecraft,
The inertial sensing component comprises a polygonal columnar inspection mass, wherein the inspection mass comprises two groups of first side surfaces with normal direction included angles of 60 degrees and four second side surfaces which are perpendicular or parallel to each other, and polar plates for detecting displacement sensing and controlling electrostatic feedback are arranged around the four second side surfaces;
The optical component comprises a laser, a local interferometry unit, an inter-satellite long-arm interferometry unit and an optical phase-locking unit, and the laser is used for emitting laser in the same spacecraft; the local interferometry unit is used for emitting local laser to one first side surface of the inspection quality and the inter-satellite long-arm interferometry unit by utilizing the laser, and obtaining first optical path information of a spacecraft platform of the spacecraft relative to the inspection quality in the spacecraft platform by utilizing interferometry generated by the local laser reflected by the first side surface and the emitted local laser; the control component in each spacecraft is used for controlling the driving component in the spacecraft to drive the spacecraft platform of the spacecraft to move along with the inspection mass in the orbit plane according to the first optical path information measured by the local interferometry unit in the spacecraft by using a drag-free algorithm;
The two inter-satellite long-arm interferometry units in each spacecraft are used for respectively transmitting inter-satellite long-arm laser to one inter-satellite long-arm interferometry unit in the two adjacent spacecraft; the optical phase locking unit in the slave spacecraft is used for carrying out phase locking on the inter-satellite long-arm laser emitted by the optical phase locking unit and the phase of the inter-satellite long-arm laser emitted by the master spacecraft, and emitting the inter-satellite long-arm laser after phase locking back to the inter-satellite long-arm interferometry unit in the master spacecraft through the inter-satellite long-arm interferometry unit in the spacecraft, and obtaining second optical path information of a spacecraft platform in the master spacecraft and a spacecraft platform in two slave spacecraft from interferometry generated by local laser emitted by the local interferometry unit in the master spacecraft;
the main control system is used for obtaining space gravitational wave signals on the ground through data processing according to the second optical path information and the first optical path information obtained by measurement of the local interferometry units in the spacecrafts.
2. The single proof mass based spatial gravitational wave detection device of claim 1, wherein said drive means employs a micro-bovine-grade propeller.
3. The single proof mass based spatial gravitational wave detection device of claim 1, wherein said local interferometry unit comprises a first beam splitter, a second beam splitter, a third beam splitter, a fourth beam splitter, a fifth beam splitter, a first fast deflecting mirror, a first reflecting mirror, a first four-quadrant photodetector, a first acousto-optic modulator, and a second acousto-optic modulator;
in the same spacecraft, laser emitted by the laser is divided into two laser beams C through the first beam splitter, one laser beam C is divided into two laser beams C through the second beam splitter, and the two laser beams are subjected to frequency shift through the first acousto-optic modulator and the second acousto-optic modulator respectively; the laser of the first acousto-optic modulator frequency shift is emitted to the first side surface of the inspection quality through the first reflecting mirror and the first rapid deflecting mirror in sequence, and the laser reflected by the first side surface of the inspection quality is irradiated to the first four-quadrant photoelectric detector after passing through the first rapid deflecting mirror and the third beam splitter in sequence; and the laser of the second acoustic optical modulator frequency shift irradiates on a first four-quadrant photoelectric detector after passing through the fifth beam splitter and the fourth beam splitter.
4. The single proof mass based spatial gravitational wave detection device of claim 3, wherein said inter-satellite long arm interferometry unit comprises an on-satellite telescope and an inter-satellite long arm interferometer, said inter-satellite long arm interferometer comprising a sixth beam splitter, a seventh beam splitter, an eighth beam splitter, a second mirror and a second four-quadrant photodetector;
In an optical platform in a spacecraft, after the laser frequency-shifted by the second optical modulator is divided into two beams of laser D by the sixth beam splitter, one beam of laser D emits inter-satellite long-arm laser by the satellite-borne telescope, the other beam of laser D forms interference laser by the eighth beam splitter, and the interference laser irradiates on the second four-quadrant photoelectric detector; and inter-satellite long-arm laser B emitted by a spacecraft adjacent to the spacecraft sequentially passes through the spaceborne telescope, the seventh beam splitter, the second reflector and the eighth beam splitter, and irradiates on the second four-quadrant photoelectric detector to form interferometry with the interference laser so as to obtain second optical path information of a spacecraft platform in the main spacecraft and a spacecraft platform in the two slave spacecraft.
5. The single proof mass based spatial gravitational wave detection device of claim 4, wherein said spaceborne telescope includes a primary mirror and a second fast deflecting mirror.
6. The single proof mass based spatial gravitational wave detection device of claim 4, wherein said optical phase lock unit comprises a ninth beam splitter, a tenth beam splitter, a third four-quadrant photodetector, a first fiber coupler, a second fiber coupler, a phase meter, and an optical phase lock loop;
In one optical platform of the main spacecraft, the other beam of laser C is divided into two beams of laser E through the ninth beam splitter, one beam of laser E is emitted into the other optical platform of the main spacecraft through the first optical fiber coupler, the other beam of laser E interferes with the laser emitted by the laser in the other optical platform of the main spacecraft through the second optical fiber coupler on the third quadrant photoelectric detector, and the phase difference of the laser emitted by the two lasers in the main spacecraft is obtained after the detection signal of the third quadrant photoelectric detector passes through the phase meter; the optical phase-locked loop is used for adjusting the phase of laser emitted by one laser in the main spacecraft according to the phase difference information so as to keep the phases of the laser emitted by the two lasers in the main spacecraft consistent;
In the slave spacecraft, second optical path information of a spacecraft platform in the master spacecraft and second optical path information of spacecraft platforms in the two slave spacecraft are measured by using the second four-quadrant photoelectric detector, and an inter-satellite long-arm laser phase difference which is received by the on-board telescope in the spacecraft and is emitted by the inter-satellite long-arm interferometry unit is calculated by using the phase meter; the optical phase-locked loop adjusts the laser phase emitted by the laser in the spacecraft according to the phase difference information, so that the laser phase is consistent with the inter-satellite long-arm laser phase received by the spaceborne telescope.
7. The single proof mass based spatial gravitational wave detection device of claim 1, wherein said proof mass is a straight octagon.
8. The single proof mass based spatial gravitational wave detection device of claim 1, wherein said proof mass is in the shape of a cuboid with four corners rounded.
9. The spatial gravitational wave detection device based on a single proof mass of claim 1, wherein said proof mass adopts a rectangular parallelepiped shape with a pair of side ends cut out respectively a specific structure, said specific structure being a rectangular parallelepiped shape with a triangular prism cut out at one corner.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210466111.6A CN114814968B (en) | 2022-04-29 | 2022-04-29 | Space gravitational wave detection device based on single inspection quality |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210466111.6A CN114814968B (en) | 2022-04-29 | 2022-04-29 | Space gravitational wave detection device based on single inspection quality |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114814968A CN114814968A (en) | 2022-07-29 |
| CN114814968B true CN114814968B (en) | 2024-05-14 |
Family
ID=82508853
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210466111.6A Active CN114814968B (en) | 2022-04-29 | 2022-04-29 | Space gravitational wave detection device based on single inspection quality |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114814968B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116184518B (en) * | 2023-02-08 | 2024-04-16 | 中国科学院力学研究所 | Laser pointing and phase locking control simulation method and system |
| CN116819637B (en) * | 2023-07-25 | 2024-05-28 | 华中科技大学 | Gravitation effect compensation method and system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1558255A (en) * | 2004-02-11 | 2004-12-29 | 华中科技大学 | Gravitational wave detecting device |
| CN104280785A (en) * | 2013-07-02 | 2015-01-14 | 江南大学 | Space laser interferometer gravitational wave detector design based on TRIZ and method thereof |
| RU2754098C1 (en) * | 2021-02-01 | 2021-08-26 | Федеральное Государственное Унитарное Предприятие "Всероссийский Научно-Исследовательский Институт Физико-Технических И Радиотехнических Измерений" (Фгуп "Вниифтри") | Laser space gravity gradiometer |
| CN115540744A (en) * | 2022-09-26 | 2022-12-30 | 中国科学院空间应用工程与技术中心 | Microgravity measuring device and method |
-
2022
- 2022-04-29 CN CN202210466111.6A patent/CN114814968B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1558255A (en) * | 2004-02-11 | 2004-12-29 | 华中科技大学 | Gravitational wave detecting device |
| CN104280785A (en) * | 2013-07-02 | 2015-01-14 | 江南大学 | Space laser interferometer gravitational wave detector design based on TRIZ and method thereof |
| RU2754098C1 (en) * | 2021-02-01 | 2021-08-26 | Федеральное Государственное Унитарное Предприятие "Всероссийский Научно-Исследовательский Институт Физико-Технических И Радиотехнических Измерений" (Фгуп "Вниифтри") | Laser space gravity gradiometer |
| CN115540744A (en) * | 2022-09-26 | 2022-12-30 | 中国科学院空间应用工程与技术中心 | Microgravity measuring device and method |
Non-Patent Citations (3)
| Title |
|---|
| TianQin: a space-borne gravitational wave detector;Jun Luo;Li-Sheng Chen;Hui-Zong Duan;Yun-Gui Gong;Shoucun Hu;Jianghui Ji;Qi Liu;Jianwei Mei;Vadim Milyukov;Mikhail Sazhin;Cheng-Gang Shao;Viktor T. Toth;Hai-Bo Tu;Yamin Wang;Yan Wang;Hsien-Chi Yeh;Ming-Sheng Zhan;Yonghe Zhang;Vladimir Zharov;Ze-Bing Zhou;General Relativity and Quantum Cosmology;20160112;第33卷(第3期);全文 * |
| 无拖曳控制技术及其应用;胡明;李洪银;周泽兵;;载人航天;20130325(第02期);全文 * |
| 空间激光干涉引力波探测;罗子人;白姗;边星;陈葛瑞;董鹏;董玉辉;高伟;龚雪飞;贺建武;李洪银;李向前;李玉琼;刘河山;邵明学;宋同消;孙保三;唐文林;徐鹏;徐生年;杨然;靳刚;;力学进展;20130725(第04期);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114814968A (en) | 2022-07-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN114814968B (en) | Space gravitational wave detection device based on single inspection quality | |
| US9952154B2 (en) | Separated parallel beam generation for atom interferometry | |
| US10935640B2 (en) | Multiplexed LIDAR transceiver | |
| KR20210092212A (en) | Scanning compensation of scanning lidar | |
| US8724108B2 (en) | Photoelectric autocollimation method and apparatus based on beam drift compensation | |
| US10054427B2 (en) | Orientation variation measurement system, satellite, and orientation variation measurement method | |
| US4473297A (en) | Ring laser gyroscope utilizing phase detector for minimizing beam lock-in | |
| JP4096823B2 (en) | Laser equipment | |
| JP2010054429A (en) | Laser tracker | |
| US9306363B1 (en) | Active bidirectional mode-locked lasers and applications to accurate measurements in navigation systems | |
| CN112433221B (en) | Absolute distance measuring device based on polarization modulation | |
| US5960022A (en) | Diode-pumped solid-state ring laser gyroscope | |
| Chaudhary et al. | Fast steering mirror for optical fine pointing applications: A review paper applications: A review paper | |
| US7414730B2 (en) | High precision interferometer apparatus employing a grating beamsplitter | |
| RU2458356C1 (en) | Heat locator | |
| Lau et al. | The new millennium separated spacecraft interferometer | |
| US9976947B1 (en) | Position measurement device | |
| Meng et al. | An active method for coupling laser with a high-finesse Fabry–Pérot cavity in ultra-stable lasers | |
| He et al. | Laser self-mixing interferometry for precision displacement measurement in resonant gyroscopes | |
| US6441907B1 (en) | High accuracy ring laser interferometer using an external cavity ring laser | |
| RU2381625C1 (en) | Device for stabilising tele-orientation laser system | |
| CN115540744A (en) | Microgravity measuring device and method | |
| CN109489651A (en) | Four-frequency differential laser gyro Faraday magneto-optical glass installation method | |
| CN111433650B (en) | Protection of monostable or quasi-monostable laser rangefinders | |
| Hashimoto et al. | Concept of MEMS ring laser gyroscope with movable optical parts |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |