A space gravitational wave detection telescope and installation method thereof

Abstract

The present invention provides a space gravitational wave detection telescope and an installation method thereof, comprising a primary mirror, wherein a first flexible member is connected to a conical hole in the center of the back of the primary mirror; a secondary mirror, wherein an outer circumference of the secondary mirror is connected to a support member; a frame, wherein the support member is connected to one end of the frame through an adjusting member; a load-bearing body, wherein the first flexible member is connected to an upper portion of one side of the load-bearing body, and a lower portion of one side of the load-bearing body is connected to the other end of the frame through a second flexible member; and a three-mirror, four-mirror, folding mirror assembly, wherein the three-mirror, four-mirror, folding mirror assembly is fixedly connected to the other side of the load-bearing body, and the other side of the load-bearing body is also connected to the frame of an interferometer. The present invention solves the problem that a telescope principle prototype cannot meet high optical path stability requirements during actual production and use, and accelerates the advancement of space gravitational wave detection projects.

Description

Technical Field

[0001] The present invention relates to the field of space laser interferometer gravitational wave detection, and specifically provides a space gravitational wave detection telescope and an installation method thereof. Background Art

[0002] The spectrum of gravitational waves is a function of frequency and time. Wave sources in different frequency bands contain different physical phenomena, from quantum fluctuations in the early universe to supernova explosions and binary black hole mergers. The frequency band is in the range of 0.1-1000mHz. The information contained in the merger of supermassive black holes may reveal the formation and history of the early structure of the universe, the evolution of solar mass black holes from the end of the galaxy to the rotation of extremely large mass ratio black holes, and a large number of binary star systems in the Milky Way.

[0003] The optical telescope is an important component of the laser interferometry system. In order to meet the stringent requirements, it is necessary to comprehensively consider both the optical and mechanical structures. To achieve the reception and transmission of lasers between two spacecraft at a distance of one million kilometers, the wavefront of the telescope system is crucial to the distribution of the intensity and phase of the transmitted and received beams. It is also important that the dimensional stability of the telescope system as part of the interference optical path directly affects the ranging accuracy at the picometer level. Another challenging technical indicator is the limitation of the interferometric measurement at the picometer level on the stray light of the telescope. Since the telescope receives weak lasers from distant spacecraft and emits high-energy lasers to distant spacecraft at the same time, the backscattering of this part of the high-energy laser in the telescope system is required to be less than the weak laser received, otherwise the signal will be completely annihilated. Therefore, the stray light of the telescope is required to be suppressed to 10% of the transmitted laser capability. -8 And optical path stability 10pm / Hz 1 / 2 The above requirements are extremely challenging problems in terms of science and engineering. For the space gravitational wave detection system, the most uncontrollable thing is that the temperature gradient in the orbit environment causes the structure of the telescope to be thermally deformed, which leads to the deterioration of the optical performance of the telescope. The optical interval "jitter" caused by temperature fluctuations will directly convert into the optical path noise of the measurement system, which is related to the success or failure of the system detection.

[0004] At present, the optical telescope in the space interferometric ranging system adopts an off-axis four-mirror afocal system, which has the advantages of no obstruction, short optical tube length and good backscattered stray light characteristics. The primary mirror adopts a parabola, the secondary mirror adopts a hyperbola, and the third and fourth mirrors adopt a spherical surface. The parallel incident light with an aperture of 400mm will converge to a point after passing through the cassette system composed of the primary mirror and the secondary mirror in sequence, and continue to propagate from this point. After passing through the collimation system composed of the third and fourth mirrors, the aperture of the emitted parallel light is reduced to 5mm and enters the interferometer. Due to the strict index requirements in the process of space interferometric ranging and the environmental factors it faces throughout its life cycle, the existing telescope prototype cannot meet the requirements of high optical path stability during actual production and application, affecting the advancement of space gravitational wave detection projects. Summary of the invention

[0005] The purpose of the present invention is to provide a space gravitational wave detection telescope, which solves the problem of the failure to meet the high optical path stability during the actual production and use of the telescope prototype, and accelerates the advancement of space gravitational wave detection. The above purpose is achieved through the following technical solutions:

[0006] A space gravitational wave detection telescope comprises a primary mirror, wherein a first flexible member is connected to a conical hole at the back center of the primary mirror; a secondary mirror, wherein an outer circumference of the secondary mirror is connected to a support member; a frame, wherein the support member is connected to one end of the frame through an adjusting member; a load-bearing body, wherein the first flexible member is connected to an upper portion of one side of the load-bearing body, and a lower portion of one side of the load-bearing body is connected to the other end of the frame through a second flexible member; and a three-mirror four-mirror folding mirror assembly, wherein the three-mirror four-mirror folding mirror assembly is fixedly connected to the other side of the load-bearing body, and the other side of the load-bearing body is also connected to the frame of an interferometer.

[0007] As a more optimal technical solution of the present invention, the primary mirror and the load-bearing body are made of the same material, the secondary mirror and the frame are made of the same material, and the thermal expansion coefficient of the material is less than 8.33×10 -8 K -1 .

[0008] As a more optimal technical solution of the present invention, the primary mirror, secondary mirror, load-bearing body and frame are made of glass-ceramic, and the first flexible part, the second flexible part and the adjusting part are made of Invar.

[0009] As a more optimal technical solution of the present invention, the first flexible part includes a flexible connecting part and a flexible inlay part. The flexible connecting part is bonded to the conical hole in the center of the back of the main mirror, and the flexible inlay part is bonded to the hole on the load-bearing body. The flexible connecting part and the flexible inlay part are connected as a whole by a first bolt.

[0010] As a more optimal technical solution of the present invention, the second flexible member is bonded to the holes on the load-bearing body and the frame, one end of the second flexible member is a convex edge end, and the other end protrudes from the surface of the load-bearing body and the frame, the two second flexible members are connected as a whole by a second bolt, a compression disc spring is placed between the nut of the second bolt and the convex edge end, and a spherical pad is placed between the screw root of the second bolt and the convex edge end.

[0011] As a more optimal technical solution of the present invention, the telescope further comprises an outer cover body surrounding the primary mirror and the secondary mirror, and the outer cover body is fixedly connected to the load-bearing main component.

[0012] Another object of the present invention is to provide a method for installing a space gravitational wave detection telescope, the specific steps of which are as follows:

[0013] Step 1: assemble and adjust the telescope optical system to determine the initial relative spatial positions of the primary mirror, secondary mirror, three-mirror, four-mirror folding mirror assembly;

[0014] Step 2: Determine the adjustment amount of the load-bearing body and the frame according to their relative spatial positions;

[0015] Step 3, connecting the unpolished and uncoated primary mirror to the load-bearing body through the first flexible member, and then polishing and coating the primary mirror;

[0016] Step 4: Connect the load-bearing body and the frame into one piece through the second flexible member;

[0017] Step 5: Connect the secondary mirror to the frame through the support member;

[0018] Step 6: Connect the three-mirror, four-mirror folding mirror assembly and the interferometer to the load-bearing body;

[0019] Step 7. Observe whether the interference image of the telescope in the interferometer is ideal. If not, remove the adjustment parts between the support and the frame, and change the distance between the secondary mirror and the primary mirror by replacing the adjustment parts with different thicknesses until an ideal interference image is obtained.

[0020] As a more optimal technical solution of the present invention, the primary mirror and the secondary mirror are specifically installed and adjusted as follows: the primary mirror is fixed, the plane reflector is placed in front of the primary mirror, the normal direction of the plane reflector and the position and orientation of the interferometer are adjusted, so that the laser beam emitted by the interferometer becomes a parallel beam after passing through the primary mirror, and the parallel beam is incident on the primary mirror as a parallel beam after being reflected by the plane reflector. After being reflected by the primary mirror, all parallel beams will be incident on the interferometer again to form an interference image; at this time, the positions of the plane reflector and the primary mirror are fixed, and the interferometer is removed; the secondary mirror is placed below the plane reflector, and its pitch and yaw angles are adjusted, and then the position of the interferometer and the direction of its outgoing beam are adjusted, so that the laser signal emitted from the interferometer is first reflected by the secondary mirror, the primary mirror and the plane reflector, and then successively passes through the primary mirror and the secondary mirror and is finally reflected back to the interferometer to form an interference image, and the secondary mirror is fixed.

[0021] As a more optimal technical solution of the present invention, the three-mirror and four-mirror installation and adjustment are specifically as follows: the converging light beam emitted from the interferometer reaches the spatial center position of the three mirrors, and the converging light beam emitted from the interferometer is incident on the surface of the three mirrors and is reflected back into the interferometer, and finally an interference image can be observed in the interferometer, and the three mirrors are installed; the converging light beam emitted from the interferometer reaches the spatial center position of the four mirrors, and the converging light beam emitted from the interferometer is incident on the surface of the four mirrors and is reflected back into the interferometer, and finally an interference image can be observed in the interferometer, and the four mirrors are installed, and the position of the interferometer is also determined.

[0022] Compared with the prior art, the present invention can achieve the following beneficial effects:

[0023] The design and installation method of the reflector assembly and the reflector support structure in the space gravitational wave detection telescope of the present invention improve the performance of the whole machine, can eliminate or reduce the support reaction force and torque on the reflector, ensure that the reflector adapts to the thermal deformation condition, thereby reducing the distortion of the reflector surface shape caused by the temperature field change condition; the reflector support structure should be able to remain in the linear elastic deformation range under the conditions of acceleration, impact and vibration, so as to elastically restore the surface shape and posture of the reflector; the design of the reflector support structure also takes into account the convenience of installation and adjustment, and reduces the distortion of the reflector surface shape caused by installation. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a schematic diagram of the connection structure of the primary mirror, secondary mirror, frame and load-bearing body of the space gravitational wave detection telescope of the present invention;

[0025] Figure 2 is a structural schematic diagram of the support structure of the present invention;

[0026] Figure 3 It is a schematic diagram of the connection structure between the primary mirror and the load-bearing body of the present invention;

[0027] Figure 4 It is a schematic diagram of the connection structure between the load-bearing body and the frame of the present invention;

[0028] Figure 5 It is a structural schematic diagram of the space gravitational wave detection telescope of the present invention. DETAILED DESCRIPTION

[0029] Hereinafter, embodiments of the present invention will be described with reference to the accompanying drawings. In the following description, the same modules are represented by the same reference numerals. In the case of the same reference numerals, their names and functions are also the same. Therefore, the detailed description thereof will not be repeated.

[0030] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and do not constitute a limitation of the present invention.

[0031] Example 1

[0032] The present invention provides a space gravitational wave detection telescope such as Figures 1 to 5 As shown, it includes a primary mirror 1, wherein a first flexible member is connected to the tapered hole at the back center of the primary mirror 1; a secondary mirror 2, wherein a support member 17 is connected to the outer circumference of the secondary mirror 2; a support structure 3, wherein the support structure includes a frame 4 and a load-bearing body 5, wherein the support member 17 is connected to one end of the frame 4 via an adjusting member 16; the first flexible member is connected to an upper portion of one side of the load-bearing body 5, and a lower portion of one side of the load-bearing body 5 is connected to the other end of the frame 4 via a second flexible member 11; a three-mirror four-mirror folding mirror assembly 10, wherein the three-mirror four-mirror folding mirror assembly 10 is fixedly connected to the other side of the load-bearing body 5, and the other side of the load-bearing body 5 is also connected to the frame of the interferometer.

[0033] The dimensions and weights of the reflectors of the present invention are shown in Table 1.

[0034] Table 1

[0035] Diameter / mm Thickness / mm Weight / kg Primary mirror 416 65 3.14 secondary mirror 27.6 21 0.039 Three mirrors 11 13 0.002 Four mirrors 15 14 0.003 Folding mirror 1 10.6 11 0.003 Folding Mirror 2 16 11 0.004

[0036] In some embodiments, the primary mirror 1 and the load-bearing body 5 are made of the same material, the secondary mirror 2 and the frame 4 are made of the same material, and the thermal expansion coefficient of the material is less than 8.33×10 -8 K -1 .

[0037] In some embodiments, the primary mirror 1 , the secondary mirror 2 , the load-bearing body 5 and the frame 4 are made of glass-ceramics, and the first flexible member, the second flexible member 11 and the adjusting member 16 are made of Invar.

[0038] In some embodiments, the first flexible member includes a flexible connector 7 and a flexible inlay 6, the flexible connector 7 is bonded to the conical hole at the back center of the primary mirror 1, the flexible inlay 6 is bonded to the hole on the load-bearing body 5, and the flexible connector 7 and the flexible inlay 6 are connected as a whole by a first bolt 8.

[0039] In some embodiments, the second flexible member 11 is bonded to the holes on the load-bearing body 5 and the frame 4, one end of the second flexible member 11 is a convex end, and the other end slightly protrudes from the surface of the load-bearing body 5 and the frame 4 to prevent the microcrystalline glass from breaking during loading. The two second flexible members 11 are connected as a whole by a second bolt, a compression disc spring 9 is placed between the nut 14 of the second bolt and the convex end, and a spherical pad 12 is placed between the screw root 13 of the second bolt and the convex end.

[0040] In some embodiments, the telescope further includes an outer cover 15 , which is fixedly connected to the load-bearing main component 5 , and the outer cover 15 surrounds the primary mirror 1 and the secondary mirror 2 .

[0041] In some embodiments, the primary mirror 1 has an aperture of 416 mm and is made of microcrystalline glass. A triangular hole is provided on the back to reduce weight. The weight of a single mirror is 3.14 kg and a back center support is used. Compared with a three-point back support, the center support has fewer support points and contact surfaces. In the case of temperature fluctuations, there is no thermal stress extrusion between support points, which is more conducive to maintaining surface shape accuracy.

[0042] In some embodiments, the first flexible member is made of Invar, and its linear expansion coefficient is modulated to be consistent with the microcrystalline glass used in the mirror body.

[0043] In some embodiments, the secondary mirror 2 is bonded to the support 17, and a mechanical interface is provided on the support 17. The secondary mirror 1 has an aperture of 40 mm, is made of microcrystalline glass, has a single mirror mass of 0.02 kg, and the support 17 is made of invar steel, with a mass of 0.03 kg.

[0044] In some embodiments, the load-bearing body 5 of the telescope carries the main mirror assembly, the three-mirror four-mirror folding mirror assembly 10 and the frame 4 with relatively large mass, and is connected to the interferometer platform frame. The load-bearing body 5 is made of a whole piece of lightweight microcrystalline glass and has a mass of 11.6 kg.

[0045] In some embodiments, the frame 4 provides a support position for the secondary mirror assembly, directly affecting the optical spacing between the primary mirror 1 and the secondary mirror 2 and the position accuracy of the secondary mirror 2. The selection of microcrystalline glass as its material and the connection method with the load-bearing body 5 are factors that reduce the impact of temperature fluctuations on the stability of the optical path. The frame 4 is made of 5mm microcrystalline glass after lightweight splicing, connected by pre-embedded invar steel, has good dynamic and static stiffness, and has a mass of 3.98kg.

[0046] In some embodiments, the outer cover 15 is made of carbon fiber composite material to meet the ultra-high stability requirements of the telescope. The outer cover 15 is installed on the load-bearing main component 5 of the core measurement system and connected through Invar connectors to release the axial degree of freedom and reduce the impact of the thermal elastic deformation of the outer cover 15 on the core measurement system.

[0047] Example 2

[0048] A method for installing a space gravitational wave detection telescope, the specific steps are as follows:

[0049] Step 1: assemble and adjust the telescope optical system to determine the initial relative spatial positions of the primary mirror 1, the secondary mirror 2, and the three-mirror four-mirror folding mirror assembly 10;

[0050] Step 2: Determine the adjustment amount of the load-bearing body 5 and the frame 4 according to their relative spatial positions;

[0051] Step 3: Connect the unpolished and uncoated primary mirror 1 to the load-bearing body 5 through the first flexible member, and then polish and coat the primary mirror 1;

[0052] Step 4: Connect the load-bearing body 5 and the frame 4 into one piece through the second flexible member 11;

[0053] Step 5: Connect the secondary mirror 2 to the frame 4 through the support member 17;

[0054] Step 6: Connect the three-mirror, four-mirror folding mirror assembly 10 and the interferometer to the load-bearing body 5;

[0055] Step 7: Observe whether the interference image of the telescope in the interferometer is ideal. If not, remove the adjustment member 16 between the support member 17 and the frame 4, and change the distance between the secondary mirror 2 and the primary mirror 1 by replacing the adjustment member 16 with different thicknesses until an ideal interference image is obtained.

[0056] In some embodiments, the off-axis four-mirror telescope optical system first installs and adjusts the primary mirror 1 and the secondary mirror 2 as follows: fix the primary mirror 1, place the plane mirror in front of the primary mirror 1, adjust the normal direction of the plane mirror and the position and direction of the interferometer, so that the laser beam emitted by the interferometer becomes a parallel beam after passing through the primary mirror, and the parallel beam is reflected by the plane mirror and then incident on the primary mirror 1 as a parallel beam. After being reflected by the primary mirror 1, all parallel beams will be incident on the interferometer again to form an interference image; at this time, fix the position of the plane mirror and the primary mirror, and remove the interferometer; place the secondary mirror 2 below the plane mirror, adjust its pitch and yaw angles, and then adjust the position of the interferometer and the direction of its outgoing beam, so that the laser signal emitted from the interferometer is first reflected by the secondary mirror 2, the primary mirror 1 and the plane mirror, and then successively passes through the primary mirror 1 and the secondary mirror 2 and is finally reflected back to the interferometer to form an interference image, and fix the secondary mirror.

[0057] In some embodiments, the off-axis four-mirror telescope optical system is first adjusted by three mirrors and then four mirrors as follows: the convergent light beam emitted from the interferometer reaches the spatial center position of the three mirrors, and the convergent light beam emitted from the interferometer is incident on the surface of the three mirrors and then reflected back into the interferometer, and finally an interference image can be observed in the interferometer, and the three mirrors are installed; the convergent light beam emitted from the interferometer reaches the spatial center position of the four mirrors, and the convergent light beam emitted from the interferometer is incident on the surface of the four mirrors and then reflected back into the interferometer, and finally an interference image can be observed in the interferometer, and the four mirrors are installed, and the position of the interferometer is also determined.

[0058] The primary mirror and secondary mirror of the telescope of the present invention adopt aspherical reflectors, and the third mirror and the fourth mirror adopt spherical reflectors. The whole system has relatively high requirements for the precision of installation and adjustment, especially the primary mirror and the secondary mirror, which are more sensitive to the performance of the whole optical system. In order to minimize the influence of sensitive factors on the whole telescope system during the installation process, the primary mirror is first fixed, and the primary mirror is used as the installation and adjustment reference, and then the secondary mirror, the third mirror and the fourth mirror, and the plane reflector are installed and adjusted, and finally the installation and debugging of the whole telescope system is realized.

[0059] Verification Example

[0060] UG modeling was used, and the geometry was imported into hypermesh to create a finite element model, which was solved by optistruct. The specific analysis included: static analysis (temperature change, static load of gravity): the telescope was installed and tested on the ground, which is different from the actual working conditions of microgravity in space, and system-level considerations are required. Therefore, the core detection system uses three-point bottom support on the ground to minimize the changes in the surface position of optical components caused by gravity release. Using this as the boundary condition, gravity and temperature deflection analysis was performed, and the displacement field results were substituted into the optical software, and the telescope system wave aberration was used as the indicator export for evaluation; modal analysis: simulate the fixed breathing angle transition section to examine whether the system can withstand the launch environment.

[0061] (1)-Y-axis gravity

[0062] The results of the mirror node displacement in the finite element displacement field were extracted and processed to obtain the relevant parameters of the surface of each optical element. Table 2 shows the PV value, RMS value, rigid body displacement in three directions and rotation angle around the X, Y and Z axes of the important component surfaces.

[0063] Table 2

[0064]

[0065]

[0066] The optical surface shape and rigid body displacement results were extracted and substituted into the optical software Zemax to simulate the wave aberration of the telescope system under microgravity conditions. The system wave aberration PV value was 00784λ and the RMS value was 0.016λ (λ=1064nm).

[0067] (2) -Y direction gravity + 3℃ temperature rise coupling

[0068] The system processed the results of the mirror node displacement in the finite element displacement field extracted by gravity in the -Y direction and 3°C temperature, and obtained the relevant parameters of the surface of each optical element. Table 3 shows the PV value, RMS value, rigid body displacement in three directions, and rotation angle around the X, Y, and Z axes of the important component surfaces.

[0069] Table 3

[0070] surface PV / nm rms / nm dx / μm dy / μm dz / μm rx / μrad ry / μrad rz / μrad Primary mirror 47.29 8.895 -0.012 -0.212 2.041 4.575 0.076 -0.001 secondary mirror 0.145 0.029 0.008 -0.026 1.009 1.753 0.1 -0.18 Three mirrors 0.027 0.006 -0.003 -1.259 1.225 11.03 0.07 0.011 Four mirrors 0.014 0.004 -0.008 -0.56 1.009 11.14 0.08 0.013

[0071] The optical surface shape and rigid body displacement results were extracted and substituted into the optical software Zemax to simulate the wavefront aberration of the telescope system under temperature rise conditions. The PV value of the system wavefront aberration was 0.1024λ, and the RMS value was 0.016λ (λ=1064nm).

[0072] (3) Steady-state temperature field of the optomechanical structure on-orbit

[0073] According to the steady-state temperature field information obtained by thermal analysis, the deformation of the optical-mechanical structure was analyzed for the difference between the steady-state temperature field on orbit and the uniform temperature level of 20°C on the ground, and the integrated analysis environment was introduced to analyze the impact on the optical system. The secondary mirror is about 23.8°C lower than the primary mirror. The thermal deformation of the optical-mechanical structure is shown in Table 4, and the maximum displacement is about 1.6μm.

[0074] Table 4

[0075]

[0076]

[0077] When the integrated analysis environment is introduced, the RMS value of the system wave aberration is 0.017λ (λ=1064nm), which indicates that the optical-mechanical structure of the present invention is insensitive to the steady-state temperature field and has little influence.

[0078] (4) Steady-state temperature field of the optomechanical structure on-orbit

[0079] When the ambient temperature of the telescope increases by 100μK, the position of each optical element changes. The changes of the third and fourth mirrors are relatively small. The changes of the positions of the primary and secondary mirrors are shown in the table. Combined with the changes in the radius of curvature of each optical element, it can be concluded that the change in the angle between the output light and the image plane is 8.20E-12rad, as shown in Table 5.

[0080] Table 5

[0081]

[0082] (5) Modal analysis

[0083] After performing modal analysis on the core measurement system, it was found that the structural modal frequency is relatively high and can fully withstand the launch environment.

[0084] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0085] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means 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 may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0086] Although the embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and cannot be understood as limiting the present invention. Those skilled in the art may change, modify, replace and modify the above embodiments within the scope of the present invention.

Claims

1. A space gravitational wave detection telescope, characterized in that: include: A primary mirror, wherein a first flexible member is connected to a conical hole at the back center of the primary mirror; A secondary mirror, wherein the outer circumference of the secondary mirror is connected to a support member; A frame, wherein the support member is connected to one end of the frame through an adjusting member; A load-bearing body, wherein the first flexible member is connected to an upper portion of one side of the load-bearing body, and a lower portion of one side of the load-bearing body is connected to the other end of the frame via a second flexible member; A three-mirror, four-mirror, folding-mirror assembly, wherein the three-mirror, four-mirror, folding-mirror assembly is fixedly connected to the other side of the load-bearing body, and the other side of the load-bearing body is also connected to the frame of the interferometer; The first flexible component includes a flexible connecting component and a flexible inlay component. The flexible connecting component is bonded to the conical hole at the back center of the primary mirror, and the flexible inlay component is bonded to the hole on the load-bearing body. The flexible connecting component and the flexible inlay component are connected as a whole by a first bolt.

2. The space gravitational wave detection telescope according to claim 1, characterized in that: The primary mirror and the load-bearing body are made of the same material, the secondary mirror and the frame are made of the same material, and the thermal expansion coefficient of the material is less than 8.33×10 -8 K -1 .

3. The space gravitational wave detection telescope according to claim 1, characterized in that: The primary mirror, secondary mirror, load-bearing body and frame are made of glass-ceramic, and the first flexible part, the second flexible part and the adjusting part are made of Invar.

4. The space gravitational wave detection telescope according to claim 1, characterized in that: The second flexible member is bonded to the holes on the load-bearing body and the frame, one end of the second flexible member is a convex edge end, and the other end protrudes from the surface of the load-bearing body and the frame, the two second flexible members are connected as a whole by a second bolt, a compression disc spring is placed between the nut of the second bolt and the convex edge end, and a spherical pad is placed between the screw root of the second bolt and the convex edge end.

5. The space gravitational wave detection telescope according to claim 1, characterized in that: The telescope also includes an outer cover body surrounding the primary mirror and the secondary mirror, and the outer cover body is fixedly connected to the load-bearing main component.

6. The method for installing a space gravitational wave detection telescope as claimed in claim 1, wherein the specific steps are as follows: Step 1: assemble and adjust the telescope optical system to determine the initial relative spatial positions of the primary mirror, secondary mirror, three-mirror, four-mirror folding mirror assembly; Step 2: Determine the adjustment amount of the load-bearing body and the frame according to their relative spatial positions; Step 3, connecting the unpolished and uncoated primary mirror to the load-bearing body through the first flexible member, and then polishing and coating the primary mirror; Step 4: Connect the load-bearing body and the frame into one piece through the second flexible member; Step 5: Connect the secondary mirror to the frame through the support member; Step 6: Connect the three-mirror, four-mirror folding mirror assembly and the interferometer to the load-bearing body; Step 7. Observe whether the interference image of the telescope in the interferometer is ideal. If not, remove the adjustment parts between the support and the frame, and change the distance between the secondary mirror and the primary mirror by replacing the adjustment parts with different thicknesses until an ideal interference image is obtained.

7. The method for installing a space gravitational wave detection telescope according to claim 6, characterized in that: The primary mirror and the secondary mirror are specifically installed and adjusted as follows: the primary mirror is fixed, the plane reflector is placed in front of the primary mirror, the normal direction of the plane reflector and the position and orientation of the interferometer are adjusted, so that the laser beam emitted by the interferometer becomes a parallel beam after passing through the primary mirror, and the parallel beam is incident on the primary mirror as a parallel beam after being reflected by the plane reflector. After being reflected by the primary mirror, all parallel beams will be incident on the interferometer again to form an interference image; at this time, the positions of the plane reflector and the primary mirror are fixed; the secondary mirror is placed below the plane reflector, its pitch and yaw angles are adjusted, and then the position of the interferometer and the direction of its outgoing beam are adjusted, so that the laser signal emitted from the interferometer is first reflected by the secondary mirror, the primary mirror and the plane reflector, and then successively passes through the primary mirror and the secondary mirror and is finally reflected back to the interferometer to form an interference image, and the secondary mirror is fixed.

8. The method for installing a space gravitational wave detection telescope according to claim 6, characterized in that: The three-mirror and four-mirror installation and adjustment are specifically as follows: the converging light beam emitted from the interferometer reaches the spatial spherical center position of the three mirrors, and the converging light beam emitted from the interferometer is incident on the surface of the three mirrors and then reflected back into the interferometer, and finally an interference image can be observed in the interferometer, and the three mirrors are installed; the converging light beam emitted from the interferometer reaches the spatial spherical center position of the four mirrors, and the converging light beam emitted from the interferometer is incident on the surface of the four mirrors and then reflected back into the interferometer, and finally an interference image can be observed in the interferometer, and the four mirrors are installed, and the position of the interferometer is also determined.

Images