Vertical adjustment, support and detection integrated system and method for large-aperture space reflector

Abstract

The invention discloses a vertical installation, adjustment, support and detection integrated system for a large-aperture space reflector. The vertical installation, adjustment, support and detection integrated system comprises a primary mirror chamber, a primary mirror, a statically determinate support assembly, a locking support assembly and a test assembly, statically-determinate supporting of the primary mirror is achieved through the statically-determinate supporting assembly. In the testing stage, one end of the locking and supporting assembly is bonded with the back of the primary mirror, the other end of the locking and supporting assembly is connected with a primary mirror chamber through the testing assembly, and the primary mirror surface shape is tested in the gravity unloading state; in the launching stage, one end of the locking and supporting assembly is bonded with the back of the primary mirror, and the other end is fixedly connected with the primary mirror chamber; when the active section is launched, the locking and supporting assembly is locked, the primary mirror is supported in an auxiliary mode, after injection, the locking and supporting assembly is unlocked, and the locking and supporting assembly is separated from a mirror chamber of the primary mirror. According to the invention, gravity unloading is carried out on the primary mirror in the test stage, the gravity influence is reduced, and the in-orbit surface shape precision is simulated; auxiliary support is provided in the active section, and the vibration resistance of the primary mirror is improved; and unlocking is carried out after injection, thereby realizing static support of the reflector and ensuring the stability of the in-orbit surface shape.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of space optical remote sensor, and particularly relates to a large-aperture space mirror vertical installation, support, detection integrated system and method. BACKGROUND

[0002] With the increase of the aperture of space optical load, the inconsistency of gravity environment between space and ground increasingly affects the ground installation, testing. Among them, the primary mirror is the largest optical component in the space optical load, and its surface accuracy is most obviously affected by gravity. The main means for current large-aperture space cameras to realize space-ground consistency evaluation is horizontal installation and detection, that is, the space camera is laid horizontally, in this direction, the optical component surface is least affected by gravity, and then the optical component position is unloaded through an external unloading tool, so as to realize system wavefront and transfer function testing. However, with the increase of the aperture of space optical load to 3 meters and more, due to the limitation of space transportation, large-aperture space optical load is installed vertically, and is launched vertically. If the horizontal installation and detection technical route is adopted, the optical load needs to be transformed between the two attitudes multiple times, which increases the development cost and technical risk of additional supporting tool equipment. When the vertical installation technical route is adopted, it is difficult to ensure that the large-aperture mirror has good surface shape in the system integration state, at this time, the number of mirror support points needs to be increased to reduce the mirror surface shape change, and more than 54 support points are needed for a 4m-aperture space mirror to meet the testing requirements. However, the increase of the number of support points will lead to a straight-line increase in the complexity of the whole system, and also cause a series of problems such as weight increase, assembly stress, thermal stress and the like of the whole support system. SUMMARY

[0003] The present application aims to overcome the above-mentioned defects, and provides a large-aperture space mirror vertical installation, support, detection integrated system and method, which solves the technical problem that in the process of vertical installation and integrated testing of large-aperture space camera, the large-aperture primary mirror is greatly deformed by gravity, and it is difficult to directly obtain accurate wavefront test results and MTF test effects. The present application provides gravity unloading for the primary mirror in the system integration testing stage, reduces the gravity influence, simulates the on-orbit surface accuracy, provides auxiliary support in the active stage, improves the vibration resistance of the primary mirror, and unlocks after entering the orbit to realize static support of the mirror and guarantee the on-orbit surface stability.

[0004] To achieve the above-mentioned application purposes, the present application provides the following technical solutions: A large-aperture space mirror vertical installation, support, detection integrated system, comprising: a primary mirror mirror chamber, a primary mirror, a static support assembly, a locking support assembly and a testing assembly; One end of the static support assembly is fixedly connected with the primary mirror mirror chamber, and the other end is adhesively connected with the back of the primary mirror; the static support of the primary mirror is realized through a plurality of groups of static support assemblies; In the system integration test stage, one end of the locking support assembly is bonded to the back of the primary mirror, and the other end is connected to the primary mirror cell through the test assembly. The test assembly performs gravity unloading on the primary mirror. In the gravity unloading state, the surface shape of the primary mirror is tested. After the test is completed, the test assembly is removed. In the launch stage, one end of the locking support assembly is bonded to the back of the primary mirror, and the other end is fixedly connected to the primary mirror cell. The locking support assembly is locked during the active segment launch to provide auxiliary support for the primary mirror. After entering the orbit, the locking support assembly is unlocked, and the locking support assembly is separated from the primary mirror cell.

[0005] Further, the statically determinate support assembly includes a statically determinate support disc, a statically determinate support BIPOD rod, and a statically determinate support BIPOD seat. The statically determinate support BIPOD rod is connected to the statically determinate support disc and the statically determinate support BIPOD seat at both ends. The statically determinate support disc is bonded to the back of the primary mirror, and the statically determinate support BIPOD seat is fixedly connected to the primary mirror cell.

[0006] Further, the locking support assembly includes a locking support disc and a memory alloy unlocker. The locking support disc is bonded to the back of the primary mirror. A radial ball bearing is installed at the center of the locking support disc. The memory alloy unlocker has a bearing rod at one end and a mounting flange at the other end. The mounting flange is fixedly installed on the primary mirror cell through a height-raising sleeve, and the bearing rod cooperates with the radial ball bearing to realize the connection with the locking support disc. The height-raising sleeve is used to simulate the height of the test assembly. A tapered slot is designed on the bearing rod. After entering the orbit, the tapered slot is heated to achieve thermal fracture and unlock.

[0007] Further, the statically determinate support disc, the statically determinate support BIPOD rod, and the statically determinate support BIPOD seat are made of invar steel with a linear expansion coefficient less than or equal to 0.03 ppm.

[0008] Further, the locking support disc is made of invar steel with a linear expansion coefficient less than or equal to 0.03 ppm.

[0009] Further, the test assembly includes an actuator and a force sensor. During the installation and adjustment test, the force sensor is installed on the primary mirror cell. The actuator has a ball head at one end and a mounting flange at the other end. The actuator mounting flange is screw-connected with the force sensor, the actuator ball head is connected with the mounting flange of the memory alloy unlocker, and the bearing rod of the memory alloy unlocker cooperates with the radial ball bearing to realize the connection between the memory alloy unlocker and the locking support disc. The actuator applies an acting force to the back of the primary mirror along the moving direction of the actuator, and the force sensor is used to display the acting force of the back of the primary mirror, and the unloading state is simulated through the actuator and the force sensor, and the primary mirror surface is tested in the unloading state.

[0010] Further, during the test, the position of the actuator is adjusted so that the value displayed by the force sensor is consistent with the design value.

[0011] Further, the statically determinate support assembly and the locking support assembly are uniformly distributed along the circumference.

[0012] Further, the statically determinate support assembly is 3-6 groups. The locking support assembly is 20-30 groups.

[0013] A large-diameter space mirror vertical assembly, support, detection integrated method is realized by using the large-diameter space mirror vertical assembly, support, detection integrated system, and the method comprises the steps of: One end of the statically determinate support assembly is fixedly connected with the primary mirror chamber, and the other end is bonded with the back of the primary mirror; the statically determinate support assembly is used to realize the statically determinate support of the primary mirror; In the real situation, one end of the locking support assembly is bonded with the back of the primary mirror, and the other end is fixedly connected with the primary mirror chamber; the locking support assembly is locked during the active segment emission, and the primary mirror is supported; after entering the orbit, the locking support assembly is unlocked, and the locking support assembly is separated from the primary mirror chamber; During the test, one end of the locking support assembly is bonded with the back of the primary mirror, and the other end is connected with the primary mirror chamber through the test assembly; the test assembly is used to simulate the unloading state, and the primary mirror surface is tested in the unloading state; after the test is completed, the test assembly is removed.

[0014] Compared with the prior art, the present application has at least one of the following beneficial effects: (1) The present application can effectively simulate the on-orbit surface of the primary mirror during the assembly, detection and testing stage, and support the ground high-precision performance test of the large-diameter space optical load. (2) The vertical assembly, support and test technical route of the large-diameter space optical load in the present application greatly reduces the development cost compared with the horizontal assembly, support and test route. BRIEF DESCRIPTION OF DRAWINGS

[0015] Figure 1 The assembly diagram of the support and detection integrated support system is shown in the figure. Figure 2 The figure shows the connection between the statically determinate support assembly and the primary mirror. Figure 3 The cross-sectional view of the connection between the locking support assembly and the primary mirror is shown in the figure. DETAILED DESCRIPTION

[0016] The features and advantages of the present application will become more apparent from the detailed description in combination with the accompanying drawings upon reading of the following detailed description.

[0017] The term "exemplary" is used herein to mean "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other implementations. Unless specifically stated otherwise, the present disclosure is not to be construed as using terms or phrases for the purpose of excluding the use of such terms or phrases by a competitor.

[0018] The primary mirror is gravity unloaded in the system integration test phase, the gravity effect is reduced, and the on-orbit surface accuracy is simulated; the auxiliary support is provided in the active section, and the primary mirror vibration resistance performance is improved; the primary mirror is unlocked after entering the orbit, the static support of the mirror is realized, and the on-orbit surface stability is ensured.

[0019] The application is a space large-aperture mirror support and inspection integrated support system, which comprises a primary mirror chamber, a primary mirror, a static support disc, a static support BIPOD rod, a static support BIPOD seat, a locking support disc, a memory alloy unlocker, an actuator and a force sensor.

[0020] One end of the static support assembly is screw-connected with the primary mirror chamber through the static support BIPOD seat.

[0021] The other end of the static support assembly is bonded with the back of the primary mirror through the static support disc.

[0022] The locking support disc is bonded with the back of the primary mirror.

[0023] A radial ball bearing is installed at the center of the locking support disc.

[0024] One end of the unlocker is a bearing rod structure, and the other end is a mounting flange structure.

[0025] One end of the actuator is a ball head structure, and the other end is a mounting flange structure.

[0026] During the assembly and adjustment test process, the force sensor is installed on the primary mirror chamber, the mounting flange end of the actuator is screw-connected with the force sensor, and the ball head structure is in contact with the mounting flange of the memory alloy unlocker.

[0027] During the movement of the actuator, the back of the primary mirror will be subjected to a force in the movement direction of the actuator.

[0028] The force sensor displays the force acting on the back of the primary mirror, and the displacement of the actuator is adjusted so that the display value of the force sensor is consistent with the design value.

[0029] In the process of vertical installation and integration test of large aperture space optical load, the main mirror gravity unloading, simulation of on-orbit stress conditions, and more accurate wavefront test results and MTF test results are obtained.

[0030] After the test, the force sensor and the actuator are removed.

[0031] One end of the unlocking flange is fixed to the main mirror chamber through a height sleeve, and the other end of the bearing rod is connected with the locking support disc bearing.

[0032] The unlocking device is composed of high-strength memory alloy, which provides auxiliary support in the stretching and shearing direction of the main mirror assembly.

[0033] The active section anti-vibration ability is improved.

[0034] After the unlocking device is launched into orbit, it is unlocked and separated from the main mirror, and only the statically determinate support assembly is connected to the main mirror and the main mirror chamber.

[0035] The high stability of the main mirror surface after being launched into orbit is realized.

[0036] Embodiment: The application is a kind of space large aperture mirror support and inspection integrated support system, as shown in Figure 1 、 Figure 2 、 Figure 3 , comprising: a main mirror chamber 1, a main mirror 2, a statically determinate support disc 3, a statically determinate support BIPOD rod 4, a statically determinate support BIPOD seat 5, a locking support disc 6, a memory alloy unlocking device 7, an actuator 8, and a force sensor 9. Among them, the statically determinate support disc 3, the statically determinate support BIPOD rod 4 and the statically determinate support BIPOD seat 5 form a statically determinate support assembly 10, and the locking support disc and the memory alloy unlocking device form a locking support assembly 11.

[0037] The statically determinate support disc 3, the statically determinate support BIPOD rod 4 and the statically determinate support BIPOD seat 5 are made of invar with a linear expansion coefficient of 0.03ppm.

[0038] One end of the statically determinate support assembly 10 is connected with the main mirror chamber 1 through the statically determinate support BIPOD seat 5.

[0039] The other end of the statically determinate support assembly 10 is bonded with the back of the main mirror through the statically determinate support disc 3.

[0040] The six statically determinate support assemblies 10 connect the main mirror with the main mirror chamber, and realize the statically determinate support of the main mirror.

[0041] The locking support disc 6 is made of invar with an expansion coefficient of 0.03ppm, and a total of 24 locking support discs 6 are bonded with the back of the main mirror.

[0042] The radial ball bearing is installed at the center of the locking support disc.

[0043] The actuator is provided with a bearing rod structure at one end and a mounting flange structure at the other end, and the number of the actuator is 24, which is consistent with the number of the locking support disc 6.

[0044] During the installation, adjustment and test process, the force sensor 9 is installed on the primary mirror cell 1, the flange end of the actuator 8 is screwed with the force sensor 6, and the bearing rod is connected with the locking support disc bearing.

[0045] During the movement of the actuator 8, the back of the primary mirror will be subjected to a force along the movement direction of the actuator.

[0046] The force sensor 9 displays the force on the back of the primary mirror, and the displacement of the actuator is adjusted so that the display values of the 24 force sensors are consistent with the required values; the primary mirror surface shape RMS is less than or equal to 31.64 nm in the unloaded state.

[0047] After the test is completed, the force sensor 9 and the actuator 8 are removed.

[0048] The flange end of the memory alloy unlocking device 7 is fixed to the primary mirror cell, the bearing rod end is connected with the locking support disc 6 bearing. The memory alloy unlocking device 7 is composed of high-strength memory alloy, which provides auxiliary support in the tensile and shearing directions of the primary mirror assembly. The number of the unlocking device is 24, which is consistent with the number of the locking support disc.

[0049] The unlocking device 7 emits the active segment locking, and provides auxiliary support for the primary mirror 2.

[0050] The unlocking device 7 is unlocked after entering the orbit, and is separated from the primary mirror, only the statically determinate support assembly is connected with the primary mirror and the primary mirror cell. The high stability of the primary mirror surface is realized after entering the orbit.

[0051] The space large-aperture mirror support and inspection integrated support system of the application realizes the integrated design of the primary mirror ground gravity unloading support, active segment auxiliary locking support and orbit static support under the vertical installation and adjustment technical route of the large-aperture space mirror, avoids the complexity of the general multi-point support technical scheme, ensures the effectiveness of the simulation of the on-orbit efficiency of the large-aperture space load in the ground test stage, and reduces the technical risk.

[0052] The application is described in detail in combination with the specific embodiments and exemplary examples, but these descriptions cannot be understood as limitations of the application. Those skilled in the art understand that the technical solutions and embodiments of the application can be variously replaced, modified or improved without departing from the spirit and scope of the application, and these all fall within the scope of the application. The protection scope of the application is subject to the appended claims.

[0053] The contents not described in detail in the specification of the application are the known technology of those skilled in the art.

Claims

1. An integrated system for vertical mounting, adjustment, support, and testing of a large-aperture space mirror, characterized in that: include: The primary mirror chamber (1), the primary mirror (2), the statically fixed support assembly (10), the locking support assembly (11), and the test assembly; One end of the statically fixed support assembly (10) is fixedly connected to the main mirror chamber (1), and the other end is bonded to the back of the main mirror (2); the statically fixed support of the main mirror (2) is achieved through several sets of statically fixed support assemblies (10); During the system integration testing phase, one end of the locking support component (11) is bonded to the back of the main mirror (2), and the other end is connected to the main mirror chamber (1) through the test component. The test component performs gravity unloading on the main mirror (2) and tests the surface shape of the main mirror under gravity unloading. After the test is completed, the test component is removed. During the launch phase, one end of the locking support component (11) is bonded to the back of the main mirror (2), and the other end is fixedly connected to the main mirror chamber (1). During the active phase launch, the locking support component (11) is locked to provide auxiliary support for the main mirror (2). After entering orbit, the locking support component (11) is unlocked and the locking support component (11) is separated from the main mirror chamber (1).

2. The integrated system for vertical mounting, adjustment, support, and testing of a large-aperture space mirror according to claim 1, characterized in that, The statically determinate support assembly (10) includes a statically determinate support plate (3), a statically determinate support BIPOD rod (4), and a statically determinate support BIPOD base (5). The statically determinate BIPOD rod (4) is connected to the statically determinate support plate (3) and the statically determinate BIPOD base (5) at both ends respectively. The statically fixed support plate (3) is bonded to the back of the primary mirror (2), and the statically fixed support BIPOD seat (5) is fixedly connected to the primary mirror chamber (1).

3. The integrated system for vertical mounting, adjustment, support, and testing of a large-aperture space mirror according to claim 1, characterized in that, The locking support assembly (11) includes a locking support disc (6) and a shape memory alloy unlocker (7). The locking support plate (6) is bonded to the back of the main mirror (2); A radial ball bearing is installed at the center of the locking support plate (6); One end of the memory alloy unlocker (7) is a bearing rod, and the other end is a mounting flange; the mounting flange is fixedly installed on the main mirror chamber (1) by means of a shim sleeve, and the bearing rod is connected to the locking support plate (6) by means of a radial ball bearing; the shim sleeve is used to simulate the height of the test component; The bearing rod is designed with a tapered groove. After it is inserted into the rail, the tapered groove is heated instantly to thermally break it, thus unlocking the bearing.

4. The integrated system for vertical mounting, adjustment, support, and testing of a large-aperture space mirror according to claim 1, characterized in that, The statically determinate support plate (3), statically determinate support BIPOD rod (4) and statically determinate support BIPOD seat (5) are made of Invar steel with a linear expansion coefficient of less than or equal to 0.03ppm.

5. The integrated system for vertical mounting, adjustment, support, and testing of a large-aperture space mirror according to claim 1, characterized in that, The locking support plate (6) is made of Invar steel with a linear expansion coefficient of less than or equal to 0.03ppm.

6. The integrated system for vertical mounting, adjustment, support, and testing of a large-aperture space mirror according to claim 1, characterized in that, The test components include an actuator (8) and a force sensor (9); During the assembly and testing process, the force sensor (9) is installed on the main mirror chamber (1); One end of the actuator (8) is a ball head and the other end is a mounting flange; the mounting flange of the actuator (8) is screwed to the force sensor (9), the ball head of the actuator (8) contacts the mounting flange of the memory alloy unlocker (7), and the bearing rod of the memory alloy unlocker (7) cooperates with the radial ball bearing to realize the connection between the memory alloy unlocker (7) and the locking support plate (6). The actuator (8) applies a force along the direction of the actuator's movement to the back of the main mirror (2). The force sensor (9) is used to display the magnitude of the force on the back of the main mirror (2). The actuator (8) and the force sensor (9) simulate the unloading state, and the surface shape of the main mirror is tested in the unloading state.

7. The integrated system for vertical mounting, adjustment, support, and testing of a large-aperture space mirror according to claim 6, characterized in that, During testing, the position of the actuator (8) is adjusted so that the value displayed by the force sensor (9) is consistent with the design value.

8. The integrated system for vertical mounting, adjustment, support, and testing of a large-aperture space mirror according to claim 1, characterized in that, The statically determinate support assembly (10) and the locking support assembly (11) are evenly distributed along the circumference.

9. The integrated system for vertical mounting, adjustment, support, and testing of a large-aperture space mirror according to claim 1, characterized in that, The statically determinate support assembly (10) consists of 3 to 6 groups; The number of locking support components (11) is 20 to 30.

10. A method for integrating vertical mounting, adjustment, support, and testing of a large-aperture space mirror, implemented using the integrated system for vertical mounting, adjustment, support, and testing of a large-aperture space mirror as described in any one of claims 1-9, comprising: One end of the statically fixed support assembly (10) is fixedly connected to the main mirror chamber (1), and the other end is bonded to the back of the main mirror (2); The primary mirror (2) is statically supported by a number of statically determinate support components (10); In reality, one end of the locking support component (11) is bonded to the back of the main mirror (2), and the other end is fixedly connected to the main mirror chamber (1); during the active phase of the launch, the locking support component (11) is locked to provide auxiliary support for the main mirror (2); after entering orbit, the locking support component (11) is unlocked and the locking support component (11) is separated from the main mirror chamber (1); During testing, one end of the locking support component (11) is bonded to the back of the main mirror (2), and the other end is connected to the main mirror chamber (1) through the test component. The test component is used to simulate the unloading state and test the surface shape of the main mirror in the unloading state. After the test is completed, the test component is removed.

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