CN115575098A - On-orbit testing method and system for structural stability of space telescope - Google Patents

On-orbit testing method and system for structural stability of space telescope Download PDF

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Publication number
CN115575098A
CN115575098A CN202211195434.2A CN202211195434A CN115575098A CN 115575098 A CN115575098 A CN 115575098A CN 202211195434 A CN202211195434 A CN 202211195434A CN 115575098 A CN115575098 A CN 115575098A
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beam splitter
light
structural stability
detector
space telescope
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林栩凌
吴金贵
吴铠岚
王小勇
郑永超
白绍竣
郭忠凯
王芸
谈宜东
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Beijing Institute of Space Research Mechanical and Electricity
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Beijing Institute of Space Research Mechanical and Electricity
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M11/00—Testing of optical apparatus; Testing structures by optical methods not otherwise provided for
    • G01M11/02—Testing optical properties
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
    • G01J9/00—Measuring optical phase difference; Determining degree of coherence; Measuring optical wavelength
    • G01J9/02—Measuring optical phase difference; Determining degree of coherence; Measuring optical wavelength by interferometric methods
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M11/00—Testing of optical apparatus; Testing structures by optical methods not otherwise provided for
    • G01M11/02—Testing optical properties
    • G01M11/0207—Details of measuring devices

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  • Length Measuring Devices By Optical Means (AREA)
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Abstract

The invention provides an on-orbit testing method and system for structural stability of a space telescope, and provides an on-orbit testing method for structural stability of a high-precision space telescope by combining heterodyne interferometry and differential wavefront phase Detection (DWS) according to the measurement precision requirement of a space task and the stability requirement of the telescope. By intercepting part of emergent light for interference, the structural stability change of the space telescope is obtained while the measurement task is not influenced. The interferometer adopted by the method and the system has the characteristics of stable and compact structure, small volume, light weight and high precision, and meets the test requirement of the structural stability of the satellite-borne telescope.

Description

On-orbit testing method and system for structural stability of space telescope
Technical Field
The invention relates to a system and a method applied to the on-orbit test of the structural stability of a space telescope, belonging to the field of space test.
Background
To meet the space task requirement, the satellite-borne optical component needs to have excellent structural stability to cope with the change of the ambient environment during the orbit period, so as to meet the expected measurement requirement. In order to ensure the smooth operation of the measurement task, it is important to pre-test the structural stability of the key element. In addition, in order to monitor the on-orbit actual performance of the satellite-borne optical device, an auxiliary measuring device which is small in size, light in weight and high in measuring accuracy on the premise of not influencing the normal work of a satellite needs to be considered so as to measure the interference brought by the structural change of a key component and make corresponding compensation in the result. The current testing method has the defects of low precision, complex structure and the like, so that an on-orbit structural stability testing scheme with compact structure and high precision is required.
Disclosure of Invention
The technical problem solved by the invention is as follows: aiming at the problems of insufficient precision, complex structure and the like in a common structural stability testing method in the prior art, the existing scheme is optimized, and a high-precision, simple and efficient on-orbit telescope testing system and method are provided.
The technical problem to be solved by the invention is realized by the following technical scheme: an on-orbit testing method for structural stability of a space telescope comprises the following steps:
after being split by a beam splitter BS3, the emergent light beam of the satellite-borne optical platform is reflected to enter a space telescope, the transmission component of the emergent light beam enters a beam splitter BS4, and the reflected and transmitted components of the light passing through the beam splitter BS4 are respectively received by a photoelectric detector PD1 and a photoelectric detector PD2;
the local light is taken as reference light, the reference light enters a beam splitter BS2, the reflection component of the reference light enters a beam splitter BS4 after passing through the beam splitter BS2, and the transmission and reflection components of the light passing through the beam splitter BS4 are respectively received by a photoelectric detector PD1 and a photoelectric detector PD2; the reference light is reflected to the structural stability measuring device by the plane mirror M1 through the component transmitted by the beam splitter BS 2;
two light beams incident to the photoelectric detector PD1 interfere to form a reference light beat which is received by the detector PD 1; two light beams incident to the photoelectric detector PD2 interfere to form a reference light beat which is received by the detector PD2;
emergent light passing through the space telescope is partially intercepted by the structural stability measuring device, and the intercepted light beam and the light beam reflected by the plane reflector M1 interfere in the structural stability measuring device to form a measuring beat which is received by a four-quadrant detector in the structural stability measuring device;
signals output by the photoelectric detectors PD1 and PD2 and the four-quadrant detector QPD are filtered by a filter, subjected to analog-to-digital conversion and input into a digital phase meter, and processed to obtain axial signals and differential wave-front phase detection DWS signals;
carrying out data processing on the obtained axial signal LPS and the differential wavefront phase detection DWS signal to obtain the variation delta z of the space telescope structure along the axial direction and the variation theta in the azimuth and the pitch direction y 、θ x 。
Further, the structural stability measuring device comprises a plane mirror M2, a lens L, a beam splitter BS5 and a four-quadrant detector;
the intercepted light beam is reflected to a lens L through a plane mirror M2, the light beam focused by the lens L enters a beam splitter BS5, and the transmission component of the light beam is received by a four-quadrant detector QPD; the light beam reflected by the plane mirror M1 enters the beam splitter BS5, is reflected by the beam splitter BS5 and then is received by the four-quadrant detector QPD; two light beams incident on the four-quadrant detector QPD interfere to form a measurement beat, which is received by the four-quadrant detector.
Furthermore, the structural stability measuring devices are respectively arranged at multiple points to measure the structural stability change of each part of the space telescope; or intercepting different parts of the emergent light passing through the space telescope, thereby obtaining the influence of the space telescope on the emergent light wave front of the space telescope.
Further, the beam splitter BS2, the beam splitter BS3, the beam splitter BS4, and the beam splitter BS5 are all non-polarizing beam splitters, and the transmission inverse ratio is 50.
Further, the axial signal LPS is:
Figure BDA0003868487150000031
wherein, each quadrant of the four-quadrant detector respectively obtains a phase result of phi A 、Φ B 、Φ C And phi D 。
Furthermore, the differential wave-front phase detection DWS signal is used for measuring the wave-front deflection angle of the two light beams and is divided into a horizontal DWS signal DWS h And vertical DWS signal DWS v Respectively is as follows:
Figure BDA0003868487150000032
Figure BDA0003868487150000033
wherein the content of the first and second substances,
Figure BDA0003868487150000034
the average phase of the left two quadrants of the four-quadrant detector is obtained;
Figure BDA0003868487150000035
the average phase of the two quadrants on the right side of the four-quadrant detector is obtained;
Figure BDA0003868487150000036
the average phase of the upper two quadrants of the four-quadrant detector is obtained;
Figure BDA0003868487150000037
the average phase of the lower two quadrants of the four quadrant detector is shown.
In a further aspect of the present invention,the variation delta z of the space telescope structure along the axial direction is a reference signal output by a detector PD
Figure BDA0003868487150000038
And measuring signal output by four-quadrant detector QPD
Figure BDA0003868487150000039
The calculation formula is obtained as follows:
Figure BDA00038684871500000310
further, the variation theta of the space telescope structure in the azimuth direction and the pitch direction y 、θ x The DWS signal is detected by the differential wave front phase output by the four-quadrant detector to obtain:
DWS h ＝C h θ y ，
DWS v ＝C v θ x ，
calibrating the four-quadrant detector in advance to obtain a proportionality coefficient C h Coefficient of proportionality C v Calculating the variation theta of the space telescope structure in the azimuth direction and the pitching direction through the obtained differential wavefront phase detection signal y ，θ x 。
An in-orbit testing system for structural stability of a space telescope, comprising: the device comprises a structural stability measuring device, a beam splitter BS2, a beam splitter BS3, a beam splitter BS4, a reflector M1, a photoelectric detector PD1 and a photoelectric detector PD2;
after an emergent light beam of the satellite-borne optical platform is split by the beam splitter BS3, a reflection component of the emergent light beam enters the space telescope, a transmission component of the emergent light beam enters the beam splitter BS4, and reflection and transmission components of light passing through the beam splitter BS4 are respectively received by the photoelectric detector PD1 and the photoelectric detector PD2;
the local light is taken as reference light, the reference light enters a beam splitter BS2, the reflected component of the reference light enters a beam splitter BS4 after passing through the beam splitter BS2, and the transmitted and reflected components of the light passing through the beam splitter BS4 are respectively received by a photoelectric detector PD1 and a photoelectric detector PD2; the reference light is reflected to the structural stability measuring device by the plane mirror M1 through the component transmitted by the beam splitter BS 2;
two light beams incident to the photoelectric detector PD1 interfere to form a reference light beat which is received by the detector PD 1; two light beams incident to the photoelectric detector PD2 interfere to form a reference light beat which is received by the detector PD2;
the emergent light passing through the space telescope is partially intercepted by the structural stability measuring device, and the intercepted light beam and the light beam reflected by the plane reflector M1 interfere in the structural stability measuring device to form a measuring beat which is received by a four-quadrant detector in the structural stability measuring device.
Further, the structural stability measuring device comprises a plane mirror M2, a lens L, a beam splitter BS5 and a four-quadrant detector;
the intercepted light beam is reflected to a lens L through a plane mirror M2, the light beam focused by the lens L enters a beam splitter BS5, and the transmission component of the light beam is received by a four-quadrant detector QPD; the light beam reflected by the plane mirror M1 enters a beam splitter BS5, and is reflected by the beam splitter BS5 and then received by a four-quadrant detector QPD; two light beams incident on the four-quadrant detector QPD interfere to form a measurement beat, which is received by the four-quadrant detector.
Compared with the prior art, the invention has the advantages that:
(1) The invention provides a high-precision on-orbit structure stability testing method, which adopts a set of a reflector, a lens, a beam splitter and a four-quadrant detector to intercept partial light beams at each part of a sample to be tested for measurement, thereby obtaining the influence of each part of the sample on the optical path. Compared with the existing scheme, the method has the advantages of fewer adopted elements, smaller volume and more flexible measurement mode, and cannot influence the satellite measurement task.
(2) The structural stability testing method provided by the invention is different from the prior method that the sample to be tested is regarded as a rigid body, and the light beam can be emitted after passing through the whole system to be tested; therefore, the emergent light is intercepted at multiple points for measurement, and the influence of the sample on the beam wavefront can be measured.
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FIG. 1 is a block flow diagram of the method of the present invention;
FIG. 2 is a schematic diagram of a ground test light path;
FIG. 3 is a schematic diagram of an on-track test optical path according to the present invention.
Detailed description of the invention
The invention provides an on-orbit stability testing method based on heterodyne interferometry. Because the reference light for interference is output by the local light source and is interfered with the measuring light after being transmitted by the free space, the obtained measuring result can better reflect the influence of the sample to be measured on the optical path; by combining the differential wavefront phase detection signal and the axial signal, the structural change of the sample to be detected in respective degree of freedom can be accurately measured; in addition, through the collection of the reflecting mirror, the lens, the beam splitter and the four-quadrant detector, a sample to be measured can be measured at multiple positions, or multiple collections are adopted for measurement simultaneously, and the wave front change of a light beam after passing through the sample can be measured. The interferometer adopted by the testing method is compact in structure, small in size and light in weight, can effectively reduce the load of a satellite, can well meet the requirement of testing the structural stability of a device, and ensures that the measurement is effectively carried out.
As shown in fig. 3, an in-orbit testing system for structural stability of a space telescope comprises: the device comprises a structural stability measuring device, a beam splitter BS2, a beam splitter BS3, a beam splitter BS4, a reflector M1, a photoelectric detector PD1 and a photoelectric detector PD2;
after being split by a beam splitter BS3, the emergent light beam of the satellite-borne optical platform is reflected to enter a space telescope, the transmission component of the emergent light beam enters a beam splitter BS4, and the reflected and transmitted components of the light passing through the beam splitter BS4 are respectively received by a photoelectric detector PD1 and a photoelectric detector PD2;
the local light is taken as reference light, the reference light enters a beam splitter BS2, the reflection component of the reference light enters a beam splitter BS4 after passing through the beam splitter BS2, and the transmission and reflection components of the light passing through the beam splitter BS4 are respectively received by a photoelectric detector PD1 and a photoelectric detector PD2; the reference light is reflected to the structural stability measuring device by the plane mirror M1 through the component transmitted by the beam splitter BS 2;
two light beams incident to the photoelectric detector PD1 interfere to form a reference light beat which is received by the detector PD 1; two light beams incident to the photoelectric detector PD2 interfere to form a reference light beat which is received by the detector PD2;
the emergent light passing through the space telescope is partially intercepted by the structural stability measuring device, and the intercepted light beam and the light beam reflected by the plane reflector M1 interfere in the structural stability measuring device to form a measuring beat which is received by a four-quadrant detector in the structural stability measuring device.
The structural stability measuring device comprises a plane reflector M2, a lens L, a beam splitter BS5 and a four-quadrant detector;
the intercepted light beam is reflected to a lens L through a plane mirror M2, the light beam focused by the lens L enters a beam splitter BS5, and the transmission component of the light beam is received by a four-quadrant detector QPD; the light beam reflected by the plane mirror M1 enters a beam splitter BS5, and is reflected by the beam splitter BS5 and then received by a four-quadrant detector QPD; two light beams incident on the four-quadrant detector QPD interfere to form a measurement beat, which is received by the four-quadrant detector.
As shown in fig. 1, the method of the present invention comprises the following steps:
(1) As shown in FIG. 2, for the ground test, laser with a wavelength of 1064nm is first output by the laser, and then the beam is split by the beam splitter 1 (BS 1), and the two beams pass through the acousto-optic modulators (AOM) 1 and 2, respectively, thereby obtaining the frequency f 1 Measured light and frequency of f 2 Δ f = f, reference light of (a) 1 -f 2 =1MHz, resulting beat frequency signal frequency f het Is f het ＝Δf。
(2) In the step (1), the measuring light is modulated by the acousto-optic modulator 1 and then enters the beam splitter 3 (BS 3). After passing through the beam splitter 3, the reflected component enters the beam splitter 4 (BS 4), and then the reflected and transmitted components are received by the photodetector 1 (PD 1) and the photodetector 2 (PD 2), respectively; then the sample to be measured is placed in the sample placing area, the transmission component of the measuring light passing through the beam splitter 3 passes through the sample to be measured, and the emergent light is partially intercepted. The intercepted light beam is reflected to the lens L via the plane mirror 2 (M2), and then the light beam focused by the lens L is incident on the beam splitter 5 (BS 5), and the transmission component thereof is received by the four-quadrant detector (QPD).
In the step (1), the reference light is modulated by the acousto-optic modulator 2 and then enters the beam splitter 2 (BS 2), after passing through the beam splitter 2, the reflection component of the reference light enters the beam splitter 4, and then the transmission component and the reflection component are respectively received by the photoelectric detectors 1 and 2; the component of the reference light transmitted through the beam splitter 2 will be reflected by the plane mirror 1 (M1) to the beam splitter 5, and thereafter reflected by the beam splitter 5 to be received by the four-quadrant detector.
As shown in fig. 3, for the in-orbit telescope structural stability test, the beam splitter 1 and the acousto-optic modulators 1 and 2 were removed. The measuring light is emergent light of the satellite-borne optical platform, the sample to be measured is an in-orbit telescope, then the sample is split by the beam splitter 3, the reflected component of the sample is partially intercepted for stability test after passing through the telescope, and the transmitted component of the sample enters the beam splitter BS4. In addition, a beam of local light is used as reference light, and the beam is split by the beam splitter 2, then enters the plane mirror M1 and the beam splitter BS4 respectively, and is used for structural stability test.
(3) The light beams incident on the photoelectric detector 1 will interfere to form a reference light beat, which is received by the detector 1; the two light beams incident on the photodetector 2 will also interfere to form a reference photo, which is received by the detector 2. Comparing the signals obtained by the photoelectric detectors 1 and 2 can reduce the system error;
(4) Emergent light passing through a sample is intercepted by a structural stability measuring device, the intercepted light beam is reflected to a lens L through a plane reflecting mirror 2 (M2), the light beam focused by the lens L enters a beam splitter 5 (BS 5), and the transmission component of the light beam is received by a four-quadrant detector (QPD); the light beam reflected by the plane mirror 1 will be incident on the beam splitter 5 and thereafter reflected by the beam splitter 5 to be received by the four-quadrant detector. Two light beams incident to the four-quadrant detector interfere to form a measuring beat, and then the measuring beat is received by the four-quadrant detector;
the adopted structural stability measuring device comprises a plane reflector, a lens, a beam splitter and a four-quadrant detector, and corresponds to the plane reflector 2, the lens L, the beam splitter 5 and the four-quadrant detector in an actual light path. The light beam emitted after passing through the sample is intercepted by a small hole below the plane reflector 2 and then enters the reflector, and the light beam is measuring light; the reference light is reflected by the plane mirror 1, then propagates through free space, enters the beam splitter 5 through a light-passing hole below the beam splitter 5, and then interferes with the measuring light to obtain a beat frequency signal.
Since the intercepted part of the outgoing light interferes with the reference light, the intercepted part may be the edge part of the outgoing laser beam, and the light intensity of the obtained light beam is weak. For heterodyne interference efficiency η, there are:
Figure BDA0003868487150000091
wherein, a i (r, t) is the amplitude of the electric field component of the interfering beam, r is the spatial position, t is time,
Figure BDA0003868487150000092
for the phase, S is the photosensitive area of the detector surface, and the visible interference efficiency is related to factors such as beat intensity and wavefront error, i =1,2. Therefore, the light beam is converged by the lens L, so that the light power received by the surface of the detector is higher, and the interference efficiency is improved.
The adopted structural stability measuring devices can be respectively arranged at multiple points to measure the structural stability change of each part of the sample; or intercepting different parts of emergent light after passing through the telescope, thereby obtaining the influence of the sample to be measured on the emergent light wave front.
The beam splitter BS2, the beam splitter BS3, the beam splitter BS4 and the beam splitter BS5 are all non-polarizing beam splitters, and the inverse transmission ratio is 50. (5) Signals output by the photoelectric detector and the four-quadrant detector are filtered by a filter, subjected to analog-to-digital conversion and input into a digital phase meter, and processed to obtain an axial signal and a differential wave front phase Detection (DWS) signal; the axial signal (LPS) is defined as:
Figure BDA0003868487150000093
four-quadrant detectorEach quadrant respectively obtains a phase result of phi A 、Φ B 、Φ C And phi D ；
The differential wave front phase detection signal is used for measuring the wave front deflection angle of two light beams and is divided into horizontal DWS signals DWS h And vertical DWS signal DWS v Respectively defined as:
Figure BDA0003868487150000094
Figure BDA0003868487150000095
wherein
Figure BDA0003868487150000101
The average phase of the left two quadrants of the four-quadrant detector is obtained;
Figure BDA0003868487150000102
the average phase of two quadrants on the right side of the four-quadrant detector is obtained;
Figure BDA0003868487150000103
the average phase of the upper two quadrants of the four-quadrant detector is obtained;
Figure BDA0003868487150000104
the average phase of two quadrants at the lower side of the four-quadrant detector is obtained;
(6) Processing the axial signal and the differential wavefront phase Detection (DWS) signal obtained in the step (5) to obtain the change deltaz of the sample structure along the axial direction and the change theta in the azimuth pitch direction y ，θ x Therefore, the multi-degree-of-freedom and high-precision structural stability measurement is carried out on the sample to be measured:
the axial variation Δ z may be a reference signal output by the detector PD
Figure BDA0003868487150000105
And the measurement signal output by the QPD
Figure BDA0003868487150000106
The calculation method comprises the following steps:
Figure BDA0003868487150000107
λ is wavelength, λ =1064nm;
variation theta of sample structure to be tested in azimuth and pitch directions y ，θ x Can be derived from the differential wavefront phase Detection (DWS) signal output by the four-quadrant detector, which is proportional to the resulting differential wavefront phase detection signal for small shifts between the interfering beams:
DWS h ＝C h θ y ，
DWS v ＝C v θ x ，
the proportional relation of the two is related to the adopted device and light beam, and the four-quadrant detector can be calibrated in advance, so that the proportionality coefficient C is obtained h 、C v Then, the change theta of the sample structure to be detected in the azimuth direction and the pitching direction can be calculated through the obtained differential wavefront phase detection signal y ，θ x 。
Parts of the invention not described in detail are well known to the person skilled in the art.

Claims (10)

1. An on-orbit testing method for structural stability of a space telescope is characterized by comprising the following steps:
after being split by a beam splitter BS3, the emergent light beam of the satellite-borne optical platform is reflected to enter a space telescope, the transmission component of the emergent light beam enters a beam splitter BS4, and the reflected and transmitted components of the light passing through the beam splitter BS4 are respectively received by a photoelectric detector PD1 and a photoelectric detector PD2;
the local light is taken as reference light, the reference light enters a beam splitter BS2, the reflection component of the reference light enters a beam splitter BS4 after passing through the beam splitter BS2, and the transmission and reflection components of the light passing through the beam splitter BS4 are respectively received by a photoelectric detector PD1 and a photoelectric detector PD2; the reference light is reflected to the structural stability measuring device through a plane mirror M1 through the component transmitted by the beam splitter BS 2;
two light beams incident to the photoelectric detector PD1 interfere to form a reference light beat which is received by the detector PD 1; two light beams incident to the photoelectric detector PD2 interfere to form a reference light beat which is received by the detector PD2;
emergent light passing through the space telescope is partially intercepted by the structural stability measuring device, and the intercepted light beam and the light beam reflected by the plane mirror M1 interfere in the structural stability measuring device to form a measuring beat which is received by a four-quadrant detector in the structural stability measuring device;
signals output by the photoelectric detectors PD1 and PD2 and the four-quadrant detector QPD are filtered by a filter, subjected to analog-to-digital conversion and input into a digital phase meter, and processed to obtain axial signals and differential wave-front phase detection DWS signals;
the obtained axial signal LPS and the differential wavefront phase detection DWS signal are subjected to data processing to obtain the variation delta z of the space telescope structure along the axial direction and the variation theta in the azimuth and pitch directions y 、θ x 。
2. The on-orbit testing method for the structural stability of the space telescope according to claim 1, characterized in that: the structural stability measuring device comprises a plane reflector M2, a lens L, a beam splitter BS5 and a four-quadrant detector;
the intercepted light beam is reflected to a lens L through a plane mirror M2, the light beam focused by the lens L enters a beam splitter BS5, and the transmission component of the light beam is received by a four-quadrant detector QPD; the light beam reflected by the plane mirror M1 enters a beam splitter BS5, and is reflected by the beam splitter BS5 and then received by a four-quadrant detector QPD; two light beams incident on the four-quadrant detector QPD interfere to form a measurement beat, which is received by the four-quadrant detector.
3. The on-orbit testing method for the structural stability of the space telescope according to claim 2, characterized in that: the structural stability measuring devices are respectively arranged at multiple points and used for measuring structural stability changes of all parts of the space telescope; or intercepting different parts of emergent light passing through the space telescope, thereby obtaining the influence of the space telescope on the emergent light wavefront of the space telescope.
4. The on-orbit testing method for the structural stability of the space telescope according to claim 3, characterized in that: the beam splitter BS2, the beam splitter BS3, the beam splitter BS4 and the beam splitter BS5 are all non-polarizing beam splitters, and the inverse transmission ratio is 50.
5. The on-orbit testing method for the structural stability of the space telescope according to claim 1, characterized in that: the axial signal LPS is:
Figure FDA0003868487140000021
wherein, each quadrant of the four-quadrant detector respectively obtains a phase result of phi A 、Φ B 、Φ C And phi D 。
6. The on-orbit testing method for the structural stability of the space telescope according to claim 5, characterized in that: the differential wave-front phase detection DWS signal is used for measuring the wave-front deflection angle of two light beams and is divided into a horizontal DWS signal DWS h And vertical DWS signal DWS v Respectively is as follows:
Figure FDA0003868487140000022
Figure FDA0003868487140000031
wherein the content of the first and second substances,
Figure FDA0003868487140000032
the average phase of the left two quadrants of the four-quadrant detector is obtained;
Figure FDA0003868487140000033
the average phase of two quadrants on the right side of the four-quadrant detector is obtained;
Figure FDA0003868487140000034
the average phase of the upper two quadrants of the four-quadrant detector is obtained;
Figure FDA0003868487140000035
the average phase of the lower two quadrants of the four quadrant detector is shown.
7. The on-orbit testing method for the structural stability of the space telescope according to claim 1, characterized in that: the variation delta z of the space telescope structure along the axial direction is a reference signal output by a detector PD
Figure FDA0003868487140000036
And the measurement signal output by the QPD
Figure FDA0003868487140000037
The calculation formula is obtained as follows:
Figure FDA0003868487140000038
8. the on-orbit testing method for the structural stability of the space telescope according to claim 1, characterized in that: the variation theta of the space telescope structure in the azimuth direction and the pitch direction y 、θ x The DWS signal is detected by the differential wave front phase output by the four-quadrant detector to obtain:
DWS h ＝C h θ y ，
DWS v ＝C v θ x ，
calibrating the four-quadrant detector in advance to obtain a proportionality coefficient C h Coefficient of proportionality C v Calculating the variation theta of the space telescope structure in the azimuth direction and the pitching direction through the obtained differential wavefront phase detection signal y ，θ x 。
9. An in-orbit testing system for structural stability of a space telescope, which is characterized by comprising: the device comprises a structural stability measuring device, a beam splitter BS2, a beam splitter BS3, a beam splitter BS4, a reflector M1, a photoelectric detector PD1 and a photoelectric detector PD2;
after being split by a beam splitter BS3, the emergent light beam of the satellite-borne optical platform is reflected to enter a space telescope, the transmission component of the emergent light beam enters a beam splitter BS4, and the reflected and transmitted components of the light passing through the beam splitter BS4 are respectively received by a photoelectric detector PD1 and a photoelectric detector PD2;
the local light is taken as reference light, the reference light enters a beam splitter BS2, the reflected component of the reference light enters a beam splitter BS4 after passing through the beam splitter BS2, and the transmitted and reflected components of the light passing through the beam splitter BS4 are respectively received by a photoelectric detector PD1 and a photoelectric detector PD2; the reference light is reflected to the structural stability measuring device by the plane mirror M1 through the component transmitted by the beam splitter BS 2;
two light beams incident to the photoelectric detector PD1 interfere to form a reference light beat which is received by the detector PD 1; two light beams incident to the photoelectric detector PD2 interfere to form a reference light beat which is received by the detector PD2;
the emergent light passing through the space telescope is partially intercepted by the structural stability measuring device, and the intercepted light beam and the light beam reflected by the plane reflector M1 interfere in the structural stability measuring device to form a measuring beat which is received by a four-quadrant detector in the structural stability measuring device.
10. The in-orbit testing system for the structural stability of the space telescope according to claim 9, wherein: the structural stability measuring device comprises a plane reflector M2, a lens L, a beam splitter BS5 and a four-quadrant detector;
the intercepted light beam is reflected to a lens L through a plane mirror M2, the light beam focused by the lens L enters a beam splitter BS5, and the transmission component of the light beam is received by a four-quadrant detector QPD; the light beam reflected by the plane mirror M1 enters the beam splitter BS5, is reflected by the beam splitter BS5 and then is received by the four-quadrant detector QPD; two light beams incident on the four-quadrant detector QPD interfere to form a measurement beat, which is received by the four-quadrant detector.
CN202211195434.2A 2022-09-28 2022-09-28 On-orbit testing method and system for structural stability of space telescope Pending CN115575098A (en)

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