A space-based gravitational wave detection signal simulation system including fault simulation

Abstract

The present invention belongs to the technical field of gravitational wave detection simulation, and relates to a space-based gravitational wave detection signal simulation system including fault simulation, including: a full-link signal output module, used to simulate and output multi-channel interferometric measurement signals of space-based gravitational wave detection formations; a burr fault simulation module, used to construct different types of numerical burr models, and generate simulation timing detection signals with burr data according to provided burr parameters, so as to realize burr fault simulation; an interrupt fault simulation module, used to construct different types of interrupt models, and add interrupt models by adding interrupt functions, so as to realize interrupt fault simulation; a phase-locking strategy change module, used to switch to a specific phase-locking strategy when a system fault occurs. The present invention constructs a more comprehensive gravitational wave detection signal simulation method, takes into account data interruption and data glitch operation fault simulation models, and can realize gravitational wave detection data simulation under normal conditions and gravitational wave detection data simulation containing faults.

Description

Technical Field

[0001] The present invention belongs to the technical field of gravitational wave detection simulation, and in particular relates to a space-based gravitational wave detection signal simulation system including fault simulation. Background Art

[0002] The space gravitational wave laser interferometry system converts the tiny distance changes caused by gravitational waves into interference phase signals through interferometric ranging between satellites, and then inverts the gravitational wave source parameters. According to the detection data obtained by LISAPathfinder and Taiji-1, frequent data interruptions and anomalies are important factors affecting the continuity and quality of detection data during the detection process of space gravitational wave detectors. The situation where the detection data is interrupted due to component failure or routine maintenance. In addition, the short-term jitter of the test quality caused by electronic defects or other factors will appear as a short-term impulse response in the inertial sensor measurement data, which is called a glitch. In view of the urgent need for space gravitational wave detection in my country for data sets containing gravitational wave signals, noise signals, and operational fault simulation, it is necessary to develop a space-based gravitational wave detection signal simulation method and system that includes data interruption and glitch operational fault simulation. Summary of the invention

[0003] The purpose of the present invention is to overcome the defects of the prior art, establish a data interruption and glitch operation fault simulation model, improve the simulation process, and propose a space-based gravitational wave detection signal simulation system including fault simulation.

[0004] In order to achieve the above object, the present invention proposes a space-based gravitational wave detection signal simulation system including fault simulation, comprising:

[0005] Full-link signal output module, used to simulate and output multi-channel interferometric measurement signals of space-based gravitational wave detection formations;

[0006] A glitch fault simulation module is used to construct different types of numerical glitch models and to generate a simulation timing detection signal with glitch data according to the provided glitch parameters to realize glitch fault simulation;

[0007] An interrupt fault simulation module is used to construct different types of interrupt models and to add interrupt models by adding interrupt functions to implement interrupt fault simulation; and

[0008] The phase-locking strategy changing module is used to switch to a specific phase-locking strategy when a system failure occurs.

[0009] Preferably, the full-link signal output module includes three spacecraft simulation platforms with the same structure, namely, spacecraft simulation platform 1, spacecraft simulation platform 2 and spacecraft simulation platform 3. Two optical platforms are arranged on each spacecraft simulation platform, namely, optical platforms A and B on spacecraft simulation platform 1, optical platforms C and D on spacecraft simulation platform 2, and optical platforms E and F on spacecraft simulation platform 3. When one of the optical platforms is the main optical platform, three phase-locking sequences correspond to it; two measurement mass blocks, as well as one scientific interferometer, one test mass interferometer and one reference interferometer are arranged on each optical platform. Each optical platform transmits and receives lasers to and receives lasers from two adjacent optical platforms respectively. The full-link signal output module has 18 phase-locking sequences and outputs 18 interference measurement signals in total. There are two intersatellite interference links between every two spacecraft simulation platforms.

[0010] Preferably, the optical platform A is used as the main optical platform, and the corresponding three phase-locking sequences are as follows:

[0011] Phase locking sequence 1 is: the laser on optical platform B is phase locked to the laser on optical platform A, the laser on optical platform C is phase locked to the laser on optical platform B, the laser on optical platform D is phase locked to the laser on optical platform C, the laser on optical platform F is phase locked to the laser on optical platform A, and the laser on optical platform E is phase locked to the laser on optical platform F;

[0012] Phase locking sequence 2 is: the laser on optical platform B is phase locked to the laser on optical platform C, the laser on optical platform C is phase locked to the laser on optical platform D, the laser on optical platform D is phase locked to the laser on optical platform E, the laser on optical platform E is phase locked to the laser on optical platform F, and the laser on optical platform F is phase locked to the laser on optical platform A;

[0013] Phase locking sequence 3 is: the optical platform B laser is phase locked to the optical platform A laser, the optical platform C laser is phase locked to the optical platform D laser, the optical platform D laser is phase locked to the optical platform E laser, the optical platform E laser is phase locked to the optical platform F laser, and the optical platform F laser is phase locked to the optical platform A laser.

[0014] Preferably, the interferometric measurement signals output by the scientific interferometer, the test quality interferometer and the reference interferometer of each of the optical platforms satisfy the following formulas:

[0015]

[0016] Among them, φ SCI (t),φ TM (t) and φ REF (t) represent the output signals of the scientific interferometer, the test quality interferometer and the reference interferometer on the optical platform respectively; φ GW (t) represents the phase change caused by the gravitational wave signal; φ Noise1(t) represents the difference between the phase change caused by the laser frequency noise and optical platform noise contained in the laser emitted by the remote optical platform and the local laser frequency noise and optical platform noise received by the optical platform; φ Noise3 (t) represents the difference between the phase change caused by the laser frequency noise and optical platform noise of the adjacent optical platform received by the local optical platform and the laser frequency noise and optical platform noise of the local optical platform, φ Noise2 (t) represents various types of additive noise in scientific interferometers, φ Noise4 (t) represents the various types of additive noise existing in the test mass interferometer and the reference interferometer, φ ACC (t) represents the acceleration noise of the inertial sensor present in the test mass interferometer, and t represents time.

[0017] Preferably, the different types of numerical burr models include:

[0018] The first type of glitch model:

[0019]

[0020] Among them, acc noise (t) represents the spur added to the link, A is the amplitude, τ is the decay time, t start Indicates the time when the glitch occurs, T Length Indicates the burr length;

[0021] The second type of burr model:

[0022]

[0023] Among them, acc noise (t) represents the spur added to the link, A is the amplitude, τ is the decay time, t start Indicates the time when the glitch occurs, T Length represents the burr length; and

[0024] The third type of burr model:

[0025]

[0026] Among them, acc noise (t) represents the spur added to the link, A is the amplitude, τ is the decay time, t start Indicates the time when the glitch occurs, T Length Indicates the burr length, f0 is t start The frequency at time t, φ0 represents start The phase of the moment.

[0027] Preferably, the step of generating a simulation timing detection signal with glitch data according to the provided glitch parameters to realize glitch fault simulation includes:

[0028] Generate timing glitch data according to the provided glitch parameters and the selected glitch model type; the glitch parameters include: amplitude A, decay time τ, glitch start time t start , glitch duration T Length , and t start The frequency f0 and t at time start The phase at time φ0;

[0029] By inputting the acceleration noise data of the inertial sensor, the acceleration noise data of the inertial sensor including the burr data is obtained, and the burr fault simulation is realized.

[0030] Preferably, the different types of interruption models include:

[0031] The first type of interrupt model:

[0032]

[0033] Among them, WA(t) represents the first type of interrupt function, t smooth Indicates the smoothing time, T Length represents the length of the interruption, t represents the time; and

[0034] The second type of interrupt model:

[0035]

[0036] Among them, WB(t) represents the second type of interrupt function, t start Indicates the interruption start time, T Length Indicates the interruption length, t smooth Indicates the smoothing duration.

[0037] Preferably, the interrupt model is added by adding an interrupt function to realize interrupt fault simulation, including:

[0038] Determine the interrupt function according to the selected interrupt model type;

[0039] Determine the length of the window function w(t) according to the set interruption length;

[0040] Set the smoothing duration;

[0041] Set the start time to realize interruption fault simulation;

[0042] The interference signal after adding the interruption satisfies the following formula:

[0043]

[0044] Among them, φ SCI (t),φ TM (t) and φ REF (t) represent the output signals of the scientific interferometer, the test quality interferometer and the reference interferometer on the optical platform respectively; φ GW (t) represents the phase change caused by the gravitational wave signal; φ Noise1 (t) represents the difference between the phase change caused by the laser frequency noise and optical platform noise contained in the laser emitted by the remote optical platform and the local laser frequency noise and optical platform noise received by the optical platform; φ Noise3 (t) represents the difference between the phase change caused by the laser frequency noise and optical platform noise of the adjacent optical platform received by the local optical platform and the laser frequency noise and optical platform noise of the local optical platform, φ Noise2 (t) represents various types of additive noise in scientific interferometers, φ Noise4 (t) represents the various types of additive noise existing in the test mass interferometer and the reference interferometer, φ ACC (t) represents the acceleration noise of the inertial sensor present in the test mass interferometer, and t represents time.

[0045] Preferably, the failure of the system includes a single-arm interruption, which is a disconnection of the interference link between the two spacecraft simulation platforms, including:

[0046] The links α1, α2 and α between optical platform A and optical platform F are broken. 12 , where α1 indicates the laser link from optical platform A to optical platform F is broken, α2 indicates the laser link from optical platform F to optical platform A is broken, and α 12 Indicates that both links are broken;

[0047] The links β1, β2 and β3 between platform B and optical platform C are broken. 12 , where β1 represents the laser link break from optical platform B to optical platform C, β2 represents the laser link break from optical platform C to optical platform B, and β 12 Indicates that both links are broken; and

[0048] The links γ1, γ2 and γ between platform E and optical platform D are broken. 12 , where γ1 represents the laser link from optical platform E to optical platform D is broken, γ2 represents the laser link from optical platform D to optical platform F is broken, and γ 12 Indicates that both links are broken;

[0049] The phase-lock sequence strategy for single-arm interruption replacement with optical platform A as the main optical platform is as follows:

[0050] When the single arm is interrupted, the phase-locked sequence is 1. If the interruption condition is α1 or α2 or α 12 , the phase-locking sequence is adjusted to phase-locking sequence 2f; if the interruption condition is β1 or β2 or β 12 , the phase-locking sequence is adjusted to phase-locking sequence 3f; if the interruption condition is γ1 or γ2 or γ 12 , then the phase-locking sequence does not need to be adjusted;

[0051] When the single arm is interrupted before the phase lock sequence 2, if the interruption condition is α1 or α2 or α 12 , the phase-locking sequence is adjusted to phase-locking sequence 2f; if the interruption condition is β1 or β2 or β 12 , the phase-locking sequence is adjusted to phase-locking sequence 3f; if the interruption situation is γ1 / γ2 / γ 12 , then the phase-locking sequence is adjusted to phase-locking sequence 1f;

[0052] When the single arm is interrupted, the phase-locked sequence is 3, if the interruption condition is α1 or α2 or α 12 , the phase-locking sequence is adjusted to phase-locking sequence 2f; if the interruption condition is β1 or β2 or β 12 , then the phase-locking sequence does not need to be adjusted; if the interruption condition is γ1 or γ2 or γ 12 , the phase-locking sequence is adjusted to phase-locking sequence 1f.

[0053] Preferably, the phase-locking sequence 1f is: select optical platform A as the main optical platform, phase-lock the laser of optical platform B to the laser of optical platform A, phase-lock the laser of optical platform C to the laser of optical platform D, phase-lock the laser of optical platform D to the laser of optical platform E, phase-lock the laser of optical platform E to the laser of optical platform F, and phase-lock the laser of optical platform F to the laser of optical platform A;

[0054] The phase locking sequence 2f is: select optical platform D as the main optical platform, phase lock the laser of optical platform E to the laser of optical platform F, phase lock the laser of optical platform F to the laser of optical platform A, phase lock the laser of optical platform A to the laser of optical platform B, phase lock the laser of optical platform B to the laser of optical platform C, and phase lock the laser of optical platform C to the laser of optical platform D;

[0055] The phase-locking sequence 3f is: select optical platform C as the main optical platform, phase-lock the laser of optical platform E to the laser of optical platform F, phase-lock the laser of optical platform F to the laser of optical platform A, phase-lock the laser of optical platform A to the laser of optical platform B, phase-lock the laser of optical platform B to the laser of optical platform C, and phase-lock the laser of optical platform D to the laser of optical platform C.

[0056] Compared with the prior art, the advantages of the present invention are:

[0057] 1. A more comprehensive gravitational wave detection signal simulation method has been constructed, taking into account the data interruption and data glitch operation fault simulation model, which can realize the simulation of gravitational wave detection data under normal conditions and the simulation of gravitational wave detection data containing faults;

[0058] 2. A general gravitational wave detection signal simulation model was constructed, including a full-link signal output module, an interruption fault simulation module, a phase-locked strategy change module, and a glitch fault simulation module;

[0059] 3. Improved the propagation path of glitch operation failures, providing data support for the subsequent development of more general data processing algorithms. BRIEF DESCRIPTION OF THE DRAWINGS

[0060] Figure 1 It is a flow chart of the glitch fault adding method;

[0061] Figure 2 It is a simulation flow chart with data interruption added;

[0062] Figure 3 It is a simulation flow chart of a space-based gravitational wave detection signal simulation system including a phase-locking mechanism of the present invention;

[0063] Figure 4 It is a single-channel interferometry data timing signal display;

[0064] Figure 5 It is the periodic data interrupt function;

[0065] Figure 6 It is the random data interruption simulation data;

[0066] Figure 7 It is to detect data after adding interruption;

[0067] Figure 8 This is the first type of glitch simulation: the timing comparison of the acceleration noise of the inertial sensor before and after adding the glitch. DETAILED DESCRIPTION

[0068] A space-based gravitational wave detection signal simulation system including fault simulation, comprising:

[0069] Full-link signal output module, used to simulate and output multi-channel interferometric measurement signals of space-based gravitational wave detection formations;

[0070] A glitch fault simulation module is used to construct different types of numerical glitch models and to generate a simulation timing detection signal with glitch data according to the provided glitch parameters to realize glitch fault simulation;

[0071] An interrupt fault simulation module is used to construct different types of interrupt models and to add interrupt models by adding interrupt functions to realize interrupt fault simulation;

[0072] The phase-locking strategy changing module is used to switch to a specific phase-locking strategy when a system failure occurs.

[0073] The space-based gravitational wave detection formation consists of three spacecraft, with a distance of one million kilometers between each other. Each spacecraft contains two optical platforms, a total of 6 optical platforms, and each optical platform carries a laser and a test mass block. The laser is used to send lasers to two adjacent optical platforms, one is another optical platform of the same spacecraft, and the other is an optical platform of another spacecraft adjacent to it. Each optical platform contains three interferometers, namely scientific interferometer, test mass interferometer and reference interferometer, which output 18 interferometric measurement signals in total. Among them, the two laser beams involved in the interference in the scientific interferometer are the lasers emitted by the local laser and the laser emitted from the optical platform (remote optical platform) of an adjacent spacecraft. The two laser beams involved in the interference of the test mass interferometer are the lasers emitted by the local laser and the lasers emitted from the laser of another optical platform (adjacent optical platform) of the same spacecraft, among which the lasers emitted from the adjacent optical platform need to pass through the test mass block. The two laser beams involved in the interference of the reference interferometer are the lasers emitted by the local laser and the lasers emitted from the laser of the adjacent optical platform, among which the lasers emitted from the adjacent optical platform do not need to pass through the test mass block.

[0074] Based on the above principles, a full-link signal output module is designed: it includes three spacecraft simulation platforms with the same structure, two optical platforms are set on each spacecraft simulation platform, two measurement mass blocks are set on each optical platform, and one scientific interferometer, one test mass interferometer and one reference interferometer are set. Each optical platform transmits and receives lasers to the two adjacent optical platforms respectively. The full-link signal output module outputs a total of 18 interferometric measurement signals. Each optical platform outputs three interferometric measurement signals. Taking one of the optical platforms as an example, the interferometric measurement signal model output by the scientific interferometer, the test mass interferometer and the reference interferometer is as follows:

[0075]

[0076] Among them, φ SCI (t),φ TM (t) and φ REF (t) represent the output signals of the scientific interferometer, the test quality interferometer and the reference interferometer on the optical platform respectively; φ GW (t) represents the phase change caused by the gravitational wave signal; φ Noise1 (t) represents the difference between the phase change caused by the laser frequency noise and optical platform noise contained in the laser emitted by the remote optical platform and the local laser frequency noise and optical platform noise received by the optical platform; φNoise3 (t) represents the difference between the laser frequency noise and optical platform noise of the adjacent optical platform received by the local optical platform and the phase change caused by the laser frequency noise and optical platform noise of the local optical platform. Noise2 (t) represents various types of additive noise in scientific interferometers, φ Noise4 (t) represents the various types of additive noise existing in the test mass interferometer and the reference interferometer, φ ACC (t) represents the inertial sensor acceleration noise present in the test mass interferometer.

[0077] The numerical burr model includes three types of burr models, among which:

[0078] The first type of burr is:

[0079]

[0080] Among them, acc noise (t) represents the spur added to the link, A is the amplitude, τ is the decay time, t start Indicates the time when the glitch occurs, T Length Indicates the burr length;

[0081] The second type of burr is:

[0082]

[0083] Among them, acc noise (t) represents the spur added to the link, A is the amplitude, τ is the decay time, t start Indicates the time when the glitch occurs, T Length Indicates the burr length;

[0084] The third type of burr is:

[0085]

[0086] Among them, acc noise (t) represents the spur added to the link, A is the amplitude, τ is the decay time, t start Indicates the time when the glitch occurs, T Length Indicates the burr length, f0 is t start The frequency at time t, φ0 represents start The phase of the moment.

[0087] Preferably, the step of generating a simulation timing detection signal with glitch data according to the provided glitch parameters to realize glitch fault simulation includes:

[0088] Generate timing glitch data according to the provided glitch parameters and the selected glitch model type; the glitch parameters include: amplitude A, decay time τ, glitch start time t start , glitch duration T Length , and t start The frequency f0 and t at time start The phase at time φ0;

[0089] By inputting the acceleration noise data of the inertial sensor, the acceleration noise data of the inertial sensor including the burr data is obtained, and the burr fault simulation is realized.

[0090] The interference signal after adding burrs is expressed as follows:

[0091]

[0092] Among them, acc noise (t) represents the acceleration noise of the inertial sensor including glitches.

[0093] The simulation flow chart with glitch fault added is as follows: Figure 1 shown.

[0094] The interference signal after adding interruptions and glitches is expressed as follows:

[0095]

[0096] Preferably, the interruption model includes two types of interruption models, wherein:

[0097] The first type of interrupt model is:

[0098]

[0099] Among them, WA(t) represents the first type of interrupt function, t smooth Indicates the smoothing time, T Length represents the interruption length, and t represents the time;

[0100] The second type of interrupt model is:

[0101]

[0102] Among them, WB(t) represents the second type of interrupt function, t start Indicates the interruption start time, T Length Indicates the interruption length, t smooth Indicates the smoothing duration.

[0103] Preferably, the interrupt model is added by adding an interrupt function to realize interrupt fault simulation, including:

[0104] Determine the interrupt function according to the selected interrupt model type; set the interrupt length; set the smoothing time; set the interrupt start time to realize interrupt fault simulation.

[0105] Preferably, the interference signal after adding the interruption is expressed as follows:

[0106]

[0107] The simulation flow chart with interruption fault added is as follows: Figure 2 shown.

[0108] Preferably, the phase-locking strategy changing module aims to simulate the change of the phase-locking strategy when a link is interrupted in an actual situation, wherein:

[0109] During the operation of the system, under normal circumstances without interruption, it is necessary to set the system phase-locking sequence and the phase-locking main optical platform, and the laser in the main optical platform is used as the global master laser. A total of 3 phase-locking sequences can be adopted, and 6 optical platforms can be used as master optics, so there are a total of 18 phase-locking strategies. In the event of an interruption, the phase-locking strategy needs to be adaptively changed to minimize the impact of the interruption on the detection signal output.

[0110] In the actual operation process, there are mainly two types of interruptions, namely multi-arm interruption and single-arm interruption. The multi-arm interruption means that due to the redirection of the receiving antenna or extreme system failure, the ground cannot receive the detection signal sent back by any spacecraft or multiple intersatellite interference links cannot obtain data. The single-arm interruption means that during the operation of the system, the laser interference link between a spacecraft and another spacecraft is partially or completely interrupted due to system failure or space environment disturbance. When a multi-arm interruption occurs, the impact on the detection signal cannot be reduced by changing the phase-locking strategy. Therefore, only the adaptive change of the phase-locking strategy during a single-arm interruption is considered.

[0111] Preferably, the three spacecraft are spacecraft 1, spacecraft 2 and spacecraft 3, and the six optical platforms are optical platform A, optical platform B, optical platform C, optical platform D, optical platform E and optical platform F. Among them, optical platforms A and B are located in spacecraft 1, optical platforms C and D are located in spacecraft 2, and optical platforms E and F are located in spacecraft 3. The three phase-locking sequences are phase-locking sequence 1, phase-locking sequence 2 and phase-locking sequence 3. For the convenience of description, optical platform A is always used as the main optical platform, and the same strategy can be obtained when the other optical platforms are used as the main optical platforms, which will not be repeated.

[0112] In the phase locking sequence 1, the laser of optical platform B is phase locked to the laser of optical platform A, the laser of optical platform C is phase locked to the laser of optical platform B, the laser of optical platform D is phase locked to the laser of optical platform C, the laser of optical platform F is phase locked to the laser of optical platform A, and the laser of optical platform E is phase locked to the laser of optical platform F.

[0113] In the phase locking sequence 2, the laser of optical platform B is phase locked to the laser of optical platform C, the laser of optical platform C is phase locked to the laser of optical platform D, the laser of optical platform D is phase locked to the laser of optical platform E, the laser of optical platform E is phase locked to the laser of optical platform F, and the laser of optical platform F is phase locked to the laser of optical platform A.

[0114] In the phase locking sequence 3, the laser of optical platform B is phase locked to the laser of optical platform A, the laser of optical platform C is phase locked to the laser of optical platform D, the laser of optical platform D is phase locked to the laser of optical platform E, the laser of optical platform E is phase locked to the laser of optical platform F, and the laser of optical platform F is phase locked to the laser of optical platform A.

[0115] The single-arm interruption means that the interference link between two spacecraft is broken. There are three types of link breaks, namely, link break between spacecraft 1 and spacecraft 2, link break between spacecraft 1 and spacecraft 3, and link break between spacecraft 2 and spacecraft 3. The space gravitational wave detection formation has a total of 6 intersatellite interference links, and there are 2 intersatellite interference links between every two spacecraft, which are respectively recorded as Link1 and Link2. For single-arm link break, there are three types of link break, namely (Link1 is broken, Link2 is not broken), (Link1 is not broken, Link2 is not broken) and (Link1 is broken, Link2 is broken).

[0116] In the case of a single-arm interruption, there are three phase-locking schemes, named phase-locking sequence 1f, phase-locking sequence 2f, and phase-locking sequence 3f. Take the interruption of the interference link between optical platform D and optical platform E as an example to illustrate, where:

[0117] In the phase-locking sequence 1f, optical platform A is selected as the main optical platform, the laser of optical platform B is phase-locked to the laser of optical platform A, the laser of optical platform C is phase-locked to the laser of optical platform D, the laser of optical platform D is phase-locked to the laser of optical platform E, the laser of optical platform E is phase-locked to the laser of optical platform F, and the laser of optical platform F is phase-locked to the laser of optical platform A.

[0118] In the phase-locking sequence 2f, optical platform D is selected as the main optical platform, the laser of optical platform E is phase-locked to the laser of optical platform F, the laser of optical platform F is phase-locked to the laser of optical platform A, the laser of optical platform A is phase-locked to the laser of optical platform B, the laser of optical platform B is phase-locked to the laser of optical platform C, and the laser of optical platform C is phase-locked to the laser of optical platform D.

[0119] In the phase-locking sequence 3f, optical platform C is selected as the main optical platform, the laser of optical platform E is phase-locked to the laser of optical platform F, the laser of optical platform F is phase-locked to the laser of optical platform A, the laser of optical platform A is phase-locked to the laser of optical platform B, the laser of optical platform B is phase-locked to the laser of optical platform C, and the laser of optical platform D is phase-locked to the laser of optical platform C.

[0120] In order to describe the interruption of all intersatellite interferometric links, the link breaks between optical platform A and optical platform F are defined as α1, α2 and α 12 , where α1 indicates the laser link from optical platform A to optical platform F is broken, α2 indicates the laser link from optical platform F to optical platform A is broken, and α 12 Indicates that both links are broken. The links between optical platform B and optical platform C are broken as β1, β2 and β 12 Similarly, β1 indicates that the laser link from optical platform B to optical platform C is broken, β2 indicates that the laser link from optical platform C to optical platform B is broken, and β 12 Indicates that both links are broken. The links between optical platform E and optical platform D are broken as γ1, γ2 and γ 12 Similarly, γ1 indicates that the laser link from optical platform E to optical platform D is broken, and γ2 indicates that the laser link from optical platform D to optical platform F is broken. 12 Indicates that both links are broken. The phase-lock sequence strategy for single-arm interruption replacement with optical platform A as the main optical platform is as follows:

[0121] Before the single-arm interruption, the phase-locked sequence is 1. If the interruption situation is α1 / α2 / α 12 , the phase-locking sequence is adjusted to phase-locking sequence 2f.

[0122] Before the single-arm interruption, the phase-locked sequence is 1. If the interruption situation is β1 / β2 / β 12 , the phase-locking sequence is adjusted to phase-locking sequence 3f.

[0123] Before the single-arm interruption, the phase-locked sequence is 1. If the interruption situation is γ1 / γ2 / γ 12 , then the phase-locking sequence does not need to be adjusted.

[0124] Before the single-arm interruption, the phase-locked sequence is 2. If the interruption situation is α1 / α2 / α 12 , the phase-locking sequence is adjusted to phase-locking sequence 2f.

[0125] Before the single-arm interruption, the phase-locked sequence is 2. If the interruption condition is β1 / β2 / β 12 , the phase-locking sequence is adjusted to phase-locking sequence 3f.

[0126] Before the single-arm interruption, the phase-locked sequence is 2. If the interruption situation is γ1 / γ2 / γ 12, the phase-locking sequence is adjusted to phase-locking sequence 1f.

[0127] Before the single-arm interruption, the phase-locked sequence is 3. If the interruption condition is α1 / α2 / α 12 , the phase-locking sequence is adjusted to phase-locking sequence 2f.

[0128] Before the single-arm interruption, the phase-locked sequence is 3. If the interruption condition is β1 / β2 / β 12 , then the phase-locking sequence does not need to be adjusted.

[0129] Before the single-arm interruption, the phase-locked sequence is 3. If the interruption situation is γ1 / γ2 / γ 12 , the phase-locking sequence is adjusted to phase-locking sequence 1f.

[0130] The technical solution of the present invention is described in detail below with reference to the accompanying drawings and embodiments.

[0131] Example

[0132] like Figure 3 As shown, an embodiment of the present invention provides a space-based gravitational wave detection signal simulation system including fault simulation, comprising:

[0133] Full-link signal output module, used to simulate and output multi-channel interferometric measurement signals of space-based gravitational wave detection formations;

[0134] A glitch fault simulation module is used to construct different types of numerical glitch models and to generate a simulation timing detection signal with glitch data according to the provided glitch parameters to realize glitch fault simulation;

[0135] An interrupt fault simulation module is used to construct different types of interrupt models and to add interrupt models by adding interrupt functions to realize interrupt fault simulation;

[0136] The phase-locking strategy changing module is used to switch to a specific phase-locking strategy when a system failure occurs.

[0137] Simulation Example 1:

[0138] The noises involved in the full-link output signal output include laser frequency noise, optical platform noise, laser pointing jitter noise, readout noise, advance pointing optical path noise, breathing angle compensation optical path noise, and inertial sensor acceleration noise. A wave source of double black hole merger was used for simulation experiments, and the signal-to-noise ratio of the wave source signal was 2000. A total of 18 interferometric measurement data were generated through simulation. Figure 4 The figure shows one of the interferometric measurement data timing signals, with a simulation duration of 10 days and a sampling rate of 3 Hz.

[0139] Simulation Example 2:

[0140] The data interruption simulation parameters are: a. Periodic data interruption: 3.5 hours per week b. Random data interruption: once a day, 10 minutes each time. The periodic data interruption window function is as follows: Figure 5 As shown; the random interruption window function is as follows Figure 6 As shown; the detection data after adding the interruption is as follows Figure 7 During the simulation process, wave source data with different types and durations including data interruptions can be constructed according to parameter settings.

[0141] The first type of burr model is used for simulation, and the parameters are set as follows:

[0142]

[0143] The first type of glitch timing simulation data and the comparison of the acceleration noise signal of the inertial sensor before and after adding the glitch. Figure 8 As shown, the red line represents the acceleration noise of the timing inertial sensor without adding glitches, and the blue line represents the acceleration noise of the timing inertial sensor after adding glitches.

[0144] Summary:

[0145] Aiming at the problem of full-link interference signal simulation including fault simulation of the long period of space-based gravitational wave detection formation, a space-based gravitational wave detection signal simulation method and system including fault simulation are proposed. Considering various noise coupling factors, a full-link signal output module, interruption fault simulation module, phase-locked strategy change module and glitch fault simulation module are constructed, which can realize normal operation data simulation and data simulation in the event of a fault.

[0146] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit the present invention. Although the present invention is described in detail with reference to the embodiments, it should be understood by those skilled in the art that any modification or equivalent replacement of the technical solutions of the present invention does not depart from the spirit and scope of the technical solutions of the present invention and should be included in the scope of the claims of the present invention.

Claims

1. A space-based gravitational wave detection signal simulation system including fault simulation, characterized in that: include: Full-link signal output module, used to simulate and output multi-channel interferometric measurement signals of space-based gravitational wave detection formations; A glitch fault simulation module is used to construct different types of numerical glitch models and to generate a simulation timing detection signal with glitch data according to the provided glitch parameters to realize glitch fault simulation; An interrupt fault simulation module is used to construct different types of interrupt models and to add interrupt models by adding interrupt functions to realize interrupt fault simulation; and A phase-locking strategy changing module is used to switch to a specific phase-locking strategy when a system failure occurs; The different types of numerical glitch models include: The first type of glitch model: Among them, acc noise (t) represents the spur added to the link, A is the amplitude, τ is the decay time, t start Indicates the time when the glitch occurs, T Length Indicates the burr length; The second type of burr model: Among them, acc noise (t) represents the spur added to the link, A is the amplitude, τ is the decay time, t start Indicates the time when the glitch occurs, T Length represents the burr length; and The third type of burr model: Among them, acc noise (t) represents the spur added to the link, A is the amplitude, τ is the decay time, t start Indicates the time when the glitch occurs, T Length Indicates the burr length, f0 is t start The frequency at time t, φ0 represents start The phase of the moment; The different types of interrupt models include: The first type of interrupt model: Among them, WA(t) represents the first type of interrupt function, t smooth Indicates the smoothing time, T Length represents the length of the interruption, t represents the time; and The second type of interrupt model: Among them, WB(t) represents the second type of interrupt function, t start Indicates the interruption start time, T Length Indicates the interruption length, t smooth Indicates the smoothing duration; The interrupt model is added by adding an interrupt function to realize interrupt fault simulation, including: Determine the interrupt function according to the selected interrupt model type; Determine the length of the window function w(t) according to the set interruption length; Set the smoothing duration; Set the start time to realize interruption fault simulation; The interference signal after adding the interruption satisfies the following formula: Among them, φ SCI (t),φ TM (t) and φ REF (t) represent the output signals of the scientific interferometer, the test quality interferometer and the reference interferometer on the optical platform respectively; φ GW (t) represents the phase change caused by the gravitational wave signal; φ Noise1 (t) represents the difference between the phase change caused by the laser frequency noise and optical platform noise contained in the laser emitted by the remote optical platform and the local laser frequency noise and optical platform noise received by the optical platform; φ Noise3 (t) represents the difference between the phase change caused by the laser frequency noise and optical platform noise of the adjacent optical platform received by the local optical platform and the laser frequency noise and optical platform noise of the local optical platform, φ Noise2 (t) represents various types of additive noise in scientific interferometers, φ Noise4 (t) represents the various types of additive noise existing in the test mass interferometer and the reference interferometer, φ ACC (t) represents the acceleration noise of the inertial sensor present in the test mass interferometer, and t represents time.

2. The space-based gravitational wave detection signal simulation system including fault simulation according to claim 1, characterized in that: The full-link signal output module includes three spacecraft simulation platforms with the same structure, namely spacecraft simulation platform 1, spacecraft simulation platform 2 and spacecraft simulation platform 3. Two optical platforms are arranged on each spacecraft simulation platform, namely optical platforms A and B on spacecraft simulation platform 1, optical platforms C and D on spacecraft simulation platform 2, and optical platforms E and F on spacecraft simulation platform 3. When one of the optical platforms is the main optical platform, three phase-locking sequences correspond to it; two measurement mass blocks, as well as one scientific interferometer, one test mass interferometer and one reference interferometer are arranged on each optical platform. Each optical platform transmits and receives lasers to and from two adjacent optical platforms respectively. The full-link signal output module has 18 phase-locking sequences and outputs 18 interference measurement signals in total. There are two intersatellite interference links between every two spacecraft simulation platforms.

3. The space-based gravitational wave detection signal simulation system including fault simulation according to claim 2, characterized in that: There are three phase-locking sequences corresponding to the optical platform A as the main optical platform, among which: Phase locking sequence 1 is: the laser on optical platform B is phase locked to the laser on optical platform A, the laser on optical platform C is phase locked to the laser on optical platform B, the laser on optical platform D is phase locked to the laser on optical platform C, the laser on optical platform F is phase locked to the laser on optical platform A, and the laser on optical platform E is phase locked to the laser on optical platform F; Phase locking sequence 2 is: the laser on optical platform B is phase locked to the laser on optical platform C, the laser on optical platform C is phase locked to the laser on optical platform D, the laser on optical platform D is phase locked to the laser on optical platform E, the laser on optical platform E is phase locked to the laser on optical platform F, and the laser on optical platform F is phase locked to the laser on optical platform A; Phase locking sequence 3 is: the optical platform B laser is phase locked to the optical platform A laser, the optical platform C laser is phase locked to the optical platform D laser, the optical platform D laser is phase locked to the optical platform E laser, the optical platform E laser is phase locked to the optical platform F laser, and the optical platform F laser is phase locked to the optical platform A laser.

4. The space-based gravitational wave detection signal simulation system including fault simulation according to claim 2, characterized in that: The interferometric measurement signals output by the scientific interferometer, the test quality interferometer and the reference interferometer of each optical platform satisfy the following formula: Among them, φ SCI (t),φ TM (t) and φ REF (t) represent the output signals of the scientific interferometer, the test quality interferometer and the reference interferometer on the optical platform respectively; φ GW (t) represents the phase change caused by the gravitational wave signal; φ Noise1 (t) represents the difference between the phase change caused by the laser frequency noise and optical platform noise contained in the laser emitted by the remote optical platform and the local laser frequency noise and optical platform noise received by the optical platform; φ Noise3 (t) represents the difference between the phase change caused by the laser frequency noise and optical platform noise of the adjacent optical platform received by the local optical platform and the laser frequency noise and optical platform noise of the local optical platform, φ Noise2 (t) represents various types of additive noise in scientific interferometers, φ Noise4 (t) represents the various types of additive noise existing in the test mass interferometer and the reference interferometer, φ ACC (t) represents the acceleration noise of the inertial sensor present in the test mass interferometer, and t represents time.

5. The space-based gravitational wave detection signal simulation system including fault simulation according to claim 1, characterized in that: The method of generating a simulation timing detection signal with glitch data according to the provided glitch parameters to realize glitch fault simulation includes: Generate timing glitch data according to the provided glitch parameters and the selected glitch model type; the glitch parameters include: amplitude A, decay time τ, glitch start time t start , glitch duration T Length , and t start The frequency f0 and t at time start The phase at time φ0; By inputting the acceleration noise data of the inertial sensor, the acceleration noise data of the inertial sensor including the burr data is obtained, and the burr fault simulation is realized.

6. The space-based gravitational wave detection signal simulation system including fault simulation according to claim 3, characterized in that: The system failures include single-arm interruption, which is the interruption of the interference link between the two spacecraft simulation platforms, including: The links α1, α2 and α between optical platform A and optical platform F are broken. 12 , where α1 indicates the laser link from optical platform A to optical platform F is broken, α2 indicates the laser link from optical platform F to optical platform A is broken, and α 12 Indicates that both links are broken; The links β1, β2 and β3 between platform B and optical platform C are broken. 12 , where β1 represents the laser link break from optical platform B to optical platform C, β2 represents the laser link break from optical platform C to optical platform B, and β 12 Indicates that both links are broken; and The links γ1, γ2 and γ between platform E and optical platform D are broken. 12 , where γ1 represents the laser link from optical platform E to optical platform D is broken, γ2 represents the laser link from optical platform D to optical platform F is broken, and γ 12 Indicates that both links are broken; The phase-lock sequence strategy for single-arm interruption replacement with optical platform A as the main optical platform is as follows: When the single arm is interrupted, the phase-locked sequence is 1. If the interruption condition is α1 or α2 or α 12 , the phase-locking sequence is adjusted to phase-locking sequence 2f; if the interruption condition is β1 or β2 or β 12 , the phase-locking sequence is adjusted to phase-locking sequence 3f; if the interruption condition is γ1 or γ2 or γ 12 , then the phase-locking sequence does not need to be adjusted; When the single arm is interrupted before the phase lock sequence 2, if the interruption condition is α1 or α2 or α 12 , the phase-locking sequence is adjusted to phase-locking sequence 2f; if the interruption condition is β1 or β2 or β 12 , the phase-locking sequence is adjusted to phase-locking sequence 3f; if the interruption situation is γ1 / γ2 / γ 12 , then the phase-locking sequence is adjusted to phase-locking sequence 1f; When the single arm is interrupted, the phase-locked sequence is 3, if the interruption condition is α1 or α2 or α 12 , the phase-locking sequence is adjusted to phase-locking sequence 2f; if the interruption condition is β1 or β2 or β 12 , then the phase-locking sequence does not need to be adjusted; if the interruption condition is γ1 or γ2 or γ 12 , the phase-locking sequence is adjusted to phase-locking sequence 1f.

7. The space-based gravitational wave detection signal simulation system including fault simulation according to claim 6, characterized in that: The phase locking sequence 1f is: select optical platform A as the main optical platform, phase lock the laser of optical platform B to the laser of optical platform A, phase lock the laser of optical platform C to the laser of optical platform D, phase lock the laser of optical platform D to the laser of optical platform E, phase lock the laser of optical platform E to the laser of optical platform F, and phase lock the laser of optical platform F to the laser of optical platform A; The phase locking sequence 2f is: select optical platform D as the main optical platform, phase lock the laser of optical platform E to the laser of optical platform F, phase lock the laser of optical platform F to the laser of optical platform A, phase lock the laser of optical platform A to the laser of optical platform B, phase lock the laser of optical platform B to the laser of optical platform C, and phase lock the laser of optical platform C to the laser of optical platform D; The phase-locking sequence 3f is: select optical platform C as the main optical platform, phase-lock the laser of optical platform E to the laser of optical platform F, phase-lock the laser of optical platform F to the laser of optical platform A, phase-lock the laser of optical platform A to the laser of optical platform B, phase-lock the laser of optical platform B to the laser of optical platform C, and phase-lock the laser of optical platform D to the laser of optical platform C.

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