A method for testing missile-borne satellite receiver compatibility

Abstract

The application discloses a kind of missile-borne satellite receiver compatibility test methods, specifically related to satellite navigation semi-physical simulation test field, for solving the problem of false carrier phase anomaly caused by test link timing slip under high dynamic concurrent test conditions and interfering compatibility determination;By extracting the basic carrier phase polynomial coefficients corresponding to the multi-source constellation observation nodes according to the upper clock frequency of the dynamic flight trajectory data, it is sent to the radio frequency generating end through the asynchronous communication bus, and then combined with the non-integer multiple phase difference component and the inherent timing residence delay to generate time micro-disturbance parameters, execute abnormal state discrimination, and complete high-frequency interpolation expansion and target radio frequency test signal reconstruction by the bottom hardware multiplication-addition pipeline array, finally, according to the dynamic tracking state data output by the measured missile-borne satellite receiver, the compatibility closed-loop evaluation is executed.

Description

Technical Field

[0001] This invention relates to the field of hardware-in-the-loop (HIL) simulation testing for satellite navigation, and more specifically, to a testing method for the compatibility of missile-borne satellite receivers. Background Technology

[0002] Hardware-in-the-loop (HIL) simulation tests for the compatibility of missile-borne satellite receivers typically use dynamic flight trajectory data as input. During the test, multi-constellation hybrid radio frequency (RF) signals corresponding to the flight state are continuously generated and physically coupled into the receiver under test. The receiver's operational status under high-maneuver conditions is then determined based on the dynamic tracking status data output by the receiver. The key to this type of test is not simply generating navigation signals, but ensuring that the host computer's trajectory calculation, cross-bus data transmission, RF generator reconstruction, and receiver response acquisition remain consistent under the same time reference. If a timing slip occurs between the host clock frequency and the underlying clock frequency, or if the link dwell time from the command to the microwave antenna radiating end accumulates offset, unnatural carrier phase anomalies may form at the radiating end. This can cause the receiver's phase-locked loop (PLL) and delay-locked loop (DLL) to respond to errors in the test platform itself, thus interfering with the compatibility assessment.

[0003] Existing technologies mostly address the aforementioned problems from a time synchronization perspective. For example, patent document CN111208539A discloses a high-precision GNSS simulator time synchronization method. Its core lies in continuously adjusting the timing period inside the external timing device based on the second pulse signal output by the GNSS simulator, thereby reducing the cumulative time error between the simulation computer and the GNSS simulator. This type of solution can improve the long-term synchronization deviation between the simulation computer and the simulator, but its focus is still on time correction or cumulative error correction. For cross-bus transmission of low-dimensional carrier phase parameters corresponding to multi-source constellation observation nodes under high dynamic flight trajectory drive, joint identification of asynchronous clock slip and physical overload, and closed-loop compatibility assessment for dynamic tracking status data of the tested missile-borne satellite receiver, an integrated processing chain from parameter generation, anomaly truncation to RF reconstruction and result attribution has not yet been formed.

[0004] To address the aforementioned problems, a technical solution is provided. Summary of the Invention

[0005] To overcome the aforementioned deficiencies in the prior art, embodiments of the present invention provide a test method for the compatibility of missile-borne satellite receivers. This method involves extracting the fundamental carrier phase polynomial coefficients corresponding to the observation nodes of a multi-source constellation from dynamic flight trajectory data at the host clock frequency, transmitting these coefficients to the radio frequency generator via an asynchronous communication bus, and then generating time perturbation parameters by combining non-integer multiple phase difference components and inherent timing dwell delays. Abnormal state identification is then performed, and high-frequency interpolation expansion and target radio frequency test signal reconstruction are completed by a low-level hardware multiply-accumulate pipeline array. Finally, a compatibility closed-loop evaluation is performed based on the dynamic tracking status data output by the missile-borne satellite receiver under test, thereby solving the problems mentioned in the background art.

[0006] To achieve the above objectives, the present invention provides the following technical solution: A test method for the compatibility of missile-borne satellite receivers, comprising the following steps: Step S1: In response to the input dynamic flight trajectory data, extract the fundamental carrier phase polynomial coefficients corresponding to the multi-source constellation observation nodes according to the host clock frequency, and send them to the radio frequency generator via the asynchronous communication bus; Step S2: Extract the non-integer multiple phase difference components between the upper clock frequency and the lower clock frequency, combine them with the inherent timing dwell delay to generate time perturbation parameters, and perform abnormal state identification based on clock slip dispersion and radial mutation rate; Step S3: The RF generator receives the untrunculated fundamental carrier phase polynomial coefficients and time perturbation parameters, performs high-frequency interpolation expansion through the underlying hardware multiply-accumulate pipeline array, and reconstructs the target RF test signal; Step S4: Physically couple the target radio frequency test signal into the receiver of the missile-borne satellite under test, receive the dynamic tracking status data output by the receiver, and perform a compatibility closed-loop evaluation based on the dynamic tracking status data.

[0007] Furthermore, in step S1, the fundamental carrier phase polynomial coefficients are obtained by the host computer within a preset time window based on dynamic flight trajectory data and multi-source constellation observation nodes. First, the Doppler frequency shift envelope curve is calculated according to the time sequence of the nodes. Then, the corresponding carrier phase node sequence is parametrically fitted and extracted based on the start time of the current preset time window. The coefficients are then combined with the preset time window identifier and the correspondence between the multi-source constellation observation nodes to form a window coefficient frame.

[0008] Furthermore, in step S1, the host computer extracts the basic carrier phase polynomial coefficients by fitting a cubic or higher-order polynomial based on the correspondence between the node time offset sequence and the carrier phase node sequence, and forms a fixed transmission order according to the correspondence between the observation nodes of the multi-source constellation. Then, using the write-side clock as the host clock frequency, the window coefficient frame is transmitted across clock cycles to the radio frequency generator via the asynchronous communication bus.

[0009] Furthermore, in step S2, the RF generator, for the window coefficient frame corresponding to the current preset time window identifier, makes the write clock corresponding to the upper clock frequency and the read clock corresponding to the lower clock frequency enter the same phase detection sampling sequence, extracts the non-integer multiple phase difference components in node order, and maps the non-integer multiple phase difference components and the inherent timing dwell delay between the instruction sent to the microwave antenna radiating end face to the same preset time window to generate time perturbation parameters.

[0010] Furthermore, in step S2, the abnormal state identification includes: obtaining the transient phase slip rate by performing first-order time derivative on the non-integer multiple phase difference components; obtaining the clock slip dispersion by statistically calculating the second-order central moment of the transient phase slip rate within the current preset time window; determining the radial motion acceleration based on the dynamic flight trajectory data and the observation nodes of the multi-source constellation and performing time-domain differential derivative to obtain the radial mutation rate; importing the clock slip dispersion and the radial mutation rate into the Mahalanobis distance anomaly detection model; triggering the polynomial time window adaptive truncation degradation action when the Mahalanobis distribution distance exceeds the safety judgment limit, and outputting the time window truncation mark and the replacement fundamental carrier phase polynomial coefficients.

[0011] Furthermore, in step S3, the radio frequency generator performs in-situ selection between the fundamental carrier phase polynomial coefficients and the alternative fundamental carrier phase polynomial coefficients based on the time window truncation mark, and loads the time perturbation parameters corresponding to the selected polynomial coefficients into the underlying hardware multiply-accumulate pipeline array. The channel scheduling order is established according to the correspondence of the observation nodes of the multi-source constellation, and multiple satellite channels are processed sequentially using a time-division multiplexing architecture. Among them, when the current preset time window has a time window truncation mark, the time perturbation parameters are degraded time perturbation parameters.

[0012] Furthermore, in step S3, the RF generator first generates an interpolated time sequence covering the current preset time window based on the underlying clock frequency, then maps the time perturbation parameters to a beat-level injection time sequence that corresponds one-to-one with the interpolated time sequence, and then substitutes the beat-level injection time sequence and the fundamental carrier phase polynomial coefficients into it step by step to generate the transient carrier phase of each channel, and then synthesizes and outputs the target RF test signal.

[0013] Furthermore, in step S4, the target radio frequency test signal is injected into the receiver of the missile-borne satellite under test through the physical coupling path in the order of the preset time window identifiers, and the corresponding injection start time and injection end time are recorded at each preset time window injection; the dynamic tracking status data is output in reverse by the baseband processing chip inside the receiver of the missile-borne satellite under test, including the unlock or lock indication flags of the phase-locked loop and the delay-locked loop, the loop traction convergence time, and the pseudorange jump slope.

[0014] Furthermore, in step S4, an injection sequence is constructed based on the preset time window identifier, injection start time, injection end time, and time window truncation mark. Dynamic tracking status data whose receiving time falls into the corresponding injection interval are assigned to the corresponding preset time window to form a window evaluation record containing the preset time window identifier, time window truncation mark, and dynamic tracking status data. Then, the receiver response is divided into continuous tracking state, transient traction state, and tracking abnormal state based on each window evaluation record.

[0015] Furthermore, in step S4, the compatibility closed-loop evaluation is performed according to the tolerance table preset in the test task file. The tolerance table includes at least the upper limit of the continuous unlock window length, the upper limit of the single window loop traction convergence time, and the upper limit of the pseudo-range jump slope. When the corresponding state of all window evaluation records has not exceeded the tolerance table, the compatibility pass conclusion is output; otherwise, the compatibility fail conclusion is output, and the first preset time window that does not meet the tolerance table is marked in the abnormal attribution record.

[0016] The technical effects and advantages of the test method for missile-borne satellite receiver compatibility of the present invention are as follows: This invention compresses the continuously changing carrier phase process under high dynamic conditions into basic carrier phase polynomial coefficients for cross-bus transmission. Compared with directly sending complete RF waveform digital sampling points, it can significantly reduce the data interaction burden between the host computer and the RF generator, enabling the carrier phase information corresponding to the observation nodes of multi-source constellations to be transmitted in a stable mathematical characteristic form within a preset time window, thus mitigating the impact of bus queuing on the signal generation link under high concurrency channel conditions.

[0017] This invention introduces a joint discrimination mechanism of clock slip dispersion and radial mutation rate while generating time perturbation parameters, and performs polynomial time window adaptive truncation degradation in abnormal conditions. This enables the anomalies caused by timing disorder and the physical impact response corresponding to dynamic flight trajectory data to be distinguished in the same processing chain, reducing the non-natural carrier phase anomalies transmitted from the instability of the test link itself to the subsequent RF reconfiguration process.

[0018] This invention further completes high-frequency interpolation expansion through a low-level hardware multiply-accumulate pipeline array, and associates the target RF test signal with the dynamic tracking status data according to a preset time window identifier, so that the compatibility closed-loop evaluation is based on a unified input waveform source, time window status, and receiver response. The resulting window evaluation record and anomaly attribution record have a clear time window index relationship, which makes it easy to identify the correspondence between the tracking anomaly of the tested missile-borne satellite receiver and the upstream time window truncation processing in the same test process. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the overall process of a test method for the compatibility of a missile-borne satellite receiver according to the present invention; Figure 2 This is a block diagram showing the system composition and data flow of the test link in this invention; Figure 3 This is a schematic diagram of the generation of basic carrier phase polynomial coefficients and the formation of window coefficient frames in step S1 of the present invention. Figure 4 This is a flowchart of the time perturbation parameter generation and abnormal state identification process in step S2 of the present invention. Figure 5 This is a block diagram of the deployment of the underlying hardware multiply-accumulate pipeline array and the reconstruction of the target RF test signal in step S3 of the present invention; Figure 6 This is a schematic diagram showing the correspondence between physical coupling injection and compatibility closed-loop evaluation in step S4 of the present invention. Detailed Implementation

[0020] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0021] Please see Figure 1 - Figure 6 This invention provides a method for testing the compatibility of missile-borne satellite receivers, comprising: This invention focuses on processing dynamic flight trajectory data. First, on the host computer side, multi-source constellation observation nodes are organized according to a preset time window, and the continuously changing carrier phase process is compressed into the fundamental carrier phase polynomial coefficients to form a window coefficient frame that can be transmitted across the asynchronous communication bus. Then, at the radio frequency generator, non-integer multiple phase difference components and inherent timing dwell delay are extracted to generate time perturbation parameters. Based on clock slip dispersion, radial mutation rate, and abnormal state identification results, it is decided whether to retain the original fundamental carrier phase polynomial coefficients or call the replacement fundamental carrier phase polynomial coefficients. On this basis, the underlying hardware multiply-accumulate pipeline array performs high-frequency interpolation expansion according to the current preset time window identifier and the correspondence between the multi-source constellation observation nodes to form a multi-channel target radio frequency test signal. Finally, the target radio frequency test signal is physically coupled and injected into the receiver of the tested missile-borne satellite, and the dynamic tracking status data is collected and organized according to the preset time window identifier to form a window evaluation record and compatibility closed-loop evaluation results.

[0022] Step S1: In response to the input dynamic flight trajectory data, the fundamental carrier phase polynomial coefficients corresponding to the multi-source constellation observation nodes are extracted according to the host clock frequency, and sent to the radio frequency generator via the asynchronous communication bus. Specifically, the implementation method is as follows: The dynamic flight trajectory data has been locked as the starting input for the entire process. The upper clock frequency, the lower clock frequency, and the preset time window boundaries that will be called in steps S2 and S3 have also been determined. However, before entering the extraction of non-integer multiple phase difference components and the generation of time perturbation parameters, it is still necessary to compress the continuously changing flight state into the basic carrier phase polynomial coefficients that can be stably transmitted across the bus, and establish a one-to-one correspondence between these coefficients and the observation nodes of the multi-source constellation and the preset time window, as the common input basis for subsequent anomaly identification and radio frequency reconstruction.

[0023] Organization of multi-source constellation observation nodes within the S101 preset time window: In this sub-step, the dynamic flight trajectory data, which starts from the input, is processed. The host computer performs time base expansion on the dynamic flight trajectory data according to the host clock frequency. First, the continuous trajectory calculation results are divided into preset time windows with the beginning and end connected. The length of each preset time window is fixed at 10 milliseconds to 50 milliseconds. Then, the clock beat corresponding to the host clock frequency is used as the node generation reference. Within each preset time window, a sequence of node times arranged in chronological order is formed. Each node time is then aligned with the observation nodes of the multi-source constellation currently participating in the test to obtain the observation node sequence within the window corresponding to each satellite channel. When determining the observation nodes of the multi-source constellation currently participating in the test, the host computer first reads the constellation system list, signal system list, and observation elevation threshold preset in the test mission file. Then, combined with the satellite ephemeris and dynamic flight trajectory data corresponding to the start time of the current preset time window, it calculates the line-of-sight direction from the missile body to the satellite and the observation elevation angle for each satellite. When the observation elevation angle is not lower than the observation elevation threshold and the constellation and signal system of the satellite are included in the test mission file, the satellite is registered as a multi-source constellation observation node within the current preset time window. The correspondence between the multi-source constellation observation nodes in the current preset time window is formed according to the fixed order of constellation type, satellite number, and signal system. If a satellite enters or exits the observation range within the current preset time window, the first node time that meets or does not meet the conditions corresponding to the host clock frequency is taken as the start and end boundary of the satellite channel within the current preset time window.

[0024] In this context, multi-source constellation observation nodes are not treated as independent waveform sampling points, but rather as connection points for linking dynamic flight trajectory data with the line-of-sight relationships of each satellite channel. The host computer reads the position, velocity, and attitude calculation results from the dynamic flight trajectory data at each node, and determines the relative motion relationship between the missile body and the corresponding satellite channel based on the multi-source constellation observation node at that node, thus forming a basic carrier evolution sequence that changes node by node within the window. To ensure that subsequent steps can trace and access the current window, the host computer simultaneously generates a unique preset time window identifier for each preset time window and generates a fixed-order correspondence between multi-source constellation observation nodes for each satellite channel within the same preset time window.

[0025] As an example of this sub-step, when the missile enters the high-maneuver flight segment, the host computer continuously receives the three-dimensional trajectory calculation results of this segment. Within a certain preset time window, it sequentially extracts all the host clock beats covered by the time window and connects each beat to the Beidou, GPS and other visible satellite channels participating in the simulation, thereby obtaining the observation node sequence within the window sorted by time. At this time, what is formed is not the radio frequency sampling stream, but the nodeized trajectory-observation correspondence required for subsequent calculation of the fundamental carrier phase polynomial coefficients.

[0026] Extraction of S102 fundamental carrier phase polynomial coefficients: After obtaining the preset time window identifier and the corresponding observation node sequence within the window, the host computer begins to extract the fundamental carrier phase polynomial coefficients for each satellite channel. Specifically, the host computer first obtains the envelope curve of the Doppler frequency shift of the satellite channel within the current preset time window based on the dynamic flight trajectory data and the relative motion relationship between the observation nodes of the multi-source constellation. Then, using this envelope curve as input, it integrates the cumulative frequency shift from the start time of the window to the time of each node to obtain the fundamental carrier phase sampling value of the corresponding node, thereby forming the carrier phase node sequence of the current satellite channel within the current preset time window.

[0027] To enable the node sequence to be transmitted in low-dimensional form in the asynchronous communication bus, the host computer uses the start time of the window as the time zero point, constructs a fitting relationship between the node time offset sequence and the carrier phase node sequence, and extracts the fundamental carrier phase polynomial coefficients using a cubic or higher-order polynomial fitting algorithm. The current preset time window contains the [number of nodes]. The fundamental carrier phase of each satellite channel can be expressed as: ; in, The preset time window is marked as Within the current preset time window, the first Each satellite channel at time The fundamental carrier phase, This is the time offset of this moment relative to the start time of the current preset time window. to The fundamental carrier phase polynomial coefficients to be extracted. The fitting order is at least 3. The host computer constructs a Vandermonde matrix using the time offsets of all nodes within the window, and an observation vector using the sampled values ​​of the fundamental carrier phase of each node. The result is then solved using least-squares fitting. to This compresses the originally continuously changing carrier phase process into a set of discrete coefficients corresponding to the current preset time window.

[0028] To ensure the continuity of carrier phase between adjacent preset time windows, the host computer uses the fundamental carrier phase at the end of the previous preset time window as the alignment reference for the constant terms of the current preset time window when solving the fundamental carrier phase polynomial coefficients for the current preset time window. When the current satellite channel is a newly entered channel within the window, the integral phase of that channel at the beginning of the current preset time window is used as the initial value of the constant terms. The resulting fundamental carrier phase polynomial coefficients retain the phase evolution trend under highly dynamic flight conditions and provide a continuous starting point for the high-frequency interpolation expansion in step S3.

[0029] As an example of this sub-step, within a preset time window during the projectile's roll and concurrent multi-satellite tracking, the host computer does not generate complete IQ sampling points for each satellite channel within that time window. Instead, it first obtains the Doppler frequency shift envelope based on the relative motion relationship at each node within the window, then converts the envelope into a carrier phase node sequence, and finally calculates a set of basic carrier phase polynomial coefficients for each satellite channel. At the end of the same preset time window, only the set of coefficients and their correspondence with the observation nodes of the multi-source constellation are retained as the result for direct calling in subsequent links.

[0030] S103 fundamental carrier phase polynomial coefficients are transmitted across the bus: After extracting the fundamental carrier phase polynomial coefficients of each satellite channel within the current preset time window, the host computer groups the coefficients of all satellite channels within the same preset time window according to the preset time window identifier, then forms a fixed transmission order according to the correspondence of observation nodes in the multi-source constellation, and encapsulates the polynomial order, fundamental carrier phase polynomial coefficients, and time reference of the start time of the current preset time window for each satellite channel into a window coefficient frame. The window coefficient frame does not carry complete RF waveform digital sampling points, but only carries the low-dimensional mathematical features required for reconstruction, thereby converting the object to be transmitted on the asynchronous communication bus from a high-frequency sampling stream into a discrete coefficient stream.

[0031] After encapsulation, the host computer uses the write-side clock as the host clock frequency to write the window coefficient frames into the cross-clock buffer queue of the asynchronous communication bus. The RF generator uses the read-side clock as the underlying clock frequency and reads the corresponding window coefficient frames in the order of the preset time window identifier. To maintain the closed loop of subsequent steps, the RF generator does not change the name and arrangement of the fundamental carrier phase polynomial coefficients during reception, but only saves the preset time window identifier, the corresponding multi-source constellation observation node correspondence, and the fundamental carrier phase polynomial coefficients of each satellite channel within the time window in the local cache. In this way, when generating time perturbation parameters and executing the abnormal state identification and processing mechanism in step S2, the fundamental carrier phase polynomial coefficients corresponding to the current time window can be located by using the preset time window identifier as an index. Step S3 can then directly call the untruncated fundamental carrier phase polynomial coefficients to complete the high-frequency interpolation expansion of the underlying hardware multiply-accumulate pipeline array.

[0032] As an example of this sub-step, after a certain preset time window ends, the host computer writes the basic carrier phase polynomial coefficients corresponding to the Beidou channel, GPS channel and other satellite channels within that time window into the asynchronous communication bus in a predetermined order. The radio frequency generator retrieves and buffers the coefficients frame by frame according to the underlying clock frequency. When the subsequent step S2 determines that a certain preset time window has an instability risk, it can directly locate the basic carrier phase polynomial coefficients corresponding to that time window based on the same preset time window identifier and decide whether to perform the time window adaptive truncation and degradation action without having to re-trace back the original trajectory sampling stream.

[0033] After processing in step S1, the dynamic flight trajectory data has been organized according to the host clock frequency into the basic carrier phase polynomial coefficients corresponding to the multi-source constellation observation nodes within a preset time window. Together with the preset time window identifier and the correspondence of the multi-source constellation observation nodes, it forms a window coefficient frame that can be transmitted across the asynchronous communication bus. Among them, the basic carrier phase polynomial coefficients serve as the common input object for the abnormal state identification in step S2 and the high-frequency interpolation expansion in step S3. The preset time window identifier serves as the index object for the current time window in-situ positioning and subsequent truncation calls. The correspondence of the multi-source constellation observation nodes serves as the constraint object for the reconstruction order of each satellite channel. Thus, the low-dimensional phase parameterization processing of the radio frequency reconstruction front end of this invention is completed.

[0034] Step S2: Extract the non-integer multiple phase difference components between the upper-level clock frequency and the lower-level clock frequency, combine them with the inherent timing dwell delay to generate time perturbation parameters, and perform abnormal state identification based on clock slip dispersion and radial mutation rate. Specifically, the implementation method is as follows: Step S1 has organized the dynamic flight trajectory data into basic carrier phase polynomial coefficients with preset time window identifiers and corresponding relationships between multi-source constellation observation nodes according to preset time windows, and sent them to the buffer area of ​​the radio frequency generator. However, the basic carrier phase polynomial coefficients only characterize the carrier phase evolution under ideal kinematic conditions, and have not absorbed the asynchronous slip between the upper clock frequency and the lower clock frequency, nor have they compensated for the inherent transmission dwell time of the command reaching the microwave antenna radiation end face. Therefore, step S2 continues to extract timing errors, perform abnormal state identification, and form time perturbation parameters for direct use in step S3 within the current preset time window.

[0035] S201 Non-integer Multiple Phase Difference Components and Inherent Timing Dwell Delay: After the fundamental carrier phase polynomial coefficients for the current preset time window have been delivered in step S1, the following sub-steps are executed collaboratively by the host computer and the RF generator. The host computer continues to provide dynamic flight trajectory data, preset time window identifiers, and the correspondence between observation nodes of the multi-source constellation. The RF generator initiates clock differential extraction for the window coefficient frame corresponding to the current preset time window identifier. The RF generator first reads the fundamental carrier phase polynomial coefficients of each satellite channel within the current preset time window according to the preset time window identifier. Then, using the node order within the same preset time window as an index, it ensures that the write clock frequency corresponding to the host clock frequency and the read clock frequency corresponding to the underlying clock frequency enter the same phase detection sampling sequence, latching the phase position difference between two clock edges node by node.

[0036] After the phase position difference of each node is latched, the RF generator removes the integer period portion corresponding to the integer number of underlying clock cycles, retaining only the fractional period portion less than one cycle, and converts this fractional period portion into a non-integer multiple phase difference component of the current node. The non-integer multiple phase difference components are arranged sequentially by node time within the current preset time window to form a phase difference sequence. This phase difference sequence maintains the same indexing system as the preset time window identifier and the correspondence between observation nodes in the multi-source constellation, thereby ensuring that subsequent calculations of transient phase slip rate, clock slip dispersion, and time perturbation parameters are performed on the same time reference.

[0037] Another input object for synchronous acquisition of non-integer multiple phase difference components is the inherent timing dwell time. The inherent timing dwell time refers to the fixed link dwell time from the time the host computer writes the window coefficient frame corresponding to the current preset time window to the asynchronous communication bus until the radio frequency waveform controlled by the window coefficient frame forms a transmittable transient at the microwave antenna radiating end face. The radio frequency generator obtains this quantity as follows: During the equipment calibration phase, reference coefficient frames with the same preset time window identifier are repeatedly sent, and the writing time and the response time at the microwave antenna radiating end face are recorded respectively. The stable values ​​measured multiple times under the same link are stored in the delay calibration table. During the current preset time window processing, the corresponding inherent timing dwell time is retrieved from the delay calibration table according to the current preset time window identifier and link number, and bound to the current preset time window. For example, during the high-speed dive phase of the projectile, after the host computer sends out the window coefficient frame of the current preset time window, the radio frequency generator latches the phase position difference between the written and read clocks by the phase detector, and retrieves the inherent timing dwell delay of the radio frequency link from the delay calibration table. This forms the two types of timing input objects required for subsequent analysis.

[0038] Construction of S202 clock glide dispersion and radial mutation rate: After the phase difference components that are not integer multiples of the current preset time window have formed a phase difference sequence, the RF generator uses this phase difference sequence as the starting point for processing. It performs first-order time derivatives on the phase difference components of adjacent nodes in node time order to obtain the transient phase slip rate sequence within the current preset time window. After the transient phase slip rate sequence is formed, the RF generator does not directly use the single-point peak value for judgment. Instead, it calculates the second-order central moment of the transient phase slip rate sequence relative to the sequence mean within the current preset time window and outputs the clock slip dispersion. This clock slip dispersion retains the dispersion of clock slip jitter within the current preset time window while eliminating the dominant role of occasional glitches from a single node in the overall judgment of the current preset time window.

[0039] While calculating the clock slip dispersion, the host computer, based on the dynamic flight trajectory data corresponding to the current preset time window identifier and the correspondence between the observation nodes of the multi-source constellation, constructs a unit vector in the line-of-sight direction from the missile body to the corresponding satellite node node by node. It then projects the missile body vector acceleration of each node in the dynamic flight trajectory data onto this line-of-sight direction, obtaining the radial motion acceleration sequence for each node in each satellite channel within the current preset time window. Subsequently, the host computer continues to perform time-domain differential differentiation on the radial motion acceleration sequence according to the node time sequence, obtaining the radial change rate sequence. The change result with the largest absolute value is taken from the radial change rate sequences of all satellite channels as the radial mutation rate of the current preset time window. Using the change result with the largest absolute value as the radial mutation rate ensures that the current preset time window remains sensitive to the strongest physical overload response and forms a dual-parameter discrimination basis under the same time window as the clock slip dispersion.

[0040] In one implementation, when the projectile performs a rapid roll accompanied by a sudden pitch change, the host computer reads the projectile's position, velocity, and acceleration calculation results node by node within the current preset time window. Then, combining the correspondence between the observation nodes of the multi-source constellation of the BeiDou and GPS channels, the projectile's vector acceleration is projected onto the line-of-sight direction of each satellite channel. Simultaneously, the radio frequency generator differentiates the phase difference sequence of the same preset time window to form a transient phase slip rate sequence. After both sequences completely cover the current preset time window, one side outputs the clock slip dispersion, and the other side outputs the radial change rate, and both are written back to the decision buffer corresponding to the current preset time window identifier.

[0041] S203 Mahalanobis distribution distance calculation and anomaly identification: After obtaining the clock slip dispersion and radial mutation rate for the current preset time window, the RF generator combines them into a two-dimensional state vector according to the current preset time window identifier and imports it into the Mahalanobis distance anomaly detection model. The Mahalanobis distance anomaly detection model is established using calibration samples before the experiment begins. In one embodiment, the Mahalanobis distance anomaly detection model is modeled using a two-dimensional state vector composed of clock slip dispersion and radial mutation rate. For example, 6000 normal large-scale maneuver test windows with no triggered time window truncation marks are selected first. The clock slip dispersion and radial mutation rate are calculated for each normal large-scale maneuver test window, and a 6000-row, 2-column two-dimensional sample matrix is ​​constructed according to the window order, where the first column is the clock slip dispersion and the second column is the radial mutation rate; then, abnormal sampling windows that exceed three times the absolute deviation of their respective medians are removed, and the reference mean vector and reference covariance matrix are obtained using the remaining samples. In one specific implementation, the baseline mean vector consists of 0.018 and 42.7, and the diagonal terms of the baseline covariance matrix are 0.00042 and 81.6, respectively, with the off-diagonal term being 0.137. To prevent numerical instability during the inversion of the baseline covariance matrix, a fixed calibration value of 0.000001 is superimposed on its diagonal before inversion. The obtained baseline mean vector and baseline covariance matrix are then written into the model storage area as model calibration parameters. The model is established using a parameter estimation method, and the model calibration parameters are directly obtained through statistical calculations of a normal high-maneuver test window. The Mahalanobis distance anomaly detection model pre-stores the baseline mean vector and baseline covariance matrix formed from normal high-maneuver test samples, where the baseline covariance matrix describes the cooperative fluctuation relationship between clock slip dispersion and radial mutation rate under normal conditions.

[0042] For example, the Mahalanobis distribution distance of the current preset time window can be expressed as: ; in, The preset time window is marked as The distance of the Mahalanobis distribution corresponding to the current preset time window. The state vector is composed of clock slip dispersion and radial mutation rate. This is the baseline mean vector corresponding to a normal large-scale maneuver sample. This is the baseline covariance matrix corresponding to the normal high-maneuver samples. After the Mahalanobis distance calculation is completed, the RF generator arranges the historical Mahalanobis distance sequence of the normal high-maneuver samples in ascending order and takes the 90th quantile to form a safety judgment boundary. For example, the value corresponding to the 5400th sample is the 90th quantile value corresponding to the historical Mahalanobis distance sequence of the normal high-maneuver test window. The safety judgment boundary is consistent with the definition of Mahalanobis distance used; when using the Mahalanobis distance expression with square root, the safety judgment boundary corresponds to the quantile value of the Mahalanobis distance sequence itself; when using the Mahalanobis quantity expression without square root, the safety judgment boundary corresponds to the quantile value of the Mahalanobis quantity sequence itself. The Mahalanobis distance of the current preset time window is compared with the safety judgment boundary window by window.

[0043] When the Mahalanobis distribution distance does not exceed the safety threshold, the current preset time window is marked as passed, and the fundamental carrier phase polynomial coefficients passed in step S1 continue to be stored in the coefficient buffer corresponding to the current preset time window. When the Mahalanobis distribution distance exceeds the safety threshold, the RF generator immediately triggers a polynomial time window adaptive truncation degradation action. This action first locks the fundamental carrier phase polynomial coefficients corresponding to the current preset time window according to the current preset time window identifier, and marks the fundamental carrier phase polynomial coefficients as distortion polynomial coefficients. Then, the residual register is cleared. The residual register here refers to the storage unit of the accumulated margin of the previous time window saved by the underlying hardware multiply-accumulate pipeline array to maintain the continuity of polynomial expansion of adjacent preset time windows. After clearing, the error propagation of the distortion polynomial coefficients to the next time window is cut off.

[0044] After truncation, the host computer uses kinematic extrapolation to regenerate alternative fundamental carrier phase polynomial coefficients for the current preset time window. Specifically, it reads the fundamental carrier phase and phase change slope of the last node of the previous preset time window that did not exceed the boundary, and then, combining this with the dynamic flight trajectory data of the current preset time window and the correspondence between observation nodes from multiple source constellations, extrapolates the fundamental carrier phase node sequence node by node within the current preset time window. It then refits the sequence according to the same fitting order as in step S1, forming alternative fundamental carrier phase polynomial coefficients. Simultaneously, the RF generator outputs a time window truncation marker to indicate that the fundamental carrier phase polynomial coefficients corresponding to the current preset time window in step S3 are derived from kinematic extrapolation, rather than the original window coefficient frame. For example, when the projectile encounters a severe impact and the phase detector detects an abnormal micro-vibration, if the abnormal micro-vibration does not satisfy the normal covariance relationship with the radial mutation rate calculated by the observation nodes of the multi-source constellation, then the Mahalanobis distribution distance exceeds the limit, the original fundamental carrier phase polynomial coefficients of the current preset time window are truncated, the residual register is cleared, and then the host computer continues to fit the replacement fundamental carrier phase polynomial coefficients based on the previous preset time window that did not exceed the limit and the current trajectory.

[0045] S204 Time Perturbation Parameter Generation and Subsequent Output: After the abnormal state identification result of the current preset time window has been determined, the RF generator begins to generate time perturbation parameters using non-integer multiple phase difference components and inherent timing dwell delay as inputs. For the current preset time window that has passed the state, the RF generator calculates the time offset node by node for each non-integer multiple phase difference component in the phase difference sequence, and adds it to the inherent timing dwell delay corresponding to the current preset time window to obtain the time perturbation parameters. The current preset time window... The time perturbation parameters of each node are expressed as follows: ; in, The preset time window is marked as The current preset time window The time perturbation parameters of each node This is the inherent timing dwell delay amount bound to the current preset time window. For the current preset time window Non-integer multiples of the phase difference components at each node This is the underlying clock frequency. The resulting time perturbation parameters maintain the node order within the current preset time window, sharing the same preset time window identifier and the correspondence between multi-source constellation observation nodes and the fundamental carrier phase polynomial coefficients.

[0046] For the current preset time window that triggers the polynomial time window adaptive truncation degradation action, the RF generator no longer directly generates time perturbation parameters using the phase difference sequence with abnormal fluctuations throughout the window. Instead, it regenerates the degradation time perturbation parameters according to the degradation branch. Specifically, the degradation time perturbation parameters are initialized with the non-integer multiple phase difference components of the last node of the previous unbounded preset time window, and the transient phase slip rate of the last node of the previous unbounded preset time window is used as the continuation slope. First-order time extrapolation is performed in the current preset time window according to the node order to obtain the extrapolated non-integer multiple phase difference components of each node in the current preset time window. These extrapolated non-integer multiple phase difference components are then added to the inherent timing dwell delay corresponding to the current preset time window to form the degradation time perturbation parameters. If there is no unbounded preset time window before the current preset time window, the degradation time perturbation parameters are set to the inherent timing dwell delay corresponding to the current preset time window and kept consistent throughout the window. The downgraded time perturbation parameter, along with the replacement fundamental carrier phase polynomial coefficients and the time window truncation mark, is written into the output buffer corresponding to the current preset time window. This enables step S3 to select the corresponding fundamental carrier phase polynomial coefficients according to the time window truncation mark when reading the current preset time window data, and to inject the time perturbation parameter into the high-frequency interpolation expansion processing of the underlying hardware multiply-accumulate pipeline array.

[0047] Therefore, step S2 generates non-integer multiple phase difference components, inherent timing dwell delay, clock slip dispersion, radial mutation rate, and Mahalanobis distribution distance that correspond one-to-one with the preset time window identifier within the current preset time window, and outputs a pass status or time window truncation mark according to the safety judgment limit; for the current preset time window in the pass status, the original fundamental carrier phase polynomial coefficients are retained and time perturbation parameters are generated; for the current preset time window in the out-of-bounds status, the replacement fundamental carrier phase polynomial coefficients, downgraded time perturbation parameters, and truncation results after clearing the residual register are output, thereby directly providing injectable timing compensation objects and callable coefficient selection basis for step S3.

[0048] Step S3: The RF generator receives the untrunculated fundamental carrier phase polynomial coefficients and time perturbation parameters, performs high-frequency interpolation expansion through the underlying hardware multiply-accumulate pipeline array, and reconstructs the target RF test signal. Specifically, the implementation method is as follows: Step S1 has compressed the dynamic flight trajectory data into fundamental carrier phase polynomial coefficients organized according to a preset time window. Step S2, under the same preset time window identifier, gives the time perturbation parameters, the passage status, the time window truncation mark, and the corresponding alternative fundamental carrier phase polynomial coefficients. However, these results are still parameterized descriptions to be expanded and have not yet been converted into continuous radio frequency waveforms that can be injected into the receiver of the missile-borne satellite under test. Therefore, step S3 continues to complete the time base mapping, multiply-accumulate expansion, phase reconstruction, and multi-channel synthesis inside the radio frequency generator to output a multi-channel target radio frequency test signal.

[0049] Input loading and time base unpacking of the S301 underlying hardware multiply-accumulate pipeline array: After entering the radio frequency (RF) generator within the current preset time window, the processing starts with the fundamental carrier phase polynomial coefficients, time perturbation parameters, passage status, and time window truncation marker corresponding to the preset time window identifier. The RF generator first performs in-situ selection based on the time window truncation marker. When the current preset time window is in the passage status, it calls the fundamental carrier phase polynomial coefficients issued in step S1; when the current preset time window has a time window truncation marker, it calls the alternative fundamental carrier phase polynomial coefficients output in step S2, and loads the corresponding degraded time perturbation parameters into the local register array. After selection, the RF generator establishes a channel scheduling order according to the multi-source constellation observation node correspondence retained in step S1, ensuring that each satellite channel has a unique channel slot and a unique coefficient read address within the current preset time window.

[0050] After the channel scheduling order is determined, the RF generator uses the underlying clock frequency to generate a clock timing sequence covering the entire current preset time window, and defines the time offset of each clock timing relative to the start time of the current preset time window as the interpolation timing sequence. Since the time perturbation parameters output in step S2 are stored in the node order within the preset time window, the RF generator further maps the time perturbation parameters to the interpolation timing sequence according to the node boundaries, forming a clock-level injection time sequence. The clock-level injection time sequence is formed by piecewise linear interpolation. Specifically, for all underlying clock ... Subsequently, the underlying hardware multiply-accumulate pipeline array loads the polynomial coefficients of each channel, the interpolation time sequence of each clock cycle, and the clock-level injection time sequence in a time-division multiplexing architecture, enabling the same hardware multiply-accumulator to poll and process different channels within different phase clock cycles of a single underlying clock cycle.

[0051] In one implementation, all the following steps are performed by the radio frequency (RF) generator. After receiving a preset time window, the RF generator first establishes channel slots in a predetermined order for the BeiDou channel, GPS channel, and other satellite channels. Then, it allocates the time perturbation parameters within the preset time window to the continuous beats generated by the underlying clock frequency according to the node position. Only after all beats have obtained the corresponding channel address and time reference does the underlying hardware multiply-accumulate pipeline array begin to enter the polynomial expansion stage.

[0052] High-frequency interpolation expansion and time perturbation parameter injection of S302 fundamental carrier phase polynomial coefficients: After the interpolation time series and the clock-level injection time series have been loaded, the underlying hardware multiply-accumulate pipeline array performs high-frequency interpolation expansion on a clock-by-clock basis for each channel. The current preset time window is marked as... Channel number is The time signature is At the processing point, the time offset corresponding to the interpolated time series is first added to the time perturbation corresponding to the beat-level injected time series to obtain the expanded time variable after injection. Then, the expanded time variable is substituted into the fundamental carrier phase polynomial coefficients of the current channel. To match the hardware multiply-accumulate structure, the RF generator uses Horner's rule to complete the step-by-step accumulation expansion. The transient carrier phase of the current clock cycle is obtained by the following formula: ; in, The current channel within the current preset time window is in the [number]th [period]. The transient carrier phase at each beat The expanded time variable is formed by the interpolation time series and the tick-level injection time series. to This refers to the fundamental carrier phase polynomial coefficients corresponding to the current channel, or their replacement. With this construction, the time perturbation parameters are directly injected into the polynomial evaluation process as expanded time variables, rather than having corrections added after evaluation.

[0053] The execution order of Horner's rule is fixed by the underlying hardware multiply-accumulate pipeline array. Each phase cycle first reads the highest-order coefficient of the current channel, then sequentially injects lower-order coefficients into adjacent multiply-accumulate stages until the transient carrier phase of the current cycle is output. Since the same hardware multiply-accumulator polls multiple channels in different phase cycles, the RF generator writes the intermediate accumulation result of the current cycle back to the corresponding register at the end of each channel slot, and continues reading when the same channel slot is polled again. When all multiply-accumulate stages of a cycle are completed, the final transient carrier phase of that cycle is output. Through this processing method, hundreds of channels within the current preset time window can sequentially obtain the cycle-level transient carrier phase expansion value with a limited number of logic units.

[0054] As an example of this sub-step, when the GPS channel in a certain preset time window carries a time window truncation mark, the RF generator loads the replacement fundamental carrier phase polynomial coefficients and degraded time perturbation parameters into the corresponding channel slot; when the BeiDou channel in the same preset time window is in a through state, the original fundamental carrier phase polynomial coefficients and time perturbation parameters are loaded. Subsequently, the underlying hardware multiply-accumulate pipeline array completes the Horner expansion of the two channels sequentially within different phase beats of one underlying clock cycle, and outputs the transient carrier phase of the two channels at the same underlying sampling time.

[0055] S303 Multi-channel Target RF Test Signal Reconstruction and Output: After the transient carrier phases of each channel have been generated beat by beat, the RF generator continues to send the transient carrier phases into the channel waveform synthesis chain according to the channel scheduling order. The channel waveform synthesis chain performs numerically controlled oscillation reconstruction according to the preset carrier frequency and amplitude coefficient of each channel. The carrier frequency is determined by the center frequency of the corresponding constellation and signal systems in the test task file, and the amplitude coefficient is determined by the link calibration results of the RF generator before injection. For the current preset time window, the [number]th [channel]... The first channel Transient carrier phase of each beat The in-phase components are calculated separately for each channel waveform synthesis chain. and orthogonal components ,in For the first The amplitude coefficients of each channel are calculated; then the in-phase and quadrature components are fed into a digital-to-analog converter link and up-converted to the corresponding carrier frequency to obtain the continuous carrier components of the current clock cycle for that channel. The continuous carrier components of all channels are superimposed on the same clock cycle to form a composite RF sample sequence, and the time alignment of each channel is maintained according to the correspondence of the observation nodes in the multi-source constellation. Since the transient carrier phase of each channel is calculated from the expanded time variable after injecting time perturbation parameters, the composite RF sample sequence already carries the timing compensation result corresponding to the current preset time window when superimposed across channels.

[0056] After all the cycles of the current preset time window are processed, the RF generator sends the continuously obtained composite RF sample sequence to the digital-to-analog converter link and the RF converter link to reconstruct the multi-channel target RF test signal corresponding to the current preset time window. This multi-channel target RF test signal is then written into the output buffer to await subsequent physical coupling injection. Along with the multi-channel target RF test signal, the current preset time window identifier and the time window truncation marker are also retained. The current preset time window identifier is used in step S4 to correlate the output waveform with the dynamic tracking status data of the tested missile-borne satellite receiver according to the time window. The time window truncation marker is used in step S4 to trace back the source of the waveform corresponding to the tracking anomaly in step S4—whether it is the original fundamental carrier phase polynomial coefficients or the substitute fundamental carrier phase polynomial coefficients.

[0057] In one implementation, when the projectile is under high overload test conditions, the RF generator sequentially performs transient carrier phase expansion on all satellite channels within the current preset time window, then superimposes the continuous carrier components of each channel on the same beat, and finally outputs the signal to the interface via a digital-to-analog converter link and an RF converter link. At this time, if some channels originate from the polynomial coefficients of the substitute fundamental carrier phase, the output buffer still stores the multi-channel target RF test signal and its corresponding time window truncation mark according to a unified preset time window identifier, thus ensuring that subsequent physical coupling injection and closed-loop evaluation maintain the same time window index.

[0058] After processing in step S3, the RF generator has mapped the fundamental carrier phase polynomial coefficients sent in step S1 and filtered in step S2, together with the corresponding time perturbation parameters, to a clock-level transient carrier phase. It then uses the underlying hardware multiply-accumulate pipeline array to complete the multi-channel time-division multiplexing expansion and channel superposition, forming a multi-channel target RF test signal that can be directly physically coupled and injected in step S4. At the same time, the current preset time window identifier and time window truncation mark are also retained along with the output result, so that the waveform source and anomaly handling path can be located according to the same time window when the dynamic tracking status data is collected in the future.

[0059] Step S4: Physically couple the target radio frequency test signal into the receiver of the missile-borne satellite under test, receive its output dynamic tracking status data, and perform a compatibility closed-loop evaluation based on the dynamic tracking status data. Specifically, the implementation method is as follows: Step S1 has formed the basic carrier phase polynomial coefficients organized according to the preset time window. Step S2 further forms the time perturbation parameters, pass status and time window truncation mark with the same index. Step S3 reconstructs the multi-channel target RF test signal with the preset time window mark. However, the multi-channel target RF test signal has not yet entered the actual tracking link of the tested missile-borne satellite receiver, nor has a closed-loop conclusion on the compatibility of the tested missile-borne satellite receiver been formed. Therefore, step S4 continues to complete the physical coupling injection, dynamic tracking status data recovery, time window correspondence organization and compatibility closed-loop evaluation.

[0060] Physical coupling injection and time window binding of S401 multi-channel target RF test signals: In this sub-step, the processing starts with the multi-channel target RF test signal, preset time window identifier, and time window truncation mark output in step S3. The RF generator injects the multi-channel target RF test signal corresponding to each preset time window into the receiver of the satellite under test via a physical coupling path, according to the order of the preset time window identifiers. This physical coupling path can be an RF cable coupling path or a spatial coupling path from the microwave antenna radiating end face. Regardless of the physical coupling path used, the same preset time window identifier serves as the unique time index for the injected waveform, ensuring that the receiver of the satellite under test can correspond to a unique preset time window when receiving each segment of the multi-channel target RF test signal. To maintain the traceability of subsequent closed-loop evaluation, the RF generator records the injection start time at the beginning of each preset time window and the injection end time at the end of that preset time window, and writes this time interval, along with the preset time window identifier and the time window truncation mark, into the corresponding injection sequence. The injected sequence refers to a time-domain aligned sequence with a preset time window identifier as the primary key and the injection start time and injection end time as the boundaries. It is subsequently used to map the dynamic tracking status data output by the receiver of the tested missile-borne satellite back to the corresponding preset time window.

[0061] Once the satellite receiver under test enters continuous reception mode, the multi-channel target RF test signal generated in step S3 no longer exists as a parameter sequence, but instead acts as a complete RF input on the RF front-end and baseband processing link of the satellite receiver under test. At this time, the time window truncation marker output in step S2 does not participate in the numerical calculation of the RF injection itself, but is synchronously retained along with the corresponding injection sequence. This is used to determine whether the source of the input waveform corresponding to the current anomaly is the original fundamental carrier phase polynomial coefficients or a substitute fundamental carrier phase polynomial coefficients when a loss of lock, reacquisition, or pseudorange jump occurs. Through this binding method, step S4 does not regenerate any RF object, but instead establishes a one-to-one correspondence between the waveform source and the receiver response on the existing injection link.

[0062] In one implementation, the receiver of the missile-borne satellite under test is mounted on a hardware-in-the-loop simulation platform. The radio frequency (RF) generator outputs multi-channel target RF test signals according to consecutive preset time window markers. The waveform corresponding to the current preset time window is sent to the antenna port of the receiver of the missile-borne satellite under test via an RF coupling link. At the same time, the injection start time, injection end time, and time window truncation mark of the preset time window are written into the corresponding injection sequence. Thus, any dynamic tracking status data subsequently recovered from the receiver of the missile-borne satellite under test can be directly referenced back to the corresponding preset time window according to the time point.

[0063] S402 Dynamic Tracking Status Data Collection and Windowing: After the multi-channel target RF test signal has entered the receiver of the tested missile-borne satellite, the processing chain transitions to response data retrieval. While completing phase-locked loop (PLL) and delay-locked loop (LDL) tracking, the baseband processing chip of the tested missile-borne satellite receiver continuously outputs dynamic tracking status data in reverse. This dynamic tracking status data includes at least the unlock or lock indication flags of the PLL and LLL, the loop traction convergence time, and the pseudorange jump slope during the calculation process. Step S4 first receives the aforementioned dynamic tracking status data at the receiving interface in chronological order, and appends the receiving time to each piece of dynamic tracking status data, forming a tracking status sequence arranged in chronological order. At this point, the tracking status sequence is still the original return result from the receiver side and has not yet established a pre-set time window level correspondence with the injected waveform.

[0064] After obtaining the complete tracking state sequence, step S4 calls the injection sequence formed in S401 and performs time-domain slicing of the tracking state sequence according to the injection start and end times of each preset time window. Dynamic tracking state data whose reception time falls within the injection interval of a preset time window are assigned to the window tracking record corresponding to that preset time window. If a change in dynamic tracking state data occurs at the boundary between two adjacent preset time windows, it is assigned to the corresponding preset time window according to its first reception time. After slicing, each window tracking record simultaneously contains the preset time window identifier, the time window truncation marker, and all dynamic tracking state data within that preset time window, thus forming a window evaluation record that can be directly called upon for subsequent compatibility closed-loop evaluation. A window evaluation record refers to an evaluation unit formed by splicing the waveform source information from the injection side and the dynamic tracking state data from the receiver side according to the same preset time window identifier; it is not subsequently split into independent objects.

[0065] To ensure the continuity of the closed-loop evaluation, step S4 further maintains the state continuity of the same satellite channel between adjacent preset time windows. Specifically, for channels that are already in a lost-lock or traction convergence state at the end of the previous preset time window, the lost-lock or locked indicator bits, loop traction convergence time, and pseudorange jump slope of the same channel are read again in the window tracking record of the next preset time window. This allows the receiver response to be fully tracked along the continuous time windows, rather than being interrupted after a single time window ends. The window evaluation record prepared in this way retains both the response details within a single window and the state evolution relationship across windows. As an example of this sub-step, if a phase-locked loop (PLL) has already lost-locked at the end of the first preset time window within three consecutive preset time windows of the projectile's large maneuvering phase, and a PLL relock and loop traction convergence time are recorded in the second preset time window, then step S4 writes these two segments of dynamic tracking state data into the corresponding window evaluation records respectively, and establishes a cross-window association of the same channel between the two records.

[0066] S403 Compatibility Closed-Loop Assessment and Anomaly Attribution Output: After the window evaluation record has been constructed, step S4 begins to perform a compatibility closed-loop evaluation for each preset time window. First, the unlock or lock indication flags of the phase-locked loop and delay-locked loop in the current preset time window are read to determine whether there is a loop interruption in the preset time window. If the phase-locked loop and delay-locked loop remain locked in the current preset time window, the loop traction convergence time and pseudorange jump slope corresponding to the preset time window are read to determine whether it maintains a continuous tracking state. If any loop loses lock in the current preset time window, the preset time window is initially judged as a tracking abnormal window, and the tracking continues along the adjacent preset time windows to see if it has subsequently completed re-acquisition. Therefore, step S4 decomposes the receiver's response to the current input waveform into three types of window response results: continuous tracking state, transient traction state, and tracking anomaly state. The continuous tracking state refers to the phase-locked loop and the delay-locked loop remaining locked and the pseudorange jump slope not showing a sudden break. The transient traction state refers to the loss of lock within the current preset time window followed by a recovery of lock within a subsequent window, forming a clear loop traction convergence time. The tracking anomaly state refers to the loss of lock continuously crossing the current preset time window and continuing into subsequent windows, or the pseudorange jump slope still showing a discontinuous abrupt change under the continuous lock indication.

[0067] After obtaining the window response result, step S4 correlates the window response result of the current preset time window with the time window truncation mark in the same window evaluation record. If the current preset time window has a time window truncation mark, but the window response result is still in a continuous tracking state, it indicates that the polynomial time window adaptive truncation degradation action in step S2 has isolated the upstream unstable waveform outside the input end, and the current receiver maintains normal tracking of the phase polynomial coefficients of the substitute fundamental carrier within the preset time window. This preset time window is included in the compatibility pass window. If the current preset time window does not have a time window truncation mark and an abnormal tracking state occurs, it indicates that under the condition of not triggering upstream substitution, the tested missile-borne satellite receiver itself failed to maintain stable tracking of the current multi-channel target RF test signal. The window is included in the incompatibility window. If the current preset time window has a window truncation mark and a tracking anomaly still occurs, step S4 continues to check whether the anomaly continues into the next preset time window without a window truncation mark. If the anomaly continues to exist in the next preset time window without a window truncation mark, then the next preset time window without a window truncation mark is taken as the starting point for receiver-side incompatibility attribution. If the anomaly is limited to the preset time window with a window truncation mark and disappears in the next preset time window without a window truncation mark, then the anomaly is recorded as a transitional response after the upstream instability has been isolated and is not included in the incompatibility window. Through the above determination path, step S4 distinguishes between the upstream waveform replacement action and the receiver's compatibility failure, avoiding directly attributing the anomaly input marked on the test link to a defect in the tested missile-borne satellite receiver.

[0068] After the entire test is completed, step S4 summarizes all window evaluation records according to the preset time window identifiers, and outputs the compatibility closed-loop evaluation results and anomaly attribution records. The compatibility closed-loop evaluation results are generated according to the tolerance table preset in the test task file. The tolerance table includes at least the upper limit of the allowed continuous unlock window length, the upper limit of the allowed single-window loop traction convergence time, and the upper limit of the allowed pseudo-range jump slope. After all preset time windows have been processed, step S4 compares the phase-locked loop and delayed-locked loop states, loop traction convergence time, and pseudo-range jump slope in each window evaluation record with the tolerance table. When all tracking anomaly state windows do not exceed the allowed continuous length, and the loop traction convergence time and pseudo-range jump slope of all transient traction state windows do not exceed the corresponding upper limit, a compatibility pass conclusion is output; otherwise, a compatibility fail conclusion is output, and the first preset time window that does not meet the tolerance table is marked in the anomaly attribution record. The compatibility closed-loop evaluation results are used to provide the distribution of compatible passes, incompatible windows, and transient traction recovery process of the tested missile-borne satellite receiver during the entire dynamic flight trajectory data test process. The anomaly attribution record is used to indicate the time window truncation mark status corresponding to each tracking anomaly window, the preset time window identifier of the first occurrence of the anomaly, and whether it was subsequently reacquired. As an example of this sub-step, in a certain continuous test, if the 8th preset time window has a time window truncation mark and the tested missile-borne satellite receiver remains locked, the 9th preset time window does not have a time window truncation mark but the phase-locked loop loses lock and is accompanied by a sudden change in pseudorange jump slope, and the 10th preset time window relocks and provides the loop traction convergence time, then step S4 records the 8th preset time window as a compatible pass window, the 9th preset time window as an incompatible window, and the 10th preset time window as a transient traction state window, and writes the 9th preset time window as the anomaly attribution starting point into the anomaly attribution record.

[0069] After processing in step S4, the multi-channel target RF test signal has been physically coupled and injected into the receiver of the missile-borne satellite under test. The reverse output dynamic tracking status data has also been organized into window evaluation records according to the preset time window identifiers and a corresponding relationship has been established with the time window truncation mark. On this basis, step S4 further outputs the compatibility closed-loop evaluation results and anomaly attribution records. The compatibility closed-loop evaluation results give the continuous tracking status, transient traction status and tracking anomaly status corresponding to each preset time window. The anomaly attribution records give the starting point of the incompatible window and its relationship with the upstream waveform substitution action, thereby completing the closed-loop determination of the compatibility of the receiver of the missile-borne satellite under test in this invention.

[0070] The above embodiments are merely preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A test method for the compatibility of missile-borne satellite receivers, characterized in that, Including the following steps: S1: In response to the input dynamic flight trajectory data, extract the fundamental carrier phase polynomial coefficients corresponding to the multi-source constellation observation nodes according to the host clock frequency, and send them to the radio frequency generator via the asynchronous communication bus; S2: Extract the non-integer multiple phase difference components between the upper clock frequency and the lower clock frequency, combine them with the inherent timing dwell delay to generate time perturbation parameters, and perform abnormal state identification based on clock slip dispersion and radial mutation rate; S3: The RF generator receives the untrunculated fundamental carrier phase polynomial coefficients and time perturbation parameters, and performs high-frequency interpolation expansion through the underlying hardware multiply-accumulate pipeline array to reconstruct the target RF test signal. S4: Physically couple the target radio frequency test signal into the receiver of the missile-borne satellite under test, receive the dynamic tracking status data output by it, and perform a compatibility closed-loop evaluation based on the dynamic tracking status data; In step S1, the basic carrier phase polynomial coefficients are obtained by the host computer within a preset time window based on dynamic flight trajectory data and multi-source constellation observation nodes. First, the Doppler frequency shift envelope curve is calculated according to the time sequence of the nodes. Then, the corresponding carrier phase node sequence is parametrically fitted and extracted based on the start time of the current preset time window. The coefficients are then combined with the preset time window identifier and the correspondence of the multi-source constellation observation nodes to form a window coefficient frame. In step S1, the host computer extracts the basic carrier phase polynomial coefficients by fitting a cubic or higher-order polynomial based on the correspondence between the node time offset sequence and the carrier phase node sequence, and forms a fixed transmission order according to the correspondence between the observation nodes of the multi-source constellation. Then, using the clock on the writing side as the host clock frequency, the window coefficient frame is transmitted across clocks to the radio frequency generator via the asynchronous communication bus. In step S2, the RF generator, for the window coefficient frame corresponding to the current preset time window identifier, makes the write clock corresponding to the upper clock frequency and the read clock corresponding to the lower clock frequency enter the same phase detection sampling sequence, extracts the non-integer multiple phase difference components in node order, and maps the non-integer multiple phase difference components and the inherent timing dwell delay between the instruction sent to the microwave antenna radiating end face to the same preset time window to generate time perturbation parameters. In step S2, the abnormal state identification includes: taking the first-order time derivative of the non-integer multiple phase difference components to obtain the transient phase slip rate, and calculating the second-order central moment of the transient phase slip rate within the current preset time window to obtain the clock slip dispersion. The radial motion acceleration is determined synchronously based on dynamic flight trajectory data and multi-source constellation observation nodes, and the radial mutation rate is obtained by time-domain differential calculation. The clock slip dispersion and radial mutation rate are imported into the Mahalanobis distance anomaly detection model. When the Mahalanobis distribution distance exceeds the safety judgment limit, the polynomial time window adaptive truncation degradation action is triggered, and the time window truncation mark and the replacement fundamental carrier phase polynomial coefficients are output.

2. The test method for the compatibility of a missile-borne satellite receiver according to claim 1, characterized in that, In step S3, the radio frequency generator performs in-situ selection between the fundamental carrier phase polynomial coefficients and the alternative fundamental carrier phase polynomial coefficients based on the time window truncation mark, and loads the time perturbation parameters corresponding to the selected polynomial coefficients into the underlying hardware multiply-accumulate pipeline array. The channel scheduling order is established according to the correspondence of the observation nodes of the multi-source constellation, and multiple satellite channels are processed sequentially using a time-division multiplexing architecture. When the current preset time window has a time window truncation mark, the time perturbation parameters are degraded time perturbation parameters.

3. The test method for the compatibility of a missile-borne satellite receiver according to claim 2, characterized in that, In step S3, the RF generator first generates an interpolated time sequence covering the current preset time window based on the underlying clock frequency. Then, it maps the time perturbation parameters to a beat-level injection time sequence that corresponds one-to-one with the interpolated time sequence. The beat-level injection time sequence and the fundamental carrier phase polynomial coefficients are added step by step and substituted to generate the transient carrier phase of each channel. Finally, the target RF test signal is synthesized and output.

4. The test method for the compatibility of a missile-borne satellite receiver according to claim 3, characterized in that, In step S4, the target radio frequency test signal is injected into the receiver of the missile-borne satellite under test through the physical coupling path in the order of the preset time window markings, and the corresponding injection start time and injection end time are recorded at each preset time window injection. The dynamic tracking status data is output in reverse by the baseband processing chip inside the receiver of the missile-borne satellite under test, including the unlock or lock indication flags of the phase-locked loop and the delay-locked loop, the loop traction convergence time, and the pseudorange jump slope.

5. The test method for the compatibility of a missile-borne satellite receiver according to claim 4, characterized in that, In step S4, an injection sequence is constructed based on the preset time window identifier, injection start time, injection end time, and time window truncation mark. Dynamic tracking status data whose receiving time falls into the corresponding injection interval are assigned to the corresponding preset time window to form a window evaluation record containing the preset time window identifier, time window truncation mark, and dynamic tracking status data. Then, the receiver response is divided into continuous tracking state, transient traction state, and tracking anomaly state based on each window evaluation record.

6. The test method for the compatibility of a missile-borne satellite receiver according to claim 5, characterized in that, In step S4, the compatibility closed-loop evaluation is performed according to the tolerance table preset in the test task file. The tolerance table includes at least the upper limit of the continuous unlock window length, the upper limit of the single window loop traction convergence time, and the upper limit of the pseudo-range jump slope. If none of the states corresponding to all window evaluation records exceed the tolerance table, output a compatibility pass conclusion; otherwise, output a compatibility fail conclusion and mark the first preset time window that does not meet the tolerance table in the anomaly attribution record.

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