Non-contact detection system and method for power-up state of satellite

Abstract

The invention relates to the technical field of satellite monitoring, in particular to a non-contact detection system and method for the power-up state of a satellite. Whether the satellite is powered on in advance in the active section or not is judged by monitoring the radio frequency signal transmitted by the satellite X-band responder through the ground antenna, and the method has the advantages of being clear, direct, reliable and non-invasive. By detecting the working radio frequency signal of the satellite key equipment, the possible false alarm problem of state signals such as a travel switch is avoided, and the key criterion of the real power supply state of the satellite is provided for a task team. As an important link of satellite state monitoring of a launching site, especially in a key stage after rocket-satellite docking, task risks caused by accidental power-on are reduced to the greatest extent.

Description

Technical Field

[0001] This disclosure relates to the field of satellite monitoring technology, and in particular to a non-contact detection system and method for satellite power-on status. Background Technology

[0002] The design of not energizing the active phase is a key strategy adopted by the satellite to avoid the harsh mechanical environment (vibration, shock) and electromagnetic interference (EMI) during the rocket's flight phase (active phase). From docking to separation, the satellite relies on the rocket's upper stage for power, while its own power system (batteries and solar panels) remains dormant. The limit switch, as the physical trigger mechanism for energizing the satellite, directly impacts the success or failure of the mission.

[0003] Limit switches need to balance high-reliability triggering (ensuring timely power-on after separation) and resistance to false triggering (avoiding abnormal power-on in the active phase); when the satellite is in a "power supply floating state" in the active phase, the upper-level power supply has been disconnected and its own power supply has not been activated, so the limit switch becomes the power-on control node.

[0004] Unstable limit switch status may be caused by the following reasons: False triggering caused by mechanical vibration and thermal deformation, such as high-frequency vibration coupling during the active phase, or random vibrations of 20–2000Hz generated during rocket flight, especially during the transonic phase, can easily induce resonance of the limit switch reeds, resulting in momentary conduction of 50–200ms. For example, a remote sensing satellite was excited by 140Hz vibration during fairing separation, causing the limit switch to be falsely triggered, leading to premature power-on and shortening the payload's lifespan. Extreme temperature variations, such as the satellite-rocket assembly experiencing alternating temperatures from -40℃ at high altitude to +60℃ under sunlight, can cause abnormal contact pressure due to the difference in thermal expansion coefficients between the aluminum alloy shell and the copper alloy contacts: insufficient contact pressure at low temperatures leads to the risk of disconnection, while overpressure at high temperatures causes adhesion, resulting in continuous conduction. Experiments show that contact resistance fluctuations reach 30–200mΩ when the temperature difference is 50℃, exceeding the design tolerance by 10 times.

[0005] Electromagnetic interference (EMI) and contact failure, electromagnetic pulse (EMP) intrusion, rocket engine ignition / separation detonation cable generate EMP with a peak value of 200V / m, which intrudes into the switch control circuit through cable coupling, triggering a latch-up effect.

[0006] The detection mechanism has inherent defects, such as the inability to capture millisecond-level transient conduction when the current is telemetryd at 1Hz, resulting in the failure to detect short-term abnormal power-on; the switch status word only provides feedback of "on / off", ignoring contact resistance and failing to identify the semi-conducting state.

[0007] The catastrophic consequences of abnormal power-up include: if the limit switch is accidentally triggered in the active phase, the battery will be activated prematurely, and the satellite will self-power itself in a vibration environment, leading to a risk of thermal runaway due to high current discharge of the battery; damage to sensitive payloads, such as optical cameras and star sensors, which are prone to lens resonance failure or circuit board solder joint fatigue failure when powered on in a vibration environment; and failure of the entire satellite mission, as the satellite will exhaust its battery power in the active phase due to the accidental triggering of the limit switch, and will be unable to deploy its solar panels after separation, ultimately resulting in failure.

[0008] In summary, there is an urgent need for a satellite power-on status detection technology solution. Summary of the Invention

[0009] To address the aforementioned issues, this disclosure provides a non-contact detection system and method for satellite power-on status. This non-contact detection method determines whether the satellite is abnormally powered on, thereby preventing prolonged abnormalities that could lead to the satellite being unable to supply power normally during satellite-launch separation.

[0010] Firstly, a non-contact detection system for the powered-on state of a satellite includes: Antenna feeder unit, radio frequency receiving unit, signal processing and decision unit, and monitoring and alarm unit; The antenna feed unit is matched with the polarization mode of the satellite X-band transmitter and is used to track and point according to the rocket's preset trajectory or the satellite's fixed position in the fairing to receive the satellite's X-band signal. The radio frequency receiving unit is used to downconvert satellite X-band signals to L-band or intermediate frequency and convert them into spectrum data; The signal processing and decision unit, based on spectrum data, is used to read the spectrum data to obtain the power value, and to issue an alarm when the power value is greater than the power threshold line; The monitoring and alarm unit is used to display the spectrum curve and power value of the target frequency point in real time, display the background noise level and power threshold line, and display alarm information.

[0011] Furthermore, the antenna feed unit employs a high-gain Cassegrain or Gregorian parabolic antenna.

[0012] Furthermore, the antenna feed unit is located at a safe distance from the launch site to avoid obstruction by the rocket's exhaust plume and other sources of interference.

[0013] Furthermore, the radio frequency receiving unit is installed behind the antenna feed of the antenna feed unit to reduce feed line loss.

[0014] Further alerts include: Level 1 alarm: When the signal briefly touches the power threshold, the yellow light on the interface flashes and the alarm is logged. Level 2 alarm: When the signal continuously exceeds the power threshold and reaches the time threshold, the red light on the interface will remain on, a high-decibel audible and visual alarm will be issued, and an alarm window will automatically pop up.

[0015] Furthermore, the background noise level includes recording the background noise level at the target frequency when it is confirmed that the satellite should be in a power-off state.

[0016] Secondly, a non-contact detection method for the powered-on state of a satellite includes: The ground antenna is matched with the polarization mode of the satellite X-band transmitter, and the satellite is tracked and pointed according to the rocket's preset trajectory or the satellite's fixed position in the fairing to receive the satellite's X-band signal. Downconvert satellite X-band signals to L-band or intermediate frequency and convert them into spectrum data; Read spectrum data to obtain power values, and issue an alarm when the power value exceeds the power threshold line; Based on spectrum data, the system displays the spectrum curve and power value of the target frequency point in real time, as well as the background noise level and power threshold line, and alarm information.

[0017] Furthermore, if a radio frequency signal higher than the power threshold is continuously detected on the target frequency during the expected power outage period of the satellite, the signal presence reaches the time threshold, and the frequency characteristics of the signal are consistent with the satellite's designed X-band downlink frequency, it is determined that the satellite has been unexpectedly powered on.

[0018] Further alerts include: Level 1 alarm: When the signal briefly touches the power threshold, the yellow light on the interface flashes and the alarm is logged. Level 2 alarm: When the signal continuously exceeds the power threshold and reaches the time threshold, the red light on the interface will remain on, a high-decibel audible and visual alarm will be issued, and an alarm window will automatically pop up.

[0019] Furthermore, the background noise level includes recording the background noise level at the target frequency when it is confirmed that the satellite should be in a power-off state.

[0020] This disclosure includes at least the following beneficial effects: This disclosure utilizes ground-based antennas to monitor radio frequency signals emitted by the satellite's X-band transponder to determine whether the satellite has prematurely powered on during the active phase. It is characterized by its clear, direct, reliable, and non-intrusive nature. By detecting the radio frequency signals of critical satellite equipment, it bypasses the potential false alarms associated with status signals such as limit switches, providing the mission team with crucial evidence of the satellite's true power status. As a vital component of satellite status monitoring at the launch site, especially in the critical phase after rocket-satellite docking, this method minimizes mission risks caused by unintended power-on.

[0021] Other features and advantages of this disclosure will be set forth in the following description and will be apparent in part from the description or may be learned by practicing the disclosure. The objects and other advantages of this disclosure may be realized and obtained by means of the structures pointed out in the description and the accompanying drawings. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments of this disclosure or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this disclosure. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1 This is a schematic diagram of the detection system architecture according to an embodiment of the present disclosure; Figure 2 This is a schematic diagram of the detection method flow according to an embodiment of the present disclosure. Detailed Implementation

[0024] To make the objectives, technical solutions, and advantages of the embodiments of this disclosure clearer, the technical solutions of the embodiments of this disclosure will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this disclosure, and not all embodiments. Based on the embodiments of this disclosure, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this disclosure.

[0025] like Figure 1 As shown, a non-contact detection system for the powered-on state of a satellite includes: Antenna feeder unit 101, radio frequency receiving unit 102, signal processing and decision unit 103, and monitoring and alarm unit 104; The antenna feed unit 101 is matched with the polarization mode of the satellite X-band transmitter and is used to track and point according to the preset trajectory of the rocket or the fixed position of the satellite in the fairing to receive the satellite X-band. The radio frequency receiving unit 102 is used to downconvert satellite X-band signals to L-band or intermediate frequency and convert them into spectrum data; The signal processing and decision unit 103 is used to read spectrum data to obtain power values ​​and to issue an alarm when the power value is greater than the power threshold line. The monitoring and alarm unit 104, based on spectrum data, is used to display the spectrum curve and power value of the target frequency point in real time, display the background noise level and power threshold line, and display alarm information.

[0026] The specific implementation details are as follows: The Relationship Between Satellite Power-On Status and Transponder Operation: The satellite's X-band transponder (or data transmitter) is one of its main radio frequency (RF) transmitting devices. This device requires the satellite's primary power supply to operate. Regardless of whether the transponder is in command reception standby, self-test, or normal transmission mode, its transmitter components (especially the local oscillator and excitation stage) typically require a warm-up period after power-on and may generate detectable RF leakage or beacon signals (even without a formal data stream). Therefore, detecting a specific RF signal (even if weak or unmodulated) on the satellite's X-band downlink frequency is direct physical evidence that the satellite's primary power system has been powered on.

[0027] Limitations of Limit Switch Detection: Limit switches are mechanical / electrical switches installed on the docking surface between the rocket and the satellite, used to detect separation. "Status detection anomalies" may include switch malfunctions, wiring faults, signal acquisition and processing unit malfunctions, or most critically—accidental triggering of the switch (misjudging separation) when separation has not actually occurred (e.g., vibration, impact, installation errors). Limit switch signals are status indication signals, and their accuracy depends on the reliability of the hardware and signal link. They do not directly reflect the actual power status inside the satellite.

[0028] The directness of radio frequency signal detection: The ground antenna directly receives the physical electromagnetic wave signal generated by the satellite transponder transmitter. The presence or absence of this signal is a direct and objective reflection of the satellite power system status and the transponder transmitter hardware status, independent of the satellite's internal switching signals or command logic. It bypasses all possible links that could lead to false alarms about the limit switch status (switch body, cables, rocket / spacecraft signal processing unit).

[0029] Main objective: During the rocket's active flight phase and pre-launch preparation phase, monitor in real time the presence of radio frequency signals on the satellite's X-band downlink frequency using passive detection methods, thereby providing a direct, reliable, and independent criterion for determining whether the satellite has been accidentally powered on.

[0030] Secondary objective: To record signal characteristics (frequency, power, bandwidth, modulation) to provide data support for fault analysis.

[0031] The entire system consists of an antenna feeder unit, an RF receiving unit, a signal processing and decision unit, and a monitoring and alarm unit.

[0032] Antenna unit: Antenna type: High-gain Cassegrain or Gregorian parabolic antenna.

[0033] Antenna aperture: ≥ 2.4 meters (determined based on link budget to ensure reception of weak signals).

[0034] Polarization: Matches the polarization of the satellite's X-band transmitter (usually right-hand circular polarization - RHCP).

[0035] Servo system: Equipped with program tracking function, it can perform high-precision pointing and maintaining according to the rocket's preset trajectory or the satellite's fixed position inside the fairing.

[0036] Deployment location: Located outside the safe distance of the launch site, avoiding obstruction from the rocket's exhaust plume and major sources of interference, with good visibility.

[0037] Radio frequency receiving unit: Low-noise amplifier (LNA): Location: Directly mounted behind the antenna feed to minimize feed line loss. Noise temperature: ≤ 50K. Gain: ≥ 40 dB.

[0038] Downconverter: Downconverts X-band (e.g., 8.025-8.4 GHz) signals to L-band or intermediate frequency (e.g., 70 MHz or 1.4 GHz) for easy coaxial cable transmission and subsequent equipment processing.

[0039] Core receiving equipment (choose one or a combination): Option A (High Sensitivity): Spectrum Analyzer Resolution bandwidth (RBW): Adjustable, with a minimum setting of 1 Hz or 10 Hz for detecting pure carrier waves.

[0040] Video bandwidth (VBW): ≤ RBW, used for smooth display.

[0041] Tracking function: Supports multiple scan averaging to reduce noise fluctuations.

[0042] Max Hold function: Used to capture transient signals.

[0043] Option B (High Integration): Dedicated Monitoring Receiver It has multiple built-in preset channels and can store satellite downlink frequencies.

[0044] Integrated power detection and simple demodulation functions.

[0045] Provides GPIB, LAN, or serial ports for remote control and data output.

[0046] Feeders and connectors: All use low-loss, phase-stable RF cables (such as the LL series), with secure interfaces and moisture-proof treatment.

[0047] Signal processing and decision unit: Hardware: Industrial control computer (ICC).

[0048] Device control: Remotely control the spectrum analyzer / receiver via GPIB / USB / LAN, and set parameters such as center frequency, span, and RBW.

[0049] Data Acquisition: Read spectrum data or channel power values ​​at a rate of ≥1 Hz.

[0050] Signal processing algorithms: background noise baseline calculation; real-time detection; persistence and consistency judgment (preventing false alarms); data logging; Monitoring and alarm unit: Monitoring positions: Independent monitoring positions will be set up in the launch control hall and satellite control center.

[0051] Visual interface: The spectrum curve and power value of the target frequency point are displayed in real time.

[0052] Displays background noise level and alarm threshold lines.

[0053] A large red / green status indicator light.

[0054] Alarm methods: Level 1 Alarm (Prompt): The signal briefly touches the threshold → the yellow light on the interface flashes and is logged.

[0055] Level 2 Alarm (Confirmed): The signal continuously and stably exceeds the threshold → the red light on the interface stays on, a high-decibel audible and visual alarm is issued, and an alarm window automatically pops up.

[0056] Send alarm information to the mission command system.

[0057] Link budget (critical computation): Ensure the system can detect even the weakest signals (such as transponder standby leakage).

[0058] Experimental and verification process: The experiment was divided into three stages, from easy to difficult, to comprehensively verify the effectiveness of the system.

[0059] Phase 1: Laboratory Validation (Satellite Electrical Testing Room) Objective: To verify that the monitoring system can correctly identify the power-on status of the satellite transponder.

[0060] Set up the test environment: Connect the satellite transponder's radio frequency output to the monitoring system via an attenuator (simulating space loss).

[0061] Measure the background noise: Record the background noise of the monitoring system while the transponder is powered off.

[0062] Baseline test: Power on the transponder, but do not send telemetry signals (carrier mode only). Record the signal power and frequency detected by the monitoring system.

[0063] By changing the attenuation value and simulating different distances, the detection threshold of the system was tested.

[0064] Characteristic test: Enable the transponder to function normally (with modulation). Verify that the system can distinguish between the modulated signal and the pure carrier wave.

[0065] Decision logic test: Simulate signal interruption and fluctuation to test the reliability of alarm triggering and recovery logic.

[0066] Phase Two: Static Testing at the Launch Site (Rocket / Satellite on the Launch Pad) Objective: To verify the system performance and establish a detection baseline under real electromagnetic conditions.

[0067] System deployment: The monitoring antennas are installed at the designed locations, precisely pointing towards the satellite inside the fairing.

[0068] Background noise measurement: With the satellite confirmed to be powered off, a full scan of the X-band is performed to plot the electromagnetic environment spectrum of the launch site and identify known interference sources. The noise level near the satellite's downlink frequency is accurately measured and set as the decision baseline.

[0069] End-to-end functional test: With the approval of the chief engineer of the mission, remotely control the satellite to power it once (or power the transponder only once) within a very short time.

[0070] Verify that the monitoring system can immediately and accurately capture signals and trigger alarms. Power off the satellite and verify that the alarms are cleared.

[0071] Anti-interference test: During the test, other radars and radio equipment at the launch site were turned on to observe whether they interfered with the monitoring system, and the filtering and decision algorithms were optimized.

[0072] Phase Three: Dynamic Simulation Testing (Joint Training or Flight Simulation) Objective: To simulate the most realistic conditions of the active segment and verify the system's performance under vibration and Doppler effects.

[0073] Simulated flight signal: A portable X-band signal source is placed inside the fairing to simulate a satellite transponder.

[0074] Simulated anomaly: The commander randomly issues the command "simulates the accidental triggering of the limit switch".

[0075] System Response: The monitoring system operator should be unaware of the incident. When the signal source is remotely activated, the monitoring system should generate a correct alarm within a specified time (e.g., 10 seconds).

[0076] Doppler effect verification: If the signal source can simulate frequency changes, a simple Doppler frequency shift can be added to test the system's ability to track the frequency (usually, the relative motion is slow in the early stage of rocket launch, and the Doppler frequency shift is within the RBW bandwidth, so the impact is small).

[0077] Task execution process: Ground station preparation: While the rocket / satellite assembly is on the launch tower or in the technical building, precisely point the ground antenna at the satellite (calculated based on the satellite's position inside the rocket fairing and the antenna's mounting position). Set the receiving equipment parameters (center frequency = satellite X-band downlink frequency, bandwidth sufficient to cover the signal).

[0078] Background noise measurement: Record the background noise level at the target frequency point when it is confirmed that the satellite should be in a power-off state (confirmed by limit switch status or other reliable means).

[0079] Continuous monitoring: During the docking of the rocket and satellite, especially before and after any operation that may affect the limit switches (such as shaking tests, plugging and unplugging cables), and throughout the pre-launch phase, continuously monitor the target frequency.

[0080] Signal detection and analysis: Spectrum Analysis: Observe the spectrum analyzer display. Look for narrowband signal peaks that suddenly appear or are significantly higher than the background noise near the satellite's X-band downlink frequency.

[0081] Power measurement: Measure the power at the target frequency using a power meter and compare it with the background noise.

[0082] Feature identification: If the signal is modulated (such as residual telemetry frames or beacon tones), attempt demodulation to confirm that the signal is indeed coming from the satellite transponder and not from an interference source.

[0083] Judgment logic: If, during the period when the satellite is expected to be powered down (before the start of the active phase and during flight), a radio frequency signal significantly higher than the background noise (e.g., exceeding the noise floor by 3-10 dB) is continuously detected at the target frequency, and this signal is stable (not a transient pulse); the frequency characteristics of this signal are consistent with the satellite's designed X-band downlink frequency; and if the satellite's identification information (such as beacon codes and partial telemetry frames) can also be demodulated, then it can be determined that the satellite has been unexpectedly powered on.

[0084] Alarms and Handling: Once it is determined that the satellite has been powered on prematurely, an alarm will be triggered immediately. Notify the launch control center and satellite control center. The satellite control center should attempt to send an emergency power-off command (if the satellite command link is established and available). The launch control center and mission team need to assess the risks: premature power-on could deplete the satellite's batteries, cause equipment to overheat, or damage it in harsh conditions during the active phase. This could lead to launch delays or the need for other contingency measures.

[0085] After separation from the launch vehicle: The satellite is powered on normally, the detected signal is as expected, and the system mission ends.

[0086] Recording and Reporting: Record in detail the time, frequency, power, duration, spectrum, etc. of the detected signal, and generate a report.

[0087] If strong external interference causes false alarms, the solution is to use a comprehensive judgment based on "duration + signal stability + spectrum shape" rather than a single power threshold.

[0088] If the signal is too weak to be detected, the solution is to ensure sufficient link budget and fully verify sensitivity in laboratory and static tests.

[0089] In the event of a ground equipment failure, the following measures should be taken: Adopt a dual-system hot backup working mode, and perform AND logic judgment on the output signals to further reduce the risk of false alarms and missed alarms.

[0090] The technical advantages of this disclosure are as follows: Direct physical evidence detects the physical signals generated by the actual operation of the satellite's internal equipment, and is the most direct reflection of the power supply status, unaffected by false alarms from status signals such as limit switches.

[0091] It is passive and non-intrusive, requiring no commands or signals to be sent to the satellite. It is a completely passive receiver and has no impact on the satellite.

[0092] It has strong real-time performance, enabling near real-time (second-level) monitoring and alarms.

[0093] It boasts high reliability, is based on physical phenomena, and its principle is simple and reliable. False alarms mainly originate from strong radio frequency interference, which can be effectively eliminated through methods such as frequency accuracy, signal stability, and feature recognition.

[0094] It covers key risk points, especially the critical period after rocket-satellite docking and before separation, during which the travel switch status may be abnormal.

[0095] It is highly versatile and applicable to the vast majority of satellites equipped with X-band (or similar frequency band) transmitters.

[0096] Regarding signal strength, with the satellite inside the fairing and the transponder potentially in low-power standby or self-test mode, the signal may be very weak. The following are required: a high-gain antenna (large enough), an extremely low-noise receiver link (high-quality LNA), precise antenna pointing towards the satellite's position within the fairing, and a good electromagnetic environment (away from strong interference sources). Regarding background interference, the launch site environment may contain interference from other radio frequency equipment. The following are required: accurate knowledge of the satellite's downlink frequency and setting up narrowband monitoring, analysis of signal characteristics (stability, spectral shape), (ideally) establishing a background noise baseline when the satellite is powered off, and using spatial isolation or filters to suppress out-of-band interference. Regarding transponder operating modes, the default behavior of the transponder after power-on needs to be clearly understood: whether it immediately generates a carrier or beacon, the transmit power, and whether there is a warm-up time. This is crucial for setting detection thresholds and determining latency. This characteristic should be verified during the satellite testing phase. Regarding antenna pointing and coverage, during active-phase flight, if in-flight monitoring is required, the ground antenna needs high dynamic tracking capability (on-the-go antenna or large tracking station). This is relatively easy during the pre-launch tower setup phase. Regarding the setting of judgment thresholds, it is necessary to scientifically set the power threshold and duration threshold for signal detection based on the measured background noise and the estimated satellite signal strength, balancing the risks of missed and false alarms. Combined with other methods: This method provides the most direct physical evidence, but it can be combined with other information to enhance the judgment: the status of the onboard limit switches (although they may be abnormal, they serve as a reference), satellite telemetry (if the satellite-rocket electrical interface supports this and the satellite is partially powered on, it may transmit voltage and current data), and other passive monitoring (such as infrared thermography to check if the satellite is overheating).

[0097] like Figure 2 As shown, a non-contact detection method for satellite power-on status includes: S201 matches the polarization of the ground antenna with that of the satellite X-band transmitter, and tracks and points the satellite according to the rocket's preset trajectory or the satellite's fixed position in the fairing to receive the satellite's X-band signal. S202 downconverts the satellite X-band signal to L-band or intermediate frequency and converts it into spectrum data; S203: Read spectrum data to obtain power value, and issue an alarm when the power value is greater than the power threshold line; S204, based on spectrum data, displays the spectrum curve and power value of the target frequency point in real time, displays the background noise level and power threshold line, and displays alarm information.

[0098] Monitoring the radio frequency (RF) signals emitted by the satellite's X-band transponder using ground antennas to determine whether the satellite has prematurely powered on during the active phase is a clear, direct, reliable, and non-intrusive effective technical solution. By detecting the physical byproducts (RF signals) of critical satellite equipment operation, it bypasses the false alarm problems that may arise from status signals such as limit switches, providing the mission team with crucial evidence of the satellite's true power status. Successful implementation hinges on ensuring the ground receiving system possesses sufficient sensitivity, anti-interference capability, and accurate pointing capability, as well as a thorough understanding of the RF characteristics of the satellite transponder after power-on. This solution should be a vital component of satellite status monitoring at the launch site, especially during the critical phase after rocket-satellite docking, to minimize mission risks caused by unintended power-on.

[0099] A comparative analysis of the core advantages of the ground antenna detection satellite transponder solution compared to the fixed limit switch solution, based on engineering practice data and technical principles: The core advantages are compared in Table 1. Table 1

[0100] The irreplaceable advantages of ground antenna detection solutions: Completely avoid physical failure chains: The inherent defects of the limit switch solution, even when using a magnetic latching relay + AuPd contacts, cannot be 100% eliminated: reed resonant response caused by high-frequency vibration (>3000Hz); control circuit latch-up caused by EMP; and material venting contamination of contacts under thermal vacuum environment.

[0101] Breakthrough in antenna design: It directly detects the satellite's power-on results (transponder transmission signals), completely bypassing the switching process and eliminating mechanical / material failure at its source.

[0102] No blind spot monitoring throughout the entire flight phase: The key scenarios covered are shown in Table 2. Table 2

[0103] Multi-target concurrent monitoring capability: The advantage of a single rocket launching multiple satellites is that the antenna solution can simultaneously locate multiple satellites (distinguished by frequency division / code division); the limit switch solution requires adding an independent detection circuit for each satellite (increasing cost by 50%).

[0104] High-fidelity fault reproduction: The pain points of limit switch solutions are difficult to reproduce in ground tests: vibration, heat, and EMP multi-field coupling environment of the rocket's active section; contact separation characteristics under microgravity in space.

[0105] Antenna solution advantages: Directly uses real on-orbit signals for verification, eliminating the need to simulate the physical environment (reducing verification costs by 90%).

[0106] Although the present disclosure has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present disclosure.

Claims

1. A non-contact detection system for the powered-on state of a satellite, characterized in that, include: Antenna feeder unit, radio frequency receiving unit, signal processing and decision unit, and monitoring and alarm unit; The antenna feed unit is matched with the polarization mode of the satellite X-band transmitter and is used to track and point according to the rocket's preset trajectory or the satellite's fixed position in the fairing to receive the satellite's X-band signal. The radio frequency receiving unit is used to downconvert satellite X-band signals to L-band or intermediate frequency and convert them into spectrum data; The signal processing and decision unit is used to read spectrum data to obtain power values ​​and to issue an alarm when the power value is greater than the power threshold line. The monitoring and alarm unit, based on spectrum data, is used to display the spectrum curve and power value of the target frequency point in real time, as well as the background noise level and power threshold line, and alarm information.

2. The non-contact detection system for satellite power-on status according to claim 1, characterized in that, The antenna feed unit uses a high-gain Cassegrain or Gregorian parabolic antenna.

3. The non-contact detection system for satellite power-on status according to claim 1, characterized in that, The antenna feed unit is located at a safe distance from the launch site to avoid obstruction by the rocket's exhaust plume and other sources of interference.

4. The non-contact detection system for satellite power-on status according to claim 1, characterized in that, The radio frequency receiving unit is installed behind the antenna feed of the antenna feed unit to reduce feed line loss.

5. A non-contact detection system for satellite power-on status according to claim 1, characterized in that, Alarms include: Level 1 alarm: When the signal briefly touches the power threshold, the yellow light on the interface flashes and the alarm is logged. Level 2 alarm: When the signal continuously exceeds the power threshold and reaches the time threshold, the red light on the interface will remain on, a high-decibel audible and visual alarm will be issued, and an alarm window will automatically pop up.

6. The non-contact detection system for satellite power-on status according to claim 1, characterized in that, Background noise level, including: recording the background noise level at the target frequency when it is confirmed that the satellite should be in a power-off state.

7. A non-contact detection method for the powered-on state of a satellite, characterized in that, include: The ground antenna is matched with the polarization mode of the satellite X-band transmitter, and the satellite is tracked and pointed according to the rocket's preset trajectory or the satellite's fixed position in the fairing to receive the satellite's X-band signal. Downconvert satellite X-band signals to L-band or intermediate frequency and convert them into spectrum data; Read spectrum data to obtain power values, and issue an alarm when the power value exceeds the power threshold line; Based on spectrum data, the system displays the spectrum curve and power value of the target frequency point in real time, as well as the background noise level and power threshold line, and alarm information.

8. A non-contact detection method for satellite power-on status according to claim 7, characterized in that, If, during the expected power outage period of the satellite, a radio frequency signal higher than the power threshold is continuously detected at the target frequency, the signal presence reaches the time threshold, and the frequency characteristics of the signal are consistent with the satellite's designed X-band downlink frequency, it is determined that the satellite has been unexpectedly powered on.

9. A non-contact detection method for satellite power-on status according to claim 7, characterized in that, Alarms include: Level 1 alarm: When the signal briefly touches the power threshold, the yellow light on the interface flashes and the alarm is logged. Level 2 alarm: When the signal continuously exceeds the power threshold and reaches the time threshold, the red light on the interface will remain on, a high-decibel audible and visual alarm will be issued, and an alarm window will automatically pop up.

10. A non-contact detection method for satellite power-on status according to claim 7, characterized in that, Background noise level, including: recording the background noise level at the target frequency when it is confirmed that the satellite should be in a power-off state.

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