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CN-122001495-A - Real-time simulation verification system for high-low temperature compact range darkroom satellite-ground link

CN122001495ACN 122001495 ACN122001495 ACN 122001495ACN-122001495-A

Abstract

The invention discloses a high-low temperature compact range darkroom satellite-ground link real-time simulation verification system, and belongs to the technical field of aerospace testing. The system comprises a compact range darkroom, an integrated high-low temperature control subsystem, an integrated cooperative control and link simulation subsystem, a radio frequency test subsystem and a mechanical support subsystem. The method has the core innovation that a closed temperature control cavity is integrally constructed by adopting a Polymethacrylimide (PMI) foam material with a dielectric constant close to air, electromagnetic measurement errors introduced by a traditional medium window at high and low temperatures are thoroughly eliminated, and wide-temperature-range environment simulation, phased array terminal calibration and dynamic satellite-to-ground communication link simulation are integrated deeply and synchronously through a high-precision synchronous control technology. The invention realizes the real, high-efficiency and closed-loop verification of the functions and performances of the satellite-ground communication system in an equivalent on-orbit temperature environment, remarkably improves the testing precision, the authenticity and the efficiency, and powerfully supports the development of the high-reliability spacecraft.

Inventors

  • LIU KUO

Assignees

  • 倍测通电子科技(上海)有限公司

Dates

Publication Date
20260508
Application Date
20260123

Claims (10)

  1. 1. The real-time simulation verification system for the satellite-ground link of the compact range darkroom is characterized by comprising a compact range darkroom subsystem, an integrated high-low temperature control subsystem, an integrated cooperative control and link simulation subsystem, a radio frequency test subsystem and a mechanical support and positioning subsystem; the compact range darkroom subsystem is used for providing an electromagnetic dead space environment, and the interior of the compact range darkroom subsystem comprises a reflecting surface and a feed source for generating quasi-plane waves; The integrated high-low temperature control subsystem is arranged in the compact range darkroom and comprises a closed temperature control cavity which is integrally constructed by polymethacrylimide foam materials and is used for accommodating a phased array terminal to be tested and providing a wide temperature range environment, wherein the temperature control cavity is not provided with an independent radio frequency transparent medium window, and is internally provided with a gas circulation pipeline and a distributed gas flow outlet so as to realize uniform temperature control; the integrated cooperative control and link simulation subsystem is used for synchronously controlling the temperature change of the temperature control subsystem, controlling the movement of the mechanical support and positioning subsystem and the working state of the radio frequency test subsystem, and running satellite-ground link simulation software to simulate the dynamic satellite orbit and channel characteristics; The mechanical support and positioning subsystem comprises a product turntable positioned in the temperature control cavity; the radio frequency test subsystem comprises instrument equipment for signal generation, channel simulation, link switching and data acquisition; the integrated cooperative control and link simulation subsystem ensures time sequence synchronization of temperature control, mechanical motion, link simulation and data acquisition through a high-precision clock synchronization protocol, and realizes closed loop synchronization of environment simulation and link verification.
  2. 2. The real-time simulation verification system for the high-low temperature compact range darkroom satellite-ground link according to claim 1, wherein the dielectric constant of the polymethacrylimide foam material is between 1.05 and 1.12, the heat conductivity coefficient is lower than 0.025W/(m.K), and the wall thickness of the temperature control cavity is 30mm to 200mm.
  3. 3. The real-time simulation verification system for the high-low temperature compact range darkroom satellite-ground link is characterized by further comprising a high-low temperature gas generating device, a temperature sensor array and a temperature controller, wherein the temperature sensor array comprises sensors arranged on a gas circulation pipeline and the inner wall of a temperature control cavity, and the temperature controller adjusts the high-low temperature gas generating device according to a set temperature curve and sensor feedback to enable the spatial temperature uniformity error in the temperature control cavity to be less than or equal to +/-2 ℃.
  4. 4. The real-time simulation verification system for the high-low temperature compact range darkroom satellite-ground link according to claim 1, wherein the integrated cooperative control and link simulation subsystem comprises a main control workstation, a time sequence synchronous controller and a device driving module, wherein the time sequence synchronous controller generates a unified time base signal and distributes the unified time base signal to each controlled device through hardware triggering or a network synchronous protocol to achieve synchronous precision superior to 10 nanoseconds, and satellite-ground link simulation software supports importing satellite ephemeris files and calculates Doppler frequency shift, path loss and channel attenuation parameters in real time.
  5. 5. The real-time simulation verification system of the high-low temperature compact range darkroom satellite-ground link according to claim 4, wherein the dynamic channel model integrated by the satellite-ground link simulation software supports simulation of free space loss, atmospheric attenuation, rain attenuation and multipath fading, and the channel simulator in the radio frequency test subsystem reproduces the calculated path loss, attenuation and Doppler frequency shift in a radio frequency channel according to instructions issued by the software, wherein the Doppler frequency shift simulation range is not lower than +/-500 kHz.
  6. 6. The real-time simulation verification system for the satellite-ground link of the compact range darkroom of claim 1, wherein the rotation center of the product turntable is aligned with the dead zone center generated by the reflecting surface of the subsystem of the compact range darkroom, and the product turntable supports continuous rotation and pitching of the azimuth within the range of-65 degrees to +90 degrees.
  7. 7. The real-time simulation verification system for the high-low temperature compact range darkroom satellite-ground link according to claim 1, wherein the radio frequency test subsystem comprises a vector network analyzer, a frequency spectrum analyzer, a signal source, a channel simulator and a radio frequency switch matrix, wherein the channel simulator is provided with a plurality of radio frequency channels, the attenuation adjustment range of the channel simulator is 0-60 dB, and the adjustment step size of the channel simulator is 0.1dB.
  8. 8. The real-time simulation and verification system of a high-low temperature compact range darkroom satellite-to-ground link according to claim 1, wherein the workflow of the system is as follows: step S1, presetting test scene parameters through the integrated cooperative control and link simulation subsystem; S2, synchronously starting the system, and executing temperature regulation and satellite-ground link simulation calculation in parallel; Step S3, under the dynamic temperature and link environment, the radio frequency test subsystem generates and transmits a test signal to the equipment to be tested, and collects a response signal; S4, integrating cooperative control and a link simulation subsystem to collect and correlate and analyze temperature data, motion data, link parameters and radio frequency performance data in real time; And S5, performing performance evaluation based on the analysis result and generating a test report.
  9. 9. The high and low temperature compact range darkroom satellite-to-ground link real-time simulation verification system according to any one of claims 1 to 8, wherein said polymethacrylimide foam material is a closed cell structure foam having an average cell diameter of less than 0.5mm.
  10. 10. A satellite-to-ground link real-time simulation verification method based on the system of claim 1, comprising the steps of: Setting a target temperature profile, satellite orbit parameters and communication link parameters; A synchronous starting stage, namely sending out a global synchronous trigger signal and simultaneously starting a high-low temperature environment simulation process and a satellite-ground dynamic link simulation process; In the joint test stage, in the process of temperature change or stabilization according to the profile, controlling the direction of a turntable according to the satellite motion state calculated in real time, and synchronously controlling a channel simulator to apply corresponding dynamic link damage to excite and test equipment to be tested; the data closed-loop stage is to synchronously collect environmental data, motion data, link simulation data and equipment radio frequency performance data in real time, and perform association analysis and evaluation; and in the output stage, a comprehensive test report is generated to reflect the adaptability of the device to be tested to the dynamic satellite-ground link under a specific high-low temperature environment.

Description

Real-time simulation verification system for high-low temperature compact range darkroom satellite-ground link Technical Field The invention relates to the technical field of aerospace testing and measurement, in particular to a real-time simulation verification system for a high-low temperature compact range darkroom satellite-ground link, and particularly relates to a testing system for calibrating a satellite-borne phased array terminal, testing radio frequency performance and simulating communication link functions and performance verification between an in-orbit satellite and a ground terminal, in particular to an integrated real-time simulation verification system capable of deeply fusing a compact range far-field testing technology and a satellite-ground dynamic communication link simulation technology in a wide temperature range (-70 ℃ to +125 ℃) high-low temperature environment. Background With the rapid development of low orbit satellite constellation, high flux communication load and phased array antenna technology, spacecraft payloads face increasingly stringent environmental test and radio frequency performance verification requirements in the development stage. Compact Range (Compact Range) technology has become the mainstream means of ground calibration and radio frequency performance test of satellite-borne phased array antennas by virtue of the advantages of high quality quasi-plane waves generated in a limited space, far field measurement conditions, high test efficiency, strong anti-interference capability and the like. However, conventional compact range darkroom test systems typically operate at normal temperature (about +20℃), and only perform measurements of basic parameters such as antenna pattern, gain, polarization, etc. The spacecraft can experience extreme temperature environments (for example, -70 ℃ to +125 ℃) during in-orbit operation, and the electrical performance parameters (such as amplitude, phase, gain, noise coefficient and the like) of key components such as a radiation unit, a feed network, an active chip (such as a power amplifier, a low-noise amplifier, a phase shifter and an attenuator) of the phased array antenna can change obviously with the temperature. The performance of the antenna in the real space environment cannot be accurately reflected only by testing at normal temperature, so that the calibration precision of the amplitude-phase characteristics of the phased array channel is insufficient, and the ground prediction reliability of key indexes such as beam forming, beam pointing precision, system-level communication capacity, error rate and the like are further affected. At present, aiming at high and low temperature test of a phased array antenna, the following technical schemes mainly exist: The scheme is that the phased array antenna to be measured is placed in an independent high-temperature and low-temperature incubator, and a dielectric window (usually made of low-loss radio-frequency transparent materials such as polytetrafluoroethylene or quartz glass) is formed on the wall surface of the incubator, so that electromagnetic waves are allowed to penetrate. The antenna signal is led out of the incubator through a waveguide rotary joint or a flexible radio frequency cable and is connected to a feed source or receiving equipment of an external compact range system. Such a method is described, for example, in literature study of thermal vacuum test methods for phased array antennas on board satellites. The scheme has the advantages that the structure is relatively modularized, and the existing compact range darkroom can be modified and upgraded. But it has obvious drawbacks: The dielectric window introduces errors, namely the dielectric constant of the dielectric window material can drift with temperature (typical value is more than or equal to +/-5%), and the insertion loss can also fluctuate (more than or equal to 0.3 dB). Especially in the high-frequency millimeter wave frequency bands of Ku, ka and the like, the additional phase error introduced by the method can reach more than +/-15 degrees, and the high-precision phase consistency calibration requirement within +/-5 degrees among phased array channels is seriously influenced. The temperature control efficiency is low, the traditional incubator relies on air convection or heat sink conduction, and the temperature rise and fall speed is generally low (usually lower than 3 ℃ per minute). To complete the full temperature zone cycle from-55 ℃ to +85 ℃ and achieve temperature stabilization, it often takes 4 to 6 hours. For an active phased array comprising hundreds or thousands of channels, if testing is required one by one at a plurality of characteristic temperature points, the total period will be tens of hours, which becomes the bottleneck of model development progress. The simulation is not true, the framework usually only carries out temperature control on the antenna body to be tested, and partial