Out-of-cabin antenna mechanism testing device under satellite vacuum thermal environment

Abstract

The application provides a kind of satellite vacuum thermal environment outside cabin antenna mechanism testing device, comprising: on-board integrated control unit, antenna mechanism driver, in-cabin on-board low-frequency cable, thermal vacuum switching cable, vacuum tank flange and driving mechanism simulator;The on-board integrated control unit is connected with antenna mechanism driver, the antenna mechanism driver is connected with the interface inside the vacuum tank flange by in-cabin on-board low-frequency cable and thermal vacuum switching cable, the interface outside the vacuum tank flange is connected with driving mechanism simulator by thermal vacuum switching cable.The application introduces the on-board antenna driving signal to the vacuum tank flange through the tank thermal vacuum switching cable, and finally the driving signal is transmitted to the antenna mechanism simulator by the tank thermal vacuum switching cable and the flange interface outside the tank, which ensures the reliable and effective transmission of the two antenna driving and telemetry signals.

Description

Technical Field

[0001] This invention relates to the field of testing satellite external antenna rotation mechanisms, specifically to a testing device for external antenna mechanisms under satellite vacuum thermal conditions. Background Technology

[0002] Vacuum thermal testing is an essential reliability environmental test before satellite launch, during which the satellite is placed inside a sealed vacuum chamber. To verify the function and performance of the onboard rotation mechanism actuator, the rotation drive signal needs to be routed outside the vacuum chamber to connect to a simulator for rotation testing.

[0003] In the vacuum thermal test, considering that the antenna's two-dimensional mechanism has already undergone a separate thermal vacuum test, and that the data transmission and relay antennas cannot be unloaded by gravity inside the vacuum chamber, the external antenna rotation mechanism will not participate in the overall satellite thermal test. However, the functional and performance testing of the antenna mechanism's actuator under vacuum thermal conditions is inseparable from the system's integrated operational testing. System testing requires assessing the antenna pointing angle calculation and actual drive execution status. Therefore, in the satellite vacuum thermal test environment, the antenna drive signal needs to be transferred out of the chamber via an adapter for rotation testing.

[0004] The following are the literature and patent technologies most similar to this achievement, based on a review:

[0005] 1) Chinese patent document CN107515410A discloses an algorithm for a data transmission antenna to reverse track a ground station and calculate the ground station the antenna is pointing to. The latitude and longitude of the ground station are dynamically displayed in real-time on monitoring software. The calculated result is then compared with the latitude and longitude data of the ground station pre-loaded into the onboard software, allowing for real-time and continuous dynamic verification of the correctness of the data transmission antenna's reverse tracking of the ground station. This primarily focuses on the software-based pointing calculation of the data transmission antenna and does not involve the antenna mechanism testing method under thermal vacuum as described in this work.

[0006] 2) Research on the pointing mechanism system technology of Gaofen-5 satellite data transmission antenna (Shanghai Aerospace, Vol. 36, 2019 Supplement). This paper mainly studies the system design of the pointing mechanism of Gaofen-5 satellite data transmission antenna. It introduces the hardware design, software design and temperature control design of the pointing mechanism from the system level. It does not involve the antenna mechanism test device under satellite vacuum thermal environment of this result.

[0007] 3) In Chinese patent document CN107167821A, a high-precision satellite relay antenna tracking function test system and its test method are disclosed. The system includes an angular error controller for installing angular error control software, controlling the parameter settings of the signal source, signal generator attenuation box, and vector network analyzer through the network, recording the parameter values ​​of each device, and performing calculations, etc., but does not involve the connection test of the antenna mechanism under the whole satellite thermal vacuum environment. Summary of the Invention

[0008] To address the shortcomings of existing technologies, the purpose of this invention is to provide a testing device for an external antenna mechanism under satellite vacuum thermal conditions.

[0009] According to the present invention, a test device for an external antenna mechanism under a satellite vacuum thermal environment includes: an on-board integrated control unit, an antenna mechanism driver, an internal on-board low-frequency cable, a thermal vacuum adapter cable, a vacuum tank flange, and an antenna mechanism simulator; the on-board integrated control unit is connected to the antenna mechanism driver, the antenna mechanism driver is connected to the interface inside the vacuum tank flange through the internal on-board low-frequency cable and the thermal vacuum adapter cable, and the interface outside the vacuum tank flange is connected to the antenna mechanism simulator through the thermal vacuum adapter cable.

[0010] Preferably, the on-board integrated control unit receives data from the satellite, including: ephemeris, satellite attitude, GPS data, time, and direct-injection pointing data packets; the on-board integrated control unit calculates the pointing information required for antenna driving and outputs control commands and two-dimensional angle information to the antenna mechanism driver.

[0011] Preferably, the antenna mechanism driver receives control commands from the on-board integrated control unit to rotate the two-dimensional pointing mechanism of the antenna, performs real-time telemetry monitoring of the position of the two-dimensional pointing mechanism, and returns the results to the on-board integrated control unit.

[0012] Preferably, the in-cabin on-board low-frequency cable is used for the transmission of antenna mechanism driver drive and telemetry signals; to meet the signal connection requirements of the antenna mechanism driver, the cable end connector of the in-cabin on-board low-frequency cable and the antenna mechanism driver is model J6W-78D02K1NMB, and the cable output end connector is model J36A-26ZKL and J14A-26ZKL.

[0013] Preferably, the thermal vacuum adapter cable includes an internal adapter cable and an external adapter cable. The connector for the internal adapter cable to the onboard low-frequency cable is model J36A-26ZJL, and the connector for the external adapter cable to the vacuum tank flange is model Y27-2255TK1LW. The connector for the external adapter cable to the mechanism simulator is model J36A-26TK, and the connector for the external adapter cable to the vacuum tank flange is model Y27III-2255TK1L.

[0014] Preferably, the antenna mechanism simulator is used to receive the drive signal output by the antenna driver after being transferred inside and outside the tank, to simulate the mechanical rotation of the on-board data transmission or relay antenna, and at the same time return the position telemetry signal of the data transmission or relay antenna to the on-board antenna mechanism driver.

[0015] Preferably, the vacuum tank flange is used for connecting the internal and external adapter cables of the vacuum tank. The vacuum tank flange is numbered C1 to C14. The internal adapter cable connects to the vacuum tank flange numbered C8. The connector model of the C8 vacuum tank flange is Y27-2255ZJB4H.

[0016] Preferably, the thermal vacuum adapter cable is a twisted-pair shielded cable.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] 1. This invention introduces the on-board antenna drive signal to the vacuum tank flange through an internal thermal vacuum adapter cable, and finally transmits the drive signal to the antenna mechanism simulator through the external thermal vacuum adapter cable and flange interface, ensuring reliable and effective transmission of the two antenna drive and telemetry signals.

[0019] 2. The device and testing method of the present invention have been applied in the vacuum thermal test of satellite models. Through this testing method, firstly, the problem of connecting the inside and outside of the vacuum tank of the antenna mechanism drive signal is solved; secondly, the problem of simulating the rotation mechanism of the antenna mechanism driver is solved; and thirdly, the test connection inside and outside the vacuum tank is flexible. Attached Figure Description

[0020] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0021] Figure 1 This is a schematic diagram of the test device for the external antenna mechanism under satellite vacuum thermal environment according to an embodiment of the present invention.

[0022] Figure 2 This is a schematic diagram illustrating the working principle of the antenna mechanism simulator of the present invention.

[0023] Figure 3This is a diagram showing the connection relationship between the antenna mechanism driver and the antenna mechanism simulator of the present invention. Detailed Implementation

[0024] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0025] This invention discloses a testing device for an external antenna mechanism under satellite vacuum thermal environment, referring to... Figure 1 It includes: an on-board integrated control unit, an antenna mechanism driver, an in-cabin on-board low-frequency cable, a thermal vacuum adapter cable, a vacuum tank flange, and an antenna mechanism simulator; the on-board integrated control unit is connected to the antenna mechanism driver, the antenna mechanism driver is connected to the interface inside the vacuum tank flange through the in-cabin on-board low-frequency cable and the thermal vacuum adapter cable, and the interface outside the vacuum tank flange is connected to the antenna mechanism simulator through the thermal vacuum adapter cable.

[0026] The on-board integrated control unit comprises a primary unit and a backup unit, operating at 28V. It enables information exchange between the subsystems and the entire satellite, and its specific functions include telemetry and remote control processing, command power supply, bus communication, system work packet processing, program control, and thermal management of external mechanisms. In this invention's device, the on-board integrated control unit receives data from the satellite, including: ephemeris, satellite attitude, GPS data, time, and directly injected pointing data packets. The on-board integrated control unit calculates the pointing information required for antenna drive and outputs control commands and two-dimensional angle information to the antenna mechanism driver.

[0027] Antenna mechanism driver: Includes main unit and backup unit, operating voltage 28V, receives speed information and other control commands from the on-board integrated control unit, realizes the rotation of the antenna's two-dimensional pointing mechanism, performs real-time telemetry monitoring of the position of the two-dimensional pointing mechanism, and returns the data to the on-board integrated control unit.

[0028] In-cabin on-board low-frequency cable: There are two bundles, each about 2.5m long, used for antenna mechanism driver drive and telemetry signal transmission; it meets the signal connection requirements of the antenna mechanism driver. The cable end connector model of the in-cabin on-board low-frequency cable connecting to the antenna mechanism driver is J6W-78D02K1NMB, and the cable output end connector models are J36A-26ZKL and J14A-26ZKL.

[0029] The thermal vacuum adapter cable includes two bundles of adapter cables for use inside the vacuum tank and two bundles for use outside the vacuum tank. The cables are twisted-pair shielded wires. Each bundle of adapter cables inside the vacuum tank is 10m long, and each bundle of adapter cables outside the vacuum tank is 7m long. These cables are used to transfer drive signals between the two antennas inside and outside the vacuum tank. The connector model for the two bundles of adapter cables inside the vacuum tank connecting to the onboard low-frequency cable is J36A-26ZJL, and the connector model for connecting to the vacuum tank flange is Y27-2255TK1LW. The connector model for the two bundles of adapter cables outside the vacuum tank connecting to the mechanism simulator is J36A-26TK, and the connector model for connecting to the vacuum tank flange is Y27III-2255TK1L. Furthermore, the thermal vacuum adapter cable can accommodate different connector models for various connection requirements.

[0030] Vacuum vessel flange: This flange ensures the satellite vacuum vessel remains in a sealed space and is used for connecting cables inside and outside the vacuum vessel. It allows drive signals from inside the vacuum vessel to be transmitted to the natural environment of the test chamber outside the vacuum vessel, facilitating the transfer of antenna mechanism drive signals to the outside. The external interface meets connection and testing requirements. The satellite uses a KM5A vacuum vessel, with flanges numbered C1~C14, used for low-frequency cables, high-frequency cables, temperature measurement, heating cage simulation, etc. The antenna drive mechanism cable connection flange is numbered C8, and the connector model for vacuum vessel flange C8 is Y27-2255ZJB4H.

[0031] Antenna Mechanism Simulator: This invention includes two simulators, capable of simultaneously simulating the rotation mechanisms of two antennas. (See reference...) Figure 2 and Figure 3 The simulator responds to the drive level output by the antenna mechanism driver and returns information such as the angle, speed, and position of the mechanism's rotation to the antenna mechanism driver. It can receive telemetry data from the entire satellite to observe the simulated mechanism's rotation, response, and other working states, facilitating the testing of the data transmission and relay subsystem's functions, performance, and specifications. It can also simulate telemetry signals for the onboard antenna's unlocking and deployment, and features equipment self-testing and zero-position calibration functions. The antenna mechanism simulator receives drive signals from the antenna driver after being transferred between the inside and outside of the tank, simulating the mechanical rotation of the onboard data transmission or relay antenna, and simultaneously returns the position telemetry signals of the data transmission or relay antenna to the onboard antenna mechanism driver.

[0032] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A testing device for an external antenna mechanism under satellite vacuum thermal environment, characterized in that, include: The onboard integrated control unit, antenna mechanism driver, onboard low-frequency cable, thermal vacuum adapter cable, vacuum tank flange, and antenna mechanism simulator; The onboard integrated control unit is connected to the antenna mechanism driver. The antenna mechanism driver is connected to the interface inside the vacuum tank flange via an onboard low-frequency cable and a thermal vacuum adapter cable. The interface outside the vacuum tank flange is connected to the antenna mechanism simulator via a thermal vacuum adapter cable.

2. The satellite vacuum thermal environment external antenna mechanism testing device according to claim 1, characterized in that: The on-board integrated control unit receives data from the satellite, including: ephemeris, satellite attitude, GPS data, time, and direct-injection pointing data packets; the on-board integrated control unit calculates the pointing information required for antenna driving and outputs control commands and two-dimensional angle information to the antenna mechanism driver.

3. The satellite vacuum thermal environment external antenna mechanism testing device according to claim 1, characterized in that: The antenna mechanism driver receives control commands from the on-board integrated control unit to rotate the two-dimensional pointing mechanism of the antenna, performs real-time telemetry monitoring of the position of the two-dimensional pointing mechanism, and returns the data to the on-board integrated control unit.

4. The satellite vacuum thermal environment external antenna mechanism testing device according to claim 1, characterized in that: The in-cabin on-board low-frequency cable is used for the transmission of antenna mechanism driver drive and telemetry signals; it meets the signal connection requirements of the antenna mechanism driver. The cable end connector of the in-cabin on-board low-frequency cable and the antenna mechanism driver is model J6W-78D02K1NMB, and the cable output end connector is model J36A-26ZKL and J14A-26ZKL.

5. The satellite vacuum thermal environment external antenna mechanism testing device according to claim 1, characterized in that: The thermal vacuum adapter cable includes an internal adapter cable and an external adapter cable. The connector for the internal adapter cable to connect with the onboard low-frequency cable is model J36A-26ZJL, and the connector for connecting with the vacuum tank flange is model Y27-2255TK1LW. The connector for the external adapter cable to connect with the mechanism simulator is model J36A-26TK, and the connector for connecting with the vacuum tank flange is model Y27III-2255TK1L.

6. The satellite vacuum thermal environment external antenna mechanism testing device according to claim 1, characterized in that: The antenna mechanism simulator is used to receive the drive signal output by the antenna driver after being transferred inside and outside the tank, simulate the mechanical rotation of the on-board data transmission or relay antenna, and at the same time return the position telemetry signal of the data transmission or relay antenna to the on-board antenna mechanism driver.

7. The satellite vacuum thermal environment external antenna mechanism testing device according to claim 1, characterized in that: The vacuum tank flange is used for connecting the internal and external adapter cables of the vacuum tank. The vacuum tank flanges are numbered C1 to C14. The internal adapter cable connects to the vacuum tank flange numbered C8. The connector model of the C8 vacuum tank flange is Y27-2255ZJB4H.

8. The satellite vacuum thermal environment external antenna mechanism testing device according to claim 1, characterized in that: The thermal vacuum adapter cable is a twisted-pair shielded cable.

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