CN215640190U

CN215640190U - Portable aerospace telemetering receiving system

Info

Publication number: CN215640190U
Application number: CN202121991727.2U
Authority: CN
Inventors: 刘赐平; 王超; 江炜; 郑琦; 侯志; 赵苏强
Original assignee: Shanghai Ases Spaceflight Technology Ltd
Current assignee: Shanghai Ases Spaceflight Technology Ltd
Priority date: 2021-08-23
Filing date: 2021-08-23
Publication date: 2022-01-25
Anticipated expiration: 2031-08-23

Abstract

The utility model discloses a portable aerospace telemetering receiving system, which comprises a monitoring terminal, a telemetering receiver set and an antenna equipment set, wherein the telemetering receiver set is detachably connected with the monitoring terminal and the antenna equipment set, and the telemetering receiver set is connected with the antenna equipment set in a one-to-one correspondence manner; the telemetering receiver set drives the antenna equipment set to receive a plurality of UHF frequency band radio frequency signals generated by the target spacecraft by using an Automatic Frequency Control (AFC) technology, and after identifying the radio frequency signals of each frequency band and analyzing the radio frequency signals into a plurality of telemetering data packets, the telemetering receiver set sends the signals to the monitoring terminal for processing, monitoring and displaying. The utility model is not limited to the flight speed and Doppler influence of the spacecraft, and can effectively receive data signals without influencing the sensitivity of signal reception when the signal frequency offset is large.

Description

Portable aerospace telemetering receiving system

Technical Field

The utility model relates to the technical field of aerospace measurement and control, in particular to a portable aerospace remote measurement receiving system.

Background

With the continuous development of aerospace technology, commercial aerospace also becomes one of the research hotspots in the aerospace field nowadays. In addition, SPACE successfully recovers a one-stage carrier rocket body in 2016, thereby greatly reducing the SPACE launching cost and enabling commercial SPACE in the world to see the development hope.

Based on this, the one-level rocket body with the largest volume and the highest cost in the carrier rocket is recycled, so that the commercial space launching cost is reduced, and the method is also a necessary way for the space application in China. The carrier rocket one-sublevel measuring system is matched with the carrier rocket one-sublevel arrow body, the falling area of the one-sublevel arrow body is different along with the position and the shot direction of a launching field, so that the measuring system cannot be a fixed ground station; since most of the currently selected first-level arrow bodies fall in the unmanned/dead zone, the first-level measurement system needs to go deep into the area with extremely inconvenient traffic. Therefore, the need to develop a portable one-level measurement system is at hand.

The existing aerospace measurement and control frequency bands openly used for commercial aerospace are mainly UHF bands and X bands, but the X band is high in frequency and narrow in wave beam, so that the development is not suitable from the commercial perspective, and therefore, the development of corresponding equipment from the UHF band is required to meet the special requirement of a sub-level measurement system.

SUMMERY OF THE UTILITY MODEL

The embodiment of the application provides a portable aerospace telemetering receiving system, and solves the technical problems that in the prior art, radio frequency signals of multiple UHF frequency bands cannot be received and identified in real time, and the telemetering requirement of commercial aerospace measurement cannot be met.

The embodiment of the application provides a portable aerospace telemetering receiving system, which comprises a monitoring terminal, a telemetering receiving unit and an antenna equipment group, wherein the telemetering receiving unit is detachably connected with the monitoring terminal and the antenna equipment group, and the telemetering receiving unit is connected with the antenna equipment group in a one-to-one correspondence manner;

the telemetering receiver set drives the antenna equipment set to receive a plurality of UHF frequency band radio frequency signals generated by the target spacecraft by using an Automatic Frequency Control (AFC) technology, and after identifying the radio frequency signals of each frequency band and analyzing the radio frequency signals into a plurality of telemetering data packets, the telemetering receiver set sends the signals to the monitoring terminal for processing, monitoring and displaying.

Furthermore, the antenna equipment group comprises three paths of antenna equipment for receiving radio frequency signals in a UHF frequency band, and the three paths of antenna equipment receive different UHF frequency bands of the same spacecraft in the same flight direction.

Furthermore, the telemetry receiver set comprises three telemetry receivers, each telemetry receiver comprises a radio frequency front end and a dual-channel modulator, and the radio frequency front end is connected with the dual-channel modulator, so that the three telemetry receivers receive the radio frequency signals of multiple UHF frequency bands transmitted by the three antenna devices one by one through the radio frequency front end, and after the radio frequency signals of each frequency band are identified by using an Automatic Frequency Control (AFC) technology, the radio frequency signals are correspondingly sent to the dual-channel modulator to be analyzed into six telemetry data packets.

Furthermore, a multi-path expander is connected between the telemetry receiver and the monitoring terminal, and the multi-path expander is correspondingly connected with the three telemetry receivers, so that the telemetry data modulated by the three telemetry receivers is received by the multi-path expander and is sent to the monitoring terminal for data fusion processing.

Further, the antenna device employs a yagi antenna.

The technical scheme provided in the embodiment of the application has at least the following technical effects:

1. the telemetering receiver adopts an Automatic Frequency Control (AFC) technology to identify and process the radio frequency signals received by the antenna equipment so as to acquire telemetering data when the spacecraft flies, is not limited to the flying speed and Doppler influence of the spacecraft, and can effectively receive data signals without influencing the sensitivity of signal receiving when the frequency of the signals deviates greatly; under the conditions of unknown real-time position, speed and the like of the spacecraft, the frequency compensation can be automatically carried out according to the received signals.

2. Due to the adoption of the detachable assembly of the portable aerospace telemetering receiving system, the monitoring terminal, the antenna equipment and the telemetering receiver, the station can be flexibly arranged without being limited to the type of a spacecraft and the environmental requirements, the station does not need to be fixed, the station can be flexibly arranged according to the requirements, and the aerospace measuring and controlling cost is effectively reduced.

3. Due to the adoption of the portable aerospace telemetering receiving system, the structure is simple, and the station arrangement and the acquisition of telemetering data can be completed in a short time.

4. The three antenna devices are adopted to receive different UHF frequency bands of the same spacecraft in the same flight direction, and the acquisition frequency bands of the three antenna devices are overlapped to a certain extent, so that the full coverage of UHF frequency band signal reception is ensured.

Drawings

FIG. 1 is a block diagram of a portable aerospace telemetry receiving system according to an embodiment of the present application;

FIG. 2 is a schematic structural connection diagram of a portable aerospace telemetry receiving system according to an embodiment of the application;

FIG. 3 is a schematic diagram of a telemetry receiver according to an embodiment of the present application.

Detailed Description

In order to better understand the technical solution, the technical solution will be described in detail with reference to the drawings and the specific embodiments.

Referring to fig. 1-3, the embodiment of the application provides a portable aerospace telemetry receiving system, which can be understood as a portable aerospace measurement and control station. The telemetry receiving system at least comprises a monitoring terminal 100, a telemetry receiving unit and an antenna equipment unit. In this embodiment, the telemetry receiver set is detachably connected to the monitoring terminal 100 and the antenna device set, and the telemetry receiver set and the antenna device set are connected in a one-to-one correspondence manner. The telemetering receiver set drives the antenna equipment set to receive a plurality of UHF frequency band radio frequency signals generated by the target spacecraft by using an Automatic Frequency Control (AFC) technology, and after identifying the radio frequency signals of each frequency band and analyzing the radio frequency signals into a plurality of telemetering data packets, the telemetering receiver set sends the radio frequency signals to the monitoring terminal for processing, monitoring and displaying.

The monitor terminal 100 in this embodiment may be understood as a task management computer that is responsible for task scheduling and data management of the all-telemetry station and can be remotely connected to a network. In addition, the telemetry receiving system in this example includes a power supply device for providing power to the respective devices, including but not limited to dry batteries, rechargeable batteries, lithium batteries, solar cells, and the like.

It can be understood that in this example, the telemetry receiver set includes a plurality of telemetry receivers 300, the antenna device set includes a plurality of antenna devices 400, the plurality of telemetry receivers 300 are connected with the plurality of antenna devices 400 in a one-to-one correspondence manner, each antenna device 400 is configured to receive radio frequency signals in different UHF frequency bands and then transmit the radio frequency signals to the telemetry receiver 300 connected in a corresponding manner, and each telemetry receiver 300 acquires the radio frequency signals in the UHF frequency band generated by the spacecraft by using an Automatic Frequency Control (AFC) technique. The Automatic Frequency Control (AFC) technology is based on a preamble technology in the existing wireless communication field, transmits known transmission data content to a telemetering receiver, determines the difference between the center Frequency of the current telemetering receiver and the signal Frequency by scanning the changed receiving Frequency, and then automatically corrects the receiving Frequency of the telemetering receiver to adapt to the special places of high flight speed and large Doppler influence of a spacecraft, so that effective data signals are received, and meanwhile, the receiving sensitivity is not reduced under the condition of large signal Frequency offset.

The spacecraft in the embodiment is a sub-stage rocket body, and based on the fact that the speed of the sub-stage rocket body is high in the flying process and the Doppler influence is large, information such as the real-time position and the speed of the sub-stage rocket body cannot be obtained in real time.

The antenna equipment set in this embodiment includes three antenna equipment 400 for receiving UHF-band radio frequency signals, and the three antenna equipment 400 receive different UHF bands in the same flight direction of the same spacecraft. The antenna device 400 in this embodiment is preferably a three-way antenna device, and after multiple tests, the three-way antenna device 400 points to the flight direction of the same spacecraft, and during the flight of the spacecraft, the three-way antenna device 400 receives radio frequency signals in different UHF frequency bands, and the receiving frequency bands of the three antenna devices 400 have a certain overlapping area, so as to ensure that the reception of the radio frequency signals in the UHF frequency band is fully covered during the flight of the spacecraft. Preferably, the antenna device employs a yagi antenna.

The telemetry receiver set in this embodiment includes three telemetry receivers 300, each telemetry receiver 300 includes a radio frequency front end and a dual-channel modulator, and the radio frequency front end is connected to the dual-channel modulator, so that the three telemetry receivers 300 receive three radio frequency signals of multiple UHF bands transmitted by the antenna device 400 one by one through the radio frequency front end, and after identifying the radio frequency signals of each band by using an Automatic Frequency Control (AFC) technique, the radio frequency signals are correspondingly sent to the dual-channel modulator to be analyzed into six telemetry data packets. Further, the radio frequency front end identifies the radio frequency signal transmitted by the corresponding antenna equipment through an Automatic Frequency Control (AFC) technology, and after the radio frequency signal is transmitted to the dual-channel modulator, the radio frequency signal is analyzed into a telemetry data packet required by the monitoring terminal. Therefore, the three-way telemetry receiver can be understood to receive three radio frequency signals of different UHF frequency bands, and identify and analyze the radio frequency signals into six telemetry data packets. Further, the telemetry receiver 300 is configured with a power switch 310, an enable switch 320, an input port 330, a first output port 340, and a second output port 350. The input port 340 is connected to the antenna device 400 to obtain the radio frequency signal received by the antenna device 400, and the first output port 340 is connected to the monitoring terminal 100 so as to transmit the processed telemetry data packet to the monitoring terminal 100; the second output port 350 is connected to the antenna device 400, and is configured to send a frequency band receiving instruction to the antenna device 400, so as to provide a receiving frequency band range for the antenna device 400 to receive the radio frequency signal.

Further, a multi-path expander 200 is further connected between the telemetry receiver 300 and the monitoring terminal 100, and the multi-path expander 200 is connected with the two-channel modulators in the three-path telemetry receiver 300 in a one-to-one correspondence manner, so that the multi-path expander receives the telemetry data modulated by the three two-channel modulators and sends the telemetry data to the monitoring terminal 100 for data fusion processing. Since only the monitoring terminal 100, the telemetry receiver 300 and the antenna device 400 are used, when the receiving frequency band is wide, the method is applied to the monitoring terminal 100, the plurality of telemetry receivers 300, the plurality of antenna devices 400 and the multi-path expander 200, so that the aerospace telemetry system is greatly simplified in the embodiment. And the devices adopt detachable structures, so that testers can lay stations at any time and any place to perform space telemetering work.

The Automatic Frequency Control (AFC) technology in the embodiment is realized at the radio frequency front end in the telemetering receiver, the radio frequency signals transmitted by the antenna equipment are received, the telemetering data packet in the flight process of the sub-level arrow body is identified and analyzed, a lead code of 32 bytes, namely 4B, is arranged in front of each data frame, and the lead code is default to 55 for the convenience of identification of the telemetering receiver. During the preamble, the telemetry receiver automatically calculates the frequency offset value of the current radio frequency signal by sweeping the frequency within the pass band, and receives the subsequent data within the data frame based thereon. The portable aerospace telemetry receiving system in the embodiment is modulated by multiple tests, and normal receiving of the whole section of telemetry data in the real-time falling process of the debris of the one-level rocket can be completed within 2 hours conventionally, so that the station arrangement cost is greatly reduced, and development and planning of commercial aerospace are facilitated.

While preferred embodiments of the present invention have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all such alterations and modifications as fall within the scope of the utility model.

It will be apparent to those skilled in the art that various changes and modifications may be made in the present invention without departing from the spirit and scope of the utility model. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.

Claims

1. A portable aerospace telemetering receiving system is characterized by comprising a monitoring terminal, a telemetering receiver set and an antenna equipment set, wherein the telemetering receiver set is detachably connected with the monitoring terminal and the antenna equipment set, and the telemetering receiver set is connected with the antenna equipment set in a one-to-one correspondence manner;

2. The portable aerospace telemetry receiving system of claim 1 wherein said antenna array includes three antenna devices for receiving UHF band radio frequency signals, and wherein three of said antenna devices receive different UHF bands from the same spacecraft in the same direction of flight.

3. The portable aerospace telemetry receiving system of claim 2, wherein the telemetry receiver set comprises three telemetry receivers, each telemetry receiver comprises a radio frequency front end and a two-channel modulator, the radio frequency front end is connected with the two-channel modulator, so that the three telemetry receivers receive three radio frequency signals of multiple UHF bands transmitted by the antenna device one by one through the radio frequency front end, and after the radio frequency signals of each band are identified by an Automatic Frequency Control (AFC) technology, the radio frequency signals are correspondingly transmitted to the two-channel modulator to be analyzed into six telemetry data packets.

4. The portable aerospace telemetry receiving system of claim 3, wherein a demultiplexer is further connected between the telemetry receiver and the monitor terminal, and the demultiplexer is correspondingly connected to the three telemetry receivers, so that the telemetry data modulated by the three telemetry receivers is received by the demultiplexer and is sent to the monitor terminal for data fusion processing.

5. A portable aerospace telemetry receiving system as claimed in claim 2 wherein said antenna apparatus employs a yagi antenna.