On-rocket integrated comprehensive radio frequency system

Abstract

An on-rocket integrated comprehensive radio frequency system comprises a comprehensive measurement module, a comprehensive radio frequency front end and a comprehensive measurement antenna, wherein the comprehensive measurement module is connected with the comprehensive radio frequency front end through a VPX bus interface; the comprehensive radio frequency front end is connected with the comprehensive measurement antenna; the comprehensive measurement module is used for collecting multiple analog quantities, processing telemetry data, externally measurement uplink and downlink communication,safety control uplink and self-destruction control and third-party monitoring; the comprehensive radio frequency front end is used for telemetering downlink amplification and filtering, external measurement uplink amplification and filtering, external measurement downlink method and filtering, and safety control uplink amplification and filtering; and the comprehensive measurement antenna is integrated with a remote / external measurement downlink antenna, an external measurement uplink antenna and a safety control uplink antenna. By the scheme, the functions of collecting, remote measuring, external measuring and safety control are integrated, scattered independent single-machine products are integrally designed into a 3U VPX module, a power amplifier and an antenna, the size and the systemcomplexity are reduced, and meanwhile the utilization rate of computing resources is increased.

Description

technical field [0001] The present application relates to rocket radio frequency technology, in particular, to an integrated radio frequency system on a rocket. Background technique [0002] With the rise of commercial launch vehicles, facing increasingly severe market competition, low-cost design has become an effective means to improve the market competitiveness of launch vehicles. Among the various solutions for low-cost design, the integrated and miniaturized design of the arrow's electrical system has become an important way. The radio frequency system of the launch vehicle covers functions such as telemetry, external measurement, and security control, and undertakes important tasks such as data communication and pipeline security control during flight. Miniaturized design, the shortcomings of the traditional solution are: [0003] 1. The products are independent and scattered, the degree of integration is not enough, the individual volume is large, and the interconne...

AI Technical Summary

Problems solved by technology

[0003] 1. The products are independent and scattered, the degree of integration is not enough, the individual volume is large, and the interconnection is complicated. Only the reliability design of local single machines is considered, which has a great impact on the system. The specific performance is: first, the scattered products are large in size and heavy in weight 1. The price is high, which makes it difficult to reduce the overall weight of the electrical system, which affects the payload of the launch vehicle, and the economy is low; 2. The product interconnection is complicated, and each subsystem has an independent antenna, power amplifier, and controller, resulting in complicated cable connections. Difficulty in assembly leads to hindered assembly speed, increased system complexity and reduced reliability

[0004] 2. The product has a single function and a fixed interface, which cannot meet the requirements of commercial aerospace big data monitoring and single bus constraint design, and is not well compatible with integrated electronic system products. single, it often happens that the additional functional requirements cannot be met; second, the product interface form is fixed and the speed is not high. For the current integrated electronic system with Ethernet as the core, it cannot be directly connected to the system bus. The external security function design is complex; third, there is no third-party data monitoring function, and the internal operating status of the single machine cannot be known, which leads to difficulties in troubleshooting and data analysis when a fault occurs

[0005] 3. The resource utilization rate is low, and the electromagnetic compatibility design on the arrow is not good, which makes the design of the system level more difficult. The specific performance is as follows: First, in the traditional solution, telemetry, external measurement, and security control each have independent controllers, power amplifiers, and antennas , it is easy to cause waste of computing resources and repeated waste of radio frequency channel resources; second, each stand-alone product only considers its own electromagnetic compatibility design, resulting in an impact on the entire system's electromagnetic compatibility during system integration, resulting in complex or difficult to solve parts of the entire system's electromagnetic compatibility design EMC issues

[0007] The telemetry, external measurement, security control and other functional products of the launch vehicle radio frequency system are independent, with high complexity and low resource utilization

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