CN-120735996-B - Alternate ignition system and method suitable for experiment of dual-component thruster

CN120735996BCN 120735996 BCN120735996 BCN 120735996BCN-120735996-B

Abstract

The invention relates to the technical field of thermal calibration of thrusters, discloses an alternate ignition system and an alternate ignition method suitable for a dual-component thruster experiment, and solves the problem of low thermal calibration efficiency of the dual-component thruster caused by waiting for structural cooling of the thruster and restarting of a vacuum injection system in the thermal calibration process of the traditional thruster. According to the invention, double-cabin alternate ignition is carried out in the thermal calibration process of the double-component 10NG/25N thruster, so that the cooling time of the thruster after ignition is effectively utilized, and meanwhile, the vacuum injection system does not need to be restarted in the thermal calibration process, so that the thermal calibration time of the two double-component thrusters is shortened from 2 days to 1.5 days.

Inventors

Qian Hengxiao
ZHONG WEI
HE SHILONG
YANG KE
LI SHUMING
LI ZHAO

Assignees

河北轩宇动力科技有限公司

Dates

Publication Date: 20260512
Application Date: 20250729

Claims (4)

1. Alternating ignition system suitable for two-component thruster experiments is characterized in that the alternating ignition system comprises: the heat mark cabin and the performance cabin are arranged in parallel, a parallel pipeline of the heat mark cabin and the performance cabin is connected with the vacuum injection system, and the vacuum injection system is connected with the steam boiler; the thermal standard cabin is used for carrying out thermal calibration of the thrusters with the number of 25N and below, the performance cabin is used for carrying out thermal calibration of the thrusters with the number of 100N and below, and the thermal standard cabin and the performance cabin are connected with a circulating water system and a tail gas treatment system; The performance cabin and the thermal standard cabin are both vacuum cabins, the performance cabin and the thermal standard cabin are further connected with a conveying system, the conveying system comprises a propellant conveying pipeline and a steam conveying pipeline, the temperature of one of the performance cabin and the thermal standard cabin is reduced after the thermal standard test working condition is completed, the temperature reduction time is 10-20 min, and a thruster in the other cabin is used for carrying out the thermal standard test according to the temperature condition in parallel while the temperature is reduced.
2. The alternating ignition system for a two-component thruster experiment according to claim 1, wherein a vacuum gauge ZKJ and a switch V01 are provided on the piping of the performance pod, and a vacuum gauge ZKJ and a switch V02 are provided on the piping of the performance pod.
3. The alternate ignition method suitable for the experiments of the two-component thruster, which is applied to the alternate ignition system suitable for the experiments of the two-component thruster as claimed in any one of claims 1-2, is characterized by comprising the following steps: And setting a starting temperature before the thermal calibration treatment, selecting a thermal calibration cabin or a performance cabin according to the thrust range of the dual-component thruster to perform dual-cabin alternate ignition, and performing parallel thermal calibration treatment to complete a thermal calibration test of the dual-component thruster.
4. The method of alternating ignition for a two-component thruster experiment of claim 3, wherein the step of parallel thermal calibration process comprises: step 1, checking and handing over the current two-time two-component thruster assembly, and welding a thermocouple to the two-component thruster assembly; Step 2, mounting the two-component thruster assembly for two times, and detecting leakage rates of two vacuum cabins of the test bed; starting a vacuum injection system, and starting a circulating water system, a steam boiler, a tail gas treatment system and a conveying system while checking and connecting the two-component thruster assembly; Step 4, conveying the propellant to a thermal standard cabin and a performance cabin through a conveying system, opening a switch V01, closing a switch V02, performing a thermal calibration test of the dual-component thruster in the thermal standard cabin, starting cooling after the test is completed, closing the switch V01, opening the switch V02, performing the thermal calibration test again in the performance cabin, and cooling after the completion; step 5, repeating the step 4 once to finish a thermal calibration test of the dual-component thruster; Step 6, blowing off and evacuating the propellant pipeline, and automatically cleaning the thruster assembly by using an automatic control cleaning system; step 7, closing the steam boiler and the vacuum injection system; step 8, closing the circulating water system, decompressing the conveying system, closing the tail gas treatment system; step 9, deflating the thermal standard cabin and the performance cabin, disassembling the thruster assembly, simultaneously checking and handing over the two-component thruster assemblies of the next two orders, and welding the thermocouple to the two-component thruster assemblies of the two orders; And 10, performing complete machine cleaning and component cleaning of the two-component thrusters for the last two times, sampling a cleaning medium, repeating the steps 2-9, and performing parallel thermal calibration of the two-component thrusters for the next two times.

Description

Alternate ignition system and method suitable for experiment of dual-component thruster Technical Field The invention relates to an alternate ignition system and method suitable for a dual-component thruster experiment, and belongs to the technical field of thruster thermal calibration. Background The dual-component 10NG/25N thruster is a key component and a final execution component of the dual-component satellite propulsion system, and the thruster is delivered to a user after the ground is subjected to thermal calibration, so that the performances of real thrust, flow, pressure, mixing ratio and the like of each thruster can be provided for the whole satellite, and the real pairing use of the dual-component thrusters is realized. The calibration time of the existing one-time double-component 10NG/25N thruster is more than 2 days, and the delivery requirement of mass products is difficult to finish. In the existing dual-component thruster thermal calibration process, a vacuum cabin is mostly adopted for thermal calibration, and after the working condition test is completed each time, the structural temperature of the thruster can be obviously increased, and the next test is required to be carried out after the structural temperature of the thruster is restored to be normal, so that the thermal calibration efficiency of the dual-component thruster is affected. Disclosure of Invention The invention aims to solve the problem of low thermal calibration efficiency caused by waiting for the structural temperature reduction of a thruster in the thermal calibration process of a traditional thruster, and further provides an alternate ignition system and method suitable for a dual-component thruster experiment. The technical scheme adopted for solving the problems is that the alternating ignition system suitable for the experiment of the dual-component thruster provided by the invention comprises the following components: the heat mark cabin and the performance cabin are arranged in parallel, a parallel pipeline of the heat mark cabin and the performance cabin is connected with the vacuum injection system, and the vacuum injection system is connected with the steam boiler. Further, the thermal standard cabin is used for carrying out thermal calibration of the thrusters of 25N and below, the performance cabin is used for carrying out thermal calibration of the thrusters of 100N and below, and the thermal standard cabin and the performance cabin are connected with a circulating water system and a tail gas water conservancy system. Further, the performance cabin and the thermal standard cabin are both vacuum cabins, the performance cabin and the thermal standard cabin are further connected with a conveying system, the conveying system comprises a propellant conveying pipeline and a steam conveying pipeline, the temperature of one of the performance cabin and the thermal standard cabin is reduced after the thermal standard test working condition is completed, the temperature reduction time is 10-20 min, and meanwhile, a thruster in the other cabin carries out the thermal standard test in parallel according to the temperature condition. Further, a vacuum gauge ZKJ and a switch V01 are arranged on the pipeline of the performance cabin, and a vacuum gauge ZKJ and a switch V02 are arranged on the pipeline of the performance cabin. The alternating ignition method suitable for the experiment of the dual-component thruster comprises the following steps: And setting a starting temperature before the thermal calibration treatment, selecting a thermal calibration cabin or a performance cabin according to the thrust range of the dual-component thruster to perform dual-cabin alternate ignition, and performing parallel thermal calibration treatment to complete a thermal calibration test of the dual-component thruster. Further, the parallel thermal calibration processing step includes: step 1, checking and handing over the current two-time two-component thruster assembly, and welding a thermocouple to the two-component thruster assembly; Step 2, mounting the two-component thruster assembly for two times, and detecting leakage rates of two vacuum cabins of the test bed; starting a vacuum injection system, and starting a circulating water system, a steam boiler, a tail gas treatment system and a conveying system while checking and connecting the two-component thruster assembly; Step 4, conveying the propellant to a thermal standard cabin and a performance cabin through a conveying system, opening a switch V01, closing a switch V02, performing a thermal calibration test of the dual-component thruster in the thermal standard cabin, starting cooling after the test is completed, closing the switch V01, opening the switch V02, performing the thermal calibration test again in the performance cabin, and cooling after the completion; step 5, repeating the step 4 once to finish a thermal calibration test of the dual-component thruster; Step 6,