Alternating ignition system and method for bipropellant thruster experiments

Abstract

The present application relates to the technical field of thruster hot calibration, and discloses an alternating ignition system and method suitable for double-element thruster experiments, which solves the problem of low hot calibration efficiency of double-element thrusters caused by waiting for the thruster structure to cool down and the vacuum injection system to restart during the hot calibration process of traditional thrusters, and comprises the following steps: setting a starting temperature before the hot calibration test, selecting a hot calibration chamber or a performance chamber according to the thrust range of the double-element thruster, carrying out double-chamber alternating ignition, and then carrying out hot calibration data processing in parallel to complete the hot calibration test of the double-element thruster. In the hot calibration process of the double-element 10NG / 25N thruster, the double-chamber alternating ignition is carried out, the cooling time after ignition of the thruster is effectively utilized, the vacuum injection system does not need to be restarted during the hot calibration process, and the hot calibration time of the two double-element thrusters is shortened from 2 days to 1.5 days.

Description

Technical Field

[0001] This invention relates to an alternating ignition system and method suitable for experiments with bicomponent thrusters, belonging to the field of thruster thermal calibration technology. Background Technology

[0002] The bicomponent 10NG / 25N thruster is a key component and final actuator of the bicomponent satellite propulsion system. After thermal calibration on the ground, the thruster is delivered to the user, providing the actual thrust, flow rate, pressure, and mixture ratio of each thruster for the entire satellite, enabling true paired use of the bicomponent thrusters. However, the current calibration time for a single bicomponent 10NG / 25N thruster exceeds two days, making it difficult to meet the delivery requirements for large-volume products.

[0003] In the current thermal calibration process of bicomponent thrusters, a vacuum chamber is mostly used for thermal calibration. However, after each operating condition test, the structural temperature of the thruster will rise significantly, and it is necessary to wait for the structural temperature of the thruster to return to normal before the next test can be carried out, which affects the thermal calibration efficiency of bicomponent thrusters. Summary of the Invention

[0004] This invention addresses the problem of low thermal calibration efficiency caused by waiting for the thruster structure temperature to drop during traditional thruster thermal calibration processes, and proposes an alternating ignition system and method suitable for bicomponent thruster experiments.

[0005] The technical solution adopted by the present invention to solve the above problems is as follows: The alternating ignition system proposed by the present invention for use in experiments with bicomponent thrusters includes:

[0006] The thermal standard chamber and the performance chamber are arranged in parallel. The parallel pipelines of the thermal standard chamber and the performance chamber are connected to the vacuum ejection system, which is connected to a steam boiler.

[0007] Furthermore, the thermal calibration chamber is used for thermal calibration of thrusters with a thrust of 25N and below, while the performance chamber is used for thermal calibration of thrusters with a thrust of 100N and below. Both the thermal calibration chamber and the performance chamber are connected to a circulating water system and an exhaust gas hydraulic system.

[0008] Furthermore, both the performance chamber and the thermal calibration chamber are vacuum chambers, and they are also connected to a delivery system, which includes propellant delivery pipelines and steam delivery pipelines. After the thermal calibration test is completed in one of the performance chambers or the thermal calibration chamber, the chamber is cooled down for 10 to 20 minutes. While the chamber is cooling down, the thruster in the other chamber conducts thermal calibration tests in parallel according to the temperature conditions.

[0009] Furthermore, the performance chamber's piping is equipped with a vacuum gauge ZKJ1 and a switch V01, and the performance chamber's piping is equipped with a vacuum gauge ZKJ6 and a switch V02.

[0010] Alternating ignition methods applicable to experiments with bicomponent thrusters include:

[0011] Set the start-up temperature before thermal calibration, select either the thermal calibration chamber or the performance chamber according to the thrust range of the bicomponent thruster, perform alternating ignition of the two chambers, and then perform parallel thermal calibration to complete the thermal calibration test of the bicomponent thruster.

[0012] Furthermore, the parallel thermal calibration process includes the following steps:

[0013] Step 1: Inspect and hand over the bi-component thruster assemblies for the current two trips, and weld the thermocouples to the bi-component thruster assemblies;

[0014] Step 2: Install the bi-component thruster assemblies on two separate occasions and perform leak rate tests on the two vacuum chambers of the test stand.

[0015] Step 3: Start the vacuum ejector system. While inspecting and handing over the bi-component thruster assembly, start the circulating water system, steam boiler, exhaust gas treatment system, and conveying system.

[0016] Step 4: The propellant is delivered to the thermal calibration chamber and performance chamber via the delivery system. Switch V01 is turned on and switch V02 is turned off. The thermal calibration test of the bicomponent thruster is carried out in the thermal calibration chamber. After the test is completed, cooling begins. At the same time, switch V01 is turned off and switch V02 is turned on. The thermal calibration test is carried out again in the performance chamber. After the test is completed, cooling begins.

[0017] Step 5: Repeat step 4 once to complete the thermal calibration test of the bicomponent thruster;

[0018] Step 6: Purge and vent the propellant lines, and use an automatic control cleaning system to automatically clean the thruster components;

[0019] Step 7: Shut down the steam boiler and vacuum ejector system;

[0020] Step 8: Shut down the circulating water system, depressurize and shut down the conveying system, and shut down the exhaust gas treatment system;

[0021] Step 9: Purge the thermal standard compartment and performance compartment, disassemble the thruster assembly, and simultaneously inspect and hand over the bi-component thruster assemblies for the next two runs, welding the thermocouples to the bi-component thruster assemblies for the two runs.

[0022] Step 10: Perform the overall cleaning and component cleaning of the previous two bi-component thrusters, and take samples of the cleaning medium. Repeat steps 2-9 to perform parallel thermal calibration of the next two bi-component thrusters.

[0023] The beneficial effects of this invention are:

[0024] 1. This invention employs alternating ignition of the two chambers during the thermal calibration of the bicomponent 10NG / 25N thruster, effectively utilizing the cooling time of the vacuum chamber. Simultaneously, the vacuum ejector system does not require restarting during the thermal calibration process, reducing the thermal calibration time of the two bicomponent thrusters from 2 days to 1.5 days. This increases the annual delivery of bicomponent thrusters by 50%-65%, significantly improving the thermal calibration efficiency of bicomponent thrusters and enabling the fulfillment of large-volume product delivery requirements.

[0025] 2. This invention sets up the thermal standard chamber and the performance chamber in parallel, so that one chamber can work independently without affecting the cooling process of the other chamber. At the same time, circulating water systems are set up in the conveying system, the thermal standard chamber and the performance chamber respectively, which ensures that the cleaning of the conveying pipeline and the cooling of the vacuum chamber can be carried out independently, thus improving work efficiency. Attached Figure Description

[0026] Figure 1 This is a flowchart illustrating the alternating ignition method for bicomponent thruster experiments provided by the present invention.

[0027] Figure 2 A schematic diagram of the parallel thermal calibration process for the bicomponent thruster provided by the present invention;

[0028] Figure 3 This is a schematic diagram of the structure of the dual-component vacuum system provided by the present invention;

[0029] Figure 4 The schematic diagram of the vacuum steam jet pump provided by the present invention shows that: 1-nozzle, 2-mixing chamber, 3-expanding pipe, 4-steam inlet, and 5-air inlet. Detailed Implementation

[0030] Combination Figure 1-4 This implementation method is described as follows: Figure 1 and Figure 2 As shown, this embodiment uses a bicomponent 10NG / 25N thruster as an example for explanation, and provides detailed examples of the working time of each component during the alternating ignition process. The steps of the alternating ignition method applicable to bicomponent thruster experiments described in this embodiment include:

[0031] Step 1: Day 1, inspect and hand over the current two bi-component thruster assemblies, and weld the thermocouples to the bi-component thruster assemblies;

[0032] Step 2: Install the bi-component thruster assembly twice and test the air and liquid leakage of the test vehicle. The time from the handover of the bi-component thruster assembly to the processing time of the air and liquid leakage test of the test vehicle is 1.5 hours.

[0033] Step 3: Start the vacuum ejector system. The start-up time is 1 hour. While checking and handing over the bi-component thruster assembly, start the circulating water system, steam boiler, exhaust gas hydraulic system and conveying system. The start-up time for the circulating water system and steam boiler is 1 hour, and the start-up time for the exhaust gas hydraulic system and conveying system is 0.5 hours.

[0034] The alternating ignition system used in this embodiment, suitable for experiments with bicomponent thrusters, is as follows: Figure 3 As shown, a steam inlet channel is provided, equipped with a gas valve S02. Steam enters the steam storage tank after passing through gas valve S02. The steam storage tank has 7 steam delivery channels, a temperature sensor Y01, a pressure sensor Y04, and a gas valve S14. The first steam delivery channel is equipped with a gas valve S07, which is connected to the steam merging channel and the other end of the J5 vacuum steam jet pump. The other end of the J5 vacuum steam jet pump is connected to the thermal standard chamber and the performance chamber. The pipeline in the thermal standard chamber is equipped with a vacuum gauge ZKJ1 and a pneumatic valve switch V01. The pipeline in the performance chamber is equipped with a vacuum gauge ZKJ6 and a pneumatic valve switch V02. The second steam delivery channel is equipped with a gas valve S06, which is connected to the other end of the J4 vacuum steam jet pump and one end of the J5 vacuum steam jet pump. Next, the third steam delivery channel is equipped with a gas valve S05, which is connected to the other end of the J3 vacuum steam jet pump and one end of the J4 vacuum steam jet pump respectively. The fourth steam delivery channel is equipped with a gas valve S08, which is connected to the other end of the J2b vacuum steam jet pump and one end of the J3 vacuum steam jet pump respectively. The fifth steam delivery channel is equipped with a gas valve S08, which is connected to the other end of the J2a vacuum steam jet pump and one end of the J2b vacuum steam jet pump respectively. The sixth steam delivery channel is equipped with a gas valve S08, which is connected to the other end of the J1b vacuum steam jet pump and one end of the J2a vacuum steam jet pump respectively. The seventh steam delivery channel is equipped with a gas valve S08, which is connected to the other end of the J1a vacuum steam jet pump and one end of the J1b vacuum steam jet pump respectively.

[0035] One end of the J1a vacuum steam jet pump is connected to the cleaning pipeline, and the other end is connected to the seventh steam delivery channel, the J1b vacuum steam jet pump, and the cleaning pipeline. The other end of the J1b vacuum steam jet pump is connected to the cleaning pipeline, and the other end is connected to the J2b vacuum steam jet pump, the cleaning pipeline, and the sixth steam delivery channel. A thermometer Y05 is installed on the cleaning pipeline connected to the other end of the J2b vacuum steam jet pump. One end of the J2a vacuum steam jet pump is connected to the cleaning pipeline, and the other end is connected to the J2b vacuum steam jet pump, the cleaning pipeline, the fifth steam delivery channel, and the steam... The storage tank is connected to the pipeline between the steam storage tank and the J2a vacuum steam jet pump. A gas valve V03 is installed on the pipeline between the steam storage tank and the J2a vacuum steam jet pump. One end of the J2b vacuum steam jet pump is connected to the cleaning pipeline, and the other end is connected to the fourth steam delivery pipeline, the cleaning pipeline, and the steam storage tank. A temperature sensor Y06 is installed on the cleaning pipeline connected to the other end of the J2b vacuum steam jet pump. A gas valve V04 is installed on the pipeline between the steam storage tank and the J2b vacuum steam jet pump. The other end of the steam storage tank is connected to the cleaning pipeline and the J3 vacuum steam jet pump. A temperature sensor Y07 is installed on the cleaning pipeline at the other end of the steam storage tank.

[0036] The structure of each vacuum steam jet pump is as follows: Figure 4 As shown, it includes a nozzle 1, a mixing chamber 2, an expansion pipe 3, a steam inlet 4, and an air inlet 5. After steam enters the nozzle 1 through the steam inlet 4, it is ejected at high speed, generating low pressure, which draws air in through the air inlet 5 and mixes it in the mixing chamber 2. After passing through the expansion pipe 3, the kinetic energy is converted into pressure energy.

[0037] The cleaning pipes connected to one end of vacuum steam jet pumps J1a, J1b, J2a, and J2b are all connected to a water storage tank. The water storage tank is equipped with a temperature sensor Y10 and a pressure sensor Y09. The cleaning pipes connected to the other end of the three pumps are connected to a first water storage tank. The first water storage tank is equipped with a level sensor SWJ-1, which is connected to a first remote control device and a second remote control device. Both the first and second remote control devices are connected to the second water storage tank. The second water storage tank is equipped with a level sensor SWJ03. The other end of the second water storage tank is connected to pump C, and the other end of pump C is connected to the first water storage tank. The other end of the first water storage pipe is connected to a third water storage tank. The third water storage tank is equipped with a level sensor SWJ02, and the other end of the third water storage tank is connected to pumps A and B. Pumps A and B are both connected to the water storage tank, and their connecting pipes are equipped with liquid valves W02.

[0038] Vacuum gauges ZKJ1 and ZKJ2 are connected to the fourth water tank via pipes. The fourth water tank is equipped with a level sensor SWJ05. The other end of the fourth water tank is connected to pump F. The other end of pump F is connected to the second water tank. The other end of the second water tank is connected to the fifth water tank. The fifth water tank is equipped with a level sensor SWJ03. The other end of the water tank is connected to pumps D and E respectively. Pumps D and E are connected to the thermal standard chamber and the performance chamber.

[0039] Both the thermal calibration chamber and the performance chamber are vacuum chambers. The thermal calibration chamber can perform thermal calibration tests on thrusters of 25N and below, while the performance chamber can perform thermal calibration tests on thrusters of 100N and below. The thermal calibration chamber is equipped with vacuum gauges ZKJ4 and ZKJ5, while the performance chamber is equipped with vacuum gauges ZKJ2 and ZKJ3.

[0040] Step 4: The propellant is transported to the thermal calibration chamber and performance chamber through the propellant delivery pipeline for combustion. After the thermal calibration test of the bicomponent thruster is carried out in the thermal calibration chamber, cooling begins. At the same time, the thermal calibration test is carried out again in the performance chamber under different temperature and pressure environments. After completion, cooling begins.

[0041] Step 5: Repeat step 4 once to complete the thermal calibration test of the bicomponent thruster. The thermal calibration test time is 6 hours.

[0042] Step 6: Purge and vent the propellant lines, and use an automatic control cleaning system to automatically clean the thruster components. The time for purging and venting the propellant lines and automatically cleaning the thruster components is 1.5 hours.

[0043] Step 7: Shut down the steam boiler and vacuum ejector system. The shutdown time for the steam boiler and vacuum ejector system is 0.5 hours.

[0044] Step 8: Shut down the circulating water system, depressurize the conveying system and then shut it down, and shut down the exhaust gas treatment system. This step takes 0.6 hours.

[0045] Step 9: Purge the thermal reference chamber and performance chamber, and disassemble the thruster assembly. The time for purging the thermal reference chamber and performance chamber and disassembling the thruster assembly is 1 hour. At the same time, inspect and hand over the bi-component thruster assemblies for the next two runs, and weld the thermocouples to the bi-component thruster assemblies for the two runs.

[0046] Step 10: Day 2, perform the overall cleaning and component cleaning of the bi-component thrusters from the previous two runs, and take samples of the cleaning medium. Complete the parallel thermal calibration of the bi-component thruster components from the previous run. Repeat steps 2-9 to perform the parallel thermal calibration of the next two bi-component thrusters.

[0047] This implementation method takes advantage of the standardized characteristics of pipeline evacuation and online cleaning processes, and makes full use of the programmable function of the self-locking valve. An automatic control interface is developed in the measurement and control software. After the measurement and control software completes the automatic control and operation of the pipeline evacuation and online cleaning processes, the risk of misoperation during the test is eliminated, the intervention of test personnel is reduced, and the test efficiency is improved.

[0048] Step 11: Repeat steps 1-10 to complete the continuous thermal calibration test of two bicomponent 10NG / 25N thrusters.

[0049] In summary, this invention conducts thermal calibration tests on bicomponent 10NG / 25N thrusters using alternating ignition. As can be seen from the detailed thermal calibration time described above, this invention reduces the thermal calibration time for two bicomponent 10NG / 25N thrusters from 2 days to 1.5 days, increasing the annual delivery of bicomponent 10NG / 25N thrusters by 50%-65%, significantly improving the thermal calibration efficiency of bicomponent 10NG / 25N thrusters, and enabling the fulfillment of large-volume product delivery requirements.

[0050] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention in any way. Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make some modifications or alterations to the above-disclosed technical content to create equivalent embodiments without departing from the scope of the present invention. Any simple modifications, equivalent substitutions, and improvements made to the above embodiments without departing from the scope of the present invention, based on the technical essence of the present invention and within the spirit and principles of the present invention, shall still fall within the protection scope of the present invention.

Claims

1. An alternating ignition system suitable for experiments with bicomponent thrusters, characterized in that, include: The thermal standard chamber and the performance chamber are arranged in parallel. The parallel pipelines of the thermal standard chamber and the performance chamber are connected to the vacuum ejection system, and the vacuum ejection system is connected to a steam boiler. The thermal calibration chamber is used for thermal calibration of thrusters of 25N and below, and the performance chamber is used for thermal calibration of thrusters of 100N and below. Both the thermal calibration chamber and the performance chamber are connected to a circulating water system and an exhaust gas treatment system. Both the performance chamber and the thermal calibration chamber are vacuum chambers. The performance chamber and the thermal calibration chamber are also connected to a transport system, which includes a propellant transport pipeline and a steam transport pipeline. After the thermal calibration test is completed in one of the performance chambers or the thermal calibration chamber, the chamber is cooled down for 10 to 20 minutes. At the same time as the chamber is cooled down, the thruster in the other chamber carries out thermal calibration test in parallel according to the temperature.

2. The alternating ignition system for bicomponent thruster experiments according to claim 1, characterized in that, The performance chamber is equipped with a vacuum gauge ZKJ1 and a switch V01 on its pipeline, and a vacuum gauge ZKJ6 and a switch V02 on its pipeline.

3. An alternating ignition method applicable to experiments with bicomponent thrusters, applied to the alternating ignition system for experiments with bicomponent thrusters as described in any one of claims 1-2, characterized in that, include: Set the start-up temperature before thermal calibration, select either the thermal calibration chamber or the performance chamber according to the thrust range of the bicomponent thruster, perform alternating ignition of the two chambers, and then perform parallel thermal calibration to complete the thermal calibration test of the bicomponent thruster.

4. The alternating ignition method for experimental bicomponent thrusters according to claim 3, characterized in that, The steps of parallel thermal calibration processing include: Step 1: Inspect and hand over the bi-component thruster assemblies for the current two trips, and weld the thermocouples to the bi-component thruster assemblies; Step 2: Install the bi-component thruster assemblies on two separate occasions and perform leak rate tests on the two vacuum chambers of the test stand. Step 3: Start the vacuum ejector system. While inspecting and handing over the bi-component thruster assembly, start the circulating water system, steam boiler, exhaust gas treatment system, and conveying system. Step 4: The propellant is delivered to the thermal calibration chamber and performance chamber via the delivery system. Switch V01 is turned on and switch V02 is turned off. The thermal calibration test of the bicomponent thruster is carried out in the thermal calibration chamber. After the test is completed, cooling begins. At the same time, switch V01 is turned off and switch V02 is turned on. The thermal calibration test is carried out again in the performance chamber. After the test is completed, cooling begins. Step 5: Repeat step 4 once to complete the thermal calibration test of the bicomponent thruster; Step 6: Purge and vent the propellant lines, and use an automatic control cleaning system to automatically clean the thruster components; Step 7: Shut down the steam boiler and vacuum ejector system; Step 8: Shut down the circulating water system, depressurize and shut down the conveying system, and shut down the exhaust gas treatment system; Step 9: Purge the thermal standard compartment and performance compartment, disassemble the thruster assembly, and simultaneously inspect and hand over the bi-component thruster assemblies for the next two runs, welding the thermocouples to the bi-component thruster assemblies for the two runs. Step 10: Perform the overall cleaning and component cleaning of the previous two bi-component thrusters, and take samples of the cleaning medium. Repeat steps 2-9 to perform parallel thermal calibration of the next two bi-component thrusters.

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