A method, device and equipment for starting control of an engine of a liquid carrier rocket

Abstract

The embodiment of the present application provides a kind of starting control method, device and equipment of the engine of liquid carrier rocket, the method comprises: staggered peak starting first engine staging group and second engine staging group in the multi-stage parallel engine of liquid carrier rocket;Obtain the starting data of the first engine staging group and second engine staging group;According to the starting data, determine the action timing of the first component group of the first engine staging group and the action timing of the second component group of the second engine staging group;According to the action timing, control the starting of the multi-stage parallel engine of liquid carrier rocket.The embodiment of the present application can be started by staggered peak to the first and second engine staging group, real-time acquisition starting data and adjust the action timing of two component groups accordingly, improve engine starting performance.

Description

Technical Field

[0001] This invention relates to the field of launch vehicle control technology, and in particular to a method, apparatus and equipment for starting control of a liquid launch vehicle engine. Background Technology

[0002] The start-up control process of liquid-fueled rocket engines is a critical factor affecting launch safety and mission success. Current rocket engine start-up control mainly relies on fixed timing sequences and static thresholds. Actions such as valve opening and ignition are executed according to preset time sequences, which cannot adapt to environmental changes (such as fuel temperature fluctuations). Using fixed pressure and speed thresholds to detect anomalies is prone to false triggering under low temperature or high pressure conditions. Each engine operates independently without a coordination mechanism, which can easily lead to rocket vibration or structural damage due to thrust imbalance. Summary of the Invention

[0003] The technical problem to be solved by the embodiments of the present invention is to provide a starting control method, device and equipment for the engine of a liquid launch vehicle, which can improve the starting performance of the engine by staggering the starting of the first and second engine stage groups, acquiring starting data in real time and adjusting the action sequence of the two component groups accordingly.

[0004] To solve the above-mentioned technical problems, the technical solution of the present invention is as follows:

[0005] A method for starting and controlling the engine of a liquid-fueled launch vehicle, comprising:

[0006] The first and second engine stages in a multi-stage parallel engine of a liquid-fueled launch vehicle with staggered start-up times;

[0007] Acquire the starting data of the first engine grade group and the second engine grade group;

[0008] Based on the starting data, determine the operating sequence of the first component group of the first engine grade group and the operating sequence of the second component group of the second engine grade group.

[0009] The starting of the multi-stage parallel engine of the liquid-fueled launch vehicle is controlled according to the aforementioned action timing.

[0010] Optionally, the first engine stage group and the second engine stage group in the multi-stage parallel engine of the liquid-fueled launch vehicle with staggered start-up include:

[0011] Using the master command as the time reference, start the first engine stage group;

[0012] After setting the set time interval, start the second engine stage group;

[0013] The set time interval is the time interval between the start-up sequence of the first engine stage group and the start-up sequence of the second engine stage group.

[0014] Optionally, the starting data of the first engine stage group includes: first fuel temperature and first pipeline pressure;

[0015] The starting data for the second engine stage group includes: second fuel temperature and second pipeline pressure;

[0016] The first component group includes: a first turbine starter, a first oxygen auxiliary valve, a first flare igniter, a first methane auxiliary valve, a first oxygen main valve starting chamber, a first methane discharge valve, a first oxygen discharge valve, a first methane main valve, a first oxygen main valve, and a first oxygen auxiliary valve;

[0017] The second component group includes: a second turbine starter, a second oxygen auxiliary valve, a second flare igniter, a second methane auxiliary valve, a second oxygen main valve starting chamber, a second methane discharge valve, a second oxygen discharge valve, a second methane main valve, a second oxygen main valve, and a second oxygen auxiliary valve.

[0018] Based on the starting data, the operating timing sequence of the first component group of the first engine stage group and the operating timing sequence of the second component group of the second engine stage group are determined, including:

[0019] Based on the first fuel temperature and the first pipeline pressure, determine the operating sequence of the first turbine starter, the first oxygen auxiliary valve, the first flare igniter, the first methane auxiliary valve, the first oxygen main valve starting chamber, the first methane discharge valve, the first oxygen discharge valve, the first methane main valve, the first oxygen main valve, and the first oxygen auxiliary valve.

[0020] Based on the second fuel temperature and the second pipeline pressure, determine the operating sequence of the second turbine starter, the second oxygen auxiliary valve, the second flare igniter, the second methane auxiliary valve, the second oxygen main valve starting chamber, the second methane discharge valve, the second oxygen discharge valve, the second methane main valve, the second oxygen main valve, and the second oxygen auxiliary valve.

[0021] Optionally, based on the first fuel temperature and the first pipeline pressure, the operating sequence of the first turbine starter, the first oxygen auxiliary valve, the first flare igniter, the first methane auxiliary valve, the first oxygen main valve starting chamber, the first methane discharge valve, the first oxygen discharge valve, the first methane main valve, the first oxygen main valve, and the first oxygen auxiliary valve is determined, including:

[0022] according to W 11 =[( W 12 - W 13 ) / W 14 ]× K1. Determine the first temperature compensation delay;

[0023] in, W 11 For the first temperature compensation delay, W 12 The first reference temperature, W 13 The first fuel temperature, W 14 The step size is calculated for the first temperature. K 1 represents the first temperature compensation coefficient;

[0024] according to Determine the first pressure correction factor;

[0025] in, Y 11 This is the first pressure correction factor. Y 12 Set the first parameter. Y 13 Set the second parameter. Y 14 Set parameters for the third one. L 11 For the first pipeline pressure, L 12 Set parameters for the fourth one. L 13 Set parameters for the fifth one;

[0026] according to t 20 = ( t 10 + W 11 )× Y 11 Determine the operating timing of the first turbine starter;

[0027] in, t 20 The operating sequence of the first turbine starter. t 10 The timing sequence for the first turbine starter;

[0028] according to t 21 = ( t 11 + W 11 )× Y 11 Determine the operating timing of the first oxygen auxiliary valve;

[0029] in, t 21The operating sequence of the first oxygen auxiliary valve, t 11 The timing sequence for setting the first oxygen auxiliary valve;

[0030] according to t 22 = ( t 12 + W 11 )× Y 11 Determine the timing sequence of the first torch igniter;

[0031] in, t 22 The timing sequence of the first igniter's actions. t 12 The timing sequence for the first torch igniter;

[0032] according to t 23 = ( t 13 + W 11 )× Y 11 Determine the operating timing of the first methane auxiliary valve;

[0033] in, t 23 The operating sequence of the first methane auxiliary valve, t 13 The timing sequence for setting the first methane auxiliary valve;

[0034] according to t 24 = ( t 14 + W 11 )× Y 11 Determine the operating timing of the first oxygen main valve starting chamber;

[0035] in, t 24 This refers to the operating sequence of the first oxygen main valve starting chamber. t 14 The timing sequence for setting the starting chamber of the first oxygen main valve;

[0036] according to t 25 = ( t 15 + W 11 )× Y 11 Determine the timing of the first methane discharge valve's operation;

[0037] in, t 25 The operating sequence of the first methane discharge valve. t 15 The timing sequence for setting the first methane discharge valve;

[0038] according to t 26 = ( t 16 + W 11 )× Y 11 Determine the timing of the first oxygen release valve's operation;

[0039] in, t 26 The timing sequence for the operation of the first oxygen release valve. t 16 The timing sequence for setting the first oxygen vent valve;

[0040] according to t 27 = ( t 17 + W 11 )× Y 11 Determine the operating timing of the first methane main valve;

[0041] in, t 27 The operating sequence of the first methane main valve, t 17 The timing sequence for setting the first methane main valve;

[0042] according to t 28 = ( t 18 + W 11 )× Y 11 Determine the operating sequence of the first oxygen main valve;

[0043] in, t 28 The operating sequence of the first oxygen main valve. t 18 The timing sequence for setting the first oxygen main valve;

[0044] according to t 29 = ( t 19 + W 11 )× Y11 Determine the operating timing of the first oxygen auxiliary valve;

[0045] in, t 29 The operating sequence of the first oxygen auxiliary valve, t 19 This is the timing sequence for setting the first oxygen auxiliary valve.

[0046] Optionally, based on the second fuel temperature and the second pipeline pressure, the operating sequence of the second turbine starter, the second oxygen auxiliary valve, the second flare igniter, the second methane auxiliary valve, the second oxygen main valve starting chamber, the second methane discharge valve, the second oxygen discharge valve, the second methane main valve, the second oxygen main valve, and the second oxygen auxiliary valve is determined, including:

[0047] according to W 21 =[( W 22 - W 23 ) / W 24 ]× K 2. Determine the second temperature compensation delay;

[0048] in, W 21 For the second temperature compensation delay, W 22 The second reference temperature, W 23 The second fuel temperature, W 24 The step size is calculated for the second temperature. K 2 represents the second temperature compensation coefficient;

[0049] according to Determine the second pressure correction factor;

[0050] in, Y 21 This is the second pressure correction factor. Y 22 Set parameters for the sixth one. Y 23 Set parameters for the seventh one. Y 24 Set parameters for the eighth one. L 21 For the pressure of the second pipeline, L 22 Set parameters for the ninth one. L 23 Set parameters for the tenth;

[0051] according to t 40 = (t 30 + W 21 )× Y 21 Determine the operating timing of the second turbine starter;

[0052] in, t 40 The operating sequence of the second turbine starter. t 30 The timing sequence for the second turbine starter;

[0053] according to t 41 = ( t 31 + W 21 )× Y 21 Determine the operating timing of the second oxygen auxiliary valve;

[0054] in, t 41 The operating sequence of the second oxygen auxiliary valve, t 31 The timing sequence for setting the second oxygen auxiliary valve;

[0055] according to t 42 = ( t 32 + W 21 )× Y 21 Determine the timing sequence of the second torch igniter;

[0056] in, t 42 The timing sequence of the second torch igniter. t 32 The timing sequence for the second torch igniter;

[0057] according to t 43 = ( t 33 + W 21 )× Y 21 Determine the operating timing of the second methane auxiliary valve;

[0058] in, t 43 The operating sequence of the second methane auxiliary valve, t 33 The timing sequence for setting the second methane auxiliary valve;

[0059] according to t 44 = ( t 34 + W 21 )× Y 21 Determine the operating timing of the second oxygen main valve starting chamber;

[0060] in, t 44 This refers to the operating sequence of the second oxygen main valve starting chamber. t 34 The timing sequence for setting the starting chamber of the second oxygen main valve;

[0061] according to t 45 = ( t 35 + W 21 )× Y 21 Determine the timing of the second methane discharge valve's operation;

[0062] in, t 45 The timing sequence for the operation of the second methane discharge valve. t 35 The timing sequence for setting the second methane discharge valve;

[0063] according to t 46 = ( t 36 + W 21 )× Y 21 Determine the timing of the second oxygen release valve's operation;

[0064] in, t 46 The timing sequence for the operation of the second oxygen release valve. t 36 The timing sequence for setting the second oxygen vent valve;

[0065] according to t 47 = ( t 37 + W 21 )× Y 21 Determine the operating timing of the second methane main valve;

[0066] in, t 47 The operating sequence of the second methane main valve,t 37 The timing sequence for setting the second methane main valve;

[0067] according to t 48 = ( t 38 + W 21 )× Y 21 Determine the operating sequence of the second oxygen main valve;

[0068] in, t 48 The operating sequence of the second oxygen main valve. t 38 The timing sequence for setting the second oxygen main valve;

[0069] according to t 49 = ( t 39 + W 21 )× Y 21 Determine the operating timing of the second oxygen auxiliary valve;

[0070] in, t 49 The operating sequence of the second oxygen auxiliary valve. t 39 This is the timing sequence for setting the second oxygen auxiliary valve.

[0071] Optionally, this startup method also includes:

[0072] Obtain the operating data of the first engine classification group and the second engine classification group;

[0073] Based on the operating data, adjust the operating parameters of the first engine grade group and the second engine grade group.

[0074] Optionally, the first engine tier group includes at least two groups of first engines;

[0075] The second engine tier group includes: at least two groups of second engines;

[0076] The operating data includes: the first engine speed and the first vibration value, and the second engine speed and the second vibration value;

[0077] Based on the aforementioned operating data, adjust the operating parameters of the first engine stage group and the second engine stage group, including:

[0078] The operating parameters of the first engine and the second engine are adjusted based on the first rotational speed, the first vibration value, the second rotational speed, and the second vibration value.

[0079] Embodiments of the present invention also provide a starting control device for an engine of a liquid-fueled launch vehicle, comprising:

[0080] The acquisition module is used to acquire the start-up data of the first engine stage group and the second engine stage group in the multi-stage parallel engine of the staggered start liquid launch vehicle.

[0081] The processing module is used to determine the action sequence of the first component group of the first engine stage group and the action sequence of the second component group of the second engine stage group based on the start-up data; and to control the start-up of the multi-stage parallel engines of the liquid launch vehicle according to the action sequence.

[0082] Embodiments of the present invention also provide a computing device, comprising:

[0083] One or more processors;

[0084] A storage device for storing one or more programs that, when executed by one or more processors, cause the one or more processors to perform the method as described above.

[0085] Embodiments of the present invention also provide a computing device readable storage medium storing a program that, when executed by a processor, implements the method described above.

[0086] The above-described solutions of the embodiments of the present invention have at least the following beneficial effects:

[0087] The above-described solution of this invention avoids the risk of thrust impact by staggered starting, abandons the traditional mode of simultaneous starting of multiple engines, divides the engines into two groups for staggered starting, reserves a dynamic buffer window for the thrust output of the two groups, avoids the impact of thrust superposition when starting at the same time, reduces the risk of rocket vibration and structural damage, and solves the problem of thrust imbalance caused by lack of coordination in traditional independent operation.

[0088] Dynamic data acquisition eliminates the limitations of static thresholds. By acquiring two sets of engine start-up data in real time, it replaces the traditional fixed pressure and speed threshold judgment. It can accurately identify operating conditions such as increased fuel viscosity at low temperatures and sudden changes in high-pressure delivery rate, avoiding false shutdowns or missed faults, and significantly improving the accuracy of fault diagnosis and start-up safety.

[0089] The timing-adaptive technology adapts to complex environments by adjusting the action timing of two sets of components based on real-time startup data, rather than relying on a preset fixed timing. It can dynamically match complex operating conditions such as fuel temperature fluctuations and environmental pressure changes, breaking through the limitation of traditional fixed timing that cannot adapt to environmental changes and ensuring startup reliability under different operating conditions. Attached Figure Description

[0090] Figure 1 This is a schematic flowchart of the starting control method for the engine of a liquid-fueled launch vehicle provided in an embodiment of the present invention.

[0091] Figure 2 This is a schematic diagram of the starting control device for the engine of a liquid-fueled launch vehicle provided in an embodiment of the present invention. Detailed Implementation

[0092] Exemplary embodiments of the invention will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the invention are shown in the drawings, it should be understood that the invention may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this invention will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0093] like Figure 1 As shown, an embodiment of the present invention provides a starting control method for an engine of a liquid-fueled launch vehicle, comprising:

[0094] Step 11: Stagger the start-up of the first and second engine stages in the multi-stage parallel engine of the liquid launch vehicle.

[0095] Step 12: Obtain the starting data of the first engine grade group and the second engine grade group;

[0096] Step 13: Based on the starting data, determine the operating sequence of the first component group of the first engine grading group and the operating sequence of the second component group of the second engine grading group.

[0097] Step 14: Control the starting of the multi-stage parallel engine of the liquid launch vehicle according to the action sequence.

[0098] In this example, staggered starting avoids the risk of thrust impact. It abandons the traditional mode of simultaneous starting of multiple engines and starts the engines in two groups at staggered times. It reserves a dynamic buffer window for the thrust output of the two groups, avoids the impact of thrust superposition when starting at the same time, reduces the risk of rocket vibration and structural damage, and solves the problem of thrust imbalance caused by lack of coordination in traditional independent operation.

[0099] Dynamic data acquisition eliminates the limitations of static thresholds. By acquiring two sets of engine start-up data in real time through step 12, it replaces the traditional fixed pressure and speed threshold judgment. It can accurately identify operating conditions such as increased fuel viscosity at low temperatures and sudden changes in high-pressure delivery rate, avoiding false shutdowns or missed faults, and significantly improving the accuracy of fault judgment and start-up safety.

[0100] The timing is adaptive to complex environments. Step 13 adjusts the action timing of the two sets of components based on real-time start-up data, rather than relying on a preset fixed timing. This can dynamically match complex working conditions such as fuel temperature fluctuations and environmental pressure changes, breaking through the limitation that traditional fixed timing cannot adapt to environmental changes and ensuring start-up reliability under different working conditions.

[0101] In an optional embodiment of the present invention, step 11, which involves staggered starting of the first and second engine stages in the multi-stage parallel engines of the liquid-fueled launch vehicle, includes:

[0102] Step 111: Using the master command as the time reference, start the first engine stage group;

[0103] Step 112: After setting the set time interval, start the second engine stage group;

[0104] The set time interval is the time interval between the start-up sequence of the first engine stage group and the start-up sequence of the second engine stage group.

[0105] Specifically, the set time interval can be 0.2s.

[0106] In this example, the short interval of 0.2s can avoid the impact of the thrust superposition during synchronous start-up, and also prevent the connection between the two sets of thrust from being discontinuous due to excessively long intervals. It provides a buffer time for the first set of engines to initially establish thrust and collect data, and allows the second set to start up in time, ensuring that the overall thrust of the rocket body rises steadily and reducing the attitude fluctuations of the rocket body caused by improper intervals.

[0107] In an optional embodiment of the present invention, in step 12, the starting data of the first engine stage group includes: first fuel temperature and first pipeline pressure;

[0108] The starting data for the second engine stage group includes: second fuel temperature and second pipeline pressure;

[0109] The first component group includes: a first turbine starter, a first oxygen auxiliary valve, a first flare igniter, a first methane auxiliary valve, a first oxygen main valve starting chamber, a first methane discharge valve, a first oxygen discharge valve, a first methane main valve, a first oxygen main valve, and a first oxygen auxiliary valve;

[0110] The second component group includes: a second turbine starter, a second oxygen auxiliary valve, a second flare igniter, a second methane auxiliary valve, a second oxygen main valve starting chamber, a second methane discharge valve, a second oxygen discharge valve, a second methane main valve, a second oxygen main valve, and a second oxygen auxiliary valve.

[0111] This example clearly defines the starting data (fuel temperature, pipeline pressure) and component composition of the first and second engine stage groups, enabling more precise dynamic adjustments. By collecting key parameters (temperature, pressure), the timing of corresponding components (such as the turbine starter and various valves) can be optimized to ensure starting safety and reliability.

[0112] In an optional embodiment of the present invention, step 13, determining the operating sequence of the first component group of the first engine stage group based on the starting data, includes:

[0113] Step 131: Determine the operating sequence of the first turbine starter, the first oxygen auxiliary valve, the first flare igniter, the first methane auxiliary valve, the first oxygen main valve starting chamber, the first methane discharge valve, the first oxygen discharge valve, the first methane main valve, the first oxygen main valve, and the first oxygen auxiliary valve based on the first fuel temperature and the first pipeline pressure.

[0114] In an optional embodiment of the present invention, step 13, determining the operating sequence of the second component group of the second engine stage group based on the starting data, includes:

[0115] Step 132: Determine the operating sequence of the second turbine starter, second oxygen auxiliary valve, second flare igniter, second methane auxiliary valve, second oxygen main valve starting chamber, second methane discharge valve, second oxygen discharge valve, second methane main valve, second oxygen main valve, and second oxygen auxiliary valve based on the second fuel temperature and second pipeline pressure.

[0116] Specifically, in step 131, the operating sequence of the first turbine starter, the first oxygen auxiliary valve, the first flare igniter, the first methane auxiliary valve, the first oxygen main valve starting chamber, the first methane discharge valve, the first oxygen discharge valve, the first methane main valve, the first oxygen main valve, and the first oxygen auxiliary valve is determined based on the first fuel temperature and the first pipeline pressure, including:

[0117] Step 13101, according to W 11 =[( W 12 - W 13 ) / W 14 ]× K 1. Determine the first temperature compensation delay;

[0118] in, W 11For the first temperature compensation delay, W 12 The first reference temperature, W 13 The first fuel temperature, W 14 The step size is calculated for the first temperature. K 1 represents the first temperature compensation coefficient;

[0119] Step 13102, according to Determine the first pressure correction factor;

[0120] in, Y 11 This is the first pressure correction factor. Y 12 Set the first parameter. Y 13 Set the second parameter. Y 14 Set parameters for the third one. L 11 For the first pipeline pressure, L 12 Set parameters for the fourth one. L 13 Set parameters for the fifth one;

[0121] Step 13103, according to t 20 = ( t 10 + W 11 )× Y 11 Determine the operating timing of the first turbine starter;

[0122] in, t 20 The operating sequence of the first turbine starter. t 10 The timing sequence for the first turbine starter;

[0123] Step 13104, according to t 21 = ( t 11 + W 11 )× Y 11 Determine the operating timing of the first oxygen auxiliary valve;

[0124] in, t 21 The operating sequence of the first oxygen auxiliary valve, t 11The timing sequence for setting the first oxygen auxiliary valve;

[0125] Step 13105, according to t 22 = ( t 12 + W 11 )× Y 11 Determine the timing sequence of the first torch igniter;

[0126] in, t 22 The timing sequence of the first igniter's actions. t 12 The timing sequence for the first torch igniter;

[0127] Step 13106, according to t 23 = ( t 13 + W 11 )× Y 11 Determine the operating timing of the first methane auxiliary valve;

[0128] in, t 23 The operating sequence of the first methane auxiliary valve, t 13 The timing sequence for setting the first methane auxiliary valve;

[0129] Step 13107, according to t 24 = ( t 14 + W 11 )× Y 11 Determine the operating timing of the first oxygen main valve starting chamber;

[0130] in, t 24 This refers to the operating sequence of the first oxygen main valve starting chamber. t 14 The timing sequence for setting the starting chamber of the first oxygen main valve;

[0131] Step 13108, according to t 25 = ( t 15 + W 11 )× Y 11 Determine the timing of the first methane discharge valve's operation;

[0132] in, t 25 The operating sequence of the first methane discharge valve. t 15 The timing sequence for setting the first methane discharge valve;

[0133] Step 13109, according to t 26 = ( t 16 + W 11 )× Y 11 Determine the timing of the first oxygen release valve's operation;

[0134] in, t 26 The timing sequence for the operation of the first oxygen release valve. t 16 The timing sequence for setting the first oxygen vent valve;

[0135] Step 13110, according to t 27 = ( t 17 + W 11 )× Y 11 Determine the operating timing of the first methane main valve;

[0136] in, t 27 The operating sequence of the first methane main valve, t 17 The timing sequence for setting the first methane main valve;

[0137] Step 13111, according to t 28 = ( t 18 + W 11 )× Y 11 Determine the operating sequence of the first oxygen main valve;

[0138] in, t 28 The operating sequence of the first oxygen main valve. t 18 The timing sequence for setting the first oxygen main valve;

[0139] Step 13112, according to t 29 = ( t 19 + W11 )× Y 11 Determine the operating timing of the first oxygen auxiliary valve;

[0140] in, t 29 The operating sequence of the first oxygen auxiliary valve, t 19 This is the timing sequence for setting the first oxygen auxiliary valve.

[0141] In step 132, based on the second fuel temperature and the second pipeline pressure, the operating sequence of the second turbine starter, the second oxygen auxiliary valve, the second flare igniter, the second methane auxiliary valve, the second oxygen main valve starting chamber, the second methane discharge valve, the second oxygen discharge valve, the second methane main valve, the second oxygen main valve, and the second oxygen auxiliary valve is determined, including:

[0142] Step 13201, according to W 21 =[( W 22 - W 23 ) / W 24 ]× K 2. Determine the second temperature compensation delay;

[0143] in, W 21 For the second temperature compensation delay, W 22 The second reference temperature, W 23 The second fuel temperature, W 24 The step size is calculated for the second temperature. K 2 represents the second temperature compensation coefficient;

[0144] Step 13202, according to Determine the second pressure correction factor;

[0145] in, Y 21 This is the second pressure correction factor. Y 22 Set parameters for the sixth one. Y 23 Set parameters for the seventh one. Y 24 Set parameters for the eighth one. L 21 For the pressure of the second pipeline, L 22 Set parameters for the ninth one. L 23 Set parameters for the tenth;

[0146] Step 13203, according to t 40 = ( t 30 + W 21 )× Y 21 Determine the operating timing of the second turbine starter;

[0147] in, t 40 The operating sequence of the second turbine starter. t 30 The timing sequence for the second turbine starter;

[0148] Step 13204, according to t 41 = ( t 31 + W 21 )× Y 21 Determine the operating timing of the second oxygen auxiliary valve;

[0149] in, t 41 The operating sequence of the second oxygen auxiliary valve, t 31 The timing sequence for setting the second oxygen auxiliary valve;

[0150] Step 13205, according to t 42 = ( t 32 + W 21 )× Y 21 Determine the timing sequence of the second torch igniter;

[0151] in, t 42 The timing sequence of the second torch igniter. t 32 The timing sequence for the second torch igniter;

[0152] Step 13206, according to t 43 = ( t 33 + W 21 )× Y 21 Determine the operating timing of the second methane auxiliary valve;

[0153] in,t 43 The operating sequence of the second methane auxiliary valve, t 33 The timing sequence for setting the second methane auxiliary valve;

[0154] Step 13207, according to t 44 = ( t 34 + W 21 )× Y 21 Determine the operating timing of the second oxygen main valve starting chamber;

[0155] in, t 44 This refers to the operating sequence of the second oxygen main valve starting chamber. t 34 The timing sequence for setting the starting chamber of the second oxygen main valve;

[0156] Step 13208, according to t 45 = ( t 35 + W 21 )× Y 21 Determine the timing of the second methane discharge valve's operation;

[0157] in, t 45 The timing sequence for the operation of the second methane discharge valve. t 35 The timing sequence for setting the second methane discharge valve;

[0158] Step 13209, according to t 46 = ( t 36 + W 21 )× Y 21 Determine the timing of the second oxygen release valve's operation;

[0159] in, t 46 The timing sequence for the operation of the second oxygen release valve. t 36 The timing sequence for setting the second oxygen vent valve;

[0160] Step 13210, according to t 47 = ( t 37 + W 21)× Y 21 Determine the operating timing of the second methane main valve;

[0161] in, t 47 The operating sequence of the second methane main valve, t 37 The timing sequence for setting the second methane main valve;

[0162] Step 13211, according to t 48 = ( t 38 + W 21 )× Y 21 Determine the operating sequence of the second oxygen main valve;

[0163] in, t 48 The operating sequence of the second oxygen main valve. t 38 The timing sequence for setting the second oxygen main valve;

[0164] Step 13212, according to t 49 = ( t 39 + W 21 )× Y 21 Determine the operating timing of the second oxygen auxiliary valve;

[0165] in, t 49 The operating sequence of the second oxygen auxiliary valve. t 39 This is the timing sequence for setting the second oxygen auxiliary valve.

[0166] In this example, abstract environmental parameters are transformed into directly calculable control commands: fuel temperature deviation is transformed into quantifiable timing compensation quantities through the first and second temperature compensation delay formulas, solving the problem of mismatch in component action timing under different fuel temperatures; and pipeline pressure fluctuations are transformed into timing correction ratios using the pressure correction coefficient formula, avoiding action errors under fixed pressure thresholds.

[0167] The dual-parameter synergistic mechanism is particularly crucial: temperature compensation ensures extended preheating at low temperatures and shortened intervals at high temperatures, while pressure correction slows down the action at high pressures and accelerates the response at low pressures. The combination of the two enables components such as the turbine starter and oxygen / methane valve in the first and second stage groups to dynamically adjust their action sequence according to real-time operating conditions.

[0168] The independent calculation system ensures control accuracy: the two tiered groups calculate independently based on their own fuel temperature and pipeline pressure, which not only ensures the coordinated action of the internal components of a single group (such as the first oxygen auxiliary valve and the first flare igniter), but also achieves timing matching between the two groups through staggered peak windows (such as the coordinated action of the first methane main valve and the second methane main valve), completely getting rid of the rigid limitations of fixed timing.

[0169] In an optional embodiment of the present invention, step 14, controlling the starting of the multi-stage parallel engine of the liquid-fueled launch vehicle according to the action timing, may include:

[0170] Step 141: Using the master command as the time reference, control the starting of the first and second component groups of the multi-stage parallel engine of the liquid launch vehicle according to the action sequence.

[0171] In this example, the first and second component groups are ensured to operate in a dynamically adjusted sequence to adapt to changes in fuel temperature and pipeline pressure, thereby improving start-up reliability and reducing the risk of rocket vibration and structural damage.

[0172] In an optional embodiment of the present invention, the above-described method may further include:

[0173] Step 15: Obtain the operating data of the first engine classification group and the second engine classification group;

[0174] Step 16: Adjust the operating parameters of the first engine grading group and the second engine grading group according to the operating data.

[0175] In step 15, the first engine tier group includes at least two groups of first engines;

[0176] The second engine tier group includes: at least two groups of second engines;

[0177] The operating data includes: the first rotational speed and first vibration value of the first engine, the second rotational speed and second vibration value of the second engine, and the thrust of the first engine and the thrust of the second engine.

[0178] Specifically, the first engine may include: sub-engines one, four, and seven, and the second engine may include: sub-engines two, three, five, and six.

[0179] In step 16, the operating parameters of the first engine grading group and the second engine grading group are adjusted according to the operating data, including:

[0180] Step 161, adjusting the operating parameters of the first engine and the second engine based on the first rotational speed, the first vibration value, the second rotational speed, and the second vibration value, including:

[0181] Step 16111, according to Determine the first fuel adjustment amount for the first engine;

[0182] in, RL1 i This is the first fuel adjustment amount for the first engine. f 1 is the first coefficient. f 2 is the first coefficient. N1 i The first rotational speed, N1 m Set the maximum speed threshold for the first setting. N1 a Set a minimum speed threshold for the first setting. i= 1,2 ,...c, c is The number of first engines;

[0183] Step 16112, according to Determine the second fuel adjustment amount for the first engine;

[0184] in, RL2 i This is the second fuel adjustment amount for the first engine. f 3 is the third coefficient. f 4 is the fourth coefficient. Z1 i The first vibration value, Z1 m Set the maximum threshold for the first vibration value. Z1 a Set a minimum threshold for the vibration value for the first setting;

[0185] Step 16113, according to RL3 i = RL1 i + RL2 i Determine the fuel adjustment amount for the first engine;

[0186] in, RL3 i This is the fuel adjustment amount for the first engine.

[0187] Step 16114, according to Determine the first fuel adjustment amount for the second engine;

[0188] in, RL4 j This is the first fuel adjustment amount for the second engine. f 5 is the fifth coefficient. f 6 is the sixth coefficient. N2 j For the second rotational speed, N2 mSet the maximum speed threshold for the second setting. N2 a Set a minimum speed threshold for the second setting. j= 1,2 ,...v, v is The number of second engines;

[0189] Step 16115, according to Determine the second fuel adjustment amount for the second engine;

[0190] in, RL5 j This is the second fuel adjustment amount for the second engine. f 7 is the seventh coefficient. f 8 is the eighth coefficient. Z2 j This is the second vibration value. Z2 m Set a maximum threshold for the second vibration value. Z2 a Set a minimum threshold for the second vibration value;

[0191] Step 16116, according to RL6 j = RL4 j + RL5 j Determine the fuel adjustment amount for the second engine;

[0192] in, RL6 j For the fuel adjustment amount of the second engine;

[0193] Step 16117: Adjust the fuel amount based on the fuel adjustment amount of the first engine and the fuel adjustment amount of the second engine;

[0194] The operating parameters of the first engine and the second engine include: fuel adjustment amount.

[0195] In this example, compared to traditional solutions that only focus on the start-up phase, this embodiment extends monitoring to the engine operation phase and covers key dimensions: On the one hand, it clarifies the specific composition of the first engine tier group (including sub-engines one, four, and seven) and the second engine tier group (including sub-engines two, three, five, and six), enabling grouped and precise monitoring of multiple engines; on the other hand, the operating data covers speed (first speed, second speed), vibration (first vibration value, second vibration value), and thrust index; speed directly reflects the engine's power output state, vibration value is related to the safety of the rocket body structure, and thrust determines the rocket body's attitude stability. The combination of these three forms a full-dimensional monitoring system of power-structure-attitude, which can capture potential risks such as abnormal speed fluctuations, excessive vibration, and thrust imbalance in real time, avoiding the problem of missed fault detection caused by the lack of continuous monitoring after start-up in traditional solutions.

[0196] Through multi-step quantitative calculations, operational data is transformed into precise fuel adjustment commands, addressing the pain point of insufficient precision in traditional experience-based adjustments. For the first engine, a first fuel adjustment amount is calculated based on the speed deviation to ensure that the power output matches the target speed; then, a second fuel adjustment amount is obtained based on the vibration deviation to suppress excessive vibration; by determining the fuel adjustment amount for the first engine, the dual objectives of power assurance and vibration control are achieved.

[0197] The second engine uses the same logic, calculating and superimposing values ​​based on speed and vibration correlations to obtain its fuel adjustment amount. This multi-dimensional calculation and superimposed adjustment method ensures that the fuel adjustment amount can accurately adapt to the real-time operating conditions of a single engine, while avoiding imbalances in other indicators caused by adjusting a single parameter, significantly improving the scientific nature and accuracy of parameter control.

[0198] By combining group monitoring and independent adjustments, the coordination among multiple engines is enhanced. The first and second tiers calculate fuel adjustment amounts based on their own operational data, ensuring coordinated operating parameters for each engine within a single group while also achieving thrust matching between the two groups through group adjustments. For example, when the thrust of the first tier is too low, its thrust is increased by increasing its fuel adjustment amount; when the vibration of the second tier exceeds the limit, vibration is reduced by fine-tuning the fuel while ensuring that the overall thrust of the two groups remains balanced. This avoids thrust imbalance caused by independent operation of multiple engines, further ensuring the attitude stability and structural safety of the rocket body during operation, and providing continuous support for the success of the launch mission.

[0199] In an optional embodiment of the present invention, step 161, adjusting the operating parameters of the first engine grading group and the second engine grading group according to the operating data, further includes:

[0200] Step 16121, according to Determine the total thrust of the first engine stage group;

[0201] in, ZTL 1 represents the total thrust of the first engine stage group. ZAT i For the thrust of each primary engine, i= 1,2 ,...c, c is The number of first engines;

[0202] Step 16122, according to Determine the total thrust of the second engine stage group;

[0203] in, ZTL 2 represents the total thrust of the second engine stage group. ZBT j For the thrust of each second engine, j=1,2 ,...v, v is The number of second engines;

[0204] Step 16123, if | ZTL 1- ZTL 2|> ZTL 3, and ZTL 1< ZTL 2, then according to YZT =| ZTL 1- ZTL 2|× h 1. Determine the thrust increase of the first engine;

[0205] in, ZTL 3. To set the thrust difference threshold, YZT This is the increase in thrust of the first engine. h 1 is the first increment coefficient;

[0206] Step 16124, if | ZTL 1- ZTL 2|> ZTL 3, and ZTL 1> ZTL 2, then according to EZT =| ZTL 1- ZTL 2|× h 2. Determine the thrust increase of the second engine;

[0207] in, EZT The increase in thrust for the second engine. h 2 is the second increase coefficient;

[0208] Step 16125, if ZAT i < ZTS According to YZT = ZTL 2 / ( c -1), determine the thrust increase of the first engine;

[0209] in, ZTS To set the thrust threshold, YZT This is the increase in thrust of the first engine. ZTL 2 represents the total thrust of the second engine stage group. i= 1,2 ,...c, c is The number of first engines;

[0210] Step 16126, if ZBT j < ZTS According to EZT = ZTL 1 / (v -1), determine the thrust increase of the second engine;

[0211] in, ZTS To set the thrust threshold, EZT The increase in thrust for the second engine. ZTL 1 represents the total thrust of the first engine stage group. j= 1,2 ,...v, v is The number of second engines;

[0212] Step 16127: Adjust according to the thrust increase of the first engine or the thrust increase of the second engine;

[0213] The operational data includes the thrust of the first engine and the thrust of the second engine.

[0214] In this example, compared to the traditional approach that focuses only on the thrust of a single engine, this embodiment first calculates the total thrust of the first and second engine tiers in steps 16121 and 16122, respectively, to achieve dual-layer thrust monitoring of single engine and tiered groups. This design can quickly locate two types of thrust anomalies: one is the overall thrust difference between the two groups, and the other is insufficient thrust of a single engine. It avoids the blind spot in traditional monitoring where the parameters of a single engine are normal but the imbalance of the group is ignored, providing accurate data for subsequent adjustments and reducing the risk of rocket attitude disturbance caused by thrust imbalance from the source.

[0215] For different thrust anomaly scenarios, the embodiments have formulated targeted adjustment schemes to avoid the limitations of a one-size-fits-all approach. On the one hand, when the total thrust difference between the two groups exceeds the limit, thrust is supplemented as needed through steps 16123 and 16124: the supplementation amount is precisely controlled to avoid over-adjustment leading to new imbalances. On the other hand, when the thrust of a single engine is insufficient, steps 16125 and 16126 adopt a group compensation logic: if the thrust of a certain first engine is insufficient, the other engines in the same group will share the supplementation, ensuring that the failure of a single engine does not affect the total thrust of the group, thus avoiding the limitations of single-engine adjustment and ensuring the stability of the group thrust.

[0216] The adjustment strategy, based on overall balance, enhances the synergy between the two engine groups. When the total thrust of the two groups becomes unbalanced, targeted thrust supplementation quickly reduces the thrust difference, preventing the rocket from tilting due to uneven thrust between groups. When the thrust of a single engine is insufficient, other engines in the same group compensate to maintain the total thrust of the group matching that of the other group, ensuring continuous and balanced thrust support for the rocket. This design not only solves the overall imbalance between groups but also addresses localized problems caused by single engine failures, completely eliminating the thrust runaway risk of traditional multi-engine independent operation. This provides crucial assurance for the attitude stability of the rocket during operation, further improving the reliability of launch missions.

[0217] Example 1

[0218] Example 1 provides a starting control method for the engine of a liquid-fueled launch vehicle, including:

[0219] Step 21, Basic parameter settings:

[0220] The core parameters (including hardware configuration, baseline threshold, and correction coefficient) for the two engine classification groups are defined as follows:

[0221]

[0222] Step 22, staggered start-up tiered group:

[0223] First, the start command of the first engine grade group (sub-engines 1, 4, and 7) is triggered. After an interval of 0.2 seconds, the start command of the second engine grade group (sub-engines 2, 3, 5, and 6) is triggered.

[0224] T =0s: Send a start-up enable signal to the first grade group to begin the component action timing stage;

[0225] T =0.2s: Send a start-up enable signal to the second group to avoid a sudden drop in pipeline pressure or overload of power supply caused by the simultaneous start-up of the two groups;

[0226] Step 23, Obtain startup data:

[0227] The engine sensors collect core starting data for the two stages in real time, with the specific values ​​as follows:

[0228]

[0229] The pipeline pressures are all within the normal threshold (2.0-3.0 MPa), therefore the pressure correction factor is... Y 11 = Y 21 =1.0 (no correction);

[0230] Step 24, determine the timing of component actions:

[0231] Based on the startup data (fuel temperature, pipeline pressure), the final action sequence of each component in the two stages is calculated using formulas, taking the first stage as an example (the calculation logic is the same for the second stage):

[0232] First-level group timing calculation:

[0233] Calculate the first temperature compensation delay: W 11=[(288−283) / 5]×0.05=1×0.05=0.05s. Since the fuel temperature is lower than the baseline, a delay of 0.05s is required to ensure that the fuel is fully atomized.

[0234] The timing sequence of each component was calculated, and the results are shown in the table below:

[0235]

[0236] Step 25, Obtain runtime data:

[0237] After the two groups of tiered groups complete the start-up ( T =5s), collect the operating data (speed, vibration, thrust) of each engine, as follows:

[0238] First Engine Classification Group (Sub-engines 1, 4, and 7):

[0239]

[0240] Second engine grading group (sub-engines two, three, five, and six):

[0241]

[0242] Step 26, adjust the operating parameters:

[0243] Based on operational data, operating parameters are adjusted from two dimensions: fuel adjustment and thrust balance, to ensure stable engine operation.

[0244] First Engine Stage Group Fuel Adjustment:

[0245] One extension ( i =1): First fuel adjustment amount (affected by engine speed): RL 11 ==0.02×(16500−16000)+0.01×(18000−16500)=0.02×500+0.01×1500=10+15=25 (unit: mL / s, the same below);

[0246] Second fuel adjustment (vibration effect): RL 21 ==0.03×(5−3.5)+0.02×(3.5−2)=0.03×1.5+0.02×1.5=0.045+0.03=0.075 (Since the vibration is normal, the adjustment amount is extremely small and can be ignored as 0).

[0247] Total fuel adjustment: RL 31 =25+0=25 (25mL / s of fuel needs to be added to maintain a stable rotation speed);

[0248] Four-part machine ( i =2): RL 12 =0.02×(17800−16000)+0.01×(18000−17800)=0.02×1800+0.01×200=36+2=38;

[0249] RL 22 =0.03×(5−4.2)+0.02×(4.2−2)=0.03×0.8+0.02×2.2=0.024+0.044=0.068 (ignored);

[0250] RL 32 =38+0=38 (38mL / s of fuel needs to be added);

[0251] Seven-point machine ( i =3): RL 13 =0.02×(15800−16000)+0.01×(18000−15800)=0.02×(−200)+0.01×2200=−4+22=18;

[0252] RL 23 =0.03×(5−5.5)+0.02×(5.5−2)=0.03×(−0.5)+0.02×3.5=−0.015+0.07=0.055 (The vibration is slightly high and needs to be fine-tuned. Calculate based on 0.1).

[0253] RL 33 =18+0.1=18.1 (18.1 mL / s of fuel needs to be added to increase the rotational speed and suppress vibration).

[0254] Second engine stage group fuel adjustment:

[0255] With two separate units ( j Taking 1 as an example, the logic for the other extensions is the same:

[0256] RL 41 =0.02×(17200−16000)+0.01×(18000−17200)=0.02×1200+0.01×800=24+8=32;

[0257] RL 51 =0.03×(5−3.0)+0.02×(3.0−2)=0.03×2+0.02×1=0.06+0.02=0.08 (neglected)

[0258] RL 61 =32+0=32 (32mL / s of fuel needs to be added);

[0259] Thrust balance adjustment:

[0260] Calculate the total thrust of the two-stage groups:

[0261] Total thrust of the first stage group: ZTL 1 = 90 + 105 + 75 = 270 kN;

[0262] Total thrust of the second stage group: ZTL 2 = 95 + 100 + 92 + 98 = 385 kN;

[0263] Total thrust deviation adjustment:

[0264] Absolute value of deviation: | ZTL 1- ZTL 2|=115kN> ZTL 3 = 30kN, and ZTL 1-< ZTL 2;

[0265] Increase in thrust of the first engine: YZT =∣ ZTL 1- ZTL 2 | × h 1 = 115 × 0.3 = 34.5 kN;

[0266] Adjustment for insufficient thrust from a single engine:

[0267] Seven-part thrust ZAT 3 = 75kN ZTS =80kN, thrust compensation is required;

[0268] Compensation amount: EZT = ZTL 1 / ( v -1) = 198.5kN.

[0269] This invention comprehensively addresses the pain points of traditional start-up schemes through multi-stage optimization and quantitative control, significantly improving launch safety and reliability. During the start-up phase, two sets of engines are started staggered by 0.2 seconds. Combining real-time collected fuel temperature and pipeline pressure data, and using temperature compensation delay and pressure correction coefficient formulas, the timing sequence of 10 types of components, including the turbine starter and various valves, is precisely adjusted to adapt to high and low temperatures and pressure fluctuations, avoiding false triggering and thrust imbalance, and reducing rocket vibration. During operation, monitoring extends to speed, vibration, and thrust, covering a grouped monitoring system for engines one through seven, enabling real-time anomaly detection. By calculating fuel adjustment amounts across multiple dimensions (combined with speed and vibration deviations), dual control of power and vibration is achieved. Furthermore, through total thrust calculation and differentiated adjustments (directional supplementation for inter-group imbalances and group compensation for single-engine deficiencies), thrust balance between the two sets is ensured, preventing rocket tilting. This completely overcomes the limitations of traditional fixed control and independent operation, comprehensively improving launch success rate.

[0270] like Figure 2 As shown, an embodiment of the present invention also provides a starting control device 20 for the engine of a liquid-fueled launch vehicle, comprising:

[0271] The acquisition module 21 is used to acquire the start-up data of the first engine stage group and the second engine stage group in the multi-stage parallel engine of the staggered start liquid launch vehicle;

[0272] The processing module 22 is used to determine the action sequence of the first component group of the first engine stage group and the action sequence of the second component group of the second engine stage group based on the start-up data; and to control the start-up of the multi-stage parallel engines of the liquid launch vehicle according to the action sequence.

[0273] Optionally, the first engine stage group and the second engine stage group in the multi-stage parallel engine of the liquid-fueled launch vehicle with staggered start-up include:

[0274] Using the master command as the time reference, start the first engine stage group;

[0275] After setting the set time interval, start the second engine stage group;

[0276] The set time interval is the time interval between the start-up sequence of the first engine stage group and the start-up sequence of the second engine stage group.

[0277] Optionally, the starting data of the first engine stage group includes: first fuel temperature and first pipeline pressure;

[0278] The starting data for the second engine stage group includes: second fuel temperature and second pipeline pressure;

[0279] The first component group includes: a first turbine starter, a first oxygen auxiliary valve, a first flare igniter, a first methane auxiliary valve, a first oxygen main valve starting chamber, a first methane discharge valve, a first oxygen discharge valve, a first methane main valve, a first oxygen main valve, and a first oxygen auxiliary valve;

[0280] The second component group includes: a second turbine starter, a second oxygen auxiliary valve, a second flare igniter, a second methane auxiliary valve, a second oxygen main valve starting chamber, a second methane discharge valve, a second oxygen discharge valve, a second methane main valve, a second oxygen main valve, and a second oxygen auxiliary valve.

[0281] Based on the starting data, the operating timing sequence of the first component group of the first engine stage group and the operating timing sequence of the second component group of the second engine stage group are determined, including:

[0282] Based on the first fuel temperature and the first pipeline pressure, determine the operating sequence of the first turbine starter, the first oxygen auxiliary valve, the first flare igniter, the first methane auxiliary valve, the first oxygen main valve starting chamber, the first methane discharge valve, the first oxygen discharge valve, the first methane main valve, the first oxygen main valve, and the first oxygen auxiliary valve.

[0283] Based on the second fuel temperature and the second pipeline pressure, determine the operating sequence of the second turbine starter, the second oxygen auxiliary valve, the second flare igniter, the second methane auxiliary valve, the second oxygen main valve starting chamber, the second methane discharge valve, the second oxygen discharge valve, the second methane main valve, the second oxygen main valve, and the second oxygen auxiliary valve.

[0284] Optionally, based on the first fuel temperature and the first pipeline pressure, the operating sequence of the first turbine starter, the first oxygen auxiliary valve, the first flare igniter, the first methane auxiliary valve, the first oxygen main valve starting chamber, the first methane discharge valve, the first oxygen discharge valve, the first methane main valve, the first oxygen main valve, and the first oxygen auxiliary valve is determined, including:

[0285] according to W 11 =[( W 12 - W 13 ) / W 14 ]× K 1. Determine the first temperature compensation delay;

[0286] in, W 11 For the first temperature compensation delay, W 12 The first reference temperature, W 13 The first fuel temperature, W 14 The step size is calculated for the first temperature. K1 represents the first temperature compensation coefficient;

[0287] according to Determine the first pressure correction factor;

[0288] in, Y 11 This is the first pressure correction factor. Y 12 Set the first parameter. Y 13 Set the second parameter. Y 14 Set parameters for the third one. L 11 For the first pipeline pressure, L 12 Set parameters for the fourth one. L 13 Set parameters for the fifth one;

[0289] according to t 20 = ( t 10 + W 11 )× Y 11 Determine the operating timing of the first turbine starter;

[0290] in, t 20 The operating sequence of the first turbine starter. t 10 The timing sequence for the first turbine starter;

[0291] according to t 21 = ( t 11 + W 11 )× Y 11 Determine the operating timing of the first oxygen auxiliary valve;

[0292] in, t 21 The operating sequence of the first oxygen auxiliary valve, t 11 The timing sequence for setting the first oxygen auxiliary valve;

[0293] according to t 22 = ( t 12 + W 11 )× Y 11Determine the timing sequence of the first torch igniter;

[0294] in, t 22 The timing sequence of the first igniter's actions. t 12 The timing sequence for the first torch igniter;

[0295] according to t 23 = ( t 13 + W 11 )× Y 11 Determine the operating timing of the first methane auxiliary valve;

[0296] in, t 23 The operating sequence of the first methane auxiliary valve, t 13 The timing sequence for setting the first methane auxiliary valve;

[0297] according to t 24 = ( t 14 + W 11 )× Y 11 Determine the operating timing of the first oxygen main valve starting chamber;

[0298] in, t 24 This refers to the operating sequence of the first oxygen main valve starting chamber. t 14 The timing sequence for setting the starting chamber of the first oxygen main valve;

[0299] according to t 25 = ( t 15 + W 11 )× Y 11 Determine the timing of the first methane discharge valve's operation;

[0300] in, t 25 The operating sequence of the first methane discharge valve. t 15 The timing sequence for setting the first methane discharge valve;

[0301] according to t 26 = ( t 16 +W 11 )× Y 11 Determine the timing of the first oxygen release valve's operation;

[0302] in, t 26 The timing sequence for the operation of the first oxygen release valve. t 16 The timing sequence for setting the first oxygen vent valve;

[0303] according to t 27 = ( t 17 + W 11 )× Y 11 Determine the operating timing of the first methane main valve;

[0304] in, t 27 The operating sequence of the first methane main valve, t 17 The timing sequence for setting the first methane main valve;

[0305] according to t 28 = ( t 18 + W 11 )× Y 11 Determine the operating sequence of the first oxygen main valve;

[0306] in, t 28 The operating sequence of the first oxygen main valve. t 18 The timing sequence for setting the first oxygen main valve;

[0307] according to t 29 = ( t 19 + W 11 )× Y 11 Determine the operating timing of the first oxygen auxiliary valve;

[0308] in, t 29 The operating sequence of the first oxygen auxiliary valve, t 19 This is the timing sequence for setting the first oxygen auxiliary valve.

[0309] Optionally, based on the second fuel temperature and the second pipeline pressure, the operating sequence of the second turbine starter, the second oxygen auxiliary valve, the second flare igniter, the second methane auxiliary valve, the second oxygen main valve starting chamber, the second methane discharge valve, the second oxygen discharge valve, the second methane main valve, the second oxygen main valve, and the second oxygen auxiliary valve is determined, including:

[0310] according to W 21 =[( W 22 - W 23 ) / W 24 ]× K 2. Determine the second temperature compensation delay;

[0311] in, W 21 For the second temperature compensation delay, W 22 The second reference temperature, W 23 The second fuel temperature, W 24 The step size is calculated for the second temperature. K 2 represents the second temperature compensation coefficient;

[0312] according to Determine the second pressure correction factor;

[0313] in, Y 21 This is the second pressure correction factor. Y 22 Set parameters for the sixth one. Y 23 Set parameters for the seventh one. Y 24 Set parameters for the eighth one. L 21 For the pressure of the second pipeline, L 22 Set parameters for the ninth one. L 23 Set parameters for the tenth;

[0314] according to t 40 = ( t 30 + W 21 )× Y 21 Determine the operating timing of the second turbine starter;

[0315] in, t 40The operating sequence of the second turbine starter. t 30 The timing sequence for the second turbine starter;

[0316] according to t 41 = ( t 31 + W 21 )× Y 21 Determine the operating timing of the second oxygen auxiliary valve;

[0317] in, t 41 The operating sequence of the second oxygen auxiliary valve, t 31 The timing sequence for setting the second oxygen auxiliary valve;

[0318] according to t 42 = ( t 32 + W 21 )× Y 21 Determine the timing sequence of the second torch igniter;

[0319] in, t 42 The timing sequence of the second torch igniter. t 32 The timing sequence for the second torch igniter;

[0320] according to t 43 = ( t 33 + W 21 )× Y 21 Determine the operating timing of the second methane auxiliary valve;

[0321] in, t 43 The operating sequence of the second methane auxiliary valve, t 33 The timing sequence for setting the second methane auxiliary valve;

[0322] according to t 44 = ( t 34 + W 21 )× Y 21 Determine the operating timing of the second oxygen main valve starting chamber;

[0323] in, t 44 This refers to the operating sequence of the second oxygen main valve starting chamber. t 34 The timing sequence for setting the starting chamber of the second oxygen main valve;

[0324] according to t 45 = ( t 35 + W 21 )× Y 21 Determine the timing of the second methane discharge valve's operation;

[0325] in, t 45 The timing sequence for the operation of the second methane discharge valve. t 35 The timing sequence for setting the second methane discharge valve;

[0326] according to t 46 = ( t 36 + W 21 )× Y 21 Determine the timing of the second oxygen release valve's operation;

[0327] in, t 46 The timing sequence for the operation of the second oxygen release valve. t 36 The timing sequence for setting the second oxygen vent valve;

[0328] according to t 47 = ( t 37 + W 21 )× Y 21 Determine the operating timing of the second methane main valve;

[0329] in, t 47 The operating sequence of the second methane main valve, t 37 The timing sequence for setting the second methane main valve;

[0330] according to t 48 = ( t 38 + W 21 )× Y21 Determine the operating sequence of the second oxygen main valve;

[0331] in, t 48 The operating sequence of the second oxygen main valve. t 38 The timing sequence for setting the second oxygen main valve;

[0332] according to t 49 = ( t 39 + W 21 )× Y 21 Determine the operating timing of the second oxygen auxiliary valve;

[0333] in, t 49 The operating sequence of the second oxygen auxiliary valve. t 39 This is the timing sequence for setting the second oxygen auxiliary valve.

[0334] Optionally, this startup method also includes:

[0335] Obtain the operating data of the first engine classification group and the second engine classification group;

[0336] Based on the operating data, adjust the operating parameters of the first engine grade group and the second engine grade group.

[0337] Optionally, the first engine tier group includes at least two groups of first engines;

[0338] The second engine tier group includes: at least two groups of second engines;

[0339] The operating data includes: the first engine speed and the first vibration value, and the second engine speed and the second vibration value;

[0340] Based on the aforementioned operating data, adjust the operating parameters of the first engine stage group and the second engine stage group, including:

[0341] The operating parameters of the first engine and the second engine are adjusted based on the first rotational speed, the first vibration value, the second rotational speed, and the second vibration value.

[0342] It should be noted that this device is a device corresponding to the above method. All implementation methods in the above method embodiments are applicable to this embodiment and can achieve the same technical effect.

[0343] Embodiments of the present invention also provide a computing device, including: one or more processors; and a storage device for storing one or more programs, wherein when the one or more programs are executed by the one or more processors, the one or more processors implement the method described above. All implementations in the above method embodiments are applicable to this embodiment and can achieve the same technical effect.

[0344] Embodiments of the present invention also provide a computing device readable storage medium storing instructions that, when executed on a computing device, cause the computing device to perform the method described above. All implementations in the above method embodiments are applicable to this embodiment and can achieve the same technical effect.

[0345] Those skilled in the art will recognize that the units and algorithm steps of the various examples described in conjunction with the embodiments disclosed in this invention can be implemented in electronic hardware, or a combination of computing device software and electronic hardware. Whether these functions are implemented in hardware or software depends on the specific application and design constraints of the technical solution. Those skilled in the art can use different methods to implement the described functions for each specific application, but such implementations should not be considered beyond the scope of this invention.

[0346] Those skilled in the art will understand that, for the sake of convenience and brevity, the specific working processes of the systems, devices, and units described above can be referred to the corresponding processes in the foregoing method embodiments, and will not be repeated here.

[0347] In the embodiments provided by this invention, it should be understood that the disclosed apparatus and methods can be implemented in other ways. For example, the apparatus embodiments described above are merely illustrative. For instance, the division of units is only a logical functional division, and in actual implementation, there may be other division methods. For example, multiple units or components may be combined or integrated into another system, or some features may be ignored or not executed. Furthermore, the coupling or direct coupling or communication connection shown or discussed may be through some interfaces; the indirect coupling or communication connection between devices or units may be electrical, mechanical, or other forms.

[0348] The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the units can be selected to achieve the purpose of this embodiment according to actual needs.

[0349] In addition, the functional units in the various embodiments of the present invention can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit.

[0350] If the aforementioned functions are implemented as software functional units and sold or used as independent products, they can be stored in a computing device-readable storage medium. Based on this understanding, the technical solution of this invention, essentially, or the part that contributes to the prior art, or a portion of the technical solution, can be embodied in the form of a software product. This computing device software product is stored in a storage medium and includes several instructions to cause a computing device (which may be a personal computing device, a server, or a network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this invention. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, ROM, RAM, magnetic disks, or optical disks.

[0351] Furthermore, it should be noted that in the apparatus and method of the present invention, it is obvious that the components or steps can be decomposed and / or recombined. These decompositions and / or recombinations should be considered equivalent solutions of the present invention. Moreover, the steps performing the above-described series of processes can naturally be executed in the order described, but are not necessarily required to be executed in chronological order; some steps can be executed in parallel or independently of each other. Those skilled in the art will understand that all or any step or component of the method and apparatus of the present invention can be implemented in any computing device (including processors, storage media, etc.) or network of computing devices, in hardware, firmware, software, or a combination thereof. This is something that those skilled in the art can achieve using basic programming skills after reading the description of the present invention.

[0352] Therefore, the object of the present invention can also be achieved by running a program or a set of programs on any computing device. The computing device can be a known general-purpose device. Therefore, the object of the present invention can also be achieved simply by providing a program product containing program code implementing the method or apparatus. That is, such a program product also constitutes the present invention, and the storage medium storing such a program product also constitutes the present invention. Obviously, the storage medium can be any known storage medium or any storage medium developed in the future. It should also be noted that in the apparatus and method of the present invention, it is obvious that the components or steps can be decomposed and / or recombined. These decompositions and / or recombinations should be considered equivalent to the present invention. Furthermore, the steps performing the above series of processes can naturally be performed in the order described, but are not necessarily required to be performed in chronological order. Some steps can be performed in parallel or independently of each other.

[0353] The above description represents the preferred embodiments of the present invention. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A starting control method for the engine of a liquid-fueled launch vehicle, characterized in that, include: The first and second engine stages in a multi-stage parallel engine of a liquid-fueled launch vehicle with staggered start-up times; Dynamically acquire starting data of the first engine grade group and the second engine grade group; Based on the starting data, determine the operating sequence of the first component group of the first engine grade group and the operating sequence of the second component group of the second engine grade group. The starting of the multi-stage parallel engine of the liquid-fueled launch vehicle is controlled according to the aforementioned action timing. Among them, the first engine stage group and the second engine stage group in the multi-stage parallel engine of the staggered-start liquid launch vehicle include: Using the master command as the time reference, start the first engine stage group; After setting the set time interval, start the second engine stage group; Wherein, the set time interval is the time interval between the start-up sequence of the first engine stage group and the start-up sequence of the second engine stage group; The method of controlling the starting of the multi-stage parallel engines of the liquid-fueled launch vehicle according to the aforementioned action timing includes: Using the master command as the time reference, the starting of the first and second component groups of the multi-stage parallel engine of the liquid launch vehicle is controlled according to the action sequence.

2. The starting control method for the engine of a liquid-fueled launch vehicle according to claim 1, characterized in that, The starting data for the first engine stage group includes: first fuel temperature and first pipeline pressure; The starting data for the second engine stage group includes: second fuel temperature and second pipeline pressure; The first component group includes: a first turbine starter, a first oxygen auxiliary valve, a first flare igniter, a first methane auxiliary valve, a first oxygen main valve starting chamber, a first methane discharge valve, a first oxygen discharge valve, a first methane main valve, a first oxygen main valve, and a first oxygen auxiliary valve; The second component group includes: a second turbine starter, a second oxygen auxiliary valve, a second flare igniter, a second methane auxiliary valve, a second oxygen main valve starting chamber, a second methane discharge valve, a second oxygen discharge valve, a second methane main valve, a second oxygen main valve, and a second oxygen auxiliary valve. Based on the starting data, the operating timing sequence of the first component group of the first engine stage group and the operating timing sequence of the second component group of the second engine stage group are determined, including: Based on the first fuel temperature and the first pipeline pressure, determine the operating sequence of the first turbine starter, the first oxygen auxiliary valve, the first flare igniter, the first methane auxiliary valve, the first oxygen main valve starting chamber, the first methane discharge valve, the first oxygen discharge valve, the first methane main valve, the first oxygen main valve, and the first oxygen auxiliary valve. Based on the second fuel temperature and the second pipeline pressure, determine the operating sequence of the second turbine starter, the second oxygen auxiliary valve, the second flare igniter, the second methane auxiliary valve, the second oxygen main valve starting chamber, the second methane discharge valve, the second oxygen discharge valve, the second methane main valve, the second oxygen main valve, and the second oxygen auxiliary valve.

3. The starting control method for the engine of a liquid-fueled launch vehicle according to claim 2, characterized in that, Based on the first fuel temperature and the first pipeline pressure, the operating sequence of the first turbine starter, the first oxygen auxiliary valve, the first flare igniter, the first methane auxiliary valve, the first oxygen main valve starting chamber, the first methane discharge valve, the first oxygen discharge valve, the first methane main valve, the first oxygen main valve, and the first oxygen minor auxiliary valve is determined, including: according to W 11 =[( W 12 - W 13 ) / W 14 ]× K 1. Determine the first temperature compensation delay; in, W 11 For the first temperature compensation delay, W 12 The first reference temperature, W 13 The first fuel temperature, W 14 The step size is calculated for the first temperature. K 1 represents the first temperature compensation coefficient; according to Determine the first pressure correction factor; in, Y 11 This is the first pressure correction factor. Y 12 Set the first parameter. Y 13 Set the second parameter. Y 14 Set parameters for the third one. L 11 For the first pipeline pressure, L 12 Set parameters for the fourth one. L 13 Set parameters for the fifth one; according to t 20 =( t 10 + W 11 )× Y 11 Determine the operating timing of the first turbine starter; in, t 20 The operating sequence of the first turbine starter. t 10 The timing sequence for the first turbine starter; according to t 21 =( t 11 + W 11 )× Y 11 Determine the operating timing of the first oxygen auxiliary valve; in, t 21 The operating sequence of the first oxygen auxiliary valve, t 11 The timing sequence for setting the first oxygen auxiliary valve; according to t 22 =( t 12 + W 11 )× Y 11 Determine the timing sequence of the first igniter; in, t 22 The timing sequence of the first torch igniter. t 12 The timing sequence for the first torch igniter; according to t 23 =( t 13 + W 11 )× Y 11 Determine the operating timing of the first methane auxiliary valve; in, t 23 The operating sequence of the first methane auxiliary valve, t 13 The timing sequence for setting the first methane auxiliary valve; according to t 24 =( t 14 + W 11 )× Y 11 Determine the operating timing of the first oxygen main valve starting chamber; in, t 24 This refers to the operating sequence of the first oxygen main valve starting chamber. t 14 The timing sequence for setting the starting chamber of the first oxygen main valve; according to t 25 =( t 15 + W 11 )× Y 11 Determine the timing of the first methane discharge valve's operation; in, t 25 The operating sequence of the first methane discharge valve. t 15 The timing sequence for setting the first methane discharge valve; according to t 26 =( t 16 + W 11 )× Y 11 Determine the timing of the first oxygen release valve's operation; in, t 26 The timing sequence for the operation of the first oxygen release valve. t 16 The timing sequence for setting the first oxygen vent valve; according to t 27 =( t 17 + W 11 )× Y 11 Determine the operating timing of the first methane main valve; in, t 27 The operating sequence of the first methane main valve, t 17 The timing sequence for setting the first methane main valve; according to t 28 =( t 18 + W 11 )× Y 11 Determine the operating timing of the first oxygen main valve; in, t 28 The operating sequence of the first oxygen main valve, t 18 The timing sequence for setting the first oxygen main valve; according to t 29 =( t 19 + W 11 )× Y 11 Determine the operating timing of the first oxygen auxiliary valve; in, t 29 The operating sequence of the first oxygen auxiliary valve, t 19 This is the timing sequence for setting the first oxygen auxiliary valve.

4. The starting control method for the engine of a liquid-fueled launch vehicle according to claim 2, characterized in that, Based on the second fuel temperature and the second pipeline pressure, determine the operating sequence of the second turbine starter, second oxygen auxiliary valve, second flare igniter, second methane auxiliary valve, second oxygen main valve starting chamber, second methane discharge valve, second oxygen discharge valve, second methane main valve, second oxygen main valve, and second oxygen auxiliary valve, including: according to W 21 =[( W 22 - W 23 ) / W 24 ]× K 2. Determine the second temperature compensation delay; in, W 21 For the second temperature compensation delay, W 22 The second reference temperature, W 23 The second fuel temperature, W 24 The step size is calculated for the second temperature. K 2 represents the second temperature compensation coefficient; according to Determine the second pressure correction factor; in, Y 21 This is the second pressure correction factor. Y 22 Set parameters for the sixth one. Y 23 Set parameters for the seventh one. Y 24 Set parameters for the eighth one. L 21 For the pressure of the second pipeline, L 22 Set parameters for the ninth one. L 23 Set parameters for the tenth; according to t 40 =( t 30 + W 21 )× Y 21 Determine the operating timing of the second turbine starter; in, t 40 The operating sequence of the second turbine starter. t 30 The timing sequence for the second turbine starter; according to t 41 =( t 31 + W 21 )× Y 21 Determine the operating timing of the second oxygen auxiliary valve; in, t 41 The operating sequence of the second oxygen auxiliary valve, t 31 The timing sequence for setting the second oxygen auxiliary valve; according to t 42 =( t 32 + W 21 )× Y 21 Determine the timing sequence of the second torch igniter; in, t 42 The timing sequence of the second torch igniter. t 32 The timing sequence for the second torch igniter; according to t 43 =( t 33 + W 21 )× Y 21 Determine the operating timing of the second methane auxiliary valve; in, t 43 The operating sequence of the second methane auxiliary valve, t 33 The timing sequence for setting the second methane auxiliary valve; according to t 44 =( t 34 + W 21 )× Y 21 Determine the operating timing of the second oxygen main valve starting chamber; in, t 44 This refers to the operating sequence of the second oxygen main valve starting chamber. t 34 The timing sequence for setting the starting chamber of the second oxygen main valve; according to t 45 =( t 35 + W 21 )× Y 21 Determine the timing of the second methane discharge valve's operation; in, t 45 The timing sequence for the operation of the second methane discharge valve. t 35 The timing sequence for setting the second methane discharge valve; according to t 46 =( t 36 + W 21 )× Y 21 Determine the timing of the second oxygen release valve's operation; in, t 46 The timing sequence for the operation of the second oxygen vent valve. t 36 The timing sequence for setting the second oxygen vent valve; according to t 47 =( t 37 + W 21 )× Y 21 Determine the operating timing of the second methane main valve; in, t 47 The operating sequence of the second methane main valve, t 37 The timing sequence for setting the second methane main valve; according to t 48 =( t 38 + W 21 )× Y 21 Determine the operating timing of the second oxygen main valve; in, t 48 The operating sequence of the second oxygen main valve. t 38 The timing sequence for setting the second oxygen main valve; according to t 49 =( t 39 + W 21 )× Y 21 Determine the timing of the second oxygen auxiliary valve; in, t 49 The operating sequence of the second oxygen auxiliary valve. t 39 This is the timing sequence for setting the second oxygen auxiliary valve.

5. The starting control method for the engine of a liquid-fueled launch vehicle according to claim 1, characterized in that, Also includes: Obtain the operating data of the first engine classification group and the second engine classification group; Based on the operating data, adjust the operating parameters of the first engine grade group and the second engine grade group.

6. The starting control method for the engine of a liquid-fueled launch vehicle according to claim 5, characterized in that, The first engine tier group includes: at least two groups of first engines; The second engine tier group includes: at least two groups of second engines; The operating data includes: the first engine speed and the first vibration value, and the second engine speed and the second vibration value; Based on the aforementioned operating data, adjust the operating parameters of the first engine stage group and the second engine stage group, including: The operating parameters of the first engine and the second engine are adjusted based on the first rotational speed, the first vibration value, the second rotational speed, and the second vibration value.

7. A starting control device for the engine of a liquid-fueled launch vehicle, characterized in that, include: The acquisition module is used to dynamically acquire the start-up data of the first and second engine stages in the multi-stage parallel engines of a liquid launch vehicle that starts during off-peak periods. The processing module is used to determine the action sequence of the first component group of the first engine stage group and the action sequence of the second component group of the second engine stage group based on the start-up data; and to control the start-up of the multi-stage parallel engines of the liquid launch vehicle according to the action sequence. The staggered start-up of the first and second engine stages in the multi-stage parallel engines of the liquid launch vehicle includes: starting the first engine stage group with the master command as the time reference; and starting the second engine stage group after setting a set time interval; wherein the set time interval is the time interval between the start-up sequence of the first engine stage group and the start-up sequence of the second engine stage group. The method of controlling the starting of the multi-stage parallel engine of the liquid launch vehicle according to the action sequence includes: using the master command as the time reference, controlling the starting of the first component group and the second component group of the multi-stage parallel engine of the liquid launch vehicle according to the action sequence.

8. A computing device, characterized in that, include: One or more processors; A storage device for storing one or more programs that, when executed by one or more processors, cause the one or more processors to implement the method as described in any one of claims 1 to 6.

9. A computing device readable storage medium, characterized in that, The computing device readable storage medium stores a program that, when executed by a processor, implements the method as described in any one of claims 1 to 6.

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