A method and apparatus for controlling the fill pressure of a bipropellant system tank

Abstract

The application provides a kind of double-component propulsion system tank filling pressure control method and device, the method comprises: according to the filling propellant mass of double-component propulsion system on filling day, target orbit tank pressure and helium dissolution rate after orbit, determine helium air cushion filling pressure on filling day;According to helium air cushion filling pressure, determine helium filling mass on filling day;Obtain tank telemetry data of double-component propulsion system on the day of air supplement;According to the helium filling mass on filling day, tank telemetry data, filling propellant mass and helium dissolution rate on the day of air supplement, determine the filling helium temperature on filling day;According to the filling helium temperature on filling day, target orbit tank pressure and helium dissolution rate after orbit, determine tank air cushion adjustment pressure on the day of air supplement.The scheme can realize the quantitative control of tank target filling pressure within the effective control precision range.

Description

Technical Field

[0001] This invention relates to the field of space propulsion technology, and in particular to a method and apparatus for controlling the refueling pressure of a tank in a dual-component propulsion system. Background Technology

[0002] High-orbit satellites typically employ a dual-component propulsion system, completing orbit transfers through multiple maneuvers at apogee. Generally, the refueling pressure of the propellant tanks in a high-orbit satellite dual-component propulsion system meets the following requirements: 1) The oxygen and fuel tank pressures must both be higher than the initial replenishment pressure of the gas supply system. This prevents situations where one tank is replenished while the other is not after orbit insertion, leading to excessively large mixture ratio deviations in the initial orbit change phase. It also ensures sufficient pressure before the gas supply system is connected. 2) The oxygen and fuel tank pressures must not exceed the maximum operating pressure of the tanks. This prevents excessively high inlet pressure for the orbit control engine during the initial orbit change ignition phase, which could affect engine performance. 3) The pressure difference between the oxygen and fuel tanks should be minimal to avoid excessively large mixture ratio deviations during the initial orbit insertion and orbit change phases, which could also affect engine performance.

[0003] However, the propellant tank filling ratio for high-orbit satellites is generally above 90%. Under high filling ratios, factors such as changes in propellant density, dissolution of the tank cushion, and changes in the tank cushion temperature can all cause significant variations in tank pressure, leading to refueling pressures exceeding the expected range. This makes it difficult to effectively achieve quantitative control of the refueling pressure in the bi-component propulsion system of high-orbit satellites. Summary of the Invention

[0004] This invention provides a method and apparatus for controlling the refueling pressure of a tank in a dual-component propulsion system, which can achieve quantitative control of the target refueling pressure of the tank within an effective control accuracy range.

[0005] In a first aspect, the present invention provides a method for controlling the refueling pressure of a tank in a dual-component propulsion system, comprising:

[0006] The helium cushion refueling pressure on the refueling day is determined based on the propellant mass, target orbital tank pressure, and helium dissolution rate after orbital insertion of the bicomponent propulsion system on the refueling day.

[0007] The helium refueling mass on the refueling day is determined based on the helium cushion refueling pressure.

[0008] Acquire the tank telemetry data of the bi-component propulsion system on the gas replenishment day;

[0009] The helium loading temperature on the refueling day is determined based on the helium loading mass on the refueling day, the tank telemetry data, the propellant loading mass, and the helium dissolution rate on the replenishment day.

[0010] The tank cushion adjustment pressure for the refueling day is determined based on the helium temperature on the refueling day, the target orbital tank pressure, and the helium dissolution rate after orbital insertion.

[0011] Optionally, determining the helium cushion refueling pressure on the refueling day based on the propellant mass, target orbital tank pressure, and helium dissolution rate after orbital insertion of the bicomponent propulsion system on the refueling day includes:

[0012] A1: Set the initial helium cushion refueling pressure for the refueling date;

[0013] A2: Obtain the initial helium loading temperature, gas cushion volume in the tank, and saturated vapor pressure of the first propellant on the loading date; wherein, the gas cushion volume in the tank is calculated from the propellant mass, propellant density, and tank volume;

[0014] A3: The first helium refueling mass is calculated based on the initial helium cushion refueling pressure on the refueling day, the initial helium refueling temperature on the refueling day, the cushion volume in the tank, and the saturated vapor pressure of the first propellant.

[0015] A4: The expected pressure of the first tank after orbit insertion is calculated based on the tank temperature after orbit insertion, the helium volume after orbit insertion, the helium dissolution rate after orbit insertion, the mass of the first helium refueling, and the saturated vapor pressure of the first propellant.

[0016] A5: Determine whether the pressure of the first storage tank meets the target orbital storage tank pressure. If yes, determine that the initial helium cushion refueling pressure is the helium cushion refueling pressure on the refueling day; otherwise, return to step A1.

[0017] Optionally, the pressure of the first tank is determined by the following formula:

[0018]

[0019] Where P1 is the pressure of the first storage tank; η 轨 The helium solubility rate after orbit insertion; m He加 The mass of the first helium gas added; R is the gas constant; T He轨 V is the temperature of the storage tank after orbit insertion; He轨 p is the volume of helium gas after orbit insertion; 蒸加 The saturated vapor pressure of the first propellant.

[0020] Optionally, determining the helium refueling mass on the refueling day based on the helium cushion refueling pressure on the refueling day includes:

[0021] The first helium refueling mass obtained based on the helium cushion refueling pressure on the refueling day is determined as the helium refueling mass on the refueling day.

[0022] Optionally, determining the helium loading temperature on the refueling day based on the helium loading mass on the refueling day, the tank telemetry data, the propellant loading mass, and the helium dissolution rate on the replenishment day includes:

[0023] The tank pressure and propellant temperature before gas replenishment are determined from the telemetry data of the tank.

[0024] The theoretical maximum helium dissolution rate is determined based on the tank pressure before gas replenishment, the propellant temperature before gas replenishment, and the mass of the propellant being added.

[0025] The current amount of helium is determined based on the helium refueling mass on the refueling day, the helium dissolution rate on the replenishment day, and the theoretical maximum helium dissolution capacity.

[0026] The helium loading temperature on the loading day is determined based on the tank pressure before refueling, tank volume, propellant mass, current helium quantity, and second propellant saturated vapor pressure.

[0027] Optionally, the theoretical maximum helium solubility is determined by the following formula:

[0028]

[0029] Where, m 溶总 M is the theoretical maximum helium solubility; 推 p is the mass of propellant added; p is the tank pressure before gas replenishment; T is the propellant temperature before gas replenishment; a, b, and c are all empirical coefficients.

[0030] The current helium quantity is determined by the following formula:

[0031] m He补 =m He加 -η 补 ×m 溶总

[0032] Where, m He补 The current helium quantity; m He加 The mass of helium refueling on the refueling day; η 补 The helium dissolution rate on the replenishment day.

[0033] Optionally, determining the tank cushion adjustment pressure on the refueling day based on the helium temperature on the refueling day, the target orbital tank pressure, and the helium dissolution rate after orbital insertion includes:

[0034] S1: Set the initial tank air cushion adjustment pressure for the refueling day;

[0035] S2: Obtain the initial current helium quantity, the helium temperature on the refueling day, the gas cushion volume in the tank on the replenishment day, and the saturated vapor pressure of the second propellant;

[0036] The initial current helium quantity is calculated from the initial tank cushion adjustment pressure, the second propellant saturated vapor pressure, and the gas cushion volume in the tank on the replenishment day.

[0037] S3: Calculate the current total amount of helium based on the initial current helium quantity, the helium dissolution rate on the replenishment day, and the theoretical maximum helium dissolution on the replenishment day;

[0038] S4: Determine the amount of helium after orbit insertion based on the current total helium amount, the helium dissolution rate after orbit insertion, and the theoretical maximum helium dissolution amount;

[0039] S5: The expected pressure of the second propellant tank after orbit insertion is calculated based on the tank temperature after orbit insertion, the volume of helium after orbit insertion, the amount of helium after orbit insertion, and the saturated vapor pressure of the second propellant.

[0040] S6: Determine whether the pressure of the second tank meets the target inlet tank pressure. If yes, determine the initial tank air cushion adjustment pressure for the replenishment day as the tank air cushion adjustment pressure for the replenishment day; otherwise, return to step S1.

[0041] Optionally, the propellant includes an oxidizer and a fuel; the helium cushion refueling pressure on the refueling day includes the helium cushion refueling pressure in the oxygen path and the helium cushion refueling pressure in the fuel path on the refueling day; the tank cushion adjustment pressure on the replenishment day includes the tank cushion adjustment pressure in the oxygen path and the tank cushion adjustment pressure in the fuel path on the replenishment day.

[0042] In a second aspect, the present invention provides a tank filling pressure control device for a dual-component propulsion system, comprising:

[0043] The refueling day processing module is used to determine the helium cushion refueling pressure on the refueling day based on the propellant mass, target orbital tank pressure, and helium dissolution rate after orbital insertion of the bicomponent propulsion system on the refueling day; and to determine the helium refueling mass on the refueling day based on the helium cushion refueling pressure on the refueling day.

[0044] The acquisition module is used to acquire the tank telemetry data of the bi-component propulsion system on the gas replenishment day;

[0045] The replenishment day processing module is used to determine the helium temperature on the replenishment day based on the helium replenishment mass, the tank telemetry data, the propellant mass, and the helium dissolution rate on the replenishment day; and to determine the tank gas cushion adjustment pressure on the replenishment day based on the helium temperature on the replenishment day, the target orbital tank pressure, and the post-orbital helium dissolution rate.

[0046] Thirdly, embodiments of the present invention also provide a computing device, including a memory and a processor, wherein the memory stores a computer program, and when the processor executes the computer program, it implements the method described in any of the first aspects of this specification.

[0047] Fourthly, embodiments of the present invention also provide a computer-readable storage medium having a computer program stored thereon, which, when executed in a computer, causes the computer to perform the methods described in any of the first aspects of this specification.

[0048] This invention provides a method and apparatus for controlling the refueling pressure of a bicomponent propulsion system's propellant tank. The method determines the helium cushion refueling pressure on the refueling day based on the propellant mass, target orbital tank pressure, and post-orbital helium dissolution rate of the bicomponent propulsion system. Based on the helium cushion refueling pressure, the helium mass on the refueling day is determined. Then, based on the helium mass, tank telemetry data acquired on the replenishment day, propellant mass, and helium dissolution rate, the helium temperature on the refueling day is determined. Finally, based on the helium temperature, target orbital tank pressure, and post-orbital helium dissolution rate, the tank cushion adjustment pressure on the replenishment day is determined. Thus, by introducing the tank helium dissolution rate parameter, quantitative control of the tank refueling pressure can be effectively achieved within a certain accuracy range, effectively ensuring the stability of the satellite propulsion system during the initial launch and orbit insertion phase. Attached Figure Description

[0049] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0050] Figure 1 This is a flowchart of a method for controlling the refueling pressure of a bicomponent propulsion system tank, provided in an embodiment of the present invention.

[0051] Figure 2 This is a hardware architecture diagram of a computing device provided in an embodiment of the present invention;

[0052] Figure 3 This is a schematic diagram of the structure of a tank filling pressure control device for a dual-component propulsion system provided in an embodiment of the present invention. Detailed Implementation

[0053] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are some embodiments of the present invention, but not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0054] Because the propellant temperature, the helium temperature added to the tank, and the dissolution process of helium in the propellant after refueling are all subject to significant uncertainties, they are difficult to obtain accurately, making it difficult to achieve quantitative control of the tank refueling pressure in the bi-component propulsion system of high-orbit satellites.

[0055] Due to the uncertainties in propellant temperature, propellant gas state, and the dissolved state of the propellant gas within the tank during refueling, as well as the complexity of factors affecting tank pressure, the post-refueling pressure is difficult to predict. Therefore, it is impossible to provide a target refueling pressure based on the required orbital pressure. To address these issues, this invention, by extracting and quantifying the main influencing factors, introduces a helium dissolution rate parameter from the tank and designs an iterative calculation method based on daily telemetry data from the refueling period. This method comprehensively considers four main factors: propellant density variation, helium dissolution, air cushion pressure variations with temperature and mass, and propellant saturated vapor pressure. This provides an effective quantitative control method for the refueling pressure of a bicomponent propulsion system tank.

[0056] The following describes the specific implementation of the concept in this application.

[0057] Please refer to Figure 1 This invention provides a method for controlling the refueling pressure of a tank in a bicomponent propulsion system, the method comprising:

[0058] Step 100: Determine the helium cushion refueling pressure on the refueling day based on the propellant mass, target orbital tank pressure, and helium dissolution rate after orbital insertion of the bicomponent propulsion system on the refueling day.

[0059] Step 102: Determine the helium refueling mass on the refueling day based on the helium cushion refueling pressure;

[0060] Step 104: Obtain the tank telemetry data of the bicomponent propulsion system on the gas replenishment day;

[0061] Step 106: Determine the helium loading temperature on the refueling day based on the helium loading mass on the refueling day, the tank telemetry data on the replenishment day, the propellant loading mass, and the helium dissolution rate on the replenishment day;

[0062] Step 108: Determine the tank cushion adjustment pressure on the refueling day based on the refueling helium temperature, target orbital tank pressure, and helium dissolution rate after orbital insertion.

[0063] In this embodiment of the invention, the helium cushion refueling pressure on the refueling day is determined by the propellant mass, target orbital tank pressure, and helium dissolution rate after orbital insertion of the bi-component propulsion system on the refueling day. Based on the helium cushion refueling pressure, the helium mass on the refueling day is determined. Then, based on the helium mass on the refueling day, the tank telemetry data obtained on the replenishment day, the propellant mass, and the helium dissolution rate on the replenishment day, the helium temperature on the refueling day is determined. Finally, based on the helium temperature on the refueling day, the target orbital tank pressure, and the helium dissolution rate after orbital insertion, the tank cushion adjustment pressure on the replenishment day is determined. Thus, by introducing the tank helium dissolution rate parameter, quantitative control of the tank refueling pressure can be effectively achieved within a certain accuracy range, effectively ensuring the initial state of the satellite propulsion system during launch and orbit insertion, which is of great significance for the stable operation of the satellite propulsion system.

[0064] It should be noted that the propellant includes both oxidizer and fuel. The helium cushion filling pressure on the refueling day includes the helium cushion filling pressure in the oxygen circuit and the helium cushion filling pressure in the fuel circuit on the refueling day; the tank cushion adjustment pressure on the replenishment day includes the tank cushion adjustment pressure in the oxygen circuit and the tank cushion adjustment pressure in the fuel circuit on the replenishment day.

[0065] Specifically, the bipropellant propulsion system typically loads propellant and helium into the tank on the refueling day. Subsequently, on the replenishment day 2-3 days later, the helium pressure in the tank is adjusted based on telemetry data from the onboard telemetry (including tank pressure and temperature parameters). This invention achieves the target refueling pressure (i.e., the target orbital tank pressure) by setting the helium cushion refueling pressure on the refueling day and the tank cushion adjustment pressure on the replenishment day.

[0066] The following description Figure 1 The execution method of each step is shown.

[0067] For step 100, based on the propellant mass, target orbital tank pressure, and helium dissolution rate of the bicomponent propulsion system on the refueling day, the helium cushion refueling pressure on the refueling day is determined, including:

[0068] A1: Set the initial helium cushion refueling pressure p on the refueling day. He加0 ;

[0069] A2: Obtain the initial helium loading temperature T on the loading date. 气加0 Volume V of the air cushion inside the storage tank He加 and the saturated vapor pressure p of the first propellant 蒸加 Among them, the volume V of the air cushion inside the storage tank He加 It is calculated from the propellant mass, propellant density, and tank volume;

[0070] A3: Based on the initial helium cushion refueling pressure p on the refueling date He加0 The initial helium filling temperature T on the filling day 气加0 Volume V of the air cushion inside the storage tank He加 and the saturated vapor pressure p of the first propellant 蒸加 The mass m of the first helium injection was calculated. He加 ;

[0071] A4: Based on the tank temperature T after orbit insertion He轨 Volume V of helium after orbit insertion He轨 Helium solubility η after orbit insertion 轨 First helium refueling mass m He加 and the saturated vapor pressure p of the first propellant 蒸加 The expected pressure P1 of the first storage tank after orbit insertion was calculated.

[0072] A5: Determine if the pressure P1 of the first storage tank meets the target orbital insertion pressure. If so, determine the initial helium cushion refueling pressure p. He加0 Helium cushion refueling pressure p on refueling day He加 Otherwise, return to step A1.

[0073] Specifically, the temperature T for helium refueling 气加0 The ambient temperature of the day can be used. If the pressure P1 of the first storage tank is within ±0.05MPa of the target entry storage tank pressure, then the storage tank pressure requirement is confirmed to be met.

[0074] Air cushion volume inside the storage tank M 推 To add propellant mass, ρ 推加 To increase propellant density, V 贮箱 ρ is the volume of the storage tank. 推加 =f1(T 推加 ), T 推加 f1 represents the average temperature measured by a temperature sensor at the bottom of the propellant loading tank during the loading process, and f1 is the standard density formula for the propellant.

[0075] In one specific implementation, the pressure of the first tank is determined by the following formula:

[0076]

[0077] Where P1 is the pressure of the first storage tank; η 轨 m is the helium solubility rate after orbit insertion. He加 The mass of the first helium charge; R is the gas constant; T He轨 V represents the temperature of the storage tank after orbit insertion. He轨 p represents the volume of helium gas after orbit insertion. 蒸加 This is the saturated vapor pressure of the first propellant.

[0078] It should be noted that the tank temperature T after entering orbit He轨 The helium solubility η is given by the satellite's thermal control design. 轨 This can be obtained by statistically analyzing data from multiple injections, with 85% being the preferred value. He轨 From the storage tank volume V 贮箱 The volume of the propellant is obtained by subtracting its volume. The amount of propellant added is fixed, the propellant density varies with temperature, and the propellant temperature can also be obtained from telemetry. Therefore, the propellant volume can also be calculated.

[0079] In this invention, the helium cushion refueling pressure on the refueling day is quantitatively determined by comprehensively considering the changes in propellant density, helium dissolution rate after orbit insertion, changes in cushion pressure with temperature and mass, and propellant saturated vapor pressure, thus effectively ensuring the state of the satellite propulsion system in the initial stage of launch and orbit insertion.

[0080] In step 102, the helium refueling mass on the refueling day is determined based on the helium cushion refueling pressure on the refueling day, including:

[0081] The first helium refueling mass, obtained based on the helium cushion refueling pressure on the refueling day, is determined as the helium refueling mass on the refueling day.

[0082] For step 106, based on the helium refueling mass on the refueling day, the tank telemetry data on the replenishment day, the propellant mass, and the helium dissolution rate on the replenishment day, the helium refueling temperature on the refueling day is determined, including:

[0083] The tank pressure p and propellant temperature T before gas replenishment were determined from the tank telemetry data.

[0084] Based on the tank pressure p before gas replenishment, the propellant temperature T before gas replenishment, and the mass of propellant added M... 推 Determine the theoretical maximum helium solubility m 溶总 ;

[0085] Based on the helium refueling mass m on the refueling day He加 Helium solubility η per day of gas replenishment 补 And the theoretical maximum helium solubility m 溶总 Determine the current helium quantity m He补 ;

[0086] Based on the tank pressure p and tank volume V before gas replenishment 贮箱 Propellant mass M 推 Current helium quantity (m) He补 Second propellant saturated vapor pressure p 蒸补 Determine the helium refueling temperature T on the refueling day. 气加 .

[0087] It should be noted that the tank telemetry data includes the tank pressure and propellant temperature before replenishment on the replenishment day. He补 The amount of helium in the storage tank before adjusting the gas cushion pressure on the replenishment day; η 补 The helium dissolution rate on the refueling day can be obtained by statistically analyzing data from multiple refuelings, with 45% being the preferred value.

[0088] Because the amount of helium added to the tank on the refueling day is large, the average temperature of the helium actually added to the tank cannot be effectively assessed. Therefore, the temperature of the gas added on the refueling day needs to be corrected using the tank telemetry parameters from the replenishment day after the temperature inside the tank has reached equilibrium, in order to correct the actual mass of helium added to the tank. In this invention, the temperature of the helium added on the refueling day is further corrected by using the helium mass added on the refueling day, tank telemetry data, propellant mass added, and helium dissolution rate on the replenishment day.

[0089] In one specific implementation, the theoretical maximum helium solubility is determined by the following formula:

[0090]

[0091] Where, m 溶总 M represents the theoretical maximum helium solubility. 推 The mass of propellant added; p is the tank pressure before gas replenishment; T is the propellant temperature before gas replenishment; a, b, and c are all empirical coefficients;

[0092] The current amount of helium is determined by the following formula:

[0093] m He补 =m He加 -η 补 ×m 溶总

[0094] Where, m He补 m is the current amount of helium. He加 For the helium refueling mass per day; η 补 The helium dissolution rate on the replenishment day.

[0095] Specifically, by comparing the predicted pressure on the gas replenishment day with the actual telemetry pressure (P) on the satellite, the temperature of the gas added on the refueling day is adjusted to ensure that the predicted pressure on the gas replenishment day matches the actual telemetry pressure on the satellite.

[0096]

[0097] Daily air cushion volume in the air replenishment tank ρ 推补 =f1(T 气加 f1 is the formula for the standard density of propellant;

[0098] T is obtained by simultaneously solving the two formulas above. 气加 .

[0099] For step 108, based on the helium temperature on the refueling day, the target orbital tank pressure, and the helium dissolution rate after orbital insertion, determine the tank cushion adjustment pressure on the replenishment day, including:

[0100] S1: Set the initial tank air cushion adjustment pressure p on the replenishment day. He补0 ;

[0101] S2: Get the initial current helium quantity m He补 Helium refueling temperature T on the refueling day 气加 The volume of the air cushion in the daily air replenishment tank, V He补 Second propellant saturated vapor pressure p 蒸补 ;

[0102] Wherein, the initial current helium quantity m He补 The initial tank air cushion adjusts the pressure p He补0 The second propellant saturated vapor pressure p 蒸补 The volume of the air cushion in the daily air replenishment tank, V He补 Calculated;

[0103] S3: Based on the initial current helium quantity m He补 Helium solubility η per day of gas replenishment 补 Theoretical maximum helium solubility m on replenishment day 溶补 The current total amount of helium, m, is calculated. He总 ;

[0104] S4: Based on the current total helium amount m He总 Helium solubility η after orbit insertion 轨 And the theoretical maximum helium solubility m 溶总 After determining the helium quantity m after orbit insertion He轨 ;

[0105] S5: Based on the tank temperature T after orbit insertion He轨 Volume V of helium after orbit insertion He轨 Helium volume (m) after orbit insertion He轨 Second propellant saturated vapor pressure p 蒸补 The expected pressure P2 of the second tank after orbit insertion was calculated.

[0106] S6: Determine whether the pressure P2 of the second storage tank meets the target orbital insertion storage tank pressure. If so, determine the initial storage tank air cushion adjustment pressure p on the refueling day. He补0 Adjust the pressure of the tank air cushion for the replenishment day; otherwise, return to step S1.

[0107] In one specific implementation, the initial current helium quantity m He补 It is calculated using the following formula:

[0108] mHe补 =f2(p He补0 -p 蒸补 T 气加 V He补 f2 is the gas law provided in the publicly available literature; m He补 Determined by the replenishment pressure of the gas storage tank on the replenishment day;

[0109] Daily air cushion volume in the air replenishment tank ρ 推补 =f1(T 气加 f1 is the formula for the standard density of propellant;

[0110] m He总 =m He补 +η 补 ×m 溶补 ;

[0111] m He轨 =m He总 -η 轨 ×m 溶总 ;

[0112]

[0113] m 溶补 It is calculated based on the mass of propellant added and the temperature and pressure on the day of replenishment, using the helium dissolution formula given in the published literature;

[0114] If the pressure P2 in the second storage tank is within ±0.05 MPa of the target inlet storage tank pressure, then the storage tank pressure requirement is confirmed to be met. At this point, the initial storage tank air cushion adjustment pressure p on the replenishment day is... He补0 Adjust the tank air cushion pressure p on the replenishment day He补 .

[0115] The method of this invention can obtain relevant parameters entirely based on conventional refueling procedures and processes, and has excellent engineering feasibility. At the same time, this method can achieve quantitative control of tank refueling pressure within a certain accuracy range, effectively ensuring the state of the satellite propulsion system in the initial stage of launch and orbit insertion, which is of great significance to the stable operation of the satellite propulsion system.

[0116] like Figure 2 , Figure 3 As shown, this invention provides a device for controlling the refueling pressure of a tank in a dual-component propulsion system. The device can be implemented via software, hardware, or a combination of both. From a hardware perspective, as... Figure 2 The diagram shown is a hardware architecture diagram of a computing device housing a tank refueling pressure control device for a dual-component propulsion system according to an embodiment of the present invention. (Except for...) Figure 2In addition to the processor, memory, network interface, and non-volatile memory shown, the computing device in the embodiment may also include other hardware, such as a forwarding chip responsible for processing packets. Taking software implementation as an example, such as... Figure 3 As shown, a device in a logical sense is formed by the CPU of its computing device reading the corresponding computer program from the non-volatile memory into memory and running it. This embodiment provides a dual-component propulsion system tank refueling pressure control device, which includes:

[0117] The refueling day processing module 300 is used to determine the helium cushion refueling pressure on the refueling day based on the propellant mass, target orbital tank pressure, and helium dissolution rate after orbital insertion of the bicomponent propulsion system on the refueling day; and to determine the helium refueling mass on the refueling day based on the helium cushion refueling pressure on the refueling day.

[0118] The acquisition module 302 is used to acquire the tank telemetry data of the bicomponent propulsion system on the gas replenishment day;

[0119] The replenishment day processing module 304 is used to determine the helium temperature on the refueling day based on the helium refueling mass, the tank telemetry data on the replenishment day, the propellant mass, and the helium dissolution rate on the replenishment day; and to determine the tank gas cushion adjustment pressure on the replenishment day based on the helium temperature on the refueling day, the target orbital tank pressure, and the helium dissolution rate after orbital insertion.

[0120] In some specific implementations, the refueling daily processing module 300 can be used to perform the above steps 100 and 102, the acquisition module 302 can be used to perform the above step 104, and the gas replenishment daily processing module 304 can be used to perform the above steps 106 and 108.

[0121] In one embodiment of the present invention, the propellant includes an oxidizer and a fuel; the helium cushion refueling pressure on the refueling day includes the helium cushion refueling pressure in the oxygen path and the helium cushion refueling pressure in the fuel path on the refueling day; the tank cushion adjustment pressure on the replenishment day includes the tank cushion adjustment pressure in the oxygen path and the tank cushion adjustment pressure in the fuel path on the replenishment day.

[0122] In one embodiment of the present invention, the refueling day processing module 300 is further configured to perform the following operations:

[0123] A1: Set the initial helium cushion refueling pressure for the refueling day;

[0124] A2: Obtain the initial helium loading temperature, gas cushion volume inside the tank, and saturated vapor pressure of the first propellant on the loading date; wherein, the gas cushion volume inside the tank is calculated from the propellant mass, propellant density, and tank volume;

[0125] A3: The mass of the first helium refueling is calculated based on the initial helium cushion refueling pressure on the refueling day, the initial helium temperature on the refueling day, the volume of the cushion in the tank, and the saturated vapor pressure of the first propellant.

[0126] A4: The expected pressure of the first tank after orbit insertion is calculated based on the tank temperature after orbit insertion, the helium volume after orbit insertion, the helium dissolution rate after orbit insertion, the mass of the first helium refueling, and the saturated vapor pressure of the first propellant.

[0127] The pressure of the first storage tank is determined by the following formula:

[0128]

[0129] Where P1 is the pressure of the first storage tank; η 轨 m is the helium solubility rate after orbit insertion. He加 The mass of the first helium charge; R is the gas constant; T He轨 V represents the temperature of the storage tank after orbit insertion. He轨 p represents the volume of helium gas after orbit insertion. 蒸加 This is the saturated vapor pressure of the first propellant;

[0130] A5: Determine whether the pressure of the first storage tank meets the target orbital storage tank pressure. If yes, determine the initial helium cushion refueling pressure as the helium cushion refueling pressure on the refueling day, and determine the first helium refueling mass obtained based on the helium cushion refueling pressure on the refueling day as the helium refueling mass on the refueling day; otherwise, return to step A1.

[0131] In one embodiment of the present invention, the daily gas replenishment processing module 304 is further configured to perform the following operations:

[0132] The tank pressure and propellant temperature before gas replenishment were determined from the tank telemetry data.

[0133] The theoretical maximum helium dissolution rate is determined based on the tank pressure before gas replenishment, the propellant temperature before gas replenishment, and the mass of propellant added.

[0134] The theoretical maximum helium solubility is determined by the following formula:

[0135]

[0136] Where, m 溶总 M represents the theoretical maximum helium solubility. 推 The mass of propellant added; p is the tank pressure before gas replenishment; T is the propellant temperature before gas replenishment; a, b, and c are all empirical coefficients;

[0137] The current amount of helium is determined based on the helium refueling mass on the refueling day, the helium dissolution rate on the replenishment day, and the theoretical maximum helium dissolution capacity.

[0138] The current amount of helium is determined by the following formula:

[0139] m He补 =m He加 -η 补 ×m 溶总

[0140] Where, m He补 m is the current amount of helium. He加 For the helium refueling mass per day; η 补 To determine the helium solubility rate on the replenishment day;

[0141] The helium loading temperature on the loading day is determined based on the tank pressure before refueling, tank volume, propellant mass, current helium quantity, and saturated vapor pressure of the second propellant.

[0142] In one embodiment of the present invention, the daily gas replenishment processing module 304 is further configured to perform the following operations:

[0143] S1: Set the initial tank air cushion adjustment pressure for the replenishment day;

[0144] S2: Obtain the initial current helium quantity, the helium temperature on the refueling day, the gas cushion volume in the tank on the replenishment day, and the saturated vapor pressure of the second propellant;

[0145] The initial current helium quantity is calculated from the initial tank cushion adjustment pressure, the second propellant saturated vapor pressure, and the tank cushion volume on the replenishment day.

[0146] S3: Calculate the current total amount of helium based on the initial current helium quantity, the helium dissolution rate on the replenishment day, and the theoretical maximum helium dissolution on the replenishment day;

[0147] S4: Determine the amount of helium after orbit insertion based on the current total helium amount, the helium dissolution rate after orbit insertion, and the theoretical maximum helium dissolution amount;

[0148] S5: The expected pressure of the second propellant tank after orbit insertion is calculated based on the tank temperature, helium volume, helium quantity, and saturated vapor pressure of the second propellant after orbit insertion.

[0149] S6: Determine whether the pressure of the second tank meets the target inlet tank pressure. If yes, determine the initial tank air cushion adjustment pressure on the replenishment day as the tank air cushion adjustment pressure on the replenishment day; otherwise, return to step S1.

[0150] It is understood that the structures illustrated in the embodiments of the present invention do not constitute a specific limitation on a tank refueling pressure control device for a bicomponent propulsion system. In other embodiments of the present invention, a tank refueling pressure control device for a bicomponent propulsion system may include more or fewer components than illustrated, or combine some components, or split some components, or have different component arrangements. The illustrated components may be implemented in hardware, software, or a combination of software and hardware.

[0151] The information interaction and execution process between the modules in the above-mentioned device are based on the same concept as the method embodiment of the present invention, and the specific details can be found in the description of the method embodiment of the present invention, and will not be repeated here.

[0152] This invention also provides a computing device, including a memory and a processor. The memory stores a computer program, and when the processor executes the computer program, it implements a method for controlling the refueling pressure of a bicomponent propulsion system tank according to any embodiment of this invention.

[0153] This invention also provides a computer-readable storage medium storing a computer program, which, when executed by a processor, causes the processor to perform a method for controlling the refueling pressure of a bicomponent propulsion system tank according to any embodiment of this invention.

[0154] Specifically, a system or apparatus equipped with a storage medium may be provided, on which software program code implementing the functions of any of the embodiments described above is stored, and the computer (or CPU or MPU) of the system or apparatus may read and execute the program code stored in the storage medium.

[0155] In this case, the program code read from the storage medium can itself implement the function of any of the above embodiments, and therefore the program code and the storage medium storing the program code constitute part of the present invention.

[0156] Examples of storage media used to provide program code include floppy disks, hard disks, magneto-optical disks, optical disks (such as CD-ROM, CD-R, CD-RW, DVD-ROM, DVD-RAM, DVD-RW, DVD+RW), magnetic tapes, non-volatile memory cards, and ROMs. Alternatively, program code can be downloaded from a server computer via a communication network.

[0157] Furthermore, it should be clear that not only can the program code read by the computer be executed, but also the operating system on the computer can be instructed based on the program code to perform some or all of the actual operations, thereby realizing the function of any of the embodiments described above.

[0158] Furthermore, it is understood that the program code read from the storage medium is written to the memory set in the expansion board inserted into the computer or to the memory set in the expansion module connected to the computer. Then, based on the instructions of the program code, the CPU or other components installed on the expansion board or expansion module execute some and all of the actual operations, thereby realizing the function of any of the above embodiments.

[0159] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0160] Those skilled in the art will understand that all or part of the steps of the above method embodiments can be implemented by hardware related to program instructions. The aforementioned program can be stored in a computer-readable storage medium. When the program is executed, it performs the steps of the above method embodiments. The aforementioned storage medium includes various media that can store program code, such as ROM, RAM, magnetic disk, or optical disk.

[0161] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method of propellant tank pressurization control for a bipropellant propulsion system, characterized in that, The method comprises the steps of: determining the helium gas cushion filling pressure on the filling day according to the filling propellant mass of the bipropellant propulsion system on the filling day, the target orbit injection tank pressure and the helium gas solubility after orbit injection; determining the helium filling mass on the filling day according to the helium gas cushion filling pressure; obtaining the tank telemetry data of the bipropellant propulsion system on the gas supplement day; determining the filling helium temperature on the filling day according to the helium filling mass on the filling day, the tank telemetry data, the filling propellant mass and the helium solubility on the gas supplement day; determining the tank gas cushion adjustment pressure on the gas supplement day according to the filling helium temperature on the filling day, the target orbit injection tank pressure and the helium solubility after orbit injection.

2. The method of claim 1, wherein, The method for determining the helium gas cushion filling pressure on the filling day according to the filling propellant mass of the bipropellant propulsion system on the filling day, the target orbit injection tank pressure and the helium solubility after orbit injection comprises the steps of: A1: setting the initial helium gas cushion filling pressure on the filling day; A2: obtaining the preliminary filling helium temperature on the filling day, the gas cushion volume in the tank and the first propellant saturated vapor pressure; wherein the gas cushion volume in the tank is calculated from the filling propellant mass, the filling propellant density and the tank volume; A3: calculating the first helium filling mass according to the initial helium gas cushion filling pressure on the filling day, the preliminary filling helium temperature on the filling day, the gas cushion volume in the tank and the first propellant saturated vapor pressure; A4: calculating the predicted first tank pressure after orbit injection according to the tank temperature after orbit injection, the helium volume after orbit injection, the helium solubility after orbit injection, the first helium filling mass and the first propellant saturated vapor pressure; A5: determining whether the first tank pressure meets the target orbit injection tank pressure, if yes, determining that the initial helium gas cushion filling pressure is the helium gas cushion filling pressure on the filling day; otherwise, returning to step A1.

3. The method according to claim 2, wherein: the first tank pressure is determined by the following formula: wherein P1 is the first tank pressure; η 轨 is the post-maneuver helium solubility; m He加 is the first helium charge mass; R is the gas constant; T He轨 is the post-maneuver tank temperature; V He轨 is the post-maneuver helium volume; p 蒸加 is the first propellant saturation vapor pressure; and / or, the method for determining the helium filling mass on the filling day according to the helium gas cushion filling pressure on the filling day comprises: determining the first helium filling mass according to the helium gas cushion filling pressure on the filling day as the helium filling mass on the filling day.

4. The method of claim 1, wherein, the method for determining the filling helium temperature on the filling day according to the helium filling mass on the filling day, the tank telemetry data, the filling propellant mass and the helium solubility on the gas supplement day comprises the steps of: determining the tank pressure before gas supplement and the propellant temperature before gas supplement from the tank telemetry data; determining the theoretical maximum helium solubility according to the tank pressure before gas supplement, the propellant temperature before gas supplement and the filling propellant mass; determining the current helium amount according to the helium filling mass on the filling day, the helium solubility on the gas supplement day and the theoretical maximum helium solubility; determining the filling helium temperature on the filling day according to the tank pressure before gas supplement, the tank volume, the filling propellant mass, the current helium amount and the second propellant saturated vapor pressure.

5. The method according to claim 4, wherein: the theoretical maximum helium solubility is determined by the following formula: wherein m 溶总 is the theoretical maximum helium gas solubility; M 推 is the propellant mass charged; p is the tank pressure before gassing; T is the propellant temperature before gassing; a, b, c are empirical coefficients; The current helium amount is determined by the following formula: m He补 = m He加 - η 补 x m 溶总 wherein m He补 is the current helium amount; m He加 is the filling day helium filling mass; η 补 is the make-up day helium dissolution rate.

6. The method of claim 1, wherein, The tank gas cushion adjustment pressure on the refueling day is determined according to the refueling helium temperature on the refueling day, the target orbiting tank pressure and the post-orbiting helium dissolution rate, and comprises: S1: setting an initial tank gas cushion adjustment pressure on the refueling day; S2: obtaining an initial current helium amount, the refueling helium temperature on the refueling day, a gas cushion volume in the tank on the refueling day and a second propellant saturated vapor pressure; Wherein, the initial current helium amount is calculated from the initial tank gas cushion adjustment pressure, the second propellant saturated vapor pressure and the gas cushion volume in the tank on the refueling day; S3: calculating a current total helium amount according to the initial current helium amount, the post-orbiting helium dissolution rate and a theoretical maximum helium dissolution amount on the refueling day; S4: determining a post-orbiting helium amount according to the current total helium amount, the post-orbiting helium dissolution rate and the theoretical maximum helium dissolution amount; S5: calculating a predicted post-orbiting second tank pressure according to a post-orbiting tank temperature, a post-orbiting helium volume, the post-orbiting helium amount and the second propellant saturated vapor pressure; S6: judging whether the second tank pressure meets the target orbiting tank pressure, if yes, determining that the initial tank gas cushion adjustment pressure on the refueling day is the tank gas cushion adjustment pressure on the refueling day; otherwise, returning to step S1.

7. The method according to any one of claims 1 to 6, characterized in that, The propellant comprises an oxidizer and a combustion agent; the helium gas cushion refueling pressure on the refueling day comprises a helium gas cushion refueling pressure on the refueling day on an oxygen path and a helium gas cushion refueling pressure on the refueling day on a combustion path; and the tank gas cushion adjustment pressure on the refueling day comprises a tank gas cushion adjustment pressure on the refueling day on the oxygen path and a tank gas cushion adjustment pressure on the refueling day on the combustion path.

8. A bipropellant system tank pressurization control apparatus characterized by, Comprise: The refueling day processing module is configured to determine the helium gas cushion refueling pressure on the refueling day according to the refueling propellant mass on the refueling day, the target orbiting tank pressure and the post-orbiting helium dissolution rate of the dual-component propelling system, and determine the refueling helium mass on the refueling day according to the helium gas cushion refueling pressure on the refueling day; The obtaining module is configured to obtain tank telemetry data on the refueling day of the dual-component propelling system; The refueling day processing module is configured to determine the refueling helium temperature on the refueling day according to the refueling helium mass on the refueling day, the tank telemetry data, the refueling propellant mass and the helium dissolution rate on the refueling day, and determine the tank gas cushion adjustment pressure on the refueling day according to the refueling helium temperature on the refueling day, the target orbiting tank pressure and the post-orbiting helium dissolution rate. 9.A computing device comprising a memory and a processor, wherein the memory stores a computer program, and the processor executes the computer program to implement the method according to any one of claims 1-7. 10.A computer readable storage medium storing a computer program, wherein the computer program, when executed in a computer, causes the computer to perform the method according to any one of claims 1-7.

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