Propellant regulating method and system for unbalanced discharge of bipropellant

Abstract

The application provides a propellant adjusting method and system for unbalanced discharge of two-component propellant, comprising the following steps: S1, adapting to the offset of the satellite center of mass by adjusting the working time of each direction thruster when the thruster is working, and obtaining the offset of the satellite center of mass through feedback; S2, calculating the propellant mass of each tank of the satellite after the thruster is working according to the offset of the satellite center of mass; and S3, analyzing and determining the propellant transfer direction and transfer mass which can satisfy the target correction amount of the satellite center of mass according to the current propellant mass of each tank and the target correction amount of the satellite center of mass. The application realizes the balanced distribution of the propellant mass of each tank of the satellite and the optimized adjustment of the satellite center of mass by adjusting the temperature difference between different tanks and the valve control logic of the propellant system, which is beneficial to the attitude control of the satellite.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of spacecraft propulsion and thermal control, in particular, to a propellant adjustment method and system for unbalanced discharge of dual-component propellant; more particularly, to a propellant distribution adjustment method and system for unbalanced discharge of dual-component propellant of a satellite. BACKGROUND

[0002] With the increase of satellite on-orbit life requirement and the application of large-thrust engines, the weight of satellite carrying propellant is increasing, so that a multi-tank parallel propulsion system is widely used, that is, the same propellant is stored in multiple parallel tanks. According to the working mode of on-orbit thruster, the multi-tank parallel propulsion system can adopt a mode of simultaneous supply of propellant by parallel tanks, or a mode of independent supply of propellant by single tank, and in the process of use, the problem of unbalanced discharge of propellant will occur, and in the extreme case, even the problem of emptying of propellant in part of the tank will occur. Unbalanced discharge of propellant will cause the shift of satellite center of mass, affect the attitude control of the satellite, produce additional consumption of propellant, and in severe cases, may lead to loss of control of the satellite attitude.

[0003] In order to solve the problem of unbalanced discharge of dual-component propellant of a satellite, the residual amount of propellant in each tank is usually measured indirectly or directly, the valve of the propulsion system is controlled before each ignition, and the tank with large residual amount of propellant is selectively selected to supply propellant, so as to adopt a mode of artificial unbalanced discharge to adjust the deviation of residual amount of propellant and the distribution of center of mass among the tanks. By using this passive consumption adjustment method, before and after each ignition of the satellite, the supply strategy and valve control strategy of the propulsion system are analyzed and adjusted according to the satellite attitude, the measured data of the center of mass, the ignition time and other conditions, and the implementation process is complex, the adjustment capacity is limited, and there is a problem of waste of propellant. SUMMARY

[0004] In view of the defects in the prior art, the purpose of the present application is to provide a propellant adjustment method and system for unbalanced discharge of dual-component propellant.

[0005] According to the propellant adjustment method for unbalanced discharge of dual-component propellant provided by the present application, the method comprises the following steps:

[0006] Step S1: by adjusting the working time of each direction thruster when the thruster is working, the shift of the center of mass of the satellite is adapted, and the shift amount of the center of mass of the satellite is fed back;

[0007] Step S2: according to the shift amount of the center of mass of the satellite, the propellant mass of each tank of the satellite after the thruster is working is calculated;

[0008] Step S3: Based on the current propellant mass of each tank and the satellite's center of mass target correction amount, analyze and determine the propellant transfer direction and transfer mass that meet the satellite's center of mass target correction amount.

[0009] Preferably, in step S1:

[0010] Based on the working time of the thrusters in each direction during satellite thruster operation, the fuel and oxidizer usage ΔMo and ΔMf, as well as the actual centroid offset of the satellite (ΔX, ΔY, ΔZ) are calculated.

[0011] The thrusters are positioned at different locations on the satellite, and are symmetrically distributed with respect to the satellite's center of mass.

[0012] If the propellant discharge is uneven, the satellite's center of mass will shift. Based on the operating time of the thrusters in each position of the satellite, the shift distance of the satellite's center of mass in the X, Y, and Z directions can be calculated.

[0013] The satellite includes a corresponding control system for controlling the switching on and off of the heaters and valves.

[0014] Preferably, in step S2:

[0015] By combining the propellant usage amounts ΔMo and ΔMf, the satellite's center of mass offset (ΔX, ΔY, ΔZ), and the satellite's layout, mass characteristics, and initial propellant loading amount, the propellant mass of each tank in the current propulsion system is obtained. This allows for the determination of whether uneven propellant discharge has occurred during thruster operation and whether propellant mass distribution adjustment is necessary to correct the satellite's center of mass. If the satellite's center of mass offset (ΔX, ΔY, ΔZ) is less than the preset standard, no propellant mass distribution adjustment is required.

[0016] The propellant consists of two components: fuel and oxidant.

[0017] The storage tanks are divided into fuel tanks and oxidizer tanks, and each type of tank is symmetrically distributed with respect to the center of mass of the satellite.

[0018] Each tank is equipped with a heater, which is a polyimide film type electric heating element.

[0019] Each tank has a thermistor attached to its surface for monitoring the tank temperature;

[0020] The tank pressure and tank temperature are positively correlated. By controlling the turn-on time of the heaters in each tank, the temperature of each tank can be controlled, thereby controlling the pressure of each tank. After opening the connecting valve between the tanks, the propellant is transferred from the high-pressure tank to the low-pressure tank until the pressure between the tanks reaches equilibrium.

[0021] Preferably, in step S3:

[0022] Based on the current propellant mass of each tank and the target correction amount (ΔX', ΔY', ΔZ') of the satellite's center of mass, and combined with the satellite layout and mass characteristics, the propellant transfer direction and transfer mass (ΔMpo, ΔMpf) that satisfy the target correction amount (ΔX', ΔY', ΔZ') of the satellite's center of mass are analyzed and determined.

[0023]

[0024] T o ′1=k×T o1 ×(M ofull -M o1 -ΔM po )

[0025] T o ′2=k×T o2 ×(M ofull -M o2 +ΔM po )

[0026] Among them, M o1 M o2 The propellant masses of oxygen tank 1 and oxygen tank 2 are ΔM and ΔM, respectively. po M represents the mass of propellant to be transferred from oxygen tank 1 to oxygen tank 2, k is a selected adjustment coefficient, freely chosen between 0.9 and 1.1, and M... ofull T' represents the propellant mass when the oxygen tank is full of propellant, To1 and To2 represent the current temperatures of oxygen tank 1 and oxygen tank 2, respectively. o1 、T′ o2 These are the adjusted temperatures of oxygen chamber 1 and oxygen chamber 2, respectively.

[0027] After the propellant is transferred between the tanks, the connecting valve between the tanks of the same type of propellant is closed, and the temperature control heater threshold of the tank from which the propellant is transferred is lowered to be consistent with the temperature control heater threshold of the tank receiving the propellant. After the temperature of the tanks of the same type of propellant is consistent, the connecting valve between the tanks of the same type of propellant is opened.

[0028] Preferably, based on the propellant transfer direction and transfer quality, and combined with the current temperature and pressure levels of each tank, the temperature level of the tank from which propellant needs to be transferred is raised by increasing the temperature control heater threshold. As the tank temperature rises, the corresponding tank pressure also rises, creating a temperature and pressure difference between the tank and the tanks whose heater thresholds have not been adjusted. The connecting valve between tanks of the same type of propellant is opened, and the propellant transfer is achieved by utilizing the pressure difference between the tanks.

[0029] A propellant regulation system for addressing uneven emission of bicomponent propellants, provided by the present invention, comprises:

[0030] Module M1: By adjusting the working time of the thrusters in each direction during operation, it adapts to the shift of the satellite's center of mass and provides feedback on the satellite's center of mass shift.

[0031] Module M2: Based on the satellite's center of mass offset, calculate the propellant mass of each tank after the thrusters operate;

[0032] Module M3: Based on the current propellant mass of each tank and the satellite's center of mass target correction amount, analyze and determine the propellant transfer direction and transfer mass that meet the satellite's center of mass target correction amount.

[0033] Preferably, in module M1:

[0034] Based on the working time of the thrusters in each direction during satellite thruster operation, the fuel and oxidizer usage ΔMo and ΔMf, as well as the actual centroid offset of the satellite (ΔX, ΔY, ΔZ) are calculated.

[0035] The thrusters are positioned at different locations on the satellite, and are symmetrically distributed with respect to the satellite's center of mass.

[0036] If the propellant discharge is uneven, the satellite's center of mass will shift. Based on the operating time of the thrusters in each position of the satellite, the shift distance of the satellite's center of mass in the X, Y, and Z directions can be calculated.

[0037] The satellite includes a corresponding control system for controlling the switching on and off of the heaters and valves.

[0038] Preferably, in module M2:

[0039] By combining the propellant usage amounts ΔMo and ΔMf, the satellite's center of mass offset (ΔX, ΔY, ΔZ), and the satellite's layout, mass characteristics, and initial propellant loading amount, the propellant mass of each tank in the current propulsion system is obtained. This allows for the determination of whether uneven propellant discharge has occurred during thruster operation and whether propellant mass distribution adjustment is necessary to correct the satellite's center of mass. If the satellite's center of mass offset (ΔX, ΔY, ΔZ) is less than the preset standard, no propellant mass distribution adjustment is required.

[0040] The propellant consists of two components: fuel and oxidant.

[0041] The storage tanks are divided into fuel tanks and oxidizer tanks, and each type of tank is symmetrically distributed with respect to the center of mass of the satellite.

[0042] Each tank is equipped with a heater, which is a polyimide film type electric heating element.

[0043] Each tank has a thermistor attached to its surface for monitoring the tank temperature;

[0044] The tank pressure and tank temperature are positively correlated. By controlling the turn-on time of the heaters in each tank, the temperature of each tank can be controlled, thereby controlling the pressure of each tank. After opening the connecting valve between the tanks, the propellant is transferred from the high-pressure tank to the low-pressure tank until the pressure between the tanks reaches equilibrium.

[0045] Preferably, in module M3:

[0046] Based on the current propellant mass of each tank and the target correction amount (ΔX', ΔY', ΔZ') of the satellite's center of mass, and combined with the satellite layout and mass characteristics, the propellant transfer direction and transfer mass (ΔMpo, ΔMpf) that satisfy the target correction amount (ΔX', ΔY', ΔZ') of the satellite's center of mass are analyzed and determined.

[0047]

[0048] T o ′1=k×T o1 ×(M ofull -M o1 -ΔM po )

[0049] T o ′2=k×T o2 ×(M ofull -M o2 +ΔM po )

[0050] Among them, M o1 M o2 The propellant masses of oxygen tank 1 and oxygen tank 2 are ΔM and ΔM, respectively. po M represents the mass of propellant to be transferred from oxygen tank 1 to oxygen tank 2, k is a selected adjustment coefficient, freely chosen between 0.9 and 1.1, and M... ofuoll T represents the propellant mass when the oxygen tank is full of propellant, To1 and To2 represent the current temperatures of oxygen tank 1 and oxygen tank 2, respectively. o ′1、T o ′2 represent the adjusted temperatures of oxygen chamber 1 and oxygen chamber 2, respectively;

[0051] After the propellant is transferred between the tanks, the connecting valve between the tanks of the same type of propellant is closed, and the temperature control heater threshold of the tank from which the propellant is transferred is lowered to be consistent with the temperature control heater threshold of the tank receiving the propellant. After the temperature of the tanks of the same type of propellant is consistent, the connecting valve between the tanks of the same type of propellant is opened.

[0052] Preferably, based on the propellant transfer direction and transfer quality, and combined with the current temperature and pressure levels of each tank, the temperature level of the tank from which propellant needs to be transferred is raised by increasing the temperature control heater threshold. As the tank temperature rises, the corresponding tank pressure also rises, creating a temperature and pressure difference between the tank and the tanks whose heater thresholds have not been adjusted. The connecting valve between tanks of the same type of propellant is opened, and the propellant transfer is achieved by utilizing the pressure difference between the tanks.

[0053] Compared with the prior art, the present invention has the following beneficial effects:

[0054] This invention achieves a balanced distribution of propellant mass in each tank of the satellite and optimized adjustment of the satellite's center of mass by adjusting the temperature difference between different tanks and the valve control logic of the propulsion system, which is beneficial for satellite attitude control. Attached Figure Description

[0055] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0056] Fig. 1 This is a schematic diagram of a dual-component multi-tank propulsion system.

[0057] Fig. 2 This is a flowchart of a propellant distribution adjustment method for uneven emission of bicomponent propellants.

[0058] Among them, 1 is the oxidant storage tank, 2 is the fuel storage tank, 3 is the heater, 4 is the valve between the oxidant storage tanks, and 5 is the valve between the fuel storage tanks. Detailed Implementation

[0059] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0060] Example 1:

[0061] This invention provides a propellant distribution adjustment method for uneven propellant discharge in satellites with dual-component propellants. Addressing the problem of uneven propellant discharge in satellite propulsion systems with multiple tanks, this method adjusts the temperature difference between different tanks and the propulsion system valve control logic based on the remaining propellant level and temperature of each tank, combined with data such as the satellite's on-orbit attitude and center of mass offset. This drives the mutual flow of propellant between different tanks, achieving a balanced distribution of propellant mass in each tank and optimized adjustment of the satellite's center of mass. Furthermore, oxidizer pressure is regulated through tank temperature adjustment, optimizing the propellant mixing ratio during thruster operation, which is beneficial for satellite attitude control and reduces propellant consumption.

[0062] According to the present invention, a propellant regulation method for uneven emission of bicomponent propellants is provided, such as... Figs. 1-2 As shown, it includes:

[0063] Step S1: By adjusting the working time of the thrusters in each direction during operation, the satellite's center of mass shift is adapted, and the satellite's center of mass shift is obtained as feedback.

[0064] Specifically, in step S1:

[0065] Based on the working time of the thrusters in each direction during satellite thruster operation, the fuel and oxidizer usage ΔMo and ΔMf, as well as the actual centroid offset of the satellite (ΔX, ΔY, ΔZ) are calculated.

[0066] The thrusters are positioned at different locations on the satellite, and are symmetrically distributed with respect to the satellite's center of mass.

[0067] If the propellant discharge is uneven, the satellite's center of mass will shift. Based on the operating time of the thrusters in each position of the satellite, the shift distance of the satellite's center of mass in the X, Y, and Z directions can be calculated.

[0068] The satellite includes a corresponding control system for controlling the switching on and off of the heaters and valves.

[0069] Step S2: Calculate the propellant mass of each tank after the thrusters operate, based on the satellite's center of mass offset.

[0070] Specifically, in step S2:

[0071] By combining the propellant usage amounts ΔMo and ΔMf, the satellite's center of mass offset (ΔX, ΔY, ΔZ), and the satellite's layout, mass characteristics, and initial propellant loading amount, the propellant mass of each tank in the current propulsion system is obtained. This allows for the determination of whether uneven propellant discharge has occurred during thruster operation and whether propellant mass distribution adjustment is necessary to correct the satellite's center of mass. If the satellite's center of mass offset (ΔX, ΔY, ΔZ) is less than the preset standard, no propellant mass distribution adjustment is required.

[0072] The propellant consists of two components: fuel and oxidant.

[0073] The storage tanks are divided into fuel tanks and oxidizer tanks, and each type of tank is symmetrically distributed with respect to the center of mass of the satellite.

[0074] Each tank is equipped with a heater, which is a polyimide film type electric heating element.

[0075] Each tank has a thermistor attached to its surface for monitoring the tank temperature;

[0076] The tank pressure and tank temperature are positively correlated. By controlling the turn-on time of the heaters in each tank, the temperature of each tank can be controlled, thereby controlling the pressure of each tank. After opening the connecting valve between the tanks, the propellant is transferred from the high-pressure tank to the low-pressure tank until the pressure between the tanks reaches equilibrium.

[0077] Step S3: Based on the current propellant mass of each tank and the satellite's center of mass target correction amount, analyze and determine the propellant transfer direction and transfer mass that meet the satellite's center of mass target correction amount.

[0078] Specifically, in step S3:

[0079] Based on the current propellant mass of each tank and the target correction amount (ΔX', ΔY', ΔZ') of the satellite's center of mass, and combined with the satellite layout and mass characteristics, the propellant transfer direction and transfer mass (ΔMpo, ΔMpf) that satisfy the target correction amount (ΔX', ΔY', ΔZ') of the satellite's center of mass are analyzed and determined.

[0080]

[0081] T o ′1=k×T o1 ×(M ofull -M o1 -ΔM po )

[0082] T o ′2=k×T o2 ×(M ofull -M o2 +ΔMpo )

[0083] Among them, M o1 M o2 The propellant masses of oxygen tank 1 and oxygen tank 2 are ΔM and ΔM, respectively. po M represents the mass of propellant to be transferred from oxygen tank 1 to oxygen tank 2, k is a selected adjustment coefficient, freely chosen between 0.9 and 1.1, and M... ofill T represents the propellant mass when the oxygen tank is full of propellant, To1 and To2 represent the current temperatures of oxygen tank 1 and oxygen tank 2, respectively. o ′1、T o ′2 represent the adjusted temperatures of oxygen chamber 1 and oxygen chamber 2, respectively;

[0084] After the propellant is transferred between the tanks, the connecting valve between the tanks of the same type of propellant is closed, and the temperature control heater threshold of the tank from which the propellant is transferred is lowered to be consistent with the temperature control heater threshold of the tank receiving the propellant. After the temperature of the tanks of the same type of propellant is consistent, the connecting valve between the tanks of the same type of propellant is opened.

[0085] Specifically, based on the propellant transfer direction and transfer quality, and combined with the current temperature and pressure levels of each tank, the temperature level of the tank whose propellant needs to be transferred is raised by increasing the temperature control heater threshold. As the tank temperature rises, its corresponding tank pressure also rises, creating a temperature and pressure difference between the tank and the tank whose heater threshold has not been adjusted. The connecting valve between tanks of the same type of propellant is opened, and the propellant transfer is achieved by utilizing the pressure difference between the tanks.

[0086] Example 2:

[0087] Example 2 is a preferred example of Example 1, and is used to illustrate the present invention in more detail.

[0088] The present invention also provides a propellant conditioning system for uneven emission of bicomponent propellants. The propellant conditioning system for uneven emission of bicomponent propellants can be implemented by executing the process steps of the propellant conditioning method for uneven emission of bicomponent propellants. That is, those skilled in the art can understand the propellant conditioning method for uneven emission of bicomponent propellants as a preferred embodiment of the propellant conditioning system for uneven emission of bicomponent propellants.

[0089] A propellant regulation system for addressing uneven emission of bicomponent propellants, provided by the present invention, comprises:

[0090] Module M1: By adjusting the working time of the thrusters in each direction during operation, it adapts to the shift of the satellite's center of mass and provides feedback on the satellite's center of mass shift.

[0091] Specifically, in module M1:

[0092] Based on the working time of the thrusters in each direction during satellite thruster operation, the fuel and oxidizer usage ΔMo and ΔMf, as well as the actual centroid offset of the satellite (ΔX, ΔY, ΔZ) are calculated.

[0093] The thrusters are positioned at different locations on the satellite, and are symmetrically distributed with respect to the satellite's center of mass.

[0094] If the propellant discharge is uneven, the satellite's center of mass will shift. Based on the operating time of the thrusters in each position of the satellite, the shift distance of the satellite's center of mass in the X, Y, and Z directions can be calculated.

[0095] The satellite includes a corresponding control system for controlling the switching on and off of the heaters and valves.

[0096] Module M2: Based on the satellite's center of mass offset, calculate the propellant mass of each tank after the thrusters operate;

[0097] Specifically, in module M2:

[0098] By combining the propellant usage amounts ΔMo and ΔMf, the satellite's center of mass offset (ΔX, ΔY, ΔZ), and the satellite's layout, mass characteristics, and initial propellant loading amount, the propellant mass of each tank in the current propulsion system is obtained. This allows for the determination of whether uneven propellant discharge has occurred during thruster operation and whether propellant mass distribution adjustment is necessary to correct the satellite's center of mass. If the satellite's center of mass offset (ΔX, ΔY, ΔZ) is less than the preset standard, no propellant mass distribution adjustment is required.

[0099] The propellant consists of two components: fuel and oxidant.

[0100] The storage tanks are divided into fuel tanks and oxidizer tanks, and each type of tank is symmetrically distributed with respect to the center of mass of the satellite.

[0101] Each tank is equipped with a heater, which is a polyimide film type electric heating element.

[0102] Each tank has a thermistor attached to its surface for monitoring the tank temperature;

[0103] The tank pressure and tank temperature are positively correlated. By controlling the turn-on time of the heaters in each tank, the temperature of each tank can be controlled, thereby controlling the pressure of each tank. After opening the connecting valve between the tanks, the propellant is transferred from the high-pressure tank to the low-pressure tank until the pressure between the tanks reaches equilibrium.

[0104] Module M3: Based on the current propellant mass of each tank and the satellite's center of mass target correction amount, analyze and determine the propellant transfer direction and transfer mass that meet the satellite's center of mass target correction amount.

[0105] Specifically, in module M3:

[0106] Based on the current propellant mass of each tank and the target correction amount (ΔX', ΔY', ΔZ') of the satellite's center of mass, and combined with the satellite layout and mass characteristics, the propellant transfer direction and transfer mass (ΔMpo, ΔMpf) that satisfy the target correction amount (ΔX', ΔY', ΔZ') of the satellite's center of mass are analyzed and determined.

[0107]

[0108] T o ′1=k×T o1 ×(M ofull -M o1 -ΔM po )

[0109] T o′ 2=k×T o2 ×(M ofull -M o2 +ΔM po )

[0110] Among them, M o1 M o2 The propellant masses of oxygen tank 1 and oxygen tank 2 are ΔM and ΔM, respectively. po M represents the mass of propellant to be transferred from oxygen tank 1 to oxygen tank 2, k is a selected adjustment coefficient, freely chosen between 0.9 and 1.1, and M... ofull T represents the propellant mass when the oxygen tank is full of propellant, To1 and To2 represent the current temperatures of oxygen tank 1 and oxygen tank 2, respectively. o ′1、T o ′2 represent the adjusted temperatures of oxygen chamber 1 and oxygen chamber 2, respectively;

[0111] After the propellant is transferred between the tanks, the connecting valve between the tanks of the same type of propellant is closed, and the temperature control heater threshold of the tank from which the propellant is transferred is lowered to be consistent with the temperature control heater threshold of the tank receiving the propellant. After the temperature of the tanks of the same type of propellant is consistent, the connecting valve between the tanks of the same type of propellant is opened.

[0112] Specifically, based on the propellant transfer direction and transfer quality, and combined with the current temperature and pressure levels of each tank, the temperature level of the tank whose propellant needs to be transferred is raised by increasing the temperature control heater threshold. As the tank temperature rises, its corresponding tank pressure also rises, creating a temperature and pressure difference between the tank and the tank whose heater threshold has not been adjusted. The connecting valve between tanks of the same type of propellant is opened, and the propellant transfer is achieved by utilizing the pressure difference between the tanks.

[0113] Example 3:

[0114] Example 3 is a preferred example of Example 1, and is used to illustrate the present invention in more detail.

[0115] This invention provides a method for adjusting propellant distribution to address uneven emission of bipropellant in satellites. A certain GEO-orbiting satellite's bipropellant propulsion system is equipped with four tanks: two oxidizer tanks (1) and two fuel tanks (2). Heaters (3) are attached to the surface of all tanks. Tanks of the same type of propellant are connected by pipelines and valves (4, 5). See details... Fig. 1 After the thrusters ignited in orbit, the fuel and oxidizer usage (ΔMo, ΔMf) and the actual satellite center-of-gravity offset (ΔX, ΔY, ΔZ) were calculated based on the thruster operating time in each direction during ignition. Furthermore, considering the satellite's layout, mass characteristics, and initial propellant loading, the propellant mass in each tank of the propulsion system (Mo1, Mo2, Mf1, Mf2) was calculated. It was determined that uneven propellant discharge occurred during ignition, resulting in a satellite center-of-gravity offset ΔZ of 2.7 mm, necessitating adjustments to the propellant mass distribution to correct the satellite's center of gravity.

[0116] Based on the mass difference of propellant in the same type of tank (Mo1-Mo2, Mf1-Mf2) and the target correction amount of the satellite's center of mass (ΔX', ΔY', ΔZ'), combined with the satellite layout, mass characteristics and other conditions, it is determined that 4.5 kg of fuel (ΔMpf = 4.5 kg) needs to be transferred from the fuel tank TFA to TFB, while no propellant transfer is required between oxidizer tanks (ΔMpo = 0 kg).

[0117] Under normal conditions, the heater temperature control thresholds for all four propellant tanks in the propulsion system are [16, 18]℃. Based on the adjustment requirement of ΔMpf = 10kg, the heater threshold of the fuel tank TFA is increased to [19, 21]℃. Simultaneously, the valve between the two fuel tanks is opened, utilizing the temperature and pressure differences between TFA and TFB to transfer fuel from TFA to TFB. After 12 hours of propellant transfer, 10kg of fuel has been transferred. The valve between the two fuel tanks is then closed, and the heater threshold of the fuel tank TFA is restored to [16, 18]℃. Once the TFA temperature drops to the same range as the TFB, the valve between the two fuel tanks is reopened. After adjusting the propellant mass distribution, the satellite's center of mass offset ΔZ is corrected to 0.2mm.

[0118] Figs. 1-2 The propellant distribution adjustment method shown is designed to address the uneven release of bicomponent propellant in satellites. This method has been verified in orbit on a GEO-orbiting satellite and can achieve propellant mass distribution adjustment and optimization, reducing the satellite's center of mass deviation caused by uneven propellant release. This provides a strong foundation for subsequent satellite attitude control and significantly reduces the amount of propellant consumed for attitude correction.

[0119] Those skilled in the art will understand that, besides implementing the system and its various devices, modules, and units provided by this invention in the form of purely computer-readable program code, the same functions can be achieved entirely through logical programming of the method steps, making the system and its various devices, modules, and units of this invention function in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers. Therefore, the system and its various devices, modules, and units provided by this invention can be considered as a hardware component, and the devices, modules, and units included therein for implementing various functions can also be considered as structures within the hardware component; alternatively, the devices, modules, and units for implementing various functions can be considered as both software modules implementing the method and structures within the hardware component.

[0120] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A propellant regulation method for addressing uneven emission of bicomponent propellants, characterized in that, include: Step S1: By adjusting the working time of the thrusters in each direction during operation, the satellite's center of mass shift is adapted, and the satellite's center of mass shift is obtained as feedback. Step S2: Calculate the propellant mass of each tank after the thrusters operate, based on the satellite's center of mass offset. Step S3: Based on the current propellant mass of each tank and the satellite's center of mass target correction amount, analyze and determine the propellant transfer direction and transfer mass that meet the satellite's center of mass target correction amount; In step S3: Based on the current propellant mass of each tank and the target correction amount (ΔX', ΔY', ΔZ') of the satellite's center of mass, combined with the satellite layout and mass characteristics, the propellant transfer direction and transfer mass (ΔMpo, ΔMpf) that satisfy the target correction amount (ΔX', ΔY', ΔZ') of the satellite's center of mass are analyzed and determined. in, , These represent the current propellant masses in oxygen tank 1 and oxygen tank 2, respectively. The mass of propellant to be transferred from oxygen tank 1 to oxygen tank 2. The selected adjustment coefficient can be freely chosen from 0.9 to 1.

1. T is the mass of the propellant when the oxygen tank is full of propellant. o1 T o2 These are the current temperatures of oxygen tank 1 and oxygen tank 2, respectively. , These are the adjusted temperatures of oxygen chamber 1 and oxygen chamber 2, respectively. After the propellant is transferred between the tanks, the connecting valve between the tanks of the same type of propellant is closed, and the temperature control heater threshold of the tank from which the propellant is transferred is lowered to be consistent with the temperature control heater threshold of the tank receiving the propellant. After the temperature of the tanks of the same type of propellant is consistent, the connecting valve between the tanks of the same type of propellant is opened.

2. The propellant adjustment method for uneven emission of bicomponent propellants according to claim 1, characterized in that, In step S1: Based on the operating time of the thrusters in each direction during satellite thruster operation, the fuel and oxidizer usage amounts ΔMo and ΔMf, as well as the actual centroid offset of the satellite (ΔX, ΔY, ΔZ) are calculated. The thrusters are positioned at different locations on the satellite, and are symmetrically distributed with respect to the satellite's center of mass. If the propellant discharge is uneven, the satellite's center of mass will shift. Based on the operating time of the thrusters in each position of the satellite, the shift distance of the satellite's center of mass in the X, Y, and Z directions can be calculated. The satellite includes a corresponding control system for controlling the switching on and off of the heaters and valves.

3. The propellant adjustment method for uneven emission of bicomponent propellants according to claim 1, characterized in that, In step S2: By combining the propellant usage amounts ΔMo and ΔMf, the satellite's center of mass offset (ΔX, ΔY, ΔZ), and the satellite's layout, mass characteristics, and initial propellant loading amount, the propellant mass of each tank in the current propulsion system is obtained. This allows for the determination of whether uneven propellant discharge has occurred during thruster operation and whether propellant mass distribution adjustment is necessary to correct the satellite's center of mass. If the satellite's center of mass offset (ΔX, ΔY, ΔZ) is less than the preset standard, no propellant mass distribution adjustment is required. The propellant consists of two components: fuel and oxidant. The storage tanks are divided into fuel tanks and oxidizer tanks, and each type of tank is symmetrically distributed with respect to the center of mass of the satellite. Each tank is equipped with a heater, which is a polyimide film type electric heating element. Each tank is fitted with a thermistor to monitor its temperature. The tank pressure and tank temperature are positively correlated. By controlling the turn-on time of the heaters in each tank, the temperature of each tank can be controlled, thereby controlling the pressure of each tank. After opening the connecting valve between the tanks, the propellant is transferred from the high-pressure tank to the low-pressure tank until the pressure between the tanks reaches equilibrium.

4. The propellant adjustment method for uneven emission of bicomponent propellants according to claim 1, characterized in that: Based on the propellant transfer direction and transfer quality, and combined with the current temperature and pressure levels of each tank, the temperature level of the tank whose propellant needs to be transferred is raised by increasing the threshold value of the temperature control heater. As the tank temperature rises, the corresponding tank pressure also rises, creating a temperature and pressure difference between the tank and the tank whose heater threshold has not been adjusted. The connecting valve between tanks of the same type of propellant is opened, and the propellant transfer is achieved by utilizing the pressure difference between the tanks.

5. A propellant regulation system for addressing uneven emission of bicomponent propellants, characterized in that, include: Module M1: By adjusting the working time of the thrusters in each direction during operation, it adapts to the shift of the satellite's center of mass and provides feedback on the satellite's center of mass shift. Module M2: Based on the satellite's center of mass offset, calculate the propellant mass of each tank after the thrusters operate; Module M3: Based on the current propellant mass of each tank and the satellite's center of mass target correction amount, analyze and determine the propellant transfer direction and transfer mass that meet the satellite's center of mass target correction amount; In module M3: Based on the current propellant mass of each tank and the target correction amount (ΔX', ΔY', ΔZ') of the satellite's center of mass, combined with the satellite layout and mass characteristics, the propellant transfer direction and transfer mass (ΔMpo, ΔMpf) that satisfy the target correction amount (ΔX', ΔY', ΔZ') of the satellite's center of mass are analyzed and determined. in, , These represent the current propellant masses in oxygen tank 1 and oxygen tank 2, respectively. The mass of propellant to be transferred from oxygen tank 1 to oxygen tank 2. The selected adjustment coefficient can be freely chosen from 0.9 to 1.

1. T is the mass of the propellant when the oxygen tank is full of propellant. o1 T o2 These are the current temperatures of oxygen tank 1 and oxygen tank 2, respectively. , These are the adjusted temperatures of oxygen chamber 1 and oxygen chamber 2, respectively. After the propellant is transferred between the tanks, the connecting valve between the tanks of the same type of propellant is closed, and the temperature control heater threshold of the tank from which the propellant is transferred is lowered to be consistent with the temperature control heater threshold of the tank receiving the propellant. After the temperature of the tanks of the same type of propellant is consistent, the connecting valve between the tanks of the same type of propellant is opened.

6. The propellant regulation system for uneven emission of bicomponent propellants according to claim 5, characterized in that, In module M1: Based on the operating time of the thrusters in each direction during satellite thruster operation, the fuel and oxidizer usage amounts ΔMo and ΔMf, as well as the actual centroid offset of the satellite (ΔX, ΔY, ΔZ) are calculated. The thrusters are positioned at different locations on the satellite, and are symmetrically distributed with respect to the satellite's center of mass. If the propellant discharge is uneven, the satellite's center of mass will shift. Based on the operating time of the thrusters in each position of the satellite, the shift distance of the satellite's center of mass in the X, Y, and Z directions can be calculated. The satellite includes a corresponding control system for controlling the switching on and off of the heaters and valves.

7. The propellant regulation system for uneven emission of bicomponent propellants according to claim 5, characterized in that, In module M2: By combining the propellant usage amounts ΔMo and ΔMf, the satellite's center of mass offset (ΔX, ΔY, ΔZ), and the satellite's layout, mass characteristics, and initial propellant loading amount, the propellant mass of each tank in the current propulsion system is obtained. This allows for the determination of whether uneven propellant discharge has occurred during thruster operation and whether propellant mass distribution adjustment is necessary to correct the satellite's center of mass. If the satellite's center of mass offset (ΔX, ΔY, ΔZ) is less than the preset standard, no propellant mass distribution adjustment is required. The propellant consists of two components: fuel and oxidant. The storage tanks are divided into fuel tanks and oxidizer tanks, and each type of tank is symmetrically distributed with respect to the center of mass of the satellite. Each tank is equipped with a heater, which is a polyimide film type electric heating element. Each tank is fitted with a thermistor to monitor its temperature. The tank pressure and tank temperature are positively correlated. By controlling the turn-on time of the heaters in each tank, the temperature of each tank can be controlled, thereby controlling the pressure of each tank. After opening the connecting valve between the tanks, the propellant is transferred from the high-pressure tank to the low-pressure tank until the pressure between the tanks reaches equilibrium.

8. The propellant regulation system for uneven emission of bicomponent propellants according to claim 5, characterized in that: Based on the propellant transfer direction and transfer quality, and combined with the current temperature and pressure levels of each tank, the temperature level of the tank whose propellant needs to be transferred is raised by increasing the threshold value of the temperature control heater. As the tank temperature rises, the corresponding tank pressure also rises, creating a temperature and pressure difference between the tank and the tank whose heater threshold has not been adjusted. The connecting valve between tanks of the same type of propellant is opened, and the propellant transfer is achieved by utilizing the pressure difference between the tanks.

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