Propellant consumption calculation method and device, electronic equipment and storage medium
By combining the thin-film method and the pressure-volume-temperature method, the propellant consumption is comprehensively evaluated, which solves the problem of insufficient accuracy in the existing technology and achieves more accurate propellant consumption calculation and more efficient propellant remaining quantity prediction.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- BEIJING INST OF CONTROL ENG
- Filing Date
- 2023-11-23
- Publication Date
- 2026-04-21
AI Technical Summary
Existing methods for calculating propellant consumption, such as the BK method and the PVT method, suffer from insufficient accuracy and cumulative errors, making it difficult to accurately estimate propellant consumption during on-orbit operation.
By combining the bookkeeping method (BK method) and the pressure-volume-temperature method (PVT method), the consumption of the first and second propellants is determined by the estimated consumption of oxidizer and propellant, and the accuracy is judged by the envelope range. The consumption of the third propellant and its error are comprehensively evaluated.
It improves the accuracy of propellant consumption calculation, reduces measurement uncertainty, enhances the predictive ability of spacecraft propellant remaining quantity and deorbit early warning mechanism, and has economic benefits.
Smart Images
Figure CN121901529A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of spacecraft chemical propulsion technology, and in particular to a method, apparatus, electronic device, and storage medium for calculating propellant consumption. Background Technology
[0002] Currently, the main methods for calculating propellant consumption are the Bookkeeping (BK) method and the Pressure-Volume-Temperature (PVT) method.
[0003] The BK method works by recording the propellant consumption for each event and then calculating the remaining amount. The key to the BK method is obtaining the propellant consumption for each event or time period. For steady-state engine ignition, a standard flow model multiplied by the ignition time can be used for calculation. However, for pulse ignition, the flow rate varies with different pulse widths, especially in small pulse conditions where the flow rate is also affected by the thruster temperature before ignition. To accurately estimate propellant consumption during on-orbit use using the BK method, it is necessary to differentiate and statistically analyze thruster operating conditions and introduce a flow model under varying operating conditions. The PVT method, based on the ideal gas law, estimates propellant volume using telemetry temperature and pressure data. Its accuracy is closely related to the accuracy of the pressure and temperature sensors installed in the propellant tank and high-pressure cylinder. Therefore, the PVT method has relatively high measurement uncertainty, while the BK method offers higher accuracy. However, the BK method relies on integration, thus introducing accumulated errors.
[0004] Therefore, in order to address the above problems, there is an urgent need for a method to calculate propellant consumption that can accurately determine the amount of propellant consumed. Summary of the Invention
[0005] This invention provides a method, apparatus, electronic device, and storage medium for calculating propellant consumption, which can accurately calculate the amount of propellant consumed.
[0006] In a first aspect, embodiments of the present invention provide a method for calculating propellant consumption, including:
[0007] The first propellant consumption is determined using a bookkeeping method based on the estimated consumption of oxidizer and propellant; wherein the propellant includes oxidizer and propellant;
[0008] Based on the pressure and temperature data of the gas cylinder and the storage tank, the second propellant consumption is determined using the pressure-volume-temperature method; wherein, the second propellant consumption includes oxidizer consumption and propellant consumption, the storage tank includes an oxidizer storage tank and a propellant storage tank, and the gas cylinder is used to provide gas pressure to drive the material in the oxidizer storage tank and the propellant storage tank to be discharged;
[0009] Determine the oxidizer envelope and the propellant envelope of the bookkeeping method;
[0010] Determine whether the oxidant consumption and the propellant consumption fall within the oxidant envelope and the propellant envelope, respectively;
[0011] If so, determine the third propellant consumption and its error based on the first propellant consumption and its error and the second propellant consumption and its error, and output the third propellant consumption and its error;
[0012] If not, output the first propellant consumption amount and the error of the first propellant consumption amount.
[0013] In one possible design, prior to determining the first propellant consumption using a bookkeeping method based on the estimated oxidizer and propellant consumption, the following method is further included:
[0014] Based on the inlet pressure, temperature, and ignition accumulation time of the main engine, the estimated oxidant consumption and the estimated propellant consumption of the main engine are calculated using the engine small deviation equation.
[0015] Based on the inlet pressure, temperature, and ignition accumulation time of the thruster under different operating conditions, the estimated consumption of oxidizer and propellant of the thruster are calculated using the thruster small deviation equation.
[0016] The estimated oxidant consumption is obtained by summing the estimated oxidant consumption of the main engine and the estimated oxidant consumption of the thruster.
[0017] The estimated propellant consumption is obtained by summing the estimated propellant consumption of the main engine and the estimated propellant consumption of the thruster.
[0018] In one possible design, the estimated oxidizer consumption of the main engine and the estimated fuel consumption of the main engine are determined as follows:
[0019] ΔM mo =ω mo Δt mt
[0020] ΔM mf =ω mf Δt mt
[0021] ω mo =ω mo0 +f mo (P mo ,P mf ,T mo ,Tmf )
[0022] ω mf =ω mf0 +f mf (P mo ,P mf ,T mo ,T mf )
[0023] Where, ΔM mo Estimated oxidant consumption of main engine, ΔM mf Estimated fuel consumption of main engine, ω mo ω mf ω represents the oxidizer flow rate and the fuel flow rate under steady-state engine operating conditions, respectively. mo0 ω mf0 These represent the oxidizer flow rate and the fuel flow rate of the engine under rated operating conditions, respectively, P mo P mf The inlet oxidizer pressure and combustion pressure of the engine, T mo T mf These are the engine inlet oxidizer temperature and the combustion agent temperature, Δt, respectively. mt For the engine ignition accumulation time, f mo (P mo ,P mf ,T mo ,T mf ), f mf (P mo ,P mf ,T mo ,T mf These are the oxidizer flow rate deviation model and the fuel flow rate deviation model for the engine, respectively.
[0024] The estimated consumption of oxidizer and the estimated consumption of propellant in the thruster are determined as follows:
[0025] ω tho =ω tho0 +f tho (P tho ,P thf ,T tho ,T thf )
[0026] ω thf =ω thf0 +f thf (P tho ,P thf ,T tho ,T thf )
[0027]
[0028]
[0029] Where, ΔM tho To estimate the oxidizer consumption of the thruster, ΔM thf For the estimated propellant consumption of the thruster, 'i' represents four ignition modes: steady-state operation, attitude control operation, east-west position maintenance operation, and north-south position maintenance operation; 'f' represents the estimated propellant consumption of the thruster. tho (P tho ,P thf ,T tho ,T thf ), f thf (P tho ,P thf ,T tho ,T thf ) are the oxidizer flow rate deviation model and the propellant flow rate deviation model of the thruster, respectively, ω tho ω thf These represent the steady-state oxidizer flow rate and propellant flow rate of the thruster, respectively, ω tho0 ω thf0 These represent the oxidizer flow rate and propellant flow rate of the thruster under rated operating conditions, respectively. tho P thf The oxidizer pressure and propellant pressure at the thrust inlet, T tho T thf These are the oxidizer temperature and the propellant temperature at the thrust inlet, Δt. th η is the cumulative time for thruster ignition. th This is the flow coefficient.
[0030] In one possible design, the second propellant consumption is determined as follows:
[0031] ΔM PVT =ΔM PVTo +ΔM PVTf
[0032]
[0033]
[0034] Where, ΔM PVT For the second propellant consumption, ΔM PVTo The oxidant consumption ΔM is the amount obtained by the pressure-volume-temperature method. PVTf The amount of propellant consumed, ρ, is obtained by the pressure-volume-temperature method. o and ρ f The densities of the oxidizer and the propellant are V, respectively. g P is the volume of the gas cylinder.gi T gi The initial cylinder pressure and temperature are P, respectively. ge T ge These are the cylinder pressure and temperature at the sampling time, respectively, V to M is the volume of the oxidant storage tank. oi P represents the initial mass of the oxidant. oi T oi The initial pressure and temperature of the gas inside the oxygen tank are P and P, respectively. oe T oe The pressure and temperature of the gas inside the oxygen chamber at the respective sampling times, V tf M is the volume of the propellant storage tank. fi P represents the initial mass of the propellant. fi T fi The pressure and temperature of the gas inside the fuel tank in the initial state are P, respectively. fe T fe These represent the pressure and temperature of the gas inside the combustion chamber at the sampling time.
[0035] In one possible design, the oxidant envelope range is as follows:
[0036] [ΔM bko -δΔM tho ΔM bko +δΔM tho ]
[0037] The envelope range of the combustion agent is as follows:
[0038] [ΔM bkf -δΔM thf ΔM bkf +δΔM thf ]
[0039] Where, ΔM bko The estimated consumption of the oxidant obtained by the bookkeeping method, ΔM bkf δΔM is the estimated consumption of the propellant obtained by the bookkeeping method. tho δΔM represents the error in thrust oxidizer consumption. thf This is the error in the amount of propellant consumed by the thruster.
[0040] In one possible design, the thrust oxidizer consumption error and the thrust propellant consumption error are determined as follows:
[0041]
[0042]
[0043] Where, δΔM thoδΔM represents the error in thrust oxidizer consumption. thf The thruster propellant consumption error is represented by ω, where i represents one of four ignition modes: steady-state operation, attitude control operation, east-west position maintenance operation, and north-south position maintenance operation. tho ω thf These represent the steady-state oxidizer flow rate and propellant flow rate of the thruster, Δt, respectively. th Δη is the cumulative time for thruster ignition. th This is the flow deviation coefficient.
[0044] In one possible design, the third propellant consumption and the error in the third propellant consumption are determined as follows:
[0045] ΔM=aΔM BK +bΔM PVT
[0046]
[0047]
[0048]
[0049] Wherein, ΔM is the amount of the third propellant consumed, and δΔM is the error in the amount of the third propellant consumed. BK For the first propellant consumption, ΔM PVT For the second propellant consumption, σ BK σ represents the error in the first propellant consumption. PVT This represents the error in the amount of the second propellant consumed.
[0050] Secondly, embodiments of the present invention also provide a propellant consumption calculation device, the calculation device comprising:
[0051] The first calculation unit is used to determine the first propellant consumption based on the estimated consumption of oxidizer and the estimated consumption of propellant; wherein the propellant includes oxidizer and propellant;
[0052] The second calculation unit is used to determine the second propellant consumption based on the pressure and temperature data of the gas cylinder and the storage tank; wherein the second propellant consumption includes oxidizer consumption and propellant consumption, the storage tank includes an oxidizer storage tank and a propellant storage tank, and the gas cylinder is used to provide gas pressure to drive the material in the oxidizer storage tank and the propellant storage tank to be discharged;
[0053] The third calculation unit is used to determine the oxidizer envelope range and the propellant envelope range;
[0054] The determination unit is used to determine whether the oxidant consumption and the propellant consumption fall within the oxidant envelope and the propellant envelope, respectively.
[0055] If so, determine the third propellant consumption and its error based on the first propellant consumption and its error and the second propellant consumption and its error, and output the third propellant consumption and its error;
[0056] If not, output the first propellant consumption amount and the error of the first propellant consumption amount.
[0057] Thirdly, embodiments of the present invention also provide an electronic 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 embodiment of this specification.
[0058] 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 embodiment of this specification.
[0059] This invention provides a method, apparatus, electronic device, and storage medium for calculating propellant consumption. In this embodiment, the first propellant consumption is determined using the bookkeeping method (BK method) based on the estimated oxidizer and propellant consumption. The second propellant consumption, including both oxidizer and propellant consumption, is determined using the pressure-volume-temperature method (PVT method) based on pressure and temperature data from the gas cylinder and tank. The oxidizer and propellant envelopes are calculated using the BK method. It is then determined whether the oxidizer and propellant consumption obtained from the PVT algorithm both fall within their respective envelopes. If so, a third propellant consumption and its error are determined based on the first and second propellant consumption and their errors, and the third propellant consumption and its error are output; otherwise, the first propellant consumption and its error are output.
[0060] This technical method addresses the challenge of measuring remaining propellant in on-orbit satellites. By subdividing the variable operating condition model and applying statistics, it effectively improves the calculation accuracy of the Black-Scholes method. Simultaneously, the effectiveness of the PVT method is verified using the effective boundary established by the Black-Scholes method. The integrated evaluation method combining the Black-Scholes and PVT methods further reduces measurement uncertainty while avoiding the shortcomings of using a single method to assess remaining propellant.
[0061] This technical method is easy to operate, can make full use of existing propulsion system data and propellant remaining quantity measurement methods, improve the ability to predict propellant levels, strengthen the early warning mechanism for spacecraft deorbiting, and has considerable economic benefits and application prospects. Attached Figure Description
[0062] 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.
[0063] Figure 1 This is a flowchart of a method for calculating propellant consumption according to an embodiment of the present invention;
[0064] Figure 2 This is a hardware architecture diagram of an electronic device provided in an embodiment of the present invention;
[0065] Figure 3 This is a structural diagram of a propellant consumption calculation device provided in an embodiment of the present invention. Detailed Implementation
[0066] 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.
[0067] Please refer to Figure 1 This invention provides a method for calculating propellant consumption, including:
[0068] Step 100: Based on the estimated consumption of oxidizer and propellant, determine the first propellant consumption using a bookkeeping method; wherein the propellant includes oxidizer and propellant;
[0069] Step 102: Based on the pressure and temperature data of the gas cylinder and the storage tank, determine the second propellant consumption using the pressure-volume-temperature method; wherein, the second propellant consumption includes oxidizer consumption and propellant consumption, the storage tank includes an oxidizer storage tank and a propellant storage tank, and the gas cylinder is used to provide gas pressure to drive the material in the oxidizer storage tank and the propellant storage tank to be discharged.
[0070] Step 104: Determine the oxidizer envelope and the propellant envelope of the bookkeeping method;
[0071] Step 106: Determine whether the oxidant consumption and propellant consumption fall within the oxidant envelope and propellant envelope, respectively;
[0072] If so, determine the third propellant consumption and its error based on the first propellant consumption and its error, and the second propellant consumption and its error, and output the third propellant consumption and its error.
[0073] If not, output the first propellant consumption amount and the error of the first propellant consumption amount.
[0074] In this embodiment, the first propellant consumption is determined using the bookkeeping method (BK method) based on the estimated oxidizer and propellant consumption. The second propellant consumption is determined using the pressure-volume-temperature method (PVT method) based on the pressure and temperature data of the gas cylinder and tank, where the second propellant consumption includes both oxidizer and propellant consumption. The oxidizer and propellant envelopes are calculated using the BK method. It is then determined whether the oxidizer and propellant consumption values obtained from the PVT algorithm both fall within their respective envelopes. If so, the third propellant consumption value and its error are determined based on the first and second propellant consumption values and their errors, and the third propellant consumption value and its error are output; otherwise, the first propellant consumption value and its error are output.
[0075] This technical method addresses the challenge of measuring remaining propellant in on-orbit satellites. By subdividing the variable operating condition model and applying statistics, it effectively improves the calculation accuracy of the Black-Scholes method. Simultaneously, the effectiveness of the PVT method is verified using the effective boundary established by the Black-Scholes method. The integrated evaluation method combining the Black-Scholes and PVT methods further reduces measurement uncertainty while avoiding the shortcomings of using a single method to assess remaining propellant.
[0076] This technical method is easy to operate, can make full use of existing propulsion system data and propellant remaining quantity measurement methods, improve the ability to predict propellant levels, strengthen the early warning mechanism for spacecraft deorbiting, and has considerable economic benefits and application prospects.
[0077] It should be noted that the errors in the first and second propellant consumption amounts, which are essentially the measurement uncertainties, are obtained by differentiating the formulas of the BK and PVT methods. This calculation is a standard algorithm for measurement uncertainty, based on fundamental mathematical theory; the specific calculation process will not be elaborated in this application.
[0078] Before step 100, the following is also included:
[0079] Based on the inlet pressure, temperature, and ignition accumulation time of the main engine, the estimated oxidant consumption and the estimated propellant consumption of the main engine are calculated using the engine small deviation equation.
[0080] Based on the inlet pressure, temperature, and ignition accumulation time of the thruster under different operating conditions, the estimated consumption of oxidizer and propellant of the thruster are calculated using the thruster small deviation equation.
[0081] The estimated oxidant consumption is obtained by summing the estimated oxidant consumption of the main engine and the estimated oxidant consumption of the thruster.
[0082] The estimated propellant consumption is obtained by summing the estimated propellant consumption of the main engine and the estimated propellant consumption of the thruster.
[0083] In some embodiments of the present invention, the estimated consumption of oxidizer in the main engine and the estimated consumption of propellant in the main engine are determined in the following manner:
[0084] ΔM mo =ω mo Δt mt
[0085] ΔM mf =ω mf Δt mt
[0086] ω mo =ω mo0 +f mo (P mo ,P mf ,T mo ,T mf )
[0087] ω mf =ω mf0 +f mf (P mo ,P mf ,T mo ,T mf )
[0088] Where, ΔM mo Estimated oxidant consumption of main engine, ΔM mf Estimated fuel consumption of main engine, ω mo ω mf ω represents the oxidizer flow rate and the fuel flow rate under steady-state engine operating conditions, respectively. mo0 ω mf0 These represent the oxidizer flow rate and the fuel flow rate of the engine under rated operating conditions, respectively, P mo P mf The inlet oxidizer pressure and combustion pressure of the engine, Tmo T mf These are the engine inlet oxidizer temperature and the combustion agent temperature, Δt, respectively. mt For the engine ignition accumulation time, f mo (P mo ,P mf ,T mo ,T mf ), f mf (P mo ,P mf ,T mo ,T mf These are the oxidizer flow rate deviation model and the fuel flow rate deviation model for the engine, respectively.
[0089] The estimated consumption of oxidizer and propellant in the thruster were determined as follows:
[0090] ω tho =ω tho0 +f tho (P tho ,P thf ,T tho ,T thf )
[0091] ω thf =ω thf0 +f thf (P tho ,P thf ,T tho ,T thf )
[0092]
[0093]
[0094] Where, ΔM tho To estimate the oxidizer consumption of the thruster, ΔM thf For the estimated propellant consumption of the thruster, 'i' represents four ignition modes: steady-state operation, attitude control operation, east-west position maintenance operation, and north-south position maintenance operation; 'f' represents the estimated propellant consumption of the thruster. tho (P tho ,P thf ,T tho ,T thf ), f thf (P tho ,P thf ,T tho ,T thf ) are the oxidizer flow rate deviation model and the propellant flow rate deviation model of the thruster, respectively, ω tho ω thf These represent the steady-state oxidizer flow rate and propellant flow rate of the thruster, respectively, ωtho0 ω thf0 These represent the oxidizer flow rate and propellant flow rate of the thruster under rated operating conditions, respectively. tho P thf The oxidizer pressure and propellant pressure at the thrust inlet, T tho T thf These are the oxidizer temperature and the propellant temperature at the thrust inlet, Δt. th η is the cumulative time for thruster ignition. th This is the flow coefficient.
[0095] Estimated oxidant consumption ΔM bko And the estimated consumption of fuel ΔM bkf It is calculated using the following formula:
[0096] ΔM bko =ΔM mo +ΔM tho
[0097] ΔM bkf =ΔM mf +ΔM thf
[0098] For step 100, the first propellant consumption is determined by the following formula:
[0099] ΔM bk =ΔM bko +ΔM bkf
[0100] Where, ΔM bko This refers to the amount of the first propellant consumed.
[0101] Regarding step 102:
[0102] In some embodiments of the present invention, the second propellant consumption is determined in the following manner:
[0103] ΔM PVT =ΔM PVTo +ΔM PVTf
[0104]
[0105]
[0106] Where, ΔM PVT For the second propellant consumption, ΔM PVTo ΔM represents the oxidant consumption obtained by the pressure-volume-temperature method. PVTf ρ represents the propellant consumption obtained by the pressure-volume-temperature method. o and ρ fThe densities of the oxidizer and the propellant are V, respectively. g P is the volume of the gas cylinder. gi T gi The initial cylinder pressure and temperature are P, respectively. ge T ge These are the cylinder pressure and temperature at the sampling time, respectively, V to M is the volume of the oxidant storage tank. oi P represents the initial mass of the oxidant. oi T oi The initial pressure and temperature of the gas inside the oxygen tank are P and P, respectively. oe T oe The pressure and temperature of the gas inside the oxygen chamber at the respective sampling times, V tf M is the volume of the propellant storage tank. fi P represents the initial mass of the propellant. fi T fi The pressure and temperature of the gas inside the fuel tank in the initial state are P, respectively. fe T fe These represent the pressure and temperature of the gas inside the combustion chamber at the sampling time.
[0107] Regarding step 104:
[0108] In some embodiments of the present invention, the oxidant envelope range is as follows:
[0109] [ΔM bko -δΔM tho ΔM bko +δΔM tho ]
[0110] The envelope of the propellant is as follows:
[0111] [ΔM bkf -δΔM thf ΔM bkf +δΔM thf ]
[0112] Where, ΔM bko To estimate the consumption of oxidant obtained by the bookkeeping method, ΔM bkf δΔM is the estimated consumption of propellant obtained by the bookkeeping method. tho δΔM represents the error in thrust oxidizer consumption. thf This is the error in the amount of propellant consumed by the thruster.
[0113] In some embodiments of the present invention, the thrust oxidizer consumption error and the thrust propellant consumption error are determined in the following manner:
[0114]
[0115]
[0116] Where, δΔM tho δΔM represents the error in thrust oxidizer consumption. thf The thruster propellant consumption error is represented by ω, where i represents one of four ignition modes: steady-state operation, attitude control operation, east-west position maintenance operation, and north-south position maintenance operation. tho ω thf These represent the steady-state oxidizer flow rate and propellant flow rate of the thruster, Δt, respectively. th Δη is the cumulative time for thruster ignition. th This is the flow deviation coefficient.
[0117] It should be noted that, through real ignition tests on the ground using the spacecraft's on-orbit thruster in four ignition modes—steady-state operation, attitude control operation, east-west position maintenance operation, and north-south position maintenance operation—the flow coefficient ηth,i and envelope range Δηth,i of different ignition modes relative to the steady-state ignition operation were obtained.
[0118] Regarding step 106:
[0119] In some embodiments of the present invention, the third propellant consumption amount and the error in the third propellant consumption amount are determined in the following manner:
[0120] ΔM=aΔM BK +bΔM PVT
[0121]
[0122]
[0123]
[0124] Where ΔM is the third propellant consumption, δΔM is the error in the third propellant consumption, and ΔM BK For the first propellant consumption, ΔM PVT For the second propellant consumption, σ BK σ represents the error in the first propellant consumption. PVT This represents the error in the amount of the second propellant consumed.
[0125] like Figure 2 , Figure 3 As shown, this embodiment of the invention provides a device for calculating propellant consumption. The device embodiment can be implemented through software, hardware, or a combination of both. From a hardware perspective, as... Figure 2 The diagram shown is a hardware architecture diagram of an electronic device containing a propellant consumption calculation device according to an embodiment of the present invention. (Except for...) Figure 2 In addition to the processor, memory, network interface, and non-volatile memory shown, the electronic 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 logical device is formed by the CPU of its host electronic device reading the corresponding computer program from non-volatile memory into memory and running it. This embodiment of the invention also provides a propellant consumption calculation device, which includes:
[0126] The first calculation unit is used to determine the first propellant consumption based on the estimated consumption of oxidizer and propellant using a bookkeeping method; wherein the propellant includes oxidizer and propellant;
[0127] The second calculation unit is used to determine the second propellant consumption based on the pressure and temperature data of the gas cylinder and the storage tank using the pressure-volume-temperature method; wherein, the second propellant consumption includes oxidizer consumption and propellant consumption, the storage tank includes an oxidizer storage tank and a propellant storage tank, and the gas cylinder is used to provide gas pressure to drive the material in the oxidizer storage tank and the propellant storage tank to be discharged;
[0128] The third calculation unit is used to determine the oxidant envelope range and the propellant envelope range of the thin-film method;
[0129] The judgment unit is used to determine whether the oxidant consumption and the propellant consumption fall within the oxidant envelope and the propellant envelope, respectively.
[0130] If so, determine the third propellant consumption and its error based on the first propellant consumption and its error, and the second propellant consumption and its error, and output the third propellant consumption and its error.
[0131] If not, output the first propellant consumption amount and the error of the first propellant consumption amount.
[0132] It should be noted that the embodiments of the computing device provided in the present invention are based on the same inventive concept as the embodiments of the above-described computing method. Therefore, they can achieve the same technical effects. For specific effects, please refer to the embodiments of the above-described computing method, which will not be repeated here.
[0133] The computing device further includes a fourth computing unit, which performs the following steps:
[0134] Based on the inlet pressure, temperature, and ignition accumulation time of the main engine, the estimated oxidant consumption and the estimated propellant consumption of the main engine are calculated using the engine small deviation equation.
[0135] Based on the inlet pressure, temperature, and ignition accumulation time of the thruster under different operating conditions, the estimated consumption of oxidizer and propellant of the thruster are calculated using the thruster small deviation equation.
[0136] The estimated oxidant consumption is obtained by summing the estimated oxidant consumption of the main engine and the estimated oxidant consumption of the thruster.
[0137] The estimated propellant consumption is obtained by summing the estimated propellant consumption of the main engine and the estimated propellant consumption of the thruster.
[0138] In some embodiments of the present invention, the fourth computing unit is further configured to perform the following steps:
[0139] The estimated oxidizer consumption and the estimated fuel consumption of the main engine are determined as follows:
[0140] ΔM mo =ω mo Δt mt
[0141] ΔM mf =ω mf Δt mt
[0142] ω mo =ω mo0 +f mo (P mo ,P mf ,T mo ,T mf )
[0143] ω mf =ω mf0 +f mf (P mo ,P mf ,T mo ,T mf )
[0144] Where, ΔM mo Estimated oxidant consumption of main engine, ΔM mf Estimated fuel consumption of main engine, ω mo ω mf ω represents the oxidizer flow rate and the fuel flow rate under steady-state engine operating conditions, respectively. mo0 ω mf0 These represent the oxidizer flow rate and the fuel flow rate of the engine under rated operating conditions, respectively, P mo P mf The inlet oxidizer pressure and combustion pressure of the engine, T mo T mfThese are the engine inlet oxidizer temperature and the combustion agent temperature, Δt, respectively. mt For the engine ignition accumulation time, f mo (P mo ,P mf ,T mo ,T mf ), f mf (P mo ,P mf ,T mo ,T mf These are the oxidizer flow rate deviation model and the fuel flow rate deviation model for the engine, respectively.
[0145] The estimated consumption of oxidizer and propellant in the thruster were determined as follows:
[0146] ω tho =ω tho0 +f tho (P tho ,P thf ,T tho ,T thf )
[0147] ω thf =ω thf0 +f thf (P tho ,P thf ,T tho ,T thf )
[0148]
[0149]
[0150] Where, ΔM tho To estimate the oxidizer consumption of the thruster, ΔM thf For the estimated propellant consumption of the thruster, 'i' represents four ignition modes: steady-state operation, attitude control operation, east-west position maintenance operation, and north-south position maintenance operation; 'f' represents the estimated propellant consumption of the thruster. tho (P tho ,P thf ,T tho ,T thf ), f thf (P tho ,P thf ,T tho ,T thf ) are the oxidizer flow rate deviation model and the propellant flow rate deviation model of the thruster, respectively, ω tho ω thf These represent the steady-state oxidizer flow rate and propellant flow rate of the thruster, respectively, ω tho0 ω thf0These represent the oxidizer flow rate and propellant flow rate of the thruster under rated operating conditions, respectively. tho P thf The oxidizer pressure and propellant pressure at the thrust inlet, T tho T thf These are the oxidizer temperature and the propellant temperature at the thrust inlet, Δt. th η is the cumulative time for thruster ignition. th This is the flow coefficient.
[0151] Estimated oxidant consumption ΔM bko And the estimated consumption of fuel ΔM bkf It is calculated using the following formula:
[0152] ΔM bko =ΔM mo +ΔM tho
[0153] ΔM bkf =ΔM mf +ΔM thf
[0154] For the first calculation unit, the first calculation unit is used to determine the first propellant consumption amount using the following formula:
[0155] ΔM bk =ΔM bko +ΔM bkf
[0156] Where, ΔM bko This refers to the amount of the first propellant consumed.
[0157] In some embodiments of the present invention, the second calculation unit determines the second propellant consumption amount in the following manner:
[0158] ΔM PVT =ΔM PVTo +ΔM PVTf
[0159]
[0160]
[0161] Where, ΔM PVT For the second propellant consumption, ΔM PVTo ΔM represents the oxidant consumption obtained by the pressure-volume-temperature method. PVTf ρ represents the propellant consumption obtained by the pressure-volume-temperature method. o and ρ f The densities of the oxidizer and the propellant are V, respectively. g P is the volume of the gas cylinder. giT gi The initial cylinder pressure and temperature are P, respectively. ge T ge These are the cylinder pressure and temperature at the sampling time, respectively, V to M is the volume of the oxidant storage tank. oi P represents the initial mass of the oxidant. oi T oi The initial pressure and temperature of the gas inside the oxygen tank are P and P, respectively. oe T oe The pressure and temperature of the gas inside the oxygen chamber at the respective sampling times, V tf M is the volume of the propellant storage tank. fi P represents the initial mass of the propellant. fi T fi The pressure and temperature of the gas inside the fuel tank in the initial state are P, respectively. fe T fe These represent the pressure and temperature of the gas inside the combustion chamber at the sampling time.
[0162] In some embodiments of the present invention, the third calculation unit is used to determine the following oxidant envelope range:
[0163] [ΔM bko -δΔM tho ΔM bko +δΔM tho ]
[0164] The third calculation unit is used to determine the following propellant envelope range:
[0165] [ΔM bkf -δΔM thf ΔM bkf +δΔM thf ]
[0166] Where, ΔM bko To estimate the consumption of oxidant obtained by the bookkeeping method, ΔM bkf δΔM is the estimated consumption of propellant obtained by the bookkeeping method. tho δΔM represents the error in thrust oxidizer consumption. thf This is the error in the amount of propellant consumed by the thruster.
[0167] In some embodiments of the present invention, the thrust oxidizer consumption error and the thrust propellant consumption error are determined by the third calculation unit in the following manner:
[0168]
[0169]
[0170] Where, δΔMtho δΔM represents the error in thrust oxidizer consumption. thf The thruster propellant consumption error is represented by ω, where i represents one of four ignition modes: steady-state operation, attitude control operation, east-west position maintenance operation, and north-south position maintenance operation. tho ω thf These represent the steady-state oxidizer flow rate and propellant flow rate of the thruster, Δt, respectively. th Δη is the cumulative time for thruster ignition. th This is the flow deviation coefficient.
[0171] It should be noted that, through real ignition tests on the ground using the spacecraft's on-orbit thruster in four ignition modes—steady-state operation, attitude control operation, east-west position maintenance operation, and north-south position maintenance operation—the flow coefficient ηth,i and envelope range Δηth,i of different ignition modes relative to the steady-state ignition operation were obtained.
[0172] In some embodiments of the present invention, the third propellant consumption amount and the error of the third propellant consumption amount are determined by the determination unit in the following manner:
[0173] ΔM=aΔM BK +bΔM PVT
[0174]
[0175]
[0176]
[0177] Where ΔM is the third propellant consumption, δΔM is the error in the third propellant consumption, and ΔM BK For the first propellant consumption, ΔM PVT For the second propellant consumption, σ BK σ represents the error in the first propellant consumption. PVT This represents the error in the amount of the second propellant consumed.
[0178] It is understood that the structures illustrated in the embodiments of the present invention do not constitute a specific limitation on a propellant consumption calculation device. In other embodiments of the present invention, a propellant consumption calculation device 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.
[0179] 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.
[0180] This invention also provides an electronic 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 calculating propellant consumption according to any embodiment of this invention.
[0181] 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 calculating propellant consumption according to any embodiment of this invention.
[0182] 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.
[0183] 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.
[0184] Storage media embodiments for providing 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.
[0185] Furthermore, it should be clear that not only can the program code read by the computer be executed, but also the operating system or other components operating 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.
[0186] 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.
[0187] 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.
[0188] 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.
[0189] 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 for calculating propellant consumption, characterized in that, include: The first propellant consumption is determined using a bookkeeping method based on the estimated consumption of oxidizer and propellant; wherein the propellant includes oxidizer and propellant; Based on the pressure and temperature data of the gas cylinder and the storage tank, the second propellant consumption is determined using the pressure-volume-temperature method; wherein, the second propellant consumption includes oxidant consumption and propellant consumption, the storage tank includes an oxidant storage tank and a propellant storage tank, and the gas cylinder is used to provide gas pressure to drive the material in the oxidant storage tank and the propellant storage tank to be discharged; Determine the oxidizer envelope and the propellant envelope of the bookkeeping method; Determine whether the oxidant consumption and the propellant consumption fall within the oxidant envelope and the propellant envelope, respectively; If so, determine the third propellant consumption and its error based on the first propellant consumption and its error and the second propellant consumption and its error, and output the third propellant consumption and its error; If not, output the first propellant consumption amount and the error of the first propellant consumption amount.
2. The calculation method according to claim 1, characterized in that, Before determining the first propellant consumption using a bookkeeping method based on the estimated oxidizer and propellant consumption, the method further includes: Based on the inlet pressure, temperature, and ignition accumulation time of the main engine, the estimated oxidant consumption and the estimated propellant consumption of the main engine are calculated using the engine small deviation equation. Based on the inlet pressure, temperature, and ignition accumulation time of the thruster under different operating conditions, the estimated consumption of oxidizer and propellant of the thruster are calculated using the thruster small deviation equation. The estimated oxidant consumption is obtained by summing the estimated oxidant consumption of the main engine and the estimated oxidant consumption of the thruster. The estimated propellant consumption is obtained by summing the estimated propellant consumption of the main engine and the estimated propellant consumption of the thruster.
3. The calculation method according to claim 2, characterized in that, The estimated oxidizer consumption and the estimated propellant consumption of the main engine are determined as follows: DM mo =ω mo Δt mt DM mf =ω mf Δt mt ω mo =ω mo0 +f mo (P mo ,P mf ,T mo ,T mf ) ω mf =ω mf0 +f mf (P mo ,P mf ,T mo ,T mf ) Where, ΔM mo Estimated oxidant consumption of main engine, ΔM mf Estimated fuel consumption of main engine, ω mo ω mf ω represents the oxidizer flow rate and the fuel flow rate under steady-state engine operating conditions, respectively. mo0 ω mf0 These represent the oxidizer flow rate and the fuel flow rate of the engine under rated operating conditions, respectively, P mo P mf The inlet oxidizer pressure and combustion pressure of the engine, T mo T mf These are the engine inlet oxidizer temperature and the combustion agent temperature, Δt, respectively. mt For the engine ignition accumulation time, f mo (P mo ,P mf ,T mo ,T mf ), f mf (P mo ,P mf ,T mo ,T mf These are the oxidizer flow rate deviation model and the fuel flow rate deviation model for the engine, respectively. The estimated consumption of oxidizer and the estimated consumption of propellant in the thruster are determined as follows: ω tho =ω tho0 +f tho (P tho ,P thf ,T tho ,T thf ) ω thf =ω thf0 +f thf (P tho ,P thf ,T tho ,T thf ) Where, ΔM tho To estimate the oxidizer consumption of the thruster, ΔM thf For the estimated propellant consumption of the thruster, 'i' represents four ignition modes: steady-state operation, attitude control operation, east-west position maintenance operation, and north-south position maintenance operation; 'f' represents the estimated propellant consumption of the thruster. tho (P tho ,P thf ,T tho ,T thf ), f thf (P tho ,P thf ,T tho ,T thf ) are the oxidizer flow rate deviation model and the propellant flow rate deviation model of the thruster, respectively, ω tho ω thf These represent the steady-state oxidizer flow rate and propellant flow rate of the thruster, respectively, ω tho0 ω thf0 These represent the oxidizer flow rate and propellant flow rate of the thruster under rated operating conditions, respectively. tho P thf The oxidizer pressure and propellant pressure at the thrust inlet, T tho T thf These are the oxidizer temperature and the propellant temperature at the thrust inlet, Δt. th η is the cumulative time for thruster ignition. th This is the flow coefficient.
4. The calculation method according to claim 1, characterized in that, The second propellant consumption was determined as follows: ΔM PVT =ΔM PVTo +ΔM PVTf Where, ΔM PVT For the second propellant consumption, ΔM PVTo The oxidant consumption ΔM is the amount obtained by the pressure-volume-temperature method. PVTf The amount of propellant consumed, ρ, is obtained by the pressure-volume-temperature method. o and ρ f The densities of the oxidizer and the propellant are V, respectively. g P is the volume of the gas cylinder. gi T gi The initial cylinder pressure and temperature are P, respectively. ge T ge These are the cylinder pressure and temperature at the sampling time, respectively, V to M is the volume of the oxidant storage tank. oi P represents the initial mass of the oxidant. oi T oi The initial pressure and temperature of the gas inside the oxygen tank are P and P, respectively. oe T oe The pressure and temperature of the gas inside the oxygen chamber at the respective sampling times, V tf M is the volume of the propellant storage tank. fi P represents the initial mass of the propellant. fi T fi The pressure and temperature of the gas inside the fuel tank in the initial state are P, respectively. fe T fe These represent the pressure and temperature of the gas inside the combustion chamber at the sampling time.
5. The calculation method according to claim 1, characterized in that, The oxidant envelope range is as follows: [ΔM bko -δΔM tho ΔM bko +δΔM tho ] The envelope range of the combustion agent is as follows: [ΔM bkf -δΔM thf ΔM bkf +δΔM thf ] Where, ΔM bko The estimated consumption of the oxidant obtained by the bookkeeping method, ΔM bkf δΔM is the estimated consumption of the propellant obtained by the bookkeeping method. tho δΔM represents the error in thrust oxidizer consumption. thf This is the error in the amount of propellant consumed by the thruster.
6. The calculation method according to claim 5, characterized in that, The thruster oxidizer consumption error and the thruster propellant consumption error are determined in the following manner: Where, δΔM tho δΔM represents the error in thrust oxidizer consumption. thf The thruster propellant consumption error is represented by ω, where i represents one of four ignition modes: steady-state operation, attitude control operation, east-west position maintenance operation, and north-south position maintenance operation. tho ω thf These represent the steady-state oxidizer flow rate and propellant flow rate of the thruster, Δt, respectively. th Δη is the cumulative time for thruster ignition. th This is the flow deviation coefficient.
7. The calculation method according to claim 1, characterized in that, The third propellant consumption amount and the error thereof are determined in the following manner: ΔM = aΔM BK +bΔM PVT Wherein, ΔM is the amount of the third propellant consumed, and δΔM is the error in the amount of the third propellant consumed. BK For the first propellant consumption, ΔM PVT For the second propellant consumption, σ BK σ represents the error in the first propellant consumption. PVT This represents the error in the amount of the second propellant consumed.
8. A device for calculating propellant consumption, characterized in that, The computing device includes: The first calculation unit is used to determine the first propellant consumption based on the estimated consumption of oxidizer and propellant using a bookkeeping method; wherein the propellant includes oxidizer and propellant; The second calculation unit is used to determine the second propellant consumption based on the pressure and temperature data of the gas cylinder and the storage tank using the pressure-volume-temperature method; wherein, the second propellant consumption includes oxidant consumption and propellant consumption, the storage tank includes an oxidant storage tank and a propellant storage tank, and the gas cylinder is used to provide gas pressure to drive the material in the oxidant storage tank and the propellant storage tank to be discharged; The third calculation unit is used to determine the oxidant envelope range and the propellant envelope range of the thin-film method; The determination unit is used to determine whether the oxidant consumption and the propellant consumption fall within the oxidant envelope and the propellant envelope, respectively. If so, determine the third propellant consumption and its error based on the first propellant consumption and its error and the second propellant consumption and its error, and output the third propellant consumption and its error; If not, output the first propellant consumption amount and the error of the first propellant consumption amount.
9. An electronic device comprising a memory and a processor, wherein the memory stores a computer program, and the processor, when executing the computer program, implements the method as described in any one of claims 1-7.
10. A computer-readable storage medium having a computer program stored thereon, which, when executed in a computer, causes the computer to perform the method of any one of claims 1-7.