Method for analyzing on-orbit utilization rate of spacecraft surface tension tank propellant

Abstract

This invention provides a method for analyzing the on-orbit utilization of propellant in a spacecraft surface tension propellant tank, under conditions where pressurized gas cannot be introduced by the tank management device. The method includes: obtaining the residual propellant dose V attached to the inner wall of the tank. tc ; Obtain the residual propulsion dose V in the pipeline gc ; Obtain the propellant dose V in the tank management device tg ; Obtain the safety margin V for propellant in spacecraft design a Obtain the total volume V of the storage tank. t According to the residual propellant dose V on the inner wall of the tank tc Residual propellant dose V in pipeline gc Propulsion dose V in tank management device tg Spacecraft design with a safety margin for propellant V a Total volume V of the storage tank t The propellant utilization rate was determined to be 1-(V). tc +V gc +V tg +V a ) / V t By integrating the working mechanism of the surface tension tank, the propellant consumption process, the overall load conditions, and the on-orbit mission profile, accurate measurement of the on-orbit utilization rate of propellant, which is less affected by on-orbit environmental factors, can be achieved.

Description

Technical Field

[0001] This invention belongs to the field of propellant on-orbit availability analysis, and specifically relates to a method for analyzing the on-orbit utilization rate of propellant in spacecraft surface tension tanks. Background Technology

[0002] Manned lunar exploration and deep space exploration and development activities have always been the main body of space exploration activities of various countries and the focus of competition among space powers. In large-scale space exploration missions such as manned lunar exploration, in order to complete flight missions such as Earth-Moon transfer, interplanetary transfer and interplanetary braking, it is necessary to carry a large amount of propellant and effectively manage the propellant under environmental conditions such as weightlessness, attitude and orbit control loads, docking and separation impacts. It is also necessary to be able to provide a stable propellant delivery to downstream thrusters as needed through the propellant delivery system to ensure reliable impulse and thrust output of the thrusters.

[0003] For spacecraft carrying large amounts of propellant, achieving high-precision on-orbit propellant availability analysis can improve the utilization rate of the propellant carried by the spacecraft, thereby achieving significant flight mission and economic benefits. Based on different principles of spacecraft propellant availability measurement, liquid propellant availability measurement methods suitable for space applications can generally be divided into three categories: First, methods based on propellant volume measurement, such as the gas law method (PVT method), volume excitation method, gas injection pressure excitation method, and gas circulation excitation method; second, methods based on propellant mass measurement, such as flow meter, bookkeeping (BK—Book Keeping), and heat capacity methods; and third, accelerometer methods based on spacecraft accelerometer output. Currently, engineering practices mostly use the bookkeeping method, the gas law method, or a combination of both for propellant availability measurement. However, these two commonly used measurement methods have limited accuracy, and their accuracy is greatly affected by the propulsion system configuration and operating status, as well as on-orbit environmental factors. They may also be unable to measure the remaining propellant in a single tank in a parallel tank system, making them unsuitable for spacecraft with parallel tank layout propulsion systems and failing to meet the requirements for high-precision propellant availability measurement.

[0004] Current large spacecraft typically employ surface tension tanks to enhance spacecraft design and mission efficiency. Compared to traditional diaphragm tanks, surface tension tanks present unique challenges. Because the pressurized gas in a surface tension tank is in direct contact with the propellant without physical isolation, and unlike diaphragm tanks where propellant usage and remaining quantity can be directly determined through diaphragm displacement, the propellant and pressurized gas in a mixed state in the surface tension tank makes it difficult to directly determine the available propellant quantity or on-orbit utilization efficiency. Considering the limitations of existing propellant availability measurement methods, a novel on-orbit utilization analysis method for surface tension tanks is proposed. This method should consider the characteristics of surface tension tanks, their working mechanism, propellant consumption process, overall spacecraft load conditions, and other factors. This new method aims to accurately and safely assess the on-orbit propellant utilization rate of spacecraft using surface tension tanks, thereby improving mission efficiency. Summary of the Invention

[0005] To overcome the shortcomings of existing technologies, the inventors have conducted intensive research and provided a method for analyzing the on-orbit utilization rate of propellant in spacecraft surface tension tanks. This method requires no additional measurement equipment and achieves accurate measurement of the on-orbit utilization rate of propellant, which is less affected by on-orbit environmental factors, by comprehensively considering the working mechanism of the surface tension tank, the propellant consumption process, the overall load conditions, and the on-orbit mission profile.

[0006] The technical solution provided by this invention is as follows:

[0007] In a first aspect, a method for analyzing the on-orbit utilization rate of propellant in a spacecraft surface tension tank, under the condition that the tank management device does not allow pressurized gas to enter, includes:

[0008] Obtain the residual propellant dose V on the inner wall of the tank. tc The residual propellant dose V hanging on the inner wall of the tank tc Determined through microgravity simulation experiments or simulations;

[0009] Obtain the residual propulsion dose V in the pipeline gc The residual propulsion dose V in the pipeline gc Determined through cold flow testing or simulation;

[0010] Obtain the propellant dose V in the tank management device tg The propellant dose V in the tank management device tg Determined by volumetric method;

[0011] Obtain the safety margin V for propellant in spacecraft design a ;

[0012] Obtain the total volume V of the storage tank t The total volume V of the storage tank t Determined through emissions testing;

[0013] Based on the residual propellant dose V on the inner wall of the tank tc Residual propellant dose V in pipeline gc Propulsion dose V in tank management device tg Spacecraft design with a safety margin for propellant V a Total volume V of the storage tank t The propellant utilization rate was determined to be 1-(V tc +V gc +V tg +V a ) / V t .

[0014] Secondly, a method for analyzing the on-orbit utilization rate of propellant in a spacecraft surface tension tank, under the condition that the tank management device allows pressurized gas to enter, includes:

[0015] The volume V of pressurized gas entering the tank management device throughout the entire mission process is obtained. tgg The pressurized gas volume V entering the storage tank management device tgg Determined through ground-based microgravity simulation experiments or simulation analysis;

[0016] Obtain the propellant dose V in the tank management device tg The propellant dose V in the tank management device tg Determined by volumetric method;

[0017] According to the propulsion dose V in the tank management device tg The pressurized gas volume V entering the storage tank management device tgg Determine the remaining propellant V in the tank management unit. tg -V tgg ;

[0018] Obtain the residual propellant dose V on the inner wall of the tank. tc The residual propellant dose V hanging on the inner wall of the tank tc Determined through microgravity simulation experiments or simulations;

[0019] Obtain the residual propulsion dose V in the pipeline gc The residual propulsion dose V in the pipeline gc Determined through cold flow testing or simulation;

[0020] Obtain the safety margin V for propellant in spacecraft design a ;

[0021] Obtain the total volume V of the storage tank t The total volume V of the storage tank t Determined through emissions testing;

[0022] According to the remaining propellant V in the tank management device tg -Vtgg Residual propellant dose V hanging on the inner wall of the tank tc Residual propellant dose V in pipeline gc Spacecraft design with a safety margin for propellant V a Total volume V of the storage tank t The propellant utilization rate was determined to be 1-(V tc +V gc +V tg -V tgg +V a ) / V t .

[0023] In conjunction with the second aspect, under the conditions that the tank management system allows air intake and there is a settling process, the propellant utilization rate is:

[0024] In the formula, V tgi The amount of pressurized gas entering the tank management device when the i-th forward thrust engine generates a settling force is represented by N; N is the number of times the propellant undergoes a settling process.

[0025] In conjunction with the second aspect, under conditions where the tank management system allows air intake and there are reverse or lateral overload missions, the propellant utilization rate is:

[0026] In the formula, V tgj The amount of pressurized gas entering the tank management device during the j-th time the spacecraft is in a reverse overload or lateral overload flight process; M is the number of times the spacecraft is in a reverse overload or lateral overload process.

[0027] In conjunction with the second aspect, under the condition that the tank management system allows air intake and there are bottoming-out + reverse overload or bottoming-out + lateral overload missions, the propellant utilization rate is:

[0028]

[0029] In the formula, V tgi The amount of pressurized gas entering the propellant tank management device when the i-th forward thrust engine generates a settling force; N is the number of times the propellant undergoes a settling process; V tgj The amount of pressurized gas entering the tank management device during the j-th time the spacecraft is in a reverse overload or lateral overload flight process; M is the number of times the spacecraft is in a reverse overload or lateral overload process.

[0030] Thirdly, a spacecraft surface tension tank propellant on-orbit utilization analysis device includes:

[0031] One or more processors;

[0032] Storage device for storing one or more programs.

[0033] When the one or more programs are executed by the one or more processors, the one or more processors implement the spacecraft surface tension tank propellant on-orbit utilization analysis method described in the first or second aspect.

[0034] Fourthly, a readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the on-orbit utilization analysis method for spacecraft surface tension tank propellants as described in the first or second aspect.

[0035] Fifthly, a computer program product comprising: a computer program (also referred to as code or instructions) that, when run, executes the on-orbit utilization analysis method for spacecraft surface tension tank propellants as described in the first or second aspect.

[0036] The method for analyzing the on-orbit utilization rate of propellant in a spacecraft surface tension tank according to the present invention has the following advantages:

[0037] This invention provides a method for analyzing the on-orbit utilization rate of propellant in spacecraft surface tension tanks. By comprehensively considering the working mechanism of the surface tension tank, the propellant consumption process, the overall load conditions, and the on-orbit mission profile, this method utilizes experimental or simulation methods to accurately measure the on-orbit utilization rate of propellant, which is less affected by on-orbit environmental factors. It is not limited by the current measurement methods, which are greatly affected by the propulsion system configuration, operating status, and on-orbit environmental factors. Furthermore, it is not limited by the current measurement methods' inability to measure the remaining propellant in a single tank in a parallel tank system, its difficulty in adapting to spacecraft parallel tank layout propulsion systems, or its inability to meet the requirements for high-precision propellant availability measurement. Attached Figure Description

[0038] Figure 1 This is a schematic diagram of a spacecraft surface tension tank system;

[0039] Figure 2 This is a diagram showing the distribution of propellant and pressurizing gas in the free-state propellant tank;

[0040] Figure 3 This is a diagram showing the distribution of propellant and pressurizing gas in the tank during the sinking process;

[0041] Figure 4 This is a diagram showing the distribution of propellant and pressurizing gas in the reverse overload tank. Detailed Implementation

[0042] The features and advantages of the present invention will become clearer and more apparent from the following detailed description.

[0043] The term “exemplary” as used herein means “serving as an example, embodiment, or illustration.” Any embodiment illustrated herein as “exemplary” is not necessarily to be construed as superior to or better than other embodiments.

[0044] This invention provides a method for analyzing the on-orbit utilization of propellant in a spacecraft surface tension tank. By directly studying the principle of on-orbit propellant discharge, and combining the surface tension mechanism, tank design scheme, and on-orbit mission profile, the available amount of propellant is determined. Compared with traditional analysis methods, this invention simplifies the analysis process and only requires the propellant temperature and overload conditions. It is not affected by other environmental factors in orbit and is easy to achieve high-precision measurement.

[0045] After the spacecraft completes propellant loading on the ground, the propellant management unit (also known as the propellant management system, used to manage the propellant in the tanks on orbit, ensuring it is concentrated in the management unit to provide a stable, non-entrained propellant supply to the downstream thrusters) is installed at the liquid outlet at the bottom of the tank, in a state of full propellant. The entire tank of propellant surrounds the propellant management unit, and the pressurized gas is located at the gas inlet at the upstream gas path of the tank. See [link / details]. Figure 1 After a spacecraft is launched into orbit and is in free flight, the propellant in the propellant management system remains within the system due to liquid surface tension. The propellant outside the propellant management system in the tank, due to weightlessness, is in a free-mixing state with the pressurized gas. This free-mixing gas and liquid fills the tank. (See...) Figure 2 .

[0046] For propellant tanks where the propellant management system cannot be vented, the method for analyzing the on-orbit utilization rate of spacecraft propellants is as follows: The residual propellant dose V, such as that attached to the tank walls, is determined through microgravity simulation experiments or modeling. tc The residual amount V in pipelines, etc., is determined through cold flow tests or simulations. gc The propellant dose V in the tank management device is determined by volumetric calculation. tg Determine the safety margin V for propellant in spacecraft design. a The total tank volume V was determined through emission tests. t The propellant utilization rate is 1-(V tc +V gc +V tg +V a ) / V t .

[0047] For propellant management systems that allow pressurized gas to enter tanks, the method for analyzing the on-orbit utilization rate of spacecraft propellants is as follows: Based on the mission profile, the volume V of pressurized gas entering the tank management system throughout the entire mission is determined through ground-based microgravity simulation experiments or simulation analysis. tgg Then determine the remaining propellant V in the tank management device. tg-V tgg The residual propellant dose V, such as that attached to the inner wall of the tank, was determined through microgravity simulation experiments or simulations. tc The residual amount V in pipelines, etc., is determined through cold flow tests or simulations. gc Determine the safety margin V for propellant in spacecraft design. a The total tank volume V was determined through emission tests. t The upper limit of propellant utilization rate is then 1 - (V tc +V gc +V tg -V tgg +V a ) / V t .

[0048] During forward thrust operation, the propellant is subjected to settling force, causing the gas and liquid mixture to separate. The liquid propellant settles to the bottom around the propellant tank management system, while the pressurized gas accumulates around the tank's gas inlet. Figure 3 In this process, the on-orbit utilization rate of the propellant can be determined based on the fact that the propellant consumption in the propellant sinking process tank management device is equal to the amount of pressurized gas entering the management device. After the forward thrust operation ends, the pressurized gas and liquid propellant are once again in a gas-liquid mixed state under the influence of weightlessness.

[0049] During the propellant settling process, the volume V of pressurized gas entering the tank management device tgg The analytical method includes: if the propellant in the tank is located at the far end of the tank management device, then during the i-th forward thrust engine operation generating a sinking force, the propellant consumption during the process of the propellant moving from the far end of the tank management device to the vicinity of the propellant management device is V. tgi Then the amount of pressurized gas entering the tank management device is equal to the propellant consumption V. tgi By determining the number of times N, the propellant is at the far end of the tank, through mission profile analysis, the total volume of pressurized gas entering the tank management device during the propellant settling process can be determined. The propellant utilization rate is:

[0050] When a spacecraft experiences a reverse or lateral overload, the liquid propellant, under the influence of the overload force, moves to the far end of the propellant management system. Figure 4 In this process, the on-orbit utilization rate of the propellant can be determined based on the fact that the propellant consumption in the propellant sinking process tank management device is equal to the amount of pressurized gas entering the management device.

[0051] During reverse overload or lateral overload processes, the volume V of pressurized gas entering the tank management device... tggThe method for determining the propellant volume V during the j-th spacecraft's reverse overload or lateral overload flight process includes: When the spacecraft is under overload and located at the far end of the propellant management device, it cannot enter the propellant management device to replenish the consumed propellant. This results in pressurized gas continuously entering the tank management device during thruster operation. The volume V of propellant consumed during the reverse overload or lateral overload is then determined. tgj It can be determined that the total volume of gas entering the tank management device during a total of M reverse overload or lateral overload processes. The propellant utilization rate is:

[0052]

[0053] When spacecraft perform missions in orbit, the flight process and payload conditions are complex and variable. Especially during multiple orbital attitude maneuvers or landing and ascent processes on extraterrestrial bodies, it is necessary to comprehensively determine the bottoming process, reverse overload, and lateral overload, as well as the total volume of pressurized gas entering the propellant tank management system, ultimately determining the propellant's on-orbit availability. That is, when the management system allows gas inflow and there are bottoming and reverse overload mission conditions, the propellant utilization rate is:

[0054] Using the above methods, during the design and development phase, the on-orbit availability of propellant can be accurately and quickly determined, and the spacecraft propellant loading amount can be determined in conjunction with the propellant usage requirements. During the flight mission implementation phase, the current on-orbit availability of propellant (or the safe baseline for availability) can be determined based on the actual flight process analysis, so as to plan subsequent flight missions and ensure the safety of spacecraft missions.

[0055] This invention also provides a device for analyzing the on-orbit utilization rate of propellant in a spacecraft surface tension tank, comprising:

[0056] One or more processors;

[0057] Storage device for storing one or more programs.

[0058] When the one or more programs are executed by the one or more processors, the one or more processors implement the above-described method for analyzing the on-orbit utilization of propellant in spacecraft surface tension tanks.

[0059] The present invention also provides a readable storage medium storing a computer program that, when executed by a processor, implements the above-described method for analyzing the on-orbit utilization of propellant in spacecraft surface tension tanks.

[0060] The readable storage media include, but are not limited to, USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, optical disks, and other media capable of storing program code.

[0061] The present invention also provides a computer program product comprising: a computer program (also referred to as code or instructions), which, when run, executes the on-orbit utilization analysis method for spacecraft surface tension tank propellants as described in the first aspect.

[0062] In the above embodiments, implementation can be achieved, in whole or in part, through software, hardware, firmware, or any combination thereof. When implemented in software, it can be implemented, in whole or in part, as a computer program product. The computer program product includes one or more computer instructions. When the computer instructions are loaded and executed on a computer, all or part of the processes or functions described in the embodiments of this application are generated. The computer can be a general-purpose computer, a special-purpose computer, a computer network, or other programmable device. The computer instructions can be stored in a computer-readable storage medium or transmitted from one computer-readable storage medium to another. For example, the computer instructions can be transmitted from one website, computer, server, or data center to another via wired (e.g., coaxial cable, fiber optic, digital subscriber line (DSL)) or wireless (e.g., infrared, wireless, microwave, etc.) means.

[0063] Those skilled in the art will recognize that the units and algorithm steps of the various examples described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, or a combination of computer software and electronic hardware. Whether these functions are implemented in hardware or software depends on the specific application and design constraints of the technical solution. Those skilled in the art can use different methods to implement the described functions for each specific application, but such implementation should not be considered beyond the scope of this application.

[0064] Those skilled in the art will clearly understand that, for the sake of convenience and brevity, the specific working processes of the devices, apparatuses, and modules described above can be referred to the corresponding processes in the foregoing method embodiments, and will not be repeated here.

[0065] In the several embodiments provided in this application, it should be understood that the disclosed devices, apparatuses, and methods can be implemented in other ways. For example, the apparatus embodiments described above are merely illustrative; for instance, the division of modules is only a logical functional division, and other division methods may be used in actual implementation.

[0066] Furthermore, if the aforementioned functions are implemented as software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, or a portion of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this application. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0067] The present invention has been described in detail above with reference to specific embodiments and exemplary examples; however, these descriptions should not be construed as limiting the present invention. Those skilled in the art will understand that various equivalent substitutions, modifications, or improvements can be made to the technical solutions and embodiments of the present invention without departing from the spirit and scope of the invention, and all such modifications and improvements fall within the scope of the present invention. The scope of protection of the present invention is defined by the appended claims.

[0068] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A method for analyzing the on-orbit utilization rate of propellant in a spacecraft surface tension tank, characterized in that, Under conditions where pressurized gas is not permitted to enter the storage tank management device, including: Obtain the residual propellant dose V on the inner wall of the tank. tc The residual propellant dose V hanging on the inner wall of the tank tc Determined through microgravity simulation experiments or simulations; Obtain the residual propulsion dose V in the pipeline gc The residual propulsion dose V in the pipeline gc Determined through cold flow testing or simulation; Obtain the propellant dose V in the tank management device tg The propellant dose V in the tank management device tg Determined by volumetric method; Obtain the safety margin V for propellant in spacecraft design a ; Obtain the total volume V of the storage tank t The total volume V of the storage tank t Determined through emissions testing; Based on the residual propellant dose V on the inner wall of the tank tc Residual propellant dose V in pipeline gc Propulsion dose V in tank management device tg Spacecraft design with a safety margin for propellant V a Total volume V of the storage tank t The propellant utilization rate was determined to be 1-(V tc +V gc +V tg +V a ) / V t .

2. A method for analyzing the on-orbit utilization rate of propellant in a spacecraft surface tension tank, characterized in that, Under conditions where the tank management device allows pressurized gas to enter, including: The volume V of pressurized gas entering the tank management device throughout the entire mission process is obtained. tgg The pressurized gas volume V entering the storage tank management device tgg Determined through ground-based microgravity simulation experiments or simulation analysis; Obtain the propellant dose V in the tank management device tg The propellant dose V in the tank management device tg Determined by volumetric method; According to the propulsion dose V in the tank management device tg The pressurized gas volume V entering the storage tank management device tgg Determine the remaining propellant V in the tank management unit. tg -V tgg ; Obtain the residual propellant dose V on the inner wall of the tank. tc The residual propellant dose V hanging on the inner wall of the tank tc Determined through microgravity simulation experiments or simulations; Obtain the residual propulsion dose V in the pipeline gc The residual propulsion dose V in the pipeline gc Determined through cold flow testing or simulation; Obtain the safety margin V for propellant in spacecraft design a ; Obtain the total volume V of the storage tank t The total volume V of the storage tank t Determined through emissions testing; According to the remaining propellant V in the tank management device tg -V tgg Residual propellant dose V hanging on the inner wall of the tank tc Residual propellant dose V in pipeline gc Spacecraft design with a safety margin for propellant V a Total volume V of the storage tank t The propellant utilization rate was determined to be 1-(V tc +V gc +V tg -V tgg +V a ) / V t .

3. The method for analyzing the on-orbit utilization rate of propellant in spacecraft surface tension tanks according to claim 2, characterized in that, Under mission conditions where the tank management system allows air intake and there is a settling process, the propellant utilization rate is: In the formula, V tgi The amount of pressurized gas entering the tank management device when the i-th forward thrust engine generates a settling force is represented by N; N is the number of times the propellant undergoes a settling process.

4. The method for analyzing the on-orbit utilization rate of propellant in spacecraft surface tension tanks according to claim 2, characterized in that, Under conditions where the tank management system allows air intake and there are reverse or lateral overload missions, the propellant utilization rate is: In the formula, V tgj The amount of pressurized gas entering the tank management device during the j-th time the spacecraft is in a reverse overload or lateral overload flight process; M is the number of times the spacecraft is in a reverse overload or lateral overload process.

5. The method for analyzing the on-orbit utilization rate of propellant in spacecraft surface tension tanks according to claim 2, characterized in that, Under conditions where the tank management system allows air intake and there are bottoming-out + reverse overload or bottoming-out + lateral overload missions, the propellant utilization rate is: In the formula, V tgi The amount of pressurized gas entering the propellant tank management device when the i-th forward thrust engine operates and generates a settling force; N is the number of times the propellant undergoes a settling process; V tgj The amount of pressurized gas entering the tank management device during the j-th time the spacecraft is in a reverse overload or lateral overload flight process; M is the number of times the spacecraft is in a reverse overload or lateral overload process.

6. A device for analyzing the on-orbit utilization rate of propellant in a spacecraft surface tension tank, characterized in that, include: One or more processors; Storage device for storing one or more programs. When the one or more programs are executed by the one or more processors, the one or more processors implement the on-orbit utilization analysis method for spacecraft surface tension tank propellants as described in any one of claims 1 to 5.

7. A readable storage medium, characterized in that, It stores a computer program that, when executed by a processor, implements the on-orbit utilization analysis method for spacecraft surface tension tank propellant as described in any one of claims 1 to 5.

8. A computer program product, characterized in that, The computer program product includes: a computer program that, when run, executes the on-orbit utilization analysis method for spacecraft surface tension tank propellant as described in any one of claims 1 to 5.

Images