CN115329467B - Method and device for distinguishing repeatedly-used rocket engine based on typical characteristics - Google Patents
Method and device for distinguishing repeatedly-used rocket engine based on typical characteristics Download PDFInfo
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Abstract
The disclosure relates to a method and a device for judging a reusable rocket engine based on typical characteristics, and belongs to the technical field of general design of a carrier rocket. According to the method, for a given engine, the engine is judged according to the multiplexing external characteristics and the multiplexing internal characteristics of the engine, and the engine can be identified as a reusable rocket engine after all the engine meets the requirement. The method further defines the external characteristics as six indexes of repeated use times, starting times in a single flight process, a lower limit of a thrust adjusting range, an arrow body interface, a propellant supercooling degree and thrust. The internal characteristics are further defined as three indexes of light weight, component or assembly and convenience for maintenance. The method can clearly judge whether the given engine meets the condition of reusing the rocket engine for vertical take-off and landing carrying, thereby further guiding the generation of the capability of reusing the rocket engine and promoting the development of reusing the carrier rocket.
Description
Technical Field
The disclosure relates to a rocket engine distinguishing method and device, in particular to a reusable rocket engine distinguishing method and device based on typical characteristics, and belongs to the technical field of carrier rocket overall design.
Background
With the rapid development of new materials and new processes, low cost has become the subject of recent development in the field of aerospace transportation. Based on the current technical level and development trend, the realization of one-sub-level vertical recovery of the carrier rocket is the main path of low-cost transportation. The key point of the reuse of a first sub-stage of the carrier rocket is the liquid rocket engine, so the development of a reusable carrier rocket engine with high performance, low cost and high reliability is imperative. However, the existing carrier rocket engines in China are designed for one-time launching, and in the face of a one-sub-stage vertical take-off and landing recovery scheme of the carrier rocket, higher requirements are put forward on the existing rocket engines, such as increased thrust transformation ratio requirements, increased starting times requirements, more complex external mechanical environment and thermal environment, and the like, and how to judge whether an engine meets the condition of reusing the rocket engines for vertical take-off and landing transportation becomes a difficult point for restricting the development of the vertical take-off and landing reusing the carrier rocket. Therefore, a scientific and reasonable discrimination method for the reusable rocket engine is urgently needed at present to judge whether the engine is suitable for a vertical recycling and reusing scene or not from the characteristics of the engine.
Disclosure of Invention
The purpose of the present disclosure is to overcome the drawbacks of the prior art, and to solve the above technical problems partially or completely, to provide a method and apparatus for identifying a reusable rocket engine based on typical features.
The purpose of the present disclosure is achieved by the following technical solutions.
In a first aspect, the present disclosure provides a method for identifying a reusable rocket engine based on typical features, comprising:
s1, obtaining an engine needing to be distinguished;
s2, judging the engine according to the multiplexing external features of the engine, if the multiplexing external features are not met, judging that the engine is not a rocket engine which is repeatedly used, and exiting;
s3, distinguishing the engine according to the multiplexing intrinsic characteristics of the engine, and if the multiplexing intrinsic characteristics are met, judging that the engine is a reusable rocket engine; otherwise the engine is not a re-use rocket engine.
In a second aspect, the present disclosure provides a reuse rocket engine discriminating device based on characteristic features, comprising an obtaining module, an extrinsic feature discriminating module and an intrinsic feature discriminating module, wherein,
the acquisition module is used for acquiring an engine needing to be distinguished;
the external feature judging module is used for judging whether the engine meets the engine multiplexing external feature;
the internal feature distinguishing module is used for distinguishing whether the engine meeting the engine multiplexing external features meets the engine multiplexing internal features.
In a third aspect, the present disclosure provides an electronic device comprising:
at least one processor; and (c) a second step of,
a memory communicatively coupled to the at least one processor; wherein the memory stores instructions executable by the at least one processor to enable the at least one processor to perform the method of any of the embodiments of the first aspect.
In a fourth aspect, the present disclosure provides a computer-readable storage medium having stored thereon a computer program which, when executed by a processor, causes the processor to perform the method according to any of the embodiments of the first aspect.
Advantageous effects
The method for judging the reusable rocket engine based on the typical characteristics can clearly judge whether the given engine reaches the condition of the reusable rocket engine for vertical take-off and landing carrying, so that the generation of the capability of the reusable rocket engine is further guided, and the development of the reusable carrier rocket is promoted.
Drawings
FIG. 1 is a schematic flow chart of a method for identifying a reusable rocket motor based on typical features according to an embodiment of the present disclosure;
FIG. 2 is a non-dimensional change in the life cycle cost of a single rocket per time with the number of times a single rocket is launched;
FIG. 3 is a graph showing the change of dimensionless cost of a single rocket in a whole life cycle with the number of times of launching the single rocket for two rockets;
FIG. 4 is a schematic diagram of propellant flow, nozzle area ratio, sea level specific impulse and thrust force variation with supercooling increment;
FIG. 5 is a schematic diagram of the variation of the first-stage thrust of a rocket with version;
fig. 6 is a schematic structural diagram of an electronic device according to an embodiment of the present disclosure.
Detailed Description
The present disclosure will be described in detail below with reference to specific embodiments shown in the drawings. These embodiments are not limited to the disclosure, and structural, methodological, or functional changes made by those of ordinary skill in the art in light of these embodiments are intended to be within the scope of the disclosure.
For the purpose of illustrating the objects, technical solutions and advantages of the embodiments of the present disclosure, the technical solutions in the embodiments of the present disclosure will be clearly and completely described below with reference to the drawings in the embodiments of the present disclosure.
The reduction of the launch cost of the carrier rocket, namely aerospace transportation, and the development of the reusable carrier rocket in China has become common knowledge in the industry. Based on the current technical level and development trend, the realization of one-sub-level vertical recovery and reuse of the carrier rocket is a main path for low-cost transportation. The key point of the reuse of a first sub-stage of the carrier rocket is the rocket engine, so the development of a reusable carrier rocket engine with high performance, low cost and high reliability is imperative. The existing carrier rocket engines in China are all designed for one-time launching, and in the face of a one-stage vertical take-off and landing recovery scheme of a carrier rocket, higher requirements are put forward on the existing rocket engines, such as increased thrust transformation ratio requirements, increased starting times requirements, more complex external mechanical environment and thermal environment, and the like, and the difficulty that how to judge whether one engine meets the condition of reusing the rocket engine for vertical take-off and landing transportation becomes the restriction on the development of reusing the carrier rocket for vertical take-off and landing is difficult. The method judges the reusable rocket engine from the angle of one-level vertical recovery and reuse of the carrier rocket, and further guides the development and production of the reusable rocket engine through comprehensive typical feature description of the system, thereby providing a set of convenient automatic judgment method for selecting the reusable engine for the reusable carrier rocket.
As shown in fig. 1, the present disclosure provides a method for identifying a reusable rocket engine based on typical features, the method comprising:
s1, obtaining an engine needing to be distinguished;
s2, judging the engine according to the multiplexing external features of the engine, if the multiplexing external features are not met, the engine does not repeatedly use the rocket engine, and quitting;
s3, judging the engine according to the multiplexing intrinsic characteristics of the engine, and if the multiplexing intrinsic characteristics are met, judging that the engine is a reusable rocket engine; otherwise the engine is not a re-use rocket engine.
The method disclosed by the invention is combined with a first-sublevel vertical recycling and reusing scene of the carrier rocket to research the characteristics of the repeatedly used rocket engine, the external characteristics and the internal characteristics of the engine are respectively judged from the reusing scene, and the given engine can be judged to belong to the repeatedly used rocket engine only after meeting all the characteristics, so that the method can be used for the first sublevel of the carrier rocket. The external characteristics are description of rocket engine function indexes, and the internal characteristics are description of rocket engine production and maintenance indexes.
As a specific implementation, the engine reuse appearance includes the following:
s11, the composite material can be repeatedly used for 10-30 times;
s12, the aircraft can be started repeatedly for at least 3 times in a single flight process;
s13, the lower limit of the thrust adjusting range of a single engine is not less than the number multiplied by 10 percent of the engines;
s14, the engine and the rocket body interface of the carrier rocket can move;
s15, the supercooling degree of the propellant of the engine is higher than that of a disposable engine;
and S16, the thrust is higher than that of a disposable engine.
For S11, the compound can be repeatedly used for 10-30 times. The reuse of the rocket determines the capability of the engine to be reused, and the reuse number of the rocket also determines the reuse number of the engine. Thus, the multiple use feature is necessarily the most direct and typical feature of reusing the engine. The purpose of multiple use is to reduce cost, so the specific number of times of reuse should be obtained by cost analysis. The total life cycle cost of a sub-level reusable carrier rocket can be calculated by adopting a calculation method in documents (reusable carrier rocket total life cycle cost analysis, missile and space carrier technology, 2016 (6): 82-85) and reusable carrier rocket technology development and prospect, missile and space carrier technology, 2017, (5): 1-7). FIGS. 2 and 3 show plots and histograms, respectively, of dimensionless single rocket full-life-cycle cost as a function of number of times a single rocket is launched for the upper limit of the proportionality factor (analysis of reusable launch vehicle full-life-cycle cost; missile and space launch technology, 2016, (6): 82-85.). It can be seen that for the production of 10 rockets, when the number of firings exceeds 10, the life cycle cost is reduced by more than 64.8%; when the emission times exceed 20 times, the whole life cycle cost is reduced by over 67.2 percent; when the emission times exceed 30 times, the cost of the whole life cycle is reduced by over 69.6 percent, the cost is not obviously reduced, and the flying repeated use times of the engine are more reasonable from 10 to 30 times by considering the factors that the reliability of the engine is reduced along with the increase of the repeated use times, the maintenance cost is increased and the like.
For S12, the launch can be repeated at least 4 times during a single flight. Research results show that for rocket-powered vertical take-off and landing aircrafts for verifying the related technology of vertical take-off and landing, such as DC-X, morpheus, grasshopper and the like, when the flight height of the aircraft is kilometer level, an engine can not be shut down. For the vertical take-off and landing carrier rocket, in order to save the propellant, the rocket engine is usually re-ignited and started for 2-3 times in the actual flight process (namely, one take-off and landing or flight process), so that the repeated use of the rocket engine has the capability of starting for multiple times. Preferably not less than 4 times.
For S13, the lower limit of the thrust adjustment range of a single engine is not more than the number of engines multiplied by 10 percent per engine.
Because the consumption of the vertical take-off and landing carrier rocket propellant in the flight process is large, the mass change of the carrier rocket in the vertical landing process is large, and therefore, in order to realize six-degree-of-freedom control in recovery, the thrust of the carrier rocket needs to be changed. Research has shown that the thrust requirement for a VTOL launch vehicle landing is about 1/10 of the takeoff thrust. Therefore, when 1 engine is adopted in a single-core stage of the rocket, the thrust transformation ratio needs to reach 10 to realize recovery, the method belongs to depth transformation thrust, and has a large variation range and high difficulty. In order to solve the problem, a layout mode of arranging the circle centers of n engines can be adopted in a single-core stage, and only the central engine works when landing, so that the thrust change requirement on the engine is greatly reduced, the implementation is easier, and the lower limit of the thrust regulation range of a single engine required by the n engines is n multiplied by 10%. Therefore, as long as the lower limit of the thrust adjusting range of the engine is not lower than n multiplied by 10 percent, the one-stage recovery scheme of the vertical take-off and landing carrier rocket can be met.
S14, the interface between the engine and the rocket body of the carrier rocket can move.
For the carrier rocket which is repeatedly used in vertical take-off and landing, under the condition that the engine cannot be maintained on the rocket, the repeated use of the carrier rocket requires that the engine can be maintained by descending the rocket or be replaced when necessary, so that in order to avoid damaging the rocket body, the mechanical interface of the rocket and the engine is in a movable state, namely the rocket and the engine are movably connected, and if the existing welding connection mode is changed into bolt connection, the connecting interface is detachable, so that the engine is convenient to replace.
And S15, the supercooling degree of the propellant of the engine is higher than that of a disposable engine.
The reuse of a sub-stage of the launch vehicle requires the consumption of more propellant and therefore the carrying of a greater quantity of propellant, which results in a larger volume of propellant tank. The data in the reference (trajectory analysis of vertical recovery mission of reused rocket, missile and space vehicle technology, 2018, (5): 21-26, 50.) is that a sub-level of a certain type of carrier rocket is used as an object, after one-level and two-level separation is considered, the ignition is returned for 50s, the ignition is returned for 20s, the ignition is landed for 30s, the ignition is returned and returned for 3 engines to work, the landing is performed for 1, and the volume of the liquid oxygen storage tank under the reuse condition after one sub-level is once used, reused and the supercooling degree of the propellant is improved is calculated, and is shown in table 1. It can be seen that the reuse rate is increased by approximately 16.6% over the mass of the single use propellant. On the other hand, when the supercooling degree is not increased, the volume of the primary reuse storage tank is increased by 16.6 percent compared with the volume of the disposable storage tank, when the supercooling degree is increased by 5K, the volume of the storage tank is increased by 14.2 percent, when the supercooling degree is increased by 10K, the volume of the storage tank is increased by 11.9 percent, which shows that the increase of the supercooling degree can play a certain role in reducing the volume of the storage tank. However, the increase of the supercooling degree increases the cost of the propellant, and the increase of the storage tank causes the increase of the structural cost of the rocket and the reduction of the carrying capacity when the supercooling degree is not increased, and the unit costs of the propellant and the storage tank should be comprehensively considered to analyze the comprehensive benefits of the supercooling degree improvement.
TABLE 1 one-sublevel disposable vs. reusable liquid oxygen tank volumes
* The adaptation improvement of one sub-stage in reuse is not considered for the moment.
On the other hand, under the condition that the volume flow of the propellant is not changed, the supercooling degree of the low-temperature propellant is improved, the mass flow can also be improved, and the thrust is further improved. Taking a certain type of carrier rocket as an example, assuming that the mixing ratio and the outlet pressure of the nozzle are unchanged, the fuel flow is synchronously increased along with the oxygen flow, and the variation conditions of the propellant flow, the nozzle area ratio, the sea level specific impulse and the thrust along with the increment of the supercooling degree are calculated, as shown in fig. 4. It can be seen that the degree of supercooling of liquid oxygen increases, the propellant flow rate increases, the maximum increase is 8.3%, and the chamber pressure can be considered to increase approximately linearly with the increase in propellant flow rate when the mixing ratio is unchanged. While the nozzle outlet pressure remained constant (0.682 atm), the increase in chamber pressure resulted in an increase in nozzle area ratio, but the maximum increase was only 6%, further resulting in an increase in sea level specific impulse, but only 0.6%. The resulting increase in both flow and specific impulse results in an increase in thrust, but the primary source is an increase in propellant flow.
And S16, the thrust is higher than that of a disposable engine.
Because more propellant is consumed for recycling, the mass of the rocket storage tank and the rocket body structure and the mass of the carried propellant are increased, and in addition, an additional recycling and landing device is required to be added, the thrust of the primary engine is properly excavated and higher than that of a disposable engine, and the carrying capacity loss (the original field return loss is nearly 40 percent, and the non-original field return loss is nearly 20 percent) caused by the increase of the rocket mass can be made up. Research has shown that some type of launch vehicle has been thrust driven for rocket reuse, as shown in figure 5. It can be seen that the thrust of the Merlin-1D engine is improved by nearly 100% from the initial version to the final version.
The above example describes the functional indexes of the reusable rocket engine meeting the use requirements of the scene by combining the application scene of one-sub-level vertical recovery and reuse of the carrier rocket, and the typical characteristic systems comprehensively illustrate the functional requirements of the reusable rocket engine.
As a specific implementation, the engine reuse intrinsic characteristics include: has the characteristics of light structure, is made of reusable elements or components, and is convenient to maintain.
S21, the structure is light.
The repeated use of the carrier rocket can increase the weight of the rocket, so the repeated use of the other connotation is light weight so as to make up for the loss of carrying capacity caused by the increased weight. The light weight mainly has three meanings, namely, the light weight material is adopted, the parameter optimization is carried out, the structural quality is lightened, and a novel manufacturing technology is adopted.
Aiming at the research of light materials, after the storage tank with the diameter of 3.35m adopts the aluminum lithium alloy, compared with the international mainstream aluminum copper alloy, the structure is reduced by more than 15%; after the composite material is adopted, the weight is reduced by over 30 percent, and the comprehensive cost of the rocket is reduced by over 25 percent.
The research result aiming at parameter optimization shows that the thrust chamber mass is reduced by 5.9% when the chamber pressure is increased from 10MPa to 15MPa when the ratio of the thrust to the area of the nozzle is unchanged by adopting an empirical estimation model of the thrust chamber (oxyhydrogen rocket engine and low-temperature technology thereof, china aerospace Press, 2016) given by Zhu Senyuan Ouchi. For an electric pump engine, the battery mass fraction is large. According to a calculation model in literature (System Scheme Design for Lox/Lch4 Variable Using Motor Pump. Acta Astronautica, 2020, 171: 139-150.), when the power density dominates the battery quality, the lithium polymer battery quality is 1/5 of that of the lithium sulfur battery; the lithium sulfur battery mass is 37% of the lithium polymer battery mass when the energy density dominates the battery mass.
Aiming at the research of a novel manufacturing technology, a thin-wall and compact structural member can be manufactured by adopting an additive manufacturing technology, such as 3D printing, and the conventional manufacturing structure is miniaturized, so that the aim of reducing weight is fulfilled. Research results show that the volume and the weight of the aviation plate-fin heat exchanger can be reduced by 20% through a 3D printing technology. On the other hand, 3D printing can be used for applying the continuous fiber conforming material to a complex configuration structure, so that weight reduction is indirectly realized.
In the case of a reusable rocket engine, the engine is manufactured by at least one of the following techniques, namely, by any of the above methods, i.e., by providing a weight reduction feature: lightweight materials, structural mass reduction by parameter optimization or novel manufacturing techniques
And S22, manufacturing by using reusable elements or components.
The reuse of the rocket engine requires that the engine components/elements can also be reused, so that disposable components or elements in the engine, such as a cartridge igniter, an ablative heat protection material and the like, are eliminated to meet the inherent requirement of reuse; components unsuitable for multiple use, such as chemical ignition devices, oxygen-rich gas generators, etc., are minimized.
And S23, maintenance is facilitated.
For reusing the rocket engine, it is necessary to facilitate maintenance. The maintenance convenience should have three meanings, namely, the maintenance time is short and is not higher than a preset time threshold t, such as 48 hours; secondly, the maintenance cost is low and is not higher than a preset cost threshold value m, such as 25 ten thousands; and thirdly, the maintenance difficulty is small and is not higher than a preset human-hour threshold value k (namely, the number of people required for maintenance once is x hour = k human-hours), such as 200 human-hours. Research data show that the space shuttle can be launched for 9 times at most one year due to long maintenance time, and the goal of 50 times per year can not be reached; due to high maintenance cost, the cost of each launch of the space shuttle is up to 4-5 hundred million dollars, which is far higher than the originally set 3000 ten thousand dollars; because space shuttle has thousands of branch system and millions of parts, the maintenance degree of difficulty is big, for example the total 31000 many heat protection tiles of heat protection system, about 50 heat protection tiles need to be changed after every flight, but all heat protection tiles need to be overhauled after flying.
The reusable rocket engine distinguishing method provided by the disclosure judges the external characteristics and the internal characteristics of the reusable rocket engine from the first-sub-level vertical recovery and reuse angle of the carrier rocket, meets the practical use requirements, and can achieve the purposes of judging whether the engine is reusable or not and whether the engine can be used for the vertical take-off and landing carrier rocket or not; the rocket engine is further judged through comprehensive typical feature description of a construction system, on one hand, research and production of the reusable rocket engine are guided, and on the other hand, a set of judgment method easy to realize automation is provided for selecting the reusable engine of the vertical take-off and landing reusable carrier rocket.
The disclosure also provides a device for judging the reusable rocket engine based on the typical characteristics, which comprises an acquisition module, an external characteristic judging module and an internal characteristic judging module, wherein,
the acquisition module is used for acquiring an engine needing to be distinguished;
the external feature judging module is used for judging whether the engine meets the engine multiplexing external feature;
the internal feature distinguishing module is used for distinguishing whether the engine meeting the engine multiplexing external features meets the engine multiplexing internal features.
Optionally, the engine multiplexing appearance comprises:
s11, the composite material can be repeatedly used for 10-30 times;
s12, the aircraft can be started repeatedly for at least 3 times in a single flight process;
s13, the lower limit of the thrust adjusting range of a single engine is not less than the number multiplied by 10 percent of the engines;
s14, the engine and the rocket body interface of the carrier rocket can move;
s15, the supercooling degree of the propellant of the engine is higher than that of a disposable engine;
and S16, the thrust is higher than that of a disposable engine.
Optionally, the engine multiplexing intrinsic characteristics include: has the characteristics of light structure, is made of reusable elements or components, and is convenient to maintain.
For the device embodiment, since it is basically similar to the method embodiment, the description is simple, and for the relevant points, refer to the partial description of the method embodiment.
Fig. 6 is a schematic structural diagram of an electronic device according to an embodiment of the present disclosure, where the electronic device may execute the processing flow provided by the foregoing method embodiment, and as shown in fig. 6, the electronic device 110 includes: memory 111, processor 112, computer programs, and communications interface 113; wherein the computer program is stored in the memory 111 and configured to be executed by the processor 112 for performing the method as described above.
In addition, the embodiment of the present disclosure also provides a computer readable storage medium, on which a computer program is stored, the computer program being executed by a processor to implement the method of the above embodiment. Those of ordinary skill in the art will understand that: all or a portion of the steps of implementing the above-described method embodiments may be performed by hardware associated with program instructions. The program may be stored in a computer-readable storage medium. When executed, the program performs steps comprising the method embodiments described above; and the aforementioned storage medium includes: various media that can store program codes, such as ROM, RAM, magnetic or optical disks.
Specific examples are given in this specification for the purpose of illustrating the disclosure and implementations. The details introduced in the examples are not intended to limit the scope of the claims but rather to aid in understanding the present disclosure. Those skilled in the art will understand that: although the present description has been described in terms of embodiments, not every embodiment includes only a single embodiment, and such descriptions are provided for clarity only, and it is to be understood that those skilled in the art will recognize that the embodiments described herein may be combined as a whole to form other embodiments as would be understood by those skilled in the art. And that various modifications, changes, or alterations to the steps of the preferred embodiments are possible without departing from the spirit and scope of this disclosure and the appended claims. Therefore, the disclosure should not be limited to the disclosure of the preferred embodiment and the drawings.
Claims (4)
1. A method for distinguishing a repeatedly used rocket engine based on typical characteristics is characterized by comprising the following steps: the method comprises the following steps:
s1, obtaining an engine needing to be distinguished;
s2, judging the engine according to the multiplexing external features of the engine, if the multiplexing external features are not met, the engine does not repeatedly use the rocket engine, and quitting;
the engine multiplexing appearance includes:
can be repeatedly used for 10-30 times;
the starting can be repeated for at least 3 times in a single flight process;
the lower limit of the thrust adjusting range of a single engine is not less than the number multiplied by 10 percent of the engines;
the interface between the engine and the rocket body of the carrier rocket can move;
the supercooling degree of the propellant of the engine is higher than that of a disposable engine;
thrust is higher than that of a disposable engine;
s3, judging the engine according to the multiplexing intrinsic characteristics of the engine, and if the multiplexing intrinsic characteristics are met, judging that the engine is a reusable rocket engine; otherwise the engine is not a re-use rocket engine;
the engine multiplexing intrinsic features include:
the structure is light; the three layers are included: firstly, a light material is adopted, secondly, parameter optimization is carried out, the structural quality is reduced, and thirdly, a novel manufacturing technology is adopted;
the engine is made of reusable components or assemblies, and disposable components or elements in the engine are eliminated;
the maintenance is convenient; the three layers are included: firstly, the maintenance time is short and is not higher than a preset time threshold t; secondly, the maintenance cost is low and is not higher than a preset cost threshold value m; and thirdly, the maintenance difficulty is small and is not higher than a preset human-time threshold value k, and when people are in need of maintenance once, the number of people is about hours.
2. A reusable rocket engine distinguishing device based on typical features is characterized in that: comprises an acquisition module, an extrinsic feature discrimination module and an intrinsic feature discrimination module, wherein,
the acquisition module is used for acquiring an engine needing to be distinguished;
the external feature judging module is used for judging whether the engine meets the engine multiplexing external feature;
the engine multiplexing appearance includes:
can be repeatedly used for 10-30 times;
the starting can be repeated for at least 3 times in a single flight process;
the lower limit of the thrust adjusting range of a single engine is not less than the number multiplied by 10 percent of the engines;
the interface between the engine and the rocket body of the carrier rocket can move;
the supercooling degree of the propellant of the engine is higher than that of a disposable engine;
thrust is higher than that of a disposable engine;
the internal feature distinguishing module is used for distinguishing whether the engine meeting the engine multiplexing external features meets the engine multiplexing internal features;
the engine multiplexing intrinsic features include:
the structure is light; the three layers are included: firstly, adopting light materials, secondly, developing parameter optimization and lightening the structural mass, and thirdly, adopting a novel manufacturing technology;
the engine is made of reusable components or assemblies, and disposable components or components in the engine are eliminated;
the maintenance is convenient; the three layers are included: firstly, the maintenance time is short and is not higher than a preset time threshold t; secondly, the maintenance cost is low and is not higher than a preset cost threshold value m; and thirdly, the maintenance difficulty is small and is not higher than a preset human-time threshold value k, and when people are in need of maintenance once, the number of people is about hours.
3. An electronic device, characterized in that the electronic device comprises:
at least one processor; and (c) a second step of,
a memory communicatively coupled to the at least one processor; wherein the memory stores instructions executable by the at least one processor to enable the at least one processor to perform the method of claim 1.
4. A computer-readable storage medium, on which a computer program is stored, which program, when being executed by a processor, causes the processor to carry out the method of claim 1.
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