CN117028076B - Rocket engine starting method and rocket - Google Patents
Rocket engine starting method and rocket Download PDFInfo
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- CN117028076B CN117028076B CN202311296338.1A CN202311296338A CN117028076B CN 117028076 B CN117028076 B CN 117028076B CN 202311296338 A CN202311296338 A CN 202311296338A CN 117028076 B CN117028076 B CN 117028076B
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
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- Aviation & Aerospace Engineering (AREA)
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- Combined Controls Of Internal Combustion Engines (AREA)
Abstract
The invention provides a rocket engine starting method and a rocket. The rocket is provided with a plurality of engines, and the engines are all connected in parallel; the starting method comprises the following steps: acquiring first parameter information of a rocket and second parameter information of an engine; grouping all the engines according to the first parameter information of the rocket and the second parameter information of the engines; and determining the starting sequence among different groups, and starting each engine unit according to the starting sequence, wherein all engines in a single engine unit are started simultaneously. The invention provides a starting method of a rocket engine and a rocket, which can reduce the power supply requirement of the rocket on starting the engine, provide opportunities for a rocket control system to judge the engine state, and can correspondingly treat the problems and improve the rocket launching reliability.
Description
Technical Field
The invention relates to the technical field of rockets, in particular to a starting method of a rocket engine and the rocket.
Background
In the related technology, the engines used at the first stage of the rocket in China at present are generally in a structure of 2 machines connected in parallel, 3 machines connected in parallel or 4 machines connected in parallel, and are started simultaneously. However, when the existing 2-4 parallel rocket engines are started simultaneously, a larger starting current is required, and the requirement on the rocket power supply capacity of the rocket is high. In addition, when one engine fails, the rocket cannot take off and the launching needs to be terminated urgently. In other words, for a mode of starting multiple engines in parallel simultaneously, on one hand, the mode has higher requirements on power supply capacity on a rocket, and on the other hand, the probability of successful starting of all engines at one time is reduced due to the increase of the number of the engines.
Therefore, the tolerance to the engine fault is 0 in a mode of connecting 2-4 machines in parallel and starting at the same time. In order to solve the problems, some rockets are started simultaneously by adopting 4 machines, but the engines work in a low thrust state, so that the thrust is smaller than the gravity of the rockets, and when the working condition of the 4 machines is judged to be normal, the thrust is adjusted to a maximum thrust state, so that the rocket take-off is completed. The low-thrust and high-thrust simultaneous starting mode is suitable for a parallel combination mode of 4 engines and below, and for a parallel combination mode of 5 engines and above carding engines, the risk that the subsequent flight procedure is influenced by the failure of starting the larger engine still exists.
Disclosure of Invention
The invention provides a starting method of a rocket engine and the rocket, which are used for solving the defects existing in the prior art and realizing the following technical effects: the power supply requirement on the rocket for starting the engine can be reduced, opportunities are provided for the rocket control system to judge the engine state, the problems can be correspondingly processed, and the rocket launching reliability is improved.
According to the starting method of the rocket engine, which is provided by the embodiment of the first aspect of the invention, the rocket is provided with a plurality of engines which are connected in parallel;
the starting method comprises the following steps:
acquiring first parameter information of a rocket and second parameter information of an engine;
grouping all the engines according to the first parameter information of the rocket and the second parameter information of the engines;
and determining the starting sequence among different groups, and starting each engine unit according to the starting sequence, wherein all engines in a single engine unit are started simultaneously.
According to one embodiment of the invention, the first parameter information comprises a takeoff thrust ratio of the rocket, and the second parameter information comprises the total number of the engines and the total position distribution condition of the engines in the rocket.
According to one embodiment of the present invention, the step of grouping all the engines according to the first parameter information of the rocket and the second parameter information of the engines specifically includes:
determining the total group number of all the engines after grouping and the number of single-group engines in each group according to the takeoff thrust ratio and the total number of the engines;
and determining a first distribution condition of each engine in each group in the rocket and a second distribution condition of each group of engine units in the rocket according to the total group number, the single group number and the total position distribution condition of the engines in the rocket.
According to one embodiment of the invention, the total number of groups is greater than or equal to 2, the number of single-group engines is greater than or equal to 2, and the individual engines within each group are symmetrical with respect to the central axis of the rocket or with respect to the plane of symmetry of the rocket.
According to one embodiment of the present invention, the step of determining the start-up sequence between the different groups specifically includes:
obtaining a single thrust-weight ratio between the thrust of a single engine and the total weight of the rocket;
calculating to obtain the total thrust-weight ratio in each engine unit according to the single thrust-weight ratio and the number of single engines in each engine unit;
and determining the starting sequence among the engine units according to the total thrust weight ratio in the groups, the total group number and the takeoff thrust weight ratio of the rocket.
According to one embodiment of the invention, the sum of the total weight ratios in the group of all the engine blocks that have been started before the last engine block is started is less than 1.
According to one embodiment of the present invention, the step of sequentially starting each engine unit according to the starting sequence specifically includes:
and determining the starting interval duration between two adjacent engine units, and sequentially starting each engine unit according to the starting sequence and every other starting interval duration.
According to one embodiment of the present invention, the step of sequentially starting each engine unit according to the starting sequence and at intervals of the starting interval length specifically includes:
and during each starting interval period, detecting faults of the various engines in the engine unit which is started before, and stopping the starting of the rocket when at least one engine is detected to be faulty.
According to one embodiment of the invention, the value of the starting interval duration ranges from 0.1s to 2s.
According to the rocket according to the embodiment of the second aspect of the present invention, the rocket is provided with a plurality of engines, the plurality of engines are all connected in parallel, and the rocket is based on the starting method of the rocket engine according to the embodiment of the first aspect of the present invention so as to realize the take-off of the rocket.
The invention provides a starting method of rocket engines, which can be suitable for rocket structures with the number of engines being 2 to 4 and rocket structures with the number of engines being 5 or more, and concretely, the invention groups all engines in a single rocket according to parameter information of the rocket and the engines, determines starting sequences among different groups of engines, and sequentially controls each engine unit to start according to the starting sequences, thereby completing the engine starting process of the whole rocket and helping the rocket take off smoothly.
In summary, according to the control method of the rocket engine according to the embodiment of the invention, a plurality of engines connected in parallel are grouped, one group of engines is started simultaneously, and different groups of starting times are staggered, so that on one hand, the power supply requirement on starting the engines on the rocket can be reduced, on the other hand, the single starting group of engines can provide small relative total thrust ratio, which is insufficient for taking off the rocket, the opportunity is provided for a rocket control system to judge the engine state, and the problems can be correspondingly processed.
Drawings
In order to more clearly illustrate the invention or the technical solutions of the prior art, the following description will briefly explain the drawings used in the embodiments or the description of the prior art, and it is obvious that the drawings in the following description are some embodiments of the invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic flow chart of a method for starting a rocket engine according to the present invention;
FIG. 2 is a second flow chart of a method for starting a rocket engine according to the present invention;
FIG. 3 is a schematic view of the rocket engine distribution provided by the invention;
FIG. 4 is a schematic diagram of a start sequence provided by the present invention for starting one set of engines at intervals of a start interval duration and starting another set of engines;
FIG. 5 is a schematic view of the configuration of the rocket engine start control device provided by the invention;
fig. 6 is a schematic structural diagram of an electronic device provided by the present invention.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings, and it is apparent that the described embodiments are some embodiments of the present invention, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present specification, a description referring to terms "one embodiment," "some embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the embodiments of the present invention. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.
The method for starting the rocket engine, the control device and the rocket provided by the invention are described below with reference to the accompanying drawings. Before the embodiments of the present invention are described in detail, the entire application scenario is described. The starting method, the control device, the electronic equipment and the computer readable storage medium of the rocket engine can be applied to rocket local area, cloud platform in the internet field, cloud platform in other kinds of internet fields or third party equipment. The third party device may include a mobile phone, a tablet computer, a notebook computer, a vehicle-mounted computer, and other intelligent terminals.
In the following, a starting method of an engine suitable for a rocket is merely described as an example, and it should be understood that the control method of the embodiment of the present invention may also be suitable for cloud platform and third party devices.
It should be noted that the starting method of the present invention is applicable to rockets with multiple engines, that is, rockets are provided with multiple engines, and the multiple engines are connected in parallel.
As shown in fig. 1, a method for starting a rocket engine according to an embodiment of the first aspect of the present invention includes:
step S1, acquiring first parameter information of a rocket and second parameter information of an engine;
s2, grouping all the engines according to the first parameter information of the rocket and the second parameter information of the engines;
and step S3, determining the starting sequence among different groups, and starting each engine unit in sequence according to the starting sequence, wherein all engines in a single engine unit are started simultaneously.
According to the starting method of the rocket engine, the specific starting process is as follows: firstly, first parameter information of a rocket and second parameter information of an engine need to be acquired, the first parameter information mainly comprises parameter information such as weight of the rocket, and the second parameter information mainly comprises parameter information such as total thrust of all engines, number of all engines, thrust of a single engine, distribution position of the engine relative to the rocket, and the like, so that after the first parameter information and the second parameter information are acquired, influence of the number and the position of different engines on a rocket take-off process after being combined together is conveniently analyzed, and therefore all the engines can be reasonably grouped based on the first parameter information and the second parameter information, namely, all the engines are divided into at least two engine units.
After the grouping of the engines is completed, the method further determines the starting sequence among the engines of different groups, and sequentially starts each engine group according to the starting sequence, and it should be pointed out that the starting sequence refers to the starting sequence among the engines of different groups, that is, the engines of different groups are sequentially started according to the starting sequence, and all the engines in the same group are simultaneously started when the engines of the group are started.
In order to solve the technical problems in the related art, the invention provides a starting method of rocket engines, which can be suitable for rocket structures with the number of engines ranging from 2 to 4 and rocket structures with the number of engines ranging from 5 and more, and particularly, the invention groups all engines in a single rocket according to parameter information of the rocket and the engines, determines starting sequences among different groups of engines, and sequentially controls the starting of each engine unit according to the starting sequences, thereby completing the engine starting process of the whole rocket and helping the rocket take off smoothly.
For the starting method provided by the invention, on one hand, the method reduces the power supply current required by single starting of each group of engines by controlling the engines to start in groups, thereby reducing the power supply requirement of the rocket on starting the engines and further reducing the design difficulty of the rocket power supply system.
For example, the total number of engines of the rocket is 7, and the engines are mutually connected in parallel, assuming that 10A current is required when a single engine is started, 70A current is required when 7 engines are started simultaneously, and according to a preferred 4-3 grouping time-sharing starting mode, namely 7 engines are divided into two groups, one group of engines is 4 in number and is started preferentially, the other group of engines is three in number and is started subsequently, the starting current is 40A at maximum, and the required current drop rate is 42.8%.
For another example, the total number of the engines of the rocket is 9, the engines are mutually connected in parallel, and assuming that 10A current is needed when a single engine is started, 90A current is needed when 9 engines are started simultaneously, and according to a preferable 3-3-3 grouping time-sharing starting mode, namely, the 9 engines are divided into three groups, the number of each group of engines is three, and the three groups of engines are sequentially started according to the starting sequence, the maximum current needed by the engines during starting is reduced from 90A to 30A, and the current reduction rate is 66.7%.
On the other hand, the starting method provided by the invention has the advantages that the ratio of the thrust provided by a group of engines started at a time relative to the total thrust is small and insufficient to enable the rocket to take off, so that opportunities are provided for judging the engine state of the rocket control system, and the problems can be correspondingly processed. For example, after each group of engines is started, a rocket control system is utilized to detect faults of all engines in the group, and when the occurrence of engine faults is detected, the starting process of the rocket engine can be timely interrupted and corresponding disposal measures can be carried out, so that the rocket launching reliability is greatly improved.
In summary, according to the control method of the rocket engine according to the embodiment of the invention, a plurality of engines connected in parallel are grouped, one group of engines is started simultaneously, and different groups of starting times are staggered, so that on one hand, the power supply requirement on starting the engines on the rocket can be reduced, on the other hand, the single starting group of engines can provide small relative total thrust ratio, which is insufficient for taking off the rocket, the opportunity is provided for a rocket control system to judge the engine state, and the problems can be correspondingly processed.
According to some embodiments of the invention, the first parameter information includes a launch thrust ratio of the rocket, and the second parameter information includes a total number of engines and a total position distribution of the engines within the rocket.
Wherein, the ratio of the takeoff thrust weight of the rocket is as follows: when the rocket takes off, the ratio of the total thrust of the engine to the weight of the rocket taking off. The takeoff thrust ratio is larger than 1, and the takeoff thrust ratio of the liquid rocket is generally between 1.2 and 2. In the method, in order to obtain the takeoff thrust ratio of the rocket, the takeoff weight of the rocket and the total thrust of all engines are firstly obtained, so that the takeoff thrust ratio of the rocket is calculated, wherein the total thrust of the engines is calculated according to the total number of the engines and the single thrust of a single engine.
As shown in fig. 2, according to some embodiments of the present invention, the step of grouping all the engines according to the first parameter information of the rocket and the second parameter information of the engines specifically includes:
and determining the total group number of all the engines after grouping and the number of single-group engines in each group according to the take-off thrust-weight ratio and the total number of the engines.
It will be appreciated that the take-off thrust-to-weight ratio and the total number of engines determine the total number of groups and the number of generators in a single group. For example, the total number of engines of the rocket is 9 and the individual engines are connected in parallel with each other. If the ratio of the takeoff thrust of the rocket is less than 1.33, the 9 engines can be divided into 2 groups, wherein 6 engines are the first group, and 3 engines are the second group, and at the moment, the first group is started and then the second group is started; alternatively, the 9 engines may be divided into 3 groups, wherein each 3 engines is 1 group, and the first group, the second group and the third group are started in this order. If the thrust-to-weight ratio of the rocket takeoff is greater than 1.33, based on the grouping principle, the 9 engines can be divided into two groups, wherein the number of the first group of engines is 5, and the number of the second group of engines is 4, so that the thrust of the started first group of engines is insufficient to enable the rocket takeoff before the second group of engines is started.
As shown in fig. 2, further, according to some embodiments of the present invention, the step of grouping all the engines according to the first parameter information of the rocket and the second parameter information of the engines further includes:
and determining a first distribution condition of each engine in each group in the rocket and a second distribution condition of each group of engine units in the rocket according to the total group number, the single group number and the total position distribution condition of the engines in the rocket.
In summary, in the method, the grouping process of the engines is mainly divided into two steps, the first step is dividing the total number of the engines and the number of the single engines in each group, the second step is dividing the first distribution condition of the engines in each group in the rocket and the second distribution condition of the engine groups in each group in the rocket, and it can be understood that the first step can ensure the rationality of the grouping number and the second step can ensure the rationality of the grouping positions.
Further, the grouping process of the above engine needs to satisfy the following principles: the total number of groups is more than or equal to 2, the number of single-group engines is more than or equal to 2, and each engine in each group is symmetrical relative to the central axis of the rocket or symmetrical relative to the symmetry plane of the rocket.
Therefore, when a single engine group is started, as each engine in each group is symmetrical relative to the central axis of the rocket or symmetrical relative to the symmetrical plane of the rocket, the thrust exerted by the engine on the rocket can be always kept in the vertical direction, so that unbalanced rocket caused by uneven thrust exerted by the engine on each position of the rocket is avoided, inclination and even tilting of the rocket in the process of taking off are avoided, and smooth taking off of the rocket is ensured.
For example, the total number of engines for the rocket is 7 and the individual engines are connected in parallel with each other, the engines being started in 4-3 groups in time sharing. The first group comprises 4 engines, the second group comprises 3 engines, and the parallel arrangement form and the number of 7 engines are shown in figure 3, wherein the engines 3, 4, 6 and 7 are arranged in one group, the engines 1, 2 and 5 are arranged in the second group, and when the engines are started in groups, the four engines 3, 4, 6 and 7 in the first group are started simultaneously, and the three engines 1, 2 and 5 in the second group are started simultaneously.
It can be seen that the engines 3, 4, 6 and 7 of the first group are symmetrical along the central axis of the rocket, so that when the engines of the first group are started, the rocket can be kept in a vertical state and is not unbalanced because the thrust exerted by the engines on the rocket is uniform and the stress positions of the rocket are symmetrical, and secondly, the engines 1, 2 and 5 of the second group are also symmetrical along the central axis of the rocket, so that the rocket can still be kept in a vertical state and is not unbalanced when the engines of the second group are started.
As shown in fig. 2, according to some embodiments of the present invention, the step of determining the start-up sequence between different groups specifically includes:
obtaining a single thrust-weight ratio between the thrust of a single engine and the total weight of the rocket;
calculating to obtain the total thrust-weight ratio in each engine unit according to the single thrust-weight ratio and the number of single engines in each engine unit;
and determining the starting sequence among the engine units according to the total thrust weight ratio in the groups, the total group number and the takeoff thrust weight ratio of the rocket.
In this embodiment, the starting sequence among the engine units needs to be determined through the total thrust ratio in the groups, the total group number and the takeoff thrust ratio of the rocket, and it should be pointed out that the determining principle of the starting sequence in the method is as follows: the total thrust of all the engine blocks that have been started before the last set of engines is insufficient to support the rocket for takeoff.
Specifically, the determination principle of the starting sequence is shown in the thrust-weight ratio: before the last engine block is started, the sum of the total push-to-weight ratios in the set of all the engine blocks that have been started is less than 1.
In this way, the rocket can take off only after all the engines of all the groups are started, and enough time can be reserved for the state detection of the rocket engines.
For example, the total number of engines for the rocket is 7 and the individual engines are connected in parallel with each other, the engines being started in 4-3 groups in time sharing. The first group comprises 4 engines, the second group comprises 3 engines, and the parallel arrangement form and the number of 7 engines are shown in figure 3, wherein the engines 3, 4, 6 and 7 are arranged in one group, the engines 1, 2 and 5 are arranged in the second group, and when the engines are started in groups, the four engines 3, 4, 6 and 7 in the first group are started simultaneously, and the three engines 1, 2 and 5 in the second group are started simultaneously.
The ratio of the total thrust of the engine structures connected in parallel by 7 machines to the thrust of the rocket is 1.4, and the ratio of the thrust of the first group of engines to the weight of the rocket after ignition is 1.4/7×4=0.8, and the thrust is smaller than the weight of the rocket at the moment, so that the first group of engines is insufficient to take off the rocket after starting. When the second group of engines is started, the ratio of the total thrust of the engines to the weight of the rocket reaches the takeoff thrust-weight ratio of 1.4, and finally the rocket enters the next stage of takeoff process.
As shown in fig. 2, according to some embodiments of the present invention, the steps of sequentially starting each engine block according to a starting sequence specifically include:
and determining the starting interval duration between two adjacent engine units, and sequentially starting each engine unit according to the starting sequence and every starting interval duration.
It will be appreciated that the present embodiment takes the form of time-sharing start during the rocket engine start, where time-sharing start refers to starting the second set of engines at intervals after the first set of engines starts, starting the third set of engines at intervals, and so on.
In this way, in the time-sharing starting, the set starting interval time reserves the engine state detection time for the control system, and if the engine starting fault is found, corresponding treatment can be carried out, so that the rocket launching reliability is improved.
Specifically, the method comprises the steps of sequentially starting each engine unit according to a starting sequence and at intervals of starting time, wherein the steps specifically comprise:
during each start interval, fault detection is performed on each engine in the previously started engine block, and the start of the rocket is stopped when at least one engine is detected to be faulty.
The fault detection method is as follows: the running parameters and running states of all the engines are continuously monitored through the data recorded in the sensor module or the system, so that whether a single engine has a starting fault or not is judged, wherein the fault condition of the engine can be judged through monitoring parameters such as the pressure of a propulsion chamber, the pressure of a propellant, the temperature of the propulsion chamber, the rotating speed of a turbopump and the like of the engine.
According to some embodiments of the invention, the value of the start interval duration ranges from 0.1s to 2s. Therefore, the starting time of the engine is enough to ensure the complete starting of the engine, and the waste of fuel caused by serious idle combustion of the engine due to overlong starting interval time can be avoided, so that the cost is saved, and the safety and the reliability are improved.
For example, the total number of engines of the rocket is 7, the engines are mutually connected in parallel, the engines are grouped according to 4-3, after the first group of 4 engines are started, the rocket control system judges that the first group of engines are started normally, and then the second group of 3 engines are started. The preferred starting interval duration is between 0.1s and 2s, as shown in fig. 4, where it is assumed that the moment of starting the first group of engines is t1 and the moment of starting the second group of engines is t2, the phase difference interval Δt between t2 and t1 is the starting interval duration, that is, Δt is preferably between 0.1s and 2s.
The following describes a start control device of a rocket engine provided by the invention, and the start control device of the rocket engine described below and the start method of the rocket engine described above can be referred to correspondingly.
As shown in fig. 5, a start control device for a rocket engine according to an embodiment of the present invention includes:
an acquisition module 110, configured to acquire first parameter information of a rocket and second parameter information of an engine;
the first execution module 120 is configured to group all the engines according to the first parameter information of the rocket and the second parameter information of the engines;
the second execution module 130 is configured to determine a starting sequence between different groups, and sequentially start each engine group according to the starting sequence, and all the engines in a single engine group are started simultaneously.
According to the rocket according to the embodiment of the second aspect of the invention, the rocket is provided with a plurality of engines, the plurality of engines are connected in parallel, and the rocket realizes the take-off of the rocket based on the starting method of the rocket engine described in the embodiment of the first aspect of the invention.
Specifically, the rocket includes a control device for executing the starting method of the rocket engine described in the first aspect.
In summary, according to the rocket of the embodiment of the present invention, the starting process of the engines is implemented by using a grouping time-sharing manner, where grouping starting refers to grouping a plurality of engines, where the engines in each group act simultaneously, such as executing a starting program. The general grouping principle is to ensure that the maximum thrust generated by all the started engines before the last started group is smaller than the thrust required by the rocket takeoff, and the engines in each grouping are symmetrical relative to the rocket axis or plane of symmetry relative to the rocket symmetry plane, and can be generally divided into 2 groups, 3 groups or more groups according to the number of the engines. Time-sharing start refers to starting a second group of engines at intervals after starting a first group of engines, starting a third group of engines at intervals, and so on.
Therefore, the multiple engines connected in parallel are grouped, one group of engines is started at the same time, starting times of different groups of engines are staggered, on one hand, the power supply requirement of the starting engines on the rocket is reduced, on the other hand, the group of engines started at a time can provide small relative total thrust ratio, which is insufficient for taking off the rocket, the opportunity is provided for a rocket control system to judge the engine state, and the problems can be correspondingly processed.
Fig. 6 illustrates a physical schematic diagram of an electronic device, as shown in fig. 6, which may include: processor 810, communication interface (Communications Interface) 820, memory 830, and communication bus 840, wherein processor 810, communication interface 820, memory 830 accomplish communication with each other through communication bus 840. Processor 810 may invoke logic instructions in memory 830 to perform the rocket engine starting method described above.
Further, the logic instructions in the memory 830 described above may be implemented in the form of software functional units and may be stored in a computer-readable storage medium when sold or used as a stand-alone product. Based on this understanding, the technical solution of the present invention may be embodied essentially or in a part contributing to the prior art or in a part of the technical solution in the form of a software product stored in a storage medium, comprising several instructions for causing a computer device (which may be a personal computer, a server, a network device, etc.) to perform all or part of the steps of the method of the embodiments of the present invention. And the aforementioned storage medium includes: a U-disk, a removable hard disk, a Read-Only Memory (ROM), a random access Memory (RAM, random Access Memory), a magnetic disk, or an optical disk, or other various media capable of storing program codes.
In another aspect, the present invention also provides a computer program product, the computer program product comprising a computer program, the computer program being storable on a non-transitory computer readable storage medium, the computer program, when executed by a processor, being capable of performing the method of starting a rocket engine as described above.
In yet another aspect, the present invention also provides a non-transitory computer readable storage medium having stored thereon a computer program which, when executed by a processor, is implemented to perform the method of starting a rocket engine as described above.
The apparatus embodiments described above are merely illustrative, wherein elements illustrated as separate elements may or may not be physically separate, and elements shown as elements may or may not be physical elements, may be located in one place, or may be distributed over a plurality of network elements. Some or all of the modules may be selected according to actual needs to achieve the purpose of the solution of this embodiment. Those of ordinary skill in the art will understand and implement the present invention without undue burden.
From the above description of the embodiments, it will be apparent to those skilled in the art that the embodiments may be implemented by software plus necessary general purpose hardware, or may be implemented by hardware. Based on such understanding, the foregoing technical solutions may be embodied essentially or in part in the form of a software product, which may be stored in a computer-readable storage medium, such as a ROM/RAM, a magnetic disk, an optical disk, etc., including several instructions to cause a computer device (which may be a personal computer, a server, or a network device, etc.) to perform the various embodiments or methods of portions of the embodiments.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and are not limiting; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (5)
1. The starting method of the rocket engine is characterized in that the rocket is provided with a plurality of engines, and the engines are all connected in parallel;
the starting method comprises the following steps:
acquiring first parameter information of a rocket and second parameter information of an engine;
grouping all the engines according to the first parameter information of the rocket and the second parameter information of the engines;
determining starting sequences among different groups, starting each engine unit in sequence according to the starting sequences, and starting all engines in a single engine unit simultaneously;
the step of grouping all the engines according to the first parameter information of the rocket and the second parameter information of the engines specifically includes:
determining the total group number of all the engines after grouping and the number of single-group engines in each group according to the takeoff thrust-weight ratio and the total number of the engines, wherein the total group number is more than or equal to 2, and the number of the single-group engines is more than or equal to 2;
determining a first distribution condition of each engine in each group in the rocket and a second distribution condition of each group of engine units in the rocket according to the total group number, the single group number and the total position distribution condition of the engines in the rocket, wherein each engine in each group is symmetrical relative to a central axis of the rocket or symmetrical relative to a symmetry plane of the rocket;
furthermore, the step of determining the start-up sequence between the different groups specifically comprises:
obtaining a single thrust-weight ratio between the thrust of a single engine and the total weight of the rocket;
calculating to obtain the total thrust-weight ratio in each engine unit according to the single thrust-weight ratio and the number of single engines in each engine unit;
determining a starting sequence among all engine units according to the total thrust weight ratio in the groups, the total group number of all the engines after grouping and the takeoff thrust weight ratio of the rocket;
wherein the sum of the total weight ratios in the group of all the engine blocks that have been started before the last engine block is started is less than 1.
2. A method of starting a rocket engine as recited in claim 1, wherein said step of sequentially starting each engine block in said starting sequence comprises:
and determining the starting interval duration between two adjacent engine units, and sequentially starting each engine unit according to the starting sequence and every other starting interval duration.
3. A method of starting a rocket engine as recited in claim 2, wherein said step of sequentially starting each engine block in said starting sequence and at intervals of said starting interval comprises:
and during each starting interval period, detecting faults of the various engines in the engine unit which is started before, and stopping the starting of the rocket when at least one engine is detected to be faulty.
4. A method of starting a rocket engine as recited in claim 2, wherein the starting interval duration ranges from 0.1s to 2s.
5. A rocket, characterized in that it is provided with a plurality of engines, a plurality of which are connected in parallel with each other, based on the starting method of the rocket engine according to any one of the preceding claims 1 to 4, to achieve the take-off of the rocket.
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