CN117028076A - Rocket engine starting method and rocket - Google Patents

Abstract

The invention provides a rocket engine starting method and a rocket. The rocket is provided with multiple engines, and the multiple engines are all connected in parallel with each other; the starting method includes: obtaining the first parameter information of the rocket and the second parameter information of the engine; and based on the first parameter information of the rocket and the second parameter information of the engine. Second parameter information, group all the engines; determine the starting sequence between different groups, and start each engine group in sequence according to the starting sequence, and all engines in a single engine group are started at the same time. The invention provides a rocket engine starting method and a rocket, which can reduce the power supply requirements for starting the engine on the rocket, provide an opportunity for the rocket control system to judge the engine status, handle problems that arise accordingly, and improve the reliability of rocket launches. .

Description

Rocket engine starting method and rocket

Technical field

The invention relates to the field of rocket technology, and in particular to a rocket engine starting method and a rocket.

Background technique

In related technologies, the engines currently used in the first stage of domestic rockets are generally two-engine parallel, three-engine parallel, or four-engine parallel structures, and they are all started at the same time. However, when two to four existing rocket engines connected in parallel are started at the same time, a large starting current is required, and the power supply capacity of the rocket's arrow is required to be high. In addition, when an engine fails, the rocket cannot take off and the launch needs to be terminated urgently. That is to say, for the method of starting multiple machines in parallel at the same time, on the one hand, this method requires high power supply capacity on the rocket, and on the other hand, due to the increase in the number of engines, the probability of successful starting of all engines at one time is reduced.

Therefore, the conventional method of connecting 2 to 4 engines in parallel and starting them at the same time has a tolerance of 0 for engine failure. In order to solve the above problems, some rockets use four engines to start at the same time, but let the engines work in a low thrust state, so that the thrust is less than the gravity of the rocket. When it is determined that the four engines are working normally, the thrust is adjusted to the maximum thrust state to complete the rocket takeoff. This low-thrust-high-thrust simultaneous start method is suitable for parallel combinations of four engines or less. For parallel combinations of five or more engines, there is still a greater risk of engine startup failure affecting subsequent flight procedures.

Contents of the invention

The invention provides a rocket engine starting method and a rocket to solve the defects existing in the prior art and achieve the following technical effects: it can reduce the power supply requirements for starting the engine on the rocket and provide an opportunity for the rocket control system to determine the engine status. , problems that arise can be dealt with accordingly and the reliability of rocket launches can be improved.

According to the starting method of a rocket engine according to the first embodiment of the present invention, the rocket is provided with multiple engines, and the multiple engines are all connected in parallel with each other;

The startup method includes:

Obtain the first parameter information of the rocket and the second parameter information of the engine;

Group all the engines according to the first parameter information of the rocket and the second parameter information of the engine;

Determine the starting sequence between different groups, and start each engine group in sequence according to the starting sequence, and all engines in a single engine group are started at the same time.

According to an embodiment of the present invention, the first parameter information includes the take-off thrust-to-weight ratio of the rocket, and the second parameter information includes the total number of the engines and the total position distribution of the engines within the rocket.

According to an 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 engine specifically includes:

According to the take-off thrust-to-weight ratio and the total number of engines, determine the total number of groups of all engines after grouping and the number of single engines in each group;

According to the total number of groups, the number of engines in a single group and the total position distribution of the engines in the rocket, determine the first distribution of the engines in each group in the rocket, and the distribution of each engine group in the rocket. ’s second distribution.

According to an embodiment of the present invention, the total number of groups is greater than or equal to 2, the number of engines in a single group is greater than or equal to 2, and each engine in each group is symmetrical with respect to the central axis of the rocket or with respect to the symmetry plane of the rocket. symmetry.

According to an embodiment of the present invention, the step of determining the startup sequence between different groups specifically includes:

Obtain the single thrust-to-weight ratio between the thrust of a single engine and the total weight of the rocket;

According to the single thrust-to-weight ratio and the number of single engines in each engine group, the total thrust-to-weight ratio of each engine group is calculated;

The starting sequence between the various engine groups is determined based on the total thrust-to-weight ratio within the group, the total number of groups, and the take-off thrust-to-weight ratio of the rocket.

According to an embodiment of the present invention, before the last engine group is started, the sum of the total thrust-to-weight ratios of all the engine groups that have been started is less than 1.

According to an embodiment of the present invention, the step of starting each engine group in sequence according to the starting sequence specifically includes:

The starting interval length between two adjacent engine groups is determined, and each engine group is started in sequence according to the starting sequence and every said starting interval length.

According to an embodiment of the present invention, the step of starting each engine group in sequence according to the starting sequence and every said starting interval length specifically includes:

Within each start interval, fault detection is performed on each engine in the previously started engine group, and the start of the rocket is suspended when at least one engine failure is detected.

According to an embodiment of the present invention, the startup interval ranges from 0.1s to 2s.

According to the rocket according to the second embodiment of the present invention, the rocket is provided with a plurality of engines, and the plurality of engines are connected in parallel with each other. The rocket is based on the starting method of the rocket engine described in the first embodiment of the present invention. Achieve take-off of the rocket.

The present invention provides a method for starting a rocket engine. This method is not only applicable to rocket structures with a number of engines from 2 to 4, but also can be applied to rocket structures with a number of engines of 5 or more. Specifically, the invention is based on rocket and The engine parameter information groups all engines in a single rocket and determines the starting sequence between different groups of engines. Then it controls the starting of each engine group in sequence according to the starting sequence, thereby completing the engine starting process of the entire rocket and helping the rocket take off smoothly.

In summary, according to the rocket engine control method of the embodiment of the present invention, by grouping multiple engines in parallel, one group of engines starts at the same time, and the starting times of different groups are staggered with each other. On the one hand, the power supply on the rocket to the starting engine can be reduced. On the other hand, the thrust provided by a group of engines started at a single time is a small proportion of the total thrust, which is not enough to make the rocket take off. This provides the rocket control system with an opportunity to judge the engine status and deal with the problems that arise accordingly.

Description of the drawings

In order to explain the present invention or the technical solutions in the prior art more clearly, the drawings needed to be used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings in the following description are of the present invention. For some embodiments of the invention, those of ordinary skill in the art can also obtain other drawings based on these drawings without exerting creative efforts.

Figure 1 is one of the flow diagrams of the starting method of the rocket engine provided by the present invention;

Figure 2 is the second schematic flow chart of the rocket engine starting method provided by the present invention;

Figure 3 is a schematic structural diagram of the rocket engine distribution provided by the present invention;

Figure 4 is a schematic diagram of the starting sequence provided by the present invention after starting one group of engines and starting another group of engines with an interval between starting intervals;

Figure 5 is a schematic structural diagram of a rocket engine startup control device provided by the present invention;

Figure 6 is a schematic structural diagram of the electronic device provided by the present invention.

Detailed ways

In order to make the purpose, technical solutions and advantages of the present invention more clear, the technical solutions in the present invention will be clearly and completely described below in conjunction with the accompanying drawings of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention. , not all examples. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without making creative efforts fall within the scope of protection of the present invention.

In the description of this specification, reference to the terms "one embodiment," "some embodiments," "an example," "specific examples," or "some examples" or the like means that specific features are described in connection with the embodiment or example. , structures, materials or features are included in at least one embodiment or example of embodiments of the present invention. In this specification, the schematic expressions of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the specific features, structures, materials or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, those skilled in the art may combine and combine different embodiments or examples and features of different embodiments or examples described in this specification unless they are inconsistent with each other.

The starting method, control device and rocket of the rocket engine proposed by the present invention will be described below with reference to the accompanying drawings. Before describing the embodiments of the present invention in detail, the entire application scenario will be described first. The rocket engine starting method, control device, electronic equipment and computer-readable storage medium of the embodiment of the present invention can be applied not only locally to the rocket, but also to cloud platforms in the Internet field, or other types of Internet fields. Cloud level one, or can also be applied to third-party devices. Among them, third-party devices may include many different types such as mobile phones, tablets, laptops, vehicle-mounted computers, and other smart terminals.

The following description only takes the starting method suitable for a rocket engine as an example. It should be understood that the control method of the embodiment of the present invention can also be applied to cloud computing and third-party equipment.

First of all, it should be pointed out that the starting method of the present invention is suitable for multi-engine rockets, that is, the rocket is equipped with multiple engines, and the multiple engines are connected in parallel with each other.

As shown in Figure 1, the starting method of a rocket engine according to the first embodiment of the present invention includes:

Step S1, obtain the first parameter information of the rocket and the second parameter information of the engine;

Step S2, group all engines according to the first parameter information of the rocket and the second parameter information of the engine;

Step S3: Determine the starting order between different groups, and start each engine group in sequence according to the starting order, and all engines in a single engine group are started at the same time.

According to the rocket engine starting method according to the embodiment of the present invention, the specific starting process is as follows: first, it is necessary to obtain the first parameter information of the rocket and the second parameter information of the engine. The first parameter information mainly includes parameter information such as the weight of the rocket, And the second parameter information mainly includes parameter information such as the total thrust of all engines, the number of all engines, the thrust of a single engine, and the distribution position of the engine relative to the rocket. In this way, after obtaining the above first parameter information and second parameter information Finally, it is convenient to analyze the impact of the number and position of different engines on the rocket take-off process after being combined together, so that all engines can be reasonably grouped based on the first parameter information and the second parameter information, that is, all engines can be divided into at least two engine unit.

After completing the grouping of engines, this method further determines the starting sequence between engines in different groups, and starts each engine group in sequence according to the starting sequence. It should be noted that the above starting sequence refers to the starting sequence between engines in different groups. , that is, engines in different groups are started sequentially according to the starting sequence, and all engines in the same group are started at the same time when the engines in this group are started.

In order to solve the technical problems existing in the above related technologies, the present invention provides a rocket engine starting method. This method can not only be applied to rocket structures with the number of engines from 2 to 4, but also can be applied to rocket structures with the number of engines 5 and above. Rocket structure, specifically, the present invention groups all the engines in a single rocket according to the parameter information of the rocket and the engine, determines the starting sequence between different groups of engines, and then controls the starting of each engine group in sequence according to the starting sequence, thereby completing the entire The rocket's engine starting process helps the rocket take off smoothly.

Regarding the starting method proposed by the present invention, on the one hand, this method controls the group starting of the engines, so that the power supply current required for a single start of each group of engines is reduced, thereby reducing the power supply requirements of the rocket when starting the engine, thereby reducing This explains the difficulty of designing the power supply system on the arrow.

For example, the total number of engines in the rocket is 7 and each engine is connected in parallel. Assuming that a single engine requires 10A current when starting, then starting 7 engines at the same time requires 70A current. According to the preferred 4-3 group time-sharing starting method, that is, The seven engines are divided into two groups. One group has four engines and starts first, and the other group has three engines and starts later. The maximum starting current is 40A, and the required current reduction rate is 42.8%.

For another example, the total number of engines in the rocket is 9 and each engine is connected in parallel. Assuming that a single engine requires 10A current when starting, then 9 engines need 90A current to start at the same time. According to the preferred 3-3-3 group time-sharing starting method , that is, the 9 engines are divided into three groups, each group has three engines, and the three groups of engines are started in sequence according to the starting sequence, then the maximum current required for the engine to start drops from 90A to 30A, and the required current decrease rate is 66.7%.

For the starting method proposed by the present invention, on the other hand, since the thrust provided by a group of engines started at a single time is a small proportion of the total thrust, it is not enough to make the rocket take off, thus providing a basis for the rocket control system to determine the engine status. If you have the opportunity, you can handle the problems that arise accordingly. For example, after each group of engines is started, the rocket control system is used to detect faults on all engines in the group. When an engine failure is detected, the rocket engine starting process can be interrupted in time and corresponding measures can be taken, thus greatly improving the efficiency of the rocket. launch reliability.

In summary, according to the rocket engine control method of the embodiment of the present invention, by grouping multiple engines in parallel, one group of engines starts at the same time, and the starting times of different groups are staggered with each other. On the one hand, the power supply on the rocket to the starting engine can be reduced. On the other hand, the thrust provided by a group of engines started at a single time is a small proportion of the total thrust, which is not enough to make the rocket take off. This provides the rocket control system with an opportunity to judge the engine status and deal with the problems that arise accordingly.

According to some specific embodiments of the present invention, the first parameter information includes the take-off thrust-to-weight ratio of the rocket, and the second parameter information includes the total number of engines and the total location distribution of the engines within the rocket.

Among them, the rocket's take-off thrust-to-weight ratio refers to the ratio of the total engine thrust and the rocket's take-off weight when the rocket takes off. The take-off thrust-to-weight ratio is greater than 1, and the take-off thrust-to-weight ratio of liquid rockets is generally between 1.2 and 2. In this method, in order to obtain the take-off thrust-to-weight ratio of the rocket, the take-off weight of the rocket and the total thrust of all engines are first obtained, thereby calculating the take-off thrust-to-weight ratio of the rocket. The total thrust of the engine needs to be calculated based on the total number of engines and the individual engine. The single body thrust is calculated.

As shown in Figure 2, according to some embodiments of the present invention, the step of grouping all engines according to the first parameter information of the rocket and the second parameter information of the engine specifically includes:

Based on the takeoff thrust-to-weight ratio and the total number of engines, determine the total number of groups of all engines and the number of single engines in each group.

It can be understood that the take-off thrust-to-weight ratio and the total number of engines determine the total number of sets and the number of generators in a single set. For example, the total number of engines in a rocket is 9 and the engines are connected in parallel. If the take-off thrust-to-weight ratio of the rocket is less than 1.33, the 9 engines can be divided into 2 groups, of which 6 engines are the first group and 3 engines are the second group. At this time, the first group is started first and then the second group. group; alternatively, the 9 engines can also be divided into 3 groups, where every 3 engines are one group. At this time, the first group, the second group, and the third group are started in sequence. If the rocket's take-off thrust-to-weight ratio is greater than 1.33, based on the above grouping principle, the 9 engines can be divided into two groups, of which the first group has 5 engines and the second group has 4 engines to ensure that the second group can , the thrust of the first set of engines that has been started is not enough to make the rocket take off.

As shown in Figure 2, further, according to some embodiments of the present invention, the step of grouping all engines according to the first parameter information of the rocket and the second parameter information of the engine also includes:

Based on the total number of groups, the number of engines in a single group, and the total position distribution of the engines in the rocket, determine the first distribution of each engine in each group within the rocket, and the second distribution of each engine group in the rocket.

In summary, in this method, the engine grouping process is mainly divided into two steps. The first step is the division of the total number of engine groups and the number of single groups of engines in each group. The second step is the division of the number of single groups of engines in each group. It can be understood that the first step can ensure the rationality of the number of groups, and the second step can ensure the grouping positions. rationality.

Furthermore, the grouping process of the above-mentioned engines needs to meet the following principles: the total number of groups is greater than or equal to 2, the number of engines in a single group is greater than or equal to 2, and each engine in each group is symmetrical with respect to the central axis of the rocket or with respect to the symmetrical face of the rocket. say.

In this way, when a single group of engines is started, since each engine in each group is symmetrical with respect to the central axis of the rocket or with respect to the symmetry plane of the rocket, the thrust exerted by the engine on the rocket can always be maintained in the vertical direction to avoid The imbalance of the rocket caused by the uneven thrust exerted by the engine on various positions of the rocket prevents the rocket from tilting or even toppling during take-off and ensures a smooth take-off of the rocket.

For example, the total number of engines in the rocket is 7 and each engine is connected in parallel. The engines are started in time-sharing groups of 4-3. The first group has a total of 4 engines, and the second group has a total of 3 engines. The parallel arrangement and numbering of the 7 engines are shown in Figure 3, where engines 3, 4, 6 and 7 are grouped together, and engines 1, 2, 5 engines are the second group. When starting in groups, the four engines 3, 4, 6, and 7 of the first group start at the same time, and the three engines 1, 2, and 5 of the second group start at the same time.

It can be seen that the No. 3, 4, 6, and 7 engines of the first group are symmetrical along the central axis of the rocket. Therefore, when the first group of engines is started, the thrust exerted by the engines on the rocket is uniform and the various force positions of the rocket are symmetrical. , so the rocket can remain vertical without being unbalanced. Secondly, engines No. 1, 2, and 5 of the second group are also symmetrical along the central axis of the rocket, so when the second group of engines is started, the rocket can still remain vertical and unbalanced. Not unbalanced.

As shown in Figure 2, according to some embodiments of the present invention, the steps of determining the startup sequence between different groups specifically include:

Obtain the single thrust-to-weight ratio between the thrust of a single engine and the total weight of the rocket;

Based on the single thrust-to-weight ratio and the number of single engines in each engine group, the total thrust-to-weight ratio of each engine group is calculated;

The starting sequence between each engine group is determined based on the total thrust-to-weight ratio within the group, the total number of groups, and the take-off thrust-to-weight ratio of the rocket.

In this embodiment, the starting sequence between each engine group needs to be determined based on the total thrust-to-weight ratio within the group, the total number of groups, and the take-off thrust-to-weight ratio of the rocket. It should be pointed out that the principle for determining the starting sequence in this method is: Before the last set of engines was started, the total thrust of all previously started engine sets was insufficient to support the rocket's takeoff.

Specifically, the above-mentioned determination principle of the starting sequence is reflected in the thrust-to-weight ratio: before the last engine group is started, the sum of the total thrust-to-weight ratios of all the engine groups that have been started is less than 1.

In this way, the rocket can take off only after all sets of engines are started, leaving enough time for the status detection of the rocket engine.

For example, the total number of engines in the rocket is 7 and each engine is connected in parallel. The engines are started in time-sharing groups of 4-3. The first group has a total of 4 engines, and the second group has a total of 3 engines. The parallel arrangement and numbering of the 7 engines are shown in Figure 3, where engines 3, 4, 6 and 7 are grouped together, and engines 1, 2, 5 engines are the second group. When starting in groups, the four engines 3, 4, 6, and 7 of the first group start at the same time, and the three engines 1, 2, and 5 of the second group start at the same time.

The take-off thrust-to-weight ratio generated by the total thrust of the 7-machine parallel engine structure is 1.4. Then 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. At this time, the thrust is less than the gravity of the rocket, so After the first set of engines started, it was not enough to make the rocket take off. When the second set of engines is also started, the ratio of the total thrust of the engine to the weight of the rocket reaches a take-off thrust-to-weight ratio of 1.4, and finally the rocket enters the next stage of take-off.

As shown in Figure 2, according to some embodiments of the present invention, the steps of starting each engine group in sequence according to the starting sequence include:

Determine the starting interval between two adjacent engine groups, and start each engine group in sequence according to the starting sequence and every starting interval.

It can be understood that this embodiment adopts the form of time-sharing starting during the starting process of the rocket engine. The time-sharing starting means that after the first set of engines is started, the second set of engines is started at a certain interval, and then the third set of engines is started at a certain interval. engine, and so on.

In this way, in time-sharing starting, the remaining starting interval time is reserved for the control system to detect the engine status. If an engine starting failure is found, corresponding handling can be carried out, which improves the launch reliability of the rocket.

Specifically, the steps of starting each engine group in sequence according to the starting sequence and every starting interval length include:

During each start interval, faults are detected for each engine in the previously started engine group, and the start of the rocket is aborted when at least one engine failure is detected.

Among them, the fault detection method is as follows: continuously monitor the operating parameters and operating status of each engine through the sensor module or the data recorded in the system, so as to determine whether a single engine has a startup failure. Among them, the engine's propulsion chamber pressure, propellant Pressure, propulsion chamber temperature, turbine pump speed and other parameters are monitored to determine engine failure.

According to some embodiments of the present invention, the startup interval ranges from 0.1s to 2s. In this way, it not only gives the engine enough starting time to ensure that the engine is fully opened, but also prevents the engine from being burned due to too long opening intervals, resulting in a waste of fuel, thus saving costs and improving safety and reliability.

For example, the total number of engines of the rocket is 7 and each engine is connected in parallel. According to the above 4-3 grouping, after the 4 engines of the first group are started, and the rocket control system determines that the engines of the first group are starting normally, the engines of the second group will be started. 3 engines. The preferred starting interval is between 0.1s and 2s, as shown in Figure 4. Assume that the time to start the first set of engines is t1, and the time to start the second set of engines is t2, then the time between t2 and t1 The phase difference interval Δt is the duration of the above-mentioned starting interval, that is, Δt is preferably between 0.1s and 2s.

The rocket engine starting control device provided by the present invention is described below. The rocket engine starting control device described below and the rocket engine starting method described above may be mutually referenced.

As shown in Figure 5, a rocket engine startup control device according to an embodiment of the present invention includes:

The acquisition module 110 is used to acquire the first parameter information of the rocket and the second parameter information of the engine;

The first execution module 120 is used to group all engines according to the first parameter information of the rocket and the second parameter information of the engine;

The second execution module 130 is used to determine the starting sequence between different groups, and start each engine group in sequence according to the starting order, and all engines in a single engine group are started at the same time.

According to the rocket according to the second embodiment of the present invention, the rocket is provided with multiple engines, and the plurality of engines are connected in parallel with each other. The rocket is based on the starting method of the rocket engine described in the first embodiment of the present invention to achieve the take-off of the rocket.

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 according to the embodiment of the present invention, the starting process of the engine is implemented using a grouped time-sharing method. Grouped starting refers to grouping multiple engines, and the engines in each group act at the same time, such as executing a starting procedure. The general principle of grouping is to ensure that the maximum thrust generated by all engines that have been started before the last group is less than the thrust required for rocket takeoff. The engines in each group are symmetrical relative to the rocket axis or symmetrical relative to the rocket's symmetrical plane. , according to the number of engines, it can generally be divided into 2 groups, 3 groups, or more groups. Time-sharing starting means that after the first group of engines is started, the second group of engines is started at a certain interval, and then the third group of engines is started at a certain interval, and so on.

In this way, the present invention groups multiple engines connected in parallel so that one group of engines starts at the same time and the starting times of different groups are staggered. On the one hand, the power supply requirements for starting the engines on the arrow are reduced. On the other hand, a group of engines that can be started in a single time can The thrust provided is a small proportion of the total thrust and is not enough to make the rocket take off. It provides the rocket control system with an opportunity to judge the engine status and deal with the problems accordingly.

Figure 6 illustrates a schematic diagram of the physical structure of an electronic device. As shown in Figure 6, the electronic device may include: a processor (processor) 810, a communications interface (Communications Interface) 820, a memory (memory) 830 and a communication bus 840. Among them, the processor 810, the communication interface 820, and the memory 830 complete communication with each other through the communication bus 840. The processor 810 can call logical instructions in the memory 830 to execute the above rocket engine starting method.

In addition, the above-mentioned logical instructions in the memory 830 can be implemented in the form of software functional units and can be stored in a computer-readable storage medium when sold or used as an independent product. Based on this understanding, the technical solution of the present invention essentially or the part that contributes to the existing technology or the part of the technical solution can be embodied in the form of a software product. The computer software product is stored in a storage medium, including Several instructions are used to cause a computer device (which may be a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the methods of various embodiments of the present invention. The aforementioned storage media include: U disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), magnetic disk or optical disk and other media that can store program code. .

On the other hand, the present invention also provides a computer program product. The computer program product includes a computer program. The computer program can be stored on a non-transitory computer-readable storage medium. When the computer program is executed by the processor, the computer can execute the above-mentioned rocket engine. startup method.

In another aspect, the present invention also provides a non-transitory computer-readable storage medium on which a computer program is stored. The computer program is implemented when executed by a processor to perform the above-mentioned starting method of the rocket engine.

The device embodiments described above are only illustrative. The units described as separate components may or may not be physically separated. The components shown as units may or may not be physical units, that is, they may be located in one place. , or it can be distributed to multiple network units. Some or all of the modules can be selected according to actual needs to achieve the purpose of the solution of this embodiment. Persons of ordinary skill in the art can understand and implement the method without any creative effort.

Through the above description of the embodiments, those skilled in the art can clearly understand that each embodiment can be implemented by software plus necessary general-purpose hardware. Of course, it can also be implemented by hardware. Based on this understanding, the part of the above technical solution that essentially contributes to the existing technology can be embodied in the form of a software product. The computer software product can be stored in a computer-readable storage medium, such as ROM/RAM, magnetic disc, optical disk, etc., including a number of instructions to cause a computer device (which may be a personal computer, a server, or a network device, etc.) to execute various embodiments or methods of certain parts of the embodiments.

Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that it can still be used Modifications are made to the technical solutions described in the foregoing embodiments, or equivalent substitutions are made to some of the technical features; however, these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims (10)

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;

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.

2. A method of starting a rocket engine as recited in claim 1, wherein the first parameter information comprises a ratio of take-off weights of the rocket and the second parameter information comprises a total number of engines and a total position distribution of the engines within the rocket.

3. A method of starting a rocket engine according to claim 2, wherein said step of grouping all of said engines according to first parameter information of the rocket and second parameter information of the engines comprises:

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.

4. A method of starting a rocket engine according to claim 3, wherein the total number of groups is 2 or more, the number of individual groups of engines is 2 or more, and each engine within each group is symmetrical about the central axis of the rocket or about the plane of symmetry of the rocket.

5. A method of starting a rocket engine according to claim 2, wherein the step of determining the starting sequence between the different groups 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;

and determining the starting sequence among the 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.

6. A method of starting a rocket engine as recited in claim 5, wherein the sum of the total in-group thrust weight ratios of all of the engine blocks that have been started before the last engine block is started is less than 1.

7. A method of starting a rocket engine according to any one of claims 1 to 6, wherein the step of sequentially starting each engine block in the 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.

8. A method of starting a rocket engine as recited in claim 7, 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.

9. A method of starting a rocket engine as recited in claim 7, wherein the starting interval duration ranges from 0.1s to 2s.

10. 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 a method of starting a rocket engine according to any one of the preceding claims 1 to 9, to achieve take-off of the rocket.