CN111142458A - Solid carrier rocket engine exhaustion judging method, device and equipment - Google Patents
Solid carrier rocket engine exhaustion judging method, device and equipment Download PDFInfo
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Abstract
The invention discloses a method, a device and equipment for judging the exhaustion of a solid carrier rocket engine, wherein the method for judging the exhaustion of the solid carrier rocket engine comprises the following steps: acquiring an axial overload average value of the solid carrier rocket in a current calculation period; and when the average value of the axial overload is smaller than a preset threshold value, judging that the engine is exhausted. The solid carrier rocket engine exhaustion judging method solves the problem that the interstage separation of subsequent rockets is influenced due to poor consistency of the working time of the engine when the solid carrier rocket engine is judged to be exhausted by adopting fixed time, and improves the accuracy and reliability of judging the exhaustion of the solid carrier rocket engine.
Description
Technical Field
The invention relates to the technical field of carrier rocket guidance control, in particular to a method, a device and equipment for judging the exhaustion of a solid carrier rocket engine.
Background
With the rapid development of aerospace technologies, space vehicles such as carrier rockets need to complete complex tasks such as maneuvering launching, satellite orbital transfer design, space station docking and interplanetary navigation track design. Therefore, the power propulsion system and the guidance control system are very important. The solid rocket is a rocket using a solid rocket engine as a power device. The solid engine has the outstanding advantages of large thrust, convenient maintenance and inspection and the like, so that the solid engine is widely adopted by a power propulsion system. The solid rocket engine adopts solid substances (energy and working medium) as a propellant, and the solid propellant is ignited and then combusted in a combustion chamber to generate high-temperature and high-pressure fuel gas, namely chemical energy is converted into heat energy; the gas expands and accelerates through the jet pipe, the heat energy is converted into kinetic energy, and the kinetic energy is discharged from the jet pipe at a very high speed, so that thrust is generated to push the rocket to fly. However, after the guidance control system requires to implement shutdown and flameout actions, the solid engine still has the aftereffect impulse with a small magnitude but is stubborn.
Since the solid carrier rocket engine cannot be actively shut down after ignition, generally, after the solid carrier rocket engine is ignited, the interstage separation is performed after the engine is naturally exhausted, and therefore the judgment on the engine exhaustion is related to whether the subsequent interstage separation time sequence can be smoothly executed. At present, a fixed time method is adopted for judging the exhaustion of most solid carrier rockets, namely, the exhaustion of the engine is judged after a fixed time from the ignition of the engine, and the fixed time adopts a statistical value of the working time in the engine test or the preorder transmission, so that the working time of the solid carrier rocket engine is lack of consistency, and the process of interstage separation of subsequent rockets is influenced.
Disclosure of Invention
In view of the above, the invention provides a method, a device and equipment for judging the exhaustion of a solid carrier rocket engine, and aims to solve the problems that in the prior art, the solid rocket engine cannot be actively shut down after ignition, the working time consistency is poor, and the subsequent rocket stage separation process is influenced.
According to a first aspect, an embodiment of the present invention provides a solid launch vehicle engine exhaustion discriminating method, including: acquiring an axial overload average value of the solid carrier rocket in a current calculation period; and when the average axial overload value is smaller than a preset threshold value, judging that the engine is exhausted.
With reference to the first aspect, in a first embodiment of the first aspect, the step of obtaining an average value of axial overload of the solid launch vehicle includes: respectively obtaining axial overload average values in the previous n calculation periods, wherein the value range of n is 4-6; and determining the axial overload average value in the current calculation period according to the axial overload average value in the previous n calculation periods.
With reference to the first aspect, in a second implementation manner of the first aspect, a value of the preset threshold ranges from 3% to 6% of the maximum axial overload value.
With reference to the second implementation manner of the first aspect, in a third implementation manner of the first aspect, the method for determining the axial maximum overload value includes: comparing the axial overload average value in the current calculation period with the current axial maximum overload value; and when the axial overload average value in the current calculation period is larger than the current axial maximum overload value, updating the current axial maximum overload value to be the axial overload average value in the current calculation period.
With reference to the first aspect, in a fourth embodiment of the first aspect, the determining that the engine is running out when the average value of the axial overload is less than a preset threshold value includes: when the axial overload average value is smaller than a preset threshold value, judging whether the axial overload average values in the previous N calculation periods are all smaller than the preset threshold value, wherein the value range of N is 2-4; and if the axial overload average values in the first N calculation periods are smaller than a preset threshold value, judging that the engine is exhausted.
With reference to the first aspect, in a fifth implementation of the first aspect, the method further comprises: in each calculation period, comparing the axial overload average value in the current calculation period with the preset threshold value; if the axial overload average value in the current calculation period is smaller than the preset threshold value, accumulating the counting times once; and if the axial overload average value in the current calculation period is not less than the preset threshold value, resetting the counting times.
With reference to the fourth implementation manner of the first aspect, in a sixth implementation manner of the first aspect, the method further includes: and judging whether the axial overload average values in the previous N calculation periods are all smaller than a preset threshold value, and determining according to the counted times.
According to a second aspect, an embodiment of the present invention provides a solid launch vehicle engine exhaustion discriminating device, including: the acquisition module is used for acquiring the axial overload average value of the solid carrier rocket in the current calculation period; and the judging module is used for judging that the engine is exhausted when the axial overload average value is smaller than a preset threshold value.
According to a third aspect, an embodiment of the present invention provides a solid launch vehicle engine exhaustion discriminating device, including: a memory and a processor, the memory and the processor being communicatively connected to each other, the memory having stored therein computer instructions, and the processor executing the computer instructions to perform the method for determining the exhaustion of a solid launch vehicle engine according to the first aspect or any of the embodiments of the first aspect.
According to a fourth aspect, an embodiment of the present invention provides a readable storage medium, wherein the computer readable storage medium stores computer instructions for causing the computer to execute a method for implementing the solid launch vehicle engine exhaustion discriminating method according to the first aspect or any of the embodiments of the first aspect.
The technical scheme of the invention has the following advantages:
according to the solid carrier rocket engine exhaustion judging method, the solid carrier rocket engine exhaustion judging device and the solid carrier rocket engine exhaustion judging equipment, the axial overload average value of the solid carrier rocket is obtained in the current calculation period, and when the axial overload average value is smaller than the preset threshold value, the engine exhaustion is judged. The exhaustion of the engine is judged by using the parameter of the axial overload average value, so that the defects that the solid rocket engine cannot be actively shut down after ignition, the consistency of the working time is poor, and the subsequent rocket interstage separation process is influenced are overcome, and the accuracy and the reliability of judging the exhaustion of the solid carrier rocket engine are improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a flow chart of a method for identifying exhaustion of a solid launch vehicle engine according to an embodiment of the present invention;
FIG. 2 is a flow chart of a method for determining exhaustion of a solid launch vehicle engine according to an embodiment of the present invention;
FIG. 3 is a flow chart of a method for determining exhaustion of a solid launch vehicle engine according to an embodiment of the present invention;
FIG. 4 is a flow chart of a method for determining exhaustion of a solid launch vehicle engine according to an embodiment of the present invention;
FIG. 5 is a block diagram of a solid launch vehicle engine exhaustion discriminating device provided in an embodiment of the present invention;
FIG. 6 is a block diagram of a solid launch vehicle engine exhaustion discriminating device provided in an embodiment of the present invention;
FIG. 7 is a block diagram of a solid launch vehicle engine exhaustion discriminating device provided in an embodiment of the present invention;
fig. 8 is a schematic structural diagram of a solid launch vehicle engine exhaustion discriminating device provided in the embodiment of the present invention.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In addition, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
Example 1
The embodiment provides a method for judging the exhaustion of a solid carrier rocket engine, which can be used for judging whether the solid carrier rocket engine is exhausted. In the embodiment of the present application, a solid launch vehicle engine is taken as an example for explanation, and as shown in fig. 1, the method for determining engine exhaustion includes:
s11: and acquiring the axial overload average value of the solid carrier rocket in the current calculation period.
The calculation period may be 5 milliseconds or 10 milliseconds, and the calculation period is not limited in the embodiment of the present application and can be determined by a person skilled in the art according to actual use needs. The axial overload value is the ratio of the axial acceleration of the rocket to the sea level gravity acceleration, and the sea level gravity acceleration at the same latitude is a certain value, so that the axial overload value can correspond to the axial acceleration. The axial overload average value is obtained by calculation according to the average value of the axial overload values in one or more previous calculation periods, and the axial overload average value of the solid launch vehicle in the current calculation period is determined according to the axial overload values in one or more previous calculation periods.
S12: and when the average axial overload value is smaller than a preset threshold value, judging that the engine is exhausted. The preset threshold value can be reasonably set as required. For example, since the axial overload value is a ratio of the axial acceleration of the rocket to the sea level gravitational acceleration, and the sea level gravitational acceleration at the same latitude is a certain value, the axial overload value may correspond to the axial acceleration, and when the average value of the axial overload is smaller than a preset threshold value, it may be considered that the axial acceleration of the solid launch vehicle is approaching zero, that is, the axial thrust is approaching zero, and thus it is determined that the engine is exhausted. For example, a preset threshold value is set as B, the determined axial overload average value is a, if a < B, the exhaustion condition of the solid carrier rocket engine can be determined, if a > B, it can be determined that the solid carrier rocket engine is not exhausted, and the value a and the value B can be continuously compared in the next calculation period until a < B.
According to the solid carrier rocket engine exhaustion judging method provided by the invention, the axial overload average value of the solid carrier rocket is obtained in the current calculation period, and when the axial overload average value is smaller than the preset threshold value, the engine exhaustion is judged. Because the axial overload value corresponds to the axial acceleration, whether the thrust still exists in the axial direction of the solid carrier rocket can be judged by comparing the relation between the axial overload average value and the preset threshold value, namely whether the acceleration still exists in the axial direction, and the acceleration is provided by the engine, namely the axial overload value is consistent with the working time of the engine. The engine exhaustion is judged by using the parameter of the axial overload average value, so that the problems that the solid rocket engine is judged to be exhausted by setting fixed time, the interstage separation cannot be carried out due to the fact that the engine is not exhausted when the fixed time is reached, and the consistency of the working time is poor are solved, and the accuracy of the solid carrier rocket engine exhaustion judgment is improved.
As an alternative embodiment of the present application, as shown in fig. 2, step S11 includes:
s111: and respectively acquiring axial overload values in the previous n calculation periods, wherein the value range of n is 4-6.
Illustratively, before obtaining the average value of the axial overload in the current calculation period, the average value needs to be calculated according to the axial overload values in the previous n calculation periods, and the value n is selected according to an empirical value and is 5. When the value n is 5, the axial overload values in the first 5 calculation periods are respectively obtained, and the axial overload values can be obtained through measurement of the accelerometer.
S112: and determining the axial overload average value in the current calculation period according to the axial overload average value in the previous n calculation periods.
Illustratively, according to the axial overload values in the previous n calculation periods, the axial overload average value in the current calculation period is calculated. The calculation formula is as follows:
wherein the content of the first and second substances,
representing the average value of the axial overload in the current calculation period;
and (3) expressing the axial overload measured value of the k-i calculation period, wherein the value range of i is 0-n-1, n expresses the number of calculation periods before the current calculation period, the value range of n is 4-6, and k expresses the k current calculation period. Taking n as an example, if n is 5, the axial overload measurement value in the first 5 calculation periods of the current calculation period needs to be obtained, and if the current calculation period is the 7 th calculation period, the axial overload average value in the current calculation period is obtained
Comprises the following steps:
wherein the content of the first and second substances,
axial overload measurements were made during the first 5 calculation cycles, respectively. If the current calculation period is the 3 rd calculation period, the axial overload average value in the current calculation period
Comprises the following steps:
and calculating the axial overload average value in the current calculation period according to the obtained axial overload values of the previous n calculation periods, so that the consistency between the judgment and the working time of the engine can be ensured, and the reliability of the judgment of the exhaustion of the engine is improved.
As an optional implementation manner of the present application, the value range of the preset threshold in step S12 is 3% to 6% of the maximum axial overload value. And determining the axial maximum overload value according to the axial overload average value in the current calculation period, and determining the maximum value of the current axial average overload value as the axial maximum overload value. And judging whether the engine is exhausted or not by comparing the relation between the average axial overload value and a preset threshold value, wherein the preset threshold value is selected to be 3% -6% of the maximum axial overload value according to an empirical value, and preferably, the preset threshold value can be set to be 5% of the maximum axial overload value.
As an optional embodiment of the present application, the method for determining the axial maximum overload value includes:
first, the average value of the axial overload in the current calculation period is compared with the current maximum axial overload value.
Illustratively, the axial overload average value in the current calculation period is calculated and compared with the current axial maximum overload value, and the initial value of the axial maximum overload value is 0. And further determining the axial maximum overload value by comparing the axial overload average value and the axial maximum overload value in the current calculation period.
And secondly, when the axial overload average value in the current calculation period is larger than the current axial maximum overload value, updating the current axial maximum overload value to be the axial overload average value in the current calculation period.
For example, if the average value of the axial overload in the current calculation period is greater than the current maximum axial overload value, the current maximum axial overload value is updated. For example, the average value of the axial overload in the current calculation period is P, the current maximum axial overload value is an initial value 0, and the current maximum axial overload value is updated to P because P is greater than 0; and if the axial overload average value obtained by calculation in the next calculation period is Q and Q is greater than P, updating the axial maximum overload value to be Q in the next period. In this way, the axial maximum overload value is continuously updated in each calculation cycle, keeping it always at a maximum value.
As an alternative embodiment of the present application, as shown in fig. 3, step S12 includes:
s121: and when the axial overload average value is smaller than the preset threshold value, judging whether the axial overload average values in the previous N calculation periods are all smaller than the preset threshold value, wherein the value range of N is 2-4.
For an exemplary specific description of the preset threshold and the axial overload average value, reference is made to the description of the corresponding parts in the above embodiments, and the embodiments of the present application are not described herein again. And comparing the relation between the axial overload average value in the current calculation period and a preset threshold, and if the axial overload average value in the current calculation period is smaller than the preset threshold, further judging the relation between the axial overload average value in the previous N calculation periods and the preset threshold, namely judging whether the axial overload average values in the continuous N +1 calculation periods are all smaller than the preset threshold when the axial overload average value in the current calculation period is smaller than the preset threshold. For example, the preset threshold is 5% of the maximum axial overload value, the N value is 2, if the maximum axial overload value is M, the preset threshold is 5% M, and when the obtained average axial overload value in the current calculation period is P, the relationship between the P value and the 5% M value is compared. If P is less than 5% M, the relation between the axial overload average value in the first 2 calculation periods and the preset threshold value is judged, and if the axial overload average value in the first 2 calculation periods is smaller than the preset threshold value, the axial overload average value in the continuous 3 calculation periods is smaller than the preset threshold value.
S122: and if the axial overload average values in the first N calculation periods are smaller than the preset threshold value, judging that the engine is exhausted.
For a specific description of the comparison between the axial overload average value in the first N calculation cycles and the preset threshold, reference is made to the description of the corresponding part in the foregoing embodiment, and details of the embodiment of the present application are not repeated herein. If the average axial overload values in the first N calculation periods are all smaller than the preset threshold value, at the moment, the exhaustion of the engine can be judged. By comparing the relation between the axial overload average value in the first N calculation periods and the preset threshold value, if the axial overload average value in the first N calculation periods is smaller than the preset threshold value, the exhaustion of the engine is judged, and the accuracy of the judging method is further ensured.
As an alternative embodiment of the present application, as shown in fig. 4, before step S121, the method includes:
and S123, in each calculation period, comparing the axial overload average value in the current calculation period with a preset threshold value.
For a specific description of the comparison between the axial overload average value in the current calculation period and the preset threshold, reference is made to the description of the corresponding part in the foregoing embodiment, and details of the embodiment of the present application are not repeated herein.
And S124, if the axial overload average value in the current calculation period is smaller than a preset threshold value, accumulating the counting times once.
For a specific description of the comparison between the axial overload average value in the current calculation period and the preset threshold, reference is made to the description of the corresponding part in the foregoing embodiment, and details of the embodiment of the present application are not repeated herein. And obtaining a comparison result by comparing the axial overload average value in the current calculation period with a preset threshold value, and if the axial overload average value in the current calculation period is smaller than the preset threshold value, accumulating the counting times once. When the counted number of times is accumulated to N +1, it is judged that the engine is exhausted. The counting times are accumulated to N +1, namely the accumulation range of the counting times is 3-5. If the value of N is 2, the engine exhaustion can be judged when the counting times are accumulated to 3.
And S125, if the axial overload average value in the current calculation period is not less than the preset threshold value, resetting the counting times.
For example, for a specific description of the comparison between the axial overload average value in the current calculation period and the preset threshold value and the number of counting, reference is made to the description of the corresponding part in the foregoing embodiment, and the embodiments of the present application are not described herein again. And obtaining a comparison result by comparing the axial overload average value in the current calculation period with a preset threshold value, and if the axial overload average value in the current calculation period is smaller than the preset threshold value, accumulating the counting times once. When the counted number of times is accumulated to N +1, it is judged that the engine is exhausted. If the value of N is 2, the engine exhaustion can be judged when the counting times are accumulated to 3. And if the counter is added to 2, the axial overload average value in the current calculation period is not less than the preset threshold, resetting the counting times, and continuously repeating the step of comparing the axial overload average value in the current calculation period with the preset threshold until the axial overload average value is added to N +1 to judge that the engine is exhausted.
As an optional embodiment of the present application, determining whether the axial overload average values in the first N calculation cycles in step S122 are all smaller than a preset threshold includes: and determining according to the counting times.
For a specific description of the counting number, reference is made to the description of the corresponding part in the above embodiments, and the embodiments of the present application are not described herein again. And counting once when the axial overload average value in each calculation period is smaller than a preset threshold value, and when the counting times reach an accumulated value, namely the axial overload average value in the current calculation period is smaller than the preset threshold value, the axial overload average values in the first N calculation periods are all smaller than the preset threshold value.
By judging the relation between the axial overload average value in each calculation period and the preset threshold value and determining the exhaustion condition of the engine according to the counting times meeting the conditions, the consistency of the judging method and the working time of the engine is ensured, and the exhaustion condition of the engine is accurately judged so as to carry out subsequent interstage separation.
Example 2
The embodiment of the invention provides a solid carrier rocket engine exhaustion judging device, as shown in fig. 5, comprising:
and the obtaining module 21 is configured to obtain an average value of the axial overload of the solid launch vehicle in the current calculation period. For details, reference is made to the description related to step S11 in the above method embodiment, and details are not repeated here.
And a determination module 22 for determining that the engine is exhausted when the average axial overload value is less than a preset threshold. For details, reference is made to the description related to step S12 in the above method embodiment, and details are not repeated here.
The solid carrier rocket engine exhaustion judging device provided by the invention obtains the axial overload average value of the solid carrier rocket through the obtaining module in the current calculation period, judges the relation between the axial overload average value and the preset threshold value through the judging module, judges the engine exhaustion when the axial overload average value is smaller than the preset threshold value, and can judge whether the axial direction of the solid carrier rocket still has thrust or not, namely whether the axial direction still has acceleration or not through comparing the relation between the axial overload average value and the preset threshold value due to the fact that the axial overload value corresponds to the axial acceleration, wherein the acceleration is provided by the engine, namely the axial overload value is consistent with the working time of the engine. The engine exhaustion is judged by using the parameter of the axial overload average value, so that the problems that the solid rocket engine is judged to be exhausted by setting fixed time, the interstage separation cannot be carried out due to the fact that the engine is not exhausted when the fixed time is reached, and the consistency of the working time is poor are solved, and the accuracy of the solid carrier rocket engine exhaustion judgment is improved.
As an alternative embodiment of the present application, as shown in fig. 6, the obtaining module 21 includes:
and the obtaining submodule 211 is configured to obtain axial overload values in the previous n calculation cycles, where a value range of n is 4-6. For details, refer to the description related to step S111 described in the above method embodiment, and are not repeated herein.
And the determining submodule 212 is used for determining the axial overload average value in the current calculation period according to the axial overload average values in the previous n calculation periods. For details, refer to the description related to step S112 described in the above method embodiment, and are not repeated herein. The axial overload values of the previous n calculation periods are obtained according to the obtaining submodule, and then the axial overload average value in the current calculation period is calculated through the determining submodule, so that the consistency of the judgment and the working time of the engine can be ensured, and the reliability of the judgment of the exhaustion of the engine is improved.
As an alternative embodiment of the present application, as shown in fig. 7, the determining module 22 includes:
the judgment submodule 221 is configured to, when the axial overload average value is smaller than the preset threshold, judge whether all the axial overload average values in the previous N calculation cycles are smaller than the preset threshold, where a value range of N is 2 to 4. For details, refer to the description related to step S121 described in the above method embodiment, and are not repeated herein.
And a determination submodule 222, configured to determine that the engine is exhausted if the average value of the axial overloads in the previous N calculation cycles is smaller than a preset threshold value. For details, refer to the description related to step S122 in the above method embodiment, and are not repeated herein.
The judgment submodule compares the axial overload average values in the first N calculation periods with a preset threshold value, and judges that the engine is exhausted if the axial overload average values in the first N calculation periods are smaller than the preset threshold value, so that the accuracy of the judgment method is further ensured.
Example 3
The embodiment of the invention also provides a solid launch vehicle engine exhaustion judging device, as shown in fig. 8, the solid launch vehicle engine exhaustion judging device includes a processor 31 and a memory 32, where the processor 31 and the memory 32 may be connected by a bus or in other manners, and fig. 8 takes the connection by a bus as an example.
The processor 31 may be a Central Processing Unit (CPU). The Processor 31 may also be other general-purpose processors, Digital Signal Processors (DSPs), Graphics Processing Units (GPUs), embedded Neural Network Processors (NPUs), or other dedicated deep learning coprocessors, Application Specific Integrated Circuits (ASICs), Field Programmable Gate Arrays (FPGAs), or other Programmable logic devices, discrete Gate or transistor logic devices, discrete hardware components, or any combination thereof.
The memory 32, which is a non-transitory computer readable storage medium, may be used to store non-transitory software programs, non-transitory computer executable programs, and modules, such as program instructions/modules (e.g., the obtaining module 21, the determining module 22 shown in fig. 5) corresponding to the solid launch vehicle engine exhaustion method in the embodiments of the present invention. The processor 31 executes various functional applications and data processing of the processor by executing non-transitory software programs, instructions and modules stored in the memory 32, namely, implements the solid launch vehicle engine exhaustion determination method in the above method embodiment.
The memory 32 may include a storage program area and a storage data area, wherein the storage program area may store an operating system, an application program required for at least one function; the storage data area may store data created by the processor 31, and the like. Further, the storage 32 may include high speed random access memory, and may also include non-transitory memory, such as at least one magnetic disk storage device, flash memory device, or other non-transitory solid state storage device. In some embodiments, the memory 32 may optionally include memory located remotely from the processor 31, and these remote memories may be connected to the processor 31 via a network. Examples of such networks include, but are not limited to, the internet, intranets, local area networks, mobile communication networks, and combinations thereof.
The one or more modules are stored in the memory 32 and, when executed by the processor 31, perform a solid launch vehicle engine exhaustion discrimination method as in the embodiment shown in figures 1-4.
The axial overload average value of the solid carrier rocket is obtained in the current calculation period, and when the axial overload average value is smaller than a preset threshold value, the exhaustion of the engine is judged. The method obtains the axial overload average value in each calculation period, judges the engine exhaustion by using the parameter of the axial overload average value, solves the problems that the solid rocket engine cannot be actively shut down after ignition, the consistency of the working time is poor, and further the subsequent interstage separation process of the solid carrier rocket is influenced, and improves the accuracy and reliability of judging the solid carrier rocket engine exhaustion.
The specific details of the solid launch vehicle engine exhaustion discriminating device can be understood by referring to the corresponding related descriptions and effects in the embodiments shown in fig. 1 to fig. 7, and are not described herein again.
It will be understood by those skilled in the art that all or part of the processes of the methods of the embodiments described above can be implemented by a computer program, which can be stored in a computer-readable storage medium, and when executed, can include the processes of the embodiments of the methods described above. The storage medium may be a magnetic disk, an optical disk, a read-only memory (ROM), a Random Access Memory (RAM), or the like.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are within the scope of the invention.
Claims (10)
1. A solid carrier rocket engine exhaustion discriminating method is characterized by comprising the following steps:
acquiring an axial overload average value of the solid carrier rocket in a current calculation period;
and when the average axial overload value is smaller than a preset threshold value, judging that the engine is exhausted.
2. The method of claim 1, wherein the step of obtaining an average value of the axial overload of the solid launch vehicle comprises:
respectively obtaining axial overload values in the previous n calculation periods, wherein the value range of n is 4-6;
and determining the axial overload average value in the current calculation period according to the axial overload values in the previous n calculation periods.
3. The method of claim 1, wherein the predetermined threshold value is in a range of 3% to 6% of the maximum axial overload value.
4. The method of claim 3, wherein the method of determining the axial maximum overload value comprises:
comparing the axial overload average value in the current calculation period with the current axial maximum overload value;
and when the axial overload average value in the current calculation period is larger than the current axial maximum overload value, updating the current axial maximum overload value to be the axial overload average value in the current calculation period.
5. The method of claim 1, wherein determining that the engine is depleted when the average axial overload value is less than a preset threshold comprises:
when the axial overload average value is smaller than a preset threshold value, judging whether the axial overload average values in the previous N calculation periods are all smaller than the preset threshold value, wherein the value range of N is 2-4;
and if the axial overload average values in the first N calculation periods are smaller than a preset threshold value, judging that the engine is exhausted.
6. The method of claim 5, wherein when the average axial overload value is smaller than the preset threshold, determining whether the average axial overload values in the first N calculation cycles are all smaller than the preset threshold comprises:
in each calculation period, comparing the axial overload average value in the current calculation period with the preset threshold value;
if the axial overload average value in the current calculation period is smaller than the preset threshold value, accumulating the counting times once;
and if the axial overload average value in the current calculation period is not less than the preset threshold value, resetting the counting times.
7. The method of claim 5, wherein determining whether the average axial overload values over the first N calculation cycles are all less than the preset threshold value comprises:
and determining according to the counting times.
8. A solid launch vehicle engine exhaustion discriminating device, comprising:
the acquisition module is used for acquiring the axial overload average value of the solid carrier rocket in the current calculation period;
and the judging module is used for judging that the engine is exhausted when the axial overload average value is smaller than a preset threshold value.
9. A solid launch vehicle engine depletion discrimination apparatus comprising:
a memory and a processor communicatively coupled to each other, the memory having stored therein computer instructions, the processor executing the computer instructions to perform the solid launch vehicle engine exhaustion discrimination method of any of claims 1-7.
10. A computer-readable storage medium having stored thereon computer instructions for causing a computer to execute the solid launch vehicle engine depletion determination method of any one of claims 1-7.
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| CN201911235636.3A CN111142458B (en) | 2019-12-05 | 2019-12-05 | Solid carrier rocket engine exhaustion judging method, device and equipment |
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| CN201911235636.3A CN111142458B (en) | 2019-12-05 | 2019-12-05 | Solid carrier rocket engine exhaustion judging method, device and equipment |
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| CN111142458A true CN111142458A (en) | 2020-05-12 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111638644A (en) * | 2020-05-13 | 2020-09-08 | 上海航天控制技术研究所 | Two-stage aircraft separation time discrimination method based on axial overload |
| CN112361896A (en) * | 2020-10-27 | 2021-02-12 | 中国运载火箭技术研究院 | Solid carrier rocket guidance method and device, storage medium, and electronic device |
| CN113758737A (en) * | 2021-08-17 | 2021-12-07 | 航天科工火箭技术有限公司 | Reusable technology demonstration and verification rocket separation detection method, system and equipment |
Citations (28)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040050282A1 (en) * | 2001-11-01 | 2004-03-18 | Solberg Mark A. | Rocket motors with insensitive munitions systems and projectiles including same |
| JP2005178771A (en) * | 2003-12-22 | 2005-07-07 | Alliant Techsyst Inc | Ordnance system having common bus, its operation method and aerospace vehicle including the system |
| CN1712691A (en) * | 2004-06-24 | 2005-12-28 | 雅马哈发动机株式会社 | Stroke discriminating device of four stroke engine |
| CN201181193Y (en) * | 2007-08-06 | 2009-01-14 | 孙再庸 | Extinguishment rocket ammunition capable of spin stabilization, emitting set and system |
| CN102736541A (en) * | 2012-06-19 | 2012-10-17 | 北京航空航天大学 | Device for acquiring rocket-borne data of solid-liquid power sounding rocket |
| CN104483088A (en) * | 2014-12-11 | 2015-04-01 | 中国航天空气动力技术研究院 | Wind tunnel multi-body separation free light test method of simulating residual engine thrust |
| CN104632933A (en) * | 2014-12-05 | 2015-05-20 | 中国航天科技集团公司第九研究院第七七一研究所 | Axial tension safe clutch for large load |
| CN105468822A (en) * | 2015-11-16 | 2016-04-06 | 北京宇航系统工程研究所 | Rocket boosted separation impact load determination method |
| CN105573337A (en) * | 2015-12-14 | 2016-05-11 | 中国人民解放军国防科学技术大学 | De-orbit braking closed circuit guidance method satisfying constrains on reentry angles and flying ranges |
| CN106114910A (en) * | 2016-06-15 | 2016-11-16 | 湖北航天技术研究院总体设计所 | A kind of spacecraft flight track roll stablized loop method |
| CN106289451A (en) * | 2016-07-27 | 2017-01-04 | 上海航天设备制造总厂 | Merogenesis condenser type Low Temperature Liquid bit changer |
| CN107133380A (en) * | 2017-03-31 | 2017-09-05 | 北京蓝箭空间科技有限公司 | Launch Vehicle Engine exhausts/shut down a kind of guidance program angle processing method of section |
| CN107327355A (en) * | 2017-07-28 | 2017-11-07 | 北京宇航系统工程研究所 | A kind of spacecraft propulsion agent management method |
| CN107576446A (en) * | 2017-08-02 | 2018-01-12 | 南京航空航天大学 | A kind of active probe device and method of scramjet engine distance piece shock train leading edge |
| US20180065637A1 (en) * | 2014-10-27 | 2018-03-08 | Brian Bassindale | Idle reduction system and method |
| CN108469207A (en) * | 2018-02-01 | 2018-08-31 | 北京蓝箭空间科技有限公司 | Launching technique, transmitting automatic control method and the launch control system of carrier rocket |
| CN108549364A (en) * | 2018-04-26 | 2018-09-18 | 北京蓝箭空间科技有限公司 | Method of controlling security, safety control system and the server of aircraft flight |
| CN109115055A (en) * | 2018-08-29 | 2019-01-01 | 上海宇航系统工程研究所 | A kind of solid boost motor connection tripper |
| CN109539903A (en) * | 2018-10-31 | 2019-03-29 | 湖北航天技术研究院总体设计所 | A kind of Solid Launch Vehicle elliptical transfer orbit interative guidance control method |
| CN109630320A (en) * | 2018-10-22 | 2019-04-16 | 陕西蓝箭航天技术有限公司 | Purging system and blowing adapter for cryogenic liquid rocket engine |
| CN109737828A (en) * | 2019-01-14 | 2019-05-10 | 北京星际荣耀空间科技有限公司 | A kind of rocket takeoff condition method of discrimination, system and equipment |
| CN109798902A (en) * | 2019-03-11 | 2019-05-24 | 北京星际荣耀空间科技有限公司 | One kind being suitable for carrier rocket and enters the orbit modified interative guidance method |
| CN109855482A (en) * | 2019-03-05 | 2019-06-07 | 北京星际荣耀空间科技有限公司 | The method of discrimination and discriminating gear of Solid Launch Vehicle lift-off zero,take-off zero |
| CN109855483A (en) * | 2019-01-22 | 2019-06-07 | 北京蓝箭空间科技有限公司 | The time sequence design method of Solid Launch Vehicle stage separation |
| CN110005546A (en) * | 2019-03-14 | 2019-07-12 | 北京星际荣耀空间科技有限公司 | A kind of multiple assisted take-off rocket engine and starting method |
| CN110032199A (en) * | 2019-04-19 | 2019-07-19 | 北京航天自动控制研究所 | The pre- drift angle linear compensation method and device at rocket engine stand stretch angle |
| JP2019156007A (en) * | 2018-03-08 | 2019-09-19 | トヨタ自動車株式会社 | Control device for hybrid vehicle |
| DE102019113564A1 (en) * | 2018-05-22 | 2019-11-28 | Ford Global Technologies, Llc | METHOD AND SYSTEM FOR MOTOR CONTROL |
-
2019
- 2019-12-05 CN CN201911235636.3A patent/CN111142458B/en active Active
Patent Citations (29)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040050282A1 (en) * | 2001-11-01 | 2004-03-18 | Solberg Mark A. | Rocket motors with insensitive munitions systems and projectiles including same |
| JP2005178771A (en) * | 2003-12-22 | 2005-07-07 | Alliant Techsyst Inc | Ordnance system having common bus, its operation method and aerospace vehicle including the system |
| CN1712691A (en) * | 2004-06-24 | 2005-12-28 | 雅马哈发动机株式会社 | Stroke discriminating device of four stroke engine |
| CN100368673C (en) * | 2004-06-24 | 2008-02-13 | 雅马哈发动机株式会社 | Stroke discriminating device of four stroke engine |
| CN201181193Y (en) * | 2007-08-06 | 2009-01-14 | 孙再庸 | Extinguishment rocket ammunition capable of spin stabilization, emitting set and system |
| CN102736541A (en) * | 2012-06-19 | 2012-10-17 | 北京航空航天大学 | Device for acquiring rocket-borne data of solid-liquid power sounding rocket |
| US20180065637A1 (en) * | 2014-10-27 | 2018-03-08 | Brian Bassindale | Idle reduction system and method |
| CN104632933A (en) * | 2014-12-05 | 2015-05-20 | 中国航天科技集团公司第九研究院第七七一研究所 | Axial tension safe clutch for large load |
| CN104483088A (en) * | 2014-12-11 | 2015-04-01 | 中国航天空气动力技术研究院 | Wind tunnel multi-body separation free light test method of simulating residual engine thrust |
| CN105468822A (en) * | 2015-11-16 | 2016-04-06 | 北京宇航系统工程研究所 | Rocket boosted separation impact load determination method |
| CN105573337A (en) * | 2015-12-14 | 2016-05-11 | 中国人民解放军国防科学技术大学 | De-orbit braking closed circuit guidance method satisfying constrains on reentry angles and flying ranges |
| CN106114910A (en) * | 2016-06-15 | 2016-11-16 | 湖北航天技术研究院总体设计所 | A kind of spacecraft flight track roll stablized loop method |
| CN106289451A (en) * | 2016-07-27 | 2017-01-04 | 上海航天设备制造总厂 | Merogenesis condenser type Low Temperature Liquid bit changer |
| CN107133380A (en) * | 2017-03-31 | 2017-09-05 | 北京蓝箭空间科技有限公司 | Launch Vehicle Engine exhausts/shut down a kind of guidance program angle processing method of section |
| CN107327355A (en) * | 2017-07-28 | 2017-11-07 | 北京宇航系统工程研究所 | A kind of spacecraft propulsion agent management method |
| CN107576446A (en) * | 2017-08-02 | 2018-01-12 | 南京航空航天大学 | A kind of active probe device and method of scramjet engine distance piece shock train leading edge |
| CN108469207A (en) * | 2018-02-01 | 2018-08-31 | 北京蓝箭空间科技有限公司 | Launching technique, transmitting automatic control method and the launch control system of carrier rocket |
| JP2019156007A (en) * | 2018-03-08 | 2019-09-19 | トヨタ自動車株式会社 | Control device for hybrid vehicle |
| CN108549364A (en) * | 2018-04-26 | 2018-09-18 | 北京蓝箭空间科技有限公司 | Method of controlling security, safety control system and the server of aircraft flight |
| DE102019113564A1 (en) * | 2018-05-22 | 2019-11-28 | Ford Global Technologies, Llc | METHOD AND SYSTEM FOR MOTOR CONTROL |
| CN109115055A (en) * | 2018-08-29 | 2019-01-01 | 上海宇航系统工程研究所 | A kind of solid boost motor connection tripper |
| CN109630320A (en) * | 2018-10-22 | 2019-04-16 | 陕西蓝箭航天技术有限公司 | Purging system and blowing adapter for cryogenic liquid rocket engine |
| CN109539903A (en) * | 2018-10-31 | 2019-03-29 | 湖北航天技术研究院总体设计所 | A kind of Solid Launch Vehicle elliptical transfer orbit interative guidance control method |
| CN109737828A (en) * | 2019-01-14 | 2019-05-10 | 北京星际荣耀空间科技有限公司 | A kind of rocket takeoff condition method of discrimination, system and equipment |
| CN109855483A (en) * | 2019-01-22 | 2019-06-07 | 北京蓝箭空间科技有限公司 | The time sequence design method of Solid Launch Vehicle stage separation |
| CN109855482A (en) * | 2019-03-05 | 2019-06-07 | 北京星际荣耀空间科技有限公司 | The method of discrimination and discriminating gear of Solid Launch Vehicle lift-off zero,take-off zero |
| CN109798902A (en) * | 2019-03-11 | 2019-05-24 | 北京星际荣耀空间科技有限公司 | One kind being suitable for carrier rocket and enters the orbit modified interative guidance method |
| CN110005546A (en) * | 2019-03-14 | 2019-07-12 | 北京星际荣耀空间科技有限公司 | A kind of multiple assisted take-off rocket engine and starting method |
| CN110032199A (en) * | 2019-04-19 | 2019-07-19 | 北京航天自动控制研究所 | The pre- drift angle linear compensation method and device at rocket engine stand stretch angle |
Non-Patent Citations (5)
| Title |
|---|
| SOWER GEARGE: ""Evalued Altas to meet space transportation meads"", 《SPACE EXPLORATION》 * |
| ZHANG SHU: ""Preseat state of Atlas V Family and its Research&Development"", 《LAUNCH VEHICLE TECHNOLOGY》 * |
| 康建斌: ""基于固体火箭发动机耗尽关机的混合轨道自适应制导方案研究"", 《固体火箭技术》 * |
| 张仝伟: ""SFMEA方法在飞行控制软件中的应用"", 《航天控制》 * |
| 杨希祥: ""基于运载能力评估的固体运载火箭推力向量控制方案比较"", 《国防科技大学学报》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111638644A (en) * | 2020-05-13 | 2020-09-08 | 上海航天控制技术研究所 | Two-stage aircraft separation time discrimination method based on axial overload |
| CN112361896A (en) * | 2020-10-27 | 2021-02-12 | 中国运载火箭技术研究院 | Solid carrier rocket guidance method and device, storage medium, and electronic device |
| CN112361896B (en) * | 2020-10-27 | 2022-04-29 | 中国运载火箭技术研究院 | Solid carrier rocket guidance method and device, storage medium, and electronic device |
| CN113758737A (en) * | 2021-08-17 | 2021-12-07 | 航天科工火箭技术有限公司 | Reusable technology demonstration and verification rocket separation detection method, system and equipment |
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