CN111380424A - Rocket launching point location determination method and device - Google Patents
Rocket launching point location determination method and device Download PDFInfo
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- CN111380424A CN111380424A CN202010367890.5A CN202010367890A CN111380424A CN 111380424 A CN111380424 A CN 111380424A CN 202010367890 A CN202010367890 A CN 202010367890A CN 111380424 A CN111380424 A CN 111380424A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
Abstract
The invention discloses a method and a device for determining the position of a rocket launching point, wherein the method comprises the following steps: acquiring real-time rocket positioning data of a satellite navigation receiver for target times to obtain a plurality of target rocket positioning data; performing target calculation according to the plurality of target rocket positioning data to obtain position data of rocket launching points; and determining the information of the rocket launching point according to the position data of the rocket launching point. The method obtains the rocket launching point location information by performing target calculation through a plurality of real-time rocket positioning data, ensures the accuracy of the rocket launching point location information, and can determine the launching point location in real time compared with the prior art that the rocket can only be launched at a fixed launching point of a fixed launching field, meets the requirements of mobile launching or launching the rocket at a newly-built launching field, does not need manual advance measurement, saves the labor cost and improves the rocket launching efficiency.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a method and a device for determining a rocket launching point position.
Background
The rocket is a carrier for realizing space flight, and related scientific research and detection work is completed by launching the carrier rocket to send the spacecraft into a preset orbit. When the existing rocket is launched, launching point location information such as longitude, latitude, elevation and the like of a launching field needs to be obtained in advance in a manual measurement mode, and then the rocket is moved to a measured fixed launching point to complete launching. However, when the rocket needs to be launched movably or launched in a newly-built launching field, the launching point position needs to be measured again manually, and the existing rocket launching point position determining mode cannot meet the real-time launching requirement, so that the rocket launching efficiency is influenced.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is to overcome the defect that the labor time is consumed for measuring the rocket launching site in advance or the rocket launching site can only be launched in the launching site which has already been subjected to site location test in the prior art, thereby providing the method and the device for determining the rocket launching site location.
According to a first aspect, the embodiment of the invention discloses a method for determining the position of a rocket launching point, which comprises the following steps: acquiring real-time rocket positioning data of a satellite navigation receiver for target times to obtain a plurality of target rocket positioning data; performing target calculation according to the plurality of target rocket positioning data to obtain position data of rocket launching points; and determining the information of the rocket launching point according to the position data of the rocket launching point.
With reference to the first aspect, in a first implementation manner of the first aspect, the obtaining real-time rocket positioning data of a satellite navigation receiver for a target number of times to obtain a plurality of target rocket positioning data includes: preprocessing the acquired real-time rocket positioning data of the satellite navigation receiver; and taking the preprocessed real-time rocket positioning data as target rocket positioning data.
With reference to the first aspect, in a second implementation manner of the first aspect, performing target calculation according to the multiple pieces of target rocket positioning data to obtain location data of a rocket launching point includes:
wherein k is recursion times, the initial value is 0, and rocket positioning data acquired by the satellite navigation receiver each time is calculated onceThen, k is added by 1;
obtaining the position data of the rocket launching point according to the rocket positioning data of the kth satellite navigation receiver;
rocket positioning data of the satellite navigation receiver acquired at the kth time;
obtaining the position data of the rocket launching point according to the rocket positioning data of the satellite navigation receiver at the kth-1 th time;
the abscissa representing the launch point of the rocket,
the ordinate of the launch point of the rocket is shown,
representing the vertical coordinates of the rocket launch point.
With reference to the second embodiment of the first aspect, in a third embodiment of the first aspect, the rocket launch point location information includes longitude information; determining the longitude information of the rocket launching point according to the position data of the rocket launching point, comprising the following steps:
wherein the content of the first and second substances,
indicating longitude information of the rocket.
With reference to the second embodiment of the first aspect, in a fourth embodiment of the first aspect, the rocket launch site location information includes latitude information; according to the position data of the rocket launching point, determining the latitude information of the rocket launching point, which comprises the following steps: calculating an initial latitude value according to the position data; determining a latitude value according to the initial latitude value, and performing iterative calculation by taking the latitude value as a new initial latitude value; and taking the latitude value reaching the preset iteration times as the latitude information of the rocket launching point.
With reference to the fourth implementation manner of the first aspect, in a fifth implementation manner of the first aspect, the initial latitude value is determined according to the following formula:
the weft value is determined according to the following formula:
wherein the content of the first and second substances,
the initial value of the latitude of the rocket is represented,
representing the latitude value, phi, of the rocket after iterationdx0_GmnssRepresenting geocentric latitude, fe2And
are all constants.
With reference to the fifth implementation manner of the first aspect, in the sixth implementation manner of the first aspect, the rocket launch site location information includes elevation information; determining the elevation information of the rocket launching point according to the position data of the rocket launching point, comprising the following steps:
wherein the content of the first and second substances,
elevation information representing the rocket.
According to a second aspect, an embodiment of the present invention further discloses a rocket launching point location determining apparatus, including: the first acquisition module is used for acquiring real-time rocket positioning data of the satellite navigation receiver for the target times to obtain a plurality of target rocket positioning data; the calculation module is used for performing target calculation according to the plurality of target rocket positioning data to obtain position data of rocket launching points; and the determining module is used for determining the information of the rocket launching point according to the position data of the rocket launching point.
According to a third aspect, an embodiment of the present invention further discloses a computer device, including: at least one processor; and a memory communicatively coupled to the at least one processor; wherein the memory stores instructions executable by the one processor to cause the at least one processor to perform the steps of the rocket launch site location determining method according to the first aspect or any embodiment of the first aspect.
According to a fourth aspect, the embodiments of the present invention further disclose a computer-readable storage medium, on which a computer program is stored, where the computer program, when executed by a processor, implements the steps of the rocket launch site location determining 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 method and the device for determining the rocket launching point location, the real-time rocket positioning data of the satellite navigation receiver of the target times are obtained to obtain the positioning data of a plurality of target rockets, and the target calculation is carried out according to the positioning data of the plurality of target rockets to obtain the position data of the rocket launching point. The method has the advantages that target calculation is carried out through the plurality of real-time rocket positioning data to obtain the rocket launching point location information, the accuracy of the rocket launching point location information is guaranteed, and compared with the prior art that launching can only be carried out at a fixed launching point of a fixed launching site, the launching point location can be determined in real time by the implementation of the method, the requirements of mobile launching or launching a rocket at a newly-built launching site are met, manual advance measurement is not needed, the labor cost is saved, and meanwhile the rocket launching efficiency is 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 flowchart of a specific example of a rocket launch site determining method in embodiment 1 of the present invention;
FIG. 2 is a schematic block diagram of a specific example of the fire arrow shooting point determining apparatus in embodiment 2 of the present invention;
fig. 3 is a schematic block diagram of a specific example of a computer device in embodiment 3 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.
The terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
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 of the invention provides a method for determining the position of a rocket launching point, which comprises the following steps as shown in figure 1:
s11: and acquiring real-time rocket positioning data of the satellite navigation receiver for the target times to obtain a plurality of target rocket positioning data.
Illustratively, the satellite navigation system can provide uninterrupted, real-time three-dimensional positioning information, and since the GPS satellite navigation system is relatively mature, in the embodiment of the present invention, a GPS satellite navigation receiver can be used to obtain real-time rocket positioning data. The method for acquiring the real-time rocket positioning data of the satellite navigation receiver for the target times is not limited by the embodiment of the invention, and the acquisition method of the real-time rocket positioning data can be set by a person skilled in the art according to actual conditions. The period of time may be 10 minutes or 15 minutes, and the period of time is not limited in the embodiment of the present invention and may be set according to actual conditions. The preset number may be 100, and in order to improve the calculation accuracy, the preset number may be set to a larger value, and the preset number is not limited in the present invention.
S12: and performing target calculation according to the positioning data of the plurality of target rockets to obtain the position data of the rocket launching points.
For example, the target calculation method may be to average the plurality of target rocket-positioning data, and use the average as the position data of the rocket launching points. The target calculation method is not limited in the embodiment of the present invention, and those skilled in the art can set the target calculation method according to actual situations.
As an optional implementation manner of this application, in the embodiment of the present invention, the position data of the rocket launching point obtained by performing target calculation according to the positioning data of a plurality of target rockets may be obtained as follows:
wherein k is recursion frequency, the initial value is 0, and k is accumulated by 1 after rocket positioning data of the satellite navigation receiver is acquired and calculated once each time;
for rocket launches derived from rocket positioning data of kth satellite navigation receiverPosition data of the shot;
rocket positioning data of the satellite navigation receiver acquired at the kth time;
obtaining the position data of the rocket launching point according to the rocket positioning data of the satellite navigation receiver at the kth-1 th time;
the abscissa representing the launch point of the rocket,
the ordinate of the launch point of the rocket is shown,
representing the vertical coordinates of the rocket launch point.
The position of the current rocket launching point calculated by the last rocket launching point position average value and the rocket positioning data obtained this time is more accurate than the position of the current rocket launching point obtained by directly averaging the obtained target rocket positioning data.
S13: and determining the information of the rocket launching point according to the position data of the rocket launching point.
For example, the rocket launching point location information may include longitude information, latitude information, elevation information, and the like, the type of the point location information is not limited in the embodiment of the present application, and a person skilled in the art may select other point location information that may be determined according to the location data according to actual needs. According to the position data of the rocket launching point, determining the rocket launching point location information can determine one point location information or a plurality of point location information, and a person skilled in the art can determine the point location information according to actual needs, for example, when determining the rocket launching direction, determining longitude information, latitude information and elevation information at the same time is needed, specifically:
first, inertial measurement data is acquired.
Illustratively, the inertial measurement data may include angular velocity and acceleration, among other things, and the inertial measurement data may enable autonomous navigation by measuring rocket acceleration and angular velocity using inertial measurement devices, such as gyroscopes and accelerometers.
And secondly, determining the launching direction of the rocket according to the inertial measurement data, the longitude information, the latitude information and the elevation information. And calculating the rocket launching direction by using a self-aiming method according to the inertial measurement data, the longitude information, the latitude information and the elevation information, wherein the self-aiming method can refer to the inertial navigation technology and is not repeated herein.
The rocket launching point location determining method obtains a plurality of target rocket positioning data by obtaining real-time rocket positioning data of a satellite navigation receiver for target times, and performs target calculation according to the plurality of target rocket positioning data to obtain the position data of the rocket launching points. The method has the advantages that target calculation is carried out through the plurality of real-time rocket positioning data to obtain the rocket launching point location information, the accuracy of the rocket launching point location information is guaranteed, and compared with the prior art that launching can only be carried out at a fixed launching point of a fixed launching site, the launching point location can be determined in real time by the implementation of the method, the requirements of mobile launching or launching a rocket at a newly-built launching site are met, manual advance measurement is not needed, the labor cost is saved, and meanwhile the rocket launching efficiency is improved.
As an alternative embodiment of the present application, step S11 includes:
firstly, preprocessing the acquired real-time rocket positioning data of the satellite navigation receiver.
For example, in the embodiment of the present invention, the preprocessing the acquired real-time rocket positioning data of the satellite navigation receiver may be to screen the acquired real-time rocket positioning data to obtain target positioning data, the screening method may be that a Position Precision factor (pdop) of the rocket positioning data is within a preset range, where the preset range may be that a pdop value is smaller than 6, and in order to improve accuracy of Position data determination, the preset range may be smaller.
Secondly, the preprocessed real-time rocket positioning data is used as target rocket positioning data.
For example, in the embodiment of the present invention, some rocket positioning data with large errors may be screened out in the screening process, and the preprocessed real-time rocket positioning data is used as the target rocket positioning data, so that the position error of the rocket launching point obtained according to the target rocket positioning data is small, and the accuracy is high.
As an optional embodiment of the present application, when the rocket launching point location information is longitude information, determining the rocket launching point location longitude information according to the location data of the rocket launching point, including:
wherein the content of the first and second substances,
indicating longitude information of the rocket.
As an optional embodiment of the present application, when the rocket launching point location information is latitude information, determining the rocket launching point location latitude information according to the position data of the rocket launching point includes:
first, an initial latitude value is calculated from the position data.
For example, in the embodiment of the present invention, according to the position data, the initial latitude value may be calculated as:
wherein the content of the first and second substances,
indicating the initial value of the latitude of the rocket, phidx0_GmnssRepresenting the geocentric latitude, can be determined by:
wherein the content of the first and second substances,
the distance from the earth center to the rocket launching point can be specifically determined by the following formula:
fe2and
are all constants, in the present example, fe2＝0.00335281068118231893543414612613，ae＝6378137。
And secondly, determining a latitude value according to the initial latitude value, and performing iterative calculation by taking the latitude value as a new initial latitude value.
For example, according to the initial latitude value, the latitude value may be determined as follows:
wherein the content of the first and second substances,
representing the latitude value of the rocket after iteration.
And performing iterative calculation by taking the obtained latitude value as a new latitude initial value, so as to obtain more accurate latitude information.
And thirdly, taking the latitude value reaching the preset iteration times as the latitude information of the rocket launching point.
For example, the preset iteration number may be 100 times or 200 times, the preset iteration number is not limited in the embodiment of the present invention, and a person skilled in the art may set the iteration number according to an actual situation.
As an optional implementation manner of the present application, when the rocket launching point location information is elevation information, determining the rocket launching point location elevation information according to the position data of the rocket launching point includes:
wherein the content of the first and second substances,
elevation information representing the rocket.
Example 2
An embodiment of the present invention provides a rocket launching point location determining apparatus, as shown in fig. 2, including:
the acquisition module 21 is configured to acquire real-time rocket positioning data of the satellite navigation receiver for the target times to obtain a plurality of target rocket positioning data; the specific implementation manner is described in relation to step S11 in embodiment 1, and is not described herein again.
The calculation module 22 is used for performing target calculation according to the positioning data of the plurality of target rockets to obtain position data of rocket launching points; the specific implementation manner is described in relation to step S12 in embodiment 1, and is not described herein again.
And the determining module 23 is configured to determine the information of the rocket launching point according to the position data of the rocket launching point. The specific implementation manner is described in relation to step S13 in embodiment 1, and is not described herein again.
The rocket launching point location determining device obtains a plurality of target rocket positioning data by obtaining the real-time rocket positioning data of the satellite navigation receiver for the target times, and performs target calculation according to the plurality of target rocket positioning data to obtain the position data of the rocket launching points. The method has the advantages that target calculation is carried out through the plurality of real-time rocket positioning data to obtain the rocket launching point location information, the accuracy of the rocket launching point location information is guaranteed, and compared with the prior art that launching can only be carried out at a fixed launching point of a fixed launching site, the launching point location can be determined in real time by the implementation of the method, the requirements of mobile launching or launching a rocket at a newly-built launching site are met, manual advance measurement is not needed, the labor cost is saved, and meanwhile the rocket launching efficiency is improved.
As an optional embodiment of the present application, the obtaining module 21 includes:
the preprocessing module is used for preprocessing the acquired real-time rocket positioning data of the satellite navigation receiver; the specific implementation manner is described in association with corresponding steps in embodiment 1, and is not described herein again.
And the positioning data obtaining module is used for taking the preprocessed real-time rocket positioning data as target rocket positioning data. The specific implementation manner is described in association with corresponding steps in embodiment 1, and is not described herein again.
As an alternative embodiment of the present application, the calculation module 22 includes:
wherein k is recursion frequency, the initial value is 0, and k is accumulated by 1 after rocket positioning data of the satellite navigation receiver is acquired and calculated once each time;
obtaining the position data of the rocket launching point according to the rocket positioning data of the kth satellite navigation receiver;
rocket positioning data of the satellite navigation receiver acquired at the kth time;
obtaining the position data of the rocket launching point according to the rocket positioning data of the satellite navigation receiver at the kth-1 th time;
the abscissa representing the launch point of the rocket,
the ordinate of the launch point of the rocket is shown,
representing the vertical coordinates of the rocket launch point.
As an alternative embodiment of the present application, the determining module 23 includes:
wherein the content of the first and second substances,
indicating longitude information of the rocket.
As an optional embodiment of the present application, the determining module 23 further includes:
the latitude initial value calculation module is used for calculating an initial latitude value according to the position data; the specific implementation manner is described in association with corresponding steps in embodiment 1, and is not described herein again.
The iterative computation module is used for determining the latitude value according to the initial latitude value and performing iterative computation by taking the latitude value as a new initial latitude value; the specific implementation manner is described in association with corresponding steps in embodiment 1, and is not described herein again.
And the latitude information acquisition module is used for taking the latitude value reaching the preset iteration times as the latitude information of the rocket launching point. The specific implementation manner is described in association with corresponding steps in embodiment 1, and is not described herein again.
As an alternative embodiment of the present application, the initial latitude value is determined according to the following formula:
the weft value is determined according to the following formula:
wherein the content of the first and second substances,
the initial value of the latitude of the rocket is represented,
representing the latitude value, phi, of the rocket after iterationdx0_GmnssRepresenting geocentric latitude, fe2And
are all constants.
As an optional embodiment of the present application, the determining module 23 further includes:
wherein the content of the first and second substances,
elevation information representing the rocket.
As an optional embodiment of the present invention, the rocket launching point location determining apparatus further includes:
and the inertial measurement data acquisition module is used for acquiring inertial measurement data. The specific implementation manner is described in association with corresponding steps in embodiment 1, and is not described herein again.
And the launching direction acquisition module is used for determining the launching direction of the rocket according to the inertial measurement data, the longitude information, the latitude information and the elevation information. The specific implementation manner is described in association with corresponding steps in embodiment 1, and is not described herein again.
Example 3
An embodiment of the present invention further provides a computer device, as shown in fig. 3, the computer device may include a processor 31 and a memory 32, where the processor 31 and the memory 32 may be connected by a bus or in another manner, and fig. 3 takes the example of being connected 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), 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 combinations 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 calculating module 22, and the determining module 23 shown in fig. 2) corresponding to the rocket launch site location determining method in the embodiment of the present invention. The processor 31 executes various functional applications and data processing of the processor by running non-transitory software programs, instructions and modules stored in the memory 32, that is, the rocket launch point location determination method in the above-described method embodiment is implemented.
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 memory 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 rocket launch site location determination method as in the embodiment shown in FIG. 1.
The details of the computer device can be understood with reference to the corresponding related descriptions and effects in the embodiment shown in fig. 1, and are not described herein again.
Example 4
The embodiment of the invention also provides a computer storage medium, wherein the computer storage medium stores computer executable instructions, and the computer executable instructions can execute the rocket launching point location determining method in any method embodiment. The storage medium may be a magnetic disk, an optical disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), a Flash Memory (Flash Memory), a Hard disk (Hard disk Drive, abbreviated as HDD), a Solid State Drive (SSD), or the like; the storage medium may also comprise a combination of memories of the kind described above.
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 rocket launching point location determining method is characterized by comprising the following steps:
acquiring real-time rocket positioning data of a satellite navigation receiver for target times to obtain a plurality of target rocket positioning data;
performing target calculation according to the plurality of target rocket positioning data to obtain position data of rocket launching points;
and determining the information of the rocket launching point according to the position data of the rocket launching point.
2. The method of claim 1, wherein obtaining real-time rocket positioning data for a satellite navigation receiver for a target number of times, resulting in a plurality of target rocket positioning data, comprises:
preprocessing the acquired real-time rocket positioning data of the satellite navigation receiver;
and taking the preprocessed real-time rocket positioning data as target rocket positioning data.
3. The method of claim 1, wherein performing object calculations based on the plurality of object rocket positioning data to obtain rocket launch point location data comprises:
wherein k is recursion frequency, the initial value is 0, and k is accumulated by 1 after rocket positioning data of the satellite navigation receiver is acquired and calculated once each time;
obtaining the position data of the rocket launching point according to the rocket positioning data of the kth satellite navigation receiver;
rocket positioning data of the satellite navigation receiver acquired at the kth time;
obtaining the position data of the rocket launching point according to the rocket positioning data of the satellite navigation receiver at the kth-1 th time;
the abscissa representing the launch point of the rocket,
the ordinate of the launch point of the rocket is shown,
representing the vertical coordinates of the rocket launch point.
4. The method of claim 3, wherein the rocket launch site location information comprises longitude information; determining the longitude information of the rocket launching point according to the position data of the rocket launching point, comprising the following steps:
wherein the content of the first and second substances,
indicating longitude information of the rocket.
5. The method of claim 3, wherein the rocket launch site location information comprises latitude information; according to the position data of the rocket launching point, determining the latitude information of the rocket launching point, which comprises the following steps:
calculating an initial latitude value according to the position data;
determining a latitude value according to the initial latitude value, and performing iterative calculation by taking the latitude value as a new initial latitude value;
and taking the latitude value reaching the preset iteration times as the latitude information of the rocket launching point.
6. The method of claim 5, wherein the initial latitude value is determined according to the following formula:
the weft value is determined according to the following formula:
wherein the content of the first and second substances,
the initial value of the latitude of the rocket is represented,
representing the latitude value, phi, of the rocket after iterationdx0_GmnssRepresenting geocentric latitude, fe2And
are all constants.
7. The method of claim 6, wherein the rocket launch site location information comprises elevation information; determining the elevation information of the rocket launching point according to the position data of the rocket launching point, comprising the following steps:
wherein the content of the first and second substances,
elevation information representing the rocket.
8. A rocket launch site location determining apparatus, comprising:
the first acquisition module is used for acquiring real-time rocket positioning data of the satellite navigation receiver for the target times to obtain a plurality of target rocket positioning data;
the calculation module is used for performing target calculation according to the plurality of target rocket positioning data to obtain position data of rocket launching points;
and the determining module is used for determining the information of the rocket launching point according to the position data of the rocket launching point.
9. A computer device, comprising: at least one processor; and a memory communicatively coupled to the at least one processor; wherein the memory stores instructions executable by the one processor to cause the at least one processor to perform the steps of the rocket launch site location determining method according to any one of claims 1-7.
10. A computer-readable storage medium, on which a computer program is stored, which, when being executed by a processor, carries out the steps of the rocket point location determination method according to any one of claims 1-7.
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| CN111895865A (en) * | 2020-08-06 | 2020-11-06 | 西安睿高测控技术有限公司 | Satellite guidance ammunition guidance method for reducing loading data requirements |
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