Method, device, equipment and storage medium for determining launch window of carrier rocket
阅读说明：本技术 运载火箭发射窗口的确定方法、装置、设备及存储介质 (Method, device, equipment and storage medium for determining launch window of carrier rocket ) 是由 刘百奇 范文锋 孙国伟 王博 刘建设 于 2021-02-10 设计创作，主要内容包括：本申请提供了一种运载火箭发射窗口的确定方法、装置、设备及存储介质。运载火箭发射窗口的确定方法包括：获取卫星的入轨时刻降交点地方时、入轨时刻降交点地理经度、发射点所用时区地理经度、入轨时刻降交点地方时的允许偏差值以及运载火箭的理论飞行时间和理论飞行时间偏差；根据入轨时刻降交点地理经度和发射点所用时区地理经度,确定卫星在入轨时刻的降交点和发射点之间的地理时间差；根据理论飞行时间和理论飞行时间偏差,确定运载火箭发射和飞行的相对时间范围；根据入轨时刻降交点地方时、地理时间差、相对时间范围和允许偏差值,确定运载火箭的发射窗口。本申请可应用于SSO轨道卫星发射任务,计算方法简单,程序运行速度快,计算结果可靠。(The application provides a method, a device, equipment and a storage medium for determining a launch window of a carrier rocket. The method for determining the launch window of the carrier rocket comprises the following steps: acquiring local time of a landing intersection point at the time of the orbit entering of a satellite, geographical longitude of the landing intersection point at the time of the orbit entering, geographical longitude of a time zone used by a launching point, an allowable deviation value of the local time of the landing intersection point at the time of the orbit entering, and theoretical flight time deviation of a carrier rocket; determining the geographical time difference between the descending intersection point and the launching point of the satellite at the time of the orbit according to the geographical longitude of the descending intersection point and the geographical longitude of the time zone used by the launching point at the time of the orbit; determining the relative time range of launch and flight of the carrier rocket according to the theoretical flight time and the theoretical flight time deviation; and determining a launching window of the carrier rocket according to the local time of the landing point at the time of the orbit entering, the geographical time difference, the relative time range and the allowed deviation value. The method can be applied to SSO orbit satellite launching tasks, and is simple in calculation method, high in program running speed and reliable in calculation result.)
1. A method for determining a launch window of a launch vehicle, comprising:
acquiring local time of a landing point at the time of the orbit entering of a satellite, geographical longitude of the landing point at the time of the orbit entering, geographical longitude of a time zone used by a launching point, an allowable deviation value of the local time of the landing point at the time of the orbit entering, and theoretical flight time deviation of a carrier rocket;
determining the geographical time difference between the descending intersection point and the transmitting point of the satellite at the time of the orbit according to the geographical longitude of the descending intersection point at the time of the orbit and the geographical longitude of the time zone used by the transmitting point;
determining the relative time range of launch and flight of the carrier rocket according to the theoretical flight time and the theoretical flight time deviation;
and determining a launching window of the carrier rocket according to the local time of the landing point at the track-entering moment, the geographical time difference, the relative time range and the allowed deviation value.
2. A method of determining a launch window for a launch vehicle according to claim 1, wherein determining a relative time range for the launch vehicle from firing to orbiting the satellite based on the theoretical time of flight and the theoretical time of flight bias comprises:
determining a first boundary value of the relative time range according to the theoretical flight time and a first deviation value of the deviation of the theoretical flight time;
determining a second boundary value of the relative time range from a second deviation value of the theoretical time of flight and the theoretical time of flight deviation; the second offset value is greater than the first offset value;
determining the relative time range based on the first boundary value and the second boundary value.
3. A method for determining a launch window of a launch vehicle according to claim 2, wherein determining a launch window of the launch vehicle based on the time at which the time of the entry landed at the point of intersection, the geographical time difference, the relative time range, and the allowed deviation value comprises:
determining a first allowable launching time of the carrier rocket according to the local time of the landing point at the track-entering time, the geographic time difference, the allowable deviation value and the first boundary value;
determining a second allowable launching time of the carrier rocket according to the local time of the landing point at the track-entering time, the geographic time difference, the allowable deviation value and the second boundary value;
and determining the emission window according to the first allowed emission time and the second allowed emission time.
4. A method for determining a launch window of a launch vehicle according to any of claims 1-3, and further comprising:
acquiring target orbit parameters and J2 perturbation parameters of the satellite;
and determining the launching window interval time of the carrier rocket according to the target orbit parameter and the J2 perturbation parameter.
5. The method of determining a launch vehicle window of claim 4, wherein said target orbit parameters include: a target track semi-major axis, a target track eccentricity, and a target track inclination.
6. The method for determining a launch window of a launch vehicle of claim 4, wherein obtaining the geographic longitude of the point of intersection at which the satellite enters the orbit, the geographic longitude of the time zone used at the launch site, the allowable deviation value of the point of intersection at which the satellite enters the orbit, and the theoretical time of flight and the deviation of the theoretical time of flight of the launch vehicle, and obtaining the target orbit parameters and the J2 perturbation parameters of the satellite comprise:
displaying input frames of the local place of the landing point at the track-entering time, the geographical longitude of the time zone used by the launching point, the allowed deviation value, the theoretical flight time, the deviation of the theoretical flight time and the target orbit parameter in the same display interface;
responding to input operation aiming at each input box, and acquiring local time of the landing point of the track-in time, geographical longitude of a time zone used by the launching point, the allowed deviation value, the theoretical flight time deviation and the target orbit parameter;
pre-stored J2 perturbation parameters were obtained.
7. The method of determining a launch vehicle window of claim 4, further comprising:
and displaying at least one piece of data in the launching window, the standard launching moment and the launching window interval time of the carrier rocket in the same display interface.
8. An apparatus for determining a launch window of a launch vehicle, comprising:
the data acquisition module is used for acquiring the local time of the landing point at the time of the orbit entering of the satellite, the geographical longitude of the landing point at the time of the orbit entering, the geographical longitude of a time zone used by a launching point, the allowable deviation value of the local time of the landing point at the time of the orbit entering, and the theoretical flight time deviation of the carrier rocket;
a first time determining module, configured to determine, according to the geographical longitude of the touchdown point at the time of the orbit entry and the geographical longitude of the time zone used by the launch point, a geographical time difference between the touchdown point and the launch point of the satellite at the time of the orbit entry;
the second time determination module is used for determining the relative time range of launching and flying of the carrier rocket according to the theoretical flying time and the theoretical flying time deviation;
and the launching window determining module is used for determining the launching window of the carrier rocket according to the local time of the landing point at the track-entering time, the geographical time difference, the relative time range and the allowed deviation value.
9. A launch window determination apparatus for a launch vehicle, comprising:
a memory;
a processor electrically connected with the memory;
the memory stores a computer program for execution by the processor to implement the method of determining a launch window of a launch vehicle of any of claims 1-7.
10. A computer-readable storage medium, in which a computer program is stored which, when being executed by a processor, carries out a method of determining a launch window of a launch vehicle according to any one of claims 1 to 7.
Technical Field
The application relates to the technical field of launch of carrier rockets, in particular to a method, a device, equipment and a storage medium for determining a launch window of a carrier rocket.
Background
The rocket launch window refers to a suitable time frame that allows the rocket to launch, also referred to as the width of the launch window. The launch window of the launch vehicle is determined according to the requirements of the launch vehicle itself and external constraints, the most important of which is the payload specifications.
The tasks of the payloads carried by the carrier rockets are different, and the limiting conditions for the launching windows are different, such as observation requirements, orbit entering conditions, solar radiation influence, returning and re-entering conditions and the like.
In the existing research for determining the rocket launching window, the multiple sides are heavier than the aspects of wide task requirements or other specific requirements (such as measurement requirements and Orbit transfer requirements) and the like, and a launching window determining method for an SSO (Sun-Synchronous Orbit) Orbit does not exist, so that great inconvenience is caused to the execution of the SSO Orbit satellite launching task.
Disclosure of Invention
The application provides a method, a device, equipment and a storage medium for determining a launch window of a carrier rocket aiming at the defects of the prior art, and aims to solve the technical problem that the launch window can not be determined aiming at an SSO (single-phase orbiting) orbit in the prior art.
In a first aspect, an embodiment of the present application provides a method for determining a launch window of a launch vehicle, including:
acquiring local time of a landing intersection point at the time of the orbit entering of a satellite, geographical longitude of the landing intersection point at the time of the orbit entering, geographical longitude of a time zone used by a launching point, an allowable deviation value of the local time of the landing intersection point at the time of the orbit entering, and theoretical flight time deviation of a carrier rocket;
determining the geographical time difference between the descending intersection point and the launching point of the satellite at the time of the orbit according to the geographical longitude of the descending intersection point and the geographical longitude of the time zone used by the launching point at the time of the orbit;
determining the relative time range of launch and flight of the carrier rocket according to the theoretical flight time and the theoretical flight time deviation;
and determining a launching window of the carrier rocket according to the local time of the landing point at the time of the orbit entering, the geographical time difference, the relative time range and the allowed deviation value.
In a second aspect, an embodiment of the present application provides an apparatus for determining a launch window of a launch vehicle, including:
the data acquisition module is used for acquiring the local time of the landing point at the time of the orbit entering of the satellite, the geographical longitude of the landing point at the time of the orbit entering, the geographical longitude of a time zone used by a launching point, an allowable deviation value of the local time of the landing point at the time of the orbit entering, and the theoretical flight time deviation of the carrier rocket;
the first time determination module is used for determining the geographical time difference between the descending intersection point and the transmitting point of the satellite at the orbit entering moment according to the descending intersection point geographical longitude and the time zone geographical longitude used by the transmitting point at the orbit entering moment;
the second time determination module is used for determining the relative time range of launch and flight of the carrier rocket according to the theoretical flight time and the theoretical flight time deviation;
and the launching window determining module is used for determining the launching window of the carrier rocket according to the local time of the landing point at the track-in time, the geographical time difference, the relative time range and the allowed deviation value.
In a third aspect, an embodiment of the present application provides a device for determining a launch window of a launch vehicle, including:
a memory;
a processor electrically connected to the memory;
the memory stores a computer program for execution by the processor to implement the method for determining a launch window of a launch vehicle provided in the first aspect of the embodiments of the present application.
In a fourth aspect, an embodiment of the present application provides a computer-readable storage medium, which stores a computer program, and the computer program, when executed by a processor, implements the method for determining a launch window of a launch vehicle provided in the first aspect of the embodiment of the present application.
The technical scheme provided by the embodiment of the application at least has the following beneficial effects:
1) according to the method and the device, the geographical longitude of the landing point at the time of the entry point is used as the constraint condition of the rocket launching window, the geographical longitude of the time zone used by the launching point, the allowed deviation value of the landing point at the time of the entry point and the theoretical flight time deviation of the carrier rocket are combined, the launching window of the carrier rocket can be determined, the method and the device can be applied to SSO orbit satellite launching tasks, the calculation method is simple, the program running speed is high, the calculation result is reliable, and meanwhile the blank that the rocket launching window cannot be determined based on the constraint of the landing point is filled.
2) The time of the arrival time landing point and the allowable deviation value thereof in the embodiment of the application are usually from a load side, namely a satellite side.
Additional aspects and advantages of the present application will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the present application.
Drawings
The foregoing and/or additional aspects and advantages of the present application will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
FIG. 1 is a schematic flow chart of a method for determining a launch window of a launch vehicle according to an embodiment of the present application;
FIG. 2 is a schematic flow chart illustrating another method for determining a launch window of a launch vehicle according to an embodiment of the present disclosure;
FIG. 3 is a schematic diagram of a display interface in an embodiment of the present application;
FIG. 4 is a schematic diagram of inputting parameters in a presentation interface according to an embodiment of the present application;
FIG. 5 is a schematic diagram illustrating a calculation result in a display interface according to an embodiment of the present application;
FIG. 6 is a schematic structural framework diagram of a means for determining the launch window of a launch vehicle according to an embodiment of the present application;
fig. 7 is a schematic structural framework diagram of a determination device for a launch window of a launch vehicle according to an embodiment of the present application.
Detailed Description
Reference will now be made in detail to the present application, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar parts or parts having the same or similar functions throughout. In addition, if a detailed description of the known art is not necessary for illustrating the features of the present application, it is omitted. The embodiments described below with reference to the drawings are exemplary only for the purpose of explaining the present application and are not to be construed as limiting the present application.
It will be understood by those within the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
As used herein, the singular forms "a", "an", "the" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof. It will be understood that when an element is referred to as being "connected" or "coupled" to another element, it can be directly connected or coupled to the other element or intervening elements may also be present. Further, "connected" or "coupled" as used herein may include wirelessly connected or wirelessly coupled. As used herein, the term "and/or" includes all or any element and all combinations of one or more of the associated listed items.
The terms referred to in this application will first be introduced and explained:
emission window: a suitable time frame to allow rocket launch.
Satellite descent intersection point local time: and during the flight from the north pole to the south pole of the satellite, when the equator is crossed, the local time of the geographic position corresponding to the subsatellite point.
Local time of descending intersection point at the time of track entering: and when the theoretical satellite descending point place is calculated according to the state parameters of the satellite orbit entering time, the theoretical satellite descending point place is also called as the satellite and rocket separation time descending point place.
SSO orbit: the orbit plane and the sun always keep a satellite orbit with a relatively fixed orientation; it can also be described as an artificial earth satellite orbit whose orbital plane precession direction is substantially the same as the earth's revolution direction, and whose precession angular rate is equal to the earth's revolution average angular rate; it can also be described as being able to guarantee that the satellite is passing over the local overhead orbit at the same latitude in the same direction every day.
Sun synchronous satellite: an artificial earth satellite having an orbit of SSO.
J2 perturbation: perturbation effect caused by ellipsoidal oblateness caused by earth rotation, namely the first order effect of earth gravitational field.
The inventor of the present application has studied and found that the earth atmosphere is observed in a fixed place by a satellite in an SSO orbit, and the satellite has a relatively fixed illumination condition, which is very advantageous for most of long-life remote sensing satellites using a solar cell as a power source or with a visible light remote sensor, and is very convenient for obtaining available data, receiving data, calculating an orbit, and the like. The artificial earth satellites used at present, such as photo reconnaissance satellites, meteorological satellites and resource satellites, are mostly SSO orbits.
For a solar synchronous satellite whose target orbit is an SSO orbit, the position of the satellite with respect to the sun is almost unchanged, and the local time when the satellite passes through a descent intersection point is generally used as an important parameter of the solar synchronous orbit, which is called a descent intersection point local time. Once the position of the descending intersection point of the satellite is determined, the irradiation relation between sunlight and the satellite is basically determined, which is significant for the design and research of the sun synchronous satellite, the on-orbit execution task and the like.
The following describes the technical solutions of the present application and how to solve the above technical problems with specific embodiments.
The embodiment of the application provides a method for determining a launch window of a launch vehicle, as shown in fig. 1, the method comprises the following steps:
s101, acquiring the local time of the landing point at the time of the orbit entering of the satellite, the geographical longitude of the landing point at the time of the orbit entering, the geographical longitude of the time zone used by the launching point, the allowable deviation value of the local time of the landing point at the time of the orbit entering, and the theoretical flight time deviation of the carrier rocket.
The local time of the point of intersection falling at the time of the orbit entering and the allowable deviation value thereof in the embodiment of the application can be determined according to the specific requirements of the satellite party, the local time of the point of intersection falling at the time of the orbit entering can be called as the local time of the point of intersection falling required by a user, and the allowable deviation value of the local time of the point of intersection falling at the time of the orbit entering can be called as the allowable deviation range of the user.
The geographical longitude of the touchdown point in the embodiment of the application refers to the longitude of the geographical position corresponding to the touchdown point of the satellite.
The geographical longitude of the time zone used by the transmitting point in the embodiment of the application refers to the longitude of the geographical position corresponding to the standard time point of the time zone used by the transmitting point; for example, if the time zone used for the launch point of the launch vehicle is the east-eight region, the standard time in the east-eight region is the time at 120 ° (degrees) from east, and the geographic longitude of the time zone used for the launch point is 120 ° from east.
S102, determining the geographical time difference between the descending intersection point and the transmitting point of the satellite at the time of the orbit according to the geographical longitude of the descending intersection point and the geographical longitude of the time zone used by the transmitting point at the time of the orbit.
Alternatively, the geographical time difference may be determined by:
expression (1)
In the expression (1), DT is the required geographic time difference; l is the geographical longitude of the time zone used for the point of emission, e.g., 120 °; l is0Descending intersection point geographical longitude at the time of track entry;7.292115e-5 (7.292115 multiplied by 10 to the minus 5 th power), in rad/s (revolutions per second) for earth rotational angular velocity; DT is the geographical time difference in units of s (seconds), and the magnitude of the value represents the absolute time difference.
The positive or negative of each value in expression (1) can be set according to the division of the time zones, for example, the east longitude value is set to positive.
S103, determining the relative time range of launch and flight of the carrier rocket according to the theoretical flight time and the theoretical flight time deviation.
Optionally, determining a first boundary value of the relative time range from the theoretical time of flight and a first deviation value of the deviation of the theoretical time of flight; determining a second boundary value of the relative time range according to the theoretical time of flight and a second deviation value of the deviation of the theoretical time of flight; the second deviation value is greater than the first deviation value; a relative time range is determined based on the first boundary value and the second boundary value.
Alternatively, the relative time range is embodied as the time range from the firing to the satellite being put into orbit.
In an alternative embodiment, the first boundary value of the relative time range may be determined by:
tfd = Tf0-Tf0d expression (2)
In expression (2), Tfd is a first boundary value of the relative time range, Tf0 is the theoretical time-of-flight, and Tf0d is a first deviation value in the theoretical time-of-flight deviation.
In an alternative embodiment, the second limit value for the relative time range may be determined by:
tfu = Tf0+ Tf0u expression (3)
In expression (3), Tfu is the second boundary value of the relative time range, Tf0 is the theoretical time-of-flight, and Tf0u is the second deviation value of the theoretical time-of-flight deviations.
And S104, determining a launching window of the carrier rocket according to the local time of the landing point at the track-in time, the geographical time difference, the relative time range and the allowed deviation value.
Optionally, determining a first allowable launching time of the carrier rocket according to the local time of the landing point at the track-entering time, the geographical time difference, the allowable deviation value and the first boundary value; determining a second allowable launching time of the carrier rocket according to the local time of the landing point at the track-entering time, the geographical time difference, the allowable deviation value and a second boundary value; a transmission window is determined based on the first allowed transmission time instant and the second allowed transmission time instant.
In an alternative embodiment, the first allowable launch time of the launch vehicle may be determined by:
twind = Tw0-DT + Tfd-Tw/2 expression (4)
In expression (4), Twind is the first allowable launch time of the launch vehicle, Tw0 is the acquired point where the.
In an alternative embodiment, the second allowable launch time of the launch vehicle may be determined by:
twinu = Tw0-DT + Tfu + Tw/2 expression (5)
In expression (5), Twinu is the second allowable launch time of the launch vehicle, Tw0 is the obtained time when the landing point is located at the time of the entry (i.e. when the user requires the landing point), Tw is the allowable deviation value (i.e. the allowable deviation range of the user) when the landing point is located at the time of the entry, and the remaining parameters are the same as the above expressions.
Twind and Twinu are respectively a lower limit value and an upper limit value of a launching window of the carrier rocket, and a time range between Twind and Twinu is the launching window of the carrier rocket.
In an alternative embodiment, if the theoretical flight time deviation and the allowable deviation value at the point of landing at the time of the orbit entry in expressions (2) to (5) are ignored, a certain time can be obtained as the allowable standard launching time of the launch vehicle.
Optionally, as shown in fig. 2, the method for determining a launch window of a launch vehicle provided in the embodiment of the present application further includes the following steps:
s201, acquiring target orbit parameters and J2 perturbation parameters of the satellite.
Optionally, the target trajectory parameters include: a target track semi-major axis, a target track eccentricity, and a target track inclination.
Optionally, the J2 perturbation parameter is specifically a J2 perturbation constant.
And S202, determining the launching window interval time of the carrier rocket according to the target orbit parameter and the J2 perturbation parameter.
Alternatively, considering only the effect of J2 perturbation, the launch window interval time of the launch vehicle may be determined as follows:
expression (6)
In the expression (6) above, the first,interval time for launch windows of the launch vehicle; t isweIs a sidereal day, 86164 s; j. the design is a square2Is J2 perturbation constant, 1.08263 e-3;Re6378.14e3 m (meters) for the equatorial radius of the earth;3.986005e 14;iis the target orbital inclination in rad (revolutions);ais a semi-major axis of a target track, and the unit is m;ethe target track eccentricity is taken.
Optionally, in step S101 and step S201, acquiring the time of the arrival time at the landing point place of the satellite, the geographic longitude of the arrival time at the landing point, the geographic longitude of the time zone used by the launch point, the allowable deviation value of the time of the arrival time at the landing point place of the satellite, and the theoretical flight time deviation of the launch vehicle, and acquiring the target orbit parameter and the J2 perturbation parameter of the satellite, includes:
displaying input frames of local time of the landing point at the time of the track entry, geographical longitude of a time zone used by a launching point, an allowed deviation value, theoretical flight time, deviation of the theoretical flight time and target orbit parameters in the same display interface; responding to input operation aiming at each input box, and acquiring local time of the landing point at the track-in time, geographical longitude of a time zone used by a launching point, an allowed deviation value, theoretical flight time deviation and target orbit parameters; pre-stored J2 perturbation parameters were obtained.
Optionally, the method for determining a launch window of a launch vehicle provided in this embodiment of the present application further includes: and displaying at least one datum in the launching window and the launching window interval time of the carrier rocket in the same display interface.
The display interface of the emission window and the interval time (hereinafter referred to as a calculation result) of the emission window in the embodiment of the application and the display interface of the input box of each parameter in steps S101 and S201 may be the same interface or different interfaces.
Fig. 3 is a schematic diagram of an interface showing input boxes of input parameters and calculation results on the same interface, a user can input values of required parameters in the input boxes of at least one of the carrier rocket launch window calculation input parameter area and the carrier rocket launch window interval calculation input parameter area shown in fig. 3, data which is not input can be defaulted to 0, and in one example, the interface after inputting data is shown in fig. 4.
The user may display the calculated launch window and launch window interval time of the launch vehicle in the area of the launch window and window interval calculation result (beijing time) shown in fig. 3. in one example, if the calculation is performed based on the input parameters shown in fig. 4, the calculation result of the launch window and launch window interval time of the launch vehicle is shown in the area below fig. 5.
Referring to the example of fig. 4, after the parameters are input, the embodiment of the application may start the calculation of the launch window and the launch window interval of the launch vehicle by triggering (clicking or touching) an icon for starting the calculation in the oval frame, and the calculation of the launch window and the launch window interval of the launch vehicle is performed independently without mutual influence after the start.
Referring to the examples of fig. 3 to 5, the presentation interface of the embodiment of the present application may further present a calculation result of the standard emission time, and the icon for starting calculation of the presentation interface may also be used to start calculation of the standard emission time.
The format, dimension and the like of each input parameter and the calculation result can be preset according to actual requirements.
Based on the same inventive concept, an embodiment of the present application provides a device for determining a launch window of a launch vehicle, as shown in fig. 6, where the device 600 includes: a data acquisition module 601, a first time determination module 602, a second time determination module 603, and a transmission window determination module 604.
The data acquisition module 601 is configured to acquire the local time of the landing point at the time of the orbit entering of the satellite, the geographical longitude of the landing point at the time of the orbit entering, the geographical longitude of the time zone used by the launch point, the allowable deviation value of the local time of the landing point at the time of the orbit entering, and the theoretical flight time deviation of the launch vehicle.
The first time determining module 602 is configured to determine, according to the geographical longitude of the descent intersection point at the time of the orbit entry and the geographical longitude of the time zone used by the transmitting point, a geographical time difference between the descent intersection point and the transmitting point of the satellite at the time of the orbit entry.
And a second time determination module 603, configured to determine a relative time range of launch and flight of the launch vehicle according to the theoretical time of flight and the theoretical time of flight deviation.
And a launch window determining module 604, configured to determine a launch window of the launch vehicle according to the local time of the landing point at the time of the track entry, the geographic time difference, the relative time range, and the allowable deviation value.
Optionally, the second time determining module 603 is specifically configured to: determining a first boundary value of the relative time range according to the theoretical flight time and a first deviation value in the deviation of the theoretical flight time; determining a second boundary value of the relative time range according to the theoretical time of flight and a second deviation value of the deviation of the theoretical time of flight; the second deviation value is greater than the first deviation value; a relative time range is determined based on the first boundary value and the second boundary value.
Optionally, the transmission window determining module 604 is specifically configured to: determining a first allowable launching time of the carrier rocket according to the local time of the landing point at the track-entering time, the geographical time difference, the allowable deviation value and the first boundary value; determining a second allowable launching time of the carrier rocket according to the local time of the landing point at the track-entering time, the geographical time difference, the allowable deviation value and a second boundary value; a transmission window is determined based on the first allowed transmission time instant and the second allowed transmission time instant.
Optionally, the data obtaining module 601 is further configured to: target orbit parameters and J2 perturbation parameters of the satellites are acquired.
Optionally, the apparatus for determining a launch window of a launch vehicle provided in this application further includes: and a window interval determination module.
The window interval determination module is to: and determining the interval time of the launching windows of the carrier rocket according to the target orbit parameters and the J2 perturbation parameters.
Optionally, the data obtaining module 601 is specifically configured to: displaying input frames of local time of the landing point at the time of the track entry, geographical longitude of a time zone used by a launching point, an allowed deviation value, theoretical flight time, deviation of the theoretical flight time and target orbit parameters in the same display interface; responding to input operation aiming at each input box, and acquiring local time of the landing point at the track-in time, geographical longitude of a time zone used by a launching point, an allowed deviation value, theoretical flight time deviation and target orbit parameters; pre-stored J2 perturbation parameters were obtained.
Optionally, the apparatus for determining a launch window of a launch vehicle provided in this application further includes: and a display module.
The display module is used for: and displaying at least one datum of the launching window, the standard launching moment and the launching window interval time of the carrier rocket in the same display interface.
The determining apparatus 600 of the launch window of the launch vehicle of this embodiment may execute any determining method of the launch window of the launch vehicle provided in this embodiment of the application, and the implementation principles thereof are similar, and the content not shown in detail in this embodiment may refer to the foregoing method embodiment, and will not be described again here.
Based on the same inventive concept, the embodiment of the application provides a device for determining a launch window of a launch vehicle, which comprises: the storage and the processor are electrically connected.
The memory has stored thereon a computer program that is executed by the processor to implement the method for determining a launch window of any launch vehicle provided by the embodiments of the present application.
Those skilled in the art will appreciate that the launch window determining apparatus of the launch vehicle provided in the embodiments of the present application may be specially designed and constructed for the required purposes, or may comprise known apparatus found in general purpose computers. These devices have stored therein computer programs that are selectively activated or reconfigured. Such a computer program may be stored in a device (e.g., computer) readable medium or in any type of medium suitable for storing electronic instructions and respectively coupled to a bus.
The present application provides in an alternative embodiment a launch window determination apparatus for a launch vehicle, as shown in fig. 7, the determination apparatus 700 comprising: the memory 701 and the processor 702 are electrically connected, such as by a bus 703.
Optionally, the memory 701 is used for storing application program codes for executing the scheme of the present application, and the processor 702 controls the execution. The processor 702 is configured to execute application program code stored in the memory 701 to implement any of the methods for determining a launch window of a launch vehicle provided by embodiments of the present application.
The Memory 701 may be a ROM (Read-Only Memory) or other type of static storage device that can store static information and instructions, a RAM (Random Access Memory) or other type of dynamic storage device that can store information and instructions, an EEPROM (Electrically Erasable Programmable Read Only Memory), a CD-ROM (Compact Disc Read-Only Memory) or other optical disk storage, optical disk storage (including Compact Disc, laser Disc, optical Disc, digital versatile Disc, blu-ray Disc, etc.), a magnetic disk storage medium or other magnetic storage device, or any other medium that can be used to carry or store desired program code in the form of instructions or data structures and that can be accessed by a computer, but is not limited to these.
The Processor 702 may be a CPU (Central Processing Unit), a general-purpose Processor, a DSP (Digital Signal Processor), an ASIC (Application Specific Integrated Circuit), an FPGA (Field-Programmable Gate Array), or other Programmable logic device, transistor logic device, hardware component, or any combination thereof. Which may implement or perform the various illustrative logical blocks, modules, and circuits described in connection with the disclosure. The processor 702 may also be a combination of computing functions, e.g., comprising one or more microprocessors, DSPs, and microprocessors, among others.
Bus 703 may include a path that transfers information between the above components. The bus may be a PCI (Peripheral Component Interconnect) bus or an EISA (Extended Industry Standard Architecture) bus. The bus may be divided into an address bus, a data bus, a control bus, etc. For ease of illustration, only one thick line is shown in FIG. 7, but this is not intended to represent only one bus or type of bus.
Optionally, the launch vehicle launch window determining apparatus 700 may further include a transceiver 704. The transceiver 704 may be used for reception and transmission of signals. The transceiver 704 may allow the electronic device 700 to communicate wirelessly or wiredly with other devices to exchange data. It should be noted that the transceiver 704 is not limited to one in practical applications.
Optionally, the determination device 700 of the launch window of the launch vehicle may further comprise an input unit 705. The input unit 705 may be used to receive input numeric, character, image, and/or sound information or to generate key signal inputs related to user settings and function control of the electronic apparatus 700. The input unit 705 may include, but is not limited to, one or more of a touch screen, a physical keyboard, function keys (such as volume control keys, switch keys, etc.), a trackball, a mouse, a joystick, a camera, a microphone, and the like.
Optionally, the apparatus 700 for determining a launch window of a launch vehicle may further comprise an output unit 706. The output unit 706 may be used to output or display information processed by the processor 702. The output unit 706 may include, but is not limited to, one or more of a display device, a speaker, a vibration device, and the like.
While FIG. 7 illustrates a launch vehicle launch window determination apparatus 700 having various means, it is to be understood that not all of the illustrated means are required to be implemented or provided. More or fewer devices may alternatively be implemented or provided.
Based on the same inventive concept, the embodiments of the present application provide a computer-readable storage medium having a computer program stored thereon, where the computer program, when executed by a processor, implements any one of the determination methods of the launch window of a launch vehicle provided by the embodiments of the present application.
The computer readable medium includes, but is not limited to, any type of disk including floppy disks, hard disks, optical disks, CD-ROMs, and magneto-optical disks, ROMs, RAMs, EPROMs (Erasable Programmable Read-Only Memory), EEPROMs, flash Memory, magnetic cards, or fiber optic cards. That is, a readable medium includes any medium that stores or transmits information in a form readable by a device (e.g., a computer).
The embodiments of the present application provide a computer-readable storage medium suitable for any determination of the launch window of the launch vehicle, which is not described herein again.
By applying the technical scheme of the embodiment of the application, at least the following beneficial effects can be realized:
1) according to the method and the device, the geographical longitude of the landing point at the time of the entry point is used as the constraint condition of the rocket launching window, the geographical longitude of the time zone used by the launching point, the allowed deviation value of the landing point at the time of the entry point and the theoretical flight time deviation of the carrier rocket are combined, the launching window of the carrier rocket can be determined, the method and the device can be applied to SSO orbit satellite launching tasks, the calculation method is simple, the program running speed is high, the calculation result is reliable, and meanwhile the blank that the rocket launching window cannot be determined based on the constraint of the landing point is filled.
2) The time of the arrival time landing point and the allowable deviation value thereof in the embodiment of the application are usually from a load side, namely a satellite side.
3) On the basis of calculating the transmitting window, the transmitting window interval time meeting the precision requirement can be quickly solved according to fewer target orbit parameters on the premise of only considering J2 perturbation, so that the satellite party can conveniently select the transmitting window, and when the satellite party misses the current transmitting window, other transmitting windows can be selected for transmitting according to the self requirement based on the transmitting window interval time, so that the selectivity of the transmitting opportunity and the practicability of the calculating program of the embodiment of the application are greatly improved; meanwhile, the algorithm is simple.
4) The technical scheme of the embodiment of the application is verified by the actual launching task, and the method is proved to be reliable in calculation process, less in dependence condition, accurate and reliable in calculation result, and the calculation time-consuming statistical results in the actual task are all less than or equal to 1 s.
Those of skill in the art will appreciate that the various operations, methods, steps in the processes, acts, or solutions discussed in this application can be interchanged, modified, combined, or eliminated. Further, other steps, measures, or schemes in various operations, methods, or flows that have been discussed in this application can be alternated, altered, rearranged, broken down, combined, or deleted. Further, steps, measures, schemes in the prior art having various operations, methods, procedures disclosed in the present application may also be alternated, modified, rearranged, decomposed, combined, or deleted.
In the description of the present application, it is to be understood that the terms "first", "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implying any number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present application, "a plurality" means two or more unless otherwise specified.
It should be understood that, although the steps in the flowcharts of the figures are shown in order as indicated by the arrows, the steps are not necessarily performed in order as indicated by the arrows. The steps are not performed in the exact order shown and may be performed in other orders unless explicitly stated herein. Moreover, at least a portion of the steps in the flow chart of the figure may include multiple sub-steps or multiple stages, which are not necessarily performed at the same time, but may be performed at different times, which are not necessarily performed in sequence, but may be performed alternately or alternately with other steps or at least a portion of the sub-steps or stages of other steps.
The foregoing is only a partial embodiment of the present application, and it should be noted that, for those skilled in the art, several modifications and decorations can be made without departing from the principle of the present application, and these modifications and decorations should also be regarded as the protection scope of the present application.