CN114969972B - Method for establishing satellite on-orbit management situation model based on single-satellite working mode - Google Patents
Method for establishing satellite on-orbit management situation model based on single-satellite working mode Download PDFInfo
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Abstract
The invention provides a method for establishing a satellite management situation model based on a single-satellite working mode, which comprises the following steps: 1) An on-orbit satellite management situation working mode is represented; 2) Element representation of the in-orbit satellite management mode; 3) Establishing an on-orbit satellite management situation mode; 4) And (5) establishing a satellite management situation model. The method realizes the establishment of the satellite management situation model through three steps of the establishment of the in-orbit satellite management mode, the establishment of the satellite situation attribute set and the design of the satellite situation management model.
Description
Technical Field
The invention belongs to the field of aerospace measurement and control, and particularly relates to a method for establishing an on-orbit satellite management situation model based on a single-satellite working mode.
Background
The increasing number of in-orbit satellites in China, and the future large-scale constellations and the appearance of a large number of satellites provide new challenges for in-orbit satellite management. Systems relying on manual data auditing or semi-automatic data processing auditing have failed to meet the need for management of a large number of satellites.
At present, each in-orbit satellite management unit mainly relies on automatic scheduling software, data processing platform, monitoring software, fault diagnosis software and other self-research software to manage satellites, so that more manpower and energy are spent, and management is needed by increasing personnel and equipment along with the increase of the number of satellites. Even so, heavy work tasks occur, which affect the management quality and benefit. Therefore, there is an urgent need for new integration and rational planning in the management method.
Disclosure of Invention
In order to overcome the defects of the existing management mode, the invention provides a method for establishing a satellite management situation model based on a single-satellite working mode.
The technical scheme of the invention is as follows: the invention relates to a method for establishing a satellite management situation model based on a single-star working mode, which is characterized by comprising the following steps: the method comprises the following steps:
1) An on-orbit satellite management situation working mode is represented;
2) Element representation of the in-orbit satellite management mode;
3) Establishing an on-orbit satellite management situation mode;
4) And (5) establishing a satellite management situation model.
Further, the specific steps of the step 1) are as follows: in the process of establishing a satellite management situation mode, a corresponding relation between situation characteristics and situation identification must be established: let the management situation pattern set be m= { G, F, D }, its elements are all situation classifications that may occur in the in-orbit satellite management, and the in-orbit satellite management situation elements are described in three layers: the first hierarchy is described in terms of satellite design as being divided into small satellites and large satellites, denoted by set D; the second level is that the description of satellite functions is divided into navigation, earth observation and communication and is represented by a set F; the third level is that the description of the satellite orbit is divided into a high orbit and a low orbit, which are represented by a set G; where g= { high orbit, low orbit } f= { navigation, remote sensing, communication }, d= { large satellite, small satellite }.
Advancing oneThe specific steps of the step 2) are as follows: and establishing elements under various management modes according to the in-orbit satellite management situation mode obtained in the step 1). The management situation pattern element is represented, and the pattern element at a certain time t is established as follows: s (t) = { P 1 (t),P 2 (t),...,P n (t) }, wherein P i (t) (i=1, 2,., n) represents a set of elements at a certain time: p (P) i = { health status, failure diagnosis, data transfer door on/off, fine orbit injection, business data injection, ground moon shadow management, ignition time, ignition duration, propellant use case }, satellite management situation pattern elements are elements that are needed and concerned in satellite management and affect on-orbit management security.
Further, in step 2), the in-orbit satellite management situation mode formed by the combination of step 1) has two properties of static property and dynamic property; the static characteristics comprise track type, attitude stability, platform health status and load on-off status; the dynamic characteristics comprise task completion, resource occupancy rate and timeliness.
Further, in step 2), the in-orbit satellite management situation pattern element set belongs to static characteristics and dynamic characteristics under each management situation pattern, wherein the static characteristics consist of two parts of general situation elements and special situation elements, the general situation pattern elements are frequent works required to be done in-orbit management, each day of work needs to be done, including orbit height, shape, inclination angle, satellite-borne point track, health state and fault diagnosis conditions of satellite design, data transmission gate on/off, business data injection, the special situation elements are those which have relatively low occurrence frequency and are required to be done in a specific time, such as ground-moon image management, whole satellite timing and the like; dynamic elements refer to satellite management situations driven by events (unscheduled), including orbital maneuver (ignition time, ignition duration and propellant use cases), collision avoidance, backup enablement, etc.; the dynamic characteristics include factors including task start time, end time and task time delay.
Further, the specific steps of the step 3) are as follows: according to the representation of the in-orbit satellite management situation mode in the step 2), the total characteristic set of the satellite management situation is represented by a set T { X, Y, Z }; the establishment process of the on-orbit satellite management situation mode is a one-to-one corresponding functional relation between a situation characteristic set and a situation mode set:
f:T→M
in this way, the goal of cognizing the management situation mode of the on-orbit satellite can be achieved.
Further, the specific steps of the step 4) are as follows: the establishment of an in-orbit satellite management situation model requires taking an event as traction, wherein the event refers to the execution of an orbit maneuver task or a direct instruction and the like; and 3) according to the satellite management situation mode established in the step 3), establishing an in-orbit satellite management situation by taking the events as traction.
In step 4), on the premise that an event occurs at a certain moment, the static characteristics of the satellite management situation mode are inspected, then the change of the situation static characteristics caused by time is analyzed, and finally the final on-orbit satellite management situation after the event occurs is obtained.
The method for establishing the satellite management situation model based on the single-satellite working mode is different from the traditional high-low orbit management mode, and is divided into different functions such as navigation, ground pair observation, communication and the like from the perspective of satellite functions (application), and the orbit characteristics of the high-low orbit satellites are fused, so that a new management mode of the in-orbit satellite is separated. The method comprises three aspects of an establishment method of an in-orbit satellite management mode, an attribute set establishment method of an in-orbit satellite management situation and model design of the in-orbit satellite management situation. And meanwhile, establishing an attribute set of the satellite management situation, wherein each separated management subset has a special attribute set on the basis of the whole set, and the special attribute consists of the sum or the union of the attribute sets contained in three aspects of satellite design, satellite application and satellite orbit. The method comprises the steps of establishing a satellite situation management model by taking a management event or a task event as traction, wherein the satellite situation management model consists of two parts, namely a satellite in-orbit management working mode and a satellite in-orbit management situation static element, and the satellite in-orbit management working mode is a set formed by meeting one element in each of three categories of satellite design, satellite function and satellite orbit; the static characteristic element of the satellite in-orbit management situation is a set consisting of a general element and a special element. When an event occurs, the situation working mode of satellite on-orbit management does not change, so that static characteristic elements of the satellite on-orbit management situation can be obtained by the situation working mode, and dynamic characteristic elements need to be obtained from the event always. Therefore, the invention has the beneficial effects that: the invention provides a method for establishing an on-orbit satellite management situation model based on a single-satellite working mode aiming at the fact that an on-orbit satellite management mode cannot meet the requirement of future large number of satellite management, and aims at the management mode characteristics of the current on-orbit satellite.
Drawings
FIG. 1 is a method framework of the present invention;
FIG. 2 is a schematic diagram of an in-orbit satellite management situation element according to the present invention;
FIG. 3 is a schematic representation of a satellite management situation mode of operation of the present invention;
FIG. 4 is a schematic diagram of an in-orbit satellite management situation model according to the present invention;
fig. 5 is a flow chart of the in-orbit satellite management situation model establishment of the present invention.
Detailed Description
The invention provides a satellite management situation model building method based on a single-star working mode, which comprises the following steps of:
1) An on-orbit satellite management situation working mode is represented;
in the process of establishing a satellite management situation mode, a corresponding relation between situation characteristics and situation identification must be established: let the management situation pattern set be m= { G, F, D }, its elements are all situation classifications that may occur in the in-orbit satellite management, and the in-orbit satellite management situation elements are described in three layers: the first hierarchy is described in terms of satellite design as being divided into small satellites and large satellites, denoted by set D; the second level is that the description of satellite functions is divided into navigation, earth observation and communication and is represented by a set F; the third level is that the description of the satellite orbit is divided into a high orbit and a low orbit, which are represented by a set G; where g= { high orbit, low orbit } f= { navigation, remote sensing, communication }, d= { large satellite, small satellite }.
2) Element representation of the in-orbit satellite management mode;
the specific steps of the step 2) are as follows: and establishing elements under various management modes according to the in-orbit satellite management situation mode obtained in the step 1). The management situation pattern element is represented, and the pattern element at a certain time t is established as follows: s (t) = { P 1 (t),P 2 (t),...,P n (t) }, wherein P i (t) (i=1, 2,., n) represents a set of elements at a certain time: p (P) i = { health status, failure diagnosis, data transfer door on/off, fine orbit injection, business data injection, ground moon shadow management, ignition time, ignition duration, propellant use case }, satellite management situation pattern elements are elements that are needed and concerned in satellite management and affect on-orbit management security.
The on-orbit satellite management situation mode formed by the combination of the step 1) has two properties of static properties and dynamic properties; the static characteristics comprise track type, attitude stability, platform health status and load on-off status; the dynamic characteristics comprise task completion, resource occupancy rate and timeliness.
The in-orbit satellite management situation pattern element set belongs to static characteristics and dynamic characteristics under each management situation pattern, wherein the static characteristics consist of general situation elements and special situation elements, the general situation pattern elements are frequent works required to be completed in the in-orbit management, each day of the work comprises orbit height, shape, inclination angle, satellite lower point track, health state and fault diagnosis conditions of satellite design, data transmission gate on/off and business data injection, and the special situation elements are those which have relatively low occurrence frequency and are required to be completed in certain specific time, such as ground and moon shadow management, whole satellite timing and the like; dynamic elements refer to satellite management situations driven by events (unscheduled), including orbital maneuver (ignition time, ignition duration and propellant use cases), collision avoidance, backup enablement, etc.; the dynamic characteristics include factors including task start time, end time and task time delay.
3) Establishing an on-orbit satellite management situation mode;
according to the representation of the in-orbit satellite management situation mode in the step 2), the total characteristic set of the satellite management situation is represented by a set T { X, Y, Z }; the establishment process of the on-orbit satellite management situation mode is a one-to-one corresponding functional relation between a situation characteristic set and a situation mode set:
f:T→M
in this way, the goal of cognizing the management situation mode of the on-orbit satellite can be achieved.
4) Building a satellite management situation model;
the establishment of an in-orbit satellite management situation model requires taking an event as traction, wherein the event refers to the execution of an orbit maneuver task or a direct instruction and the like; and 3) according to the satellite management situation mode established in the step 3), establishing an in-orbit satellite management situation by taking the events as traction.
The method is characterized in that the on-orbit satellite management situation is established on the premise that a certain event occurs at a certain moment, the static characteristics of the satellite management situation mode are inspected, then the change of the situation static characteristics caused by time is analyzed, and finally the final on-orbit satellite management situation after the event occurs is obtained.
The general aspects of the invention will be described in further detail below with reference to the attached drawings and to specific examples:
referring to fig. 1, the method of the present invention is as follows:
firstly, carrying out step 1-1) of representing an in-orbit satellite management situation mode, dividing the in-orbit satellite management situation mode into three layers, analyzing the satellite management situation mode from three layers of satellite design, satellite function and satellite orbit, and representing the in-orbit satellite management situation mode by a set.
And secondly, carrying out element representation of the in-orbit satellite management situation mode in the step 1-2), and decomposing out constituent elements of the two characteristics on the basis of analyzing the characteristics of the in-orbit satellite management situation mode.
And then establishing an on-orbit satellite management situation mode in the step 1-3), wherein the on-orbit satellite management situation mode is established through matching of the corresponding relation between the satellite management situation feature set and the situation mode.
And finally, establishing an in-orbit satellite management situation model in the steps 1-4), wherein the establishment of the model is required to be carried out under the drive of a task event, firstly, confirming the property of the event, splitting the event into a form of a simple instruction or a processable data block, managing the satellites in a form of uploading remote control instructions and remote control data, and the like, wherein each satellite can be managed by utilizing the steps, so that the in-orbit satellite management situation model is formed.
Referring to fig. 2, the satellite management situation element is first classified into two kinds of static characteristics and dynamic characteristics in terms of whether or not it is changed by an external event during the in-orbit management, the component elements of the static characteristics are composed of a general element that the satellite has in each satellite management situation mode, and two parts that are each distinguished from other specific elements, which are the minimum attribute or called non-subdividable attribute in the satellite management.
Referring to fig. 3, the in-orbit satellite management situation pattern is composed of static characteristics in the in-orbit satellite management operation pattern and the satellite management situation elements. In order to clearly describe the in-orbit satellite management situation mode, the in-orbit satellite management situation working mode is divided from three layers of satellite design requirements, satellite functions and satellite orbit types. Each satellite in the orbit satellite can find a corresponding working mode in each layer, and the combination of three different characteristics in three layers forms a specific working attribute in the satellite management situation and a static characteristic in the satellite management situation to form the satellite management situation mode. It does not change due to the in-orbit operation and control events of the satellite, and is therefore a unique management situation pattern that distinguishes the satellite from other types of satellites.
Referring to fig. 4, the management situation of the satellite is formed by combining the dynamic characteristics of the in-orbit satellite management situation and the satellite management situation mode, and the construction of the dynamic characteristics of the satellite is completed based on the static characteristics of the satellite management situation by taking an event as traction, so that the establishment of the in-orbit satellite management situation is completed.
Referring to fig. 5, the flow of satellite management situation establishment of the present invention is as follows.
Firstly, step 5-1) initializing satellite situation elements, external event information and the like; then, step 5-2) is carried out to determine special elements of the satellite management situation; then, carrying out the step 5-3) to determine the working mode of the satellite, then carrying out the step 5-4) to judge whether the external event affects the current satellite management situation, if so, carrying out the step 5-5) to generate a dynamic characteristic set of satellite management, and then carrying out the step 5-6) to form the satellite management situation; if steps 5-6) are not performed directly). The management situation of one satellite is formed up to this point, then step 5-7) is performed to determine whether there are any more satellites to form the in-orbit satellite management situation, if so, step 5-1) is performed, otherwise, step 5-6) is performed.
The technical matters not specifically described in the foregoing embodiments are the same as those in the prior art.
The above is only a specific embodiment disclosed in the present invention, but the scope of the present invention is not limited thereto, and the scope of the present invention should be defined by the claims.
Claims (4)
1. A method for establishing a satellite management situation model based on a single-star working mode is characterized by comprising the following steps: the method comprises the following steps:
1) An on-orbit satellite management situation working mode is represented;
the specific steps of the step 1) are as follows: in the process of establishing a satellite management situation mode, a corresponding relation between situation characteristics and situation identification must be established: let the management situation pattern set be m= { G, F, D }, its elements are all situation classifications that may occur in the in-orbit satellite management, and the in-orbit satellite management situation elements are described in three layers: the first hierarchy is described in terms of satellite design as being divided into small satellites and large satellites, denoted by set D; the second level is that the description of satellite functions is divided into navigation, earth observation and communication and is represented by a set F; the third level is that the description of the satellite orbit is divided into a high orbit and a low orbit, which are represented by a set G; wherein g= { high orbit, low orbit } f= { navigation, remote sensing, communication }, d= { large satellite, small satellite };
2) Element representation of the in-orbit satellite management mode;
according to the in-orbit satellite management situation mode obtained in the step 1), establishing elements under various management modes; the management situation pattern element is represented, and the pattern element at a certain time t is established as follows: s (t) = { P 1 (t),P 2 (t),...,P n (t) }, wherein P i (t) (i=1, 2,., n) represents a set of elements at a certain time: p (P) i = { health status, fault diagnosis, data transmission gate on/off, fine orbit injection, business data injection, ground moon shadow management, ignition time length, propellant use situation }, satellite management situation pattern elements are elements which are needed and concerned in satellite management and affect on-orbit management security;
3) Establishing an on-orbit satellite management situation mode;
the specific steps of the step 3) are as follows: according to the representation of the in-orbit satellite management situation mode in the step 2), the total characteristic set of the satellite management situation is represented by a set T { X, Y, Z }; the establishment process of the on-orbit satellite management situation mode is a one-to-one corresponding functional relation between a situation characteristic set and a situation mode set:
f:T→M
4) Building a satellite management situation model;
the specific steps of the step 4) are as follows: the establishment of an in-orbit satellite management situation model requires taking an event as traction, wherein the event refers to the execution of an orbit maneuver task or a direct instruction; and 3) according to the satellite management situation mode established in the step 3), establishing an in-orbit satellite management situation by taking the events as traction.
2. The method for establishing the satellite management situation model based on the single-star working mode according to claim 1, wherein the method comprises the following steps of: in the step 2), the in-orbit satellite management situation mode formed by combining the steps 1) has two properties of static properties and dynamic properties; the static characteristics comprise track type, attitude stability, platform health status and load on-off status; the dynamic characteristics comprise task completion, resource occupancy rate and timeliness.
3. The method for establishing the satellite management situation model based on the single-star working mode according to claim 2, wherein the method comprises the following steps of: in the step 2), the in-orbit satellite management situation mode element set belongs to static characteristics and dynamic characteristics under each management situation mode, wherein the static characteristics consist of general situation elements and special situation elements, the general situation mode elements are frequent works required to be done in-orbit management, each day of the work needs to be completed, the work comprises orbit height, shape, inclination angle, satellite-under-the-satellite point track, health state and fault diagnosis conditions of satellite design, data transmission gate on/off, service data injection, the special situation elements are those which have relatively low occurrence frequency and are required to be completed in a certain specific time, and the certain specific time is ground-moon shadow management and whole-satellite timing; dynamic elements refer to satellite management situations driven by unplanned events, including orbiting situations: ignition time, ignition duration and propellant service condition, collision avoidance, backup starting; the dynamic characteristics include factors including task start time, end time and task time delay.
4. A method for building a satellite management situation model based on a single-star mode of operation according to claim 3, wherein: in the step 4), the establishment of the in-orbit satellite management situation is that firstly, on the premise that a certain event occurs at a certain moment, the static characteristics of the satellite management situation mode are inspected, then the change of the situation static characteristics caused by the time is analyzed, and finally, the final in-orbit satellite management situation after the event occurs is obtained.
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