阅读说明：本技术 组合体测控覆盖区域拓展方法 (Method for expanding measurement and control coverage area of assembly ) 是由 潘瑞雪 陈占胜 张国升 杨琳 扈宗鑫 杜一凡 于 2021-09-10 设计创作，主要内容包括：本发明提供一种组合体测控覆盖区域拓展方法,包括第一卫星和第二卫星,所述第一卫星和第二卫星具备独立的在轨测控覆盖能力,通过多种关联参数联合设计,得到卫星在星上大部件收拢状态的组合一体状态下进行覆盖区域补偿,得到组合体和独立两星各任务阶段的测控天线覆盖区域；所述方法包括如下步骤：步骤S1：根据第一卫星和第二卫星在轨运行测控覆盖要求设定独立的测控天线覆盖；步骤S2：选择一颗卫星测控覆盖进行波束拓展；步骤S3：对第二颗卫星的测控进行改善,拓展第一卫星覆盖下的不足。本发明面向双星组合入轨、分离独立运行的特定应用条件,拓展组合体转移测控可达范围,提高卫星姿态异常下测控可用性；有效拓展组合体的测控覆盖范围。(The invention provides a method for expanding a combined measurement and control coverage area, which comprises a first satellite and a second satellite, wherein the first satellite and the second satellite have independent on-orbit measurement and control coverage capacity, and coverage area compensation is carried out on the satellites in a combined integrated state of a large part of on-board components in a folded state through combined design of multiple associated parameters to obtain the coverage areas of measurement and control antennas of each task stage of a combined body and two independent satellites; the method comprises the following steps: step S1: setting independent measurement and control antenna coverage according to the measurement and control coverage requirements of the first satellite and the second satellite in orbit operation; step S2: selecting a satellite measurement and control coverage for beam expansion; step S3: the measurement and control of the second satellite are improved, and the defect under the coverage of the first satellite is expanded. The invention expands the reachable range of transfer measurement and control of the assembly and improves the measurement and control availability under abnormal satellite attitude for specific application conditions of dual-satellite combination orbit entering and separated independent operation; the measurement and control coverage range of the assembly is effectively expanded.)

1. A method for expanding a combined measurement and control coverage area is characterized by comprising a first satellite and a second satellite, wherein the first satellite and the second satellite have independent on-orbit measurement and control coverage capacity, and coverage area compensation is carried out on the satellites in a combined integrated state of a large part of on-board components in a folded state through combined design of multiple associated parameters, so that the coverage areas of measurement and control antennas of each task stage of the combined body and two independent satellites are obtained; the method comprises the following steps:

step S1: setting independent measurement and control antenna coverage according to the measurement and control coverage requirements of the first satellite and the second satellite in orbit operation;

step S2: selecting a satellite measurement and control coverage for beam expansion;

step S3: the measurement and control of the second satellite are improved, and the defect under the coverage of the first satellite is expanded.

2. The method for expanding the measurement and control coverage area of the combined unit according to claim 1, wherein the independent in-orbit measurement and control coverage capabilities of the first satellite and the second satellite comprise measurement and control antenna coverage under quasi-omnidirectional satellite measurement and control coverage and attitude control constraints.

3. The method for expanding the measurement and control coverage area of the assembly according to claim 1, wherein the solar sailboard integrated by the first satellite and the second satellite is in an unfolded state when the on-board antenna is in a folded state, and the rest large on-board components are in a folded state.

4. The method for expanding measurement and control coverage areas of an assembly according to claim 1, wherein the step S2 selects a satellite to expand the task measurement and control coverage angle and the antenna gain with continuity by using a space-to-ground power division ratio, an asymmetric space-to-ground beam angle, and the like.

5. The method for expanding the measurement and control coverage area of the assembly according to claim 1, wherein the coverage area of the satellite in the step S2 serving as the measurement and control antenna of the assembly meets more than 80% of application requirements of the assembly.

6. The method for expanding the measurement and control coverage area of the combined body according to claim 1, wherein the first satellite and the second satellite have different tasks in a stationary orbit, and when the satellites take off, a compressed state exists, and most of the components expand after being in orbit to directly influence the beam gain and the available angle of the measurement and control antenna.

7. The method for expanding the measurement and control coverage area of the assembly according to claim 6, wherein the coverage areas of the first satellite and the second satellite measurement and control antennas are required to simultaneously meet measurement and control requirements under various attitudes of transfer into orbit under the assembly and measurement and control requirements under various attitude conditions of independent operation of the satellite after normal expansion of in-orbit equipment.

8. The method according to claim 1, wherein the measurement and control coverage area of the second satellite is included in the coverage area of the emergency measurement and control directional diagram of the combined body during the transfer of the combined body into the orbit.

9. The method for expanding the measurement and control coverage area of the combined body according to claim 1, wherein the first satellite and the second satellite enter a stationary orbit, and three measurement and control coverage states exist, wherein the first satellite and the second satellite are combined into a whole and the first satellite and the second satellite are independent.

10. The method for expanding the measurement and control coverage area of the combined body according to claim 1, wherein after the first satellite and the second satellite are combined into a whole, the two-satellite measurement and control directional diagram is shielded by the other satellite.

Technical Field

The invention relates to the technical field of satellite measurement and control subsystem design, in particular to a method for expanding a measurement and control coverage area of an assembly.

Background

The directional diagram of the conventional satellite measurement and control subsystem mainly covers quasi-omni-directionally, and the task direction is ensured to be far away from the interference area of the combined directional diagram of the sky and the ground as far as possible. The measurement and control directional diagram in the dual-satellite combination state generally takes the measurement and control directional diagram of the master control satellite as a main point, and other satellites are in measurement and control silent states.

Patent document No. CN102544750B discloses a method for manufacturing a large-angle attitude mobile satellite measurement and control antenna, which includes the following steps: 1. adjusting the beam width of the antenna; 2. feeding the unequal amplitude signals; 3. pressing a combined radiation interference area; 4. simulation verification; 5. simulation analysis; 6. and (5) testing the star loading state.

In the related art, it is described that for measuring and controlling antenna adjustment parameters, power of unequal amplitude signals, and suppressing a combined radiation interference area, the interference area is suppressed to a sky space, and a measurement and control coverage area is narrow, so a technical scheme needs to be provided to improve the technical problem.

Disclosure of Invention

Aiming at the defects in the prior art, the invention aims to provide a method for expanding a combined measurement and control coverage area.

The invention provides a combined measurement and control coverage area expanding method which comprises a first satellite and a second satellite, wherein the first satellite and the second satellite have independent on-orbit measurement and control coverage capacity, and coverage area compensation is carried out on the satellites in a combined integrated state of a large part of on-board components in a folded state through combined design of multiple associated parameters to obtain measurement and control antenna coverage areas of each task stage of a combined body and two independent satellites; the method comprises the following steps:

step S1: setting independent measurement and control antenna coverage according to the measurement and control coverage requirements of the first satellite and the second satellite in orbit operation;

step S2: selecting a satellite measurement and control coverage for beam expansion;

step S3: the measurement and control of the second satellite are improved, and the defect under the coverage of the first satellite is expanded.

Preferably, the independent in-orbit measurement and control coverage capabilities of the first satellite and the second satellite comprise measurement and control antenna coverage ranges under quasi-omnidirectional satellite measurement and control coverage and attitude control constraints.

Preferably, the solar sailboard integrated by the first satellite and the second satellite is in an unfolded state when the on-satellite antenna is in a folded state, and the rest large on-satellite components are in a folded state.

Preferably, in step S2, a satellite is selected to expand the task measurement and control coverage angle and the antenna gain with continuity by using methods such as a space-ground power division ratio and an asymmetric space-ground beam angle.

Preferably, the satellite in step S2 is used as an assembly measurement and control antenna coverage area, and meets more than 80% of the application requirements of the assembly.

Preferably, the tasks of the first satellite and the second satellite in the stationary orbit are different, and the beam gain and the usable angle of the measurement and control antenna are directly influenced by the fact that the first satellite and the second satellite are expanded after being inserted into the orbit in a compressed state when the satellite takes off.

Preferably, the coverage areas of the first satellite measurement and control antenna and the second satellite measurement and control antenna need to simultaneously meet measurement and control requirements under various postures of transferring into orbit under the combination and measurement and control requirements under various posture conditions of independent operation of each device in orbit of the satellite after normal expansion.

Preferably, the measurement and control coverage range of the second satellite is included in the coverage range of the emergency measurement and control directional diagram of the combined body during the transfer process of the combined body into the orbit.

Preferably, the first satellite and the second satellite enter a stationary orbit, and three measurement and control coverage states exist, wherein the first satellite and the second satellite are combined into a whole and are independent from the first satellite and the second satellite.

Preferably, after the first satellite and the second satellite are combined into a whole, the two-satellite measurement and control directional diagram is shielded by the other satellite.

Compared with the prior art, the invention has the following beneficial effects:

1. the invention expands the reachable range of transfer measurement and control of the assembly and improves the measurement and control availability under abnormal satellite attitude for specific application conditions of dual-satellite combination orbit entering and separated independent operation;

2. the invention effectively expands the measurement and control coverage range of the assembly and meets the measurement and control coverage requirements under the conditions of normal state and abnormal posture of the transfer section; the two-star measurement and control system is fully adjusted, and the measurement and control robustness of the transfer track section assembly is improved;

3. the invention greatly improves the ground measurable and controllable duration of the assembly under the condition of abnormal track posture, and provides valuable time for ground intervention.

Drawings

Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:

FIG. 1 is a schematic diagram of the independent operation of the star patterns of the present invention;

FIG. 2 is a schematic diagram of a region of a first satellite under the dual satellite combination shielded by a second satellite directional diagram according to the present invention;

fig. 3 is a schematic diagram of the coverage expansion of the dual-star measurement and control system.

Detailed Description

The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.

The patent provides a method for expanding a measurement and control coverage range to complete a multi-stage satellite measurement and control task under a two-satellite combination state. The two independently operating GEO satellites have independent measurement and control coverage ranges. When the two stars are combined into a whole, the reach range of the measurement and control antennas is affected. In the two-satellite combined integrated orbit transfer task, a method for expanding the beam range of a main task A satellite to the ground, compressing the beam to the sky, obliquely installing an antenna to the ground, redistributing the power to the sky and the ground and the like is used for avoiding the shielding area of a transfer section of the assembly, and a method for expanding the measurement and control reachable range of the assembly by utilizing the beam range compensation of a slave task B satellite is used.

A method for expanding a combined measurement and control coverage area is characterized in that two satellites have independent on-orbit measurement and control coverage capacity, and coverage area compensation of the satellites is realized under the combined and integrated state that antennas on the satellites are folded through combined design of multiple associated parameters, so that the measurement and control antenna coverage area of each task stage is obtained. The method mainly comprises the following steps:

step S1: setting independent measurement and control antenna coverage according to the measurement and control coverage requirement of the on-orbit operation of two stars; step S2: selecting a small shielded satellite measurement and control coverage to expand wave beams, wherein the small shielded satellite measurement and control coverage is used as the coverage range of a main measurement and control antenna of the assembly, and the application requirements of the assembly of more than 80% are met; step S3: the measurement and control of the second satellite are improved in a targeted manner, the method is used for expanding insufficient points covered by the satellite A and improving the measurement and control availability under the abnormal satellite attitude.

The two-star independent on-orbit measurement and control coverage capability is accurate to omnidirectional satellite measurement and control coverage, and can also be the measurement and control antenna coverage under attitude control constraint. The measurement and control coverage areas of the two satellites can be the same or different.

The two stars are combined into a whole under the folding state of the on-board antenna, except that the solar sailboard is unfolded, other on-board large components are in the folding state so as to reduce the influence on the coverage area of the new measurement and control antenna.

And (4) multiple associated parameter joint design is mainly used for step S2, the first measurement and control coverage uncertainty under the cruise attitude, the measurement and control coverage range of the far-spot ignition attitude to measurement and control, the measurement and control coverage angle lost in the two-satellite joint state and other constraints, and a satellite is selected to expand the task measurement and control coverage angle and the antenna gain with continuity by methods of a space-to-ground power division ratio, an asymmetric space-to-ground beam angle and the like.

The coverage areas of the measurement and control antennas at each task stage are different in the tasks of two satellites in a static orbit, and when the satellites take off, a compressed state exists, most of the devices expand after being in orbit, and beam gain and available angles of the measurement and control antennas can be directly influenced, so that the coverage areas of the two-satellite measurement and control antennas need to meet measurement and control requirements under various postures of transfer into orbit under combination and under various posture conditions of independent operation of the devices in orbit of the satellites after being normally expanded.

The invention mainly uses the measurement and control coverage area formed by combining two satellites, adopts the ways of oblique antenna installation, high ground power distribution, narrowing the beam angle of a sky antenna and the like to form a main task A satellite, and meets the requirements of on-orbit application and the measurement and control coverage of a transfer section on the ground. Meanwhile, according to the coverage requirement of the on-orbit measurement and control antenna of the satellite B, the interference area after the satellite A is adjusted and the area shielded by the satellite B are made up in a targeted manner, new measurement and control coverage of the double-satellite assembly is formed, the transfer measurement and control reachable range of the assembly is expanded, and the measurement and control availability under the condition of satellite attitude abnormality is improved.

Two satellites which need to enter a static orbit together have three measurement and control coverage states of double-satellite combination and two-satellite independence.

The invention mainly aims at the satellites with independent GEO on-orbit measurement and control coverage of two satellites, and effectively expands the measurement and control coverage range of the assembly by the following design method under the assembly state, thereby meeting the measurement and control coverage requirements under the conditions of normal state and abnormal posture of a transfer section. The two-star measurement and control system is fully adjusted, and the measurement and control robustness of the transfer track section assembly is improved.

In the process of transferring the combination body into the orbit, the measurement and control coverage range of the slave task star B is brought into the coverage range of the emergency measurement and control directional diagram of the combination body, so that the ground measurement and control duration of the combination body under the abnormal orbit attitude is greatly prolonged, and valuable time is provided for ground intervention.

The combination body is composed of an A star and a B star, and the A star and the B star measurement and control system are both quasi-omnidirectional coverage. When the requirement of the two-star geosynchronous orbit is met, the two-star measurement and control beam distribution is shown in figure 1. After the two satellites are combined into a whole, the measurement and control directional diagram of each satellite is shielded by the other satellite, and fig. 2 exemplifies that in the combined state, after the A satellite is shielded by the B satellite, the usable and unusable beam ranges of the directional diagram are synthesized. Similarly, the measurement and control directional diagram of the B star is also shielded by the A star. The shielded directional diagram cannot meet the satellite measurement and control coverage of each attitude of the transfer orbit section.

Firstly, selecting the A star as a main task star of a transfer section, expanding the A star earth measurement and control antenna beam to +/-90 degrees from +/-75 degrees, reducing the earth measurement and control antenna beam to +/-45 degrees from +/-75 degrees, and after the earth measurement and control antenna is obliquely installed and the like in consideration of the earth coverage of the transfer section and the on-orbit, the beam coverage of the A star can meet the requirements of most measurement and control tasks of the A star on-orbit and AB assembly transfer section to form a main beam A1 and a safety beam A2,

and secondly, adjusting the measurement and control coverage of the satellite B to make up the blind area and the interference area of the current measurement and control antenna of the satellite A, and forming combined supplementary beams B1 and B2 as shown in figure 3.

Even if the part of the measurement and control antenna of the satellite A is still shielded by the satellite B, the measurement and control directional diagram of the satellite B is covered, the data of the above ground notes can be given to the satellite A for processing, and the purpose of expanding the range of the assembly is achieved.

The invention expands the reachable range of transfer measurement and control of the assembly and improves the measurement and control availability under abnormal satellite attitude for specific application conditions of dual-satellite combination orbit entering and separated independent operation; the measurement and control coverage range of the assembly is effectively expanded, and the measurement and control coverage requirements under the conditions of normal state and abnormal posture of the transfer section are met; the two-star measurement and control system is fully adjusted, and the measurement and control robustness of the transfer track section assembly is improved; the ground measurable and controllable duration of the combined body under the abnormal track posture is greatly improved, and valuable time is provided for ground intervention.

Those skilled in the art will appreciate that, in addition to implementing the system and its various devices, modules, units provided by the present invention as pure computer readable program code, the system and its various devices, modules, units provided by the present invention can be fully implemented by logically programming method steps in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers and the like. Therefore, the system and various devices, modules and units thereof provided by the invention can be regarded as a hardware component, and the devices, modules and units included in the system for realizing various functions can also be regarded as structures in the hardware component; means, modules, units for performing the various functions may also be regarded as structures within both software modules and hardware components for performing the method.

The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.