阅读说明：本技术 一种电离层探测小卫星网络规划方法 (Ionosphere detection small satellite network planning method ) 是由 徐彬 冯杰 吴健 朱庆林 李辉 马征征 张雅彬 刘瑶 梁勇敢 李海英 李统乐 于 2020-11-20 设计创作，主要内容包括：本发明公开了一种电离层探测小卫星网络规划方法,包括如下步骤：步骤1,小卫星基本参数设定；步骤2,单颗小卫星的覆盖能力计算；步骤3,轨道参数对覆盖能力影响分析；步骤4,确定小卫星星座数目和轨道参数；步骤5,组网小卫星观测能力评估与网络规划。本发明所公开的电离层探测小卫星网络规划方法,基于轨道参数对覆盖区的影响分析,实现了对小卫星星座电离层观测能力的评价,对电离层探测小卫星网络规划设计具有重要意义。(The invention discloses a network planning method for an ionosphere exploration small satellite, which comprises the following steps: step 1, setting basic parameters of a small satellite; step 2, calculating the coverage capability of a single small satellite; step 3, analyzing the influence of the track parameters on the coverage capability; step 4, determining the constellation number and orbit parameters of the small satellites; and 5, evaluating the observation capability of the networking small satellite and planning a network. The ionosphere detection small satellite network planning method disclosed by the invention realizes the evaluation of the ionosphere observation capability of the constellation of small satellites based on the analysis of the influence of the orbit parameters on the coverage area, and has important significance on the ionosphere detection small satellite network planning design.)

1. An ionosphere exploration small satellite network planning method is characterized by comprising the following steps:

step 1, setting basic parameters of a small satellite, setting the orbit height and the carrying load type of the small satellite, and providing constraint conditions for the coverage capability calculation of a single small satellite;

step 2, calculating the coverage capacity of a single small satellite, calculating the size of the coverage area of the single small satellite, and providing a design basis for the number of the small satellites required by global coverage;

step 3, analyzing the influence of the track parameters on the coverage capability, analyzing the influence of the track inclination angle, the ascension of the ascending intersection point and the true approach point angle on the coverage characteristic, and further selecting and optimizing the track parameters;

step 4, designing orbit parameters of the small satellites and selecting the number of the constellation satellites, and determining the number of the constellation of the small satellites and the orbit parameters based on the calculation result of the coverage capability of a single small satellite and the analysis result of the influence of the orbit parameters on the coverage capability;

step 5, networking small satellite observation capability assessment and network planning: and calculating the global coverage characteristics of the small satellite constellation with different orbit parameters, and finally selecting the optimized observation network.

2. The ionospheric sounding small satellite network planning method of claim 1, wherein: in the step 1, the height of the small satellite orbit is 1125km, the observation mode is earth observation, the carried load adopts a far ultraviolet airglow imager, the range of the earth depression angle of the far ultraviolet airglow imager is 117 degrees, and the normal direction is the direction pointing to the intersatellite point.

3. The ionospheric sounding small satellite network planning method of claim 1, wherein: in step 2, the adopted microsatellite orbit parameters include: height of the track: 1125 km; eccentricity ratio: 0 degree; track inclination angle: 90 degrees; argument of perigee: 0 degree; ascending crossing right ascension: 0 degree; true proximal angle: 0 degree.

4. The ionospheric sounding small satellite network planning method of claim 1, wherein: in step 3, the adopted microsatellite orbit parameters include: height of the track: 1125 km; eccentricity ratio: 0 degree; track inclination angle: 120 degrees; argument of perigee: 0 degree; ascending crossing right ascension: 0 degrees, 60 degrees, 120 degrees; true proximal angle: 0 degrees, 45 degrees, 90 degrees, 135 degrees, 180 degrees, 225 degrees, 270 degrees, 315 degrees.

5. The ionospheric sounding small satellite network planning method of claim 1, wherein: in step 4, the constellation three-orbit parameters composed of 24 small satellites are as follows: height of the track: 1125 km; eccentricity ratio: 0 degree; track inclination angle: 90 degrees; argument of perigee: 0 degree; ascending crossing right ascension: 0 degrees, 60 degrees, 120 degrees; true proximal angle: 0 degrees, 45 degrees, 90 degrees, 135 degrees, 180 degrees, 225 degrees, 270 degrees, 315 degrees; the constellation four-orbit parameters composed of 32 small satellites are as follows: height of the track: 1125 km; eccentricity ratio: 0 degree; track inclination angle: 90 degrees; argument of perigee: 0 degree; ascending crossing right ascension: 0 degrees, 45 degrees, 90 degrees, 135 degrees; true proximal angle: 0 degrees, 45 degrees, 90 degrees, 135 degrees, 180 degrees, 225 degrees, 270 degrees, 315 degrees.

Technical Field

The invention belongs to the technical field of ionosphere detection, and particularly relates to a network planning method for an ionosphere detection small satellite in the field.

Background

With the advances in microelectronics, light materials, and high power solar cell technologies, small satellites have seen explosive growth. The total amount of the small satellites transmitted by the international grand project such as SpaceX, Amazon, Boeing, Oneweb, Telesat and the like exceeds 40000. With the explosive increase of the number of space sensors, the space situation including the ionosphere environment is enabled to be transparent in a high-precision manner, and the development of a new concept of space situation perception capability can emerge endlessly by utilizing the detection capability of mass sensors, and the development of a transparent ionosphere technology is a necessary trend. Therefore, before the arrival of the intensive small satellite network era, the development of ionosphere exploration small satellite network planning research has important significance, and the ionosphere network planning research is also a problem to be solved urgently in compliance with the technical development trend and improvement of the ionosphere global remote sensing capability of China.

Disclosure of Invention

The invention aims to provide a network planning method for an ionosphere detection small satellite.

The invention adopts the following technical scheme:

the improvement of a network planning method for ionosphere exploration small satellites is that the method comprises the following steps:

step 1, setting basic parameters of a small satellite, setting the orbit height and the carrying load type of the small satellite, and providing constraint conditions for the coverage capability calculation of a single small satellite;

step 2, calculating the coverage capacity of a single small satellite, calculating the size of the coverage area of the single small satellite, and providing a design basis for the number of the small satellites required by global coverage;

step 3, analyzing the influence of the track parameters on the coverage capability, analyzing the influence of the track inclination angle, the ascension of the ascending intersection point and the true approach point angle on the coverage characteristic, and further selecting and optimizing the track parameters;

step 4, designing orbit parameters of the small satellites and selecting the number of the constellation satellites, and determining the number of the constellation of the small satellites and the orbit parameters based on the calculation result of the coverage capability of a single small satellite and the analysis result of the influence of the orbit parameters on the coverage capability;

step 5, networking small satellite observation capability assessment and network planning: and calculating the global coverage characteristics of the small satellite constellation with different orbit parameters, and finally selecting the optimized observation network.

Further, in step 1, the height of the small satellite orbit is 1125km, the observation mode is earth observation, the carried load adopts a far ultraviolet airglow imager, the range of the earth depression angle of the far ultraviolet airglow imager is 117 degrees, and the normal direction is the direction pointing to the intersatellite point.

Further, in step 2, the adopted small satellite orbit parameters include: height of the track: 1125 km; eccentricity ratio: 0 degree; track inclination angle: 90 degrees; argument of perigee: 0 degree; ascending crossing right ascension: 0 degree; true proximal angle: 0 degree.

Further, in step 3, the adopted microsatellite orbit parameters include: height of the track: 1125 km; eccentricity ratio: 0 degree; track inclination angle: 120 degrees; argument of perigee: 0 degree; ascending crossing right ascension: 0 degrees, 60 degrees, 120 degrees; true proximal angle: 0 degrees, 45 degrees, 90 degrees, 135 degrees, 180 degrees, 225 degrees, 270 degrees, 315 degrees.

Further, in step 4, the constellation three-orbit parameters formed by 24 small satellites are as follows: height of the track: 1125 km; eccentricity ratio: 0 degree; track inclination angle: 90 degrees; argument of perigee: 0 degree; ascending crossing right ascension: 0 degrees, 60 degrees, 120 degrees; true proximal angle: 0 degrees, 45 degrees, 90 degrees, 135 degrees, 180 degrees, 225 degrees, 270 degrees, 315 degrees; the constellation four-orbit parameters composed of 32 small satellites are as follows: height of the track: 1125 km; eccentricity ratio: 0 degree; track inclination angle: 90 degrees; argument of perigee: 0 degree; ascending crossing right ascension: 0 degrees, 45 degrees, 90 degrees, 135 degrees; true proximal angle: 0 degrees, 45 degrees, 90 degrees, 135 degrees, 180 degrees, 225 degrees, 270 degrees, 315 degrees.

The invention has the beneficial effects that:

the ionosphere detection small satellite network planning method disclosed by the invention realizes the evaluation of the ionosphere observation capability of the constellation of small satellites based on the analysis of the influence of the orbit parameters on the coverage area, and has important significance on the ionosphere detection small satellite network planning design.

The ionosphere detection small satellite network planning method disclosed by the invention can be also used for performance evaluation and network planning of other monitoring systems of earth observation small satellites, and has important significance for developing a space-based environment remote sensing system.

Drawings

FIG. 1 is a schematic flow chart of the method disclosed in example 1 of the present invention;

FIG. 2 is a diagram of the footprint of a single microsatellite over the ground;

FIG. 3 is a graph of the effect of track inclination, ascension at the ascending intersection, and true paraxial angle on coverage characteristics;

FIG. 4 is a diagram of a 24-microsatellite footprint;

FIG. 5 is a global proportion of 24 constellation coverage times;

FIG. 6 is a time evolution of the percent global coverage over one orbital period of the 24 constellation;

FIG. 7 is a diagram of a 32-microsatellite footprint;

FIG. 8 is a global proportion of 32 constellation coverage times;

fig. 9 is a time evolution of the percent global coverage over one orbital period of the 32 constellation.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail below with reference to the accompanying drawings and examples. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

Embodiment 1, as shown in fig. 1, this embodiment discloses a method for planning an ionosphere-sounding small satellite network, including the following steps:

step 1, setting the basic parameters of the small satellite:

setting the basic parameters of the small satellite refers to setting the orbit height and the carrying load type of the small satellite and providing constraint conditions for the coverage capability calculation of a single small satellite;

in the embodiment, according to the preliminary design requirement of the network planning of the small satellites, the orbit height of the small satellites is 1125km, the observation mode is earth observation, in order to realize ionosphere observation, a far ultraviolet airglow imager is adopted for carrying loads, and the system can realize inversion of the electron density parameters of the ionosphere through far ultraviolet waveband airglow imaging. The depression range of the far ultraviolet airglow imager to the ground is 117 degrees, and the normal direction is the direction pointing to the subsatellite point.

Step 2, calculating the coverage capability of a single small satellite:

the coverage capability calculation of a single small satellite is to calculate the size of a coverage area of the single small satellite and provide a design basis for the number of the small satellites required by global coverage;

the microsatellite orbit parameters adopted in the embodiment include: height of the track: 1125 km; eccentricity ratio: 0 degree; track inclination angle: 90 degrees; argument of perigee: 0 degree; ascending crossing right ascension: 0 degree; true proximal angle: 0 degree.

Figure 2 shows a map of the footprint of a single microsatellite over the ground. As can be seen, a single microsatellite can cover a latitude and longitude range of about 60 ° x 60 °. Thus, at least 18 microsatellites are required to achieve global coverage, although such an arrangement may have large observation holes between the coverage areas of the microsatellites.

And 3, analyzing the influence of the track parameters on the coverage capacity:

analyzing the influence of the track parameters on the coverage capability means analyzing the influence of the track inclination angle, the ascension of the ascending intersection point and the true approach point angle on the coverage characteristic, and further selecting and optimizing the track parameters;

the influence of the orbital inclination, the ascension at the ascending intersection and the true paraxial angle on the coverage characteristics is shown in fig. 3, and the adopted microsatellite orbital parameters include: height of the track: 1125 km; eccentricity ratio: 0 degree; track inclination angle: 120 degrees; argument of perigee: 0 degree; ascending crossing right ascension: 0 degrees, 60 degrees, 120 degrees; true proximal angle: 0 degrees, 45 degrees, 90 degrees, 135 degrees, 180 degrees, 225 degrees, 270 degrees, 315 degrees.

It can be seen from the figure that the true paraxial angle mainly affects the latitudinal position to the geospatial region, the ascension at the ascending intersection mainly affects the meridional position to the geospatial region, and the dip angle mainly affects the trend of the variation of the geospatial region.

Step 4, small satellite orbit parameter design and constellation satellite number selection:

the small satellite orbit parameter design and the constellation satellite number selection are based on the coverage capability calculation result and the orbit parameter influence analysis result of a single small satellite to the coverage capability, and the small satellite constellation number and the orbit parameter are determined;

based on analysis of influence of orbit parameters on coverage capacity, the number of the selected small satellites is 24 (three-orbit) and 32 (four-orbit), and the orbit parameters are as follows:

the constellation orbit parameters composed of 24 small satellites are as follows: height of the track: 1125 km; eccentricity ratio: 0 degree; track inclination angle: 90 degrees; argument of perigee: 0 degree; ascending crossing right ascension: 0 degrees, 60 degrees, 120 degrees; true proximal angle: 0 degrees, 45 degrees, 90 degrees, 135 degrees, 180 degrees, 225 degrees, 270 degrees, 315 degrees; the constellation orbit parameters composed of 32 small satellites are as follows: height of the track: 1125 km; eccentricity ratio: 0 degree; track inclination angle: 90 degrees; argument of perigee: 0 degree; ascending crossing right ascension: 0 degrees, 45 degrees, 90 degrees, 135 degrees; true proximal angle: 0 degrees, 45 degrees, 90 degrees, 135 degrees, 180 degrees, 225 degrees, 270 degrees, 315 degrees.

Step 5, networking small satellite observation capability assessment and network planning:

networking small satellite observation capability evaluation and network planning refer to calculating the global coverage characteristics of small satellite constellations with different orbit parameters and finally selecting an optimized observation network.

The global coverage characteristics of the two constellations are calculated and figure 4 gives a map of the coverage of 24 microsatellites. Unlike ground parameter remote sensing, the coverage area of the ionosphere height becomes smaller, so that gaps exist among the coverage areas of the stars, and multiple coverage situations occur in a polar region, and 5-fold coverage can be realized at most. Fig. 5 shows a global occupancy map of 24 constellation coverage times, where the coverage hole is about 6.27%, the global coverage percentage is 93.73%, and the single coverage is more. Fig. 6 shows the time evolution of the global coverage percentage for 24 constellation in one orbital period, where the orbital period is 6468 s. From the figure it can be seen that the global percentage coverage has a minimum value of 92.9656%, a mean value of 93.8213%, and a maximum value of 94.6686%.

Figure 7 shows a map of the footprint of 32 microsatellites. As can be seen from the figure, the coverage blind area is obviously reduced, the multiple coverage condition is increased, and 7-fold coverage can be realized at most. Fig. 8 shows a global proportion of the number of 32-constellation coverage, in which the coverage blind area is only 0.8035%, the global coverage percentage is 99.1965%, and the two coverage cases are significantly increased. Fig. 9 shows the time evolution of the global coverage percentage for one orbital period of the 32 constellation. From the figure it can be seen that the global percentage coverage has a minimum value of 98.4820%, a mean value of 99.0931%, and a maximum value of 99.5557%. The overall observation capability of the 32-satellite constellation is remarkably improved, so that a small satellite constellation scheme can be selected according to comprehensive evaluation of angles such as cost and observation requirements.

In conclusion, the method realizes the evaluation of the small satellite constellation ionosphere observation capability through the steps of small satellite basic parameter setting, single small satellite coverage capability calculation, orbit parameter influence analysis on the coverage capability, small satellite orbit parameter design and constellation satellite number selection, networking small satellite observation capability evaluation, network planning and the like, and has important significance for ionosphere detection small satellite network planning design and development of a space-based environment remote sensing system.