阅读说明：本技术 非太阳同步轨道通信卫星单轴太阳翼驱动方法及系统 (Single-axis solar wing driving method and system for non-sun synchronous orbit communication satellite ) 是由 刘培 周必磊 邹兴 刘莹 杜宣 徐云东 成飞 舒适 杨先睿 于 2021-09-15 设计创作，主要内容包括：本发明提供了一种非太阳同步轨道通信卫星单轴太阳翼驱动方法及系统,包括：计算一年内卫星轨道光照角的变化曲线,根据轨道光照角的变化趋势,太阳翼一维转动保证轨道周期内持续对日,通过一维摆动适应轨道光照角的变化；太阳翼一维摆动角度岁轨道光照角β变化超过角度C时停止摆动,太阳翼只做一维转动,当轨道光照角β变化超过设定角度D时,向卫星本体-Z方向摆动至90°,轨道光照角β为正值时,太阳翼贴片面朝向卫星本体+Y方向,β角为负值时太阳翼贴片面朝向星体-Y方向。本发明针对通信卫星工作时间连续、载荷对地视场约束严苛、低轨非太阳同步轨道光照角变化大等特点和约束,通过顶层多要素综合分析,得到太阳翼最优驱动方法。(The invention provides a method and a system for driving a single-axis solar wing of a non-sun synchronous orbit communication satellite, which comprises the following steps: calculating a change curve of the satellite orbit illumination angle in one year, ensuring continuous sun-facing in an orbit period by one-dimensional rotation of the solar wing according to the change trend of the orbit illumination angle, and adapting to the change of the orbit illumination angle through one-dimensional swing; when the change of the orbit illumination angle beta exceeds a set angle D, the sun wing swings to 90 degrees in the-Z direction of the satellite body, when the change of the orbit illumination angle beta exceeds the set angle D, the sun wing patch surface faces to the + Y direction of the satellite body, and when the beta angle is a negative value, the sun wing patch surface faces to the-Y direction of the satellite body. The optimal driving method of the solar wing is obtained through comprehensive analysis of top-level multi-elements aiming at the characteristics and constraints of continuous working time of a communication satellite, severe constraint of load on the earth view field, large change of illumination angle of a low-orbit non-solar synchronous orbit and the like.)

1. A single-axis solar wing driving method for a non-sun synchronous orbital communication satellite is characterized by comprising the following steps:

step S1: calculating a change curve of an orbit illumination angle of the satellite in one year based on orbit parameters, wherein the orbit illumination angle is an included angle beta between a sun vector and an orbit plane of the satellite, and the orbit parameters comprise an orbit height and an orbit inclination angle;

step S2: according to the variation trend of the track illumination angle, the solar wing ensures continuous sun-facing in the track period through one-dimensional rotation, and adapts to the variation of the track illumination angle through one-dimensional swing;

step S3: when the change of the solar wing one-dimensional swing angle year orbit illumination angle beta exceeds a set angle C, the swing is stopped, and the solar wing only rotates one-dimensionally, so that the blocking of a communication load field is avoided;

step S4: when the change of the orbit illumination angle beta exceeds a set angle D, the sun wing patch surface swings to 90 degrees towards the satellite body-Z direction, the sun wing patch surface faces towards the satellite body + Y direction when the orbit illumination angle beta is a positive value, and the sun wing patch surface faces towards the satellite body-Y direction when the beta angle is a negative value.

2. The single-axis solar wing driving method for a non-sun synchronous orbital communication satellite according to claim 1, characterized in that: the calculation method of the angle C in step S3 is as follows: and C is 90-A, wherein A is the communication load field angle.

3. The single-axis solar wing driving method for a non-sun synchronous orbital communication satellite according to claim 1, characterized in that: the calculation method of the angle D in step S4 is as follows: d is 90-A/2, wherein A is the communication load field angle.

4. The single-axis solar wing driving method for a non-sun synchronous orbital communication satellite according to claim 1, characterized in that: calculating a change curve of an orbit shadow period T in one year based on orbit parameters, wherein the orbit parameters comprise orbit height and inclination angle, fitting the change curve of the orbit shadow period T and the change curve of an orbit illumination angle to obtain a solar illumination angle threshold beta of the satellite in a full illumination period₁。

5. The single-axis solar wing driving method for a non-sun synchronous orbital communication satellite according to claim 4, wherein: maximum shadow time T in change curve based on track shadow period T in one year₁Calculating the ratio (P) of the whole satellite power consumption and the output power of the solar wing under vertical irradiation_sat/(1-5％))/P_solarObtaining the maximum deviation angles B and P of the solar wing which allow the non-vertical incidence of the sunlight when the storage battery pack is not charged in the full-light period_satThe power consumption of the whole satellite in the satellite working state is obtained.

6. The single-axis solar wing driving method for a non-sun synchronous orbital communication satellite according to claim 1, characterized in that: the calculation method of the angle B comprises the following steps: b ═ arccos ((P)_sat/(1-5％))/P_solar)。

7. The single-axis solar wing driving method for a non-sun synchronous orbital communication satellite according to claim 1, characterized in that: in order to ensure that the driving method can meet the requirement of single-circle energy balance,

if C is greater than beta₁And A/2 is smaller than B, the solar wing does not need to increase the area adaptively;

if C is greater than beta₁And A/2 is greater than B, the solar wing area needs to be adaptively increased, and the output power P_add1The number of the required steps is increased,

if C is less than beta₁And A/2 is less than B, then at an orbital illumination angle-beta₁-C and C-beta₁In the change interval, the track illumination angle changes 1 degree every time, and the required solar wing output power P is calculated according to the shadow time at the moment₁Whether or not both are less than P_solarIf so, the solar wing area does not need to be increased adaptively, otherwise, the output power P needs to be increased_add2；

If C is less than beta₁And A/2 is greater than B, the solar wing area needs to be increased adaptively, and the output power needs to be increased by P_add3While at the orbital illumination angle-beta₁-C and C-beta₁In the change interval, the track illumination angle changes 1 degree every time, and the required solar wing output power P is calculated according to the shadow time at the moment₂Whether or not both are less than P_solar+P_add3If so, the area of the solar wing does not need to be increased adaptively, and if not, the output power needs to be increased.

8. The single-axis solar wing driving method for a non-sun synchronous orbital communication satellite according to claim 7, characterized in that: the P is₁Is calculated as follows:

in the formula: t is t_{Shadow masking}Representing the time of the ground shadow, t, corresponding to the illumination angle beta_{Illumination of light}The illumination time corresponding to the track illumination angle beta;

if P_solar＞P_max1，P_max1Is P₁The maximum value of (3) without increasing the solar wing area;

if P_solar＜P_max1Then the output power needs to be increased by P_add2＝P_max1-P_solar。

9. The single-axis solar wing driving method for a non-sun synchronous orbital communication satellite according to claim 7, characterized in that: the P is₂Is calculated as follows:

in the formula: t is t_{Shadow masking}Representing the time of the ground shadow, t, corresponding to the illumination angle beta_{Illumination of light}The illumination time corresponding to the track illumination angle beta;

if P_solar+P_add3＞P_max2，P_max2Is P₂The maximum value of (3) does not need to increase the solar wing area;

if P_solar+P_add3＜P_max2Then the output power needs to be increased by P_add3＝P_max2-P_solar-P_add3(ii) a The total power increase is: p_add4＝P_add3+P_add3＝P_max2-P_solar。

10. A single-axis solar wing driving system of a non-sun synchronous orbital communication satellite is characterized by comprising the following modules:

module M1: calculating a change curve of an orbit illumination angle of the satellite in one year based on orbit parameters, wherein the orbit illumination angle is an included angle beta between a sun vector and an orbit plane of the satellite, and the orbit parameters comprise an orbit height and an orbit inclination angle;

module M2: according to the variation trend of the track illumination angle, the solar wing ensures continuous sun-facing in the track period through one-dimensional rotation, and adapts to the variation of the track illumination angle through one-dimensional swing;

module M3: when the change of the solar wing one-dimensional swing angle year orbit illumination angle beta exceeds a set angle C, the swing is stopped, and the solar wing only rotates one-dimensionally, so that the blocking of a communication load field is avoided;

module M4: when the change of the orbit illumination angle beta exceeds a set angle D, the sun wing patch surface swings to 90 degrees towards the satellite body-Z direction, the sun wing patch surface faces towards the satellite body + Y direction when the orbit illumination angle beta is a positive value, and the sun wing patch surface faces towards the satellite body-Y direction when the beta angle is a negative value.

Technical Field

The invention relates to the field of overall satellite design, in particular to a single-axis solar wing driving method for a non-solar synchronous orbital communication satellite, and particularly relates to a single-axis solar wing driving method for a non-solar synchronous orbital communication satellite for flat stacking launching.

Background

Compared with other satellites, the communication satellite has the characteristics of long service life, high power consumption and long full-period work, and an energy system is required to provide stable and sufficient energy guarantee uninterruptedly in the service life. The traditional communication satellites are geosynchronous orbit satellites, and the solar cell array design and driving method are different from the solar cell array design and driving method under the different illumination conditions of low earth orbit.

With the rise of low-orbit communication satellite constellations, higher requirements are put forward on low-orbit communication satellite design with low cost, high efficiency and high reliability. The low earth orbit can be divided into a sun synchronous orbit and a non-sun synchronous orbit, the change of the illumination angle of the sun synchronous orbit is small, and the solar cell array can be realized by adopting the traditional one-dimensional rotation; the illumination angle of the non-solar synchronous orbit changes greatly, the solar cell array needs to swing while rotating, if the design is carried out according to the traditional method, the swing angle is too large, the communication load view field of the communication satellite is usually large, and therefore the view field of the communication load is shielded, and the normal service operation of the satellite is influenced.

In the field of satellite overall design, according to the searched patents, researchers in the field have proposed various methods for designing a satellite solar cell array and a driving mode. In chinese patent publication No. CN102004492B, a method for controlling a dual-axis windsurfing board of a non-solar synchronous orbit satellite is introduced, which only designs a specific driving control method for a solar wing of the satellite according to an illumination angle of the non-solar synchronous orbit, and does not consider the problem of blocking a load view field after the solar wing swings from the perspective of the overall design of the satellite. The method is a swing strategy design method which is used for solving the problem that the influence of the swing of the solar wing on the load view field in the future is minimum, and is obviously different from the method.

Chinese patent publication No. CN106697334B discloses a method for controlling driving of a satellite solar wing sailboard, which mainly aims at the hardware design of a driving mechanism, and is significantly different from the present patent.

In chinese patent publication No. CN105035364B, a solar array driving and swinging method for a low-inclination orbit radar satellite is disclosed, which designs different layout methods of solar wings and whether to drive the solar wings according to different yaw flight states of the satellite, and because the radar satellite does not require ground orientation in the whole orbit period, the sunlight incident angle can be in an expected range, and two-dimensional driving is not required, and because the load characteristic does not consider the problem of shielding of the solar wings to the load view field, the method is obviously different from the method.

Chinese patent publication No. CN112758354A discloses a method for calculating the control and energy balance coupling of a biaxial solar wing of a low-orbit satellite, which does not combine the mutual characteristics of the orbit illumination angle and the shadow period to optimize the driving method of the solar wing, and is obviously different from the driving method proposed in this patent.

Chinese patent publication No. CN112937923A discloses a method for controlling a biaxial solar wing driving mechanism for a near-earth inclined orbit satellite, which does not consider the influence on the field of view of communication load when designing the solar wing driving mechanism control method, and does not optimize the solar wing driving method in combination with the mutual characteristics of the orbit illumination angle and the shadow period, and is significantly different from the driving method proposed in the present patent.

Chinese patent publication No. CN112937919A discloses a method for controlling a two-degree-of-freedom sun wing of a low-orbit satellite, which is how to control how the two-degree-of-freedom sun wing moves, and a method for driving the sun wing is not designed from the overall perspective of the satellite, which is significantly different from this patent.

In chinese patent publication No. CN111792058A, a method for driving solar wings to face sun by using low-inclination orbital single-axis SADA is disclosed, which comprises the following steps: s1, determining the coordinates of the sun vector in the orbital system by the on-satellite sensor; s2, calculating the yaw angle of the satellite according to the projection of the sun vector on the XoOYo plane of the orbit; s3, calculating the expected yaw angle and angular speed information in the satellite attitude motion; s4, calculating the rotation angle of the solar wing driving device according to the included angle between the normal coordinate of the solar sailboard and the sun vector when the solar wing driving device is at zero position; and S5, controlling satellite maneuvering by the satellite actuator, and simultaneously, matching the sun wing driving device to rotate so as to ensure that the sun wing points to the sun.

Disclosure of Invention

Aiming at the defects in the prior art, the invention aims to provide a method and a system for driving a single-axis solar wing of a non-solar synchronous orbit communication satellite.

The invention provides a method for driving a single-axis solar wing of a non-sun synchronous orbit communication satellite, which comprises the following steps:

step S1: calculating a change curve of an orbit illumination angle of the satellite in one year based on orbit parameters, wherein the orbit illumination angle is an included angle beta between a sun vector and an orbit plane of the satellite, and the orbit parameters comprise an orbit height and an orbit inclination angle;

step S2: according to the variation trend of the track illumination angle, the solar wing ensures continuous sun-facing in the track period through one-dimensional rotation, and adapts to the variation of the track illumination angle through one-dimensional swing;

step S3: when the change of the solar wing one-dimensional swing angle year orbit illumination angle beta exceeds a set angle C, the swing is stopped, and the solar wing only rotates one-dimensionally, so that the blocking of a communication load field is avoided;

step S4: when the change of the orbit illumination angle beta exceeds a set angle D, the sun wing patch surface swings to 90 degrees towards the satellite body-Z direction, the sun wing patch surface faces towards the satellite body + Y direction when the orbit illumination angle beta is a positive value, and the sun wing patch surface faces towards the satellite body-Y direction when the beta angle is a negative value.

Preferably, the method for calculating the angle C in step S3 is as follows: and C is 90-A, wherein A is the communication load field angle.

Preferably, the method for calculating the angle D in step S4 is as follows: d is 90-A/2, wherein A is the communication load field angle.

Preferably, a change curve of the orbit shadow period T in one year is calculated based on orbit parameters, the orbit parameters comprise orbit height and inclination angle, the change curve of the orbit shadow period T is fitted with a change curve of the orbit illumination angle, and a solar illumination angle threshold beta of the satellite in a full illumination period is obtained₁。

Preferably, the maximum shadow time T in the variation curve based on the track shadow period T in one year₁Calculating the ratio (P) of the whole satellite power consumption and the output power of the solar wing under vertical irradiation_sat/(1-5％))/P_solarObtaining the maximum deviation angles B and P of the solar wing which allow the non-vertical incidence of the sunlight when the storage battery pack is not charged in the full-light period_satThe power consumption of the whole satellite in the satellite working state is obtained.

Preferably, the calculation method of the angle B is as follows: b ═ arccos ((P)_sat/(1-5％))/P_solar)。

Preferably, in order to ensure that the driving method can meet the requirement of single-circle energy balance,

if C is greater than beta₁And A/2 is smaller than B, the solar wing does not need to increase the area adaptively;

if C is greater than beta₁And A/2 is greater than B, the solar wing area needs to be adaptively increased, and the output power P_add1The number of the required steps is increased,

if C is less than beta₁And A/2 is less than B, then at an orbital illumination angle-beta₁-C and C-beta₁Within the variation interval, the track illumination angle is changed every time1 degree, calculating the required solar wing output power P according to the shadow time at the moment₁Whether or not both are less than P_solarIf so, the solar wing area does not need to be increased adaptively, otherwise, the output power P needs to be increased_add2；

If C is less than beta₁And A/2 is greater than B, the solar wing area needs to be increased adaptively, and the output power needs to be increased by P_add3While at the orbital illumination angle-beta₁-C and C-beta₁In the change interval, the track illumination angle changes 1 degree every time, and the required solar wing output power P is calculated according to the shadow time at the moment₂Whether or not both are less than P_solar+P_add3If so, the area of the solar wing does not need to be increased adaptively, and if not, the output power needs to be increased.

Preferably, said P₁Is calculated as follows:

in the formula: t is t_{Shadow masking}Representing the time of the ground shadow, t, corresponding to the illumination angle beta_{Illumination of light}The illumination time corresponding to the track illumination angle beta;

if P_solar＞P_max1，P_max1Is P₁The maximum value of (3) without increasing the solar wing area;

if P_solar＜P_max1Then the output power needs to be increased by P_add2＝P_max1-P_solar。

9. The single-axis solar wing driving method for a non-sun synchronous orbital communication satellite according to claim 7, characterized in that: the P is₂Is calculated as follows:

in the formula: t is t_{Shadow masking}Representing the time of the ground shadow, t, corresponding to the illumination angle beta_{Illumination of light}The illumination time corresponding to the track illumination angle beta;

if P_solar+P_add3＞P_max2，P_max2Is P₂The maximum value of (3) does not need to increase the solar wing area;

if P_solar+P_add3＜P_max2Then the output power needs to be increased by P_add3＝P_max2-P_solar-P_add3(ii) a The total power increase is: p_add4＝P_add3+P_add3＝P_max2-P_solar。

The invention provides a single-axis solar wing driving system of a non-sun synchronous orbit communication satellite, which comprises the following modules:

module M1: calculating a change curve of an orbit illumination angle of the satellite in one year based on orbit parameters, wherein the orbit illumination angle is an included angle beta between a sun vector and an orbit plane of the satellite, and the orbit parameters comprise an orbit height and an orbit inclination angle;

module M2: according to the variation trend of the track illumination angle, the solar wing ensures continuous sun-facing in the track period through one-dimensional rotation, and adapts to the variation of the track illumination angle through one-dimensional swing;

module M3: when the change of the solar wing one-dimensional swing angle year orbit illumination angle beta exceeds a set angle C, the swing is stopped, and the solar wing only rotates one-dimensionally, so that the blocking of a communication load field is avoided;

module M4: when the change of the orbit illumination angle beta exceeds a set angle D, the sun wing patch surface swings to 90 degrees towards the satellite body-Z direction, the sun wing patch surface faces towards the satellite body + Y direction when the orbit illumination angle beta is a positive value, and the sun wing patch surface faces towards the satellite body-Y direction when the beta angle is a negative value.

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

1. the invention designs a non-solar synchronous orbit communication satellite single-axis solar wing driving method facing flat stack emission, and reasonably sets an on-orbit full-period solar wing driving strategy by fully utilizing the characteristics of a non-solar synchronous orbit satellite in a full light period aiming at the layout of the flat stack emission satellite single-axis solar wings.

2. The invention improves the use efficiency of the solar wing and reduces the area of the solar wing while avoiding shielding the communication load view field.

3. The invention lays a foundation for low-cost and high-efficiency development of low-orbit large-batch satellites in the future.

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 flow chart of a method for driving a single-axis solar wing of a non-solar synchronous orbit communication satellite according to an embodiment of the present invention;

FIG. 2 is a schematic diagram of an in-orbit flight state of a satellite according to an embodiment of the invention;

FIG. 3 is a schematic diagram illustrating a variation law fitting between an orbit illumination angle β and a shadow period T according to an embodiment of the present invention;

FIG. 4 is a schematic view of a solar wing drive strategy in an embodiment of the present invention;

FIG. 5 is a schematic view of a non-vertical illumination off-angle of a solar wing according to an embodiment of the present invention.

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 invention provides a method for driving a single-axis solar wing of a non-sun synchronous orbit communication satellite, which comprises the following steps of with reference to fig. 1:

step S1: calculating a change curve of the satellite orbit illumination angle in one year based on orbit parameters, wherein the orbit illumination angle is an included angle beta between a sun vector and a satellite orbit surface, and the orbit parameters comprise an orbit height and an orbit inclination angle.

Step S2: according to the change trend of the track illumination angle, the solar wing ensures continuous sun-facing in the track period through one-dimensional rotation, and adapts to the change of the track illumination angle through one-dimensional swing.

Step S3: when the change of the one-dimensional swing angle of the solar wing and the orbital illumination angle beta exceeds a set angle C, the solar wing stops swinging, the solar wing only rotates in one dimension to avoid blocking a communication load field, and C is 90-A, wherein A is a communication load field angle.

Step S4: when the change of the orbit illumination angle beta exceeds a set angle D, the satellite body swings to 90 degrees towards the Z direction of the satellite body, the solar wing patch surface faces towards the + Y direction of the satellite body when the orbit illumination angle beta is a positive value, the solar wing patch surface faces towards the-Y direction of the satellite body when the beta angle is a negative value, the maximum deviation angle of sunlight which is not vertically incident to the solar wing is reduced, the service efficiency of the solar wing is improved, the D is 90-A/2, and the A is a communication load view angle.

Calculating a change curve of the orbit shadow period T in one year based on orbit height and inclination angle orbit parameters, fitting the change curve of the orbit shadow period T with a change curve of the orbit illumination angle to obtain a solar illumination angle threshold beta of the satellite in a full illumination period₁. Maximum shadow time T in change curve based on track shadow period T in one year₁Calculating the ratio (P) of the whole satellite power consumption and the output power of the solar wing under vertical irradiation_sat/(1-5％))/P_solarObtaining the maximum deviation angles B and P of the solar wing which allow the non-vertical incidence of the sunlight when the storage battery pack is not charged in the full-light period_satFor the whole satellite power consumption in the satellite working state, B ═ arccos ((P))_sat/(1-5％))/P_solar)。

In order to ensure that the driving method can meet the requirement of single-circle energy balance,

if C is greater than beta₁And A/2 is smaller than B, the solar wing does not need to increase the area adaptively;

if C is greater than beta₁And A/2 is greater than B, the solar wing area needs to be adaptively increased, and the output power P_add1The number of the required steps is increased,

if C is less than beta₁And A/2 is less than B, then at an orbital illumination angle-beta₁-C and C-beta₁In the change interval, the illumination angle of the track changes 1 degree every time, according to the shading time at the momentCalculating the required solar wing output power P₁Whether or not both are less than P_solarIf so, the solar wing area does not need to be increased adaptively, otherwise, the output power P needs to be increased_add2；

P₁Is calculated as follows:

in the formula: t is t_{Shadow masking}Representing the time of the ground shadow, t, corresponding to the illumination angle beta_{Illumination of light}The illumination time corresponding to the track illumination angle beta;

if P_solar＞P_max1，P_max1Is P₁The maximum value of (3) without increasing the solar wing area;

if P_solar＜P_max1Then the output power needs to be increased by P_add2＝P_max1-P_solar。

If C is less than beta₁And A/2 is greater than B, the solar wing area needs to be increased adaptively, and the output power needs to be increased by P_add3While at the orbital illumination angle-beta₁-C and C-beta₁In the change interval, the track illumination angle changes 1 degree every time, and the required solar wing output power P is calculated according to the shadow time at the moment₂Whether or not both are less than P_solar+P_add3If so, the area of the solar wing does not need to be increased adaptively, and if not, the output power needs to be increased.

P₂Is calculated as follows:

in the formula: t is t_{Shadow masking}Representing the time of the ground shadow, t, corresponding to the illumination angle beta_{Illumination of light}The illumination time corresponding to the track illumination angle beta;

if P_solar+P_add3＞P_max2，P_max2Is P₂The maximum value of (3) does not need to increase the solar wing area;

if P_solar+P_add3＜P_max2Then the output power needs to be increased by P_add3＝P_max2-P_solar-P_add3(ii) a The total power increase is: p_add4＝P_add3+P_add3＝P_max2-P_solar。

The present invention is further illustrated below with reference to specific parameters.

The present embodiment is analyzed in conjunction with a flat stack launch non-solar synchronous orbit communications satellite, but is not limited to the orbit and configuration of the satellite. The satellite works on a non-solar synchronous orbit with the orbit height of 1175km and the inclination angle of 86.5 degrees, is in a flat configuration, and a solar cell array is positioned on the +/-Y surface, and is shown in figure 2 after the orbit is unfolded.

In the present embodiment, the entire satellite power consumption is 2000W, the bus voltage is 42V, and the communication load field angle is 55 ° in the satellite operating state.

In the step 1, a change curve of an included angle beta (orbit illumination angle) between a sun vector and a satellite orbit surface within 1 year is calculated based on orbit parameters such as orbit height, inclination angle and the like. The orbital plane illumination angle was found to vary from-88.92 ° to +78.82 °, with an absolute value approaching 90 °.

According to the change curve of the track shadow period T in 1 year, the maximum shadow time in the track period is 34.8 minutes, the full light period exists, and the duration is 29-48 days. Fitting the change curve of the sun illumination angle with the change curve of the orbit illumination angle to obtain the sun illumination angle threshold beta of the satellite in the full illumination period₁At 58 deg., as shown in fig. 3.

Calculating the area of the solar wing required by the satellite to be 12.4m according to the maximum shadow time and the single-circle energy balance requirement²The output power of the solar wing is 3205.7W when the solar wing receives the vertical irradiation of sunlight.

When the solar wing does not need to charge the storage battery pack in full-light period, the maximum deviation angle B of the solar wing allowing the non-vertical incidence of sunlight is arccos ((P)_sat/(1-5％))/P_solar) Arccos (2000W (1-5%)/3205.7W) ═ 48.94 °. The off-normal angle of the sun wing is shown in fig. 5.

In step 3, the angle C is 90 ° -55 ° -35 °.

In step 4, the angle D is 90 ° -55 °/2 is 62.5 °.

In the present embodiment, therefore, the solar wing oscillation is divided into three states, as shown in fig. 4:

state 1: the satellite solar wing swings along with the change of the orbit illumination angle within the range of +/-35 degrees of the orbit illumination angle, and the rotating shaft always rotates along with the sun;

state 2: the satellite solar wing stops swinging within the range of-62.5 DEG to-35 DEG of the orbit illumination angle and 35 DEG to 62.5 DEG, the swinging angle is fixed to +/-35 DEG or-35 DEG, and only one-dimensional rotation is carried out;

state 3: the swinging and the rotation are stopped within the range of minus 90 degrees to minus 62.5 degrees and 62.5 degrees to 90 degrees, the swinging angle is fixed to plus 90 degrees, and the solar wing patch faces to plus Y or minus Y direction.

Meanwhile, since C is less than beta₁And A/2 is less than B, and in the interval of track illumination angle from-58 deg. to-35 deg. and 35-58 deg., every track illumination angle is changed into 1 deg., according to the shadow time calculating required solar wing output power is less than P or not_solarThe calculation is satisfied, so that the area of the solar wing does not need to be increased adaptively.

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.

In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.

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.