CN114826438B - Method for determining installation position of ground measurement and control antenna - Google Patents
Method for determining installation position of ground measurement and control antenna Download PDFInfo
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- H—ELECTRICITY
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Abstract
The invention relates to a method for determining the installation position of a ground measurement and control antenna, which is suitable for determining the position for erecting a satellite measurement and control antenna near a launching field by analyzing the time length conditions that the ground measurement and control antenna at different installation positions at different moments of a launch active section of a carrier rocket can receive telemetry when the carrier rocket launches satellites with wave transmission characteristics. The method mainly comprises five steps, namely setting input parameters, determining the coverage range of the satellite antenna to the ground at different moments, determining the possible antenna erection positions according to the surrounding topography of the transmitting field, calculating the start-stop time and measurement and control duration of each position capable of receiving telemetry according to the direction angle of the ground measurement and control antenna, and completing the ground measurement and control antenna erection position calculation according to task requirements. The method can solve the problem that the satellite telemetry cannot be received due to the lack of the ground measurement and control station in the active stage of launch of the carrier rocket at the present stage, and can be popularized to the calculation of the installation position of the ground measurement and control antenna during the satellite orbit.
Description
Technical Field
The invention relates to a method for determining the installation position of a ground measurement and control antenna, and belongs to the technical field of spacecrafts.
Background
The inclusion of all state information of the satellite during its in-orbit operation in the satellite's in-orbit telemetry is an extremely valuable satellite resource. The designer utilizes the telemetry data of the satellite to carry out scientific analysis, and has important significance for long-term stable operation and subsequent improved design of the satellite. On the one hand, the health state of the satellite can be monitored and evaluated by analyzing the on-orbit telemetry data, so that the satellite can be timely found out of order and effective countermeasures can be taken to ensure long-term stable operation of the satellite in orbit. On the other hand, after the satellite fails, by analyzing the on-orbit telemetry data, a designer can be assisted in recording the failure phenomenon and locating the failure cause, and a valuable reference is provided for the follow-up improved design to reduce or avoid the occurrence of similar failures. Therefore, after satellite transmission, telemetry data is acquired early and scientifically analyzed, and the method is very important for safe and stable on-orbit operation of the satellite.
In the prior art, when a carrier rocket is used for launching satellites, due to the lack of a proper ground measurement and control station and other reasons near a launching field, before the active section of the carrier rocket launching, namely the ground measurement and control station, satellite designers on the ground cannot always obtain telemetry data of the satellites in the time period, and satellite states are difficult to evaluate. Once an abnormal situation occurs on the satellite during the period, the subsequent fault locating and troubleshooting work faces great difficulty because fault data cannot be acquired. In order to avoid this, timely acquisition of telemetry data carrying the transmitting active segment satellite is of great engineering significance.
With the development of technology, more and more carrier rockets in recent years are additionally provided with wave-transparent windows in design, which provides possibility for acquiring telemetry data of satellites carrying and transmitting active segments. On the basis, in order to make up the shortages of the ground measurement and control station, an antenna can be erected near a launch site to solve the problem of receiving the satellite telemetry data of the launch active section of the carrier rocket, so that how to determine the installation position of the ground measurement and control antenna is the key of successful implementation of the scheme.
Disclosure of Invention
The invention solves the technical problems that: the method is suitable for determining the position of the ground measurement and control antenna erected in a launch site when the launch satellite of the carrier rocket with wave transmission property launches the satellite active section, so that the problem of receiving telemetry data of the satellite of the launch satellite active section is effectively solved.
The technical scheme of the invention is as follows:
A method for determining the installation position of a ground measurement and control antenna comprises the following steps:
Setting input parameters, including: the installation position and the installation angle of the satellite antenna main shaft in the satellite body system and the installation angle of the satellite in the carrier rocket body system; position and attitude angle information of a launch active section of the carrier rocket at different moments; a pattern of satellite antennas; the direction angle of the ground measurement and control antenna;
Calculating cut-off lines of the pattern boundaries of the satellite antennas at different moments and the ground level, and determining the coverage ranges of the satellite antennas at different moments to the ground;
According to the surrounding terrain of the transmitting field, removing water surfaces and mountains in the coverage area of the satellite antenna to the ground, selecting the rest available plain areas as target areas for erecting the ground measurement and control antenna, and uniformly dividing the target areas to obtain a plurality of positions as possible to erect the ground measurement and control antenna;
Aiming at a plurality of positions obtained in a target area, calculating telemetry starting time, telemetry ending time and measurement and control duration at each position one by one according to the direction angle of a ground measurement and control antenna;
according to task demands, selecting a position meeting the requirements of the measurement and control duration and the start and stop time of receiving telemetry, and taking the position as the ground measurement and control antenna installation position.
Further, setting the pattern of the satellite antenna to be a fixed value of 2 pi; setting the direction angle of the ground measurement and control antenna to be xi, 0 degree < xi <90 degrees, and setting the direction angle of the antenna to be a fixed value after the installation is finished; the installation position and the installation angle of the satellite antenna main shaft in the satellite body system and the installation angle of the satellite in the carrier rocket body system are obtained by measurement before satellite launching.
Further, the implementation method for calculating the t moment cut-off line is as follows:
the first step: according to the position and attitude angle information of the launch active section t moment of the carrier rocket, determining the position of the antenna main shaft under the launch system t moment, specifically comprising the following steps:
Knowing the t moment, the coordinates of the rocket position in the launching system are Plv_fs= [ x_L, y_L, z_L ], wherein x_L, y_L and z_L respectively represent the distance of the projection of the rocket position on the horizontal plane along the launching direction, the distance of the rocket position along the vertical launching direction and the carrying elevation at the t moment; the attitude angles of the carrier rockets in 321 turn are LV_attitude= [ alpah _L, beta_L, gama_L ], alpah _L, beta_L and gama_L respectively represent the roll angle, pitch angle and yaw angle of the carrier at the moment t; the installation angle of the satellite in the carrier rocket body system is S_angle= [ phi_s, theta_s, psi_s ], the installation angle of the satellite antenna main shaft in the satellite body system is theta_sa= [ alpha_sa, beta_sa, gama_sa ], and the satellite antenna main shaft position under the launching system is calculated according to the following formula:
v_axis＝[A3(gama_L)×A2(beta_L)×A1(alpha_L)]-1×[A3(psi_s)×A2(theta_s)×A1(phi_s)]-1×[A3(gama_sa)×A2(beta_sa)×A1(alpha_sa)]-1×[0 0 1]
Wherein, A3 (i), A2 (j) and A1 (k) are respectively rotation matrixes under 321 rotation sequences, and the calculation formulas are as follows:
A3(i)＝[cos(i),sin(i),0；-1×sin(i),cons(i),0；0 0 1]；
A2(j)＝[cos(j),0,-1×sin(j)；0 1 0；sin(j),0,cons(j)]；
A1(k)＝[1 0 0；0cos(k),sin(k)；0-1×sin(k)cos(k)]；
Where i=gama_l, psi_s, gama_sa;
j＝beta_L,theta_s,beta_sa；
k＝alpha_L,phi_s,alpha_sa；
and a second step of: determining the z position of a cut-off line at the moment t according to the following calculation formula by utilizing the vertical relation between the main axis of the satellite antenna and the cut-off line:
z＝{2/(x1_jz-x2_jz)}×x+{1-2×x1_jz/(x1_jz-x2_jz)}
where (x1_jz, 0, 1), (x2_jz, 0, -1) is the coordinates of two points on the cut-off line.
The formulas of x1_jz and x2_jz are as follows:
x1_jz＝x_L+{y_L×v_axis×[0 1 0]-(1-z_L×v_axis×[0 0 1])}/{v_axis×[1 0 0]}
x2_jz＝x_L+{y_L×v_axis×[0 1 0]-(-1-z_L×v_axis×[0 0 1])}/{v_axis×[1 0 0]}。
Further, the implementation manner of uniformly dividing the target area to obtain a plurality of positions as the positions for possibly erecting the ground measurement and control antenna is as follows:
Assuming that the target area is rectangular, defining a point at intervals of 1 meter to the east along the north boundary line in the target area by taking one vertex of the west boundary line as a starting point location_11, and marking the defined point as location_1j, j=2, …, n until the east boundary line is reached; then, using location_11 as a starting point, defining a point at intervals of 1 meter to the south along a west boundary line until the south boundary line, and marking the defined point as location_i1, i=2, …, m; next, each point is defined at 1 meter intervals east along a line parallel to the north boundary line starting from location_i1, and the defined point is denoted as location_ij until the east boundary line, whereby m×n positions of the target area are obtained.
Further, the implementation method for calculating the telemetry starting time, the telemetry ending time and the measurement and control duration at each position is as follows:
Knowing t moment, the coordinates of the rocket position in a launching system are (x_L, y_L and z_L), the position of a certain ground measurement and control antenna selected at the moment is (xg, yg and zg), the direction angle of the ground measurement and control antenna is xi, and judging whether the connecting line of the ground measurement and control antenna-on-satellite antenna mounting position is in the direction angle of the ground measurement and control antenna in a z=zg plane or not, namely whether the following formula is established or not:
(y_L-yg)/(x_L-xg)>cot(ξ/2)
If the above formula is satisfied, the indication is in the telemetry visible range, otherwise, the indication is not in the telemetry visible range; substituting rocket position at each moment into the formula to judge, marking the earliest moment of the establishment of the formula as t_start and the latest moment of the establishment of the formula as t_end, so when the ground measurement and control antenna is arranged at the position of (xg, yg, zg), the telemetry starting time is t_start, the telemetry ending time is t_end, and the measurement and control duration is tck=t_end-t_start;
And a second step of: and calculating corresponding telemetry starting time, telemetry ending time and measurement and control duration according to the steps aiming at each selected ground measurement and control antenna position.
Further, according to task requirements, selecting a position meeting requirements of the measurement and control duration and the start and stop time of receiving telemetry, and taking the position as a ground measurement and control antenna installation position, wherein the implementation mode is as follows:
If the task requirement is that the measurement and control time is longest, selecting the position corresponding to the maximum measurement and control time as the erection position of the antenna; if the task requirement is that the telemetry starting time is earliest, selecting a position corresponding to the minimum value of the telemetry starting time as an erection position of the antenna; if the task requirement is that the telemetry ending time is the latest, selecting the corresponding position when the telemetry ending time is the maximum value as the erection position of the antenna.
Compared with the prior art, the invention has the beneficial effects that:
(1) According to the invention, the installation positions of the satellite ground measurement and control antennas are erected near the launching field by analyzing the time length conditions that the ground measurement and control antennas at different installation positions can receive telemetry at different moments when the launch active section of the carrier rocket is launched, so that the problem that satellite telemetry data cannot be received due to the lack of the ground measurement and control station in the launch active section at the present stage can be solved;
(2) The invention provides the telemetry starting time, telemetry ending time and measurement and control duration of the measurement and control antennas at different positions on the ground, so that a user can reasonably determine the positions of the measurement and control antennas on the ground according to the needs; the method has strong calculation flow operability and engineering applicability;
(3) The method can be popularized to the calculation of the ground measurement and control antenna installation position during the satellite in-orbit period, and only the relevant parameters of the satellite track in the expected measurement and control period are needed to be given.
Drawings
FIG. 1 is a schematic diagram of a telemetry scene of a satellite received by an erect ground measurement and control antenna, wherein LP represents a launch pad, LV represents a carrier rocket, S represents a satellite, GA represents the ground measurement and control antenna, FLIGHT PATH represents a flight track of the carrier rocket in an active section;
fig. 2 is a2 pi spatial pattern of a satellite antenna, wherein: a-axis represents the main axis of the antenna, 2 pi space represents the antenna space (as shown by the black dashed area) when the direction angle is 2 pi;
FIG. 3 is a flow chart of the calculation of the ground measurement and control antenna installation position.
Detailed Description
As shown in figure 1, the invention sets up a scene schematic diagram of a ground measurement and control antenna for receiving satellite telemetry, and when a carrier rocket with a wave-transparent window is used for launching satellites, the ground measurement and control antenna set up at a position near a launching field is used for receiving satellite telemetry data before a launch active section of the carrier rocket-a ground measurement and control station is visible.
As shown in fig. 2, is a2 pi spatial pattern of the satellite antenna.
As shown in fig. 3, the invention provides a method for determining the installation position of a ground measurement and control antenna, which comprises the following specific steps:
step one: setting input parameters, including:
(1) Setting the installation position SA_position, the installation angle theta_sa= [ alpha_sa, beta_sa, gama_sa ] of the main shaft of the satellite antenna in a satellite body system, and the installation position S_position= [ x_s, y_s, z_s ] of the satellite in a carrying interior, wherein the parameters can be measured by test equipment before the satellite is transmitted;
(2) The position lv_positon= [ x_l, y_l, z_l ] and the attitude angle lv_attitude= [ alpah _l, beta_l, gama_l ] at the time of the carrying position t at the coordinates of the emission system are set in the southeast coordinate system of the earth. Wherein x_L, y_L and z_L respectively represent the distance of the projection of the carrying position on the horizontal plane along the transmitting direction at the moment t, the distance of the carrying position along the vertical transmitting direction and the carrying elevation, alpah _L, beta_L and gama_L respectively represent the rolling angle, the pitch angle and the yaw angle of the carrying at the moment t;
(3) Setting the pattern of the satellite antenna to be a fixed value 2 pi;
(4) Setting the direction angle of the ground measurement and control antenna to be xi (0 degree < xi <90 degrees), and setting the direction angle of the antenna to be a fixed value after the installation is finished;
step two: and calculating a cut-off line CF of the pattern boundary of the satellite antenna at different moments t intersecting with the ground level, and determining the coverage area covered area of the satellite antenna at different moments t to the ground.
The implementation method for calculating the t moment cut-off line is as follows:
the first step: according to the position and attitude angle information of the launch active section of the carrier rocket at different moments, the position of the antenna main shaft under the launch system at different moments is determined, and the method specifically comprises the following steps:
Knowing the t moment, the coordinates of the rocket position in the launching system are Plv_fs= [ x_L, y_L, z_L ], wherein x_L, y_L and z_L respectively represent the distance of the projection of the rocket position on the horizontal plane along the launching direction, the distance of the rocket position along the vertical launching direction and the carrying elevation at the t moment; the attitude angles of the carrier rockets in 321 turn are LV_attitude= [ alpah _L, beta_L, gama_L ], alpah _L, beta_L and gama_L respectively represent the roll angle, pitch angle and yaw angle of the carrier at the moment t; the installation angle of the satellite in the carrier rocket body system is S_angle= [ phi_s, theta_s, psi_s ], the installation angle of the satellite antenna main shaft in the satellite body system is theta_sa= [ alpha_sa, beta_sa, gama_sa ], and the satellite antenna main shaft position under the launching system is calculated according to the following formula:
v_axis＝[A3(gama_L)×A2(beta_L)×A1(alpha_L)]-1×[A3(psi_s)×A2(theta_s)×A1(phi_s)]-1×[A3(gama_sa)×A2(beta_sa)×A1(alpha_sa)]-1×[0 0 1]
Wherein, A3 (i), A2 (j) and A1 (k) are respectively rotation matrixes under 321 rotation sequences, and the calculation formulas are as follows:
A3(i)＝[cos(i),sin(i),0；-1×sin(i),cons(i),0；0 0 1]；
A2(j)＝[cos(j),0,-1×sin(j)；0 1 0；sin(j),0,cons(j)]；
A1(k)＝[1 0 0；0cos(k),sin(k)；0-1×sin(k)cos(k)]；
Where i=gama_l, psi_s, gama_sa;
j＝beta_L,theta_s,beta_sa；
k＝alpha_L,phi_s,alpha_sa；
and a second step of: determining the z position of the cut-off line at different moments according to the following calculation formula by utilizing the vertical relation between the main axis of the satellite antenna and the cut-off line:
z＝{2/(x1_jz-x2_jz)}×x+{1-2×x1_jz/(x1_jz-x2_jz)}
where (x1_jz, 0, 1), (x2_jz, 0, -1) is the coordinates of two points on the cut-off line.
The formulas of x1_jz and x2_jz are as follows:
x1_jz＝x_L+{y_L×v_axis×[0 1 0]-(1-z_L×v_axis×[0 0 1])}/{v_axis×[1 0 0]}
x2_jz＝x_L+{y_L×v_axis×[0 1 0]-(-1-z_L×v_axis×[0 0 1])}/{v_axis×[1 0 0]}。
removing water surfaces and mountains in the coverage area of the satellite antenna to the ground according to the surrounding terrain of the transmitting field, selecting the rest available plain areas as target areas for erecting the ground measurement and control antenna, and uniformly dividing the target areas to obtain a plurality of positions as possible to erect the ground measurement and control antenna;
Assuming that the target area is rectangular, defining a point at intervals of 1 meter to the east along the north boundary line in the target area by taking one vertex of the west boundary line as a starting point location_11, and marking the defined point as location_1j, j=2, …, n until the east boundary line is reached; then, using location_11 as a starting point, defining a point at intervals of 1 meter to the south along a west boundary line until the south boundary line, and marking the defined point as location_i1, i=2, …, m; next, each point is defined at 1 meter intervals east along a line parallel to the north boundary line starting from location_i1, and the defined point is designated as location_ij until the east boundary line, thereby obtaining m×n positions of the target area; assuming that the target area is of other shapes, the target area can be defined into a plurality of positions with the same distance according to the dividing position mode of the rectangular area.
Step four, calculating telemetry starting time, telemetry ending time and measurement and control duration of each position one by one according to the direction angle of the ground measurement and control antenna aiming at a plurality of positions obtained in the target area;
Knowing t moment, the coordinates of the rocket position in a launching system are (x_L, y_L and z_L), the position of a certain ground measurement and control antenna selected at the moment is (xg, yg and zg), the direction angle of the ground measurement and control antenna is xi, and judging whether the connecting line of the ground measurement and control antenna-on-satellite antenna mounting position is in the direction angle of the ground measurement and control antenna in a z=zg plane or not, namely whether the following formula is established or not:
(y_L-yg)/(x_L-xg)>cot(ξ/2)
If the above formula is true, then the indication is in the telemetry visible range; otherwise, the indication is not in the telemetry visible range. And substituting the rocket position at each moment into the formula to judge, marking the earliest moment when the above formula is established as t_start, and marking the latest moment when the above formula is established as t_end. Therefore, when the ground measurement and control antenna is arranged at the position of (xg, yg, zg), the telemetry starting time is t_start, the telemetry ending time is t_end, and the measurement and control duration is tck=t_end-t_start;
And a second step of: and calculating corresponding telemetry starting time, telemetry ending time and measurement and control duration according to the steps aiming at each selected ground measurement and control antenna position.
Selecting a position meeting the requirements of the measurement and control time length and the start-stop time of receiving telemetry according to task requirements, and taking the position as a ground measurement and control antenna erection position; if the task requirement is that the measurement and control time is longest, selecting the position corresponding to the maximum measurement and control time as the erection position of the antenna; if the task requirement is that the telemetry starting time is earliest, selecting a position corresponding to the minimum value of the telemetry starting time as an erection position of the antenna; if the task requirement is that the telemetry ending time is the latest, selecting the corresponding position when the telemetry ending time is the maximum value as the erection position of the antenna.
The invention provides a method for determining the installation position of a ground measurement and control antenna, which is suitable for determining the position where the satellite measurement and control antenna is erected near a launch site by analyzing the time length conditions that the ground measurement and control antenna at different installation positions at different moments of a launch active section of a carrier rocket can receive telemetry when the carrier rocket launches satellites with wave transmission characteristics. The method mainly comprises five steps, namely setting input parameters, determining the coverage range of the satellite antenna to the ground at different moments, determining the possible antenna erection positions according to the terrain of a transmitting field, calculating the starting and stopping time and measurement and control duration of each position according to the direction angle of the ground measurement and control antenna, and completing the ground measurement and control antenna erection position calculation according to task requirements. The method can solve the problem that the satellite telemetry data cannot be received due to the lack of the ground measurement and control station in the active stage of launch of the carrier rocket at the present stage, and can be popularized to calculation of the installation position of the ground measurement and control antenna during the satellite orbit.
The invention is not described in detail in the field of technical personnel common knowledge.
Claims (6)
1. A method for determining the installation position of a ground measurement and control antenna is characterized by comprising the following steps of: comprising
Setting input parameters, including: the installation position and the installation angle of the satellite antenna main shaft in the satellite body system and the installation angle of the satellite in the carrier rocket body system; position and attitude angle information of a launch active section of the carrier rocket at different moments; a pattern of satellite antennas; the direction angle of the ground measurement and control antenna;
Calculating cut-off lines of the pattern boundaries of the satellite antennas at different moments and the ground level, and determining the coverage ranges of the satellite antennas at different moments to the ground;
According to the surrounding terrain of the transmitting field, removing water surfaces and mountains in the coverage area of the satellite antenna to the ground, selecting the rest available plain areas as target areas for erecting the ground measurement and control antenna, and uniformly dividing the target areas to obtain a plurality of positions as possible to erect the ground measurement and control antenna;
Aiming at a plurality of positions obtained in a target area, calculating telemetry starting time, telemetry ending time and measurement and control duration at each position one by one according to the direction angle of a ground measurement and control antenna;
selecting a position meeting the requirements of the measurement and control duration and the start and stop time of receiving telemetry according to task requirements, and taking the position as a ground measurement and control antenna installation position;
the implementation method for calculating the t moment cut-off line is as follows:
the first step: according to the position and attitude angle information of the launch active section t moment of the carrier rocket, determining the position of the antenna main shaft under the launch system t moment, specifically comprising the following steps:
Knowing the t moment, the coordinates of the rocket position in the launching system are Plv_fs= [ x_L, y_L, z_L ], wherein x_L, y_L and z_L respectively represent the distance of the projection of the rocket position on the horizontal plane along the launching direction, the distance of the rocket position along the vertical launching direction and the carrying elevation at the t moment; the attitude angles of the carrier rockets in 321 turn are LV_attitude= [ alpah _L, beta_L, gama_L ], alpah _L, beta_L and gama_L respectively represent the roll angle, pitch angle and yaw angle of the carrier at the moment t; the installation angle of the satellite in the carrier rocket body system is S_angle= [ phi_s, theta_s, psi_s ], the installation angle of the satellite antenna main shaft in the satellite body system is theta_sa= [ alpha_sa, beta_sa, gama_sa ], and the satellite antenna main shaft position under the launching system is calculated according to the following formula:
v_axis＝[A3(gama_L)×A2(beta_L)×A1(alpha_L)]-1×[A3(psi_s)×
A2(theta_s)×A1(phi_s)]-1×[A3(gama_sa)×A2(beta_sa)×
A1(alpha_sa)]-1×[0 0 1]
Wherein, A3 (i), A2 (j) and A1 (k) are respectively rotation matrixes under 321 rotation sequences, and the calculation formulas are as follows:
A3(i)＝[cos(i),sin(i),0；-1×sin(i),cons(i),0；0 0 1]；
A2(j)＝[cos(j),0,-1×sin(j)；0 1 0；sin(j),0,cons(j)]；
A1(k)＝[1 0 0；0cos(k),sin(k)；0-1×sin(k)cos(k)]；
Where i=gama_l, psi_s, gama_sa;
j＝beta_L,theta_s,beta_sa；
k＝alpha_L,phi_s,alpha_sa；
and a second step of: determining the z position of a cut-off line at the moment t according to the following calculation formula by utilizing the vertical relation between the main axis of the satellite antenna and the cut-off line:
z＝{2/(x1_jz-x2_jz)}×x+{1-2×x1_jz/(x1_jz-x2_jz)}
Wherein (x1_jz, 0, 1), (x2_jz, 0, -1) is the coordinates of two points on the cut-off line;
the formulas of x1_jz and x2_jz are as follows:
x1_jz＝x_L+{y_L×v_axis×[0 1 0]-(1-z_L×v_axis×[0 0 1])}/{v_axis×[10 0]}
x2_jz＝x_L+{y_L×v_axis×[0 1 0]-(-1-z_L×v_axis×[0 0 1])}/{v_axis×[1 0 0]}；
the realization mode of uniformly dividing the target area to obtain a plurality of positions as the positions for possibly erecting the ground measurement and control antenna is as follows:
Assuming that the target area is rectangular, defining a point at intervals of 1 meter to the east along the north boundary line in the target area by taking one vertex of the west boundary line as a starting point location_11, and marking the defined point as location_1j, j=2, …, n until the east boundary line is reached; then, using location_11 as a starting point, defining a point at intervals of 1 meter to the south along a west boundary line until the south boundary line, and marking the defined point as location_i1, i=2, …, m; next, each point is defined at 1 meter intervals east along a line parallel to the north boundary line starting from location_i1, and the defined point is designated as location_ij until the east boundary line, thereby obtaining m×n positions of the target area;
The method for calculating the telemetry starting time, telemetry ending time and measurement and control duration at each position comprises the following steps:
Knowing t moment, the coordinates of the rocket position in a launching system are (x_L, y_L and z_L), the position of a certain ground measurement and control antenna selected at the moment is (xg, yg and zg), the direction angle of the ground measurement and control antenna is xi, and judging whether the connecting line of the ground measurement and control antenna-on-satellite antenna mounting position is in the direction angle of the ground measurement and control antenna in a z=zg plane or not, namely whether the following formula is established or not:
(y_L-yg)/(x_L-xg)>cot(ξ/2)
If the above formula is satisfied, the indication is in the telemetry visible range, otherwise, the indication is not in the telemetry visible range; substituting rocket position at each moment into the formula to judge, marking the earliest moment of the establishment of the formula as t_start and the latest moment of the establishment of the formula as t_end, so when the ground measurement and control antenna is arranged at the position of (xg, yg, zg), the telemetry starting time is t_start, the telemetry ending time is t_end, and the measurement and control duration is tck=t_end-t_start;
And a second step of: and calculating corresponding telemetry starting time, telemetry ending time and measurement and control duration according to the steps aiming at each selected ground measurement and control antenna position.
2. The method for determining the installation position of the ground measurement and control antenna according to claim 1, wherein the method comprises the following steps: the pattern of the satellite antenna is set to a fixed value of 2pi.
3. The method for determining the installation position of the ground measurement and control antenna according to claim 1, wherein the method comprises the following steps: setting the direction angle of the ground measurement and control antenna to be xi, 0 degree < xi <90 degrees, and setting the direction angle of the antenna to be a fixed value after the installation is finished.
4. The method for determining the installation position of the ground measurement and control antenna according to claim 1, wherein the method comprises the following steps: according to task requirements, selecting a position meeting requirements of measurement and control duration and start and stop time of receiving telemetry, and taking the position as a ground measurement and control antenna installation position, wherein the implementation mode is as follows:
If the task requirement is that the measurement and control time is longest, selecting the position corresponding to the maximum measurement and control time as the erection position of the antenna; if the task requirement is that the telemetry starting time is earliest, selecting a position corresponding to the minimum value of the telemetry starting time as an erection position of the antenna; if the task requirement is that the telemetry ending time is the latest, selecting the corresponding position when the telemetry ending time is the maximum value as the erection position of the antenna.
5. The method for determining the installation position of the ground measurement and control antenna according to claim 1, wherein the method comprises the following steps: the carrier rocket is a carrier rocket with a wave-transparent window.
6. The method for determining the installation position of the ground measurement and control antenna according to claim 1, wherein the method comprises the following steps: the installation position and the installation angle of the satellite antenna main shaft in the satellite body system and the installation angle of the satellite in the carrier rocket body system are obtained by measurement before satellite launching.
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| CN111427002A (en) * | 2020-03-19 | 2020-07-17 | 上海卫星工程研究所 | Azimuth angle calculation method for ground measurement and control antenna pointing satellite |
| CN111661366A (en) * | 2020-05-27 | 2020-09-15 | 上海卫星工程研究所 | Radome wave-transmitting port arrangement method suitable for satellite wave-transmitting requirements |
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| CN111427002A (en) * | 2020-03-19 | 2020-07-17 | 上海卫星工程研究所 | Azimuth angle calculation method for ground measurement and control antenna pointing satellite |
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