CN107330136B - Layout method of remote sensing satellite navigation antenna suitable for double-side-view work - Google Patents
Layout method of remote sensing satellite navigation antenna suitable for double-side-view work Download PDFInfo
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- CN107330136B CN107330136B CN201710344896.9A CN201710344896A CN107330136B CN 107330136 B CN107330136 B CN 107330136B CN 201710344896 A CN201710344896 A CN 201710344896A CN 107330136 B CN107330136 B CN 107330136B
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- G06F2119/08—Thermal analysis or thermal optimisation
Abstract
The invention discloses a layout method of a remote sensing satellite navigation antenna suitable for double-side-view work, which comprises the following steps: step one, finding out an available single machine layout space outside a satellite body by utilizing whole satellite three-dimensional model analysis according to configuration layout space constraint of a double-side-view working remote sensing satellite, and determining an available layout space position with minimum single machine shielding; and step two, according to the performance and the available space position of the navigation antenna, carrying out simulation analysis on the captured star number of the navigation antenna, and determining the optimal pointing direction and the like of the navigation antenna at the star body layout position according to the simulation result. The invention solves the problem of the layout of the navigation antenna of a certain bilateral-view working remote sensing satellite, and increases the available effective field of view of the navigation antenna in a common working mode and the number of the navigation satellites which can be captured in orbit, thereby improving the in-orbit positioning and speed measuring precision of the satellite, reducing the measurement error of the in-orbit running orbit of the satellite and laying a solid foundation for the high-resolution imaging of the load antenna.
Description
Technical Field
The invention relates to the technical field of satellite overall design, in particular to a layout method of a remote sensing satellite navigation antenna suitable for double-side-view work.
Background
With the rapid development of satellite technology, the problem that the improvement of high-resolution imaging quality is urgently needed to be solved by satellite models is solved, the influence of orbit measurement errors needs to be eliminated in remote sensing satellite imaging, the on-orbit flight is realized in a side-view working mode on a general satellite, the imaging resolution ratio is relatively low, the influence of the satellite orbit measurement errors can be solved by adopting a ground or on-satellite measuring mode at the moment, but with the increase of task requirements of a satellite on a double side-view working mode, the higher-resolution imaging quality and the like, the influence of the orbit measurement errors on positioning is reduced, and high-precision navigation orbit measurement data are directly adopted in ground imaging processing. The accuracy of the navigation orbit determination data depends to a large extent on the effective field of view of the navigation antenna and the number of the navigation satellites that can be captured by the navigation antenna. Due to the limitation of the satellite configuration layout space, the space outside the satellite for the layout of the navigation antenna is easily shielded and influenced by nearby measurement and control antennas, data transmission antennas, relay antennas and the like, so that a navigation antenna layout design method which can adapt to a double-side-view working remote sensing satellite is needed to improve the effective view field of the satellite navigation antenna and capture the number of navigation satellites, thereby improving the navigation orbit measurement data accuracy received by the satellite and ensuring the imaging resolution of the satellite.
At present, no explanation or report of the similar technology of the invention is found, and similar data at home and abroad are not collected.
Disclosure of Invention
The invention aims to solve the technical problem of providing a layout method of a navigation antenna suitable for a double-side-view working remote sensing satellite, which solves the problem of the layout of the navigation antenna of a certain double-side-view working remote sensing satellite, and improves the positioning and speed measuring accuracy of the satellite in orbit by increasing the available effective field of view of the navigation antenna in a common working mode and the number of the navigation satellites capable of being captured in orbit, thereby reducing the measurement error of the satellite in-orbit running orbit and laying a solid foundation for the high-resolution imaging of a load antenna.
The invention solves the technical problems through the following technical scheme: a layout method suitable for double-side-view working remote sensing satellite navigation antenna comprises the following steps:
step one, finding out an available single machine layout space outside a satellite body by utilizing whole satellite three-dimensional model analysis according to configuration layout space constraint of a double-side-view working remote sensing satellite, and determining an available layout space position with minimum single machine shielding;
carrying out simulation analysis on the captured star number of the navigation antenna according to the performance and the available space position of the navigation antenna, and determining the optimal pointing direction of the navigation antenna at the star body layout position according to the simulation result;
thirdly, according to the restraint of an 85-degree cone of the navigation antenna with the antenna potential center as the origin, a maximum available view field analysis model of the navigation antenna is manufactured, and view field shielding analysis of the navigation antenna is carried out on the whole satellite three-dimensional model;
and step four, designing the navigation antenna support according to the mechanical interface and the thermal environment constraint of the layout position of the navigation antenna, and carrying out mechanical analysis and thermal analysis of the navigation antenna support.
Preferably, the on-orbit working mode of the double-side-view working remote sensing satellite is that the double-side-view working remote sensing satellite swings around a rolling shaft in a left-right side mode by 35 degrees, flies around the rolling shaft in a left-side view mode by clockwise rotation, flies around the rolling shaft in a right-side view mode by anticlockwise rotation, and is a normal working mode in a right-side view state and a maneuvering working mode in a left-side view state.
Preferably, the navigation antenna is a BD2/GPS navigation antenna or a BD2/GPS dual-frequency navigation antenna, and the maximum field angle of the navigation antenna is a cone angle of 85 degrees around an optical axis.
Preferably, the axis of the BD2/GPS navigation antenna points at an optimal angle of 10 degrees with respect to the fixed longitudinal axis of the star.
The positive progress effects of the invention are as follows: the invention solves the problem of the layout of the navigation antenna of a certain bilateral-view working remote sensing satellite, and increases the available effective field of view of the navigation antenna in a common working mode and the number of the navigation satellites which can be captured in orbit, thereby improving the in-orbit positioning and speed measuring precision of the satellite, reducing the measurement error of the in-orbit running orbit of the satellite and laying a solid foundation for the high-resolution imaging of the load antenna.
Drawings
FIG. 1 is a flow chart of the present invention.
Detailed Description
The following provides a detailed description of the preferred embodiments of the present invention with reference to the accompanying drawings.
As shown in FIG. 1, the layout method of the remote sensing satellite navigation antenna suitable for double-side-view working comprises the following steps:
step one, finding out an available single machine layout space outside a satellite body by utilizing whole satellite three-dimensional model analysis according to configuration layout space constraint of a double-side-view working remote sensing satellite, and determining an available layout space position with minimum single machine shielding;
carrying out simulation analysis on the captured star number of the navigation antenna according to the performance and the available space position of the navigation antenna, and determining the optimal pointing direction of the navigation antenna at the star body layout position according to the simulation result;
thirdly, according to the restraint of an 85-degree cone of the navigation antenna with the antenna potential center as the origin, a maximum available view field analysis model of the navigation antenna is manufactured, and view field shielding analysis of the navigation antenna is carried out on the whole satellite three-dimensional model;
and step four, designing the navigation antenna support according to the mechanical interface and the thermal environment constraint of the layout position of the navigation antenna, and carrying out mechanical analysis and thermal analysis of the navigation antenna support.
The on-orbit working mode of the double-side-view working remote sensing satellite is that the satellite swings around a rolling shaft by 35 degrees in a left-right side mode, flies around the rolling shaft in a left-side view mode when rotating clockwise, flies around the rolling shaft in a right-side view mode when rotating anticlockwise, and is a normal working mode in a right-side view state and a maneuvering working mode in a left-side view state, so that the flexibility is improved.
The navigation antenna is a BD2/GPS navigation antenna or a BD2/GPS dual-frequency navigation antenna, and the maximum field angle of the navigation antenna is a cone angle of 85 degrees around an optical axis, so that the signal strength is enhanced.
The axis of the BD2/GPS navigation antenna is pointed at an optimum angle of 10 ° to the fixed longitudinal axis of the star, which improves accuracy.
The detailed description is given by combining a BD2 (second generation beidou navigation System)/GPS (global positioning System) navigation antenna layout of a double-side view remote sensing satellite.
A certain bilateral-view working remote sensing satellite can realize 70-degree large-amplitude maneuver around a rolling shaft in an orbit flying state, wherein the left-side view flying state is realized by clockwise rotating around the rolling shaft by 35 degrees, the right-side view flying state is realized by anticlockwise rotating around the rolling shaft by 35 degrees, the right-side view state is a normal working mode, and the left-side view state is a maneuvering working mode.
According to the satellite configuration layout space constraint, as the load antenna, the data transmission antenna, the relay antenna, the two-wing solar cell array and other large parts exist outside the satellite body, the space of four side surfaces outside the satellite body is basically unavailable, and the BD2/GPS navigation antenna needs to work in an on-orbit mode to maximize the field of view of the sky, so that the available layout space of the navigation antenna in the whole satellite is basically limited on the bottom plate of the satellite. Meanwhile, through the acquisition efficiency analysis and the satellite electromagnetic compatibility analysis of the satellite BD2/GPS navigation antenna, the result shows that when the navigation antenna forms an included angle of 45 degrees with the opposite heaven axis of the satellite and forms an included angle of 10 degrees with the longitudinal axis of the satellite, the navigation antenna inclines towards the interior of the satellite, and the height from the bottom plate of the satellite is 210mm, the maximum effective field of view (above the horizon and without shielding) of the navigation antenna under the orbit right side viewing state can reach 150 degrees, the minimum number of captured stars can be 5, the average number of stars is 8.5, the position measurement precision of the satellite can reach 10m (three-axis synthesis), the speed measurement precision reaches 0.05m/s (three-axis synthesis), data can be provided in real time, finally, the ground verification test is carried out according to the design state, and the results of simulation analysis and ground verification test show that the design can meet the navigation orbit measurement precision requirement of the high-resolution.
Under the layout position and the antenna pointing state, a field-of-view analysis model of the navigation antenna is manufactured by combining the performance of the 85-degree maximum cone angle of the BD2/GPS navigation antenna, detailed shielding condition analysis is carried out on the whole satellite three-dimensional model, and an analysis result shows that the effective field of view of the navigation antenna can meet the use requirements of the satellite in the on-orbit left-right side-viewing state.
The mechanical interface of the mounting flange of the BD2/GPS navigation antenna is that 3 phi 4.5mm round holes are uniformly distributed on a circle with the diameter phi of 60mm, wherein phi represents the diameter, and the axes of threaded hole embedded parts in a star bottom plate are vertical to the bottom plate; in the environment thermal environment of the sun synchronous orbit, the environment is periodically influenced by sunlight. Therefore, three threaded holes with the model number of M4 are pre-embedded in the corresponding layout position on the satellite bottom plate, the detailed design of the navigation antenna support is developed, the requirement that the included angle between the axis direction of the BD2/GPS navigation antenna and the fixed longitudinal axis of the satellite is 10 degrees is realized through the navigation antenna support, the weight of the support is not more than 1kg, and the results show that the strength, the mechanical response and the like of the support meet the normal working requirements of the BD2/GPS navigation antenna through structural simulation analysis and mechanical test verification; the white paint spraying treatment is carried out on the navigation antenna bracket, and the results of thermal simulation analysis and thermal vacuum test verification show that the thermal control measures meet the on-orbit working temperature requirements of the BD2/GPS navigation antenna and the bracket.
The invention provides a new design idea for the layout method for improving the working efficiency of the navigation antenna on the double-side vision remote sensing satellite, the design method becomes the first choice of the general satellite designer, and the invention can be widely applied in the field.
The above embodiments are described in further detail to solve the technical problems, technical solutions and advantages of the present invention, and it should be understood that the above embodiments are only examples of the present invention and are not intended to limit the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (4)
1. A layout method suitable for double-side-view working remote sensing satellite navigation is characterized by comprising the following steps:
step one, finding out an available single machine layout space outside a satellite body by utilizing whole satellite three-dimensional model analysis according to configuration layout space constraint of a double-side-view working remote sensing satellite, and determining an available layout space position with minimum single machine shielding;
carrying out simulation analysis on the captured star number of the navigation antenna according to the performance and the available space position of the navigation antenna, and determining the optimal pointing direction of the navigation antenna at the star body layout position according to the simulation result;
thirdly, according to the restraint of an 85-degree cone of the navigation antenna with the antenna potential center as the origin, a maximum available view field analysis model of the navigation antenna is manufactured, and view field shielding analysis of the navigation antenna is carried out on the whole satellite three-dimensional model;
and step four, designing the navigation antenna support according to the mechanical interface and the thermal environment constraint of the layout position of the navigation antenna, and carrying out mechanical analysis and thermal analysis of the navigation antenna support.
2. The method as claimed in claim 1, wherein the dual side-looking working remote sensing satellite has an in-orbit working mode of swinging 35 ° left and right around the rolling axis, rotating clockwise around the rolling axis as left-side view flight, rotating counterclockwise around the rolling axis as right-side view flight, and a normal working mode in a right-side view state and a maneuvering working mode in a left-side view state.
3. The method for laying out a dual side-looking working remote sensing satellite navigation antenna suitable for use according to claim 1, wherein the navigation antenna is a BD2/GPS navigation antenna or a BD2/GPS dual-band navigation antenna, and the maximum field angle of the navigation antenna is an 85 ° cone angle around the optical axis.
4. The method for laying out the antenna suitable for the double-side-view remote sensing satellite navigation antenna according to claim 3, wherein the axis of the BD2/GPS navigation antenna points to form an optimal included angle of 10 degrees with the fixed longitudinal axis of the satellite body.
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102508260A (en) * | 2011-11-30 | 2012-06-20 | 武汉大学 | Geometric imaging construction method for side-looking medium resolution ratio satellite |
| CN105035358A (en) * | 2015-07-31 | 2015-11-11 | 上海卫星工程研究所 | In-orbit expansion-type satellite structure |
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| US8917207B2 (en) * | 2007-10-16 | 2014-12-23 | Livetv, Llc | Aircraft in-flight entertainment system having a multi-beam phased array antenna and associated methods |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102508260A (en) * | 2011-11-30 | 2012-06-20 | 武汉大学 | Geometric imaging construction method for side-looking medium resolution ratio satellite |
| CN105035358A (en) * | 2015-07-31 | 2015-11-11 | 上海卫星工程研究所 | In-orbit expansion-type satellite structure |
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