CN113919048A - Modular configuration layout method adaptive to satellite incremental load change - Google Patents

Modular configuration layout method adaptive to satellite incremental load change Download PDF

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CN113919048A
CN113919048A CN202110988391.2A CN202110988391A CN113919048A CN 113919048 A CN113919048 A CN 113919048A CN 202110988391 A CN202110988391 A CN 202110988391A CN 113919048 A CN113919048 A CN 113919048A
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cabin
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梁翠娜
周耀华
嵇景全
丛飞
周孝伦
王东
吴振宇
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China Academy of Space Technology CAST
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Abstract

A modular configuration layout method for adapting to satellite incremental load change comprises the following steps: step A: according to the satellite configuration layout design baseline, determining the balance of weight, heat consumption, layout area in the cabin and layout area outside the cabin as expandable resources by calculating the difference between the total resource amount of the new satellite configuration and the total resource amount of the satellite configuration layout design baseline, including the difference between the weight, the heat consumption, the layout area in the cabin and the layout area outside the cabin; and B: dividing the satellite into a basic module and an increment module; and C: calculating resources required by the incremental load according to the satellite matching files; step D: judging the resource satisfaction, and performing layout feasibility analysis; step E: and performing incremental module layout according to the mechanical, electrical and thermal interfaces of the incremental load and the requirements of view field, installation precision and electromagnetic compatibility. The invention meets the layout requirements of different load configurations of the satellite and can quickly adapt to incremental load layout and switching of various incremental configurations.

Description

Modular configuration layout method adaptive to satellite incremental load change
Technical Field
The invention relates to a satellite modular configuration layout method, and belongs to the field of satellite overall design.
Background
The development of the spacecraft is a complex system engineering, how to complete the configuration layout design of the spacecraft in a limited size envelope, provide the working conditions of each device, achieve various indexes of flight tasks, and is a main problem to be solved by the configuration layout design of the spacecraft.
For mass produced satellites, it is difficult to avoid situations where the external environment changes, the payload requirement changes, or the inside of the satellite changes, so each satellite has its own personality in addition to the commonality of the model satellite. Because the satellites produced in batch have the characteristics of small batch, various configuration states and different technical states, compared with the development of a single satellite, the satellites in batch have different states, and higher requirements are provided for the configuration layout design of the satellites. Meanwhile, with cognitive progress and new technology development, a user can put forward new requirements on functions and indexes of the satellite, and the configuration layout design of the satellite can meet the requirements of incremental development and function expansion.
The configuration layout design of the current satellite generally determines the configuration and layout of the satellite at the initial design stage according to the determined task requirement, if the task requirement changes, the configuration layout design needs to be newly developed or modified on the basis of the original configuration, and the new design or modification project is generally high in complexity, large in workload, long in development period, high in cost and easy to cause interference or other quality problems.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the modular configuration layout method suitable for satellite incremental load change is provided for overcoming the defects of the prior art and aiming at the requirements of task expansion and incremental load configuration of mass production satellites, can be suitable for the layout requirements of different load configurations of satellites, and can be quickly suitable for incremental load layout and switching of multiple incremental configurations.
The technical scheme adopted by the invention is as follows: a modular configuration layout method for adapting to satellite incremental load change comprises the following steps:
step A: according to the satellite configuration layout design baseline, determining the balance of weight, heat consumption, layout area in the cabin and layout area outside the cabin by calculating the difference between the total resource amount of the new satellite configuration and the total resource amount of the satellite configuration layout design baseline, including the difference between the weight, the heat consumption, the layout area in the cabin and the layout area outside the cabin, as expandable resources, specifically as follows:
the weight balance is as follows:
Figure BDA0003231585090000021
heat loss allowance:
Figure BDA0003231585090000022
layout area allowance in the cabin:
Figure BDA0003231585090000023
extra-cabin layout area allowance:
Figure BDA0003231585090000024
and B: dividing the satellite into a basic module and an increment module;
the mode of dividing the basic module and the incremental module is as follows: designing a base line according to configuration layout, and taking a fixed and non-detachable structural plate in a satellite configuration and equipment mounted on the structural plate as a basic module; and the detachable structural plate, the secondary structural plate which can be further expanded and the equipment mounted on the secondary structural plate are used as incremental modules.
And C: calculating resources required by the incremental load according to the satellite matching files;
according to the satellite matching file, n types of incremental loads are determined: x1，X2，…，Xi，…，Xn(ii) a Respectively calculating the sum of the weight, the heat consumption, the layout area in the cabin and the layout area outside the cabin required by the n incremental loads, wherein the formula is as follows:
Figure BDA0003231585090000031
Miweight of the i-th incremental load, TiHeat rate for the ith incremental load, SiRequired cabin layout area and V for ith incremental loadiThe outboard layout area is the ith incremental load; 1,2,3, n, n is a positive integer;
step D: judging the resource satisfaction, and performing layout feasibility analysis;
and D, completing the preliminary feasibility analysis of the configuration layout according to the satisfaction condition of the resource expansion allowance calculated in the step A to the resource required by the incremental load calculated in the step C, wherein the constraint conditions are as follows:
Figure BDA0003231585090000032
specifically, there are 4 cases according to the interpretation results:
a. if the weight, the heat consumption, the layout area in the cabin and the layout area outside the cabin meet the requirements, entering the step E;
b. if any one of the weight, the heat consumption and the layout area in the cabin does not meet the requirement, optimizing the incremental load, reducing the weight, the heat consumption and the layout area of the incremental load, returning to the step C, and recalculating resources required by the incremental load until the requirements are met;
c. if the weight, the heat consumption and the layout area in the cabin meet the requirements and the layout area outside the cabin does not meet the requirements, two measures are taken:
optimizing the incremental load to reduce the required layout area outside the cabin;
expanding the deck within the carrying envelope limit, and expanding the layout area resources outside the deck by adding a secondary structure so as to meet the installation requirement of incremental load;
d. after optimization, if one or more of the weight, the heat consumption, the layout area in the cabin and the layout area outside the cabin are not qualified, the layout is not feasible under the configuration, and the platform needs to be replaced or the configuration number of incremental loads needs to be reduced.
Step E: performing incremental module layout according to mechanical, electrical and thermal interfaces of incremental loads, and visual field requirements, installation accuracy requirements and electromagnetic compatibility requirements;
specifically, the method comprises the following steps:
if the constraint requirements of a) and b) in the step D are met, independently arranging the incremental load on a detachable structural plate;
if the constraint requirement of c) in the step D is met, adding a secondary structural plate on the satellite, and installing incremental load on the secondary structural plate.
Compared with the prior art, the invention has the advantages that:
(1) the invention provides a modularized configuration layout method adapting to satellite incremental load change, which adopts modularized extension design to divide a satellite into a basic module and an incremental load module, and resources such as weight, power consumption, layout area and the like have extension allowance on the basis of a satellite configuration layout design baseline;
(2) the method provided by the invention can realize rapid configuration layout design by changing or adding the incremental module on the basis of the basic configuration; an independent standard interface is designed on the main structure, and the standard interface can adapt to structural plates in various technical states and meet the configuration requirements of various incremental loads;
(3) according to the method provided by the invention, the secondary structure is fixed on the main structure of the whole satellite, so that main load is not transferred, and the structure of the fundamental frequency and the vibration mode of the whole satellite is not obviously influenced; the replacement of the incremental load module can be realized, and the incremental configuration switching can be quickly adapted; the incremental module can be disassembled for multiple times;
(4) the method provided by the invention has the advantages that modular design and assembly are realized, and development of a main line of a decoupling satellite and development of incremental loads are realized; in the aspects of configuration layout and process planning, the flexible and adjustable capacity is provided; in the aspect of process planning, incremental load development is parallel to whole-satellite development, and a plurality of entry points are created for integrating the incremental load into the whole-satellite development process.
Drawings
FIG. 1 is a flow chart of a method for modular configuration placement to accommodate incremental satellite load changes;
FIG. 2 is a diagram of a truss-type platform satellite configuration;
FIG. 3 is a diagram of a satellite configuration for a type I incremental load configuration scheme;
FIG. 4 is a diagram of a satellite configuration for a type II, III incremental load configuration scheme;
FIG. 5(a) is a layout view of the inner surface of the load compartment-X plate under the type I incremental load configuration;
FIG. 5(b) is a layout view of the outer surface of the load compartment-X plate under the type I incremental load configuration scheme;
FIG. 6(a) is a layout view of the inner surface of the X plate of the load compartment under the type II incremental load configuration scheme;
FIG. 6(b) is a layout of the outer surface of the X plate and the independent capsule of the lower load capsule of the type II incremental load configuration scheme;
FIG. 6(c) is a layout diagram of the independent cabin outside the lower load cabin + X plate of the type II incremental load configuration scheme;
FIG. 7(a) is a layout view of the inner surface of the load compartment-X plate under a type III incremental load configuration scheme;
FIG. 7(b) is a layout of the outer surface of the X plate and the independent capsule of the load capsule under the type III incremental load configuration scheme;
FIG. 7(c) is a layout diagram of the independent cabin outside the load cabin + X plate under the type III incremental load configuration scheme;
fig. 8 is a diagram of the matching of incremental load and whole star development process.
Detailed Description
The invention is explained with reference to the figures and the examples.
As shown in fig. 1, a method for arranging a modular configuration to adapt to incremental load changes of a satellite includes the following steps:
step A: and calculating extensible resources according to the satellite configuration layout design baseline.
The configuration layout design baseline in step a is: formally confirmed and used as a design reference of the future configuration layout; according to a satellite configuration layout design baseline, determining the balance of weight, heat consumption, layout area in the cabin and layout area outside the cabin as expandable resources by calculating the total amount of resources such as weight, heat consumption, layout area in the cabin and layout area outside the cabin which are closely related to configuration layout design and the difference value of the weight, the heat consumption, the layout area in the cabin and the layout area outside the cabin in the baseline scheme, wherein the expandable resources are as follows:
weight:
Figure BDA0003231585090000061
heat consumption:
Figure BDA0003231585090000062
layout area in the cabin:
Figure BDA0003231585090000063
layout area outside the cabin:
Figure BDA0003231585090000064
and B: the satellite is divided into a base module and an incremental module.
B, dividing the basic module and the incremental module in the step B, designing a base line according to the configuration layout, and taking a fixed and non-detachable structural plate in the satellite configuration and equipment installed on the structural plate as the basic module; and the detachable structural plate, the secondary structural plate which can be further expanded and the equipment mounted on the secondary structural plate are used as incremental modules.
And C: and calculating the resources required by the incremental load according to the satellite matching file.
In the step C, according to the satellite matching files, the incremental loads are n types:
X1，X2，…，Xi，…，Xn(ii) a Respectively calculating the weight, the heat consumption, the layout area in the cabin and the layout area outside the cabin required by the incremental load, wherein the specific method comprises the following steps:
the weight, heat consumption, required layout area in the cabin and layout area outside the cabin of the ith increment load are respectively Mi，Ti，Si，ViThe total resources required by the incremental load are as follows:
Figure BDA0003231585090000071
step D: judging the resource satisfaction, and carrying out layout feasibility analysis.
And D, completing the preliminary feasibility analysis of the configuration layout according to the satisfaction condition of the resource expansion allowance calculated in the step A to the resource required by the incremental load calculated in the step C, wherein the constraint conditions are as follows:
Figure BDA0003231585090000072
wherein, the weight, the heat consumption and the layout area in the cabin are strong constraints, and if the constraint conditions are not met, the next step of work cannot be carried out; the layout area outside the cabin is weakly restricted, and if the constraint condition is not met, the layout requirement can be met by adding the secondary structural plate. Specifically, there are 4 cases according to the interpretation results:
a) the weight, the heat consumption, the layout area in the cabin and the layout area outside the cabin all meet the requirements, and the next step of work can be carried out to develop detailed layout design.
b) And any one of the weight, the heat consumption and the layout area in the cabin does not meet the requirement, the incremental load is optimized, the weight, the heat consumption, the layout area and the like of the load are reduced, and the incremental load is further iterated with the overall design until the incremental load meets the requirement.
c) The weight, the heat consumption and the layout area in the cabin meet the requirements, the layout area outside the cabin does not meet the requirements, and two measures can be taken:
optimizing the incremental load to reduce the required layout area outside the cabin;
secondly, the cabin plate is expanded within the carrying envelope limit, and the layout area resources outside the cabin are expanded by adding a secondary structure so as to meet the installation requirement of incremental load.
d) After optimization, one or more of the weight, the heat consumption, the layout area in the cabin and the layout area outside the cabin are still not qualified, which indicates that the layout is not feasible under the configuration, and the platform needs to be replaced or the configuration quantity of incremental load needs to be reduced.
Step E: and (4) designing the incremental load detailed layout.
And step E, developing the detailed layout design of the incremental module according to the mechanical, electrical and thermal interfaces of the incremental load, the requirement of a view field, the requirement of installation precision and the requirement of electromagnetic compatibility.
Specifically, the method comprises the following steps:
meeting the constraint requirements of a) and b) in the step D), and independently arranging the incremental load on a detachable structural plate;
and step two, satisfying the constraint requirement of step D), adding a secondary structural plate on the satellite, and installing the incremental load on the secondary structural plate.
The changeable structural plate and the equipment installed on the changeable structural plate are used as independent incremental modules in the two methods, and the configuration and layout design of other fixed satellites are not influenced.
Examples
Taking a certain truss type platform satellite as an example, the specific implementation steps of the invention are as follows:
1) taking a configuration layout scheme of a certain truss type platform satellite only matched with basic loads as a design baseline, calculating the total weight, total heat consumption, total layout area in the cabin and total layout area constraint outside the cabin of the satellite, calculating the weight, heat consumption, layout area in the cabin and layout area outside the cabin of the baseline scheme, and calculating the expandable allowance of the weight, heat consumption, layout area in the cabin and layout area outside the cabin of the baseline scheme, wherein the expandable allowance is as follows:
Figure BDA0003231585090000091
2) as shown in fig. 2, the main force-bearing structure of the truss-type platform satellite is a cuboid truss structure and is divided into a platform and a load cabin, wherein the load cabin comprises a load cabin + Z plate 1, a load cabin + Y plate 2, a load cabin-Y plate 3, a load cabin + X plate 4 and a load cabin-X plate 5. The platform 6 does not involve incremental change, and the load cabin + Z plate 1, the load cabin + Y plate 2 and the load cabin-Y plate 3 are fixed structural plates and are not detachable, so that the platform 6, the load cabin + Z plate 1, the load cabin + Y plate 2 and the load cabin-Y plate 3, and equipment mounted on the structural plates are divided into basic modules; the load compartment + X-plate 4, the load compartment-X-plate 5 as a detachable structural plate, together with a secondary structural plate on which it can be further expanded, will be used for the expanded installation of incremental load devices as incremental modules.
3) The incremental loads related to a certain truss type platform satellite are 5 kinds, X1，X2，X3，X4，X5The weight, heat consumption, layout area in the cabin and layout area outside the cabin of the 5 kinds of incremental loads are respectively as follows:
Figure BDA0003231585090000101
according to satellite matching files, the truss type platform satellite has three incremental load configuration schemes of type I, type II and type III. Wherein, type I scheme configuration X1，X2，X4Three incremental load, type II scheme configuration X1，X3，X4Three incremental load, type III scenario configuration X1，X3，X5Three incremental loads.
Respectively calculating the weight, heat consumption, layout area in the cabin and layout area outside the cabin required by the incremental load under the three configuration schemes, specifically as follows:
the weight, heat consumption, layout area in the cabin and layout area outside the cabin of the I-type satellite are as follows:
Figure BDA0003231585090000102
the weight, heat consumption, layout area in the cabin and layout area outside the cabin of the II type satellite are as follows:
Figure BDA0003231585090000103
the weight, heat consumption, layout area in the cabin and layout area outside the cabin of the type III satellite are as follows:
Figure BDA0003231585090000104
4) and judging the satisfaction conditions of the resources required by the incremental load under the three configuration schemes calculated in the step C according to the resource expansion allowance calculated in the step A:
the interpretation results of the weight, heat consumption, layout area in the cabin and layout area outside the cabin of the I-type configuration scheme are as follows:
Figure BDA0003231585090000111
the interpretation results of the weight, heat consumption, layout area in the cabin and layout area outside the cabin of the type II configuration scheme are as follows:
Figure BDA0003231585090000112
the interpretation results of the weight, heat consumption, layout area in the cabin and layout area outside the cabin of the type III configuration scheme are as follows:
Figure BDA0003231585090000113
the resource margin under the type I configuration scheme meets the incremental load requirement, and a detailed layout design can be further developed on the load compartment-X board shown in fig. 3.
Under the type II and type III configuration schemes, the incremental load X is configured3The required extra-cabin layout area is large, and the current extra-cabin layout area allowance cannot meet the increment load requirement. For type II and type III configurations, the satellite architecture is expanded and secondary architectures are added, as shown in FIG. 4, to incrementally load X3Mounted on a separate capsule 7.
5) And developing the detailed layout design of the incremental module according to the mechanical, electrical and thermal interfaces of the incremental load, the requirement of a view field, the requirement of installation precision and the requirement of electromagnetic compatibility.
Wherein, the type I configuration scheme loads the increment X 18. Incremental load X2In-cabin equipment 9, incremental load X4Is mounted on the inner surface of the load compartment-X plate 5, the incremental load X2Outboard equipment 11 and incremental load X4The outboard equipment 12 of (a) is mounted on the outer surface of the load compartment-X plate 5, see fig. 5(a), 5(b) for a detailed layout. In fig. 5(a) and 5 (b): incremental load X4Installation of the extra-cabin equipment 12 at incremental load X2Below the outboard equipment 11, wherein an incremental load X4The height of the outer part of the cabin from the cabin plate is 40mm, and the incremental load X is2The height of the outboard section from the deck plate is 90 mm.
Type II configuration scheme, loading increments X 18. Incremental load X4In-cabin equipment 10, incremental load X3Is mounted on the inner surface of the load compartment-X plate 5; incremental load X4The outboard equipment 12 is mounted on the outer surface of the load compartment-X plate 5; and independent cabins 7 are respectively added outside the-X plate 5 and the + X plate 4 of the load cabin to increase the load X3The extra-cabin equipment 14 is mounted on the individual cabin 7, see fig. 6(a) - (c) for a detailed layout.
Type III configuration scheme for loading increments of X 18. Incremental load X3In-cabin equipment 13, incremental load X5Is mounted on the inner surface of the load compartment-X plate 5; incremental load X5Outboard equipment 16AIs arranged on the outer surface of the load compartment-X plate 5; and independent cabins 7 are respectively added outside the-X plate 5 and the + X plate 4 of the load cabin to increase the load X3The extra-cabin equipment 14 is mounted on the individual cabin 7, see fig. 7(a) - (c) for a detailed layout.
6) According to the design of the fig. 5(a), the fig. 5(b), the fig. 6(a) - (c) and the fig. 7(a) - (c), the load cabin-X plate 5 and the independent cabin 7 which are suitable for the type I, the type II and the type III configuration schemes are respectively put into production, after the structural plate and the incremental load equipment are delivered, the structural plate and the incremental load equipment are assembled into an incremental module, and the test work of the incremental load is carried out on the incremental module. And integrally replacing the increment module at a proper time according to the development process of the satellite.
The modular configuration layout scheme enables the incremental modules to be relatively independent, and the integration with the whole satellite development process has flexible and adjustable capacity. As shown in fig. 8, the entry point may be selected at a plurality of timings before a large-scale test, before shipment, and the like.
It should be understood that the above description is only an example of the present invention, and is not intended to limit the present invention. Any changes or substitutions that may be easily made by those skilled in the art within the technical scope of the present disclosure are intended to be included within the scope of the present disclosure.
The present invention has not been described in detail, partly as is known to the person skilled in the art.

Claims (7)

1. A modular configuration layout method for adapting to satellite incremental load change is characterized by comprising the following steps:
step A: according to the satellite configuration layout design baseline, determining the balance of weight, heat consumption, layout area in the cabin and layout area outside the cabin as expandable resources by calculating the difference between the total resource amount of the new satellite configuration and the total resource amount of the satellite configuration layout design baseline, including the difference between the weight, the heat consumption, the layout area in the cabin and the layout area outside the cabin;
and B: dividing the satellite into a basic module and an increment module;
and C: calculating resources required by the incremental load according to the satellite matching files;
step D: judging the resource satisfaction, and performing layout feasibility analysis;
step E: and performing incremental module layout according to the mechanical, electrical and thermal interfaces of incremental loads, the view field requirement, the installation precision requirement and the electromagnetic compatibility requirement.
2. The method of claim 1, wherein in step A,
the weight balance is as follows:
Figure FDA0003231585080000011
heat loss allowance:
Figure FDA0003231585080000012
layout area allowance in the cabin:
Figure FDA0003231585080000021
extra-cabin layout area allowance:
Figure FDA0003231585080000022
3. the modular configuration layout method for adapting to satellite incremental load change according to claim 2, wherein in the step B, the basic module and the incremental module are divided by: designing a base line according to configuration layout, and taking a fixed and non-detachable structural plate in a satellite configuration and equipment mounted on the structural plate as a basic module; and the detachable structural plate, the secondary structural plate which can be further expanded and the equipment mounted on the secondary structural plate are used as incremental modules.
4. The modular configuration layout method for adapting to satellite incremental load change according to claim 3, wherein in the step C, n incremental loads are determined according to satellite supporting files: x1，X2，…，Xi，…，Xn(ii) a Respectively calculating the sum of the weight, the heat consumption, the layout area in the cabin and the layout area outside the cabin required by the n incremental loads, wherein the formula is as follows:
Figure FDA0003231585080000023
wherein M isiWeight of the i-th incremental load, TiHeat rate for the ith incremental load, SiRequired cabin layout area and V for ith incremental loadiThe outboard layout area is the ith incremental load; 1,2,3, n, n is a positive integer.
5. The modular configuration layout method adapting to satellite incremental load change according to claim 4, wherein in step D, the preliminary feasibility analysis of the configuration layout is completed according to the satisfaction condition of the resource expansion allowance calculated in step A to the resource required by the incremental load calculated in step C, and the constraint conditions are as follows:
Figure FDA0003231585080000031
6. the method for modular configuration layout adapting to incremental load change of satellite according to claim 5, wherein in step D, there are 4 cases according to the interpretation result:
a. if the weight, the heat consumption, the layout area in the cabin and the layout area outside the cabin meet the requirements, entering the step E;
b. if any one of the weight, the heat consumption and the layout area in the cabin does not meet the requirement, optimizing the incremental load, reducing the weight, the heat consumption and the layout area of the incremental load, returning to the step C, and recalculating resources required by the incremental load until the requirements are met;
c. if the weight, the heat consumption and the layout area in the cabin meet the requirements and the layout area outside the cabin does not meet the requirements, two measures are taken:
optimizing the incremental load to reduce the required layout area outside the cabin;
expanding the deck within the carrying envelope limit, and expanding the layout area resources outside the deck by adding a secondary structure so as to meet the installation requirement of incremental load;
d. after optimization, if one or more of the weight, the heat consumption, the layout area in the cabin and the layout area outside the cabin are not qualified, the layout is not feasible under the configuration, and the platform needs to be replaced or the configuration number of incremental loads needs to be reduced.
7. The method for constructing a modular configuration layout capable of adapting to incremental satellite load changes according to claim 6, wherein the specific method of the step E is as follows:
if the constraint requirements of a) and b) in the step D are met, independently arranging the incremental load on a detachable structural plate;
if the constraint requirement of c) in the step D is met, adding a secondary structural plate on the satellite, and installing incremental load on the secondary structural plate.
CN202110988391.2A 2021-08-26 2021-08-26 Modular configuration layout method adaptive to satellite incremental load change Pending CN113919048A (en)

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