A modular configuration layout method to adapt to satellite incremental payload changes

Abstract

A modular configuration layout method adapted to changes in satellite incremental payloads includes the following steps: step A: according to the satellite configuration layout design baseline, by calculating the difference between the total amount of resources of the new satellite configuration and the total amount of resources of the satellite configuration layout design baseline, including the difference in weight, heat consumption, in-cabin layout area, and out-cabin layout area, determine the weight, heat consumption, in-cabin layout area, and out-cabin layout area margins as expandable resources; step B: dividing the satellite into basic modules and incremental modules; step C: calculating the resources required for the incremental payload according to the satellite supporting files; step D: judging resource satisfaction and conducting layout feasibility analysis; step E: conducting incremental module layout according to the mechanical, electrical, thermal interface, field of view requirements, installation accuracy requirements, and electromagnetic compatibility requirements of the incremental payload. The present invention adapts to the layout requirements of different satellite payload configurations and can quickly adapt to the incremental payload layout and the switching of multiple incremental configurations.

Description

Technical Field

[0001] The invention relates to a satellite modular configuration layout method, belonging to the field of satellite overall design. Background Art

[0002] Spacecraft development is a complex system engineering project. How to complete the spacecraft configuration layout design within a limited size envelope, provide working conditions for various equipment, and achieve various indicators of the flight mission are the main problems that need to be solved in the spacecraft configuration layout design.

[0003] For mass-produced satellites, it is difficult to avoid changes due to various reasons, such as changes in the external environment, changes in payload requirements, or changes inside the satellite. Therefore, each satellite has its own personality in addition to the common characteristics of the model satellite. Since mass-produced satellites are characterized by small batches, diverse configuration states, and different technical states, compared with the development of a single satellite, the different states of each satellite during mass production put forward higher requirements for its configuration layout design. At the same time, with the advancement of cognition and the development of new technologies, users will put forward new requirements for the functions and indicators of satellites. The configuration layout design of satellites should be able to adapt to the needs of incremental development and functional expansion.

[0004] The current satellite configuration and layout design is generally based on certain mission requirements. The satellite configuration and layout are determined in the early stages of the design. If the mission requirements change, it is necessary to re-design the configuration and layout or to modify the original configuration. New designs or modification projects are usually highly complex, labor-intensive, have a long development cycle, cost a lot of money, and are prone to interference or other quality problems. Summary of the invention

[0005] The technical problem to be solved by the present invention is: to overcome the shortcomings of the prior art, and to provide a modular configuration layout method that adapts to changes in satellite incremental payloads in response to the needs of mass-produced satellite mission expansion and incremental payload configuration. The method can adapt to the layout requirements of different satellite payload configurations and can quickly adapt to incremental payload layout and switching of multiple incremental configurations.

[0006] The technical solution adopted by the present invention is: a modular configuration layout method adapted to the change of satellite incremental load, comprising the following steps:

[0007] Step A: According to the satellite configuration layout design baseline, by calculating the difference between the total amount of resources of the new satellite configuration and the total amount of resources of the satellite configuration layout design baseline, including the difference in weight, heat consumption, cabin layout area, and cabin layout area, the weight, heat consumption, cabin layout area, and cabin layout area margin are determined as expandable resources, as follows:

[0008] Weight allowance:

[0009]

[0010] Heat loss margin:

[0011]

[0012] Cabin layout area margin:

[0013]

[0014] Outside cabin layout area margin:

[0015]

[0016] Step B: Divide the satellite into basic modules and incremental modules;

[0017] The way to divide basic modules and incremental modules is as follows: according to the configuration layout design baseline, the fixed, non-removable structural panels in the satellite configuration and the equipment installed on them are regarded as basic modules; the removable structural panels, secondary structural panels that can be further expanded and the equipment installed on them are regarded as incremental modules.

[0018] Step C: Calculate the resources required for the incremental payload based on the satellite supporting documents;

[0019] According to the satellite supporting documents, there are n types of incremental payloads: X1, X2, ..., X i , …, X n ; Calculate the weight, heat consumption, cabin layout area, and total cabin layout area required for n types of incremental loads respectively. The formula is as follows:

[0020]

[0021] M i is the weight of the i-th incremental load, T i is the heat consumption of the ith incremental load, S i is the required cabin layout area and V for the i-th incremental load i is the outer layout area of ​​the i-th incremental load; i=1,2,3,...,n, n is a positive integer;

[0022] Step D: Determine resource satisfaction and conduct layout feasibility analysis;

[0023] According to the satisfaction of the resource expansion margin calculated in step A with the resources required for the incremental load calculated in step C, the preliminary feasibility analysis of the configuration layout is completed, and the constraints are as follows:

[0024]

[0025] Specifically, according to the interpretation results, it is divided into 4 situations:

[0026] a. If the weight, heat consumption, cabin layout area, and cabin layout area meet the requirements, proceed to step E;

[0027] b. If any of the weight, heat consumption, and cabin layout area does not meet the requirements, optimize the incremental load to reduce its weight, heat consumption, and layout area, return to step C, and recalculate the resources required for the incremental load until it meets the requirements;

[0028] c. If the weight, heat consumption and cabin layout area meet the requirements, but the cabin layout area does not meet the requirements, two measures are taken:

[0029] ① Optimize the incremental load to reduce the required outer cabin layout area;

[0030] ② Expand the cabin plate within the load envelope limit and expand the outer layout area resources of the cabin by adding secondary structures to meet the installation requirements of the incremental load;

[0031] d. After optimization, if one or more of the weight, heat consumption, in-cabin layout area, and out-cabin layout area still do not meet the requirements, it means that the layout is not feasible under this configuration, and it is necessary to replace the platform or reduce the number of incremental load configurations.

[0032] Step E: Layout the incremental modules according to the mechanical, electrical, and thermal interfaces of the incremental load, as well as the field of view requirements, installation accuracy requirements, and electromagnetic compatibility requirements;

[0033] Specifically:

[0034] If the constraint requirements of a) and b) in step D are met, the incremental load is arranged separately on a removable structural plate;

[0035] If the constraint requirements of step D c) are met, a secondary structure plate is added to the satellite and the incremental load is installed on the secondary structure plate.

[0036] The advantages of the present invention compared with the prior art are:

[0037] (1) The present invention proposes a modular configuration layout method that adapts to the change of satellite incremental payload. The modular expansion design is adopted to divide the satellite into a basic module and an incremental payload module. On the basis of the satellite configuration layout design baseline, resources such as weight, power consumption, and layout area have expansion margins.

[0038] (2) The method proposed in the present invention can realize rapid configuration layout design by changing or adding incremental modules on the basis of the basic configuration; an independent standard interface is designed on the main structure, through which structural plates of various technical states can be adapted to meet the configuration requirements of various incremental loads;

[0039] (3) In the method proposed by the present invention, the secondary structure is fixed on the main structure of the whole satellite, does not transmit the main load, and does not significantly affect the structure of the fundamental frequency and vibration mode of the whole satellite; 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 multiple times;

[0040] (4) The method proposed in the present invention has modular design and assembly, decoupling the main line development of the satellite and the development of the incremental payload. It has flexible adjustability in terms of configuration layout and process planning. In terms of process planning, the development of the incremental payload is carried out in parallel with the development of the whole satellite, creating multiple entry points for the integration of the incremental payload into the development process of the whole satellite. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] Figure 1 The present invention is a flow chart of a modular configuration layout method for adapting to the change of satellite incremental payload;

[0042] Figure 2 This is a configuration diagram of a truss platform satellite;

[0043] Figure 3 This is the satellite configuration diagram for the Type I incremental payload configuration scheme;

[0044] Figure 4 Satellite configuration diagram for type II and III incremental payload configuration schemes;

[0045] Figure 5 (a) is the layout diagram of the inner surface of the load compartment-X plate under the I-type incremental load configuration scheme;

[0046] Figure 5 (b) is the layout diagram of the outer surface of the load compartment-X plate under the type I incremental load configuration scheme;

[0047] Figure 6 (a) is the layout diagram of the inner surface of the load compartment-X plate under the type II incremental load configuration scheme;

[0048] Figure 6 (b) The layout diagram of the load cabin-X plate outer surface and independent cabin under the type II incremental load configuration scheme;

[0049] Figure 6 (c) is the layout diagram of the payload cabin + X-board external independent cabin under the type II incremental payload configuration scheme;

[0050] Figure 7 (a) is the layout diagram of the inner surface of the load compartment-X plate under the type III incremental load configuration scheme;

[0051] Figure 7 (b) The layout diagram of the load compartment-X plate outer surface and independent cabin under the Type III incremental load configuration scheme;

[0052] Figure 7(c) is the layout diagram of the payload cabin + X-board external independent cabin under the Type III incremental payload configuration scheme;

[0053] Figure 8 This is a diagram showing the compatibility of the incremental payload with the entire satellite development process. DETAILED DESCRIPTION

[0054] The present invention is described with reference to the accompanying drawings and embodiments.

[0055] like Figure 1 As shown, a modular configuration layout method adapted to satellite incremental payload changes includes the following steps:

[0056] Step A: Calculate scalable resources based on the satellite configuration layout design baseline.

[0057] The configuration layout design baseline in step A is: the scheme that is formally confirmed and used as the basis for future configuration layout design; according to the satellite configuration layout design baseline, by calculating the total amount of resources such as weight, heat consumption, cabin layout area, and cabin layout area that are closely related to the configuration layout design, and the difference between the weight, heat consumption, cabin layout area, and cabin layout area in the baseline scheme, the weight, heat consumption, cabin layout area, and cabin layout area margins are determined as expandable resources, as follows:

[0058] weight:

[0059]

[0060] Heat consumption:

[0061]

[0062] Cabin layout area:

[0063]

[0064] External layout area:

[0065]

[0066] Step B: Divide the satellite into basic modules and incremental modules.

[0067] The way to divide the basic modules and incremental modules in step B is that, based on the configuration layout design baseline, the fixed, non-detachable structural panels in the satellite configuration and the equipment installed thereon are used as basic modules; and the detachable structural panels, the secondary structural panels that can be further expanded and the equipment installed thereon are used as incremental modules.

[0068] Step C: Calculate the resources required for the incremental payload based on the satellite supporting documents.

[0069] In step C, according to the satellite supporting documents, there are n types of incremental payloads:

[0070] X1, X2, …, X i , …, X n ; Calculate the weight, heat consumption, cabin layout area, and cabin layout area required for the incremental load respectively. The specific methods are as follows:

[0071] The weight, heat consumption, required interior layout area and exterior layout area of ​​the ith incremental load are M i , T i , S i , V i , the total resources required for the incremental load are:

[0072]

[0073] Step D: Determine resource sufficiency and conduct layout feasibility analysis.

[0074] In step D, the preliminary feasibility analysis of the configuration layout is completed based on the satisfaction of the resource expansion margin calculated in step A with the resources required for the incremental load calculated in step C. The constraints are as follows:

[0075]

[0076] Among them, weight, heat consumption, and cabin layout area are strong constraints. If the constraints are not met, the next step cannot be carried out; the cabin layout area is a weak constraint. If the constraints are not met, the layout requirements can be met by adding secondary structural plates. Specifically, according to the interpretation results, it is divided into 4 cases:

[0077] a) The weight, heat consumption, interior layout area, and exterior layout area all meet the requirements, and the next step is to carry out detailed layout design.

[0078] b) If any of the weight, heat consumption, and cabin layout area does not meet the requirements, the incremental load is optimized to reduce its weight, heat consumption, layout area, etc., and further iterated with the overall design until it meets the requirements.

[0079] c) If the weight, heat consumption and cabin layout area meet the requirements, but the cabin layout area does not meet the requirements, two measures can be taken:

[0080] ① Optimize the incremental load to reduce the required outer cabin layout area;

[0081] ② Expand the cabin plate within the limits of the transport envelope and expand the external layout area resources of the cabin by adding secondary structures to meet the installation requirements of the incremental load.

[0082] d) After optimization, one or more of the weight, heat consumption, interior layout area, and exterior layout area still do not meet the requirements, indicating that the layout is not feasible under this configuration and that it is necessary to replace the platform or reduce the number of incremental load configurations.

[0083] Step E: Detailed layout design of incremental loads.

[0084] In step E, detailed layout design of the incremental module is carried out according to the mechanical, electrical, and thermal interfaces of the incremental load, as well as the field of view requirements, installation accuracy requirements, and electromagnetic compatibility requirements.

[0085] Specifically:

[0086] ① Satisfy the constraint requirements of a) and b) in step D and place the incremental loads separately on a detachable structural plate;

[0087] ② If the constraint requirements of step D c) are met, a secondary structure plate is added to the satellite and the incremental load is installed on the secondary structure plate.

[0088] The variable structural plates and the equipment installed thereon involved in the above two methods are separate incremental modules and do not affect the satellite configuration and layout design in other fixed states.

[0089] Example

[0090] Taking a truss platform satellite as an example, the specific implementation steps of the present invention are as follows:

[0091] 1) Take the configuration layout scheme of a truss platform satellite with only basic payload as the design baseline, calculate the total weight, total heat consumption, total cabin layout area, and total cabin layout area constraints of the satellite, and calculate the weight, heat consumption, cabin layout area, and cabin layout area of ​​the baseline scheme, as well as the expandable margin relative to the weight, heat consumption, cabin layout area, and cabin layout area of ​​the baseline scheme, as follows:

[0092]

[0093] 2) If Figure 2As shown, the main load-bearing structure of the truss-type platform satellite is a rectangular truss structure, which is divided into a platform and a payload cabin, and the payload cabin includes a payload cabin + Z plate 1, a payload cabin + Y plate 2, a payload cabin-Y plate 3, a payload cabin + X plate 4, and a payload cabin-X plate 5. Among them, the platform 6 does not involve incremental changes, and the payload cabin + Z plate 1, the payload cabin + Y plate 2, and the payload cabin-Y plate 3 are fixed structural plates and cannot be disassembled. Therefore, the platform 6, the payload cabin + Z plate 1, the payload cabin + Y plate 2, and the payload cabin-Y plate 3, together with the equipment installed on these structural plates, are divided into basic modules; the payload cabin + X plate 4 and the payload cabin-X plate 5 are detachable structural plates, together with the secondary structural plates that can be further expanded thereon, which will be used for the expansion installation of incremental payload equipment as incremental modules.

[0094] 3) There are five types of incremental loads involved in a truss platform satellite, X1, X2, X3, X4, and X5. The weight, heat consumption, in-cabin layout area, and out-cabin layout area of ​​these five incremental loads are as follows:

[0095]

[0096] According to the satellite supporting documents, the truss platform satellite has three incremental payload configuration schemes: Type I, Type II, and Type III. Among them, Type I scheme is configured with three incremental payloads: X1, X2, and X4; Type II scheme is configured with three incremental payloads: X1, X3, and X4; and Type III scheme is configured with three incremental payloads: X1, X3, and X5.

[0097] The weight, heat consumption, cabin layout area, and cabin exterior layout area required for the incremental load under the three configuration schemes are calculated respectively, as follows:

[0098] The weight, heat consumption, interior layout area, and exterior layout area of ​​a Type I satellite are:

[0099]

[0100] The weight, heat consumption, interior layout area, and exterior layout area of ​​the Type II satellite are:

[0101]

[0102] The weight, heat consumption, interior layout area, and exterior layout area of ​​the Type III satellite are:

[0103]

[0104] 4) Based on the resource expansion margin calculated in step A, the satisfaction of the resources required for the incremental load under the three configuration schemes calculated in step C is interpreted:

[0105] The results of the weight, heat loss, interior layout area, and exterior layout area of ​​Type I configuration are as follows:

[0106]

[0107] The results of the weight, heat loss, interior layout area, and exterior layout area of ​​the Type II configuration are as follows:

[0108]

[0109] The results of the weight, heat consumption, interior layout area, and exterior layout area of ​​the Type III configuration are as follows:

[0110]

[0111] Under the I-type configuration scheme, the resource margin meets the incremental load requirements. Figure 3 Further detailed layout design is carried out on the payload bay-X board shown.

[0112] Under the II and III configuration schemes, the required extravehicular layout area is large due to the configuration of the incremental payload X3, and the current extravehicular layout area margin cannot meet the incremental payload requirements. For the II and III configuration schemes, the satellite structure is expanded and a secondary structure is added, such as Figure 4 As shown, the incremental load X3 is installed on the independent cabin 7.

[0113] 5) Carry out detailed layout design of incremental modules based on the mechanical, electrical, and thermal interfaces of the incremental load, as well as field of view requirements, installation accuracy requirements, and electromagnetic compatibility requirements.

[0114] In the type I configuration scheme, the incremental load X18, the cabin equipment 9 of the incremental load X2, and the cabin equipment 10 of the incremental load X4 are installed on the inner surface of the load cabin-X plate 5, and the extravehicular equipment 11 of the incremental load X2 and the extravehicular equipment 12 of the incremental load X4 are installed on the outer surface of the load cabin-X plate 5. For detailed layout, see Figure 5 (a) Figure 5 (b) In Figure 5 (a) Figure 5 In (b): the extravehicular equipment 12 of the incremental load X4 is installed below the extravehicular equipment 11 of the incremental load X2, wherein the height of the extravehicular part of the incremental load X4 from the cabin board is 40 mm, and the height of the extravehicular part of the incremental load X2 from the cabin board is 90 mm.

[0115] Type II configuration scheme, the cabin equipment 10 of the incremental load X18, the cabin equipment 10 of the incremental load X4, and the cabin equipment 13 of the incremental load X3 are installed on the inner surface of the load cabin-X plate 5; the extravehicular equipment 12 of the incremental load X4 is installed on the outer surface of the load cabin-X plate 5; and independent small cabins 7 are added outside the load cabin-X plate 5 and +X plate 4 respectively, and the extravehicular equipment 14 of the incremental load X3 is installed on the independent small cabin 7. For detailed layout, see Figure 6 (a)~(c).

[0116] Type III configuration scheme, the incremental load X18, the cabin equipment 13 of the incremental load X3, and the cabin equipment 15 of the incremental load X5 are installed on the inner surface of the load cabin-X plate 5; the extravehicular equipment 16 of the incremental load X5 is installed on the outer surface of the load cabin-X plate 5; and independent small cabins 7 are added outside the load cabin-X plate 5 and +X plate 4, and the extravehicular equipment 14 of the incremental load X3 is installed on the independent small cabin 7. For detailed layout, see Figure 7 (a)~(c).

[0117] 6) According to Figure 5 (a) Figure 5 (b) Figure 6 (a) to (c) and Figure 7 Designs (a) to (c) are put into production respectively for the payload cabin-X plate 5 and the independent cabin 7 of type I, type II, and type III configuration schemes. After the delivery of the structural plate and incremental payload equipment, they are assembled into incremental modules, on which the incremental payload testing work is carried out. According to the satellite development process, the incremental module is replaced as a whole at an appropriate time.

[0118] The modular configuration layout scheme makes the incremental modules relatively independent and has flexible and adjustable capabilities when integrated with the whole satellite development process. Figure 8 As shown, the entry point can be selected from multiple opportunities such as before large-scale tests and before shipment.

[0119] It should be understood that the above description is only an embodiment of the present invention and is not intended to limit the embodiments of the present invention. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed by the present invention should be included in the protection scope of the present invention.

[0120] Parts of the present invention that are not described in detail belong to the well-known technologies of those skilled in the art.

Claims

1. A modular configuration layout method adapted to satellite incremental payload changes, characterized in that: The following steps are involved: Step A: According to the satellite configuration layout design baseline, by calculating the difference between the total amount of resources of the new satellite configuration and the total amount of resources of the satellite configuration layout design baseline, including the difference in weight, heat consumption, cabin layout area, and cabin layout area, the weight, heat consumption, cabin layout area, and cabin layout area margin are determined as expandable resources; Step B: Divide the satellite into basic modules and incremental modules; Step C: Calculate the resources required for the incremental payload based on the satellite supporting documents; Step D: Determine resource satisfaction and conduct layout feasibility analysis; Step E: Layout the incremental modules according to the mechanical, electrical, and thermal interfaces of the incremental load, as well as the field of view requirements, installation accuracy requirements, and electromagnetic compatibility requirements; In step A, Weight allowance: Heat loss margin: Cabin layout area margin: Outside cabin layout area margin: ； In step B, the basic module and the incremental module are divided as follows: according to the configuration layout design baseline, the fixed, non-detachable structural panels and the equipment installed thereon in the satellite configuration are used as basic modules; the detachable structural panels, the secondary structural panels that can be further expanded and the equipment installed thereon are used as incremental modules; In step C, according to the satellite supporting documents, the total number of incremental payloads is determined. n kind: ; Calculate the weight, heat consumption, cabin layout area, and total cabin layout area required for n types of incremental loads respectively. The formula is as follows: in, For the i The weight of the incremental load, For the i The heat loss of the incremental load is For the i The required cabin layout area and For the i The outer layout area of ​​the cabin for the incremental load; , n is a positive integer.

2. A modular configuration layout method adapted to satellite incremental load changes according to claim 1, characterized in that: In step D, the preliminary feasibility analysis of the configuration layout is completed based on the satisfaction of the resource expansion margin calculated in step A with the resources required for the incremental load calculated in step C. The constraints are as follows: 。 3. A modular configuration layout method for adapting to satellite incremental load changes according to claim 2, characterized in that: In step D, there are four situations according to the interpretation results: a. If the weight, heat consumption, cabin layout area, and cabin layout area meet the requirements, proceed to step E; b. If any of the weight, heat consumption, and cabin layout area does not meet the requirements, optimize the incremental load to reduce its weight, heat consumption, and layout area, return to step C, and recalculate the resources required for the incremental load until it meets the requirements; c. If the weight, heat consumption and cabin layout area meet the requirements, but the cabin layout area does not meet the requirements, two measures are taken: ① Optimize the incremental load to reduce the required outer cabin layout area; ② Expand the cabin plate within the load envelope limit and expand the outer layout area resources of the cabin by adding secondary structures to meet the installation requirements of the incremental load; d. After optimization, if one or more of the weight, heat consumption, in-cabin layout area, and out-cabin layout area still do not meet the requirements, it means that the layout is not feasible under this configuration, and it is necessary to replace the platform or reduce the number of incremental load configurations.

4. A modular configuration layout method for adapting to satellite incremental load changes according to claim 3, characterized in that: The specific method of step E is as follows: If the constraint requirements of a) and b) in step D are met, the incremental load is arranged separately on a removable structural plate; If the constraint requirements of step D c) are met, a secondary structure plate is added to the satellite and the incremental load is installed on the secondary structure plate.

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