A multi-constraint parameter satellite stealth optimization configuration

Abstract

This invention discloses a multi-constraint parameter satellite stealth optimization configuration, belonging to the field of satellite configuration design. The multi-constraint parameter satellite stealth optimization configuration is a teardrop-shaped stealth satellite configuration. The external frame of the configuration is a teardrop-shaped structure formed by truss combinations and interconnected triangular configuration parts. The top octagonal pyramid structure, octagonal frustum structure, octagonal pyramid structure, and square pyramid structure are all truss structures. The configuration minimizes strong scattering, and the smooth structure reduces specular reflection, thus exhibiting excellent stealth characteristics. The RCS characteristics are very good, meeting the stealth requirements of stealth satellites: in the dangerous band, the RCS is below -10dB within ±30° of the nose cone incident angle. The circumferential RCS value is kept as low as possible. Load-bearing plates, load-bearing rods, and supporting stiffeners are added to the structure to meet mechanical constraints: the satellite structure has sufficient stiffness, strength, and stability. The heater power and heat dissipation device mounting positions are determined to meet the satellite's thermal constraints.

Description

Technical Field

[0001] This invention relates to the field of satellite configuration design, and more specifically to a multi-constraint parameter satellite stealth configuration optimization design. Background Technology

[0002] While most common stealth designs offer some degree of stealth capability, each has its limitations. Taking the "Tianxun-1" as an example, it suffers from being too small and not fully considering actual operational conditions. Therefore, this configuration is not optimal and can be further optimized to reduce RCS and improve stealth performance. Summary of the Invention

[0003] To overcome the shortcomings of existing technologies, this invention proposes a multi-constraint parameter satellite stealth configuration optimization design, which is based on a teardrop-shaped radar stealth satellite configuration that meets actual working conditions. It can be applied to satellite design, improving the carrying capacity and stealth capability of stealth satellites, and conforming to the future development trend and application needs of aerospace technology.

[0004] This invention is implemented as follows:

[0005] A multi-constraint parameter satellite stealth optimization configuration is characterized in that the multi-constraint parameter satellite stealth optimization configuration is a basic configuration of a teardrop-shaped stealth satellite, the configuration including: a top octagonal pyramid structure, an octagonal frustum structure, five octagonal pyramid structures, twelve square pyramid structures, and twenty-four triangular configuration parts; the top octagonal pyramid structure, octagonal frustum structure, octagonal pyramid structure, and square pyramid structure are all truss structures, and the external frame of the configuration is a teardrop-shaped structure formed by truss combination and interconnection and fixation by triangular configuration parts.

[0006] The multi-constraint parameter satellite stealth optimization configuration of the present invention is assembled in layers. The first layer is a top octagonal pyramid structure that is welded and fixed to an octagonal frustum structure. The second layer consists of four square pyramid structures and twelve triangular configuration parts that are welded and fixed according to matching side lengths. The third layer consists of four octagonal pyramid structures and four square pyramid structures that are alternately welded. The fourth layer repeats the design of the second layer, consisting of four square pyramid structures and twelve triangular configuration parts that are welded and fixed according to matching side lengths. Finally, the fifth layer is a bottom octagonal pyramid structure. Welding and fixing the five layers in hierarchical order yields the multi-constraint parameter satellite stealth optimization configuration.

[0007] Furthermore, the entire teardrop-shaped structure is wrapped with a solar panel backsheet to provide power to the instruments inside the satellite.

[0008] Furthermore, the teardrop-shaped structure also includes two load-bearing plates and eight load-bearing rods, as well as a supporting stiffener; in the configuration, it is supported by two load-bearing plates, eight load-bearing rods, and a supporting stiffener.

[0009] Furthermore, the load-bearing plates are polygonal in shape at distances of 182.77 mm and 798.33 mm from the apex, respectively, and are welded and fixed to the beam edges related to these locations. The load-bearing rods are 493.96 mm long, and their cross-sections are pentagons with side lengths of 18.48 mm, 10 mm, 10 mm, 8 mm, and 8 mm, respectively. The top and bottom edges connect to the apexes of the two load-bearing plates. The supporting stiffeners are octagons with a bottom perimeter of 158.42 mm and a thickness of 15 mm. Six intersecting stiffeners with a thickness of 5 mm, a length of 366.5 mm, and a width of 110.5 mm are added to the bottom surface to satisfy the mechanical constraints and provide sufficient stiffness, strength, and stability. The supporting stiffeners are welded and fixed to the bottom octagonal pyramid structure.

[0010] Furthermore, the payload is primarily mounted on two load-bearing plates; heaters are located at the bottom of the upper load-bearing plate, and heat dissipation pipes are distributed inside the octagonal structure, thus satisfying the satellite's thermodynamic constraints: in a near-Earth orbit of 400km, the overall surface temperature of the satellite is controlled to remain stable within a certain range, with a maximum temperature not exceeding 100℃ and a minimum not exceeding -30℃.

[0011] Furthermore, the heater has a power of 1W.

[0012] Furthermore, the teardrop-shaped structure has an overall height of 867.07 mm and a maximum width of 762.06 mm; the octagonal pyramid structure at the top has a height of 20.31 mm and a base side length of 23.83 mm; the octagonal frustum structure has a height of 162.46 mm, an upper base length of 23.83 mm, and a lower base length of 158.42 mm; the octagonal pyramid structure has a height of 68.71 mm and a base side length of 158.42 mm; the square pyramid structure has a rectangular base with a length of 162.46 mm and a width of 158.42 mm, and a vertex height of 34.41 mm; the triangular component is an isosceles triangle with a waist length of 162.46 mm and a base side length of 158.42 mm; the tensile thickness of the beams and components of the above truss structure is 5 mm; the width of the intermediate support beam of all pyramids and frustum structures is 10 mm, while the width of the beams at the top and bottom bases is 5 mm.

[0013] The multi-constraint parameter satellite stealth optimization configuration described in this invention, with its teardrop-shaped structure and nose cone facing the ground under the critical 5.45 GHz incident wave band, achieves the following bistatic RCS: At zero roll angle, the average circumferential bistatic RCS is below -20 dB at the critical incident angle (0°-20°); and the RCS is below -10 dB over a relatively large incident range (22.5°-67.5°); simultaneously, the RCS is below -10 dB at incident angles (0°-30°); and the circumferential average value is below 0 dB within a roll angle range of 0°-±45°. This excellently satisfies the requirements for a stealth satellite. The supporting stiffener is a structure composed of multiple stiffeners. The supporting stiffener, consisting of six intersecting stiffeners, serves as the load-bearing structure and thus satisfies the mechanical constraints: it has reasonable strength and stability under extreme overload conditions, and the modal conditions are: the first-order transverse bending frequency is greater than 20 Hz; the first-order torsional and first-order longitudinal vibration frequencies are greater than 25 Hz and 35 Hz, respectively.

[0014] The advantages of this invention compared to the prior art are as follows:

[0015] The multi-constraint parameter satellite stealth optimization configuration of the present invention is a basic configuration of a teardrop-shaped stealth satellite, which reserves sufficient payload volume as much as possible. Compared with Tianxun-1, it has a payload volume of 1.33 times to meet the different mission requirements of the satellite.

[0016] The multi-constraint parameter satellite stealth optimization configuration of this invention is teardrop-shaped, which greatly reduces strong scattering. The smooth structure reduces specular reflection, thus exhibiting excellent stealth characteristics. The RCS characteristics very well meet the stealth requirements of stealth satellites: in the dangerous band, the RCS is below -10dB within ±30° of the nose cone at the incident angle. The circumferential RCS value is kept as low as possible.

[0017] This invention, through the design of the basic configuration, enables the satellite to meet the stealth requirements in terms of RCS value during normal operation, that is, during the flight of the nose cone towards the Earth.

[0018] This invention, through the design of a pyramidal frustum and a teardrop-shaped polygonal load-bearing frame, greatly increases the effective payload area of ​​the satellite, thereby enhancing its payload capacity and the versatility of its applications.

[0019] This invention, through the design of the heater and heat dissipation device positions, enables the satellite to maintain good temperature conditions and sustainability during normal operation.

[0020] This invention improves the strength and stability of the satellite through the design of load-bearing plates, load-bearing rods, and supporting stiffeners, enabling it to operate under normal mechanical conditions. Attached Figure Description

[0021] Figure 1This is a structural schematic diagram of a multi-constraint parameter satellite stealth optimization configuration according to the present invention;

[0022] Figure 2 This is a schematic diagram of a layered installation of a multi-constraint parameter satellite stealth optimization configuration according to the present invention;

[0023] Figure 3 This is a structural cross-sectional view of a multi-constraint parameter satellite stealth optimization configuration according to the present invention;

[0024] Figure 4 This is a schematic diagram of the payload configuration layout of the present invention;

[0025] Among them, 1-top octagonal pyramid structure, 2-octagonal frustum structure, 3-octagonal pyramid structure, 4-solar cell backsheet, 5-quadrangular pyramid structure, 6-triangular component, 7-support plate, 8-support rod, 9-support rib, 10-heater, 11-heat pipe. Detailed Implementation

[0026] To make the objectives, technical solutions, and effects of this invention clearer and more explicit, the following examples provide a more detailed description of the invention. It should be noted that the specific embodiments described herein are merely illustrative and not intended to limit the scope of the invention.

[0027] This invention proposes a teardrop-shaped radar stealth satellite configuration based on actual working conditions, which can be applied to satellite design and improves the carrying capacity and stealth capability of stealth satellites.

[0028] This invention relates to a multi-constraint parameter satellite stealth configuration optimization design, which is a basic configuration of a teardrop-shaped stealth satellite. It consists of a top octagonal pyramid structure 1, an octagonal frustum structure 2, an octagonal pyramid structure 3, a square pyramid structure 5, triangular components 6, a load-bearing plate 7, load-bearing rods 8, and supporting stiffeners 9, all assembled to form a basic outer contour. A solar panel backplate 4 is used for basic coverage, and heaters 10 and heat dissipation pipes 11 are added to complete the stealth satellite configuration suitable for actual operating conditions. In the above-mentioned satellite stealth configuration optimization design, the top octagonal pyramid structure 1, octagonal frustum structure 2, octagonal pyramid structure 3, square pyramid structure 5, triangular components 6, load-bearing plate 7, load-bearing rods 8, and supporting stiffeners 9 are fixed by welding. The load-bearing rods 8 are symmetrical and connected to the vertices of the load-bearing plate 7 by welding, and the bottom surface of the supporting stiffeners 9 is welded to the bottom octagonal pyramid structure 3.

[0029] The following example uses a satellite orbiting at an altitude of 400km, with a maximum overload of 5g during launch.

[0030] like Figure 1 , Figure 2As shown, the basic configuration of this invention includes an octagonal pyramid structure 1, an octagonal frustum structure 2, five octagonal pyramid structures 3, twelve square pyramid structures 5, twenty-four triangular components 6, two load-bearing plates 7 and eight load-bearing rods 8, and supporting stiffeners 9. The structures of the heater 10, heat dissipation pipe 11, and solar cell backplate 4 are as follows... Figure 3 As shown.

[0031] The top octagonal pyramid structure 1, octagonal frustum structure 2, octagonal pyramid structure 3, and four-sided pyramid structure 5 are all truss structures. The external frame trusses are combined and interconnected using triangular structural parts 6 to form a teardrop-shaped structure. The solar panel backplate 4 wraps around the entire structure and can be coated externally, such as with sonar stealth coatings. A schematic diagram of the solar panel wrapping is shown below. Figure 3 As shown.

[0032] The aforementioned multi-constraint parameter satellite stealth optimization configuration is assembled in layers, such as... Figure 2 As shown, the first layer consists of an octagonal pyramid structure 1 fixedly connected to an octagonal frustum structure 2. The second layer is composed of four square pyramid structures 5 and twelve triangular components 6 assembled and fixed according to their side lengths. The third layer is formed by alternating connections of four octagonal pyramid structures 3 and four square pyramid structures 5. The fourth layer repeats the design of the second layer, consisting of four square pyramid structures 5 and twelve triangular components 6 welded and fixed according to their matching side lengths, assembled sequentially. Finally, the fourth layer is connected and assembled with the fifth layer of octagonal pyramid structures 3.

[0033] The configuration is supported by two load-bearing plates 7, eight load-bearing rods 8, and one supporting rib 9. The load-bearing plates are located at distances of 182.77 mm and 798.33 mm from the top of the configuration, respectively. The supporting rib 9 is an octagon with a base perimeter of 158.42 mm, as shown below. Figure 3 As shown, the six intersecting stiffeners are added as load-bearing support to meet mechanical constraints, thus providing sufficient stiffness, strength, and stability.

[0034] The effective load is mainly supported by two load-bearing plates. The heaters 10 are located at the bottom of the upper load-bearing plate, while the heat dissipation pipes 11 are located inside the octagonal frustum 2. Figure 4 As shown, this satisfies the satellite's thermodynamic constraints.

[0035] The payload can be configured and laid out differently depending on the mission, such as adding motors, communicators, momentum wheels, etc. This design provides as much space as possible for the payload to meet the different mission requirements of the satellite.

[0036] Under the critical 5.45 GHz incident wave band, with its nose cone directly facing the ground, the satellite's bistatic RCS meets the following requirements: at zero roll angle, the average circumferential bistatic RCS is below -20 dB at the critical incident angle (0°-20°), and below -10 dB over a relatively large incident range (22.5°-67.5°); simultaneously, the RCS is below -10 dB at incident angles (0°-30°), and the average circumferential RCS is below 0 dB within a roll angle range of 0°-±45°. This very well meets the requirements for a stealth satellite.

[0037] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements can be made without departing from the principle of the present invention, and these improvements should also be considered within the scope of protection of the present invention.

Claims

1. A multi-constrained parameter satellite stealth optimized configuration, characterized in that, The multi-constraint parameter satellite stealth optimization configuration is a basic configuration of a teardrop-shaped stealth satellite, which includes: Top octagonal pyramid structure (1), octagonal frustum structure (2), five octagonal pyramid structures (3), twelve quadrangular pyramid structures (5), twenty-four triangular configuration parts (6). The top octagonal pyramid structure (1), octagonal frustum structure (2), octagonal pyramid structure (3), and quadrangular pyramid structure (5) are all truss structures. The external frame of the configuration is a teardrop-shaped structure formed by truss combination and interconnection and fixation with triangular configuration parts (6). The multi-constraint parameter satellite stealth optimization configuration is assembled in layers. The first layer is the top octagonal pyramid structure (1), which is first welded and fixed to the octagonal frustum structure (2). The second layer is four square pyramid structures (5) and twelve triangular configuration parts (6) welded and fixed according to the matching side lengths. The third layer is formed by alternating welding of four octagonal pyramid structures (3) and four square pyramid structures (5). The fourth layer repeats the design of the second layer, consisting of four square pyramid structures (5) and twelve triangular configuration parts (6) welded and fixed according to the matching side lengths. Finally, the fifth layer is the bottom octagonal pyramid structure (3). The five layers are welded and fixed in hierarchical order to obtain the multi-constraint parameter satellite stealth optimization configuration. The teardrop-shaped structure also includes two load-bearing plates (7) and eight load-bearing rods (8), and a supporting rib plate (9); In the configuration, it is supported by two load-bearing plates (7) and eight load-bearing rods (8), and a supporting rib plate (9); The load-bearing plates (7) are respectively located at 182.77 mm and 798.33 mm from the vertex, and are polygonal in shape, respectively, and are welded to the beam edges related to the cross-section; the load-bearing rod (8) is 493.96 mm long, and the cross-section of the load-bearing rod (8) is a pentagon with side lengths of 18.48 mm, 10 mm, 10 mm, 8 mm, and 8 mm, and the upper and lower bottom edges are respectively connected to the vertices of the two load-bearing plates; respectively connected to the corresponding vertices of the two load-bearing plates; the supporting stiffener (9) is a regular octagon with a bottom perimeter of 158.42 mm and a thickness of 15 mm, and six intersecting stiffeners with a thickness of 5 mm, a length of 366.5 mm, and a width of 110.5 mm are added to the bottom surface to meet the mechanical constraints and have sufficient stiffness, strength, and stability; the bottom surface of the supporting stiffener (9) is welded to the bottom octagonal pyramid structure (3); The teardrop-shaped structure has an overall height of 867.07 mm and a maximum width of 762.06 mm. The top octagonal pyramid structure (1) has a height of 20.31 mm and a base length of 23.83 mm. The octagonal frustum structure (2) has a height of 162.46 mm, an upper base length of 23.83 mm, and a lower base length of 158.42 mm. The octagonal pyramid structure (3) has a height of 68.71 mm and a base length of 158.42 mm. The square pyramid structure (5) has a base that is a rectangle with a length of 162.46 mm and a width of 158.42 mm, and a vertex height of 34.41 mm. The triangular component (6) is an isosceles triangle with a waist length of 162.46 mm and a base length of 158.42 mm. The tensile thickness of the beams and components of the above truss structures is 5 mm. The width of the intermediate support beams of all pyramids and frustum structures is 10 mm, while the width of the beams at the top and bottom edges is 5 mm.

2. The multi-constrained parameter satellite stealth optimal configuration of claim 1, wherein, The entire teardrop-shaped structure is wrapped with a solar panel backplate (4) to provide power to the instruments inside the satellite.

3. The multi-constraint parameter satellite stealth optimization configuration according to claim 1, characterized in that, The payload is mainly built on two load-bearing plates (7); the heater (10) is distributed at the bottom of the upper load-bearing plate (7), and the heat dissipation pipe (11) is distributed inside the octagonal structure, so as to meet the thermodynamic constraints of the satellite: a near-Earth orbit of 400km, controlling the overall temperature of the satellite surface to be stable within a certain range, with the highest temperature not exceeding 100℃ and the lowest not exceeding -30℃.

4. The multi-constraint parameter satellite stealth optimization configuration according to claim 3, characterized in that, The heater (10) has a power of 1W.

5. A multi-constraint parameter satellite stealth optimization configuration according to any one of claims 1 to 4, characterized in that, With the nose cone facing the ground, the teardrop-shaped structure, under the critical incident wave band of 5.45 GHz, achieves the following bistatic radar cross-section (RCS): at zero roll angle, the average circumferential bistatic RCS is below -20 dB at the critical incident angles of 0°-20°; within a relatively large incident range of 22.5°-67.5°, the RCS is below -10 dB; and at incident angles of 0°-30°, the RCS is below -10 dB. Furthermore, the average circumferential RCS is below 0 dB within a roll angle range of 0°-±45°. This very well meets the requirements for a stealth satellite. The supporting stiffener (9) is a structure composed of multiple stiffeners. The supporting stiffener (9) composed of six intersecting stiffeners serves as a load-bearing structure to meet the mechanical constraints: it has reasonable strength and stability under extreme overload conditions, and the modal conditions are: the first-order transverse bending frequency is greater than 20 Hz; the first-order torsional and first-order longitudinal vibration frequencies are greater than 25 Hz and 35 Hz, respectively.

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