A stability augmentation layout for ultra-low earth orbit satellites

Abstract

The application discloses a super-low-orbit satellite stability-increasing layout, which comprises a super-low-orbit satellite body, a set of swept-back solar cell wings and a set of swept-back side plates. The super-low-orbit satellite body is an octagonal prism structure with a cross-section regular octagon, which can provide equipment loading space and solar cell sheet distribution requirements; the set of solar cell wings are respectively arranged on two sides of the super-low-orbit satellite body; and the set of side plates are arranged at tail ends of the solar cell wings and are perpendicular to the solar cell wings and used for passive control of the super-low-orbit satellite attitude. The stability-increasing layout designed by the application can effectively reduce the roll torque of the super-low-orbit satellite when the super-low-orbit satellite runs in a deep atmosphere layer, reduce the influence of the rare atmosphere in the deep atmosphere layer on the running track of the super-low-orbit satellite, help to improve the attitude control of the super-low-orbit satellite and improve the running stability of the super-low-orbit satellite.

Description

TECHNICAL FIELD

[0001] The present application relates to a super low orbit satellite stability layout, belonging to the field of upper atmosphere vehicle aerodynamic design. BACKGROUND

[0002] The attitude control system design is one of the key technologies of satellite development, and the research on the attitude control system of super low orbit satellite mainly focuses on attitude measurement and control algorithm, and the research on space environment torque is less and lacks practical guiding significance. For super low orbit satellite, due to its low orbit height, the aerodynamic force and aerodynamic moment received are several orders of magnitude higher than those of traditional low orbit satellite, so that the attitude control system of super low orbit satellite is significantly different from that of traditional satellite, and the aerodynamic moment of super low orbit satellite is the most important environmental moment that affects its attitude control accuracy and even determines whether it is stable or not. Therefore, it is necessary to study the aerodynamic moment of super low orbit satellite. SUMMARY

[0003] The technical problem solved by the present application is to overcome the problem of large aerodynamic moment of existing super low orbit satellite, and a super low orbit satellite stability layout is provided, which can effectively reduce the aerodynamic moment of super low orbit satellite, thereby improving the accuracy of super low orbit satellite attitude control.

[0004] The technical solution of the present application is:

[0005] A super low orbit satellite stability layout, comprising a super low orbit satellite body, a swept back solar cell wing and a swept back side plate; the super low orbit satellite body is a regular polygonal prism, the swept back solar cell wing is located on both sides of the super low orbit satellite body and is symmetrically distributed, the swept back side plate is located at the end edge of the solar cell wing away from the super low orbit satellite body and is perpendicular to the solar cell wing, and the swept back side plate is located above the solar cell wing.

[0006] In some implementations, the super low orbit satellite body is a regular octagonal prism.

[0007] In some implementations, the cross-sectional edge length of the regular octagon of the super low orbit satellite body is W, the body length is L, 1m≦L≦30m, and 0.1m≦W≦1m.

[0008] In some implementations, the super low orbit satellite body operates in a super low orbit, and the height of the super low orbit is 100-300km.

[0009] In some implementations, the solar cell wing adopts a horizontal symmetric layout and is located at a rear position in the middle of the super low orbit satellite body.

[0010] In some implementations, the axial displacement of the solar cell wing relative to the head of the ultra-low-orbit satellite body is L1, and 0 < L1 ≤ 0.3L; L is the length of the ultra-low-orbit satellite body.

[0011] In some implementations, the solar cell wing is in a backward-swept structure along the flight direction, and the backward-swept angle θ is in the range of 0 ≤ θ ≤ 60°.

[0012] In some implementations, the length Ls of the solar cell wing near one end of the ultra-low-orbit satellite body is in the range of 0.3L ≤ Ls < L. s The width W of the solar cell wing is in the range of L s < L. s s <2L.

[0013] In some implementations, the backward-swept side plate is located at the tail end of the solar cell wing and is perpendicular to the solar cell wing, and is in a backward-swept structure.

[0014] In some implementations, the backward-swept angle θ of the backward-swept side plate is in the range of 0 ≤ θ ≤ 90°, and the height Hb is in the range of 0 ≤ Hb < L. b b b s .

[0015] In summary, the present application at least includes the following beneficial technical effects:

[0016] (1) The stability-enhancing layout of the ultra-low-orbit satellite provided by the present application adopts a regular octagonal body structure, which can make the cross section closer to a circle than a regular square, provide more equipment loading space, and be more conducive to the layout of solar cell pieces.

[0017] (2) The stability-enhancing layout of the ultra-low-orbit satellite provided by the present application adopts a small-aspect-ratio backward-swept solar cell wing structure (trapezoidal configuration), which helps to reduce the wave resistance of the ultra-low-orbit satellite, thereby reducing the satellite drag and reducing the fuel consumption for compensating the drag of the ultra-low-orbit satellite.

[0018] (3) The stability-enhancing layout of the ultra-low-orbit satellite provided by the present application adopts a backward-swept side plate configuration, which reduces the wave resistance of the ultra-low-orbit satellite while reducing the aerodynamic moment of the ultra-low-orbit satellite, thereby improving the attitude control accuracy of the ultra-low-orbit satellite.

[0019] (4) The overall structure of the present application is simpler and has lower economic cost, which can produce greater social and economic effects and has greater engineering application value. BRIEF DESCRIPTION OF DRAWINGS

[0020] Figure 1 : The stability-enhancing layout of the ultra-low-orbit satellite provided by the present application; ​​​​

[0021] Figure 2 : top view of super low earth orbit satellite;

[0022] Figure 3 : front view of super low earth orbit satellite;

[0023] Figure 4 : pressure contour of super low earth orbit satellite;

[0024] Figure 5 : shear stress contour of super low earth orbit satellite;

[0025] Figure 6 : influence of side plate height on roll moment of super low earth orbit satellite;

[0026] Figure 7 : influence of side plate height on yaw moment of super low earth orbit satellite.

[0027] Table 1: incoming flow conditions of super low earth orbit satellite for stability augmentation layout evaluation example;

[0028] Table 2: aerodynamic characteristics of super low earth orbit satellite when side plate height is 0;

[0029] Table 3: aerodynamic characteristics of super low earth orbit satellite when side plate height is 520mm.

[0030] BRIEF DESCRIPTION OF DRAWINGS: 1, super low earth orbit satellite body; 2, solar cell wing; 3, swept side plate. DETAILED DESCRIPTION

[0031] The present application will be further described in detail below in conjunction with the accompanying drawings and specific embodiments:

[0032] The embodiments of the present application disclose a stability augmentation layout of super low earth orbit satellite, as shown in the drawings, comprising a super low earth orbit satellite body 1, a swept solar cell wing 2 and a swept side plate 3. Figures 1-3

[0033] The super low earth orbit satellite body 1 operates in a super low orbit (100-300km), and the atmosphere in the airspace is thin.

[0034] The super low earth orbit satellite body 1 is a regular octagonal prism, the solar cell wing 2 is located on both sides of the super low earth orbit satellite body and is symmetrically distributed, the swept side plate 3 is located at the tail end of the solar cell wing 2 and is perpendicular to the solar cell wing 2, the swept side plate 3 is located above the solar cell wing 2 and is used for passive control of the attitude of the super low earth orbit satellite, thereby improving the operation stability of the super low earth orbit satellite.

[0035] The cross-sectional side length of the super low earth orbit satellite body 1 perpendicular to the edge line thereof is W, and the body length is L. The specific value range of the side length W and the length L is 1m≤L≤30m and 0.1m≤W≤1m.

[0036] ​The solar panel 2 adopts a horizontally symmetrical layout and is located in the middle and rear of the ultra-low orbit satellite body 1. The axial displacement of the solar panel 2 relative to the ultra-low orbit satellite body 1 is L1, and the value range is: 0 < L1 ≤ 0.3L.

[0037] The solar cell wing 2 has a swept-back structure (i.e., trapezoidal configuration) along the flight direction, with a sweep angle θ ranging from 0 to 60°. The length L of the end closest to the VLEO satellite body 1 is... s The range of values ​​for is: 0.3L ≤ L s <L, width W s The range of values ​​for L is: s ≤W s <2L, the length of the tail end of the solar cell wing 2 is determined by the aforementioned dimensions (θ, L) of the solar cell wing. s W s )Sure.

[0038] The swept-back side plate 3 is located at the tail end of the solar cell wing 2 and is perpendicular to the solar cell wing, forming a swept-back structure with a sweep angle θ. b The range of values ​​for θ is: 0 ≤ θ b ≤90°, height H b The range of values ​​for is: 0 ≤ H b <L s The width above the side panel is determined by the aforementioned dimension (θ) of the side panel. b H b )Sure.

[0039] The stabilization layout designed in this invention can effectively reduce the rolling moment of ultra-low orbit satellites when operating in the deep atmosphere, reduce the impact of the thin atmosphere in the deep atmosphere on the orbit of ultra-low orbit satellites, help improve the attitude control of ultra-low orbit satellites, and improve the operational stability of ultra-low orbit satellites.

[0040] Example:

[0041] The specific implementation scheme of the present invention will be described below with reference to examples.

[0042] As a specific design example of the stabilization layout for ultra-low Earth orbit satellites, such as Figure 1 As shown. In this embodiment, the dimensions of the ultra-low orbit satellite body 1 are: length L = 10000 mm, and the side length of the regular octagon is W = 500 mm; each side of the ultra-low orbit satellite is equipped with a swept-back solar panel with dimensions: length L S =3500mm, width W S = 4000mm, thickness H S =20mm, sweep angle θ=20°; the swept side plate 3 is located at the end of the solar cell wing 2, and its dimensions are: height H b = 520mm, sweep angle θ b= 67.5°. As a comparison, the results without the back-swept side plates 3 (height H b = 0 mm) are also given in this example. The flight altitude is taken as 250 km, and the specific inflow conditions are shown in Table 1.

[0043] Table 1 Inflow conditions of the stability augmentation layout evaluation example of the super low earth orbit satellite

[0044]

[0045] Figure 4 and Figure 5 are respectively the surface pressure and shear stress contours of the super low earth orbit satellite at a flight altitude of 250 km. Tables 2 and 3 are respectively the aerodynamic characteristics of the super low earth orbit satellite with side plate heights of 0 and 520 mm. FD is the drag, Fy is the side force, FL is the lift, Mx is the roll moment, and Mz is the yaw moment. It can be seen from Tables 2 and 3 that the stability augmentation device has a relatively large effect on the roll moment.

[0046] Table 2 Aerodynamic characteristics of the super low earth orbit satellite with side plate height Hb = 0

[0047] β / ° F D / N]] Fy / N F L / N]] Mx / (N.m) Mz / (N.m) -20 3.67E-02 1.06E-03 -7.04E-05 4.30E-04 6.81E-02 -10 2.80E-02 7.16E-04 -4.78E-05 2.33E-04 2.77E-02 0 2.30E-02 1.54E-05 -3.40E-05 -9.10E-06 1.12E-04 10 2.81E-02 -7.37E-04 -4.82E-05 -2.69E-04 -2.81E-02 20 3.67E-02 -1.08E-03 -8.04E-05 -4.05E-04 -6.81E-02

[0048] Table 3 Aerodynamic characteristics of the super low earth orbit satellite with side plate height Hb = 520 mm

[0049] β / ° F D / N]] Fy / N F L / N]] Mx / (N.m) Mz / (N.m) -20 3.96E-02 1.23E-03 -1.19E-04 -2.33E-04 7.44E-02 -10 2.96E-02 8.48E-04 -7.23E-05 -3.19E-05 3.03E-02 0 2.37E-02 1.10E-05 -5.24E-05 8.72E-06 -6.69E-06 10 2.96E-02 -8.49E-04 -7.23E-05 4.07E-05 -3.02E-02 20 3.97E-02 -1.24E-03 -1.32E-04 1.85E-04 -7.49E-02

[0050] Figure 6 is the effect of the height of the back-swept side plate 3 on the roll moment of the super low earth orbit satellite. It can be seen from the figure that when the tail end of the back-swept solar cell wing 2 of the super low earth orbit satellite is not provided with a side plate, the roll moment is large, and the maximum roll moment is 4.30E-04 N.m at a sideslip angle of -20°. After the stability augmentation device side plate is installed, the roll moment is obviously reduced, and the maximum roll moment is -2.33E-04 N.m at a sideslip angle of -20°. It can be seen that after the stability augmentation layout is adopted, the roll moment of the super low earth orbit satellite is obviously improved, which is helpful for the attitude control of the super low earth orbit satellite.

[0051] Figure 7 is the effect of the height of the back-swept side plate 3 on the yaw moment of the super low earth orbit satellite. It can be seen from the figure that the back-swept side plate at the tail end of the back-swept solar cell wing 2 of the super low earth orbit satellite has a relatively small effect on the yaw moment, and the influence is about 9.9%, which is much smaller than the effect on the roll moment.

[0052] The implementation principle of the present application is:

[0053] When flying in ultra-low orbit, the lateral aerodynamic force receiving surface above the satellite's center of mass is increased due to the setting of the swept-back side plate structure, and when the sideslip angle increases, an additional rolling moment is generated, which makes the sideslip angle have a decreasing tendency, thereby realizing the stability increasing function.

[0054] The non-disclosed technology of the present application is common knowledge to those skilled in the art.

[0055] Although the present application is disclosed with the preferred embodiments as above, it is not intended to limit the present application, and any possible changes and modifications can be made by those skilled in the art without departing from the spirit and scope of the present application, therefore, the protection scope of the present application should be defined by the scope of the claims of the present application.

Claims

1. A stabilization configuration for an ultra-low Earth orbit satellite, characterized in that: It includes an ultra-low orbit satellite body (1), solar cell wings (2) and swept-back side plates (3); The ultra-low orbit satellite body (1) is in the shape of a regular prism. The solar cell wings (2) are located on both sides of the ultra-low orbit satellite body (1) and are symmetrically distributed. The swept-back side plates (3) are located at the end edges of the solar cell wings (2) away from the ultra-low orbit satellite body (1) and are perpendicular to the solar cell wings (2). The swept-back side plates (3) are located above the solar cell wings (2); The ultra-low orbit satellite body (1) is in the shape of a regular octagonal prism; The side length of the cross-section of the ultra-low orbit satellite body (1) perpendicular to its own edge line is W, and the body length is L, where 1m ≤ L ≤ 30m and 0.1m ≤ W ≤ 1m; The solar cell wings (2) adopt a horizontally symmetric layout and are located at a position slightly behind the middle of the ultra-low orbit satellite body (1); The axial displacement of the solar cell wings (2) relative to the head of the ultra-low orbit satellite body (1) is L1, and 0 < L1 ≤ 0.3L; L is the length of the ultra-low orbit satellite body; The solar cell wings (2) are in a swept-back structure along the flight direction, and the value range of the swept-back angle θ is: 0 ≤ θ ≤ 60°; The value range of the length Ls of one end of the solar cell wing (2) close to the ultra-low orbit satellite body (1) is: 0.3L ≤ L s <L, and the width W s The value range of is: L s ≤ W s <2L; The swept-back side plates (3) are located at the tail ends of the solar cell wings (2) and are perpendicular to the solar cell wings (2), and are in a swept-back structure; The sweep angle θ of the swept side plate (3) b The range of values ​​for θ is: 0 ≤ θ b ≤90°, height H b The range of values ​​for is: 0 < H b <L s .

2. The stabilization configuration for an ultra-low Earth orbit satellite according to claim 1, characterized in that: The ultra-low orbit satellite body (1) operates in an ultra-low orbit, and the altitude of the ultra-low orbit is 100 - 300 km.

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