Adjustable air-breathing power ultra-low orbit satellite configuration

Abstract

The invention provides an adjustable air-breathing power ultra-low orbit satellite configuration. The adjustable air-breathing power ultra-low orbit satellite configuration comprises an adjustable closed head part, a body, a stable wing surface and a contraction tail part, the adjustable closing head and the contraction tail are connected to the two opposite ends of the body respectively, and the stable wing face is connected to the side, close to the contraction tail, of the body. The design that the adjustable closing head is an openable / closable head is adopted, the adjustable closing head is a spherical head after being closed when a satellite does not need to inhale, and resistance is reduced; and after being expanded, the air inlet channel can be contracted into an inwards-concave air inlet channel, so that active compression of air is achieved. Therefore, task requirements under different flight heights can be met through flexible switching of the inspiration working mode and the non-inspiration working mode, the aerodynamic resistance of the satellite in an ultra-low orbit is effectively reduced, and the hang time of the satellite is prolonged.

Description

Technical Field

[0001] The present invention relates to the technical field of low-orbit satellite aerodynamic design, and in particular to an adjustable air-breathing powered ultra-low-orbit satellite configuration. Background Art

[0002] Ultra-low earth orbit (ULEO) satellites are located between 100 and 300 km, between near-space and traditional space orbits. There are no long-term spacecraft in this airspace. In recent years, the development and utilization of this airspace has gradually attracted attention from countries around the world, and major space powers have successively carried out technical verification work in this airspace to seize space resources. Ultra-low earth orbits offer unique geographical advantages such as short orbital periods, close proximity to the ground, and close proximity to atmospheric resources. To develop and utilize ultra-low earth orbits, major space powers, led by the United States and Russia, are actively conducting technical research related to ultra-low earth orbit satellites.

[0003] As an emerging airspace, the presence of a thin, low-density atmosphere in this region makes aircraft design in this region distinct from both traditional low-altitude, high-density aircraft and spacecraft orbiting in space, where the effects of air are relatively weak. Consequently, comprehensive design theories and methods are still lacking. The drag of this thin atmosphere is a major obstacle to flight in this region. To maintain long-term operations in this region, like satellites, engines are required to overcome air resistance and maintain orbital speed. A well-designed low-drag aerodynamic shape can significantly reduce engine requirements and extend on-orbit life, offering significant engineering application value. Summary of the Invention

[0004] The purpose of the present invention is to provide an adjustable air-breathing powered ultra-low orbit satellite configuration, which can effectively reduce the aerodynamic drag of the satellite in the ultra-low orbit and extend the satellite's flight time;

[0005] The present invention provides an adjustable air-breathing powered ultra-low-orbit satellite configuration, comprising an adjustable closed head, a body, a stabilizing wing surface, and a retractable tail; the adjustable closed head and the retractable tail are respectively connected to opposite ends of the body, and the stabilizing wing surface is connected to one side of the body adjacent to the retractable tail.

[0006] Furthermore, the adjustable closing head includes an opening and closing structure.

[0007] Furthermore, the adjustable closing head is closed into a spherical head when the satellite is not inhaling air.

[0008] Furthermore, the adjustable closed head is expanded when the satellite inhales and then contracts into an inwardly concave air inlet.

[0009] Furthermore, the adjustable closed head, the body and the retractable tail constitute a capsule-shaped satellite body.

[0010] Furthermore, the main body is a cylindrical shell.

[0011] Furthermore, there are solar cells on the surface of the body.

[0012] Furthermore, the surface of the stabilizing wing is provided with solar cells.

[0013] Furthermore, the sweep angle of the stabilizing wing surface is θ, the span of the single wing surface is W, the chord length of the wing root is B, and the chord length of the wing tip is b, and the value range is: 0≤θ≤80°, 0.5m≤W≤30m, 0.1m≤B≤L1, 0m≤b≤B.

[0014] Furthermore, there are multiple stabilizing wing surfaces, which are circumferentially connected to the four sides of the body.

[0015] The present invention utilizes an adjustable, openable / closable head design. When closed, it forms a spherical head when the satellite doesn't need to inhale, reducing drag. When opened, it retracts into an inward-concave inlet, achieving active gas compression. This allows the present invention to flexibly switch between inhalation and non-inhalation modes to meet mission requirements at varying flight altitudes, effectively reducing aerodynamic drag in ultra-low orbits and extending satellite flight time. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0017] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0018] Figure 2 A schematic diagram of the adjustable closed head of the present invention being opened and then contracted into a concave air inlet;

[0019] Figure 3 This is a schematic diagram of the dimensions of the satellite body of the present invention;

[0020] Figure 4 Schematic diagram of the dimensions of the stabilizing airfoil of the present invention;

[0021] Figure 5 The flow field and surface pressure cloud map of the present invention;

[0022] Description of reference numerals:

[0023] 1-Adjustable closed head; 2-Main body; 3-Stabilizing wing surface; 4-Retractable tail; 5-Concave air inlet. DETAILED DESCRIPTION

[0024] The following will clearly and completely describe the technical solutions of the present invention in conjunction with the embodiments. Obviously, the embodiments described are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0025] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like to indicate directions or positional relationships based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operate in a specific direction, and therefore should not be understood as limiting the present invention.

[0026] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the said features. In the description of the present invention, "multiple" means two or more, unless otherwise clearly and specifically defined. In addition, the terms "installed", "connected", and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be a communication between the two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to the specific circumstances.

[0027] Example 1

[0028] like Figure 1 and Figure 2As shown, the present invention provides an adjustable, air-breathing, powered ultra-low-orbit satellite configuration. The satellite body is capsule-shaped and includes an adjustable, closed head 1, a body 2, stabilizing surfaces 3, and a retractable tail 4. The adjustable, closed head 1 is connected to the front end of the body 2, and the retractable tail 4 is connected to the rear end of the body 2. The stabilizing surfaces 3 are connected to the side of the body 2 adjacent to the retractable tail 4, with multiple stabilizing surfaces 3 distributed around the body 2. The retractable tail 4 is located behind the stabilizing surfaces 3. The body is composed of a cylindrical surface, with the stabilizing surfaces arranged in the tail area. Solar cells can be attached to the entire surface, achieving a fusion of aerodynamic shape and solar panels, capturing solar energy from multiple angles. The cylindrical body reduces drag. The stabilizing surfaces are connected to the body to achieve aerodynamic stability control. The retractable tail reduces drag and serves as a power cabin.

[0029] The adjustable closure head 1 comprises an openable / closable head structure. When the satellite does not need to inhale, the adjustable closure head 1 closes to a spherical shape. When the satellite needs to inhale, it opens and contracts to form an inwardly concave air inlet 5, with a diameter D of 0.5m≤D≤5m.

[0030] The satellite body consists of a concave air inlet 5 and a cylindrical shell. The concave air inlet 5 is formed by the spherical head opening and then contracting inward. It realizes the drag reduction function of the body while meeting the loading requirements. It is connected to the satellite's adjustable closed head 1. Solar cells can be attached to the surface as needed. The diameter D is the same as that of the satellite's adjustable closed head 1, that is, it meets 0.5m≤D≤5m. The length L1 of the satellite body can be based on the satellite loading requirements, and the value range is: 0.5m≤L1≤20m.

[0031] The surface of the stabilizing wing 3 can be attached to solar cells. The sweep angle of the stabilizing wing 3 is θ, the span of the single wing is W, the root chord length is B, and the wingtip chord length is b. The values ​​range are: 0≤θ≤80°, 0.5m≤W≤30m, 0.1m≤B≤L1, and 0m≤b≤B. There are multiple stabilizing wing surfaces 3, which are circumferentially connected to the body 2. The number of stabilizing wing surfaces 3 is n, and the value range is: 2≤n≤10.

[0032] The length of the contraction tail 4 is L2, and the diameter is d, and the value range is: 0.1m≤L2≤L1, 0.01m≤d≤D.

[0033] The present invention integrates an adjustable nose air intake with the satellite body, effectively reducing drag while meeting mission requirements. Furthermore, the fusion of the aerodynamic shape and solar wing design creates a simple and compact structure, effectively reducing aerodynamic drag in ultra-low orbits and extending the satellite's flight time, ensuring low-drag, stable flight while providing solar power generation.

[0034] As a specific design example, Figure 3 and Figure 4The specific satellite dimensions in this example are: 2400mm diameter, 6000mm length, 30-degree stabilizing wing sweep, 3800mm single-wing span, 1900mm wing root chord, 120mm wingtip chord, 1500mm tail length, and 1500mm tail diameter. The calculated flight altitude is 100km, and the flight speed is the orbital velocity of 7800m / s.

[0035] Figure 5 This is a cloud map of the satellite flow field and surface pressure. It can be seen from the figure that when the satellite's head is open, the incoming gas is compressed inside the air inlet, and the local pressure increases sharply; the compression of the leading edge of the satellite wing also increases the local flow field pressure. It can also be clearly seen from the satellite surface that a high-pressure area is formed in the air inlet and the leading edge of the wing, while the pressure at the tail of the satellite is relatively low. This flow field structural feature is consistent with the expected design.

[0036] Finally, it should be noted that the undisclosed technologies of this invention are common knowledge to those skilled in the art. The above embodiments are intended only to illustrate the technical solutions of this invention and are not intended to limit them. Although the invention has been described in detail with reference to the above embodiments, those skilled in the art will understand that they may modify the technical solutions described in the above embodiments or replace some or all of the technical features therein with equivalents. Such modifications or replacements do not deviate from the essence of the corresponding technical solutions within the scope of the technical solutions of the embodiments of this invention.

Claims

1. An adjustable air-breathing powered ultra-low-orbit satellite configuration, characterized by: It comprises an adjustable closed head (1), a body (2), a stabilizing wing (3) and a retractable tail (4); The adjustable closing head (1) and the retracted tail (4) are respectively connected to opposite ends of the body (2), and the stabilizing wing (3) is connected to a side of the body (2) adjacent to the retracted tail (4).

2. The adjustable air-breathing powered ultra-low-orbit satellite configuration according to claim 1 is characterized in that: The adjustable closing head (1) comprises an opening and closing structure.

3. The adjustable air-breathing powered ultra-low-orbit satellite configuration according to claim 2 is characterized in that: The adjustable closing head (1) is closed into a spherical head when the satellite is not inhaling air.

4. The adjustable air-breathing powered ultra-low-orbit satellite configuration according to claim 2 is characterized in that: The adjustable closed head (1) is opened when the satellite inhales and then contracts to form an inwardly concave air inlet (5).

5. The adjustable air-breathing powered ultra-low-orbit satellite configuration according to claim 1 is characterized in that: The adjustable closed head (1), the body (2) and the retractable tail (4) form a capsule-shaped satellite body.

6. The adjustable air-breathing powered ultra-low-orbit satellite configuration according to claim 1 is characterized in that: The body (2) is a cylindrical shell.

7. The adjustable air-breathing powered ultra-low-orbit satellite configuration according to claim 1 is characterized in that: The surface of the body (2) is provided with a solar cell.

8. The adjustable air-breathing powered ultra-low-orbit satellite configuration according to claim 1 is characterized in that: The surface of the stabilizing wing (3) is provided with solar cells.

9. The adjustable air-breathing powered ultra-low-orbit satellite configuration according to claim 1 is characterized in that: The sweep angle of the stabilizing wing surface (3) is θ, the span of the single wing surface is W, the chord length of the wing root is B, and the chord length of the wing tip is b, and the value range is: 0≤θ≤80°, 0.5m≤W≤30m, 0.1m≤B≤L1, 0m≤b≤B.

10. The adjustable air-breathing powered ultra-low-orbit satellite configuration according to claim 1 is characterized in that: There are multiple stabilizing wing surfaces (3), which are circumferentially connected around the four sides of the body (2).

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