A momentum body shape for an upper atmospheric spacecraft

Abstract

This invention discloses a momentum body shape for an upper atmospheric vehicle, comprising a nose, body, swept wing surfaces, and V-tails at the wingtips. The nose is a wedge-shaped polyhedron that connects to the rear body; the body is a multi-tiered trapezoidal protrusion that tapers backward to reduce drag; the swept wing surfaces are connected to the body to achieve pitch static stability; and two V-tails are located at the wingtips. This invention utilizes the momentum exchange principle of interaction between upper atmospheric gas and the surface to design a polyhedral aerodynamic shape that satisfies low-drag aerodynamic characteristics. It achieves a fusion of aerodynamic performance and solar array design, effectively reducing the aerodynamic drag compensation requirements in this airspace and extending the vehicle's loiter time.

Description

Technical Field

[0001] This invention relates to the momentum body shape of an upper atmospheric vehicle, belonging to the field of upper atmospheric vehicle aerodynamic design. Background Technology

[0002] The upper atmosphere, located between 100 and 300 km, lies between near space and traditional space orbits, a region of airspace that has long been desired but untapped. Research on ultra-low Earth orbit (ULO) flight technology in the upper atmosphere is increasingly attracting global attention. In recent years, countries have been continuously conducting related technology verification and spacecraft development to accelerate the acquisition of usable space resources. ULE has unique geographical advantages, including a short orbital period, close proximity to the ground, and proximity to atmospheric resources, making it increasingly important. Research on ULE spacecraft technologies is actively underway to support its development and utilization.

[0003] As an emerging flight airspace, the upper atmosphere embodies a high degree of unity and organic integration of aerospace technology. However, the upper atmosphere has extremely low gas density, stronger non-equilibrium gas flow, and strong multi-scale characteristics. Simultaneously, the low-density environment causes the effects of the object surface to propagate farther, resulting in severe aerodynamic and material multi-field coupling effects. The extremely thin atmospheric drag remains a major obstacle to long-term on-orbit and maneuvering flight in this airspace. To achieve long-term agile operation in this airspace like a satellite, engines are needed to overcome air resistance and maintain orbital speed. A good low-drag aerodynamic shape can significantly reduce engine requirements, increase on-orbit lifespan, and has significant engineering application value. Summary of the Invention

[0004] The technical problem solved by this invention is to overcome the problem of high aerodynamic drag in existing aircraft and to provide a momentum body shape for upper atmospheric aircraft, which can effectively reduce the aerodynamic drag of upper atmospheric aircraft, thereby improving the design performance of aircraft.

[0005] The technical solution of the present invention is: a momentum body shape for an upper atmospheric spacecraft, comprising a head, a body, swept wing surfaces and a wingtip V-tail; the head of the spacecraft is connected to the body; the body is composed of multiple trapezoidal protrusions that gradually taper from the head to the tail; the swept wing surfaces are connected to the body and symmetrically distributed on both sides of the body; the wingtip V-tail is located at the wingtip of the swept wing surface and is connected to the swept wing surface.

[0006] The nose of the aircraft is a polyhedral wedge shape.

[0007] The wedge angle θ0 of the aircraft's nose satisfies 1 0 ≤θ0≤89 0 The length L0 satisfies 0.1m≤L0≤10m.

[0008] The aircraft body is composed of multiple trapezoidal protrusions that gradually taper from the head to the tail, achieving drag reduction while meeting loading requirements. The number of protrusions is i, and the length of each protrusion is L. i The contraction angle of each stage is θ. i .

[0009] The length L of each level i All are equal, and the contraction angle θ of each level is equal. i Decreasing sequentially.

[0010] The 0.1m≤L i ≤10m, 0.01 0 ≤θ i ≤60 0 , 1≤i≤10.

[0011] The swept wing surface has a wingspan of W and a wingtip chord length of b1, with values ​​ranging from 0.5m ≤ W ≤ 10m to 0.1m ≤ b1 ≤ 5m.

[0012] The wingtip V-tail has a wingtip chord length of b2, a thickness of D, a height of H, and a tilt angle α, with values ​​ranging from: 0.1m ≤ b2 ≤ b1, 0.1m ≤ D ≤ b2, 0.1m ≤ H ≤ W / 2, 0 0 ≤ɑ≤60 0 .

[0013] Solar panels are attached to the surfaces of the aircraft’s nose, body, swept wing surfaces, and wingtip V-tail.

[0014] Advantages of this invention compared to existing technologies:

[0015] (1) The present invention provides a momentum body shape for an upper atmospheric spacecraft, which adopts a head polyhedral wedge structure to effectively reduce the aerodynamic drag of the head of the spacecraft in the airspace.

[0016] (2) The present invention provides a momentum body shape for an upper atmospheric spacecraft. The spacecraft body adopts a multi-stage trapezoidal boss design with contraction, which can greatly reduce the aerodynamic drag of the body while meeting the same loading requirements.

[0017] (3) The polyhedral structure design of this invention realizes the integration of drag-reducing aerodynamic shape and solar wing design. The structure is simple and compact, which can not only meet the low drag and stable flight of the aircraft, but also provide solar power generation. Attached Figure Description

[0018] Figure 1 This invention provides a schematic diagram of the momentum body shape of an upper atmospheric spacecraft.

[0019] Figure 2 : Schematic diagram of the momentum body dimensions of an upper atmospheric spacecraft;

[0020] Figure 3 Pressure cloud map of the flow field of a momentum body shape for an upper atmospheric spacecraft;

[0021] Figure 4 Schematic diagram of solar cell arrangement. Detailed Implementation

[0022] like Figure 1 As shown, the present invention discloses a momentum body shape for an upper atmospheric spacecraft, comprising a head 1, a body 2, swept wing surfaces 3, and a wingtip V-tail 4. The head 1 is a polyhedral wedge structure connected to the body 2. The body 2 is composed of multi-stage trapezoidal protrusions that contract backward in the x-direction. The swept wing surfaces 3 are connected to the body 2 and symmetrically distributed on both sides of the body 2. The wingtip V-tail 4 is located at the wingtip of the swept wing surface 3 and is connected to the swept wing surface 3.

[0023] The aircraft's nose section 1 is a polyhedral wedge shape, serving to reduce drag. Its wedge angle is θ0, and its length is L0, docking with the rear body. Specific dimensional values ​​range from 1... 0 ≤θ0≤89 0 , 0.1m≤L0≤10m.

[0024] The aircraft body 2 is a multi-stage trapezoidal protrusion that tapers backward, i.e., in the x-direction. This design reduces drag while meeting loading requirements. It has i stages and a length of L. i The contraction angle is θ i The specific value range is: 0.1m ≤ L i ≤10m, 0.01 0 ≤θ i ≤60 0 , 1≤i≤10.

[0025] The swept wing surface 3 is connected to the main body 2 and is positioned relatively far back to achieve pitch static stability. Its wingspan is W and its wingtip chord length is b1, with specific values ​​ranging from 0.5m to 10m and 0.1m to 5m.

[0026] The wingtip V-tail 4 is located at the wingtip and connects to the wing surface 3. This avoids wing surface obstruction during flight in this airspace and improves lateral stability. Its wingtip chord length is b2, thickness is D, height is H, and tilt angle α, with specific values ​​ranging from: 0.1m ≤ b2 ≤ b1, 0.1m ≤ D ≤ b2, 0.1m ≤ H ≤ W / 2, 0 0 ≤ɑ≤60 0 .

[0027] like Figure 4 As shown, solar panels are attached to the entire surface of the aircraft, achieving a fusion design between the aerodynamic shape and the solar array.

[0028] The specific implementation scheme of the present invention will be described below with reference to examples.

[0029] As a specific design example of the momentum body shape of an upper atmospheric spacecraft, such as Figure 2 As shown. The specific dimensions of the aircraft in this example are as follows: the nose wedge angle is 30 degrees, and the length is 3000 mm; the multi-stage trapezoidal protrusions that retract into the aircraft body are in three stages, divided into three sections: section 21, section 22, and section 23, each with a length of 1000 mm and a retraction angle change of 2 degrees for each stage; the swept wing surface has a wingspan of 2600 mm and a wingtip chord length of 1000 mm; the two V-tails have a wingtip chord length of 500 mm, a thickness of 30 mm, a height of 500 mm, and a tilt angle of 30 degrees. The calculated flight altitudes are 100 km, 120 km, 150 km, 200 km, 250 km, and 300 km, located in the upper atmosphere. The flight speed is taken as the orbital velocity of 7800 m / s.

[0030] Figure 3 The figures show pressure cloud maps of the flow field for aircraft at altitudes of 100km and 120km, and pressure cloud maps of the aircraft surface in the upper atmosphere at an altitude of 200km. As can be seen from the figures, with increasing flight altitude, the compressibility of the aircraft's flow field decreases, the area of ​​influence of the aircraft increases, and the pressure is higher at the wedge-shaped surface of the aircraft's nose and the windward side.

[0031] Table 1 shows the aerodynamic drag of the aircraft at different altitudes. The aerodynamic drag of the low-drag aerodynamic shape aircraft is shown at different antenna installation angles. It can be observed that the aerodynamic drag decreases sharply with increasing flight altitude. At 100km, the drag is approximately 32N, while at 200km it is approximately 16mN, and at 300km it decreases to 1mN. For a conventional satellite of the same volume, this significant reduction in drag can reduce fuel consumption of the electric propulsion engine and extend the on-orbit life of the aircraft.

[0032] Table 1 Aerodynamic drag of the aircraft at different altitudes

[0033] 100 120 150 160 180 200 250 32N 1.6N 132mN 80mN 34mN 16mN 4mN

[0034] The undisclosed technologies in this invention are common knowledge to those skilled in the art.

Claims

1. A momentum body shape for an upper atmospheric spacecraft, characterized in that: It includes the aircraft nose (1), body (2), swept wing surface (3) and wingtip V-tail (4); the aircraft nose (1) is connected to the body (2); the body (2) is composed of multi-level trapezoidal protrusions that gradually taper from the nose to the tail; the swept wing surface (3) is connected to the body (2) and is symmetrically distributed on both sides of the body (2); the wingtip V-tail (4) is located at the wingtip of the swept wing surface (3) and is connected to the swept wing surface (3); The main body (2) is composed of a multi-stage trapezoidal protrusion that gradually tapers from the head to the tail, achieving drag reduction while meeting the loading requirements. It has i stages, and the length of each stage is L. i The contraction angle of each stage is θ. i .

2. The momentum body shape of an upper atmospheric spacecraft according to claim 1, characterized in that: The nose (1) of the aircraft is a polyhedral wedge shape.

3. The momentum body shape of an upper atmospheric spacecraft according to claim 2, characterized in that: The wedge angle θ0 of the aircraft nose (1) satisfies 1 0 ≤θ0≤89 0 The length L0 satisfies 0.1m≤L0≤10m.

4. The momentum body shape of an upper atmospheric spacecraft according to claim 3, characterized in that: The length L of each level i All are equal, and the contraction angle θ of each level is equal. i Decreasing sequentially.

5. The momentum body shape of an upper atmospheric spacecraft according to claim 3, characterized in that: 0.1m≤L i ≤10m,0.01 0 ≤θ i ≤60 0 ,1≤i≤10。 6. The momentum body shape of an upper atmospheric spacecraft according to claim 1, characterized in that: The swept wing surface (3) has a wingspan of W and a wingtip chord length of b1, with the following values: 0.5m≤W≤10m, 0.1m≤b1≤5m.

7. The momentum body shape of an upper atmospheric spacecraft according to claim 1, characterized in that: The wingtip V-tail (4) has a wingtip chord length of b2, a thickness of D, a height of H, and a tilt angle α, with the following values: 0.1m ≤ b2 ≤ b1, 0.1m ≤ D ≤ b2, 0.1m ≤ H ≤ W / 2, 0 0 ≤ɑ≤60 0 .

8. The momentum body shape of an upper atmospheric spacecraft according to claim 1, characterized in that: Solar panels are attached to the surfaces of the aircraft’s nose (1), body (2), swept wing surface (3) and wingtip V-tail (4).

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