Momentum body shape of upper atmosphere aircraft

Abstract

The invention discloses a momentum body appearance of an upper atmospheric aircraft. The momentum body appearance comprises an aircraft head, a body, a sweepback airfoil and a wingtip V-shaped tail. The head of the aircraft is a wedge-shaped polyhedron and is in butt joint with a rear body. The body is a multi-stage trapezoidal boss which shrinks backwards, so that the resistance of the body is reduced; the sweepback airfoil is connected with the body to realize static pitching stability; and the two V tails are positioned at the positions of wingtips. According to the invention, the momentum exchange principle that the upper atmospheric layer gas interacts with the object plane is adopted, a polyhedral aerodynamic shape meeting the low-resistance aerodynamic characteristic is designed, the fusion design of the aerodynamic performance and the solar wing is realized, the aerodynamic resistance compensation requirement of the aircraft in the airspace can be effectively reduced, and the hang time of the aircraft is prolonged.

Description

Technical Field

[0001] The invention relates to an upper atmosphere aircraft momentum body shape, belonging to the field of upper atmosphere aircraft aerodynamic design. Background Art

[0002] The upper atmosphere is located between 100-300km, between near-space and traditional space orbits. It is an airspace that people have always wanted to use but have not used. The research on upper atmosphere ultra-low orbit flight technology has attracted increasing attention from various countries. In recent years, various countries have continuously carried out relevant technical verification and spacecraft research and development to accelerate the occupation of available space resources. Ultra-low orbit has unique geographical advantages such as short orbital period, close distance to the ground and close proximity to atmospheric resources. It has been increasingly highly valued. Focusing on the development and utilization of ultra-low orbit, relevant technical research on ultra-low orbit aircraft is being actively carried out.

[0003] As an emerging flight airspace, the upper atmosphere embodies the high degree of unity and organic integration of aerospace technology. However, the gas density in the upper atmosphere is extremely low, the non-equilibrium of gas flow is stronger, and it has strong multi-scale characteristics. At the same time, the low-density environment causes the impact of the surface to propagate farther, and the aerodynamic and material multi-field coupling effects are serious. The extremely thin atmospheric drag is still the main obstacle to achieving long-term orbital and maneuvering flight in this airspace. To stay in this airspace for a long time like a satellite, it is necessary to use an engine to overcome air resistance and maintain the orbital speed without attenuation. A good low-drag aerodynamic shape can greatly reduce the requirements for the engine and increase the orbital life, which has great engineering application value. Summary of the invention

[0004] The technical problem solved by the present invention is: to overcome the problem of large aerodynamic drag of existing aircraft, and to provide a momentum body shape of an upper atmosphere aircraft, which can effectively reduce the aerodynamic drag of the upper atmosphere aircraft, thereby improving the design performance of the aircraft.

[0005] The technical solution of the present invention is: an upper atmosphere aircraft momentum body shape, including an aircraft head, a body, a swept wing surface and a wing tip V-shaped tail; the aircraft head is connected to the body; the body is composed of a multi-stage trapezoidal boss that gradually shrinks from the head to the tail; the swept wing surface is connected to the body and is symmetrically distributed on both sides of the body; the wing tip V-shaped tail is located at the wing tip position of the swept wing surface and is connected to the swept wing surface.

[0006] The aircraft head is in the shape of a polyhedron wedge.

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

[0008] The aircraft body is composed of a multi-stage trapezoidal boss that gradually shrinks from the head to the tail, and realizes the drag reduction function of the body while meeting the requirements of loading. The number of stages is i, and the length of each stage is L i , the contraction angle of each stage is θ i .

[0009] The length L of each stage i are equal, the contraction angle θ of each stage i In descending order.

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

[0011] The wingspan of the swept wing is W, and the chord length of the wingtip is b1, and the value range is: 0.5m≤W≤10m, 0.1m≤b1≤5m.

[0012] The wing tip V-shaped tail has a wing tip chord length of b2, a thickness of D, a height of H, and an inclination angle ɑ, and the value range is: 0.1m≤b2≤b1, 0.1m≤D≤b2, 0.1m≤H≤W / 2, 0 0 ≤ɑ≤60 0 .

[0013] Solar cells are attached to the surface of the aircraft head, body, swept wing surface and wingtip V-tail.

[0014] The advantages of the present invention compared with the prior art are:

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

[0016] (2) The present invention provides an upper atmosphere aircraft momentum body shape, in which the aircraft body adopts a retracted multi-stage trapezoidal boss design, which can greatly reduce the aerodynamic resistance of the body while meeting the same loading requirements.

[0017] (3) The polyhedral structural design of the present invention realizes the integrated design of the drag-reducing aerodynamic shape and the solar wing. The structure is simple and compact, which can not only meet the low-drag stable flight of the aircraft but also provide solar power generation. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 : A schematic diagram of the shape of a momentum body of an upper atmosphere aircraft of the present invention;

[0019] Figure 2 : Schematic diagram of the dimensions of the momentum body of the upper atmosphere vehicle;

[0020] Figure 3 : A pressure cloud diagram of the flow field of the momentum body of an upper atmosphere aircraft;

[0021] Figure 4 : Schematic diagram of solar cell arrangement. DETAILED DESCRIPTION

[0022] like Figure 1 As shown, the present invention provides an upper atmosphere aircraft momentum body shape, including an aircraft head 1, a body 2, a swept wing surface 3 and a wingtip V-shaped tail 4; the aircraft head 1 is a polyhedral wedge-shaped structure, connected to the body 2, the body 2 is composed of a multi-stage trapezoidal boss that shrinks backward, i.e., in the x direction, the swept wing surface 3 is connected to the body 2, and is symmetrically distributed on both sides of the aircraft body 2, and the wingtip V-shaped tail 4 is located at the wingtip position of the swept wing surface 3 and is connected to the swept wing surface 3.

[0023] The aircraft head 1 is a polyhedral wedge-shaped, which realizes the head drag reduction function, and its wedge angle is θ0, the length is L0, and it is connected with the rear body. Specific size range: 1 0 ≤θ0≤89 0 , 0.1m≤L0≤10m.

[0024] The aircraft body 2 is a multi-stage trapezoidal boss that shrinks backward, that is, in the x direction, and realizes the body drag reduction function while meeting the requirements of loading. The number of stages is i and the length is L. i , the contraction angle is θ i , specific value range: 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 rearward to achieve pitch static stability. Its wingspan is W and its wingtip chord length is b1, with specific value ranges of: 0.5m≤W≤10m, 0.1m≤b1≤5m.

[0026] The wing tip V-shaped tail 4 is located at the wing tip position and connected to the wing surface 3, which can avoid the wing surface blocking problem during flight in this airspace and improve the lateral heading stability. The wing tip chord length is b2, the thickness is D, the height is H, and the inclination angle ɑ. The specific value range is: 0.1m≤b2≤b1, 0.1m≤D≤b2, 0.1m≤H≤W / 2, 0 0 ≤ɑ≤60 0 .

[0027] like Figure 4 As shown, the entire surface of the aircraft is covered with solar cells, realizing the fusion design of aerodynamic shape and solar wings.

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

[0029] As a specific design example of the momentum body shape of an upper atmosphere vehicle, Figure 2 As shown. The specific dimensions of the aircraft body in this example are: the angle of the head wedge is 30 degrees and the length is 3000mm; the multi-stage trapezoidal boss of the aircraft body is 3 levels, divided into the first section 21, the second section 22 and the third section 23, the length is 1000mm, and the change of the contraction angle is 2 degrees respectively; the wingspan of the swept wing is 2600mm, and the chord length of the wing tip is 1000mm; the chord length of the wing tip of the two V-tails is 500mm, the thickness is 30mm, the height is 500mm, and the inclination angle is 30 degrees. The calculated flight altitudes are 100km, 120km, 150km, 200km, 250km and 300km, respectively, in the upper atmosphere airspace. The flight speed is the orbital speed of 7800m / s.

[0030] Figure 3 The pressure cloud diagram of the aircraft flow field at 100km and 120km. The pressure cloud diagram of the aircraft surface in the upper atmosphere when the flight altitude is 200km. It can be seen from the figure that as the flight altitude increases, the compressibility of the aircraft flow field decreases, the aircraft's influence area increases, and the pressure is higher on the wedge surface and windward surface of the aircraft head.

[0031] Table 1 shows the aerodynamic drag of the aircraft at different altitudes. The aerodynamic drag of the low-drag aerodynamic shape aircraft at different antenna installation angles. It can be found that with the increase of flight altitude, the aerodynamic drag of the aircraft decreases sharply. At 100km, the aircraft drag is about 32N, while at 200km it is about 16mN, and at 300km it is reduced to 1mN. For conventional satellites of the same size, this greatly reduces the drag, which can reduce the fuel consumption of the electric propulsion engine and extend the on-orbit life of the aircraft.

[0032] Table 1 Aerodynamic drag of 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 the present invention are common knowledge to those skilled in the art.

Claims

1. An upper atmosphere vehicle momentum body shape, characterized in that: The invention comprises an aircraft head (1), a body (2), a swept wing surface (3) and a wing tip V-shaped tail (4); the aircraft head (1) is connected to the body (2); the body (2) is composed of a multi-stage trapezoidal boss that gradually shrinks from the head 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 wing tip V-shaped tail (4) is located at the wing tip of the swept wing surface (3) and is connected to the swept wing surface (3).

2. The upper atmosphere vehicle momentum body shape according to claim 1, characterized in that: The aircraft head (1) is in the shape of a polyhedral wedge.

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

4. The upper atmosphere vehicle momentum body shape according to claim 1, characterized in that: The aircraft body (2) is composed of a multi-stage trapezoidal boss that gradually shrinks from the head to the tail, and realizes the body drag reduction function while meeting the requirements of loading. The number of stages is i, and the length of each stage is L. i , the contraction angle of each stage is θ i .

5. The upper atmosphere vehicle momentum body shape according to claim 4, characterized in that: The length L of each stage i are equal, the contraction angle θ of each stage i In descending order.

6. The upper atmosphere vehicle momentum body shape according to claim 4, characterized in that: 0.1m≤L i ≤10m, 0.01 0 ≤θ i ≤60 0 , 1≤i≤10.

7. The upper atmosphere vehicle momentum body shape according to claim 1, characterized in that: The wingspan length of the swept wing surface (3) is W, and the chord length of the wing tip is b1, and the value range is: 0.5m≤W≤10m, 0.1m≤b1≤5m.

8. The upper atmosphere vehicle momentum body shape according to claim 1, characterized in that: The wing tip V-shaped tail (4) has a wing tip chord length of b2, a thickness of D, a height of H, and an inclination angle ɑ, and the value range is: 0.1m≤b2≤b1, 0.1m≤D≤b2, 0.1m≤H≤W / 2, 0 0 ≤ɑ≤60 0 .

9. The upper atmosphere vehicle momentum body shape according to claim 1, characterized in that: Solar cell sheets are attached to the surfaces of the aircraft head (1), the main body (2), the swept wing surface (3) and the wing tip V-shaped tail (4).

Images