CN110539898A - A rocket engine integrated waverider aircraft - Google Patents

Abstract

A rocket engine integrated waverider aircraft, comprising a waverider wing (1), a load compartment (2), an engine compartment (3), a tail compartment (5), a V tail (4) and an engine tail nozzle (6) ); the load compartment (2), the engine compartment (3) and the tail compartment (5) are successively connected by transition to form the fuselage; the waverider wing (1) is located under the fuselage, and the V tail (4) is symmetrically installed in the engine compartment ( 3) Above the tail and tail compartment (5); the engine tail nozzle (6) protrudes from the rear end face of the tail compartment (5). The waverider aircraft of the present invention can solve and avoid the existing technologies such as poor shape stability characteristics of the combined body of the boost-gliding hypersonic aircraft and the booster, high risk of separation between stages with high dynamic pressure in non-axisymmetric shape, and large aerodynamic resistance in the active section. problems, and achieve overall performance indicators such as higher lift-to-drag ratio and higher loading volume utilization.

Description

A rocket engine integrated waverider aircraft

technical field

The invention relates to a waverider hypersonic aircraft powered by a solid rocket, which can be applied to boost gliding hypersonic flight.

Background technique

Near-space boost-gliding vehicles generally use solid rocket boosters to obtain initial velocity. As shown in Figure 1, after the flight of the rocket's active segment is completed, the vehicle and the booster are separated, and then the vehicle flies in an unpowered gliding manner. In order to achieve long-distance and long-term gliding flight, the near-space gliding vehicle needs to adopt a symmetrical aerodynamic layout with a high lift-to-drag ratio. The booster rocket that is symmetrical with the axis is generally connected in series during launch, which brings the combination of the aircraft and the booster. There are technical problems such as poor body shape stability, non-axisymmetric shape, high dynamic pressure, high risk of separation between stages, and large aerodynamic resistance in the active section.

SUMMARY OF THE INVENTION

The technical problem to be solved by the present invention is: to overcome the deficiencies of the prior art, the present invention provides a rocket motor integrated waverider aircraft, the booster rocket and the high lift-to-drag ratio gliding aircraft are integrated, and the solid rocket motor and the waverider are integrated. The body is designed in an integrated manner to achieve overall performance indicators such as high lift-to-drag ratio, high loading volume utilization rate, and low structural quality coefficient.

The technical scheme adopted in the present invention is: a rocket engine integrated waverider aircraft, comprising a waverider wing, a load compartment, an engine compartment, a tail compartment, a V tail and an engine tail nozzle; a load compartment, an engine compartment and a tail The cabins are connected in turn to form the fuselage; the waverider wing is located under the fuselage, the V-tail is symmetrically installed at the rear of the engine compartment and above the tail compartment; the engine tail nozzle protrudes from the rear end face of the tail compartment.

The waverider wing is obtained by the streamline tracing method based on the kiss-cut cone waverider configuration. By giving the exit profile of the lower surface, the forward streamline tracing is performed in each kiss-cut plane to generate the lower surface of the waverider configuration. ; The upper surface of the waverider configuration is a free flow surface, and the shape of the lower surface of the waverider configuration remains unchanged. The upper surface of the waverider configuration is expanded by the fuselage, which is spliced with the load compartment, engine compartment and tail compartment respectively. Corner transition.

The load compartment includes a front section, a middle section, and a tail section; the front section is duckbill-shaped; the middle section is raised upward, and the cross section is parabolic; the tail section is circular in cross section, connecting the engine compartment.

The engine compartment is truncated, the front end is connected to the load compartment, and the rear end is connected to the tail compartment.

A truncated solid motor is selected as the power device of the waverider aircraft, and the engine casing is used as a part of the aircraft fuselage.

The cone-shaped solid motor has a taper of less than 5°.

The tail cabin is cylindrical, and the tail end is connected to the engine tail nozzle.

There are two V-tails, and the included angle between the two V-tails is 80° to 100°.

The trailing edge of the waverider wing is equipped with a pneumatic control surface.

The trailing edge of the V-tail is fitted with a pneumatically controlled rudder surface.

The advantages of the present invention compared with the prior art are as follows:

The invention integrates the booster rocket and the waverider aircraft, and does not need to separate the high dynamic pressure in the atmosphere between the booster and the gliding aircraft, thereby reducing the technical risk. The aircraft of the present invention adopts the wave riding design method to design the wings, and can obtain a higher lift-to-drag ratio. The aircraft of the present invention uses the solid rocket motor structure as a part of the entire aircraft structure, which can reduce the overall structural quality factor. The aircraft of the present invention can reduce the aerodynamic resistance of the launching active section, so as to obtain a higher initial velocity. The aircraft of the present invention has a larger load space.

Description of drawings

FIG. 1 is a three-dimensional schematic diagram of an existing hyper-gliding vehicle and a booster assembly.

FIG. 2 is a three-dimensional outline view of the rocket engine/body integrated waverider aircraft of the present invention.

Figure 3 is a schematic diagram of a longitudinal section of the fuselage.

FIG. 4 is a comparison diagram of the aerodynamic resistance of the integrated waverider of the present invention and the existing warhead/booster combination.

Detailed ways

The specific embodiments of the present invention will be described below with reference to examples.

As shown in Figure 2, a rocket engine integrated waverider aircraft includes a waverider wing 1, a load compartment 2, an engine compartment 3, a tail compartment 5, a V tail 4 and an engine tail nozzle 6; the load compartment 2. The engine compartment 3 and the tail compartment 5 form a fuselage, and the fuselage is located above the wing 1; the V-tail 4 is located above the fuselage.

As shown in FIG. 3 , the present invention provides a waverider aircraft integrated with a solid rocket motor. The design principle of waverider wing 1 is based on the streamline tracing method of the kiss-cut cone waverider configuration. The forward streamline is traced to generate the lower surface of the waverider configuration. The upper surface of the waverider configuration is a free flow surface. The shape of the lower surface of the waverider configuration is kept unchanged, and the upper surface is designed for fuselage expansion. , The engine compartment 3 and the tail compartment 5 are spliced together, there is no lead angle transition at the splicing, and there are obvious characteristic lines;

The front section of the load compartment 2 is duckbill-shaped, the middle section is raised upward, the cross section in the vertical direction of the fuselage is parabolic, and the cross section of the tail section is circular, which is connected to the engine compartment 3;

The engine compartment 3 is in the shape of a truncated truncated cone, and the front and rear ends are circular with different radii. The front end is connected to the load compartment 2, and the rear end is connected to the tail compartment 5. The small conic (less than 5°) circular truncated solid engine 8 is used as the waverider aircraft. The engine casing is used as a part of the fuselage of the aircraft, and the load compartment 7 located at the head and the tail compartment 9 located at the tail together form the fuselage of the aircraft, as shown in Figure 3;

The tail cabin 5 is cylindrical, and the tail end is connected with the engine tail nozzle 6; the V tail 4 is fixed above the rear of the fuselage, the included angle θ is 80°~100°, and the cross-sectional shape is trapezoid; The trailing edge and the trailing edge of the V-tail 4 are designed with aerodynamic control surfaces.

The present invention can reduce the aerodynamic resistance of the launching active section, as shown in FIG. 4 , so as to obtain a higher initial velocity.

The content not described in detail in the present invention is known to those skilled in the art.

Claims (10)

1. A rocket engine integrated wave-rider aircraft is characterized in that: the aircraft comprises a wave-rider wing (1), a load cabin (2), an engine cabin (3), a tail cabin (5), a V tail (4) and an engine tail nozzle (6); the load cabin (2), the engine cabin (3) and the tail cabin (5) are in transitional connection in sequence to form a fuselage; the wave-rider wing (1) is positioned below the fuselage, and the V tail (4) is symmetrically arranged at the tail part of the engine cabin (3) and above the tail cabin (5); the engine tail nozzle (6) extends out of the end surface of the rear part of the tail cabin (5).

2. A rocket engine integrated wave-rider aircraft according to claim 1, wherein: the lower surface of the wave-rider wing (1) is obtained by a streamline tracking method based on osculating cone wave-rider configuration, forward streamline tracking is carried out in each osculating plane through a given lower surface outlet molded line, and the lower surface of the wave-rider configuration is generated; the upper surface of the wave-rider configuration is a free flow surface, the shape of the lower surface of the wave-rider configuration is kept unchanged, the upper surface of the wave-rider configuration is subjected to fuselage expansion and is respectively spliced with the load cabin (2), the engine cabin (3) and the tail cabin (5), and no conduction angle transition exists at the splicing position.

3. A rocket-engine integrated wave-rider aircraft according to claim 1 or 2, wherein: the load cabin (2) comprises a front section, a middle section and a tail section; the front section is in a duckbill shape; the middle section is raised upwards, and the cross section is parabolic; the cross section of the tail section is circular and is connected with an engine compartment (3).

4. A rocket engine integrated wave-rider aircraft according to claim 3, wherein: the engine compartment (3) is in a circular truncated cone shape, the front end of the engine compartment is connected with the load compartment (2), and the rear end of the engine compartment is connected with the tail compartment (5).

5. a rocket engine integrated wave-rider aircraft according to claim 4, wherein: a truncated cone-shaped solid engine (8) is selected as a power device of the wave-rider aircraft, and an engine shell is used as a part of an aircraft body.

6. a rocket engine integrated wave-rider aircraft according to claim 4, wherein: the conicity of the truncated cone-shaped solid engine (8) is less than 5 degrees.

7. A rocket-engine integrated wave-rider aircraft according to claim 4 or 5, wherein: the tail cabin (5) is cylindrical, and the tail end of the tail cabin is connected with an engine tail nozzle (6).

8. A rocket engine integrated wave-rider aircraft according to claim 7, wherein: the V-shaped tails (4) are two, and the included angle between the two V-shaped tails (4) is 80-100 degrees.

9. A rocket engine integrated wave-rider aircraft according to claim 1, wherein: the trailing edge of the wave-rider wing (1) is provided with a pneumatic control surface.

10. A rocket engine integrated wave-rider aircraft according to claim 1, wherein: the rear edge of the V tail (4) is provided with a pneumatic control surface.