CN110539898A

CN110539898A - Rocket engine integrated wave-rider aircraft

Info

Publication number: CN110539898A
Application number: CN201910765464.4A
Authority: CN
Inventors: 陈冰雁; 关发明; 徐国武; 艾邦成; 李锋
Original assignee: China Academy of Aerospace Aerodynamics CAAA
Current assignee: China Academy of Aerospace Aerodynamics CAAA
Priority date: 2019-08-19
Filing date: 2019-08-19
Publication date: 2019-12-06

Abstract

A rocket engine integrated wave-rider aircraft comprises wave-rider wings (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). The waverider aircraft can solve and avoid the technical problems of poor appearance stability characteristic, high risk of separation between non-axisymmetric outer high dynamic pressure stages, large pneumatic resistance of an active section and the like of the conventional boosting gliding hypersonic aerocraft and booster combination, and realize overall performance indexes such as higher lift-drag ratio, higher loading volume utilization rate and the like.

Description

Rocket engine integrated wave-rider aircraft

Technical Field

The invention relates to a waverider hypersonic aircraft adopting solid rocket power, which can be suitable for boosting gliding hypersonic flight.

Background

The near space boosting gliding type aircraft generally adopts a solid rocket booster to obtain an initial speed, as shown in figure 1, after the flight of the rocket active section is finished, the aircraft is separated from the booster, and then the aircraft flies in an unpowered gliding mode. In order to realize long-distance long-time gliding flight, a gliding aircraft in the near space needs to adopt a high-lift-ratio plane symmetric pneumatic layout, and is generally in serial combined connection with an axisymmetric booster rocket during launching, so that the technical problems of poor appearance stability characteristic of the aircraft and booster combination, high risk of separation between non-axisymmetric external high-pressure stages, large pneumatic resistance of an active section and the like are brought.

Disclosure of Invention

The technical problem to be solved by the invention is as follows: the invention overcomes the defects of the prior art, provides a rocket engine integrated waverider aircraft, integrates a boosting rocket and a high lift-drag ratio gliding aircraft, and integrally designs a solid rocket engine and a waverider aircraft to realize overall performance indexes such as high lift-drag ratio, high filling volume utilization rate, low structural mass coefficient and the like.

The technical scheme adopted by the invention is as follows: a rocket engine integrated wave-rider aircraft comprises wave-rider wings, a load cabin, an engine cabin, a tail cabin, a V tail and an engine tail nozzle; the load cabin, the engine cabin and the tail cabin are in transitional connection in sequence to form a fuselage; the wave-rider wings are positioned below the fuselage, and the V tails are symmetrically arranged at the tail part of the engine cabin and above the tail cabin; the engine tail nozzle extends out of the end face of the rear part of the tail cabin.

The method comprises the following steps that (1) a waverider wing is obtained by a streamline tracking method based on osculating cone waverider configuration, forward streamline tracking is carried out in each osculating plane through a given lower surface outlet molded line, and a lower surface of the waverider 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, the engine cabin and the tail cabin, and no conduction angle transition exists at the splicing position.

The load cabin 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 tail section is circular in cross section and is connected with an engine compartment.

The engine compartment is in a circular truncated cone shape, the front end of the engine compartment is connected with the load compartment, and the rear end of the engine compartment is connected with the tail compartment.

A truncated cone-shaped solid engine is selected as a power device of the wave-rider aircraft, and an engine shell is used as a part of an aircraft fuselage.

The taper of the truncated cone shaped solid engine is less than 5 degrees.

The tail cabin is cylindrical, and the tail end of the tail cabin is connected with an engine tail nozzle.

The V tail has two pieces, and the included angle between the two V tails is 80-100 degrees.

The trailing edge of the wave-rider wing is provided with a pneumatic control surface.

And the rear edge of the V tail is provided with an air-operated control surface.

compared with the prior art, the invention has the following advantages:

The invention integrally designs the boosting rocket and the wave-carrier aircraft, does not need to carry out high dynamic pressure separation in the atmosphere between the booster and the gliding aircraft, and reduces technical risk. The aircraft of the invention adopts a wave-rider design method to design the wings, and can obtain higher lift-drag ratio. The aircraft of the invention takes the solid rocket engine structure as one part of the whole aircraft structure, and can reduce the mass coefficient of the overall structure. The aircraft can reduce the aerodynamic resistance of the launching active section, thereby obtaining higher initial speed. The aircraft of the invention has larger load loading space.

Drawings

Fig. 1 is a three-dimensional schematic view of a conventional hypersonic flight vehicle and booster combination.

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

Fig. 3 is a schematic longitudinal cross-section of the fuselage.

Fig. 4 is a comparison of aerodynamic drag of the integrated wave-rider aircraft of the present invention and a conventional warhead/booster combination.

Detailed Description

The following describes embodiments of the present invention with reference to examples.

As shown in fig. 2, a rocket engine integrated wave-rider 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 form a fuselage, and the fuselage is positioned on the wing 1; the V-tail 4 is positioned above the machine body.

As shown in FIG. 3, the present invention provides a waverider aircraft integrated with a solid rocket engine. The design principle of the waverider wing 1 is based on a streamline tracking method of an osculating cone waverider configuration, forward streamline tracking is carried out in each osculating plane by giving outlet molded lines (middle arcs and oblique lines on two sides) of a lower surface to generate a lower surface of the waverider configuration, the upper surface of the waverider configuration is a free stream surface, the shape of the lower surface of the waverider configuration is kept unchanged, the upper surface of the waverider wing is subjected to fuselage expansion design and is respectively spliced with a load cabin 2, an engine cabin 3 and a tail cabin 5, and the spliced part has no guide angle transition and has obvious characteristic lines;

the front section of the load cabin 2 is in a duckbill shape, the middle section of the load cabin is upwards raised, the section of the load cabin in the direction vertical to the body is in a parabola shape, and the cross section of the tail section of the load cabin is in a circle shape and is connected with the engine cabin 3;

The engine cabin 3 is in a cone shape, the front end and the rear end are in circles with different radiuses, the front end is connected with the load cabin 2, the rear end is connected with the tail cabin 5, a cone-shaped solid engine 8 with small taper (less than 5 degrees) is selected as a power device of the wave-rider aircraft, the engine shell is used as a part of the aircraft fuselage, and the engine shell, the load cabin 7 positioned at the head part and the tail cabin 9 positioned at the tail part jointly form the aircraft fuselage, as shown in fig. 3;

The tail cabin 5 is cylindrical, and the tail end of the tail cabin is connected with an engine tail nozzle 6; the V tail 4 is fixed above the rear part of the machine body, the included angle theta is 80-100 degrees, and the section shape is trapezoidal; aerodynamic control surfaces can be designed at the trailing edge of the wave-rider wing 1 and the trailing edge of the V-tail 4.

The present invention can reduce the aerodynamic drag of the active section of the launch, as shown in figure 4, to achieve a higher initial velocity.

The present invention has not been described in detail as is known to those skilled in the art.

Claims

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.