JPH0840397A - High-speed flight vehicle - Google Patents

Abstract

PURPOSE:To change the shape of a shock wave generated from the tip of a fuselage and moved outward so at to avoid incidence of the shock wave by installing a jet nozzle for spouting a jet in the direction opposite to an air current of an airframe in a high-speed flight vehicle such as a space shuttle or the like. CONSTITUTION:In a space shuttle having main wings 3 fitted to the right and left of a fuselage 2, jet nozzles 5 for spouting jets 6 bilateral-symmetrically obliquely forward in the direction opposite to an air current 1 are fitted to the root parts of the respective main wings 3. When the space shuttle receives an air current 1 in the condition of making a flight at the hypersonic speed at the time of re-entry to the atmosphere, a shock wave 4 is generated from the vicinity of the tip of the fuselage 2. When the shock wave enters the main wing 3, high aerodynamic heating is caused at the front edge thereof. In order to avoid the above, the shape of the shock wave is changed outward by spouting a jet 6 in the direction opposite to an air current from the nozzle 5 so that the shock wave is forced to bypass the wing tip 8 of the main wing 3.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a high-speed flight vehicle such as a space shuttle, which can reduce aerodynamic heating during high-speed flight.

[0002]

2. Description of the Related Art In a conventional winged space shuttle, as shown in FIG. 3, a shock wave 4 generated from the tip of the body 2 is incident on the main wing 3 during re-entry, so that large aerodynamic heating occurs at the incident part. 9 is generated. In order to mitigate this, conventionally, a passive method of dealing by increasing the radius of curvature of the leading edge of the main wing 3 and an active method of cooling the leading edge of the main wing from the inside have been used.

[0003]

In the above-mentioned conventional technique, if the leading edge radius of the main wing is increased, aerodynamic characteristics are deteriorated in a velocity range other than the hypersonic range where aerodynamic heating is a problem. Further, when cooling from the inside, since the weight of the space vehicle is increased by mounting the mechanism of the cooling system, the payload is reduced due to the limitation of the launch weight.

The present invention solves the above problems in the prior art and reduces aerodynamic heating without affecting the aerodynamic shape and without requiring a complicated mechanism. The aim is to provide a high-speed flying vehicle that can.

[0005]

The high speed aircraft of the present invention comprises:
It is characterized in that a jet nozzle that blows out a jet in a direction against the air flow of the airframe is attached to control the shape of the shock wave.

[0006]

In the present invention, the shape of the shock wave generated from the tip of the fuselage changes and moves outward by ejecting a jet from the jet nozzle attached to the machine body in a direction against the air flow. As a result, it is possible to avoid the incidence of shock waves, which has been the cause of increased aerodynamic heating at the leading edge of the main wing, and reduce aerodynamic heating.

[0007]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A first embodiment of the present invention will be described with reference to FIG. Reference numeral 2 is a fuselage of the space vehicle, and reference numeral 3 is two main wings attached to the left and right of the fuselage 2. At the root of each main wing 3, a jet nozzle 5 is attached that blows out a jet 6 symmetrically in a direction diagonally forward and against the air flow 1.

When the space vehicle receives the air flow 1 while flying at hypersonic speed during re-entry, the tip of the body 2 of the space vehicle is flying because it is flying in the hypersonic flow. Shock wave 4 is generated from the vicinity. When this shock wave enters the main wing 3, high aerodynamic heating occurs at its leading edge. In the present embodiment, in order to avoid this, the nozzle 5 attached to the blade root portion of the main wing 3
By ejecting the jet 6 in a direction counter to the air flow, the shape of the shock wave bends outward, and the tip end 8 of the main wing 3 is circumvented as indicated by reference numeral 7. This prevents the shock wave 4 from entering the main wing 8 and reduces aerodynamic heating.

Further, in this embodiment, since the jets 6 are blown out symmetrically from the blade roots of the two left and right main wings 3, it is possible to avoid affecting the lateral characteristics of the space shuttle. .

A second embodiment of the present invention will be described with reference to FIG. In the second embodiment, the jet nozzle 5 is attached to the stagnation point position near the tip of the body 2 of the space shuttle having two main wings 3 on the left and right, and the jet 6 is blown out in the forward direction against the air flow 1. I have to.

As described above, by ejecting the jet 6 from the jet nozzle 5 at the stagnation point near the tip of the body 2 toward the front against the air flow, the position where the shock wave 4 is generated becomes farther from the body 2, and as a whole. The shape of the shock wave 4 spreads to the outside and bypasses the wing tip 8 of the main wing 3. As a result, it is possible to avoid the shock wave from entering the main wing and reduce aerodynamic heating.

Further, in this embodiment, since the jet nozzle 5 is attached to the stagnation point position near the tip of the body 2 so as to blow the jet 6 forward, generally, the aerodynamic heating of the space shuttle is the most important. It is possible to reduce the aerodynamic heating of the stagnation point near the tip of the fuselage, which is high, and to avoid affecting the lateral characteristics of the space shuttle.

Although the first and second embodiments are related to the space shuttle, the present invention can be widely applied to high-speed flying vehicles such as winged space planes and flying vehicles.

[0014]

As described above, according to the present invention, aerodynamic heating of a high-speed flight vehicle such as a space shuttle can be reduced without changing the internal cooling system or the aerodynamic shape of the airframe.
Therefore, aerodynamic heating of the high-speed flying object can be reduced and safe operation can be realized without a large penalty in weight and aerodynamic characteristics.

[Brief description of drawings]

FIG. 1 is a conceptual diagram of a first embodiment of the present invention.

FIG. 2 is a conceptual diagram of a second embodiment of the present invention.

FIG. 3 is a conceptual diagram of a conventional space shuttle.

[Explanation of symbols]

 1 Airflow 2 Body 3 Main Wing 4 Shock Wave 5 Jet Nozzle 6 Jet 7 Bent Shock Wave 8 Wing Tip of Main Wing 9 Aerodynamic Heating by Injecting Shock Wave

Claims (1)

[Claims] 1. A high-speed flying object, characterized in that a jet nozzle that blows out a jet in a direction against the air flow of the airframe is attached to control the shape of a shock wave.