CN211996174U - Integrated configuration of circumferential four-inlet-channel layout of conical aircraft forebody - Google Patents
Integrated configuration of circumferential four-inlet-channel layout of conical aircraft forebody Download PDFInfo
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- CN211996174U CN211996174U CN202020661305.8U CN202020661305U CN211996174U CN 211996174 U CN211996174 U CN 211996174U CN 202020661305 U CN202020661305 U CN 202020661305U CN 211996174 U CN211996174 U CN 211996174U
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Abstract
The utility model relates to a four intake duct overall arrangement integration configurations of toper aircraft forebody circumference, this configuration are equipped with the toper aircraft forebody, and four three-dimensional adversion intake ducts and the outside radome fairing of intake duct that circumference was arranged. The utility model discloses when keeping the forebody advantage of toper aircraft, arrange three-dimensional internal contraction intake duct in four positions of circumference to introduce new thinking for the forebody of aircraft and the design of three-dimensional internal rotation intake duct.
Description
Technical Field
The utility model relates to a forebody and intake duct integrated configuration technical field, concretely relates to four intake duct overall arrangement integrated configurations of toper aircraft forebody circumference.
Background
Air-breathing propulsion can provide high specific impulse for hypersonic flight, and is considered as a preferred propulsion system for designing and developing hypersonic aircrafts for a long time. A great deal of research has proved that the key to achieving near-space flight lies in the integrated design of the aircraft fuselage and the propulsion system, the most critical and difficult problem being the integrated design of the aircraft forebody and the air intake. Internationally, Frederick Ferguson and the like complete the integrated design of an aircraft body and a two-dimensional air inlet channel based on a wedge-guided wave theory, and the method is developed by analyzing the problem of coupling between a wedge-guided wave body and the air inlet channel under a planar flow condition. In addition, based on osculating conic guided waverider theory, Naruhisa Takashima et al propose an integrated design for realizing good coupling of an external flow osculating waverider and an internal flow two-dimensional air inlet channel. In China, the wave multiplication theory is deeply researched and applied to the internal contraction flow by the Eultan Cheng and the like, a double wave multiplication theory method simultaneously applicable to an aircraft body and a three-dimensional internal contraction air inlet channel is provided, and the problem of integration of hypersonic speed outflow and inflow is solved. It can be seen that most of the current hypersonic aircraft integration schemes focus on the matching problem of the wave-rider forebody and the air inlet channel. However, although the waverider aircraft has better design point performance, the defects of the waverider aircraft are obvious, and the waverider aircraft mainly shows the aspects of volume ratio, attack angle characteristics, non-design point working performance and the like.
The conical aircraft is particularly emphasized in the pneumatic design of the aircraft and the missile due to the advantages of simple structure, large volume ratio, good attack angle characteristic and the like. Many scholars have studied curved cone configuration aircraft. Frank in 1979 proposed a submandibular inlet duct layout form adopting air inlet below the head of a curved cone projectile body, and named as ASLAM, and the inlet duct in the scheme is essentially a part of an axisymmetric inlet duct, so that the phenomenon of compression efficiency compared with three-dimensional inner contraction inlet duct intersection exists. In recent years, the three-dimensional inner contraction inlet channel has attracted much attention in the design of an air intake system because of its advantages such as high compression efficiency and good flow capture characteristics, and the american hypersonic percussion weapon (HSSW) issued by rockschid martin will also adopt an aerodynamic layout of a cone outer compression precursor plus abdominal three-dimensional inner rotation air in consideration of the advantages of a cone aircraft and the three-dimensional inner contraction inlet channel. Therefore, it is a critical problem to be solved to develop a precursor/inlet integrated design method capable of simultaneously exerting excellent performance of a conical aircraft and a three-dimensional internal contraction inlet. The conical aircraft is in a conical or curved cone configuration, so that the aircraft has axial symmetry, and the patent adopts a circumferential four-inlet-channel layout form and provides an integrated circumferential four-inlet-channel layout configuration of a conical aircraft forebody.
SUMMERY OF THE UTILITY MODEL
The utility model discloses the problem that will solve is: the integrated configuration of the circumferential four-inlet-channel layout of the conical aircraft forebody is provided, and the three-dimensional inner contraction inlet channels are arranged at four circumferential positions while the advantages of the conical aircraft forebody are kept, so that a new thought is introduced for the design of the aircraft forebody and the three-dimensional inner rotation inlet channels.
The utility model discloses a solve the technical scheme that above-mentioned problem provided and do: a conical aircraft forebody integrated configuration with a circumferential four-inlet duct layout is provided with a conical aircraft forebody, four three-dimensional inward turning inlet ducts arranged circumferentially and an inlet duct outer fairing. The conical aircraft forebody is in a conical configuration, a conical generatrix is a cubic curve, and the coefficients are determined to be the coordinates and the slopes of a starting point and an end point respectively according to 4 parameters; the four three-dimensional inward turning air inlet channels which are circumferentially arranged are respectively arranged on four circumferential cross sections of the conical aircraft precursor, the cross section angles are respectively 0 degree, 90 degrees, 180 degrees and 270 degrees, the three-dimensional inward turning air inlet channel is provided with a three-dimensional inward turning air inlet channel compression profile, a three-dimensional inward turning air inlet channel inlet, a three-dimensional inward turning air inlet channel shoulder molded line, a three-dimensional inward turning air inlet channel isolation section and a three-dimensional inward turning air inlet channel isolation section outlet, wherein three-dimensional internal rotation intake duct import is the three-dimensional curve that the plane shape is waist shape, and three-dimensional internal rotation intake duct compression profile adopts the streamline tracing method to generate in appointed internal contraction basic flow field, has the internal contraction configuration that the area reduces in succession, and three-dimensional internal rotation intake duct shoulder molded lines are the ending curve of three-dimensional internal rotation intake duct compression profile, and three-dimensional internal rotation intake duct isolation section is obtained according to the straight backward stretching of three-dimensional internal rotation intake duct shoulder molded lines equidirectional, and three-dimensional internal rotation intake duct isolation section export is the ending curve of three-dimensional internal rotation intake duct isolation section. The outer fairing of the air inlet channel is obtained by stretching the inlet of the three-dimensional inward-turning air inlet channel in the equal direction backwards.
Compared with the prior art, the utility model has the advantages that: the utility model provides a four intake duct overall arrangement integrated configuration of toper aircraft forebody circumference has introduced new thinking for toper aircraft and propulsion system's integrated design. According to the configuration, the integrated design of the aircraft and a plurality of sets of propulsion systems can be realized, so that the flight capability of the hypersonic conical aircraft is obviously improved.
Drawings
The accompanying drawings, which are described herein, serve to provide a further understanding of the invention and constitute a part of this specification, and the exemplary embodiments and descriptions thereof are provided for explaining the invention without unduly limiting it.
FIG. 1 is a three-dimensional schematic diagram of a circumferential four-inlet integrated configuration of a conical aircraft forebody.
FIG. 2 is a three-dimensional schematic representation of a circumferential four-inlet integrated configuration of a conical aircraft nose body with an inlet outer cowl.
FIG. 3 is an elevation view of a circumferential four-inlet integrated configuration of a conical aircraft forebody.
The labels in the figure are: 1 denotes a conical aircraft forebody, 2 denotes a three-dimensional inward turning inlet, 3 denotes a three-dimensional inward turning inlet compression profile, 4 denotes a three-dimensional inward turning inlet shoulder profile, 5 denotes a three-dimensional inward turning inlet isolation section, 6 denotes a three-dimensional inward turning inlet isolation section outlet, and 7 denotes an inlet outer fairing.
Detailed Description
The following detailed description will be made with reference to the accompanying drawings and examples, so that how to implement the technical means of the present invention to solve the technical problems and achieve the technical effects can be fully understood and implemented.
The embodiment of the utility model provides a four intake duct overall arrangement integration configurations of toper aircraft forebody circumference, including toper aircraft forebody 1, and four three-dimensional adversion intake ducts and the outside radome fairing 7 of intake duct that circumference was arranged. The conical aircraft precursor 1 is in a conical configuration, a conical generatrix is a cubic curve, and the coefficients are determined to be the coordinates and the slopes of a starting point and an end point respectively according to 4 parameters; the four three-dimensional inward turning air inlet channels which are circumferentially arranged are respectively arranged on four circumferential cross sections of a conical aircraft precursor 1, the cross section angles are respectively 0 degrees, 90 degrees, 180 degrees and 270 degrees, the three-dimensional inward turning air inlet channels are provided with three-dimensional inward turning air inlet channel compression profiles 3, three-dimensional inward turning air inlet channel inlets 2, three-dimensional inward turning air inlet channel shoulder profiles 4, three-dimensional inward turning air inlet channel isolation sections 5 and three-dimensional inward turning air inlet channel isolation section outlets 6, the three-dimensional inward turning air inlet channel inlets 2 are three-dimensional curves with waist-shaped planar shapes, the three-dimensional inward turning air inlet channel compression profiles 3 are generated in a specified inward shrinkage basic flow field by adopting a streamline tracing method, and the three-dimensional inward turning air inlet channel shoulder profiles 4 are of the three-dimensional inward turning air inlet channel compression profiles 3 and obtained by equal-directional backward stretching of the three-dimensional inward turning air inlet, the three-dimensional inward-turning inlet duct isolating section outlet 6 is a cut-off curve of the three-dimensional inward-turning inlet duct isolating section 5. The air inlet channel outer fairing 7 is obtained by stretching the air inlet channel inlet 2 in an equal direction backwards according to three-dimensional inward rotation.
The conical aircraft forebody circumferential four-inlet-channel layout integrated device keeps the advantages of the conical aircraft forebody and the three-dimensional inner contraction inlet channel, arranges the three-dimensional inner contraction inlet channel at four circumferential positions of the conical aircraft forebody, and introduces a new idea for the design of the aircraft forebody and the three-dimensional inner rotation inlet channel.
The utility model has the advantages that: the integrated configuration of the circumferential four-inlet-channel layout of the conical aircraft forebody can introduce a new design idea for the integrated design of the conical aircraft and a propulsion system. The integrated design of the aircraft and a plurality of sets of propulsion systems can be realized, so that the flight capability of the hypersonic conical aircraft is obviously improved.
The above description is only an example of the preferred embodiment of the present invention, and not intended to limit the scope of the present invention, and those skilled in the art should be able to realize the equivalent alternatives and obvious variations of the present invention.
Claims (1)
1. A conical aircraft forebody four-inlet-channel circumferential layout integrated configuration is characterized in that the configuration is provided with a conical aircraft forebody, four three-dimensional inward turning inlet channels which are circumferentially arranged and an inlet channel outer fairing; the conical aircraft forebody is in a conical configuration, a conical generatrix is a cubic curve, and the coefficients are determined to be the coordinates and the slopes of a starting point and an end point respectively according to 4 parameters; the four three-dimensional inward turning air inlet channels which are circumferentially arranged are respectively arranged on four circumferential cross sections of the conical aircraft precursor, the cross section angles are respectively 0 degree, 90 degrees, 180 degrees and 270 degrees, the three-dimensional inward turning air inlet channel is provided with a three-dimensional inward turning air inlet channel compression profile, a three-dimensional inward turning air inlet channel inlet, a three-dimensional inward turning air inlet channel shoulder molded line, a three-dimensional inward turning air inlet channel isolation section and a three-dimensional inward turning air inlet channel isolation section outlet, the three-dimensional inward turning inlet is a three-dimensional curve with a waist-shaped plane shape, a three-dimensional inward turning inlet compression profile is generated in a specified inward-shrinkage basic flow field by adopting a streamline tracing method and has an inward shrinkage configuration with a continuously reduced area, a shoulder profile of the three-dimensional inward turning inlet is a cut-off curve of the three-dimensional inward turning inlet compression profile, a three-dimensional inward turning inlet isolation section is obtained by stretching the three-dimensional inward turning inlet shoulder profile in an equal direction, and an outlet of the three-dimensional inward turning inlet isolation section is the cut-off curve of the three-dimensional inward turning inlet isolation section; the outer fairing of the air inlet channel is obtained by stretching the inlet of the three-dimensional inward-turning air inlet channel in the equal direction backwards.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020661305.8U CN211996174U (en) | 2020-04-27 | 2020-04-27 | Integrated configuration of circumferential four-inlet-channel layout of conical aircraft forebody |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020661305.8U CN211996174U (en) | 2020-04-27 | 2020-04-27 | Integrated configuration of circumferential four-inlet-channel layout of conical aircraft forebody |
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| Publication Number | Publication Date |
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| CN211996174U true CN211996174U (en) | 2020-11-24 |
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|---|---|---|---|
| CN202020661305.8U Expired - Fee Related CN211996174U (en) | 2020-04-27 | 2020-04-27 | Integrated configuration of circumferential four-inlet-channel layout of conical aircraft forebody |
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| CN (1) | CN211996174U (en) |
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2020
- 2020-04-27 CN CN202020661305.8U patent/CN211996174U/en not_active Expired - Fee Related
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| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20201124 |