CN-122016231-A - Complex flow general research model for internal and external flow coupling wide-domain Reynolds number of flying wing layout aircraft

CN122016231ACN 122016231 ACN122016231 ACN 122016231ACN-122016231-A

Abstract

The application belongs to the field of wind tunnel test model design, and discloses an aircraft layout aircraft internal and external flow coupling wide-domain Reynolds number complex flow general research model which comprises a machine head part, an air inlet lip part, a machine body upper cover plate, a machine body lower cover plate, a front edge flap part, a tail nozzle part and a machine body main body, wherein the machine body main body is integrated with a mounting interface of the machine head part, the air inlet lip part, the machine body upper cover plate, the machine body lower cover plate, the front edge flap part and the tail nozzle part, an internal flow channel and a measuring balance mounting interface are designed in the machine body main body, and a sensor mounting position is reserved. The model has the characteristics of modularization, generalization, inclined abdomen support, extreme environment applicability and the like in design.

Inventors

MA SHANG
Yang Lejie
XU YANGFAN
YAN CHUNHUI
LI GUOSHUAI
PENG XIN
XIE CHENYU
QUAN LI

Assignees

中国空气动力研究与发展中心高速空气动力研究所

Dates

Publication Date: 20260512
Application Date: 20260416

Claims (10)

1. The complex flow general research model of the internal and external flow coupling wide-domain Reynolds number of the flying wing layout aircraft is characterized by comprising the following components: A nose part (1), an air inlet lip part (2), a fuselage upper cover plate (3), a fuselage lower cover plate (4), a leading edge flap part (5), a tail nozzle part (6) and a fuselage main body (7), The device is characterized in that the machine body main body (7) is integrated with a mounting interface of the machine head component (1), the air inlet lip component (2), the machine body upper cover plate (3), the machine body lower cover plate (4), the front edge flap component (5) and the tail nozzle component (6), and an inner runner channel and a measuring balance mounting interface are designed in the machine body main body (7), and a sensor mounting position is reserved.
2. The complex flow generic research model of an internal and external flow coupling wide-area reynolds number for an aircraft according to claim 1, further comprising a belly support structure, The inclined abdomen supporting structure comprises a supporting rod (14) and is used for connecting and fixing the research model, the supporting rod (14) is of a V-shaped structure design, and an interface matched with the supporting rod (14) is arranged on the main body (7) of the machine body; one end of the supporting rod (14) is connected with the measuring balance by adopting an inner taper hole, and the other end of the supporting rod is connected with the hole body mechanism by adopting a cylindrical surface and is tensioned by a screw.
3. The complex flow general research model of internal and external flow coupling wide-area Reynolds number of the flying wing layout aircraft according to claim 1, wherein the nose component (1) comprises a head appearance structure of the flying wing layout aircraft, and an acceleration sensor mounting interface is integrated inside the nose component (1); The aircraft nose component (1) is manufactured to obtain an aircraft nose shell by adopting a CNC processing method according to geometric parameters of the flying wing layout, and is provided with an adaptive interface connected with the aircraft body (7).
4. A complex flow general research model of internal and external flow coupling wide-area reynolds number of an aircraft with an all-wing layout according to claim 3, wherein the aircraft nose component (1) and the main body (7) are matched by shaft holes, positioned by pins and tensioned by screws.
5. The aircraft interior and exterior flow coupling wide-area reynolds number complex flow general research model of claim 1, wherein the air inlet lip component (2) is of modular design, supports a plugging configuration or a ventilation configuration, and selects an air inlet lip type according to test requirements; the cone blocking configuration is that a cone blocking part (9) is arranged at an inlet (12) of the air inlet channel to isolate internal flow so as to independently study the characteristics of an external flow field; And the ventilation configuration is that a ventilation lip part (8) is adopted to enable the inner flow field and the outer flow field to interact, so that the coupling effect of a real aircraft is simulated.
6. The complex flow general research model of the internal and external flow coupling wide-area Reynolds number of the flying wing layout aircraft according to claim 1, wherein the upper airframe cover plate (3) and the lower airframe cover plate (4) are detachable modules, and sensor mounting slots are reserved in the upper airframe cover plate (3) and the lower airframe cover plate (4) so as to complete the arrangement and the installation of pressure measuring hoses and pulse pressure sensor equipment in experiments.
7. The complex flow general research model for the internal and external flow coupling wide-area Reynolds number of the aircraft with the flying wing layout according to claim 1 is characterized in that the leading edge flap component (5) supports the configuration of flaps with different deflection angles, and the leading edge flap component (5) is processed according to the leading edge geometric parameters of the flying wing layout and is designed with an adaptive interface to realize the rapid switching of different deflection angles.
8. The aircraft internal and external flow coupling wide-area reynolds number complex flow generic research model of claim 1, wherein the nozzle component (6) supports replacement of nozzle profiles based on different research objectives.
9. The aircraft internal and external flow coupling wide-domain Reynolds number complex flow general research model of claim 1, wherein an ejector (10) is arranged between an inlet channel outlet (11) of the main body (7) of the aircraft body and a jet pipe inlet (13); The ejector (10) is provided with a plurality of adjustable jet orifices, and flow coefficients with different sizes can be simulated by changing the area and the quantity parameters of the jet orifices.
10. The complex flow general research model of the internal and external flow coupling wide-area Reynolds number of the flying wing layout aircraft according to claim 1 is made of 18Ni200D steel.

Description

Complex flow general research model for internal and external flow coupling wide-domain Reynolds number of flying wing layout aircraft Technical Field The application belongs to the field of wind tunnel test model design, and particularly relates to a general research model for complex flow of an internal and external flow coupling wide-domain Reynolds number of an aircraft with an all-wing layout. Background The wind tunnel test universal research model is an important tool for the aerodynamic characteristic research and flow field characteristic analysis of the aircraft, and mainly plays a role in verifying the accuracy of a numerical simulation method, can be used for basic aerodynamic performance research of a typical layout aircraft, lays a foundation for the design optimization of the aircraft, and can be used for the research of a complex flow mechanism and the verification of the quality of a wind tunnel flow field to ensure the authenticity and reliability of an experimental result. Low aspect ratio flying wing aircraft are widely used in the design of many aircraft as a typical aerodynamic layout. Therefore, the basic aerodynamic characteristics of the aircraft with the layout are mastered, and the method is very important for optimizing the aerodynamic layout of the aircraft with the advanced flying wing and improving the performance of the aircraft. However, the current general research model for low aspect ratio flying wing aircraft has obvious limitations. These models tend to be simplistic and are designed based on a simple delta wing version only. Although such a model is capable of modeling the delta wing class aircraft leading edge vortex structure and associated aerodynamic characteristics, it simplifies the study of flow complexity. However, for a real aircraft, not only the thickness of the fuselage is affected, but the appearance characteristics of the external components such as the propulsion system, the air inlet duct, etc. can also have a significant impact on the overall aerodynamic performance. More importantly, in the research of the flying wing type aircraft, the research of the coupling characteristics of the internal flow and the external flow is a key problem. Currently, most research is limited to modeling the fuselage or the air intake duct alone, and lacks a general research model that can take into account both the effects of the internal and external coupling. Therefore, aiming at the low aspect ratio flying wing layout aircraft, the invention provides a general research model which not only comprehensively considers the external characteristics of the thickness of the aircraft body, the appearance of a propulsion system and the like, but also can simulate the coupling effect of internal and external flows simultaneously, and has important theoretical significance and practical application value. Disclosure of Invention The application aims to solve the problems in the prior art and discloses a general research model for complex flow of internal and external flow coupling wide-domain Reynolds numbers of an aircraft with an all-wing layout. The aim of the application is achieved by the following technical scheme: An all-wing aircraft layout aircraft internal and external flow coupling wide-domain reynolds number complex flow general research model, the all-wing aircraft layout aircraft internal and external flow coupling wide-domain reynolds number complex flow general research model comprising: a nose part, an air inlet lip part, a fuselage upper cover plate, a fuselage lower cover plate, a leading edge flap part, a tail nozzle part and a fuselage main body, The main body of the machine body is integrated with a machine head part, an air inlet lip part, an upper cover plate of the machine body, a lower cover plate of the machine body, a front edge flap part and a mounting interface of a tail nozzle part, an inner flow passage and a measuring balance mounting interface are designed in the main body of the machine body, and a sensor mounting position is reserved. According to a preferred embodiment, the aircraft-layout internal and external flow coupling wide-domain Reynolds number complex flow general research model further comprises a belly support structure, The inclined abdomen supporting structure comprises a supporting rod which is used for connecting and fixing the research model, the supporting rod is of a V-shaped structure design, and an interface which is matched with the supporting rod is arranged on the main body of the machine body; one end of the supporting rod is connected with the measuring balance through an inner taper hole, and the other end of the supporting rod is connected with the hole body mechanism through a cylindrical surface and is tensioned through a screw. According to a preferred embodiment, the nose part comprises a nose shape structure of an all-wing aircraft, and the nose part is internally integrated with an acceleration sensor mounting