CN-224225302-U - Low negative pressure flank guide wall for aircraft test

CN224225302UCN 224225302 UCN224225302 UCN 224225302UCN-224225302-U

Abstract

The utility model provides a low negative pressure flank guide wall for an aircraft test, which comprises a guide structure surrounding an aircraft, wherein the guide structure comprises a tail guide wall corresponding to the tail of the aircraft and a flank guide wall corresponding to a flank of the aircraft, the whole flank guide wall is parallel or slightly inclined to the axial direction of an aircraft body and is connected with the ground, the flank guide wall comprises a windward side and a leeward side, the windward side is formed by continuously splicing a plurality of metal plates, the leeward side is connected with a support frame, the bottom of the support frame is connected with a concrete ground anchor bolt, a plurality of silencing ducts are arranged in the flank guide wall, the opening ends of the silencing ducts penetrate through the windward side and face the aircraft, and through arranging the silencing ducts on the flank guide wall, air flow can be introduced, so that the internal and external pressure difference of the guide wall is reduced, the test environment of the aircraft is facilitated, and meanwhile, the influence of noise is greatly reduced through matching of perforated metal plates and resistive sound absorbing materials in the silencing ducts.

Inventors

JIANG BO
SHU YANG
AN DI
LIU YANG

Assignees

东莞英达士声学设备有限公司

Dates

Publication Date: 20260512
Application Date: 20250530

Claims (10)

1. The low negative pressure flank guide wall for the aircraft test is characterized by comprising a guide structure (9) surrounding an aircraft, wherein the guide structure (9) comprises a tail guide wall (7) corresponding to the tail of the aircraft and flank guide walls (1) corresponding to flanks of the aircraft, the flank guide walls (1) are wholly parallel or slightly inclined to the axial direction of the aircraft body and are connected with the ground, the flank guide walls (1) comprise a windward side (11) and a leeward side (12), the windward side (11) is formed by continuously splicing a plurality of metal plates (13), the leeward side (12) is connected with a support frame (2), the bottom of the support frame (2) is connected with a concrete ground anchor bolt, a plurality of silencing ducts (3) are further arranged in the flank guide walls (1), and the opening ends of the silencing ducts (3) penetrate through the windward side (11) and face towards the aircraft.
2. The low negative pressure side wing guide wall for airplane test run according to claim 1, wherein the silencing duct (3) comprises an air vent (31) and an air passage (34) communicated with the air vent (31), the air vent (31) is opposite to the direction of an airplane engine, and the air passage (34) is inclined to the obliquely rear direction of an airplane body.
3. The low negative pressure side wing guide wall for airplane test run according to claim 2, wherein the inner wall surface of the air passage (34) is a silencing plate (32), and the silencing plate (32) is a resistive silencing material.
4. The low negative pressure side wing guide wall for aircraft test run according to claim 3, wherein the resistive muffling material is centrifugal fiber glass.
5. A low negative pressure side wing guide wall for aircraft test according to claim 3, wherein the silencer plate (32) is provided with a plurality of silencing holes (321).
6. The low negative pressure side wing guide wall for aircraft test run according to claim 2, wherein the sound attenuation duct (3) further comprises a duct support member (33) for fixing the sound attenuation duct (3) on the support frame (2).
7. The low negative pressure side wing guide wall for airplane test run according to claim 1, wherein the side wing guide wall (1) forms a silencing duct group (8) at a plurality of silencing ducts (3) along the vertical direction, and a plurality of silencing duct groups (8) are arranged at intervals along the horizontal direction.
8. The low negative pressure side wing guide wall for aircraft test according to claim 7, wherein one end of the side wing guide wall (1) close to the aircraft nose direction is a curved surface outer contour (14), the end face of the curved surface outer contour (14) is inclined upwards towards the aircraft tail direction, and a guide angle line (131) is arranged at the top of the end face.
9. The low negative pressure side wing guide wall for aircraft test run according to claim 8, wherein the radius R1 of the guide angle arc of the guide angle line (131) is 1200mm.
10. The low negative pressure side wing guide wall for airplane test according to claim 1, wherein the upper and lower adjacent metal plates (13) are connected through pressing plates (4), the metal plates (13) in the vertical direction are connected to form a module (5), and the adjacent modules (5) are fixedly connected through connecting frames (6).

Description

Low negative pressure flank guide wall for aircraft test Technical Field The utility model belongs to the field of aviation equipment, and particularly relates to a low negative pressure side wing guide wall for airplane test. Background When the aircraft performs ground test, high-temperature and high-speed wake flow at the rear of the engine, negative pressure environments at the front of the engine can cause harm to personnel and facilities on the ground, engine noise with a sound power level of up to 140 db can cause serious auditory interference and even harm to hearing of surrounding residents; the construction of the ground noise reduction facilities for the airplane at present mainly concentrates on a wake flow guide wall at the rear of the airplane, and the structure has a certain protection effect on the rear area of the airplane, but the lateral air flow is still greatly influenced when the side surface of the airplane is exposed, the noise protection area is a space closely attached to the guide wall, and the noise protection area is an airport boundary area which is more required to be protected outside hundreds of meters, and is greatly weakened because of the sound diffraction at the two ends of the wall; Meanwhile, domestic attempts are made to construct a side wing guide wall, however, the negative pressure problem of air suction of an aircraft engine is not well overcome in the prior art, so that pneumatic pressure loss introduced by the guide wall is overlarge, turbulence occurs at the edge of the guide wall during aircraft test, and further the problems of vibration of the guide wall structure, poor pneumatic environment of aircraft test and the like are caused. Disclosure of utility model (1) Technical problem to be solved The utility model provides a low negative pressure flank guide wall for an airplane test, and aims to provide a guide wall which is capable of achieving both guide and sound insulation protection and effectively controlling pneumatic negative pressure. (2) Technical proposal The utility model provides a low negative pressure flank guide wall for an airplane test, which comprises a guide structure surrounding an airplane, wherein the guide structure comprises a tail guide wall corresponding to the tail of the airplane and a flank guide wall corresponding to a flank of the airplane, the whole flank guide wall is parallel or slightly inclined to the axial direction of the airplane body and is connected with the ground, the flank guide wall comprises a windward side and a leeward side, the windward side is formed by continuously splicing a plurality of metal plates, the leeward side is connected with a support frame, the bottom of the support frame is connected with a concrete ground anchor bolt, a plurality of silencing ducts are arranged in the flank guide wall, and the opening ends of the silencing ducts penetrate through the windward side and face the airplane. Further, the silencing duct comprises an air vent and an air passage communicated with the air vent, the air vent is opposite to the direction of the aircraft engine, and the air passage is inclined to the inclined rear of the aircraft body. Further, the inner wall surface of the air passage is a silencing plate, and the silencing plate is made of a resistive silencing material. Further, the resistive muffler material is centrifugal fiber glass. Further, the silencing plate is provided with a plurality of silencing holes. Further, the sound-damping duct further comprises a duct support member for securing the sound-damping duct to the support frame. Further, the side wing guide wall forms a silencing duct group at a plurality of silencing ducts along the vertical direction, and a plurality of silencing duct groups are arranged at intervals along the horizontal direction. Further, one end of the side wing guide wall, which is close to the aircraft nose direction, is a curved outer contour, the end face of the curved outer contour is inclined upwards in the aircraft tail direction, and a guide angle line is arranged at the top of the end face. Further, the radius R1 of the lead angle arc of the lead angle line is 1200mm. Further, the upper and lower adjacent metal plates are connected through a pressing plate, the metal plates in the vertical direction are connected to form a module, and the adjacent modules are fixedly connected through a connecting frame. Compared with the prior art, the utility model has the beneficial effects that: 1. By arranging the silencing duct on the side wing guide wall, air flow can be introduced, and the pressure difference between the inside and the outside of the guide wall is reduced, so that the test run environment of the aircraft is facilitated. 2. By perforating the metal plate in the sound attenuating duct and mating with the resistive sound absorbing material, the effects of noise are greatly reduced. Drawings Fig. 1 is a schematic diagram of the overall structure of the pre