摘要
针对飞翼布局飞机武器舱高强度气动噪声、内埋武器分离安全性和全机开舱附加阻力问题,以高速风洞气动噪声及气动力测量为研究手段,开展了基于前缘扰流片激励的武器舱综合流动控制技术试验研究。试验结果表明:对于飞翼布局飞机,武器舱开启对飞机气动性能有较大影响,巡航状态下,武器舱打开后使全机阻力增加了60%～110%;武器舱气动噪声高达185dB;内埋武器分离过程中存在较大的抬头力矩,不利于武器分离。通过在武器舱前缘布置扰流片对剪切层施加激励,可以有效改善武器舱流动特性。巡航状态下武器舱开舱附加阻力最多降低20%;武器舱噪声降低5～8dB;同时可以有效改善内埋弹分离特性。
An experimental investigation is conducted in a high speed wind tunnel to suppress the acoustic resonance and additional drag of a weapons bay for flying wing configuration aircraft and to improve its store separation characteristics when its doors are opened. Conventional leading edge spoilers are used to disturb the weapons bay free shear layer. Detailed static-pressure and fluctuating-pressure measurements are obtained on the weapons bay walls to determine the effects on weapons bay flow characteristics. Forces and moments on the aircraft and the store model are measured to determine the effects of the flow control method on additional drag and store separation characteristics. The results indicate that for a flying wing con- figuration aircraft, the additional drag of the weapons bay accounts for as much as 60%-110% of the total vehicle drag. The amplitude of resonant tones is measured up to 185 dB. Very large pitching moment renders store release difficult, and it may cause the stores to rise back into the cavity and collide with the aircraft. Using the flow control method can reduce the amplitude of the weapons bay tones by 5-8 dB and can reduce additional drag up to 20%. Meanwhile, spoilers can enhance the characteristics of weapon departure from the weapons bay effectively.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2012年第5期781-787,共7页
Acta Aeronautica et Astronautica Sinica
关键词
飞翼布局
武器舱
气动噪声
流动控制
分离特性
flying wing configuration
weapons bay
acoustic resonance
flow control
separation characteristic
