Separation Mechanism for Hypersonic Inlet Shield

Abstract

The invention provides a separation mechanism applicable to a hypersonic speed air inlet duct protection cover. The separation mechanism comprises an aircraft precursor and the air inlet duct protection cover. On the premise of meeting the requirement for structural strength, the interior of the aircraft precursor is hollowed out to form a cavity, the aircraft precursor is further provided with asquare hole, the air inlet duct protection cover is provided with an unlocking hook which can stretch into the cavity through the square hole, a rotary sliding rod is further arranged in the cavity and used for locking the unlocking hook before unlocking, one end of the sliding rod is a restrained end, the other end is a free end, a tension spring fixed to the wall face of the cavity is connectedto one side of the free end, and the tension spring is in a tensioned state when the sliding rod locks the unlocking hook. The other side of the free end is connected with a fiber fusing device. By means of the separation mechanism, the problem that an explosive bolt separation mechanism way cannot be used for a wind tunnel shrinkage model is solved, and the ability of a hypersonic speed wing tunnel carrying out air inlet duct protection cover dynamic separation testing is improved.

Description

technical field [0001] The invention relates to a separation mechanism suitable for a hypersonic air inlet protective cover, in particular to an actively separated dynamic separation mechanism for a hypersonic air inlet protective cover. Background technique [0002] The hypersonic inlet does not start when the Mach number is low, which not only reduces the performance of the engine, but also seriously deteriorates the aerodynamic performance of the aircraft. In order to avoid the influence of the intake port not starting, usually at low Mach number, a protective cover is used to block the intake port and rectify the incoming flow to improve the aerodynamic performance of the aircraft at low Mach number. When the flight speed reaches the operating point of the intake port, the protective cover will Hood detached. The separation process of the inlet protection cover is short, the attitude changes greatly, and the flow field changes drastically. Whether the separation can be ...

AI Technical Summary

Problems solved by technology

However, one of the key difficulties restricting the dynamic separation test technology is how to realize the dynamic separation of the scale model in the wind tunnel.

The explosive bolt separation mechanism used in the aircraft cannot be scaled. In view of this, it is very necessary to propose a design method for the protective cover separation mechanism suitable for the scale model to realize the dynamic separation test in the wind tunnel.

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