The environmental factors in survivable civil aircraft crash accidents have a significant impact on passenger evacuation. Based on the characteristics of typical survivable civil aircraft crash accident scenarios, this paper proposes an experimental method for passenger emergency evacuation that can simulate typical crash accident environments, and introduces simulation methods for aircraft body attitudes, environmental sound/light, cabin obstacles, visual environment of portholes, and high-precision measurement methods for the personnel evacuation trajectory. The impact of crash environment factors such as aircraft body tilt attitudes, accident sound/light environments, and aisle obstacles on the emergency evacuation of civil aircraft passengers is studied through volunteer experiments. The results indicate that the proposed experimental method for emergency evacuation considering the impact of crash environment and the simulation scheme for crash environment are feasible, and obtain effective experimental data; the aircraft body attitude change within a pitch angle of ± 5° has no significant impact on the total evacuation time and evacuation efficiency of multi-passenger evacuation, and the difference in the speed of passengers moving uphill and downhill in the aisle area increases with the increase of pitch angle; the sound and lighting environment of the crash accident have a certain impact on the emergency evacuation of passengers, and the accident background sound can reduce the total evacuation time, while emergency lighting increases the total evacuation time; obstacles in the cabin aisle overall increase the total evacuation time, with a shorter distance between the obstacles and the exit resulting in lower evacuation efficiency; compared to movable obstacles, fixed obstacles can lead to lower evacuation efficiency.

The crash test of civil aircraft is a worldwide technical problem, and it is the most direct means to evaluate the crashworthiness of civil aircraft. In this paper, the high precision lifting height control and high reliability delivery method of the full-scale aircraft crash test are proposed, and the testing methods of the key physical parameters such as structural response and dummy response are given. A dynamic response test system for the whole aircraft crash test was constructed, and using a unified time reference trigger method, the ground impact load, structural acceleration response, dummy response, and aircraft failure and deformation were analyzed. The response distribution rules of different parts of the aircraft were obtained. The revised comprehensive evaluation index ICI of the adaptability was put forward. The results show that the test data are complete and reliable. After the vertical crash at 5.71 m/s, the lower structure of the cabin floor is seriously deformed, and the upper structure of the fuselage in the central wing area is obviously deformed due to the inertia effect of the wing. The stiffness difference of the different fuselage segments results in significant differences in crash load and dynamic response. The higher the stiffness is, the smaller the deformation and the greater the acceleration response will be. After the crash, the load on the passengers was within safe range, the cabin seats are intact, the cabin doors can be opened normally., the living space of the passengers is sufficient, and the evacuation channel of the passengers is unblocked. Compared with the original ICI index, the revised evaluation result has better engineering applicability.