The invention relates to an aircraft propulsion system (100) comprising: a turbojet engine (102) having a fan housing (103) with an aft face portion (103a); a pylon (104) with a front portion (106a) and a lower spar (106b) with a rear fitting (108) secured thereto; a front engine attachment (150) fixed between the upper portion and the front portion (106a) of the fan housing (103); a front arch (152) having two arms (152b-152c), each arm having a first end secured to the lower spar (106b) and a second end hingedly secured to the rear face (103a); and two lateral levers (154), each having a first end hingedly secured to the rear fitting (108) and a second end hingedly secured to the rear face portion (103a). In this arrangement, a force is transmitted to the rear of the pylon.
本发明涉及一种飞行器推进系统(100),其包括:涡轮喷气发动机(102),其具有带后面部(103a)的风扇壳体(103);带前部部分(106a)和下翼梁(106b)的挂架(104),下翼梁(106b)带与其固定的后配件(108);前发动机附接件(150),其固定在风扇壳体(103)的上部部分与前部部分(106a)之间;前拱形件(152),其具有两个臂(152b-152c),每个臂具有固定到下翼梁(106b)的第一端和以铰接方式固定到后面部(103a)的第二端;以及两个侧向杆(154),每个侧向杆具有以铰接方式紧固到后配件(108)的第一端和以铰接方式紧固到后面部(103a)的第二端。以此布置,力被传递到挂架的后部。
Propulsion system for aircraft comprising turbojet engine, pylon and engine attachment
包括涡轮喷气发动机、挂架和发动机附接件的用于飞行器的推进系统
2025-01-07
Patent
Electronic Resource
Chinese
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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