| 摘要 |
An automatic tow release system for model aircraft launched with the help of a tow line (12) which has novel means for continuously and automatically adjusting the climb angle of the fuselage and automatically releasing the tow line (12) when the aircraft reaches a predetermined climbing position. The tow release system comprises a primary (16) and a secondary (18) control string, a connecting body (20), a primary (42) and a secondary (44) connecting means between the connecting body (20) and the aircraft, and a release promoting means. The release promoting means is a feature of the particular design of the tow release system. The control strings (16, 18) are attached to the tow line (12) at one end and to the connecting body (20) at the other end. The connecting body (20) is demountably connected to the aircraft during the tow through the primary (42) and secondary (44) connecting means, respectively. At the beginning of the take-off, the pulling force of the tow line (12) is conveyed to the aircraft mostly through the primary control string (16). During the climb, the tension is gradually transferred to the secondary control string (18). The release promoting means is activated and the primary (42) and secondary (44) connecting means are disengaged upon the complete transfer of the pulling force from the primary (16) to the secondary control string (18), whereby the tow line is released. The timing of the release depends on some user-adjustable geometric parameters of the tow release system. The user can set the system to release the tow line when the aircraft is in position for a slow gliding flight or for a fast looping flight.
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