小升阻比载人飞船返回舱的配平气动特性

本文主要介绍小升阻比载人飞船返回舱的配平气动特性。研究表明，采用返回舱重心横编的方法，在保持对静稳定性的要求下，可以获得飞行轨迹机动控制所需的配平升阻比。返回舱飞行试验的配平气动特性可从舱内惯性平台的加速度和姿态记录数据以及轨道数据求出。风洞试验的配平气动特性数据与飞行试验结果比较之后发现，以往风洞试验得出的马赫数大于６后，返回舱的配平气动特性基本不变的结果未被飞行试验所证实。在高超声速下，随着马赫数的增大，飞行试验得出的配平攻角和配平升阻比基本上呈线性减小。返回舱的静稳定性数据表明，有时会出现不希望的第二配平点。消除该第二配平点的主要方法是进行外形修改设计和在返回舱小头上加装调整翼片。

THE TRIM AERODYNAMIC CHARACTERISTICS OF CAPSULE TYPE RE-ENTRY VEHICLE

This paper introduces the trim aerodynamic characteristics of re-entry modules.It was shown that design placement of the center of gravity can provide the necessary re-entry trim lift-to drag ratio while still maintaining stability.The flight trim aerodynamic characteristics of re-entry modules were calculated from on board-recorded inertial-platform accelerations and attitudes and from reconstructed trajectory data.Modified trim wind tunnel data were compared to the flight-derived data.Previous wind tunnel test had indicated that trim aerodynamic characteristics remain essentially constant above Mach 6.But the flight test results did not verify this indication.The flight-derived trim lift-to-drag ratio and trim angle of attack in the hypersonic region were essentially linear with Mach number down to 6.Static stability data showed a secondary undesirable trim point, it could be eliminated by possible configuration modifications designed and by assembled tabs or flaps on the nose of the re-entry module.