Otorhinolaryngological problems in medical support of space flights

At present the main trends among the most important problems of otorhinolaryngology in space medicine have become defined as vestibulology, audiology and clinical aspects (prophylaxis, diagnosis and treatment of ENT diseases in flight). The principal result of recent vestibular studies has probably been the establishment of an apparent relationship between the resistance of the vestibular system to adequate ground-based stimulation and tolerance to space flight. The findings of the studies formed the basis for the development of a new system of vestibular selection, as well as demonstrated the usefulness of special vestibular training of astronauts by active and passive methods. In audiology certain urgency is acquired by the problem of noise limitation in space cabins and auditory system reliability prediction for preserving a high work capability in crew members. The hemodynamic changes in weightlessness, as well as the possibility for allergic lesions, create conditions for distorted course of the ENT diseases and vaso-motor disorders. The prophylaxis of aspirations also deserves close attention since the possibilities of their onset increase in weightlessness. The rendering of immediate, timely aid will depend not only on the presence of the necessary medical equipment but also on the ability of the crew members to render the appropriate otorhinolaryngological aid.     

Potentialities of theoretical and experimental prediction of Life Support Systems reliability.

To develop and design Life Support Systems it is necessary to evaluate their reliability. However direct experiments take much time, are very expensive, and therefore are practically impossible. Promising way is to use approximate estimates of reliability, which need essentially fewer amounts of experimental data. Two types of estimates of Life Support System reliability--additive and multiplicative ones are considered in the paper. Additive estimate is based on the assumption that total system failure probability is low and therefore it can be considered as the sum of failure probability of separate units. Additive approach allows obtaining near lower-bounded estimate of failure probability. Multiplicative estimate allows evaluating the possibility of system catastrophe due to simultaneous effect of several factors when each of them separately is not dangerous. Evaluation shows that the possible error of reliability forecast increases with the increasing of number of external factors faster than exponential function. An illustration of the ecological similarity approach as promising tool for providing estimation of full-scale system reliability by means the set of small similar experimental models.     

Influence of gravity on the photomorphism of secondary moss protonemata

In dark-grown plantlets of the moss, Pottia intermedia, negatively gravitropic secondary protonemata differentiate from the superficial cells of leafy shoots. When transferred to the light, distal parts of the protonemata nearest to the apical cells begin to ramify and the apical cells of the side branches as well as of the main protonemal filaments often differentiate as buds. Dark-grown protonemata were oriented horizontally and illuminated from below with white light of different intensities. Only light with an intensity of 4.5 μmol·m⁻²·s⁻¹ was sufficient to induce: (a) phototropism in the apical cells, (b) light-directed initiation of branch primordia, and (c) directed growth of side branches and bud differentiation. Apical cells illuminated with light of lower (0.03–0.37 μmol·m⁻²·s⁻¹) intensity grew upwards (i.e., away from the light). It was shown that this upward growth was determined by the action of gravity. Although initiation of branch primordia was only slightly affected, their growth was strongly stimulated on the upper side of the protonemata.     

高超声速脉冲风洞中带燃料的超燃冲压发动机模型试验

给出了在ITAM最近投入使用的高超声速脉冲绝热压缩风洞AT-303中进行超燃冲压发动机模型实验的结果.实验马赫数M∞≈8,运行时间τ=50~60 ms,雷诺数范围Re1∞=2.7×106~4.0×107,模型表面的边界层自然转捩.在实验中,模型中有燃料供给:把气态氢以超过化学量比率的空气燃料因子注入到燃烧室.提供了足以发生氢燃料自点燃的流动条件.测量了沿进气道楔型压缩面和整个发动机通道上的纵向压力和热流分布.所获数据与同一模型在热射流风洞IT-302M(实验马赫数M∞≈6,8,运行时间τ=100~120 ms,雷诺数范围Re1∞=(1.3~1.8)×106,进气道压缩面和侧压缩面进行了边界层转捩).结果表明:实验模型发动机在两座风洞中进行实验所获得的流态类型相同.发动机刚刚启动时,在进气道入口及其下游的发动机通道内形成超声速流.注入氢后,首先在燃烧室内形成平均流速是超声速的燃烧流动.之后,在燃烧室出口出现热拥塞现象、在进气道扩压段产生伪激波流态.在两座风洞中进行了进气道和发动机通道的流动特征试验,获得了令人满意的结果.     

高超声速飞行器表面气动热和粘性摩擦力计算

本文给出了高超声速飞行器表面摩阻和传热系数 (斯坦顿数 )的计算结果。采用两种方法平面切面法亦即二维边界层近似法和工程方法计算了飞行器高超声速绕流的粘性效应 ,并对两种方法的计算结果作了仔细的比较。由文可见 ,对于在稠密大气层内 ,沿轨道运行头速度恒定的高超声速有翼飞行器 ,能够用本文所采用的两种方法计算其表面摩阻和热载荷。此二法可成功地应用于绕复杂形状物体的流动参数计算。