1) Reentry trajectory
再入轨道设计
2) Re-entry
再入
1.
Reaction Control System of RLV Blended Control in Re-entry Mode;
反作用控制系统在RLV再入复合控制中的研究
2.
Design of an Predictive Control Law for Re-entry Aerospace Vehicle;
空天飞行器再入制导的预测控制
3.
Based on characters of high dynamic near space unmanned aerial vehicle(UAV) in re-entry mode,which has a large dynamic flight range and paramter uncertainty,a multiple-time-scale continuous sliding mode control(SMC) system is designed with Lyapunov methods.
针对临近空间高动态无人飞行器(UAV)再入飞行动态范围跨度大,气动参数存在不确定性等特点,利用李雅普诺夫方法设计了具有不同时间量程的双回路滑模控制系统。
3) Reentry
再入
1.
Analysis of Scattering for the Flow Field of Reentry Blunted Cone;
再入钝锥体绕流流场电磁散射特性分析
2.
Influence of Wind Field on the Hit Accuracy of Ballistic Missile in Reentry Stage;
再入段风场对弹道导弹射击精度影响的仿真试验研究
3.
Study on Robust Variable Structure Control for Hypersonic Missile in Reentry;
高超声速导弹再入的鲁棒变结构控制方法研究
4) readmission
再入院
1.
A clinical analysis of cause and strategy of 100 cases of short-term readmission of pediatric patients;
儿童患者短期再入院100例临床分析及对策
2.
Results The causes of readmission were residual prostatic hyperplasia for 32 patients (31.
目的分析前列腺电切术后因并发症再入院患者的原因及治疗方法。
3.
Objective:To expound the correlation between readmission of apoplexy patients and burden of family caregiver,to identify the main intervention method for decreasing readmission rate of apoplexy patients because of overburden of caregivers,and so as to provide supportive guidance for caregivers of apoplexy cases.
[方法]用自设问卷和相关量表调查病人及其主要照顾者各100例,将再入院率与照顾者负担进行分析。
5) reentry guidance
再入制导
1.
A Kind of Mixed Reentry Guidance Method for Weapon System of Space-based Attack Ground;
天基对地攻击武器的一种混合再入制导方法研究
2.
This paper introduce the recent development of the spacecraft reentry guidance method in the world.
介绍了国内外航天器再入制导方法领域研究的近期进展,分标准轨道制导法和预测-校正制导法详细剖析了各种再入制导律的设计思路与研究框架,指出了自主性、自适应性和鲁棒性、并且能够适应多任务的新型再入制导方法是目前的研究热点和发展方向。
3.
The predictor-corrector reentry guidance algorithm for reusable launch vehicles was studied.
研究了可重复使用运载器的预测-校正再入制导方案。
6) Entry guidance
再入制导
1.
Entry guidance and trajectory tracking error analysis;
再入制导和弹道跟踪误差分析(英文)
2.
A new reusable launch vehicle(RLV) entry guidance algorithm with ranging technique which only needs to update flight profile parameters was developed and a predictor-corrector entry guidance methodology using Runge-Kutta-Fehlberg method for RLVs combined with trajectory online generation technology was studied.
进一步对两种制导方法进行了比较分析研究,研究认为标准轨道制导与轨道预测制导都是可行的RLV再入制导方案,其有机结合是未来可重复使用跨大气层飞行器再入制导的发展趋势。
参考词条
补充资料：再入轨道
| 再入轨道 re-entry trajectory 航天器在完成预定使命后，进入地球大气层并在地球表面降落过程中其质心的运动轨迹。航天器到达大气层边界的点称为再入点。为了使航天器再入地球大气层，必须首先点燃制动火箭，使其改变速度的方向和大小，脱离原来的轨道。根据再入方式的不同，再入轨道主要有两种类型：①弹道式。航天器进入大气层后不控制升力，沿着单调下降路线返回地面。这种方式技术简单、容易实现，但气动力引起的过载较大，落点精度也较差。②滑翔式。航天器作为一个滑翔体，利用其在大气层中运动时产生的升力控制下降速度，因而承受的过载显著减小，降落时的航向和侧向都可以作适当调整，以提高落点精度。但是升力控制的技术比较复杂，难度较大。 |
说明：补充资料仅用于学习参考，请勿用于其它任何用途。