Re-entry and Planetary Entry Physics and Technology: II / Advanced Concepts, Experiments, Guidance-Control and TechnologyDuring the last decade, a rapid growth of knowledge in the field of re-entry and planetary entry has resulted in many significant advances useful to the student, engineer and scientist. The purpose of offering this course is to make available to them these recent significant advances in physics and technology. Accordingly, this course is organized into five parts: Part 1, Entry Dynamics, Thermodynamics, Physics and Radiation; Part 2, Entry Abla tion and Heat Transfer; Part 3, Entry Experimentation; Part 4, Entry Concepts and Technology; and Part 5, Advanced Entry Programs. It is written in such a way so that it may easily be adopted by other universities as a textbook for a two semesters senior or graduate course on the sub ject. In addition to the undersigned who served as the course instructor and wrote Chapters, 1, 2, 3 and 4, guest lecturers included: Prof. FRANKLIN K. MOORE who wrote Chapter 5 "Entry Radiative Transfer," Prof. SHIH-I PAI who wrote Chapter 6 "Entry Radiation-Magnetogasdy namics," Dr. CARL GAZLEY, J r. who wrote Chapter 7 "Entry Deaccelera [ion and Mass Change of an Ablating Body," Dr. SINCLAIRE M. SCALA who wrote Chapter 8 "Entry Heat Transfer and Material Response," Mr. |
Contents
reentry and planetary entry has resulted in many significant advances | 1 |
Dynamics Thermodynamics Physics and Radiation Part 2 Entry Abla | 15 |
Part One Entry Dynamics Thermodynamics | 17 |
Copyright | |
3 other sections not shown
Other editions - View all
Common terms and phrases
ablation aerodynamic heating altitude altitude density analytical approximate solution angle of elevation angles of inclination Astrodynamic ballistic entry boundary layer circular orbit velocity Co-Planar coefficient convective cos² drag drag coefficient Earth electrons energy Entry at Constant equations equilibrium flight flow fluid ft/sec gasdynamic Gazley gliding entry heat conduction heat input heat transfer heating rate hypersonic initial angles initial entry integration k₁ Kepler Number large angles launch radius lift lift-drag ratio magnetic field mass loss maximum deceleration Norair Report Numerical exact solution obtains optically thick optimum Order Theory parameter perigee planet planetary atmosphere plasma problem radiation magnetogasdynamics Re-Entry Reference region satellite second order solution Section shield shock wave shown in Figure speed stagnation point Substituting Eq surface temperature thermal radiation tion trajectory transverse waves true anomaly V₁ variables vehicle тв