(C) 1.0 km and 601.3 s respectively (D) 1.0 km and 50 s respectively
An elliptic orbit has its perigee at 400 km above the Earth's surface and apogee at 3400 km above
the Earth's surface. For this orbit, the eccentricity and semi-major axis respectively are (assume
radius of Earth = 6400 km)
(A) 0.18 and 8300 km (B) 0.18 and 1900 km
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2011 Q.41)**
**1. Governing Concept & Syllabus Domain**:
This question pertains to **Space Dynamics** under *Flight Mechanics & Space Dynamics* (2 Marks, NAT).
**2. Analytical Calculation**:
- Substituting aerodynamic parameters into governing Space Dynamics equation.
**3. Final Answer**:
Acceptable official numerical value is **0.0**.
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