An earth satellite moves in an elliptical orbit with a perigee altitude of 300 km and
an apogee altitude of 3000 km. Assume that the radius of the earth is 6378 km.
The eccentricity of the orbit is __________ (rounded off to three decimal places).
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2026 Q.55)**
**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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