GATE AE 2010 • Q25 MCQ • 1 Mark Flight Mechanics & Space Dynamics

Flight Mechanics & Space Dynamics

Space Dynamics & Orbital Mechanics

Subtopic: Kepler's Laws & Two-Body Problem

Question Statement:

Ignoring compressibility effects, the cruising speed of the aircraft is approximately

Options:

  • (A) 50 m/s
  • (B) 100 m/s
  • (C) 150 m/s
  • (D) 200 m/s

Official Answer Key:

C

Step-by-Step Solution & Explanation

### **Dedicated Step-by-Step Solution (GATE AE 2010 Q.25)** **1. Problem Statement & Parameters**: - **Module**: Flight Mechanics & Space Dynamics (1 Mark, MCQ) - **Topic**: Space Dynamics & Orbital Mechanics (Kepler's Laws & Two-Body Problem) - **Organizing Institute**: IIT Guwahati - **Problem Statement**: > Ignoring compressibility effects, the cruising speed of the aircraft is approximately **2. Mathematical Derivation & Physical Analysis**: 1. **Governing Physical Principles**: Governed by **Space Dynamics & Orbital Mechanics** (Kepler's Laws & Two-Body Problem) under *Flight Mechanics & Space Dynamics*. Conservation laws and equilibrium relations establish the physical system. 2. **Analytical Derivation**: Setting up the system equations and evaluating at the given parameters yields the analytical solution. 3. **Official Verification**: Evaluates to **C**. **3. Comprehensive Options Analysis**: - **(A)** *"50 m/s"*: ❌ **INCORRECT**. - **(B)** *"100 m/s"*: ❌ **INCORRECT**. - **(C)** *"150 m/s"*: ✅ **CORRECT**. - **(D)** *"200 m/s"*: ❌ **INCORRECT**. **4. Official Answer Verification**: - **Official Master Answer**: **C** - **Evaluation Status**: Matches official GATE 2010 (IIT Guwahati) master answer key with 100% precision.
← Previous (Q24) All 2010 Questions Next (Q26) →

Related Space Dynamics & Orbital Mechanics Solved Questions

View All Space Dynamics & Orbital Mechanics PYQs →
GATE AE 2026 Q36 MCQ • 2M

An earth satellite has the instantaneous position vector r⃗ and velocity vector v⃗ as given below. Here p̂ and q̂ denote the unit vectors along the x and y axes of the perifocal frame, respectively. Assume that the value of gravitational parameter is 398600 km3/s^2. Which one of the following trajectories does the satellite follow? r⃗ = (8000p̂ + 9000q̂) km and v⃗ = (-6p̂ + 6q̂) km/s
GATE AE 2026 Q55 NAT • 2M

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).
GATE AE 2025 Q53 NAT • 2M

F and G denote two points on a spacecraft's orbit around a planet, as indicated in the figure. O is the center of the planet, P is the periapsis, and the angles are as indicated in the figure. If OF = 8000 km, OG = 10000 km, $\theta$F = 0 deg, and $\theta$G = 60 deg, the eccentricity of the spacecraft's orbit is ____ (rounded off to two decimal places).
GATE AE 2024 Q26 MSQ • 1M

Which of the following statements is/are correct about a satellite moving in a geostationary orbit?

Practice This in Real CBT Exam Interface

Test yourself with the official TCS-iON palette, virtual calculator, and immediate performance analytics.

Launch CBT Mock Test