JNTU B.Tech IV LAUNCH VEHICLE AND MISSILE TECHNOLOGY Previous Question Paper (July - 2021 - R15)

A sounding rocket, or research rocket, is an instrument-carrying rocket designed to take measurements and perform scientific experiments during its sub-orbital flight. These vehicles are primarily used to probe the upper atmosphere, conduct microgravity research, and test components for larger space systems. Unlike orbital launch vehicles, they do not achieve the velocity required to enter Earth's orbit.

The similarities between launch vehicles and missiles include the use of propulsion systems (solid or liquid propellants), aerodynamic control surfaces or thrust vector control for stability, and guidance and navigation systems to manage the flight trajectory.

The primary differences are:

• Purpose: Launch vehicles are designed to deliver payloads (satellites or spacecraft) into orbit or beyond, whereas missiles are designed to deliver a warhead to a specific target.
• Trajectory: Launch vehicles follow a precise, pre-calculated trajectory to reach orbital velocity, whereas missiles often require terminal guidance to intercept moving or stationary targets.
• Recovery: Launch vehicles (especially reusable ones) are designed for controlled descent or orbit insertion, while missiles are typically expendable and intended for impact.
• Payload Integration: Launch vehicles prioritize mass-to-orbit capability, while missiles prioritize accuracy, lethality, and rapid deployment readiness.

An ideal rocket is characterized by the following features:

• High Specific Impulse: It should provide maximum thrust per unit of propellant consumed to ensure high efficiency.
• High Mass Ratio: The rocket should have a high ratio of initial mass to final mass, implying a lightweight structure and high propellant capacity.
• Structural Efficiency: The airframe must be constructed from high-strength, low-density materials to minimize dead weight.
• Reliability: It must possess high operational reliability under extreme thermal, vibrational, and acoustic loads.
• Controllability: It should feature advanced thrust vectoring or reaction control systems for precise attitude and trajectory management throughout the flight.