Liquid Propulsion System Center (LPSC), Bengluru

Liquid Propulsion Systems Centre (LPSC) is the lead Centre for development and realization of earth-to-orbit advanced propulsion stages for Launch Vehicles and also the in-space propulsion systems for Spacecrafts. The LPSC activities and facilities are spread across its two campuses viz., LPSC Headquarters and Design Offices at Valiamala/Thiruvananthapuram, and Spacecraft Propulsion Systems Unit at LPSC, Bangalore/Karnataka. LPSC is vested with the responsibility of design, development and system engineering of high performance Space Propulsion Systems employing Earth Storable and Cryogenic Propellants for ISRO’s Launch Vehicles and Satellites. Development of fluid control valves, transducers, propellant management devices and other key components of Liquid Propulsion Systems are also under the purview of LPSC.

LPSC Valiamala is the Centre Headquarters, responsible for R & D, System Design/Engineering and Project Management functions. The Fluid Control Components Entity and the Materials & Mechanical Engineering Entity are located here apart from the Earth Storable & Cryogenic Propulsion Entities, handling the core tasks of the Centre.

LPSC Bangalore focuses on satellite propulsion. Design & Realisation of Propulsion Systems, integration of spacecraft propulsion systems for Remote Sensing and Communication satellites, Development and production of transducers / sensors are other major activities at LPSC, Bangalore. Fabrication of launch vehicle stage tanks and structure at ASD/HAL is also coordinated and managed by LHWC at Bangalore.,

Liquid Propulsion System Center (LPSC), Bangalore is a major propulsion complex of the Indian Space Research Organisation (ISRO). It is located in Peenya Industrial Area, Bangalore, Karnataka, India. The LPSC was established in 1969 to develop and manufacture liquid propulsion systems for ISRO’s launch vehicles.

The LPSC has a number of facilities, including a propellant plant, a test facility, and a manufacturing facility. The propellant plant produces liquid propellants, such as kerosene and liquid Oxygen, for ISRO’s launch vehicles. The test facility tests the performance of liquid propulsion systems. The manufacturing facility manufactures liquid propulsion systems for ISRO’s launch vehicles.

The LPSC has developed and manufactured a number of liquid propulsion systems for ISRO’s launch vehicles. These include the Vikas engine, the S139 engine, and the CE-7.5 engine. The Vikas engine is a liquid-fueled rocket engine that is used in the second stage of the Polar Satellite Launch Vehicle (PSLV). The S139 engine is a liquid-fueled rocket engine that is used in the third stage of the Geosynchronous Satellite Launch Vehicle (GSLV). The CE-7.5 engine is a liquid-fueled rocket engine that is used in the first stage of the Small Satellite Launch Vehicle (SSLV).

The LPSC has also been involved in a number of projects, including the Chandrayaan-1 mission, the Mars Orbiter Mission (MOM), and the Gaganyaan mission. The Chandrayaan-1 mission was a lunar exploration mission that was launched in 2008. The MOM mission was a Mars exploration mission that was launched in 2013. The Gaganyaan mission is a human spaceflight mission that is scheduled to be launched in 2023.

The LPSC has achieved a number of successes in its history. It has developed and manufactured a number of liquid propulsion systems for ISRO’s launch vehicles. It has also been involved in a number of successful space missions, such as the Chandrayaan-1 mission, the Mars Orbiter Mission (MOM), and the Gaganyaan mission.

The LPSC has a number of future plans. It plans to develop and manufacture new liquid propulsion systems for ISRO’s launch vehicles. It also plans to be involved in a number of future space missions, such as the Aditya-L1 mission and the Aditya-V mission.

The LPSC is a major propulsion complex of ISRO. It has a number of facilities and has developed and manufactured a number of liquid propulsion systems for ISRO’s launch vehicles. It has also been involved in a number of successful space missions. The LPSC has a number of future plans, such as developing and manufacturing new liquid propulsion systems and being involved in a number of future space missions.

What is a liquid-propellant rocket engine?

A liquid-propellant rocket engine is a rocket engine that uses liquid propellants as its working fluid. The propellants are stored in separate tanks and are pumped into the combustion chamber, where they are ignited and burned. The hot gases produced by the combustion are then expanded through a nozzle to produce thrust.

What are the advantages of liquid-propellant rocket engines?

Liquid-propellant rocket engines have several advantages over solid-propellant rocket engines. They can be throttled, which means that the thrust can be varied during flight. This is useful for maneuvers such as orbit insertion and landing. Liquid-propellant rocket engines also have a higher specific impulse, which means that they produce more thrust for a given amount of propellant. This makes them more efficient for long-range missions.

What are the disadvantages of liquid-propellant rocket engines?

Liquid-propellant rocket engines have several disadvantages compared to solid-propellant rocket engines. They are more complex and require more maintenance. They also take longer to start and shut down. Liquid-propellant rocket engines are also more expensive than solid-propellant rocket engines.

What are the different types of liquid-propellant rocket engines?

There are two main types of liquid-propellant rocket engines: bipropellant engines and hypergolic engines. Bipropellant engines use two different propellants, such as kerosene and liquid oxygen. Hypergolic engines use two propellants that ignite spontaneously when they come into contact with each other, such as hydrazine and nitrogen tetroxide.

What are some of the applications of liquid-propellant rocket engines?

Liquid-propellant rocket engines are used in a variety of applications, including:

Spacecraft propulsion: Liquid-propellant rocket engines are used to propel spacecraft into orbit and to maneuver them in space.
Missile propulsion: Liquid-propellant rocket engines are used to propel missiles to their targets.
Launch vehicle propulsion: Liquid-propellant rocket engines are used to propel launch vehicles into orbit.
Aircraft propulsion: Liquid-propellant rocket engines are used to power some experimental aircraft.

What are some of the challenges of using liquid-propellant rocket engines?

One of the biggest challenges of using liquid-propellant rocket engines is the need to store the propellants in separate tanks. This can be difficult and expensive, and it also increases the risk of leaks. Another challenge is the need to keep the propellants at the correct temperature and pressure. This can be difficult to do, especially in the harsh Environment of space.

What are some of the future developments in liquid-propellant rocket engines?

One of the most promising future developments in liquid-propellant rocket engines is the development of new propellants that are more efficient and less toxic. Another promising development is the development of new engine designs that are more reliable and easier to maintain.

Which of the following is not a type of rocket propellant?
(A) Solid propellant
(B) Liquid propellant
(C) Hybrid propellant
(D) Gaseous propellant
Which of the following is the main advantage of solid propellant rockets?
(A) They are simpler and cheaper to manufacture than liquid propellant rockets.
(B) They can be stored for longer periods of time without being used.
(C) They have a higher thrust-to-weight ratio than liquid propellant rockets.
(D) They are more reliable than liquid propellant rockets.
Which of the following is the main disadvantage of solid propellant rockets?
(A) They cannot be shut down once they have been ignited.
(B) They have a lower specific impulse than liquid propellant rockets.
(C) They are more difficult to control than liquid propellant rockets.
(D) They are more dangerous to handle than liquid propellant rockets.
Which of the following is the main advantage of liquid propellant rockets?
(A) They can be shut down and restarted in flight.
(B) They have a higher specific impulse than solid propellant rockets.
(C) They are more controllable than solid propellant rockets.
(D) They are safer to handle than solid propellant rockets.
Which of the following is the main disadvantage of liquid propellant rockets?
(A) They are more complex and expensive to manufacture than solid propellant rockets.
(B) They require cryogenic propellants, which are difficult to store and handle.
(C) They have a lower thrust-to-weight ratio than solid propellant rockets.
(D) They are less reliable than solid propellant rockets.
Which of the following is the main advantage of hybrid propellant rockets?
(A) They are simpler and cheaper to manufacture than liquid propellant rockets.
(B) They can be stored for longer periods of time without being used.
(C) They have a higher thrust-to-weight ratio than solid propellant rockets.
(D) They are more reliable than solid propellant rockets.
Which of the following is the main disadvantage of hybrid propellant rockets?
(A) They cannot be shut down once they have been ignited.
(B) They have a lower specific impulse than liquid propellant rockets.
(C) They are more difficult to control than liquid propellant rockets.
(D) They are more dangerous to handle than liquid propellant rockets.
Which of the following is the main advantage of storable propellant rockets?
(A) They can be stored for long periods of time without being used.
(B) They are less complex and expensive to manufacture than cryogenic propellant rockets.
(C) They have a higher specific impulse than cryogenic propellant rockets.
(D) They are more reliable than cryogenic propellant rockets.
Which of the following is the main disadvantage of storable propellant rockets?
(A) They have a lower thrust-to-weight ratio than cryogenic propellant rockets.
(B) They are more difficult to control than cryogenic propellant rockets.
(C) They are more dangerous to handle than cryogenic propellant rockets.
(D) They are less efficient than cryogenic propellant rockets.
Which of the following is the main advantage of cryogenic propellant rockets?
(A) They have a higher specific impulse than storable propellant rockets.
(B) They are more efficient than storable propellant rockets.
(C) They are more reliable than storable propellant rockets.
(D) They are less dangerous to handle than storable propellant rockets.
Which of the following is the main disadvantage of cryogenic propellant rockets?
(A) They require cryogenic propellants, which are difficult to store and handle.
(B) They are more complex and expensive to manufacture than storable propellant rockets.
(C) They have a lower thrust-to-weight ratio than storable propellant rockets.
(D) They are more difficult to control than storable propellant rockets.
Which of the following is the main advantage of reusable launch vehicles?
(A) They can be used multiple times, which reduces the cost of launches.
(B) They are more reliable than expendable launch vehicles.
(C) They can be launched on shorter notice than expendable launch vehicles.
(D) They are more environmentally friendly than expendable launch vehicles.
Which of the following is the main disadvantage of reusable launch vehicles?
(A) They are more complex and expensive to develop and manufacture than expendable launch vehicles.
(B) They have a lower payload capacity than expendable launch vehicles.
(C) They are more difficult to maintain and refurbish than expendable launch vehicles.
(D) They are more dangerous to operate than expendable launch vehicles.
Which of