06-03-2017, 10:42 AM
Successful exploration of space requires a system that will reliably transport the payload, such as personal and instrumental, etc. Into space and return them to the earth without subjecting them to an uncomfortable or dangerous environment. In other words, the spacecraft and its payloads have to be safely recovered on the ground. We have seen re-entry capsules and winged space vehicles approaching the ground followed by a safe landing.
However, this could be achieved only after considerable research into high-speed aerodynamics and after many parametric studies to select the optimal design concept.
Reentry systems were one of the first technologies developed in the 1960s for military photographic reconnaissance, life sciences and manned spaceflight. In the 1970s, it led to the development of new space shuttle remodeling. Nowadays space technology has been developed to space airplanes who intend to regularly go and return from Earth to space stations. HERMS from the United States and Japan's HOPE is designed to land at conventional airports. Few significant advances in the current proposed re-entry capsules are ballistic designs to reduce development and renewable cost, to simplify operations.
To enter the atmospheric and non-atmospheric planet, the problem is to reduce the speed of the spacecraft. For an atmospheric planet the problem essentially involves deceleration, aerodynamic heating, time tracking and landing location. For non-atmospheric planets, the problem only involves slowing down and controlling the time and location of the landing.
The vehicle selected to perform a re-entry mission incorporates a modified aerodynamic subsonic (Mach <1) thick wing to meet the hypersonic thermodynamic requirements (Mach >> 1). The flight mechanics of this vehicle are unique in that rolling maneuvers are employed during the descent so that dynamic loading and aerodynamic warm-up are kept to a minimum.
Therefore, re-entry technology requires studies in the following areas:
1. Deceleration
2. Aerodynamic heating and air loads
3. Stability of the vehicle
4. Thermal Protection Systems (TPS)
5. Orientation and landing.
However, this could be achieved only after considerable research into high-speed aerodynamics and after many parametric studies to select the optimal design concept.
Reentry systems were one of the first technologies developed in the 1960s for military photographic reconnaissance, life sciences and manned spaceflight. In the 1970s, it led to the development of new space shuttle remodeling. Nowadays space technology has been developed to space airplanes who intend to regularly go and return from Earth to space stations. HERMS from the United States and Japan's HOPE is designed to land at conventional airports. Few significant advances in the current proposed re-entry capsules are ballistic designs to reduce development and renewable cost, to simplify operations.
To enter the atmospheric and non-atmospheric planet, the problem is to reduce the speed of the spacecraft. For an atmospheric planet the problem essentially involves deceleration, aerodynamic heating, time tracking and landing location. For non-atmospheric planets, the problem only involves slowing down and controlling the time and location of the landing.
The vehicle selected to perform a re-entry mission incorporates a modified aerodynamic subsonic (Mach <1) thick wing to meet the hypersonic thermodynamic requirements (Mach >> 1). The flight mechanics of this vehicle are unique in that rolling maneuvers are employed during the descent so that dynamic loading and aerodynamic warm-up are kept to a minimum.
Therefore, re-entry technology requires studies in the following areas:
1. Deceleration
2. Aerodynamic heating and air loads
3. Stability of the vehicle
4. Thermal Protection Systems (TPS)
5. Orientation and landing.