Types of Satellite Orbits



Types of Satellite Orbits

Satellite orbits are mainly classified into three based on the satellite's position relative to Earth's surface.
 First one is called Geostationary Orbits or Geosynchronous or Synchronous orbits.  In this orbit the satellite is always positioned over the same spot on Earth. 

Geostationary Orbits

Geostationary satellites are positioned in a band along the equator, at an altitude of about 35,786 km / 22,223 miles. Television, communications and weather satellites use geostationary orbits.
Second types of orbits are called Asynchronous Orbit. This orbit is much lower than geostationary orbits. Satellites in asynchronous orbit will pass overhead at different times of the day. The space stations and many other satellites are positioned in an asynchronous orbit at various  altitudes depending of the application of satellite. 
 Asynchronous Orbit

Third type of orbit is called Polar Orbit. In polar orbit, the satellite generally flies at a low altitude. The satellite in this orbit passes over the planet's poles on each revolution. 


  Polar Orbit
The polar orbit remains fixed in space and Earth rotates inside the polar orbit. As a result almost all part of earth passes under a satellite in a polar orbit and satellites in polar orbits achieve excellent coverage of the planet.  They are often used for remote sensing satellites.

Indian Remote Sensing Satellites


Indian Remote Sensing Satellites

Remote Sensing effort in India started in late sixties with the aerial survey using multi-data instrument and aircraft carrying variety of sensors like infra-red scanner and multi-specialty scanner, radio meter etc. for monitoring different crops, soil degradation, water pollution, land usage etc. Considering the need to have a global picture on a larger scale, development efforts for remote sensing satellite were pursued. Based on the successful launch of Aryabhata and Bhaskara, new series of remote sensing satellite called IRS were developed. 
 Aryabhata
ISRO has designed and developed high performance remote sensing satellite system for India and the first one, IRS-1A was launched on March 17, 1988 on board a Soviet Vostok Rocket.
The second satellite IRS-1B identical to IRS-1A was launched August 29, 1991. This carried complex payloads like linear imaging Self Scanner – LISS-1 with the resolution of 72.5 m and LISS -2A, LISS -2B with a resolution of 36.25 m. The satellite was placed in 904 km polar sun synchronous orbit with an orbital period of 103 minutes. The satellite return to their original orbital trace every 22 days enabling repeated collection of data over the same place and at the same local time. This was followed by IRS-1C class satellites.

With the PSLV getting operational, IRS-P2 satellites were placed in sun-synchronous orbit on October 15, 1994.
 The satellite control center located at Bangalore and other ground stations at different locations regularly track and monitor IRS satellite. National Remote Sensing Agency (NRSA) at Hyderabad receives the data from the IRS satellites. After processing & distribute it to the user agencies.

IRS data has been extensively used to evaluate agricultural crops yield estimate, drought monitoring and assessment, flood mapping, land use and land cover mapping, waste land management, water resource land management, ocean/marine resource survey, urban planning, mineral prospecting, various resource survey etc. The IRS system has become one of the main service sectors of ISRO for the nation.
 The TES-Satellite has provided a resolution of better than 1 m in which one could clearly identify the vehicles moving on the road. 

Flow variation along a nozzle



Flow variation along a nozzle





‘V’ - Velocity of flow of gases
‘M’ - Mach Number of fluid flow
‘P’ -   Pressure of gases
‘T’ - Temperature of flow gases

How a Solid Rocket Motor works?



How a Solid Rocket Motor works?

  • Heat sensitive charge of the initiating system is ignited by passing electric current through the embedded wire.
  • The energy release system of igniter catches fire and delivers sustained heat energy to the propellant surface.
  • Solid propellant which contains both oxygen and fuel burns and builds up pressure.
  • Pressure stabilizes when rate of gas production equals rate of gas flow through the nozzle.
  • Thrust is generated when hot gases pass through the nozzle.

Geo-Synchronous Satellite Launch Vehicle (GSLV)


Geo-Synchronous Satellite Launch Vehicle (GSLV)

ISRO  developed a Geo-Synchronous Satellite Launch Vehicle (GSLV) by incorporating the PSLV solid and liquid stage technologies for the booster system and a cryogenic upper stage as a third stage. This vehicle is about 49 m tall with a lift-off mass of 400 t. 

 First stage of GSLV
The first stage of GSLV comprises of solid propellant motor and four liquid propellant strap-on motors derived from the PSLV second stage. First stage is 20.3 m long and 2.8 m in diameter and carries 129 tons of Hydroxyl Terminated Poly Butadiene (HTPB) based solid propellant. The stage develops about 4700 kN thrust and burns for 100 s. 
 Four strap-on stages

The four strap-on stages are 19.70 m long and 2.1 m in diameter. The strapon liquid stage adopts VIKAS engine and stage is loaded with 40 tons of hypergolic propellants, namely, Unsymmetrical Di-Methyl Hydrazine (UDMH) as fuel and Nitrogen Tetroxide (N2O4) as oxidizer, stored in two separate tanks.
 Second stage of GSLV

The second stage of GSLV is 11.6 m long and 2.8 m in diameter and loaded with 37.5 tonne of UDMH and N2O4 in two compartments of an aluminium alloy tank separated by a thin metal sheet known as common bulkhead. The VIKAS engine used for the second stage employs a turbo-pump system producing a thrust of about 700 kN in vacuum.


 Third stage of GSLV
  The third stage of GSLV uses a Cryogenic Stage (CS) which is procured from Russia. The stage, that employs liquid hydrogen and liquid oxygen as fuel and oxidizer respectively. It is 8.7 m long and 2.9 m in diameter. Liquid hydrogen and liquid oxygen (LOX) are stored in two separate aluminium alloy tanks.  With a propellant loading of 12.5 tonne, the stage can burn for duration of about 750 s producing a nominal thrust of 75 kN.
 The heat shield which protects the spacecraft during the flight is of 3.4 m diameter and 7.8 m long. 








 The first flight of GSLV was on April 18. 2001 and it successfully launched G-SAT spacecraft of 1540 kg into geo-synchronous transfer orbit. 

The overall lift-off mass of the vehicle - 400 tons
Length of vehicle                                  - 49m

Payload capacity of PSLV : 

Low Earth Orbit (LEO)                        - 4.5 tons
Sun Synchronous Polar Orbit (SSPO)   - 2.2 tons

Geo Transfer orbit (GTO)                     - 2 ton.








Comparison of Solid Rocket Motors around the world



Comparison of Solid Rocket Motors around the world







Parameter
RSRM
  (Space     Shuttle)
P230
(Araine 5)
PS1 (S139)(PSLV/
GSLV)
S200
(LVM3)
Diameter (m)
3.7
3.05
2.8
3.2
Length (m)
38.2
27.0
20.2
24.9
Motor case material
D6AC
D6AC
M250
M250
Propellant mass (t)
504
237
138
207
Nozzle expansion ratio
7.7
11
9
12
Vacuum specific impulse (s)
268
275
270
274.5





Comparison of Solid Rocket Motors of Space Shuttle, Araine 5, PSLV, GSLV, and LVM3, 
 Comparison of  RSRM, P230, S139 and S200 Solid Rocket Motors 





Comparison of SOLID Propellant Vs LIQUID Propellant

Comparison of SOLID Propellant Vs LIQUID Propellant 




PROPELLANT
HTPB
(SOLID)
UDMH-N2O4
(Liquid)
LOX- P1
( Semi Cryogenic)
LOX- LH2
(Cryogenic)
Density
1.80
1.15
1.05
0.35
Theoretical ISP Vacuum
310 s
340 s
360 s
460 s
Density x ISP
558s
391 s
378 s
161 s
VOLUME RATIO
REF.
X 1.5
X 1.5
X 3

ADVANTAGES OF SOLID ROCKET MOTORS (SRMs)


ADVANTAGES OF SOLID ROCKET MOTORS (SRMs)
  1. Low cost 
  2. Longer shelf life
  3. Simplicity of system
  4. High reliability
  5. Predetermined thrust level
  6. High thrust for initial lift off

Current Solid Rocket Motors around the world




 
Current Solid Rocket Motors around the world

SPACE SHUTTLE       —    SOLID ROCKET BOOSTER / RSRM

TITAN 4B                   —    SRMU  
 
ATLAS V                    —    SRB 

DELTA IV                   —    GEM 60 

ARIANE 5                   —    P230 

H II A                          —    SRB-A 

PSLV / GSLV               —    S139 & S9 

LVM3                          —    S200 

SMALL LAUNCHERS —    ATHENA, TAURUS, PEGASUS, M5 & VEGA





Boosters Solid Motor




Solid Rocket Motors and its clasification


 
Classification of Solid Motors

Solid rocket motors are classified into four categories. They are
1.   Boosters
        Used as the first stage of a launch vehicle (Rocket). It provides the required upward thrust to enable the lift of the rocket. It also provides the sufficient thrust to overcome the fiction from the lower atmosphere during it flight.  
2.   Upper stages
Upper stage solid motors are used in any other stage other than first stage. It can be second, third or fourth stage based on the vehicle configuration. It operates above the lower atmospheric region.  So the thrust produced by upper stage motors are less compared to booster solid motors. Since it is an upper stage motor, its inert weight should be maintained as small as possible.
3.   Strapons
 It provides the required upward thrust to enable the lift of the rocket along with the booster.
4.   Special motors -The special Motors are further classified as
    •   Igniters
    •   Separation rockets
    •   Ullage motors
    •   Sounding rockets
    •   Missiles
    •   Spin / de-spin motors

  
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