Wednesday 4 September 2013

HELLO! GUYS 

This is Team "SRM VAIMAANIX" of SRM University, Kattankulathur, Chennai and this is a CANSAT project reference blog.

Our Team SRM VAIMAANIX (2446) got successful in getting 5th place in the world and 1st in asia in the Annual Cansat Competition-2015.

5th place award

Click at the links below


Article about our team in The Hindu Newspaper

Cansat 2015 Winners

Article about our achievement in our university website

Information in Wikipedia


Theme:

We are team of 10 students who will be working for the Team Cansat of SRM University. We will be working on CANSAT regarding-

Thats actually our rocket with our payload inside it
  • DESIGN OF THE CANSAT (WITH DETAILS)
  • EXPLANATIONS OF WHY DID WE SELECT THE DESIGN.
  • MECHANICAL STRUCTURE
  • SENSORS TESTING
  • SELECTION OF SENSORS
  • INTERFACING
  • REDUNDANCY OF ELECTRONIC SYSTEM
  • POWER SUPPLY SYSTEM
  • EGG PROTECTION SYSTEM
  • COMMUNICATION SYSTEM
  • GROUND STATION
  • INTEGRATED CIRCUITS
  • MANAGEMENT
  • ARDUINO PROGRAMING
  • PAYLOAD
  • DESCEND SYSTEM
  • EXPENCES
  • CANSAT MANAGEMENT
  • REVIEW DOCUMENTATION






Our team with the Rocket loaded with our cansat


Team just 2 seconds away from getting award

About the competition



The American Astronautical Society (AAS) and American Institute of Aeronautics and Astronautics (AIAA) have organized an annual student design-build-launch competition for space-related topics. Although similar competitions exist for other fields of engineering (robots, radio-control airplanes, racing cars, etc.), most space-related competitions are paper design competitions. While these are worthwhile, they do not give students the satisfaction of being involved with the end-to-end life cycle of a complex engineering project, from conceptual design, through integration and test, actual operation of the system and concluding with a post-mission summary and debrief. This competition fulfills that need!

This annual competition is open to teams from universities and colleges. Teams must be able to design and build a space-type system, following the approved competition guide, and then compete against each at the end of two semesters to determine the winners. Rockets will be provided but teams are responsible for funding the construction of their CanSat and all travel/lodging expenses.

it has many rounds
1>PDR PRILIMINARY DESIGN REVIEW
2>CDR CRITICAL DESIGN REVIEW
3>LAUNCH
4>POST FLIGHT REVIEW

THIS COMPETITION IS GUIDED BY 













THE 2016 MISSION 

The 2016 mission simulates a sensor payload traveling through a planetary atmosphere sampling the atmospheric composition during flight.

The overall CanSat system is composed of two primary components, a science vehicle and a re-entry container that protects the vehicle during ascent, "near-apogee" deployment and initial re-entry/descent.

When deployed from the rocket the re-entry container shall descend with the vehicle secured in the container. Either the container shall release the vehicle or the science vehicle shall release itself from the container any time after deployment from the rocket. The intention of the container is to protect the science vehicle from the violent deployment and provide a more stable and less forceful release environment.

When the science vehicle is released from the container, it shall glide in a circular pattern with a diameter of no more than 1000 meters.

During flight, the glider science vehicle shall sample the air pressure and temperature at a rate of 1 sample per second and transmit the data to a ground station. Position data of the sample data shall also be recorded and included in the telemetry at the same rate. Speed of the glider shall be measured with a pitot tube and compared with GPS generated velocity data.

The glider science vehicle shall take a picture of the ground with the camera pointing at the ground when requested by the ground station judge. The imaging shall be initiated by a command sent from the ground station to the glider science vehicle. The images shall be recorded for retrieval after landing. Telemetry shall indicate the time the last command was received and the number of times the command was received.

When the science vehicle lands, transmission shall automatically stop and an audio beacon shall be activated automatically for recovery.

No egg this year.

THE 2015 MISSION //COMPLETED 


The 2015 mission simulates a Science Vehicle traveling through a planetary atmosphere sampling the atmospheric composition during descent. 

The overall CanSat system is composed of two primary components, a Science Vehicle and a re-entry Container that protects the vehicle during ascent, "near-apogee" deployment from the rocket and initial re-entry/descent. 

When initially deployed from the rocket, the re-entry Container shall descend via parachute with the Science Vehicle secured within the Container.  At any desired point after the initial 
deployment from the rocket the Container and Science Vehicle shall separate and the Science Vehicle will begin normal operations.  Note: The intent of the Container is to protect 
the Science Vehicle from the violent deployment from the rocket and provide a more stable release environment. 

When the Science Vehicle is released from the Container, it shall use passive helicopter/auto-gyro recovery method reduce its descent rate to less than 10 meters/second. The Science Vehicle must stabilize and descend properly at a minimum altitude of 300 meters. During descent, the Science Vehicle shall record video in the nadir (Earth pointing) direction until it lands.  The video camera must be stabilized in real time during descent so that the 
video image of the ground is not spinning.  The video can be recorded on-board for downloading after recovery.  The video cannot be post processed to remove the spin of the ground image.  The Science Vehicle shall collect telemetry data during descent which includes; altitude based on barometric air pressure, outside air temperature, inside temperature, flight software state, stabilization parameters, battery voltage, and bonus telemetry.  The data shall be transmitted at a 1 Hz rate to a ground station. 

When the Science Vehicle lands, transmission shall automatically stop and an audio beacon shall be activated automatically for recovery. 

The Science Vehicle shall hold one large raw hen’s egg and protect it from breaking during 
the mission. 

THE 2014 MISSION //COMPLETED 


The 2014 mission simulates a sensor payload traveling through a planetary atmosphere sampling the atmospheric composition during descent.
The overall CanSat system is composed of two primary components, a science payload and a re-entry container that protects the payload during ascent, "near-apogee" deployment and initial re-entry/descent.
Once the deployed container/payload system reaches a specified altitude the payload is released from the container to gently descend and safely land.  All operations are to be autonomous.  "Near apogee" deployment will occur at an altitude of approximately 670 meters or higher.  Upon deployment from the rocket the container and payload shall descend at  12 meters per second using any passive descent control system.  At an altitude of  500 meters the payload shall be released from the container and descend under its own control to a safe landing.  The safe landing of the payload shall be accomplished without using a parachute, para-foil, streamer, or any similar device to reduce its speed.  The payload descent rate shall be 10 m/s or less.  After release, the descent rate of the container shall not be maintained.  The payload will send telemetry during descent and not use any batteries.  All power must be harnessed from the environment.  The payload shall safely carry one raw hen's egg, which simulates  delicate payload instrumentation.
Telemetry shall be collected at a minimum 1 Hz rate.  The payload must transmit as much data as possible during descent.  Telemetry can be sent continuously or in bursts.  Once the payload lands, data transmission must stop.  Points are awarded for each 1Hz data sample collected from payload deployment from the container through landing.  Judges will review data submitted and only count the data during active descent of the payload.


SRM VAIMAANIX
Dept. of
Electronics and Instrumentation




SHIVAM PRAKASH
(Team Leader)



**THANK YOU**
=)