Archytas’ Pigeon ⇒ ~400 BC Hero’s Engine - Hero of Alexandria ⇒ 100 AD Fire Arrows ⇒ 1045 AD - Chinese vs Mogols de Laval Nozzle → 1888 Gustaf de Laval - Converging / Diverging Meter - for subsonic flow and super sonic flow The german v2 rocket - werner von braun
- warhead , guidance, lox, water-alcohol mix, turbomachiner, rocket nozzle
yuri gagarin → the first man in space
- vostok 1 ⇒ 1961, mission name
aero-spike nozzles → due to de Laval nozzle being in-efficient in space but aero-spike is efficient almost in all pressure aeras.
- downside - not yet built
rocket lab, seirra space, astra, firefly aerospace, blue origin, stoke space, virgin galactic skyroot aerospace - indian startup
$9.6b in 2020 → indian market sharei in space - 2-3%
Ignition teams
- airframe & structures ⇒ building the body of the rocket
- focus on aerodynamics
- centre of pressure
- centre of gravity
- cog should be ahead of cop
- open rocket software → for building and simulation model rockets
- CAD / solidworks → for building the 3d model of the rocket
- parts
- part assembly
- assign materials to the parts
- Ansys - CFD (Computational Fluid Dynamics) analysis - fluid aerodynamics
- FEA (Finite Element Analysis) - structure analysis
- static structural
- FEA analysis on the static test pad
- focus on aerodynamics
- propulsion
- specific impulse
- thrust
- nozzle ldesign
- ideal rocket equation
- types of fuel
- liquid
- pressure fed
- gas generator
- solid
- motor casing ⇒ outer lining to hold the structure
- forward closure ⇒ cap for the motor attached on the top
- thermal liner ⇒
- nozzle ⇒ convergent / divergent nozzle
- fuel → bates fuel → reaches a temp. that can burn through metal → 1600 C
- types of solid fuel
- bates
- rod and tube
- finocyl → star become a bigger circle (increases surface area ⇒ more thrust)
- moon burner
- hybrid fuel ⇒ oxidizer tank and fuel grain. control the oxidizer flow to manage thrust
- liquid
- first attempt → leakage from screw holes due to o-rings placed outside
- second attempt → screw alignment was off the mark
- nozzle types
- bell shaped
- more gradual increase but harder to manufacture
- convergent / divergent nozzle
- was tending to reach mach 1 but never reached it
- bell shaped
- expansion ratio (types of nozzles)
- under expanded
- optimally expanded
- over expanded (prefer this kind of nozzles)
- mach diamonds / shock diamonds ⇒ structure that form due to differences in pressure
- make motor on “open motor” software
- cooking fuel → casting → stuffing in the motor → launch
Abyudhay → siddesh → 3rd year from IITM team abyudhay that makes sounding rockets (rocket testing - that don’t go to space, for research in the atmosphere; weather studies) goddard space flight center - works on sounding rockets
- study the affect of suns rays in the atmosphere
- micro gravity experiments
- world’s largest tower for microgravity - 9seconds
- IITM plans to give about 10 minutes of micro gravity time
- new mexico - space world cup america - chetak 1.0 in 2023 - scored 16th rank in 160 participating teams
- overall ranking was 67th in the competition
- 2024 - reached mach .9 → overall ranking was 20 and categorical ranking of 11
- asia’s best student rocket team
- solid - cots engine - commercially bought
- pressure proof testing → 30 bars for this rocket , (have to ensure the rocket doesn’t leak)
- 8 o rings
- 60 bolts
- failed leak test thrice → 1.5x times the original pressure for pressure proof testing
- 120 bars for pressure testing
- testing hybrid engine with different oxidier pressure to achieve variable thrust
-
- continuous 6 static firing tests
- maximum seed start efficiency and thrust → 250N , 4.92 converging area ratio
- next goal → build a 3kN engine to be fit in chetak 3.0 for next years space port competition
- predicting the trajectory of the hybrid rockets is very hard compared to hybrid rockets
- planning to host a space port cup in india next year
-
recovery system
- safely return to surface of earth after launch
- recovery through parachutes
- single deployment
- dual deployment
- drogue chute → decrease speed, provides control and stability
- main chute
- ejection mechanism to eject the parachute
- electric discharge
- pyrotechnique
- 16 gram CO2 catridges (team iginition rocket)
- compression of spring through a retention pin and remove retention pin to puncture co2 canister and eject the chute
-
avionics (Gokul team lead)
- blend of aviation & electronics
- avionics acts as the brain. To make decisions based on the sensor’s data
- accelerometers, gyroscope, GPS, GNS, GNC
- detecting apogee and other measurements
- two sensors → using low pass filters to get accurate data
- altimeter → barometer sensor by measuring pressure
- Telemetry system → establishing the connection between the ground station and the rocket
- LoRA sensor → transfer data from rocket’s computer to ground station
- Stguard → storage of flight data
-
payload
- different types of payloads -
- scientific payloads → hubble, JWST, curiosity rover, perseverance
- communcation payload - the ultimate group chat admins i
- cargo payloads - apollo lunar module
- shapes
- cylindrical cansat - hubble, soyuz → pr
- box -shaped cubesat
- cone-shaped payloads → mostly preferred for re-entry
- SuryaSat: (Ignition’s Payload)
- radiation detection
- exploring UV shielding efficiency of advanced materials
- UV rays :
- why go for UV shielding:
- very harmful for human beings
- to reduce noise in communication
- materials: kapton: good at heat resistance & thermal insulation, polyester, teflon
- testing setup
- data collection through sensors
- converting raw analog values to digital usign ADC
- logging data onto SD card
- secondary payload
- raspberry pi
- BME280
- MPU6050
- Buzzer
- SD Card Module
- Neo6m GPS
- EPS → Electrical power system
- air pressure, sensor
-
software
- technical simluations
- predicting where the rocket would go is the hard part
- simulink : simlation and modelling
- flight control systems: brains of aviation
- telemetry systems
- kalman filter: to filter noise from the data
Ignition got selected in the IAC
- propellant composition of model rocket of ignition → potassium nitrate and sorbitol