In Seds, we work together as different teams to achieve the goals and the targets in a more specialized way. Our rocketry team is a group of around 25 highly enthusiastic and determined people who are passionately working to achieve their targets and is named as Artemis. 

The aim of the team is to build a rocket and participate in the SA Cup. The Spaceport America Cup on the SA Cup is intercollegiate rocket building competition. Nearly 1700 students participate from about 150 countries. The teams go to New Mexico, USA where they are providing with the opportunity to launch your own rockets at the controlled airspace of Spaceport America. They provide all the launch facilities, and the teams just need to make the rocket and fix it to the launcher.  The main objective is to launch the rocket till an altitude of 10,000 ft. and make it land safely. The Artemis team participates in the COTS (commercially off the shelf) category in which we can buy the motor and fix it to our rocket, we need not make it.
Basically, we build two rockets with different specifications:

Apeiron II-
Airframe length: 267 cm
Peak thrust: 2680 N
Predicted Apogee:10102 ft

Apeiron III-
Airframe length: 2.5 m
Peak thrust: 2680 N
Predicted Apogee: 3.028 km

Team Artemis further has four subsystems to ensure that every aspect of the process is covered in a professional way, and these are named as - Structures, Avionics, Recovery and Payload. 

Here’s how building rockets in SEDS BPHC works:  

1. We design every part on software like OpenRocket and then simulate them using other softwares. Then we verify the simulations with the help of seniors, PhD Scholars and professors.
After all the verification is completed, we go for actual manufacturing. We outsource some parts and build some on our own. 


In Seds we work as different teams to achieve the goals and the targets in a more specialised way and our rocketry team is a group of around 25 highly enthusiastic and determined people who are passionately working to achieve their targets and is named as Artemis. 

The aim of the team is to build a rocket and participate in the SA Cup. The Spaceport America Cup on the SA Cup is intercollegiate rocket building competition. Nearly 1700 students participate from about 150 countries. The teams go to New Mexico, USA where they are providing with the opportunity to launch your own rockets at the controlled airspace of Spaceport America. They provide all the launch facilities and the teams just need to make the rocket and fix it to the launcher.  The main objective is to launch the rocket 10,000 ft. and make it land safely. The Artemis team participates in the COTS (commercially off the shelf) category in which we can buy the motor and fix it to our rocket, we need not make it.
Basically, we build two rockets with different specifications:

Apeiron II-
Airframe length: 267 cm
Peak thrust: 2680 N
Predicted Apogee:10102 ft

Apeiron III-
Airframe length: 2.5 m
Peak thrust: 2680 N
Predicted Apogee: 3.028 km

Team Artemis further has four subsystems to ensure that every aspect of the process is covered in a professional way and these are named as - Structures, Avionics, Recovery and Payload. 

Here’s how building rockets in SEDS BPHC works:  
1. We design every part on softwares like OpenRocket and then simulate them using other softwares. Then we verify the simulations with the help of seniors, PhD Scholars and professors.
After all the verification is completed, we go for actual manufacturing. We outsource some parts  and build some on our own. Let us have a look on how different subsystems work in Team Artemis.

(1) Structures 
This subsystem is responsible for the design, simulation, and fabrication of the rocket airframe. We work with composite materials and employ CAD and CFD for our design and simulations.

With the rocket model having been edited according to manufacturability, simulations concerning the structure and fluid dynamics were run. After ordering the various components involved, the focus shifted towards manufacturing body tubes for the rocket, an airbrake assembly for the rocket and multiple prototypes needed for trial launches and requisite tests to be conducted.


2) Avionics
This subsystem looks into the electronics requirements of the mission. This involves telemetry logging, GPS, ground communication, altimetry, etc. We used Printed Circuit Board (PCB) and coded it using Arduino. Now, with the aim to reduce PCB footprints and accommodate more sensers and for accurate measurement: SMD Components have been incorporated.

3) Recovery

This subsystem deals with safely getting the rocket back to the ground. They are in charge of designing parachutes, optimizing descent rates, designing ejection charges, and other details related to the safe recovery of the rocket.
The reefing mechanisms that control the rate of opening of parachute and it’s opening area are set in place with the completion of allied calculations. After seeking guidance from a high-ranking scientist regarding parachute manufacturing, we designed a first of its kind CO2 ejection system. With the CAD files in place, purchase of components is awaited at the time of writing.


4) Payload
We used a biological payload for which we got a special mention at the 2021 SA Cup. We are no longer using a biological payload is and the subsystem is being restructured. 

Our pivot
In the coming few months, we are going to pivot into a project-based team. All the subsystems will focus on a few projects relevant to their area and publish papers. This will help students interested in aerospace get an exposure to the field with hands-on experience as well points on their resume for external research internships and master’s applications. 




 SPACEPORT AMERICA CUP

We have modelled a rocket engine motor which fell under the J class.

The propellant was worked upon initially with the help of juniors in the team, while the seniors were invested in developing a remotely activated igniter to initiate ignition wirelessly through the Bolt IoT kit.

All the steps and the processes were later documented as well as organized for future references. It’s written in such a way that the information can be published when combined on the whole.

By the end of November 2022, we had successfully fired two motors and acquired their data through the NI DAQ max and MATLAB. The data had been processed by the following week and was made ready for the finishing of documentation.

CURRENT ENDEAVOURS:
Currently, we have procured all the logistical items required for the next level of the rocket motor which is expected to reach the M class mark.
This includes getting the chemicals, body tubes, liners, bulkhead, nozzle, and other requirements for assembling the motor.

FUTURE BIDDINGS:
Currently, we are in the face of cooking the propellant.
We are simultaneously working on the calibration of the load cells for the data acquisition of the larger forces it is going to experience.




ROCKET PROPULSION

A cube satellite or a CubeSat is essentially a type of miniature satellite. The primary design of a CubeSat is a 10-centimeter cube that weighs less than 1.33 kilograms. Therefore, it requires less power than traditional large satellites and is faster and cheaper to develop. 

The components of a CubeSat can be classified into the following subsystems: 
1)Structures 
2)Communication 
3)Electrical power systems (EPS) 
4)Altitude Determination and Control Systems (ADCS) 
5)Command and Data Handling (C&DH)

CubeSats are primarily used for remote sensing and communication in the lower orbits of Earth as well as for defense purposes. Since they are of low cost, they are used frequently in research fields related to science, exploration, technology development, etc. 

Team Hyperion is one of the technical teams of SEDS and their main aim is to construct a CubeSat. They are planning to launch a cube satellite sometime in the near future. It has been named NEMO lite and has the standard dimensions of I U (10cm x 10cm x 10cm) satellite. The team will be looking to get some flight time with the satellite and to run tests to check the functioning of its subsystems.



CUBESAT

The CanSat is a miniature satellite payload that consists of a container and payload (attached to the container by a tether). The CanSat container has a compact Avionics Bay consisting of Pressure, Rotation & GPS sensors to collect accurate data. 
Our CanSat Team (Team Janus) finished 23rd globally out of the 50 teams that participated in the CanSat Tournament at Virginia Tech University, USA on 9th June 2022. The CanSat was launched to an altitude ranging from 670 to 725 meters above the launch site and deployed near apogee. Once the CanSat is deployed from the rocket, it descends using a parachute at a rate of 15 m/s. At 400 meters, a larger parachute was deployed to reduce the descent rate to 5 m/s. At 300 meters, the CanSat released a tethered payload to a distance of 10 meters in 20 seconds. During that time, the payload maintained the orientation of a video camera pointing in the south direction. The video camera, pointed 45 degrees downward, ensured that the terrain was in the video.

Apart from the modeling, designing, software development, sensor integration, and manufacturing, four tests were conducted to test the recovery system of the container, the release mechanism for releasing the CanSat from the container, construction quality, and material performance.




CANSAT

Team Archangel is the Research and Development division of SEDS BPHC.


**Grains:**

- When the solid propellant mass is cast, moulded and shaped into a specific geometrical configuration, the final product obtained is called a grain.
- Solid propellant we use is a mixture of Potassium Nitrate (KNO3) and Dextrose, together called KNDx.

**Liner:**

- It is a thin adhesive layer which lies between the solid propellant and the outer casing layer.
- It provides resistance to heat which develops inside the chamber.


**Casing:**

- The casing is the outermost layer of the rocket motor.
- It provides resistance to the chamber pressure.

**Bulkhead:**

- The topmost part of the rocket motor, the bulkhead, blocks off the air flowing through the rocket tube.
- It is fitted on the rocket tube using bolts and nuts.

**Nozzle:**

The lowermost part of the rocket tube, nozzle, is used to accelerate hot exhaust to produce thrust as described by Newton's Third Law of Motion.

**Solid Rocket Motors:**

- The team has built and fired E, F and K-class motors.
- For Kalypso (a K-class rocket motor), the team used a propellant made of KNO3 (Potassium Nitrate) and sugar and simulated characteristics such as the burn time of the motor before testing it out in the field.
- Now, we aim to not only improvise, design and test K class motors with the desired impulse of 2500N, but do the same for subsequent higher classes of motors.
- The thrust stand has been designed completely by us and uses aluminium profiles to provide a rigid framework for testing various solid rocket motors and hybrid rocket engines. Several iterations of FEA simulations and calculations were done to validate the design and ensure that the stand is safe for use.

**Apart from building solid rocket motors, we have other ongoing projects in Archangel such as:**

**Thrust Vector Control:**

- It is the ability of a rocket to maintain its trajectory in motion by manipulating the direction of thrust coming out of the exhaust of the engine.
- This maintenance is handled by special types of motors known as servo motors which in turn are controlled by controllers to acquire highest precision. Reinforcement learning is used for this purpose and will cancel all the hurdles that come in the way of the rocket when subjected to an uncertain environment, thus combating the disruption in its trajectory.
- The gimballed thrust then allows swivelling of the rocket from side to side.

### HRE(Hybrid Rocket Engine):

- The Hybrid Rocket Engine (HRE) project at SEDS is a part of the next generation of rocket propulsion research at BITS.
- An HRE uses a liquid or a gaseous oxidizer along with a solid propellant. It is suitable for academic and research settings due to the relatively safer operation of hybrid engines in comparison to liquid rocket engines.
- The current HRE testbed is being designed for a maximum thrust of 1KN. This allows us to rapidly prototype and test different injection and feed systems. In the future, learnings from this project will be implemented in the design and manufacture of flight-ready HREs for our rockets.
- Currently, the team is designing the feed system that would deliver the oxidizer to the combustion chamber of the rocket engine. This project allows students to work with both solid and liquid components in a rocket engine, thereby imparting the necessary knowledge to develop more sophisticated systems in the future.

Intro To Archangel

### Sometimes, never is the way

Just something to live by.

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SPACEPORT AMERICA CUP

ROCKET PROPULSION

CUBESAT

CANSAT

Intro To Archangel

Never. Forever.