Project Description

Background

In recent years, the NAU rocket club has successfully participated in several NASA sponsored high-powered collegiate rocket competitions and this year, a capstone group will be centered around developing a high-powered research rocket that is two staged, built from advanced composite materials and will house a scientific payload meeting the customer requirements from Northrop Grumman (NRG).

Description

The primary objective of this mission is to develop a cost-effective test platform capable of reaching a peak altitude of at least 30,000 feet, maintaining a supersonic speed of Mach 2, and enduring accelerations exceeding 12g, all while carrying a scientific payload that adheres to Northrop Grumman's (NG) exact specifications. Although the initial altitude requirement was set at 40,000 feet, it has been adjusted to 30,000 feet due to launch site restrictions, while all other performance criteria remain unchanged.

The launch vehicle is constructed from composite materials selected during the analysis phase of the critical design review, ensuring optimal strength-to-weight characteristics. To enhance performance and reliability, the team will utilize tools such as RASAero and other simulation software to predict flight trajectories, conduct structural analyses, and model aerodynamic flows. These simulations will ensure the vehicle is fully equipped to meet the requirements established by the course, client, and project sponsors.

Client Requirements

CR1- Develop a two-stage launch vehicle -- The vehicle will be a two-stage rocket, requiring an initial booster that detaches after use to optimize flight time and speed. Once the first stage is ejected, the second stage will continue the flight.
CR2- Use of a specific stage separation device -- The client requests that the team use a particular separation method previously discussed. Details on this system are proprietary to Northrop Grumman and cannot be included in the report.
CR3- The vehicle will be constructed of composite materials -- The client prefers the vehicle to be made from a composite material due to its strength and lightweight properties. They also want this composite material to be reusable.
CR4- Vehicle will reach an altitude of at least 40,000 ft AGL (Above Ground Level) -- The client requires the vehicle to reach a fixed altitude of 40,000 feet. The chosen launch site has an altitude ceiling of 48,000 feet above sea level.
CR5- Final launch vehicle will be required to carry a maximum 10 Lb payload that will fit within a 6” diameter bay -- A key client requirement is that the vehicle includes a payload bay with a 6-inch diameter and the capability to carry at least a 10-pound payload. This is essential, as the vehicle is intended for research purposes.
CR6- Vehicle required to reach a maintain over Mach 2 or roughly 1500 mph and maximize time spent at that speed or greater -- A major client requirement is for the vehicle to not only reach Mach 2 (approximately 1,500 mph) but also to maximize the time spent at this speed or higher. Achieving such speeds will introduce compressible flow dynamics and non-linear effects.
CR7- Acceleration of the vehicle needs to meet a minimum of 12g’s --The force acting on the vehicle at launch should result in at least 12g acceleration.
CR8- Vehicle trajectory will be simulated in Rocksim -- The vehicle's trajectory should be modeled in RockSim, a rocket simulation application that allows users to set parameters to predict various measurements for the vehicle.
CR9- Vehicle required to use commercial rocket motors -- The team must utilize solid fuel commercial rocket motors for easy vehicle replacement and reuse.
CR10- Recovery of entire launch vehicle for reuse -- The client requests that the entire vehicle design be reusable after each launch, except for the motors.

Engineering Requirements

ER1- Max Velocity – Mach 2 or 1500 mph -- The vehicle's velocity refers to its speed in flight. The main engineering goal is to reach Mach 2 (1,500 mph) and maintain it for at least 30 seconds.The requirement is a two-sided constraint influenced by body size, with other factors also affecting vehicle velocity. Every rocket part impacts velocity, as added or removed weight will change it.
ER2- Separation Event – Successful or unsuccessful separation -- The project requires a simple yes or no on whether the separation works with the chosen device. It's not focused on designing a separation system, but the vehicle needs two stages. This requirement presents a one-sided constraint, as the only factor affecting the separation event is the separation device and method. Nothing else influences the separation event.
ER3- Altitude – 40,000 ft AGL (Above Ground Level) -- Altitude is a critical engineering requirement, as the team is responsible for ensuring the vehicle achieves the client's target of 50,000 feet, which is the maximum elevation allowed at the selected launch site.
This requirement is a two-sided constraint; weight and speed impact the vehicle's altitude. Changing weight or fins will affect the altitude it can reach.
ER4- Payload Weight – 10lbs -- The client requires the research vehicle to sustain supersonic flight with a 10 lbs. payload and safely return to the ground. The exact payload is unknown, but the vehicle must maximize the weight it can carry while maintaining supersonic flight. This requirement is a one-sided constraint that cannot change due to the client’s needs. This goal is fixed and will only influence other requirements, rather than being adjustable.
ER5- Cost of production - $7000 USD -- The client wants a cost-effective vehicle that can be reused and built more without high expenses. The project budget is approximately $7000; staying within this limit will fulfill this engineering requirement. Building the vehicle for less will result in an even better outcome. This requirement is a one-sided constraint since we can't design specifically for low production costs. We can focus on using affordable materials and parts, but production costs don’t significantly impact this project.
ER6- Reusable – more than 1 use -- The requirement will be evaluated based on how many uses the vehicle can withstand before major maintenance or replacement is needed. The team can only launch the final product once or twice. If the vehicle shows minimal damage post-launch, they will estimate its total usable lifespan.
§ER7- Payload Volume – 282.7 in^3 -- The client prioritized payload weight over volume and did not specify a volume requirement. The team assumes a 10 lbs. payload is under 10 inches tall. Success is defined as reaching 282.7 in³ in volume. This is a two-sided constraint because the team's engineering capabilities influence the lightweight constraint. It can be affected by other requirements, making it more complex than a one-sided constraint.