# Simulation Model for Hardware-in-the-Loop Tests of the ILR-33 AMBER Rocket Control System

## TL;DR

This paper presents a simulation model for testing the control system of the ILR-33 AMBER rocket using Hardware-in-the-Loop methods.

## Contribution

The novel contribution is an advanced 6DOF simulation model integrated with hardware for real-time HiL testing of a suborbital rocket control system.

## Key findings

- The simulation model effectively replicates flight dynamics and control system behavior in real-time.
- HiL tests demonstrated the impact of the control system on flight trajectories and other key parameters.
- The model proved useful for validating control system design and mission scenarios.

## Abstract

In this paper, an advanced flight simulation model of the ILR-33 AMBER rocket is shown. The model is designed for Hardware-in-the-Loop (HiL) tests of the rocket control system. It permits us to simulate flight dynamics in a 6DOF environment, with consideration of the variable thrust, mass-inertia, and aerodynamics. It reproduces key functionalities of on-board computer and sensors and allows us to reproduce multiple mission scenarios. Simplifying assumptions concerning the environment and coordinate systems were made, reducing calculation costs while preserving key functionalities of the simulation. The control system consists of four movable canards, actuators, and motion controllers. The process of integration between the simulation model and hardware using a real-time computer is shown. Efficient communication between those elements was developed and tested in simulated flight conditions. In the final part, relevant control system HiL tests were presented. An extensive comparison between unguided and guided flight trajectories was performed. The impact of the control system operation on all analyzed parameters is clearly demonstrated. The results confirmed the usefulness of the simulation model for the task it was developed for. The potential of the HiL method in the design of complex control systems for suborbital rockets is proven.