Showing papers on "Rocket published in 2022"
TL;DR: In this article, an Analytically Reduced Chemistry (ARC) is proposed for accurate chemistry description at a reasonable computational cost, which is validated by comparison with its parent skeletal mechanism on a series of laminar flames.
9 citations
TL;DR: The authors demonstrated the performance of flight control systems of a hybrid rocket in a hovering flight test by developing a rocket designated HTTP-3AT powered by High Test Peroxide (HTP), a term used for concentrated hydrogen peroxide, H 2 O2).
9 citations
TL;DR: In this article, the experimental and numerical investigations of both swirling hybrid rocket motors without and with the design of regenerative cooling (RC hereafter), using 90%-wt H 2 O2 and polypropylene (PP) as the liquid oxidizer and the solid fuel, respectively, were performed and compared.
9 citations
TL;DR: In this paper, a numerical framework was developed to design a sub-scale transpiration cooled rocket thrust chamber ground test, where a liquid oxygen (LOX) and methane (CH 4 ) oxidiser and fuel combination was used.
5 citations
TL;DR: In this paper, an imaging-based deep learning tool was used to measure the fuel regression rate in a 2D slab burner experiment for hybrid rocket fuels, which was designed to verify mechanistic models of reacting boundary layer combustion in hybrid rockets by the measurement of fuel regression rates.
4 citations
TL;DR: A rocket-based combined-cycle (RBCC) inlet is always required to start at a relatively low Mach number in consideration of the fuel consumption in the ejector mode and the comprehensive propulsion system as mentioned in this paper.
Abstract: A rocket-based combined-cycle (RBCC) inlet is always required to start at a relatively low Mach number in consideration of the fuel consumption in the ejector mode and the comprehensive eng...
2 citations
01 Jan 2022
1 citations
DOI•
01 Jan 2022
TL;DR: In this paper, a simulation method and technology for the effect of the ejection seat rocket pack tail flame on the heat flow field of the engine room under the multi-seat ejection condition was proposed.
Abstract: This paper proposes a simulation method and technology for the effect of the ejection seat rocket pack tail flame on the heat flow field of the engine room under the multi-seat ejection condition, combines the six-degree-of-freedom motion model of the ejection seat with the CFD numerical simulation method to realize the simulation process of the thermal flow field in the engine room according to the working mechanism of the seat. The motion trajectory and attitude change law of the first ejected seat under different ejection conditions is calculated by a program written in C#, the movement of the human-seat system and the rocket at the boundary in FLUENT is specified with UDF, then the temperature and pressure change law of the second ejected seat, occupant and the surface of the cockpit during a side ejection at different ejection speeds are simulated. The simulation results show that the temperature of different characteristic points in the engine room rises first and then decreases after the rocket package is working, reaching a peak at about 60ms. The temperature at the back of the seat is the highest, and the temperature in the engine room drops faster while the pressure peak is lower when the seat is ejected at a certain speed. The analysis results can provide a theoretical basis for the design and verification of occupant thermal protection equipment.
DOI•
01 Jan 2022TL;DR: In this paper, a gravity-turn-based precise landing guidance algorithm for reusable rockets with the consideration of aerodynamic drag and necessary path constraints for operation safety is presented, which can design an algorithm requiring only solving a oneparameter root-finding problem and a small-scale linear programming problem.
Abstract: This paper presents a gravity-turn-based precise landing guidance algorithm for reusable rockets with the consideration of aerodynamic drag and necessary path constraints for operation safety. First, a gravity-turn trajectory is found to make the rocket have a soft landing. Then, to eliminate the downrange and crossrange errors, which is required by precise landing, we propose to solve an optimal control problem to correct the thrust acceleration associated with the gravity-turn trajectory. In the end, we can design an algorithm requiring only solving a one-parameter root-finding problem and a small-scale linear programming problem. Numerical examples are provided to demonstrate the performance of the guidance algorithm.
01 Jan 2022
01 Jan 2022