Abstract
Sounding rockets are the only direct detection method for near-space and are utilized for different kinds of scientific research. Dynamic models are the foundation of research on sounding rockets. However, no dynamic models have included all the working processes of a sounding rocket. A high-precision dynamic model of a sounding rocket is proposed in this article; the model includes motion on the launch rail, the free flight phase, parachute deployment, the inflation process, and steady descent. Through the model, the entirety of the dynamic process can be understood in detail to help improve performance. A combination wind compensation method was investigated to rapidly and accurately obtain launch parameters; the method was derived from a wind weighting and pattern search method. Based on the simulation results, the proposed approaches are proven to be effective.
Highlights
Sounding rockets, which lack control systems, are simple structures, and their costs are relatively low
We will introduce a high-precision dynamic model of a sounding rocket, which consists of motion on the launch rail, free flight, the drawing out and inflation of parachutes, and the steady descent of the sonde–parachute system
By running the program and using the simple software designed for wind compensation, the launch parameters can be updated, considering the wind effect
Summary
Sounding rockets, which lack control systems, are simple structures, and their costs are relatively low. We will introduce a high-precision dynamic model of a sounding rocket, which consists of motion on the launch rail, free flight, the drawing out and inflation of parachutes, and the steady descent of the sonde–parachute system. The main parachute in the pack is dragged out by the pilot chute, and the entire deployment process is the result of the relative motion between the pack and the pilot chute Speaking, it is a variable mass system with two bodies. Sonde has a certain mass mb, and the moment of inertia about the joint point O is Ib. Let the generalized mass of the parachute be mp and the generalized moment of inertia about O be Ip. After the successful deployment and inflation processes, the sonde enters the steady descent stage. By introducing antisymmetric matrices about LbðLxb;Lyb;LzbÞ and LpðLxp;Lyp;LzpÞ and using E3 3 3 to denote the third-order unit matrix and 03 3 3 to denote the null matrix, we can obtain the generalized mass matrix Amass and the generalized force matrix Bforce as equations (20) and (21)
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