Syncrosoft license control error hypersonic

As shown in Figure 2, it can be sent to a predetermined height by a launch vehicle, or released by a space-based platform. Such vehicle usually adopts a large lift-to-drag ratio wave-rider configuration, and its flying Mach number is greater than 5. This vehicle reentries at hypersonic speed and flies in the near space (20-100вЂ‰km) at most of the time, of which the flight attitude is between that of the aircraft and spacecraft. It is a kind of plane-symmetry hypersonic vehicle with lifting-body configuration. At present, a feasible scheme is to use a hypersonic glide vehicle with a вЂњboost+glideвЂќ motion (as shown in Figure 1). Besides, a long flight in the near space, and the complexity of the fight trajectory, results in difficulty in controlling it. Owing to its great space application value, the hypersonic vehicle has attracted attention all over the world.

The simulation results show that the designed decoupling control method has superior control performances, and the influence of channel-coupling and uncertainty is compensated to a great extent. The simulation is carried out on the hypersonic glide vehicle model and compared with the traditional subchannel feedback control method. The theoretical deduction proves that the proposed method can ensure that the tracking error of the closed-loop system is uniformly bounded. According to the decentralized robust control theory of TornambГЁ, the coupling terms and the uncertainties are regarded as generalized uncertainties, and the NESO-based estimation and compensation signals are added to the closed-loop control law. Aiming at solving the attitude control problem of a hypersonic glide vehicle, this paper proposes a decoupling control method based on a nonlinear extended state observer (NESO).

Syncrosoft license control error hypersonic