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Motion control simulation method for near-space hypersonic aircraft

A technology of hypersonic speed and simulation method, which is applied in the aerospace field and can solve problems such as aircraft modeling problems that are not considered

Inactive Publication Date: 2011-05-25
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

while such research work represented by the published literature does not consider the problem of modeling the vehicle in the complex near-space environment and under the specific engine thrust model

Method used

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  • Motion control simulation method for near-space hypersonic aircraft
  • Motion control simulation method for near-space hypersonic aircraft
  • Motion control simulation method for near-space hypersonic aircraft

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Embodiment Construction

[0058] (1) Establish the motion model of the aircraft under changing wind field conditions;

[0059] The modeling process of the near-space hypersonic vehicle will be described in detail below.

[0060] The near-space hypersonic vehicle provided by the present invention is based on the technical report (Shaughnessy J D, Pinckney S Z, McMinn J D, Cruz C I, Kelley M-L. Hypersonic Vehicle Simulation Model: Winged-cone Configuration. NASA TM -102610, 1990) proposed a winged cone structure with triangular wings, a single vertical tail rudder, and left and right elevon rudders that can work independently. Its aerodynamic layout is shown in Figure 1(a) and Figure 1(b) The relevant geometric parameters of the aircraft can be found in this technical report, and will not be repeated here.

[0061] Due to the relative complexity of the near-space flight environment, it brings certain difficulties to the design of the control system of the near-space hypersonic vehicle, so the modeling i...

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Abstract

The invention discloses a control simulation method for a near-space hypersonic aircraft. The method comprises the following steps of: (1) establishing a motion model of the aircraft under the condition of a variable wind field; (2) establishing a motor power model of the near-space hypersonic aircraft; (3) establishing a pneumatic parameter base and an engine parameter base related with the motion model and the power model; (4) designing an attitude steady tracking control law and a centre-of-gravity motion control law on the basis of the motion model according to different task requirements; and (5) calculating atmosphere data and wind field data in the current state in real time, calculating all states of the aircraft according to the atmosphere data and wind field data and the designed control law, and repeating the steps until the simulation is finished. In the method, a whole set of the motion model of the near-space hypersonic aircraft under the condition of the variable wind field is provided on the basis of fully analyzing dynamic and kinematic laws of the near-space hypersonic aircraft and by combining the actual conditions of the motor power model and the atmospheric wind field environment. The invention also discloses an aircraft-based control simulation platform.

Description

technical field [0001] The invention relates to a modeling and control simulation problem in the field of aerospace, in particular, it is a motion modeling and control simulation method for aircraft, which can be applied to the flight stability analysis and automatic control scheme design of hypersonic aircraft in near space . Background technique [0002] Due to the particularity of the near-space environment and hypersonic flight, the stable intelligent autonomous adaptive control of the near-space hypersonic vehicle faces some important technical problems, such as the precise mathematical description of the near-space environment, the aerodynamic layout design and motion of the hypersonic vehicle. Modeling, experimental and calculation acquisition of aerodynamic parameter database, thrust model and thrust scheme design of the engine used, and design of flight control system simulation platform closely related to the research, etc. [0003] At present, the following fou...

Claims

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Application Information

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IPC IPC(8): G06F17/50B64G7/00
Inventor 程路都延丽姜长生薛雅丽蒲明傅健文杰
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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