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Hypersonic aircraft self-adaptive control method considering attack angle constraints

An adaptive control, hypersonic technology, applied in vehicle position/route/altitude control, non-electric variable control, control/regulation system, etc., can solve the problem of poor transient performance of hypersonic aircraft and insufficient combustion of scramjets And other issues

Inactive Publication Date: 2020-05-15
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The present invention aims to solve the problems of poor transient performance of the hypersonic vehicle and insufficient combustion of the scramjet when the actuator of the existing hypersonic vehicle is often in a fault condition and the angle of attack of the hypersonic vehicle is limited.

Method used

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  • Hypersonic aircraft self-adaptive control method considering attack angle constraints
  • Hypersonic aircraft self-adaptive control method considering attack angle constraints
  • Hypersonic aircraft self-adaptive control method considering attack angle constraints

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specific Embodiment approach 1

[0087] Specific implementation mode one: refer to figure 1 Specifically illustrate the present embodiment, the adaptive control method of the hypersonic vehicle considering the angle of attack constraint described in the present embodiment, the method includes the following steps:

[0088] Step 1, according to the flight state quantity of the hypersonic vehicle, establish the dynamic equation of the hypersonic vehicle;

[0089] Step 2, according to the state quantity in the dynamic equation of the hypersonic vehicle and the set reference value, establish the tracking error system of the hypersonic vehicle;

[0090] Step 3. Control the speed and height in the dynamic equation of the hypersonic vehicle according to the tracking error system of the hypersonic vehicle, the designed fuel equivalence ratio control law, the designed canard deflection angle control law and the designed elevator deflection angle control law, In order to realize the control of hypersonic aircraft.

specific Embodiment approach 2

[0091] Specific embodiment 2: This embodiment is to further explain the adaptive control method of the hypersonic vehicle considering the angle of attack constraint described in the specific embodiment 1. In this embodiment, in step 1, the dynamic equation of the hypersonic vehicle Including velocity V dynamic equation, altitude h dynamic equation, flight path angle γ dynamic equation, hypersonic vehicle attack angle α dynamic equation and pitch rate Q dynamic equation;

[0092] The velocity V kinetic equation is expressed as:

[0093]

[0094] In the formula, is the variation of velocity V, T is thrust aerodynamic force, m is mass, g is gravitational acceleration, D is drag aerodynamic force, is the dynamic pressure, ρ is the air density, S is the reference area, CD is the drag coefficient, δc is the canard deflection angle, δe is the elevator deflection angle, d γ,B is the unparameterized bounded unknown of the canard clearance feature, ζ2 is the failure coefficie...

specific Embodiment approach 3

[0145] Specific embodiment three: This embodiment is to further explain the adaptive control method of the hypersonic aircraft considering the angle of attack constraint described in the second specific embodiment. In this embodiment,

[0146] In step two, the hypersonic vehicle tracking error system includes the velocity tracking error z V , height tracking error z h , Angle of attack tracking error z α , flight track angle tracking error z γ and pitch rate tracking error z Q ;

[0147] speed tracking error z V for:

[0148] z V =V-V ref Formula 6,

[0149] In the formula, V ref a sufficiently smooth reference for velocity;

[0150] height tracking error z h for:

[0151] z h =h-h ref Formula 7,

[0152] where h ref A sufficiently smooth reference representing height,

[0153] flight track angle tracking error z γ for:

[0154] z γ =γ-v γ Formula 8,

[0155] In the formula, v γ A reference input representing the track angle γ;

[0156] Angle of atta...

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Abstract

The invention discloses a hypersonic aircraft self-adaptive control method considering attack angle constraints, and relates to the field of aerospace control. The invention aims to solve the problemsof poor transient performance and insufficient combustion of a scramjet engine of an existing hypersonic aircraft under the conditions that an actuator of the hypersonic aircraft is often in a faultcondition and the attack angle of the hypersonic aircraft is limited. The method comprises: 1, establishing a kinetic equation of the hypersonic aircraft according to the flight state quantity of thehypersonic aircraft; 2, establishing a hypersonic aircraft tracking error system according to the state quantity in the dynamic equation of the hypersonic aircraft and a set reference value; and 3, controlling the speed and the height in the dynamic equation of the hypersonic aircraft according to the hypersonic aircraft tracking error system, the designed fuel equivalence ratio control law, the designed canard deflection angle control law and the designed elevator deflection angle control law so as to control the hypersonic aircraft. The methodis used to control an aircraft.

Description

technical field [0001] The invention relates to a control method of a hypersonic aircraft. It belongs to the field of aerospace control. Background technique [0002] The control of hypersonic vehicles (HFVs) faces great challenges due to complex dynamics, strong couplings, and serious uncertainties. Therefore, the analysis and control techniques of HFV mainly focus on longitudinal flight, and have achieved fruitful results, such as control-oriented modeling, linear time-varying parameter modeling, singular perturbation structure analysis, feedback linearization-based control, based on Observer design for backstepping, sliding mode control, switching control, fuzzy methods, and neutral network control. [0003] Adaptive backstepping is a good choice for engineers due to its superiority in dealing with system nonlinearities and parameter uncertainties. As a result, pioneering adaptive backstepping designs for HFVs have emerged that focus on uncertain aerodynamic parameters...

Claims

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Application Information

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IPC IPC(8): G05D1/10
CPCG05D1/101
Inventor 吴立刚孙光辉刘健行高亚斌王家慧
Owner HARBIN INST OF TECH
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