RU2217353C1

RU2217353C1 - Method of evasion of flying vehicle from guided destruction weapon

Info

Publication number: RU2217353C1
Application number: RU2002124531A
Authority: RU
Inventors: Ю.Я. Алексеев; В.В. Дрогалин; А.И. Канащенков; В.И. Меркулов; Г.А. Пучков; О.Ф. Самарин; В.В. Францев; В.П. Харьков
Original assignee: Открытое акционерное общество "Корпорация "Фазотрон-Научно-исследовательский институт радиостроения"
Priority date: 2002-09-16
Filing date: 2002-09-16
Publication date: 2003-11-27
Also published as: RU2002124531A

Abstract

FIELD: combat flying vehicles. SUBSTANCE: proposed method includes measurement of flight parameters of flying vehicle and guided destruction weapon and calculation of control signal of flying vehicle in such way that range between flying vehicle and guided destruction weapon change in accordance with where law third derivative of its change is present. EFFECT: enhanced safety of flights. 2 dwg

Description

Таблицых Table

Claims

The method of evading the aircraft (LA) from controlled weapons of destruction (USP), which consists in the fact that onboard the aircraft measure the heading angle of the aircraft, the onboard bearing of the USP, the approach speed of the USP and the aircraft, the airspeed of the aircraft, the distance between the aircraft and the USP, angular the rotation speed of the line of sight of the USP in the horizontal plane, the normal overload of the aircraft, the angle of attack of the aircraft, the pitch angle of the aircraft, the roll angle of the aircraft, calculate the control signal of the aircraft in the horizontal plane in accordance with the formulas:

ε = ψ _c -φ _c , (1)

where ψ _c - heading angle of the aircraft;

φ _c - onboard bearing USP;

ε is the angle of sight of the aircraft with USP;

- the speed of convergence of USP and aircraft;

V _c - airspeed of the aircraft;

ψ _p - heading angle USP;

D - the distance between the aircraft and USP;

ω is the angular velocity of rotation of the line of sight of the USP in the horizontal plane;

N ₀ - navigation constant;

g = 9.81 ^m / s ² - acceleration from the free fall of the body;

n _us - normal aircraft overload;

γ _{with the} angle of heel of the aircraft;

α _{with the} angle of attack of the aircraft;

υ _с - pitch angle of the aircraft;

- the rate of change of the aircraft heading angle;

B is the projection of the normal acceleration of the aircraft on the line of sight of the USP; δ is a constant value, the value of which is determined based on the type of aircraft;

- the required range values between the aircraft and the USP, its first, second and third time derivatives and their initial values, respectively, which are determined from the condition for matching the required and actual flight path of the aircraft at the initial moment of evasion, i.e. at t = 0; t is the current time;

λ ₀ , λ ₁ - constant coefficients, the values of which are determined from the conditions for ensuring sustainable elimination of control errors of a particular type of aircraft;

kΔ is the scale factor;

Δ _g is the control signal of the aircraft, the control signal of the aircraft Δ _g is supplied to its automatic control system and the aircraft is controlled in accordance with its value.