Method and system for controlling the decelerated approach of an aerodyne
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G05D-001/00
G05D-001/12
출원번호
US-0850134
(1977-11-10)
우선권정보
FR-0342181 (1976-11-12); FR-0030703 (1977-10-12)
발명자
/ 주소
Sicre Jean-Luc (Meudon la Foret FRX) Gruaz Daniel (Le Chesnay FRX)
출원인 / 주소
Societe Francaise d\Equipements pour la Navigation Aerienne (S.F.E.N.A.) (Velizy-Villacoublay FRX 03)
인용정보
피인용 횟수 :
10인용 특허 :
2
초록▼
A method for controlling the decelerated approach of an aerodyne on radio-alignment generally referred to as “glide,”in particular for the purpose of reducing its fuel consumption and reducing the noise, mainly in the final stage of the approach, by approaching the glide at high speed, initiating th
A method for controlling the decelerated approach of an aerodyne on radio-alignment generally referred to as “glide,”in particular for the purpose of reducing its fuel consumption and reducing the noise, mainly in the final stage of the approach, by approaching the glide at high speed, initiating the descent according to the glide angle, also at high speed then beginning a decelerated phase in order to reach a predetermined speed V sel+k, k being generally equal to 10 knots, on reaching a predetermined altitude, hF, and then passing progessively from the speed V sel+k to the speed V sel. From the time when the aerodyne reaches the axis of the glide path, a course is determined in two sections, as regards the variables of speed and altitude, for reaching the point situated at the altitude hF at the given speed V sel+k, namely a first section, at the beginning of which the aerodyne which was previously travelling along the glide, begins a first braking stage, the speed of the aerodyne, during this first section, bein reduced by at least a predetermined speed D1, and a second section, at the beginning of which the aerodyne initiates a second braking stage, the gradient dv/dh along these two sections having to satisfy the relationship P32=k P1 P1 and P2 being the respective gradients on each of the two sections and k being a value determined experimentally.
대표청구항▼
A method of controlling the decelerated approach of an aircraft on glide radioalignment, said aircraft having equipment comprising at least one landing gear which can take the positions gear retracted and gear down, at least one control surface such as a flap which can take at least three positions,
A method of controlling the decelerated approach of an aircraft on glide radioalignment, said aircraft having equipment comprising at least one landing gear which can take the positions gear retracted and gear down, at least one control surface such as a flap which can take at least three positions, flap in final position for landing, flap at one notch from the final position for landing, and flap at two notches from the final position for landing, and a throttle having a slow position, comprising the following steps: (a) approaching the capture of glide at high speed, at which the aircraft equipment is in the positions gear retracted and flap at two notches from the final position for landing; (b) determining, at the capture of the glide, a theoretical trajectory in two stages, AB and BC, in a program of speed/altitude variables, the trajectory having the following characteristics, (i) point C is situated at a predetermined altitude ho and at a speed Vsel+Vo (Vsel being a predetermined speed and Vo a reference speed), (ii) in the first stage AB, the speed of the aircraft is reduced by at least a predetermined speed D1, and (iii) the slope along these two stages satisfies the equation P2=kP1 P1 and P2 being the respective slopes of stages AB and BC, with k being an experimentally determined value; (c) determining an altitude hA which the aircraft is to reach in the first stage; (d) decelerating the aircraft in a first phase including at the start thereof engaging the landing gear in the gear down position and engaging the flap at one notch from the final position for landing; (e) determining the actual trajectory of the aircraft and comparing the actual trajectory with the theoretical trajectory; (f) correcting the power by manipulating the throttle if the total deceleration is too great after a decrease of speed DB where the second stage should begin; (h) decelerating the aircraft in a second phase at the beginning of which the flap is engaged in final position for landing and the throttle is placed in the slow position; (i) correcting the power by manipulating the throttle; and (j) capturing and maintaining Vref, whereby the speed of the aircraft should be less than the speed Vsel+Vo and/or the altitude of the aircraft is reduced below a predetermined altitude.
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이 특허에 인용된 특허 (2)
Boyle James Alfred (Bellevue WA) Galins Peteris Adams (Renton WA) Gregoire Mark Charles (Issaquah WA) O\Toole Peter L. M. (Bellevue WA), Automatic controls for airplane take-off and landing modes.
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Demortier, Jean-Pierre; Lacaze, Isabelle; De Menorval, Jean-Louis, System for aiding the piloting of an aircraft during the approach to a runway with a view to a landing.
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