CN103192996A - Method for determining drift-down flight path of large airplane - Google Patents

Method for determining drift-down flight path of large airplane Download PDF

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Publication number
CN103192996A
CN103192996A CN2013101462520A CN201310146252A CN103192996A CN 103192996 A CN103192996 A CN 103192996A CN 2013101462520 A CN2013101462520 A CN 2013101462520A CN 201310146252 A CN201310146252 A CN 201310146252A CN 103192996 A CN103192996 A CN 103192996A
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flight
speed
thrust
favourable
drift
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CN2013101462520A
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Chinese (zh)
Inventor
耿汝光
唐长红
任江涛
商立英
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Xian Aircraft Design and Research Institute of AVIC
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Xian Aircraft Design and Research Institute of AVIC
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Priority to CN2013101462520A priority Critical patent/CN103192996A/en
Publication of CN103192996A publication Critical patent/CN103192996A/en
Pending legal-status Critical Current

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Abstract

The invention belongs to the field of design of large aviation aircrafts, relates to test flight of a large airplane and in particular relates to a method for determining a drift-down flight path of a large airplane. The method comprises the following steps: determining the drift-down performance, and performing test flight verification by utilizing the drift-down performance so as to obtain the drift-down flight path. According to the method, due to the mode of determining the favorable drift-down speed to obtain favorable drift-down performance and performing test flight verification, the drift-down flight path of the airplane is obtained. The favorable calculation method for the favorable drift-down speed V is simple, the speed is conveniently acquired, the result is characterized to be a correction speed, the speed is only related to the flight weight of the airplane and is conveniently remembered and used, and the user's manual of the airplane is easily written; and meanwhile, the method has important guiding significance on the test flight verification, the test flight number can be reduced, the test flight period is shortened, and lots of test flight expenditure is saved. The method is comprehensive in consideration and high in universality and is suitable for twin-engine or over-twin-engine turbofan type flying boxcars and air buses.

Description

A kind of large aircraft wafts and falls definite method of flight path
Technical field
The invention belongs to aviation large aircraft design field, relate to large aircraft and take a flight test, be specifically related to a kind of large aircraft and waft and fall definite method of flight path.
Background technology
Require and CCAR-121 portion of Civil Aviation Administration of China (moving qualified official laws) according to world civil aviation organization, in order to guarantee the course line flight safety, the flight of carrying out high height above sea level course line must waft and fall safety inspection, accurately the obstacle clearing capability that flight path both had been conducive to improve aircraft falls in believable wafing, ensure flight safety, the airline operation maximum weight of favourable raising aircraft again increases the economic benefit of airline company.External Performance Flight Test is fallen in wafing of large aircraft do not have clear and definite method, and because blockade on new techniques, the technical materials that can't obtain to be correlated with from disclosed channel.By the patent website inquiry, do not see similar and relevant patent, the domestic present relevant achievement in research that also do not have yet.The method that the present invention proposes has obtained checking in concrete model.
Summary of the invention
The objective of the invention is: provide a kind of large aircraft to waft to fall definite method of flight path, solve at present big aircraft not have the Performance Evaluation means of determining and the verification method of taking a flight test in the process of falling of wafing problem.
Technical scheme of the present invention is: a kind of large aircraft wafts and falls definite method of flight path, and at first determining wafts falls performance, and utilizing then wafts falls the performance checking of taking a flight test, and obtains wafing falling flight path.
Determine to waft and fall the performance particular content and be: by determining thrust-drag margin Δ P, choosing the speed V of thrust-drag margin Δ P when maximum is the favourable reduction of speed degree V that wafts Favourable, aircraft is at V FavourableFollowing flight obtains optimum and wafts and fall performance; Wherein, Δ P=P Available-P Need to use, P AvailableBe thrust available, P Need to useBe thrust required, P Available=nP (V) η,
Figure BDA00003099472900011
C D=f (C L),
Figure BDA00003099472900012
C DBe C LFunction, the drag coefficient C that obtains and consider to cause after the power failure by test DIncrement; Wherein:
The G-aircraft weight;
The S-wing area;
The P-engine thrust;
ρ-atmospheric density;
C L-lift coefficient;
C D-drag coefficient;
N-working engine platform number;
η-driving engine installation coefficient of correction
P Need to use-thrust required;
P Available-thrust available;
V-flying speed.
Take a flight test the checking particular content be: under representative cruising altitude, with flying speed from current favourable cruising speed V CruiseDecelerate to V Favourable, then at V FavourableFly under the speed, flying height reduces gradually in the flight course, reaches balance until flying height, finishes the checking of taking a flight test.
Advantage of the present invention is: the present invention obtains favourable wafing by earlier definite favourable reduction of speed degree that wafts and falls performance, and then the mode of the checking of taking a flight test, and obtains wafing of aircraft and falls track.The favourable reduction of speed degree V that wafts FavourableMethod of calculating simple, be convenient to obtain, the result is characterized by corrected speed, only with aircraft operating weight relation is arranged, and both has been convenient to aviator memory and uses, and is easy to writing of aircraft user manual again.Simultaneously, for the checking of taking a flight test important directive significance is arranged, can save the sortie of taking a flight test, shorten and take a flight test the cycle, save a large amount of funds of taking a flight test.This method is considered comprehensively, and highly versatile is applicable to and twoly sends out and twoly send out turbofan class large transport airplane and airliner above.
Description of drawings
Fig. 1 chooses scheme drawing for the reduction of speed degree that wafts.
The specific embodiment
Below in conjunction with accompanying drawing and example the present invention is done to describe in further detail, see also figure.
A kind of large aircraft wafts and falls definite method of flight path, and at first determining wafts falls performance, and utilizing then wafts falls the performance checking of taking a flight test, and obtains wafing falling flight path.Large aircraft wafts to fall and refers in the process of cruising, and when one (or several) stop, must reduce cruising altitude and cruising speed, is reduced to this transient process of new cruising altitude from original cruising altitude, is called large aircraft and wafts and fall.The process of falling of wafing is fallen by slowing down, wafing and is leveled off three phases and form, when one (driving engine) stops, still the driving engine in work pushes away the thrust that large throttle loses with compensation parking driving engine to rated condition, aircraft reduces speed now, when reaching the reduction of speed that wafts and spend, aircraft begins to waft and falls, till level-off altitude.
Determine to waft and fall the performance particular content and be: by determining thrust-drag margin Δ P, choosing the speed V of thrust-drag margin Δ P when maximum is the favourable reduction of speed degree V that wafts Favourable, aircraft is at V FavourableFollowing flight obtains optimum and wafts and fall performance; Wherein, Δ P=P Available-P Need to use, P wherein AvailableBe thrust available, P Need to useBe thrust required, P Available=nP (V) η, C wherein D=f (C L),
Figure BDA00003099472900032
C DBe C LFunction, do not have concrete algorithm, be the drag coefficient C that obtains and consider to cause after the power failure by test DIncrement and draw between the two relation; Wherein:
The G-aircraft weight;
The S-wing area;
The P-engine thrust;
ρ-atmospheric density;
C L-lift coefficient;
C D-drag coefficient;
N-working engine platform number;
η-driving engine installation coefficient of correction;
P Need to use-thrust required;
P Available-thrust available;
V-flying speed.
Take a flight test the checking particular content be: under representative cruising altitude, with flying speed from current favourable cruising speed V CruiseDecelerate to V Favourable, then at V FavourableFly under the speed, flying height reduces gradually in the flight course, reaches balance until flying height, finishes the checking of taking a flight test.
Representative cruising altitude generally is between 9km～12km, aircraft after reaching and estimating cruising altitude and cruising speed is received critical engine to flight idling, and other driving engines place maximum cruise, keep current flying height, until flying speed from current favourable cruising speed V CruiseDecelerate to V Favourable, keep V FavourableSpeed flight, the cruise ceiling after aircraft reaches single-shot under the current weight and lost efficacy also is that flying height reaches balance, finishes the checking of taking a flight test; Overall process is carried out acquisition and recording to relevant flight parameter.
Embodiment:
Certain aircraft, wing area 300m 2, flying weight 150000kg, place flight atmospheric density 0.332kg/m 3, adorn 4 certain h type engine hs, thrust available P AvailableCalculating sees Table 1, thrust required P Need to useCalculating sees Table 2, and thrust-drag margin sees Table 3.As seen from Table 3, when speed is 480km/h, thrust-drag margin Δ P maximum, for-450kgf, this speed is the favourable reduction of speed degree that wafts.
Table 1 thrust available P AvailableCalculate
Figure BDA00003099472900041
Table 2 thrust required P Need to useCalculate
Figure BDA00003099472900042
Table 3 thrust-drag margin Δ P calculates
Figure BDA00003099472900043

Claims (3)

1. a large aircraft wafts and falls definite method of flight path, it is characterized in that, at first determines to waft to fall performance, and utilizing then wafts falls the performance checking of taking a flight test, and obtains wafing falling flight path.
2. a kind of large aircraft according to claim 1 wafts and falls definite method of flight path, it is characterized in that, determines to waft to fall the performance particular content and be: by determining thrust-drag margin Δ P, choosing the speed V of thrust-drag margin Δ P when maximum is the favourable reduction of speed degree V that wafts Favourable, aircraft is at V FavourableFollowing flight obtains optimum and wafts and fall performance; Wherein, Δ P=P Available-P Need to use, P AvailableBe thrust available, P Need to useBe thrust required, P Available=nP (V) η,
Figure FDA00003099472800011
C D=f (C L),
Figure FDA00003099472800012
C DBe C LFunction, the drag coefficient C that obtains and consider to cause after the power failure by test DIncrement; Wherein:
The G-aircraft weight;
The S-wing area;
The P-engine thrust;
ρ-atmospheric density;
C L-lift coefficient;
C D-drag coefficient;
N-working engine platform number;
η-driving engine installation coefficient of correction
P Need to use-thrust required;
P Available-thrust available;
V-flying speed.
3. waft according to claim 1 or 2 any described a kind of large aircrafts and fall definite method of flight path, it is characterized in that, the particular content of the checking of taking a flight test is: under representative cruising altitude, with flying speed from current favourable cruising speed V CruiseDecelerate to V Favourable, then at V FavourableFly under the speed, flying height reduces gradually in the flight course, reaches balance until flying height, finishes the checking of taking a flight test.
CN2013101462520A 2013-04-24 2013-04-24 Method for determining drift-down flight path of large airplane Pending CN103192996A (en)

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104408243A (en) * 2014-11-19 2015-03-11 中国航空工业集团公司沈阳飞机设计研究所 Method for correcting installation thrust of engine model
CN105628326A (en) * 2014-10-31 2016-06-01 中国飞行试验研究院 Low-risk helicopter rising and landing critical decision point test flight method
CN106529032A (en) * 2016-11-09 2017-03-22 中国商用飞机有限责任公司 Method for determining drift-down failure points

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4538229A (en) * 1983-03-10 1985-08-27 Kavouras, Inc. System for preparing aircraft driftdown plans
CN101476892A (en) * 2008-01-02 2009-07-08 波音公司 Prioritizing alternative landing facilities in flight planning

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4538229A (en) * 1983-03-10 1985-08-27 Kavouras, Inc. System for preparing aircraft driftdown plans
CN101476892A (en) * 2008-01-02 2009-07-08 波音公司 Prioritizing alternative landing facilities in flight planning

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
李旭等: "民用飞机飘降总轨迹计算分析", 《中国民航大学学报》 *
肖艳平等: "高原航线飘降越障要求和算例分析", 《中国民航飞行学院学报》 *

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105628326A (en) * 2014-10-31 2016-06-01 中国飞行试验研究院 Low-risk helicopter rising and landing critical decision point test flight method
CN104408243A (en) * 2014-11-19 2015-03-11 中国航空工业集团公司沈阳飞机设计研究所 Method for correcting installation thrust of engine model
CN104408243B (en) * 2014-11-19 2019-02-12 中国航空工业集团公司沈阳飞机设计研究所 A kind of engine mockup installed thrust modification method
CN106529032A (en) * 2016-11-09 2017-03-22 中国商用飞机有限责任公司 Method for determining drift-down failure points

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Application publication date: 20130710