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1、International Standard 1151 I7 0 a 4 4gb INTERNATIONAL ORGANIZATION FOR STANDARDIZATIONWdEX,lYHAPOAHAR OPTAHWBAL z !i! Price based on 6 pages Copyright International Organization for Standardization Provided by IHS under license with ISO Licensee=NASA Technical Standards 1/9972545001 Not for Resale,
2、 04/25/2007 02:10:18 MDTNo reproduction or networking permitted without license from IHS -,-,- IS0 1151, Flight dynamics - Concepts, quantities and symbols, comprises, at present, seven parts : Part 1 : Aircraft motion relative to the air. Part 2 : Motions of the aircraft and the atmosphere relative
3、 to the Earth. Part 3 : Derivatives of forces, moments and their coefficients. Part 4 : Parameters used in the study of aircraft stability and control. Part 5 : Quantities used in measurements. Part 6 : Aircraft geometry. Part 7 : Flight points and flight envelopes. IS0 1151 is intended to introduce
4、 the main concepts, to include the more important terms used in theoretical and experimental studies and, as far as possible, to give cor- responding symbols. In all the parts comprising IS0 1151, the term “aircraft” denotes a vehicle intended for atmosphere or space flight. Usually, it has an essen
5、tially port and starboard symmetry with respect to a plane. That plane is determined by the geometric characteristics of the aircraft. In that plane, two orthogonal directions are defined: fore-and-aft and dorsal-ventral. The transverse direction, on the perpendicular to that plane, follows. When th
6、ere is more than one plane of symmetry, or when there is none, it is necessary to introduce a reference plane. In the former case, the reference plane is one of the planes of symmetry. In the latter case, the reference plane is arbitrary. In all cases, it is necessary to specify the choice made. Ang
7、les of rotation, angular velocities and moments about any axis are positive clockwise when viewed in the positive direction of that axis. All the axis systems used are three-dimensional, orthogonal and right-handed, which implies that a positive rotation through x/2 around the x-axis brings they-axi
8、s into the position previously occupied by the z-axis. Numbering of sections and clauses With the aim of easing the indication of references from a section or a clause, a decimal numbering system has been adopted such that the first figure is the number of the part of IS0 1151 considered. Copyright
9、International Organization for Standardization Provided by IHS under license with ISO Licensee=NASA Technical Standards 1/9972545001 Not for Resale, 04/25/2007 02:10:18 MDTNo reproduction or networking permitted without license from IHS -,-,- Contents Page . . 7.0 Introduction 7.1 Accomplishment of
10、a mission 7.2 Controls, geometric configuration and condition of systems 7.3 State of the aircraft . 7.4 Environment . 7.5 Flightpoints . 7.6 Effective flight points . 7.7 Flightenvelopes . . . . . . . . . . . . . . . . . . * iv Copyright International Organization for Standardization Provided by IH
11、S under license with ISO Licensee=NASA Technical Standards 1/9972545001 Not for Resale, 04/25/2007 02:10:18 MDTNo reproduction or networking permitted without license from IHS -,-,- INTERNATIONAL STANDARD IS0 1151/7-1995(E) Flight dynamics - Concepts, quantities and symbols - Part 7: Flight points a
12、nd flight envelopes 7.0 Introduction This part of IS0 1151 is intended to define the concepts and terms used in flight dynamics studies to specify aircraft flight conditions and envelopes. It is necessary, for this purpose, to give definitions specifying the terms: mission, controls, geometric confi
13、guration, situation of the systems, state of the aircraft, environment, etc. These concepts are necessary for safety analyses, for qualification purposes, and they apply to the analysis of operational, experimen- tal or simulated flights, taking into account potential failures and likely environment
14、al conditions. The following International Standards are necessary as reference documents for application of this part of IS0 1151: IS0 2533, Standard atmosphere. IS0 5878, Reference atmospheres for aerospace use. 7.1 Accomplishment of a mission No. 1 Term Definition 7.1.1 Mission The purpose of a f
15、light achieved while respecting some constraints, among others, of time and of space. NOTE - The objective and the constraints can be specified in a flight plan. 7.1.2 Flight programme The preschedule of intermediate objectives required to fulfil the mission (7.1.1) within an authorized flight envel
16、ope (7.7. I). NOTE - Provision can be made in the flight programme for some conditional changes of intermediate objectives according to circumstances arising during the flight (failure, meteorology, traffic, etc. ) 7.1.3 (Flight) phase The portion of the flight characterized by an intermediate objec
17、tive. Examples: take-off, climb, cruise, descent, approach, landing. The intermediate objective is defined with some tolerance as to the accuracy with which the objective is considered to have been achieved, such that the following phase can be initiated under conditions that allow it to be executed
18、. 7.1.4 (Flight) sub-phase The portion of a (flight) phase (7.1.3) characterized by an elementary objective. Examples: “ground run” in the “take-off” phase, “flare” and “ground run” in the “landing” phase. The elementary objective is defined with some tolerance as to the accuracy with which the obje
19、ctive is considered to have been achieved, such that the following sub-phase can be initiated under conditions that allow it to be executed. NOTE - Following the breakdown ,of a phase into sub-phases, certain parameters can often be considered as constants dunng the sub-phase (for example: mass char
20、acteristics of the aircraft, state of the atmosphere, etc.). 1 Copyright International Organization for Standardization Provided by IHS under license with ISO Licensee=NASA Technical Standards 1/9972545001 Not for Resale, 04/25/2007 02:10:18 MDTNo reproduction or networking permitted without license
21、 from IHS -,-,- IS0 1151/7-1985 (E) 7.2 Controls, geometric configuration and condition of systems No. 7.2.1 Controls* Term Definition The set of elements located in the cockpit and operated by the crew to fly the aircraft. 7.2.1.1 Piloting control 7.2.1.2 Selector 7.2.2 (Geometric) configuration Ex
22、amples: stick; throttles; undercarriage and flap selection levers; switches to engage autopilot or dampers; pressurization and air conditioning controls; etc. A control (7.2.1) operated by the pilot, in a continuous or intermittent manner, during a sub-phase (7.1.4) in order to comply with the pilot
23、ing rules (7.5. I) and to achieve the objective of that sub-phase. A control (7.2.1) put into a position by the crew, as laid down in the flight manual, at the beginning of a sub-phase (7.1.4) and which remains in that pos- ition throughout that sub-phase. The set of quantities characterizing the re
24、lative positions of the various com- ponents (6.0.2) of the aircraft, that can be controlled by selectors (7.2.1.2). 7.2.3 Situation of the systems NOTES 1 The list of quantities is restricted to those involved in the problem under consideration. 2 The geometric configuration defined above shall not
25、 be confused with the geometric state (6.1.17) of which it forms only a part. The set of parameters defining the operating behaviour of the aircraft systems concerned with flight dynamics. NOTE - The list of parameters is restricted to those involved in the problem under con- sideration. * The same
26、control can be a piloting control (7.2.1 .l) during one sub-phase (7.1.4) and a selector (7.2.1.2) during another sub-phase. Example: The throttle is a selector during the “take-off” phase and a piloting control during the “approach” phase. 7.3 State of the aircraft For a given type of aircraft, the
27、re exists a technical reference definition that specifies the geometric shape, the nominal mass, the nominal distribution of masses, the influence on the centre of gravity of the aircraft of the quantities of fuel distributed in internal tanks, the systems which can be used (inertial navigation syst
28、em, air data system, artificial stabilization systems, etc.). For each mission, it is necessary to complete the reference definition with a description of the internal and external stores required for the accomplishment of that mission. No. 7.3.1 Term Situation of loads carriage Definition For a giv
29、en mission (7.1.1), the situation of the loads carriage is defined by the list of the different internal or external loads (passengers, freight, containers and pallets, fixed or jettisonable fuel tanks, internally or externally carried stores, etc.), with their positions, that modify the mass, the m
30、ass distribution, and, in certain cases, the geometric form of the aircraft. 1) NOTE - Internal fuel is not included in these loads. For flight refuelling tankers, fuel is considered to be a load. I) For certain missions, the situation of loads carriage (7.3.1) can be modified during a transition su
31、b-phase (for example: by jettisoning stores or dropping parachutists). (See note 1 in 7.3.2.2.) 2 Copyright International Organization for Standardization Provided by IHS under license with ISO Licensee=NASA Technical Standards 1/9972545001 Not for Resale, 04/25/2007 02:10:18 MDTNo reproduction or n
32、etworking permitted without license from IHS -,-,- IS0 1151/7-1985 (E) No. Term 7.3.2 Selected situation Definition During a sub-phase (7.1.41, the selected situation is defined as the list of the set of “positions” of the different selectors (7.2.1.2). For each sub-phase, there is a single selected
33、 situation, defined either in the flight manual for operational flights or in the study programme for experimental flights. The selected situation can be divided into two sub-sets: a selected geometric configuration (7.3.2.1) and a selected situation of the systems (7.3.2.2). NOTE - An order to chan
34、ge the “ position” of a selector may not be associated with a geometric displacement of the selector itself, but may be achieved by appropriate signal- ling. 7.3.2.1 Selected geometric configuration During a sub-phase (7.1.41, the selected geometric configuration is defined by the list of the set of
35、 “positions” of only those selectors (7.2.1.2) concerned with the geometric configuration (7.2.2) of the aircraft. 7.3.2.2 Selected situation of the systems During a sub-phase (7.1.4), the selected situation of the systems is defined by the list of the set of “positions” of only those selectors (7.2
36、.1.2) concerning the systems (7.2.3). NOTES 1 Certain sub-phases, called transition sub-phases, are characterized by the change either in the “ position” of components or in the state of the systems controlled by the change in “ position” of one or of several selectors. The duration of the transitio
37、n sub- phase is then determined by the time taken to change the position of the components or the state of the system. Example: sub-phase “ undercarriage out” . 7.3.3 Failure situation 2 In certain studies, and in particular during a flight test, it may be useful to study the behaviour of the aircra
38、ft in positions of the components or for system functions that do not usually occur during operational flights. For example, the flight can be studied at low incidence with leading edge slats extended or at high incidence with slats retracted, even though in operational flight the position of the sl
39、ats can be automatically fixed by the incidence and the speed. To describe those particular selected situations (7.3.21, it is necessary to indicate that the automatic system has been made inoperative by a selector activated specifically for that purpose During a sub-phase (7.1.41, the failure situa
40、tion is defined by the list of the set of abnormal positions of components (6.0.2) and of the set of abnormal functions of the systems. NOTES 1 The failure of a system, the operation of which is not involved in a sub-phase, shall be taken into consideration in defining the failure situation, because
41、 it can modify the probability of failures in that sub-phase or in other sub-phases. 2 In line with the definition above, the non-operation of one of the lines of a redundant system shall be considered as a failure, even if the other lines maintain the function of the system. In those conditions, th
42、e failure situation is said to be a “ partial failure situation” 3 In the case of a flight or simulator test, or of a training flight, a failure may be provoked or simulated. 7.3.4 Real situation During a sub-phase (7.1.41, the real situation is the result of the selected situa- tion (7.3.2) and of
43、the failure situation (7.3.3). The real situation may be broken down into two sub-sets: real geometric con- figuration (7.3.4.1) and real situation of the systems (7.3.4.2). I 3 Copyright International Organization for Standardization Provided by IHS under license with ISO Licensee=NASA Technical St
44、andards 1/9972545001 Not for Resale, 04/25/2007 02:10:18 MDTNo reproduction or networking permitted without license from IHS -,-,- IS0 1151/7-1995 (E) Real geometric configuration Real situation of the systems State of the aircraft 7.4 Environment No. 7.4.1 7.4.2 7.4.3 7.4.4 Term Term State of the a
45、tmosphere Model state of the atmosphere Standard state of the atmosphere Reference state of the atmosphere Definition During a sub-phase (7.1.41, the real geometric configuration is the result of the selected geometric configuration (7.3.2. I) and of the failure situation (7.3.3). During a sub-phase
46、 (7.1.4). the real situation of the systems is the result of the selected situation of the systems (7.3.2.2) and of the failure situation (7.3.3). The state of the aircraft, during a sub-phase (7.1.41, is the result of a situation of loads carriage (7.3.1), a real situation (7.3.41, a mass and a mas
47、s distribution of the aircraft. NOTE - In some cases, for calculations, for flight tests or simulated flight tests, it may be useful to define the state of the aircraft independently of the sub-phase. Definition The set of physical parameters characterizing, at a point, the atmosphere con- sidered a
48、s undisturbed by the aircraft and having an influence on the motion of the aircraft and on the behaviour of the crew. Usually, the following parameters and certain gradients, when necessary, are taken into consideration: pressure (5.1. I), temperature (5.1.21, density (5.1.31, humidity, wind speed (
49、2.2.31, intensity and distribution of turbulence, visibility, icing conditions. The point considered is either the actual point at which the aircraft is, or one of the points at which it is likely to be, during its flight. NOTES 1 During a sub-phase (7.1.41, it is often possible to consider that the state of the at- mosphere does not vary. 2 The state of th