CN112380792A - Method for evaluating airworthiness conformity of flight performance of amphibious aircraft - Google Patents
Method for evaluating airworthiness conformity of flight performance of amphibious aircraft Download PDFInfo
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Abstract
The invention provides an assessment method for airworthiness conformity of flight performance of an amphibious aircraft, which comprises the following steps: according to a design scheme of the amphibious aircraft, first data are acquired, and the first data comprise: hydrodynamic lift and hydrodynamic resistance data, aerodynamic lift and aerodynamic resistance data, engine tension characteristics, engine oil consumption characteristics and weight characteristic data under different throttle, height, speed and temperature conditions of the airplane; obtaining a calculation result according to the first data, an external force mathematical model of the amphibious aircraft and a plane two-degree-of-freedom translational motion equation set, wherein the calculation result comprises operation parameters of the aircraft under operation state value combinations specified by different airworthiness terms; and comparing the operating parameters under the airworthiness clauses with the requirements of the corresponding airworthiness clauses on the operating parameters of the airplane to obtain a conclusion of airworthiness conformity of the flight performance.
Description
Technical Field
The invention belongs to the technical field of airplane airworthiness verification, and particularly relates to an assessment method for airworthiness conformity of flight performance of an amphibious airplane.
Background
The airworthiness of the flight performance of a conventional aircraft is to determine flight parameter values which ensure flight safety and have good economic benefits, such as ground take-off and landing speed, maximum allowable take-off weight and landing weight, maximum fuel-saving or lowest-cost climb, cruise, descent speed and cruise altitude, and to provide flight time and fuel consumption of each flight phase for making a flight plan.
The amphibious aircraft is a novel aircraft which can realize water surface take-off and landing by utilizing a hull of the lower half part of the aircraft body and can also finish ground take-off and landing at a land airport by utilizing a landing gear, and has wide application scenes and great research significance. However, when the amphibious aircraft is used for airworthiness conformance research, the existing flight mechanics model aiming at the conventional land-based aircraft cannot be directly adopted.
Therefore, the prior art lacks a method for evaluating the seaworthiness of the water surface performance of the amphibious aircraft.
Disclosure of Invention
The purpose of the invention is as follows: the method for evaluating the airworthiness conformity of the flight performance of the amphibious aircraft can calculate and evaluate the conformity of relevant airworthiness terms of the aircraft in the water surface operation process, is integrated with airworthiness conformity conclusion obtained by a conventional evaluation method of land and air performance terms, identifies parts which do not meet the airworthiness requirement in a design scheme in advance, and solves the problem of the compatibility of the aerodynamic and hydrodynamic design schemes of the amphibious aircraft.
The invention provides an assessment method for airworthiness conformity of flight performance of an amphibious aircraft, which comprises the following steps:
according to a design of an amphibious aircraft, first data is acquired, the first data comprising: the method comprises the following steps of (1) data of hydrodynamic lift and hydrodynamic resistance of an airplane, data of aerodynamic lift and aerodynamic resistance under different flaps, engine tension characteristics, engine oil consumption characteristics and weight characteristics under different throttles, heights, speeds and temperatures;
obtaining a calculation result according to the first data, an external force mathematical model of the amphibious aircraft and a translational motion equation set of the aircraft with two degrees of freedom, wherein the calculation result comprises operation parameters of the aircraft under operation state value combinations specified by different airworthiness terms;
and comparing the operating parameters under the airworthiness terms with the requirements of the airworthiness terms on the operating parameters of the airplane to obtain a conclusion of airworthiness conformity of the flight performance.
Optionally, the external force mathematical model of the amphibious aircraft comprises:
the model comprises a hydrodynamic mathematical model, an aerodynamic mathematical model, an engine tension mathematical model and a gravity mathematical model of the amphibious aircraft.
Optionally, the operating parameters of the aircraft include: the speed, the angle of attack, the track angle, the attitude angle, the climbing or descending gradient, the distance and time of movement, and the fuel consumption of the aircraft flight.
Optionally, the operating state specified by the airworthiness clause includes: weight center of gravity, height, speed, configuration, water surface acceleration stop distance, water surface water-leaving speed, water surface take-off distance, water receiving speed, water surface landing distance, water drawing distance, water interruption drawing distance and water drawing speed.
Optionally, the method further includes:
when the operation parameters under a certain airworthiness term do not meet the requirements of the airworthiness term on the operation parameters of the airplane, correcting the airplane design parameters related to the airworthiness term to obtain a corrected amphibious airplane design scheme;
and evaluating the airworthiness conformity of the flight performance of the airplane again according to the corrected design scheme.
Optionally, the hydrodynamic mathematical model of the amphibious aircraft is as follows: and the mapping relation between the design parameters of the aircraft hull, the weight gravity center inertia moment data and the hydrodynamic lift force and hydrodynamic resistance of the hull.
Optionally, the calculation result includes: a numerical matrix, a curve picture, the method further comprising;
and storing the calculation result in the form of the numerical matrix in an excel document mode, and storing the calculation result in the form of the curve picture in a word document mode.
Optionally, the file names of the stored excel document and word document include airworthiness regulation clause number and operation state value combination information corresponding to the calculation result.
The invention has the advantages that: the invention systematizes, integrates and specializes the flight performance evaluation work of the amphibious aircraft on the water surface, the ground and the air, and avoids the uniformity problem caused by different methods and versions in model research and development work; meanwhile, the rapid evaluation method for the airworthiness conformity of the flight performance of the amphibious aircraft is adopted, so that the design iteration efficiency is further improved.
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FIG. 1 is a schematic diagram of a method for evaluating airworthiness of flight performance of an amphibious aircraft according to an embodiment of the invention;
fig. 2 shows the input state variables and the output hydrodynamic components of the hydrodynamic force of the amphibious aircraft according to an embodiment of the present invention;
FIG. 3 is a flow chart of an application of an embodiment of the present invention in an aircraft design iteration process.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention.
In the drawings, the described embodiments are illustrative of some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
Exemplary, seaworthiness requirements such as "minimum water draw speed" for certain amphibious aircraft water surface performance specific conditions: "the minimum water drawing speed of surface sliding must be satisfied, when the critical engine is suddenly stopped, the climbing gradient of the amphibious aircraft must be larger than zero, and the amphibious aircraft can safely leave the water and can not sink into the water".
In a design scheme of a certain amphibious aircraft, the flap angle of the water surface water drawing configuration is 17 degrees, and the water drawing bucket entersThe cross-sectional area of the port was 0.05m2. Meanwhile, in order to ensure that the amphibious aircraft draws the water tank in 20s, the speed corresponding to the lowest pressure requirement at the inlet of the water drawing bucket is not less than 130 km/h. The preliminarily determined minimum water drawing speed is 130 km/h.
As shown in fig. 1, by using the performance airworthiness conformity assessment method provided by the invention, an external force mathematical model and an aircraft two-degree-of-freedom translational motion equation set corresponding to the amphibious aircraft are obtained, a calculation result is obtained, and an operation parameter of the aircraft under an operation state value combination specified by different airworthiness terms is obtained.
The hydrodynamic mathematical model comprises: hydrodynamic lift and hydrodynamic drag.
The method for establishing the hydrodynamic lift force and the hydrodynamic resistance is to obtain hydrodynamic force applied to the amphibious aircraft in the process of off-step water separation (or off-step water collection) of low-speed sliding and high-speed sliding on the water surface by calculating the computational fluid mechanics numerical value of the amphibious aircraft or identifying the parameters of water surface sliding test data according to the steady state of the aircraft at different sliding speeds, draught depths and trim angles as shown in figure 2; the hydrodynamic force comprises hydrodynamic lift force and hydrodynamic drag force of a specific configuration of the airplane in the steady state. The aircraft specific configuration comprises: the structure of the smooth hull of the airplane and the structure of the hull of the airplane with the water drawing bucket put down.
The different coasting speeds include a maximum coasting speed Vmax(the leaving speed or receiving speed is larger) 0.8Vmax、0.65Vmax、0.5Vmax、0.38Vmax、0.25Vmax、0.1Vmax. Within the above speed range, the hydrodynamic drag of the aircraft will exhibit an obvious "bump" at a specific speed point, that is, a maximum point of the hydrodynamic drag along with the change of the airspeed, and the speed point corresponding to the maximum point of the hydrodynamic drag is called as a peak drag speed Vhump. Peak velocity of resistance VhumpTypically at 0.25Vmax～0.5VmaxThe method is characterized in that important characteristic points of hydrodynamic force are selected, and the selected sliding speed point is at the peak resistance speed V according to the actual situationhumpThe vicinity is properly encrypted.
By adopting the flight quality airworthiness conformity evaluation method provided by the invention, the critical engine is suddenly stopped when the amphibious aircraft is in a state of airworthiness requirement of 'minimum water drawing speed' under a special condition of water surface performance, and the climbing gradient of the amphibious aircraft can be ensured to be larger than zero only when the water drawing speed is increased to be more than 142km/h from 130 km/h. Therefore, the 'minimum water drawing speed' required by the special condition of the water surface performance of the amphibious aircraft is 142 km/h. When the amphibious aircraft is in failure and the critical engine is suddenly stopped at the minimum water drawing speed of 142km/h, although the total thrust of the aircraft is reduced, the climbing gradient can still be ensured to be larger than zero, so that the aircraft safely climbs out of water without sinking into the water, and the disaster accident that the aircraft collides with an obstacle is prevented from being influenced by factors such as the area, the length and the interferent of a water drawing water surface field.
The other optimization scheme is as follows: in order to keep the minimum water drawing speed of the airplane at 130km/h and ensure that the climbing gradient of the amphibious airplane is larger than zero, the shape parameters and the flap skewness of the water drawing bucket can be comprehensively corrected, the hydrodynamic resistance of the water drawing bucket is reduced, iterative calculation analysis is carried out after the parameter influence is carried out according to the method shown in figure 3, and when the cross section area of the inlet of the water drawing bucket is reduced to 0.045m2And when the flap deviation degree is 25 degrees, the minimum water drawing speed required by the special condition for the water surface performance of the amphibious aircraft is 130km/h, and the climbing gradient of the critical engine when the engine is stopped is larger than zero.
Finally, it should be pointed out that: the above examples are only for illustrating the technical solutions of the present invention, and are not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (8)
1. An assessment method for airworthiness of flight performance of an amphibious aircraft is characterized by comprising the following steps:
according to a design of an amphibious aircraft, first data is acquired, the first data comprising: the method comprises the following steps of (1) data of hydrodynamic lift and hydrodynamic resistance of an airplane, data of aerodynamic lift and aerodynamic resistance under different flaps, engine tension characteristics, engine oil consumption characteristics and weight characteristics under different throttles, heights, speeds and temperatures;
obtaining a calculation result according to the first data, an external force mathematical model of the amphibious aircraft and a translational motion equation set of the aircraft with two degrees of freedom, wherein the calculation result comprises operation parameters of the aircraft under operation state value combinations specified by different airworthiness terms;
and comparing the operating parameters under the airworthiness terms with the requirements of the airworthiness terms on the operating parameters of the airplane to obtain a conclusion of airworthiness conformity of the flight performance.
2. The method according to claim 1, wherein the mathematical model of external forces of an amphibious aircraft comprises:
the model comprises a hydrodynamic mathematical model, an aerodynamic mathematical model, an engine tension mathematical model and a gravity mathematical model of the amphibious aircraft.
3. The method of claim 1, wherein the operating parameters of the aircraft comprise: the speed, the angle of attack, the track angle, the attitude angle, the climbing or descending gradient, the distance and time of movement, and the fuel consumption of the aircraft flight.
4. The method of claim 1, wherein the operational status specified by the airworthiness clause comprises: weight center of gravity, height, speed, configuration, water surface acceleration stop distance, water surface water-leaving speed, water surface take-off distance, water receiving speed, water surface landing distance, water drawing distance, water interruption drawing distance and water drawing speed.
5. The method of claim 1, further comprising:
when the operation parameters under a certain airworthiness term do not meet the requirements of the airworthiness term on the operation parameters of the airplane, correcting the airplane design parameters related to the airworthiness term to obtain a corrected amphibious airplane design scheme;
and evaluating the airworthiness conformity of the flight performance of the airplane again according to the corrected design scheme.
6. The method according to claim 2, wherein the hydrodynamic mathematical model of the amphibious aircraft is: and the mapping relation between the design parameters of the aircraft hull, the weight gravity center inertia moment data and the hydrodynamic lift force and hydrodynamic resistance of the hull.
7. The method of claim 1, wherein the computed result comprises: a numerical matrix, a curve picture, the method further comprising;
and storing the calculation result in the form of the numerical matrix in an excel document mode, and storing the calculation result in the form of the curve picture in a word document mode.
8. The method according to claim 7, wherein the file names of the stored excel document and word document comprise airworthiness regulation clause numbers corresponding to the calculation results and operation state value combination information.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113856098A (en) * | 2021-10-25 | 2021-12-31 | 中航通飞华南飞机工业有限公司 | Water drawing fire extinguishing system and method for large fire extinguishing amphibious aircraft |
| CN113895645A (en) * | 2021-12-09 | 2022-01-07 | 四川腾盾科技有限公司 | Propeller unmanned aerial vehicle autonomous takeoff obstacle crossing capability analysis method |
| CN114001861A (en) * | 2021-10-25 | 2022-02-01 | 中航通飞华南飞机工业有限公司 | Method for determining front and rear limits of water flying gravity center of water surface aircraft |
| CN114001861B (en) * | 2021-10-25 | 2024-05-24 | 中航通飞华南飞机工业有限公司 | Method for determining front and rear limits of water flight center of gravity of water surface aircraft |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113856098A (en) * | 2021-10-25 | 2021-12-31 | 中航通飞华南飞机工业有限公司 | Water drawing fire extinguishing system and method for large fire extinguishing amphibious aircraft |
| CN114001861A (en) * | 2021-10-25 | 2022-02-01 | 中航通飞华南飞机工业有限公司 | Method for determining front and rear limits of water flying gravity center of water surface aircraft |
| CN114001861B (en) * | 2021-10-25 | 2024-05-24 | 中航通飞华南飞机工业有限公司 | Method for determining front and rear limits of water flight center of gravity of water surface aircraft |
| CN113895645A (en) * | 2021-12-09 | 2022-01-07 | 四川腾盾科技有限公司 | Propeller unmanned aerial vehicle autonomous takeoff obstacle crossing capability analysis method |
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