Method for evaluating the power augmentation effect of an outward blowing type flap layout aircraft

A blown-out, aircraft technology, applied in computer-aided design, instrumentation, geometric CAD, etc., can solve the problem of calculation of take-off and landing performance of power-increased aircraft, optimization of layout and configuration of increase-lift devices, and inability to evaluate the effect of power-increased lift can't wait

Active Publication Date: 2019-04-12
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

[0003] Summary of the invention: Provide a method for evaluating the effect of power-increasing lift of an aircraft with a blown flap layout, to solve the problem that conventional performance calculation methods cannot be applied to power-increasing aircraft Problems such as calculation of degraded performance, inability to evaluate the effect of power increase, and inability to optimize the layout configuration of the increase device

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  • Method for evaluating the power augmentation effect of an outward blowing type flap layout aircraft
  • Method for evaluating the power augmentation effect of an outward blowing type flap layout aircraft
  • Method for evaluating the power augmentation effect of an outward blowing type flap layout aircraft

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Embodiment Construction

[0047] A method for evaluating the power-increasing effect of an aircraft with an externally blown flap layout, comprising the following steps:

[0048] Step 1: Establish the performance calculation model of the power-lift aircraft;

[0049] Step 2: Calculation of performance integral characteristic velocity;

[0050] Step 3: Establish an aerodynamic incremental correction model at a non-reference speed point;

[0051] Step 4: Complete the calculation of the aerodynamic force at the non-reference speed point according to the aerodynamic incremental correction model in step 3;

[0052] Step 5: Complete the calculation of the take-off distance of the aircraft;

[0053] Step 6: According to the calculation result of step 5, evaluate the effect of aircraft power increase.

[0054] The establishment of the performance calculation model of the power-lift aircraft described in step 1 also includes the following steps:

[0055] Step 1.1: Calculate the aircraft ground roll distance L...

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Abstract

The invention discloses a method for evaluating the power augmentation effect of an outward blowing type flap layout aircraft. The method comprises the following steps: 1) establishing a power augmentation aircraft performance calculation model; 2) calculating a performance integral characteristic speed; 3) establishing a non-reference velocity point aerodynamic force increment correction model; 4) completing calculation of non-reference velocity point aerodynamic force according to the aerodynamic force increment correction model in the step 3; 5) calculating the takeoff distance of the aircraft; and 6) according to the calculation result of the step 5), evaluating the aircraft power augmentation effect. The method is suitable for calculation of the take-off and landing performance of thepower augmentation aircraft of the outward blowing type flap layout aircraft, evaluation of the power augmentation effect and optimization of the layout configuration of the augmentation device, andan effective design tool is provided for layout and type selection of the power augmentation aircraft.

Description

technical field [0001] The invention relates to the technical field of aircraft low-speed configuration layout optimization, in particular to a method for evaluating the power increase effect of an aircraft with an externally blown flap layout. Background technique [0002] The power boost technology can effectively shorten the take-off and landing distance of the aircraft, and the blown power boost flap has been successfully applied to the US military C-17 transport aircraft. The evaluation method of power-lift effect is one of the key technologies in the design of power-lift aircraft. The aerodynamic coefficient of the power-lift aircraft is different from the conventional layout aircraft. The aerodynamic coefficient is significantly affected by the speed and the working state of the engine. The conventional performance calculation method cannot be applied to the take-off and landing performance calculation. Therefore, the evaluation of the power-lift effect cannot be carr...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F2119/06G06F30/20Y02T90/00
Inventor 张声伟
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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