Dynamic rapid prediction method for fuel oil temperature in aircraft fuel tank under flight envelope
A technology for aircraft fuel tanks and flight envelopes, applied in computer-aided design, special data processing applications, instruments, etc., can solve problems such as irregularity, reduced simulation efficiency, and consumption, and achieve the effect of saving calculation and improving efficiency
Pending Publication Date: 2022-03-01
BEIHANG UNIV
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Problems solved by technology
However, there are various forms and locations of aircraft fuel tanks, and their design is not regular due to the great differences of different aircraft models; Calculation results are not portable
The grid generation and calculation process of CFD consumes a lot of time and computing resources, and its process is repeated, which greatly reduces the simulation efficiency
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Embodiment 1
[0147] The following takes the No. 3 fuel tank (fuel supply tank) of a single-engine stealth multipurpose fighter as an example to illustrate the specific steps of predicting the dynamic change of fuel temperature in the fuel tank. The input parameters are from the flight profile, and the output parameters are the average fuel temperature in the fuel tank. Based on the CFD calculation results of the fuel flow in the fuel tank, a proxy model was established to predict the average convective heat transfer coefficient of the wall. The fuel temperature is obtained by the average convective heat transfer coefficient, the fuel temperature dynamic fast prediction control equation and the numerical method.
[0148] A total of 7 fuel tanks are loaded on the stealth fighter, which are distributed in the fuselage, wings and vertical tail of the aircraft. The fuel tanks are symmetrically distributed along the central axis of the aircraft, as shown in Figure 4 shown. In this fighter, onl...
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The invention discloses a dynamic rapid prediction method for fuel oil temperature in an aircraft fuel tank under a flight envelope, and relates to the field of fuel oil thermal management of aircraft platforms and propulsion systems. The method comprises the steps that output values of sample points are obtained through CFD simulation calculation, sensitivity analysis is conducted through a variance analysis method, and finally the sensitivity degree of input parameters to output parameters is judged according to the analysis result of the sensitivity method. Sampling in an input parameter range by adopting Latin hypercube test design, establishing a sample point database based on a CFD simulation calculation result, and then establishing an agent model and verifying the precision of the agent model; and finally, predicting the temperature of the fuel in the fuel tank of the aircraft under the typical flight mission profile in real time by adopting a fuel temperature dynamic prediction control equation and a numerical calculation method. According to the method, the obtained fuel temperature change result is in good accordance with engineering experience, the calculation amount in the simulation process is saved, and the efficiency is greatly improved.
Description
technical field [0001] The invention relates to the research on flow heat transfer inside the fuel tank of fighter jets and the calculation of fuel temperature in the field of fuel thermal management of aircraft platforms and propulsion systems, in particular to a dynamic and rapid prediction method for the temperature of fuel in the aircraft fuel tank under the flight envelope. Background technique [0002] With the continuous improvement of the requirements for aircraft combat performance in the modern military field, it is urgently required that the performance of fighter jets develop in the direction of high speed, high stealth, and high intelligence. The improvement of the combat performance of the aircraft will inevitably lead to a substantial increase in the thermal load of the aircraft. For example, investing more high-power electronic equipment to support advanced system tasks will generate more heat, and the use of directed energy weapons and radar will bring great ...
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IPC IPC(8): G06F30/28G06F30/15G06F111/10G06F113/08G06F119/14
CPCG06F30/28G06F30/15G06F2111/10G06F2113/08G06F2119/14Y02T90/00
Inventor 郭京辉林贵平刘勇
Owner BEIHANG UNIV