Configuration method for man-machine interactive airplane mission payload

A configuration method and interactive technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve problems such as the inability to evaluate the range of the center of gravity of the aircraft loading state in real time.

Pending Publication Date: 2015-02-04
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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Problems solved by technology

[0005] The purpose of the present invention is: this technical solution aims to solve the problem that the traditional method cannot comprehensively, ...

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  • Configuration method for man-machine interactive airplane mission payload
  • Configuration method for man-machine interactive airplane mission payload

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Embodiment Construction

[0015] The present invention will be described in further detail below through specific embodiments and in conjunction with the accompanying drawings.

[0016] Using the configuration method of man-machine interactive aircraft task load, the task load configuration and center of gravity evaluation of a certain type of aircraft in a certain loading state are carried out. The specific examples are as follows:

[0017] 1) Task load configuration:

[0018] Task load configuration, including configuring fuel consumption rules and load types. On the task load configuration page ( figure 1 ), set 4 functional areas: respectively:

[0019] A) Fuel consumption rule selection area: Displays the fuel consumption rule available for the current aircraft model;

[0020] B) Payload selection area: display the payload available for the current aircraft model;

[0021] C) Current load configuration area: Display the payload configured by the current aircraft model.

[0022] Mass character...

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Abstract

The invention discloses a configuration method for man-machine interactive airplane mission payload, and belongs to the field of airplane weight engineering. The configuration method comprises the following steps: configuring an oil consumption rule: selecting a corresponding oil consumption rule by aiming at different mission configurations; configuring effective payload: according to mission requirements, assigning an effective payload type for the specific position of the airplane; virtualizing fuel consumption: simulating the change of the weight, the center of gravity and the rotation inertia of the airplane in a fuel consumption process; virtualizing payload consumption: under the state of airplane assigned excess oil, simulating the change situation of the weight, the center of gravity and the rotation inertia during effective payload consumption (such as weapon put/emission). The configuration method has the advantages that the technical scheme can virtualize the payload put/emission on the basis of the center of gravity and the fuel consumption curve of the airplane to precisely calculate the weight, the center of gravity and the rotation inertia of the airplane in real time, and estimate the change range of the center of gravity of the airplane, and therefore, a problem that the change range of the center of gravity of the airplane only can be roughly estimated with a traditional means is solved.

Description

technical field [0001] The invention provides a man-machine interactive aircraft task load configuration method, which belongs to the field of aircraft weight engineering. Background technique [0002] When the aircraft is performing tasks, it will be loaded with different task loads according to actual needs. The state of the aircraft after loading the task load is called the loading state of the aircraft. The same aircraft will produce multiple loading states due to different task loads. In order to calculate the mass characteristic data such as weight, center of gravity, and moment of inertia of the aircraft in the loading state, it is necessary to configure the task load of the aircraft in the loading state, that is, to configure the type and position of the payload and the law of fuel consumption of the aircraft (that is, to control the center of gravity of the aircraft in a safe range , a means to control the weight and position sequence of fuel consumption) It can be...

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Application Information

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IPC IPC(8): G06F19/00
Inventor 潘若刚刘欣李海泉张安坤
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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