CN110929392A - Flight technology judging system - Google Patents
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- CN110929392A CN110929392A CN201911089419.8A CN201911089419A CN110929392A CN 110929392 A CN110929392 A CN 110929392A CN 201911089419 A CN201911089419 A CN 201911089419A CN 110929392 A CN110929392 A CN 110929392A
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Abstract
The invention discloses a flight technology evaluation system, which adopts the technical scheme that various data of a pilot in the process of simulating flight are recorded in real time through a computer simulation system, a new model is formed after the various data are connected and compared with an existing model, and evaluation is carried out through comprehensive evaluation. The invention has the advantages that the height and speed difference of each time period can be directly calculated by a computer, and the comprehensive scoring is carried out by the performance in each time period, so that a driver in the simulation cabin can visually find out the problem through a model to correct errors.
Description
The technical field is as follows:
the invention belongs to the technical field of flight technology evaluation, and relates to a flight technology evaluation system.
Background art:
the flight simulator refers to an aircraft flight simulator used for flight training of a driver. At present, China's civil aviation does not have such equipment, all of which are directly operated on the aircraft after theoretical learning, and the cost is extremely high.
The flight simulator developed and produced by our company becomes indispensable important training equipment for guaranteeing flight safety, greatly improving skills of flight personnel and flight crew, shortening training period of the flight personnel, reducing training cost and improving training efficiency.
However, driving training in the simulation cabin cannot intuitively evaluate training participants, so an evaluation system is needed to evaluate the training participants.
Disclosure of Invention
The invention aims to provide a flight technology evaluation system, which enables the driving training in a simulation cabin to have visual evaluation results.
In order to achieve the purpose, the technical scheme provided by the invention is as follows:
1) establishing a coordinate system in a computer; the coordinate systems are a speed and time coordinate system and a height and time coordinate system, wherein the speed is taken as a vertical axis, the time is taken as a horizontal axis, the height is taken as a vertical axis, and the time is taken as a horizontal axis;
2) inputting a height data model and a speed data model in the coordinate system of the step 1); the height data model is a graph formed by connecting the maximum values and the minimum values at a plurality of time points; the speed data model is a graph formed by connecting limit maximum values and limit minimum values at a plurality of time points;
3) acquiring instant data, wherein the instant data are the speed and the altitude of a simulated aircraft recorded by a simulated flight system in a simulated cabin on a plurality of time nodes, and the instant data form a data table consisting of the time nodes and the speed and a data table consisting of the time nodes and the altitude;
4) respectively importing a speed and time coordinate system and an altitude and time coordinate system into a time node and speed number table and a time node and altitude number table generated by instant data;
5) importing the data table of the time nodes and the speed in the step 4) into a speed and time coordinate system, and connecting points formed by the time nodes and the speed into corresponding curves to form an actual speed data model; importing the table of time nodes and heights in the step 4) into a height and time coordinate system, and connecting points formed by a plurality of time nodes and heights into corresponding curves to form an actual height data model;
6) calculating the difference value between the height data model and the actual height data model, and calculating the difference value between the speed data model and the actual speed data model;
7) and comprehensively evaluating the comprehensive height difference value and the speed difference value and giving corresponding scores.
The invention has the following effects: the height and speed difference of each time period can be directly calculated through a computer, comprehensive scoring is carried out through the performance in each time period, and a driver in the simulation cabin can visually find out the problem through a model so as to correct errors.
Drawings
FIG. 1 is a general calculation formula;
FIG. 2 is a graph of instantaneous data values lower than model values;
FIG. 3 shows that the instant data curve value is higher than the model curve value.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
After a student logs in a simulation cabin, the student carries out identity recognition on the simulation cabin, judges whether a simulation cabin height simulator and a speed simulator are communicated or not, and 1) establishes a new blank height coordinate system and a new blank speed coordinate system at the same time; the coordinate systems are a speed and time coordinate system and a height and time coordinate system, wherein the speed is taken as a vertical axis, the time is taken as a horizontal axis, the height is taken as a vertical axis, and the time is taken as a horizontal axis;
2) judging the selected model, and inputting a height data model and a speed data model in the blank coordinate system in the step 1); the height data model is a graph formed by connecting the maximum values and the minimum values at a plurality of time points; the speed data model is a graph formed by connecting limit maximum values and limit minimum values at a plurality of time points;
the altitude data model and the speed data model are actual data acquired by a mature pilot in the actual flight process, namely the time and the sliding speed of the aircraft from a static state to a lift state capable of taking off, the aircraft nose elevation angle and the aircraft nose speed in a lift-off state, the time and the aircraft nose speed in a standard flight altitude, the aircraft nose inclination angle and the aircraft nose speed in a descent state, the aircraft speed in a landing state, and the altitude and speed model recorded by the time nodes are used as a reference model.
3) Acquiring instant data, and after judging that the simulation cabin height simulator and the speed simulator are on line simultaneously, simulating a pilot in a cabin to start flying the airplane and finish the flight of one flight line, namely taking off and landing; recording the speed and the altitude of the simulated aircraft on a plurality of time nodes by the simulated cabin altitude simulator and the speed simulator, and forming a data table consisting of the time nodes and the speed and a data table consisting of the time nodes and the altitude by instant data;
4) respectively importing a speed and time coordinate system and an altitude and time coordinate system into a time node and speed number table and a time node and altitude number table generated by instant data;
5) importing the data table of the time nodes and the speed in the step 4) into a speed and time coordinate system, and connecting points formed by the time nodes and the speed into corresponding curves to form an actual speed data model; importing the table of time nodes and heights in the step 4) into a height and time coordinate system, and connecting points formed by a plurality of time nodes and heights into corresponding curves to form an actual height data model;
6) calculating the difference value between the height data model and the actual height data model, and calculating the difference value between the speed data model and the actual speed data model;
7) dividing the time and the sliding speed of the aircraft from a static state to a lift state capable of taking off, the aircraft nose elevation angle and the aircraft nose speed when the aircraft ascends from the ground, the time and the aircraft nose speed when the aircraft reaches a standard flying height, the aircraft nose inclination angle and the aircraft nose speed when the aircraft descends, and the area of the aircraft speed when the aircraft lands on a time axis, and respectively calculating a height difference value and a speed difference value, wherein the difference values are determined by a formula 1: shown in FIG. 1, wherein S’ 1For highly simulating data model area, S "1For the velocity simulation data model area, SHeightFor the real-time height data model area, SSpeed of rotationFor the area of the instantaneous velocity data model, X1For height correction of parameters, X2For the speed correction parameter, when the region division is performed, if the instant data curve value is lower than the model curve value, equation 2 is used, as shown in fig. 2, and if the instant data curve value is higher than the model curve value, equation 3 is used, as shown in fig. 3, by performing the comprehensive evaluation and giving the corresponding score.
The comprehensive evaluation is that the curve numerical value fluctuation is uncontrollable, the corresponding accurate area of the graph is difficult to calculate, a weighing method is adopted for estimating the value, paper or metal sheets with uniform texture are adopted as cut objects, the cut objects are placed in a cutting machine or a laser cutting machine, the graph obtained by difference calculation is cut and cut, the weighing is carried out immediately, and the obtained weight is calculated and corrected according to the height and speed correction parameters respectively to obtain the accurate value. The height correction parameter is 0.11 and the velocity correction parameter is 0.37, taking the boeing 737 as an example.
The illustrative embodiments of the present invention are not intended to limit the scope of the present invention. Any equivalent changes and modifications that can be made by one skilled in the art without departing from the spirit and principles of the invention should fall within the protection scope of the invention.
Claims (3)
1. A flight technical judgment system is characterized by comprising the following steps:
1) establishing a coordinate system in a computer; the coordinate systems are a speed and time coordinate system and a height and time coordinate system, wherein the speed is taken as a vertical axis, the time is taken as a horizontal axis, the height is taken as a vertical axis, and the time is taken as a horizontal axis;
2) inputting a height data model and a speed data model in the coordinate system of the step 1); the height data model is a graph formed by connecting the maximum values and the minimum values at a plurality of time points; the speed data model is a graph formed by connecting limit maximum values and limit minimum values at a plurality of time points;
3) acquiring instant data, wherein the instant data are the speed and the altitude of a simulated aircraft recorded by a simulated flight system in a simulated cabin on a plurality of time nodes, and the instant data form a data table consisting of the time nodes and the speed and a data table consisting of the time nodes and the altitude;
4) respectively importing a speed and time coordinate system and an altitude and time coordinate system into a time node and speed number table and a time node and altitude number table generated by instant data;
5) importing the data table of the time nodes and the speed in the step 4) into a speed and time coordinate system, and connecting points formed by the time nodes and the speed into corresponding curves to form an actual speed data model; importing the table of time nodes and heights in the step 4) into a height and time coordinate system, and connecting points formed by a plurality of time nodes and heights into corresponding curves to form an actual height data model;
6) calculating the difference value between the height data model and the actual height data model, and calculating the difference value between the speed data model and the actual speed data model;
7) and comprehensively evaluating the comprehensive height difference value and the speed difference value and giving corresponding scores.
2. A flight technique assessment system according to claim 1, wherein: and 6) respectively determining the height data difference value and the speed data difference value as the area difference between the height data model and the actual height data model and the area difference between the speed data model and the actual speed data model.
3. A flight technique assessment system according to claim 2, wherein: the area difference between the height data model and the actual height data model, and the area difference between the speed data model and the actual speed data model are the area difference in a unit time period.
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| CN201911089419.8A CN110929392A (en) | 2019-11-08 | 2019-11-08 | Flight technology judging system |
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| CN201911089419.8A CN110929392A (en) | 2019-11-08 | 2019-11-08 | Flight technology judging system |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202221566U (en) * | 2011-07-08 | 2012-05-16 | 中国民航科学技术研究院 | Flight programming system and verification platform of performance-based navigation |
| US20140120500A1 (en) * | 2012-10-31 | 2014-05-01 | Honeywell International Inc. | Integrated flight training and evaluation systems and methods for handheld and portable navigation devices |
| CN206991121U (en) * | 2017-04-28 | 2018-02-09 | 四川翼飞腾科技有限公司 | A kind of attitude of flight vehicle sensory perceptual system |
| CN109064019A (en) * | 2018-08-01 | 2018-12-21 | 中国民航大学 | A kind of system and method tested and assessed automatically for controller's simulated training effect |
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2019
- 2019-11-08 CN CN201911089419.8A patent/CN110929392A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202221566U (en) * | 2011-07-08 | 2012-05-16 | 中国民航科学技术研究院 | Flight programming system and verification platform of performance-based navigation |
| US20140120500A1 (en) * | 2012-10-31 | 2014-05-01 | Honeywell International Inc. | Integrated flight training and evaluation systems and methods for handheld and portable navigation devices |
| CN206991121U (en) * | 2017-04-28 | 2018-02-09 | 四川翼飞腾科技有限公司 | A kind of attitude of flight vehicle sensory perceptual system |
| CN109064019A (en) * | 2018-08-01 | 2018-12-21 | 中国民航大学 | A kind of system and method tested and assessed automatically for controller's simulated training effect |
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