CN108009361A - A kind of helicopter existence hydraulic design method - Google Patents
A kind of helicopter existence hydraulic design method Download PDFInfo
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- CN108009361A CN108009361A CN201711256534.0A CN201711256534A CN108009361A CN 108009361 A CN108009361 A CN 108009361A CN 201711256534 A CN201711256534 A CN 201711256534A CN 108009361 A CN108009361 A CN 108009361A
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Abstract
The present invention provides a kind of helicopter existence hydraulic design method, belong to technology of helicopter design field, it includes step 1：Viability project directory is established according to helicopter viability feature；Step 2：Counted according to available data, establish the mapping relations of viability project directory and chief threat project, and viability design grade standard is formulated to the anti-shot ability of chief threat according to viability project, and In Grade carries out Quantitative marking；Step 3：Scoring is weighted and establishes the comprehensive quantitative model of viability, while establishes Cost Model caused by viability；Step 4：Improved according to viability comprehensive quantification scores or evaluated for viability designs.The key point of the present invention is to have quantified the validity of each helicopter viability design object according to statistics, Integrated Evaluation Model is formd using weigthed sums approach again, it according to assessment result, can suggest improvements to great viability design defect, instruct helicopter viability to design.
Description
Technical Field
The invention belongs to the field of helicopter viability design, and particularly relates to a helicopter viability design method.
Background
Helicopter operational viability refers to the ability of an operational helicopter to avoid or withstand an artificially hostile environment, and includes three components: firstly, sensitivity; secondly, vulnerability; and thirdly, rush repair in wartime. Statistical data indicate that viability is increased by 1% and combat effectiveness is increased by 26%. In order to ensure the safety and the wartime output rate of the pilot, the attack helicopter needs to comprehensively improve the viability; the transportation helicopter emphasizes the viability in order to ensure the safety of transportation personnel; in order to ensure the task completion rate and avoid enemy attack, the unmanned helicopter also needs to consider proper viability design. Therefore, in helicopter model design, viability design is already in an increasingly important position.
Disclosure of Invention
The invention aims to provide a helicopter viability design method, which quantifies the vulnerability, sensitivity and wartime rush repair indexes of a helicopter based on domestic and foreign statistical data, adopts a linear weighting method to construct a viability evaluation model, and finally forms a set of viability design method capable of guiding the model design of the helicopter.
The technical scheme of the invention is as follows: a helicopter viability designing method comprises
The method comprises the following steps: establishing a viability item catalog according to the viability characteristics of the helicopter;
step two: according to the existing data statistics, a mapping relation between a viability item catalog and a main threat item is established, a viability design grade standard is formulated according to the resistance capability of the viability item to the main threat, and the grade is quantitatively scored;
step three: weighting the scores, establishing a comprehensive viability quantification model, establishing a cost model brought by viability,
wherein, the comprehensive score of the viability is f, the cost brought by the viability design measure is D, the cost comprises weight cost and cost, beta is the weight coefficient of each viability design project, A is the grade score of each viability design project, and W is the weight coefficient of each viability design project k 、C k The weight and cost penalty incurred for the viability design project, respectively;
step four: and improving or evaluating the viability design according to the viability comprehensive quantification score result.
Further, in the step one, the viability characteristics comprise stealth performance, airborne weapon performance, alarm self-inquiry capability, anti-striking capability of key components, anti-crash performance, maneuverability performance, reliability and maintainability.
Further, in the second step, the main threats include enemy detection equipment and enemy weapons, the enemy detection equipment includes radar, infrared light, visible light and the like, and the enemy weapons include bullets, rocket projectiles, missiles, cannonballs, anti-helicopter mines and the like.
And further, in the third step, a linear weighting method is adopted as the weighting method.
Further, if the comprehensive quantified score of the viability is greater than or equal to the qualified value, the viability of the helicopter meets the requirement, if the comprehensive quantified score of the viability is smaller than the qualified value, the viability project of the helicopter is improved, and the comprehensive quantified score of the viability is recalculated until the requirement is met.
The method has the key points that the effectiveness of each helicopter viability design project is quantified according to statistical data, a comprehensive evaluation model is formed by adopting a linear weighting method, and improvement suggestions can be provided for serious viability design defects according to evaluation results to guide the viability design of the helicopters. The helicopter viability design method is simple to operate, is applied to a certain type of transport plane, has engineering application value, and can guide the model design of various helicopters.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the invention and together with the description, serve to explain the principles of the invention.
FIG. 1 is a schematic diagram of the grading of the resistance to the main threats.
Fig. 2 is a schematic diagram of helicopter viability and major threat items.
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.
The helicopter viability design method is formed through the quantitative assessment of the viability indexes and the comprehensive assessment of the viability. Which comprises
Firstly, based on the sensitivity, the vulnerability and the war injury rush repair performance of the viability of the helicopter, various viability characteristics of the helicopter, such as stealth, airborne weapon performance, warning self-defense capability, anti-strike capability of key components, anti-crash capability, maneuverability, reliability, maintainability and the like, are sorted and classified, and a detailed list of viability design projects is established. As shown in fig. 1, the helicopter sensitivity includes the payload capacity, RCS (Radar Cross Section) area, and the like, the vulnerability includes armor thickness, crash-resistant overload coefficient, and the like, and the battlefield first-aid repair time includes equipment replacement time, equipment declaration, and the like.
Secondly, establishing a mapping relation between a viability design project and main threat projects according to domestic and foreign statistical data, establishing a viability design effective grade standard of the helicopter according to the effectiveness (including anti-strike capability, reliability and the like) of the viability design project against each threat project, and quantitatively scoring each grade, wherein parameters in a figure 1 are taken as examples, the load capacity is less than 0.5 tonnage and is taken as a grade 1, the load capacity is taken as a grade 2 from 0.5 to 1 tonnage, and the load capacity is taken as a grade 1 to 1.5The tonnage is grade 3; the loading capacity is more than 1.5 tonnage and is grade 4, the RCS area is less than 1.5m 2 Is grade 1,RCS area of 1.5-1 m 2 Is grade 2, the RCS area is 1-0.5 2 In a grade of 3,RCS area of less than 0.5m 2 Is grade 4; the thickness of the armor is less than 0.5cm and is grade 1, the thickness of the armor is 0.5-1 cm and is grade 2, the thickness of the armor is 1-1.5 cm and is grade 3, and the thickness of the armor is more than 1.5cm and is grade 4; the anti-crash overload coefficient is less than 2g (g is gravity acceleration) and is level 1, the anti-crash overload coefficient is 2-3 g and is level 2, the anti-crash overload coefficient is 3-4 g and is level 3, and the anti-crash overload coefficient is more than 4g and is level 4; the equipment replacement time is grade 1 when less than 0.25h, the equipment replacement time is grade 2 when 0.25-0.5 h, the equipment replacement time is grade 3 when 0.5-1 h, and the equipment replacement time is grade 4 when more than 1 h; the service life of the equipment is less than 1kh and is grade 1, the service life of the equipment is grade 2 when being 1-2 kh, the service life of the equipment is grade 3 when being 2-3 kh, and the service life of the equipment is grade 4 when being more than 3 kh. It is easily understood that the above parameters can improve the viability of the helicopter from level 1 to level 4 in sequence, so that the quantitative scores from level 1 to level 4 are set to be improved in sequence, and 4 scores, 6 scores, 8 scores and 10 scores are schematically given in the embodiment.
And thirdly, establishing a comprehensive quantitative evaluation model for the sensitivity, the vulnerability and the battlefield emergency repair of the helicopter by using a linear weighting method, and analyzing and counting the weight cost (performance cost) and the cost brought by each viability design measure to form a systematic and comprehensive helicopter viability evaluation method. Wherein the comprehensive viability score is f, and the cost brought by the viability design measure is D (comprising the weight W and the cost C):
in the formula: beta is the weight coefficient of each viability design item, A is each viability design itemGrade score, W k 、C k The weight and cost penalty incurred for the viability design project, respectively.
Fourthly, whether a major viability design defect exists or not is analyzed according to the evaluation result, improvement opinions are provided for major defect items, and improvement opinions are provided for minor defect items after the cost D (including weight cost and cost) is changed in comprehensive consideration, as shown in fig. 2. Based on the quantitative score given in this embodiment, if the calculated integrated score f <100 is the maximum defect, the integrated score f <180 is the minor defect.
The helicopter viability design method quantifies the effectiveness of each helicopter viability design project according to statistical data, forms a comprehensive evaluation model by adopting a linear weighting method, and can provide improvement suggestions for designing defects with heavy viability and guide the design of the helicopter viability according to an evaluation result. The helicopter viability design method disclosed by the invention is simple to operate, effective in design and high in engineering application value, and can guide the model design of various helicopters.
The above description is only for the best mode of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (5)
1. A helicopter viability design method is characterized by comprising
The method comprises the following steps: establishing a viability item catalog according to the viability characteristics of the helicopter;
step two: according to the existing data statistics, establishing a mapping relation between a viability item catalog and a main threat item, establishing a viability design grade standard according to the resistance capability of the viability item to the main threat, and quantitatively scoring the grades;
step three: weighting the scores, establishing a comprehensive viability quantification model, establishing a cost model brought by viability,
wherein, the comprehensive score of the viability is f, the cost brought by the viability design measure is D, the cost comprises weight cost and cost, beta is the weight coefficient of each viability design project, A is the grade score of each viability design project, and W is the weight coefficient of each viability design project k 、C k The weight and cost penalty incurred for the viability design project, respectively;
step four: and improving or evaluating the viability design according to the viability comprehensive quantification score result.
2. A helicopter viability design method according to claim 1, wherein in step one, the viability characteristics include stealth performance, airborne weapon performance, warning self-questioning capability, impact resistance of key components, crash resistance, maneuverability, reliability and maintainability.
3. A helicopter viability design method according to claim 1 wherein in step two, the primary threats include enemy detection equipment including, for example, radar, infrared, visible light, etc. and enemy weapons including bullets, rocket projectiles, missiles, cannonballs, anti-helicopter mines, etc.
4. A helicopter viability design method according to claim 1 wherein, in the third step, the weighting method uses a linear weighting method.
5. A method of designing helicopter viability according to claim 1 wherein if the integrated quantified score of viability is greater than or equal to the qualifying value, the helicopter viability meets the requirements, if the integrated quantified score of viability is less than the qualifying value, the helicopter viability project is improved and the integrated quantified score of viability is recalculated until the requirements are met.
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2017
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| CN104691748A (en) * | 2013-12-04 | 2015-06-10 | 中国直升机设计研究所 | Gun-launched unmanned helicopter and expansion method thereof |
| CN204056291U (en) * | 2014-01-14 | 2014-12-31 | 郝振兴 | Novel helicopter |
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| CN107092972A (en) * | 2016-02-18 | 2017-08-25 | 中国电力科学研究院 | A kind of transmission line of electricity cooperates with inspection performance evaluation method |
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