CN-122021248-A - Task efficiency-oriented tiltrotor performance requirement index generation and optimization method and system

CN122021248ACN 122021248 ACN122021248 ACN 122021248ACN-122021248-A

Abstract

The invention belongs to the technical field of aircraft overall demonstration, and relates to a method and a system for generating and optimizing a capability requirement index of a tilting rotor wing facing task efficiency. Firstly, a group of low-coupling technical demand index vectors are defined as optimization objects, and a computable mapping from the technical demand index to the capacity demand index is established by constructing a rapid overall performance comprehensive model. And secondly, introducing task-level simulation and efficiency evaluation as feedback links, combining engineering feasibility constraint judgment, performing iterative optimization in a solution space by using a heuristic algorithm, and finally outputting an optimized capacity demand index sequence to realize quick positioning of the requirements of the tiltrotor aircraft. The invention effectively solves the problems of difficult feasible solution searching and high forward modeling cost caused by strong coupling among capability requirement indexes in the early stage of demonstration, can rapidly generate and output the capability requirement index sequence with engineering realizability and stronger task pertinence, and provides basis for the overall demonstration and conceptual design of the tiltrotor aircraft.

Inventors

WANG GAOFENG
CHENG WENYUAN
Zhao Luodai
LI HAO
Wu Yangmeng
CHEN YUWEI

Assignees

航空工业信息中心

Dates

Publication Date: 20260512
Application Date: 20251224

Claims (9)

1. The task efficiency-oriented tiltrotor performance requirement index generation and optimization method is characterized by comprising the following steps of: S1, acquiring task input information of a task to be demonstrated, wherein the task input information comprises a task section, task load requirements and task environment conditions; s2, defining a technical requirement index vector theta as an optimization object, wherein the theta is formed by a group of technical requirement indexes which describe the design characteristics of the tiltrotor aircraft and have lower coupling among parameters; S3, defining a capability requirement index set Y as an evaluation object, wherein the Y consists of indexes representing the overall capability or performance of the tiltrotor aircraft and is used as the input of the subsequent task simulation; S4, establishing a calculation relation from the technical requirement index vector theta to the overall ruler measurement, and calculating based on the given theta to primarily obtain the overall ruler measurement; S5, constructing a rapid overall performance estimation model = ( , ) Based on the overall ruler measurement, combining with an external condition eta, calculating a capacity demand index set Y corresponding to a given theta through a model; s6, defining a task simulation evaluation external interface, wherein the interface receives the capability requirement index set Y and the task input information and outputs task simulation data; s7, constructing a constraint set of a technical requirement index and a capability requirement index, judging theta and Y generated by calculation, and screening out infeasible solutions; S8, constructing a task efficiency target function, wherein the function receives the task simulation data and quantitatively calculates a task execution effect as an efficiency index E; S9, performing iterative optimization, namely updating a technical requirement index vector theta in the constraint set by using a heuristic algorithm, and sequentially performing steps S4 to S8 on each group of theta, wherein the iterative optimization is performed with the aim of maximizing the efficiency index E to obtain a final capacity requirement index sequence; And S10, outputting an optimal capacity demand index sequence and a corresponding technical demand index vector.
2. The method of claim 1, wherein the technical demand indicators of step S2 include parameters such as mission load, air-to-weight ratio, fuel weight ratio, tip speed, hover efficiency coefficient, fuel consumption per unit power, rotor disk load, power load, and aspect ratio.
3. The method of claim 1, wherein the set of capability requirement indicators Y of step S3 includes parameters such as maximum flat flight speed, cruise speed, maximum climb rate, maximum range, maximum dead time, maximum lift height, maximum hover height, practical lift limit, hover fuel consumption rate, and flat flight fuel consumption rate, and maximum takeoff weight.
4. The method of claim 2, wherein the overall metric of step S4 is maximum takeoff weight, rotor radius, reference power.
5. The method of claim 4, wherein the overall scale calculation relationship is as follows: Calculating the maximum take-off weight by utilizing a weight decomposition relation based on the task load, the space-weight ratio and the fuel weight ratio; Thrust back rotor radius based on maximum takeoff weight and rotor disk load; the reference power is back-pushed based on the maximum takeoff weight and the power load.
6. The method according to claim 1, wherein the fast overall performance estimation model in step S5 = ( , ) At least comprises the following steps: 1) Calculating hover and vertical take-off capability, namely calculating air density according to flying height, calculating rotor pulling force according to maximum take-off weight, calculating hover required power according to hover efficiency coefficient, and calculating vertical climbing margin and hover limit according to comparison of available power of an engine; 2) Calculating forward flight parameters of a helicopter mode, namely scanning and calculating a rotor wing tension coefficient and an induction speed under a forward flight working condition by taking a forward ratio or speed as a variable, solving the induction power, the model resistance power and the waste resistance power to form a required power curve, and calculating a long voyage point and a climbing margin; 3) And calculating fixed wing mode parameters, namely calculating the lift resistance characteristic and the power based on the aspect ratio and the rotor wing scale reverse thrust equivalent wing area, calculating the fuel consumption rate curve by combining the unit power fuel consumption, and calculating the maximum flat flight speed, the cruising speed, the maximum range and the maximum endurance.
7. The method according to claim 1, wherein the set of constraints in step S7 comprises: performance parameter constraint, namely setting threshold constraint based on requirements for the calculated capacity requirement index Y; Technical parameter constraint, namely setting threshold constraint based on engineering practice or experience rules for the technical demand index vector theta; and forming a feasible domain through the constraint, and judging the solution which does not meet the constraint as infeasible or adjusting through a penalty function method in the subsequent iteration process.
8. The method according to claim 1, wherein the iterative optimization process in step S9 includes updating the candidate set using a heuristic algorithm, generating a new θ according to the performance value calculated by the simulation evaluation in each iteration, and recording candidates meeting the condition as a part of the output sequence according to a preset rule or recording all candidate sets meeting the task performance threshold.
9. Task performance oriented tiltrotor performance requirement index generation and optimization system implementing a method according to one of claims 1-8, The system comprises a demand input module, an overall performance estimation module, a task simulation evaluation module and an iteration optimization module, wherein, The requirement input module is used for acquiring, processing and transmitting the initial requirement of the tiltrotor aircraft; the overall performance estimation module is used for calculating overall ruler measurement, hovering and vertical take-off and landing capacity of the tiltrotor aircraft, helicopter mode forward flight parameters and fixed wing mode parameters; the task simulation evaluation module is used for performing task-level simulation on the calculated capacity demand index and performing task efficiency evaluation on a simulation result; the iterative optimization module is used for managing the iterative optimization flow, executing constraint definition and judgment, and completing the output of the optimization result.

Description

Task efficiency-oriented tiltrotor performance requirement index generation and optimization method and system Technical Field The invention belongs to the technical field of aircraft overall demonstration, relates to a demand analysis and index generation technology in the overall demonstration and conceptual design stage of a tiltrotor aircraft, and particularly relates to a task efficiency-oriented tiltrotor aircraft capability demand index generation and optimization method and system. Background The tiltrotor aircraft has the vertical take-off and landing and fixed wing high-speed cruising capabilities of the helicopter, has obvious potential advantages corresponding to tasks such as emergency assistance, marine guarantee and general transportation, and the like, but simultaneously relates to multi-working modes such as a helicopter, a fixed wing mode and the like, capability requirement indexes are usually formed by strong coupling indexes such as a hover limit, a maximum take-off and landing height, a maximum speed, a voyage and loading capability and the like, and the change of any single index can possibly cause linkage influence on other indexes, so that in the design early stage of a general demonstration stage or a conceptual scheme, a capability requirement index scheme capable of guiding demonstration and design is difficult to scientifically and rapidly form under the condition of lacking a reference model machine and a statistical rule, and further the design efficiency of the follow-up general demonstration and the conceptual scheme is directly influenced. In existing tiltrotor aircraft research practices, three types of paths are typically present for creating demand indicators or developing solution tradeoffs at the early demonstration stage. One is relying on experience analogy or expert index assignment, the mobility of the method is weak in a new configuration and a new scene, and the index boundary and the trade-off relation of the tiltrotor aircraft in multiple tasks, multiple environments and multiple modes are difficult to systematically describe. Secondly, the capacity demand index parameter is directly used as an optimization object to carry out multi-objective optimization, the calculation entrance of the method is visual, but because of strong coupling among all optimization parameters, complex physical constraint relation and difficulty in display and expression, the problems of 'mathematical optimization but engineering incapability' or 'constraint difficult modeling and low search efficiency' are easy to occur, and the stable output of an index sequence which can be used for demonstration is difficult. Thirdly, complete forward overall design optimization is performed from the overall design quantity, but the method needs to establish a relatively complete comprehensive model of pneumatic, power, control and the like, performs multidisciplinary iterative computation, may not have a complete overall calculation model in the overall demonstration stage or the initial conceptual design stage of the new-configuration aircraft, and generally does not have the conditions of rapid construction and mass running of the multidisciplinary optimization, so that the method faces practical obstacles such as poor timeliness, high cost, high model construction threshold and the like on the problems of 'capacity requirement index generation and optimization'. On the other hand, task level simulation and efficiency evaluation are mature in application in the related field, but are mostly used for capability verification and comparison analysis of a given design scheme or index set, if the task level simulation and efficiency evaluation are used for generating and optimizing capability requirement indexes from a task, a computable mapping from technical indexes to capability indexes to task results and task efficiency still needs to be established, multiple iterative calls are supported on the premise of ensuring the computing efficiency, and the problems of feasibility degradation and searching failure caused by strong coupling among the capability requirement indexes are avoided. Based on this, there is a need for an engineering method that is capable of generating and optimizing an index sequence in a low-computational-power environment with capability requirement indexes as output objects in the overall demonstration stage and the early conceptual design stage. Disclosure of Invention The technical problems to be solved by the invention are that the tiltrotor aircraft lacks a reference model machine and a statistical rule in the stage before the formation of the overall demonstration and concept scheme, the capability requirement index is strongly coupled and is difficult to balance to obtain a feasible solution, and the optimization method based on the capability requirement index/forward overall design is difficult to meet engineering requirements under the requirements of new configurat