CN109815528A - A method of the aircraft parameters optimization based on large-scale composite wing gas - Google Patents
A method of the aircraft parameters optimization based on large-scale composite wing gas Download PDFInfo
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Abstract
A method of the aircraft parameters optimization based on large-scale composite wing gas first determines the flight vehicle aerodynamic formal parameter of initialization, is compiled by aerodynamic configuration parameter of the VB software to the aircraft of extraction, generates the file that Catia tool can identify；The file that the Catia tool generated can identify is read using Catia tool, the aerodynamic configuration of aircraft is established in Catia tool, obtains the file of aerodynamic configuration；By the file of aerodynamic configuration, it is input to Unstlin software and carries out aerodynamic analysis, obtain the lift coefficient and lift resistance ratio of aircraft；The lift coefficient and lift resistance ratio of aircraft are judged, if the lift coefficient and lift resistance ratio of aircraft are all satisfied mission requirements, retain the aerodynamic configuration parameter of the aircraft of extraction as the aircraft parameters after optimization；Otherwise, the flight vehicle aerodynamic formal parameter for adjusting initialization has obtained the high aircraft shape of pneumatic efficiency, has improved the flying quality of aircraft.
Description
Technical field
The method for the aircraft parameters optimization based on large-scale composite wing gas that the present invention relates to a kind of, belongs to unmanned vehicle
Technical field.
Background technique
Over nearly two, 30 years, the development of unmanned plane is worldwide flourished, and especially America and Europe etc. sends out
A large amount of technical problems are broken through in this field up to country, searching to the bottom is because there are unmanned plane many manned aircrafts can not compare
Quasi- advantage, for example, it is cheap, cost of use is low, without taking one's life in one's hands, therefore, unmanned flight in many cases,
Device can complete manned machine with flying colors and be difficult to competent task.
If unmanned plane using the form of fixed-wing, will necessarily just be subject to certain restrictions in landing, be unable to fully body
Now convenient, flexible, hidden feature.Its takeoff and landing performance could be improved by only making basic change to the distribution form of aircraft, directly
The characteristics of machine of liter is the extreme of this change, helicopter is to generate lift by rotor wing rotation, therefore helicopter can vertically fly
Row, requires ground when landing very low, does not need special airport, can also hover in the sky, and what is fallen between is exactly
VTOL aircraft.
Fixed-wing quadrotor composite aircraft (compound quadrotor) is that successfully a kind of new vertical landing flies for latest developments
Machine obtains simple and effective VTOL solution in such a way that quadrotor is combined with fixed wing aircraft platform.It is multiple
Closing quadrotor has various performance advantages relative to other unmanned vehicles, is in a few years developed, compound quadrotor technology
Breakthrough development is had been carried out, small-sized compound quadrotor product has been launched.Since large-scale quadrotor system and fixed-wing fly
Machine platform is integrated to have coupling, and pneumatic efficiency is not high, pneumatic design is more difficult, therefore has certain technological challenge.
Summary of the invention
Present invention solves the technical problem that are as follows: it overcomes the shortage of prior art, provides a kind of winged based on large-scale composite wing gas
The method of row device parameter optimization, is optimized by the shape to fuselage, wing, is determined that a aeroperformance is higher and is flown
Row device shape overcomes problem, improves pneumatic efficiency.
The technical solution that the present invention solves are as follows: a method of the aircraft parameters optimization based on large-scale composite wing gas, step
It is rapid as follows:
(1) the flight vehicle aerodynamic formal parameter for determining initialization, flies extraction by VB software (Visual Basic)
The aerodynamic configuration parameter of row device is compiled, and generates the file that Catia tool can identify；
(2) file that can be identified using the Catia tool that Catia tool read step (1) generates, in Catia tool
The middle aerodynamic configuration for establishing aircraft, obtains the file of aerodynamic configuration；
(3) file for the aerodynamic configuration for obtaining step (2) is input to Unstlin software and carries out aerodynamic analysis, obtains
The lift coefficient and lift resistance ratio of aircraft；
(4) lift coefficient of the aircraft obtained to step (3) and lift resistance ratio judge, if the lift system of aircraft
Several and lift resistance ratio is all satisfied mission requirements, then retains step (1) and extract the aerodynamic configuration parameter of aircraft as winged after optimization
Row device parameter；Otherwise, the flight vehicle aerodynamic formal parameter for adjusting initialization, by flight in parameter alternative steps (1) adjusted
Device aerodynamic configuration parameter, as the flight vehicle aerodynamic formal parameter of initialization, return step (1)；
Aircraft based on large-scale composite wing gas, comprising: large-scale composite wing, fuselage, empennage, propelling screws；
Large-scale composite wing is located at the middle part of fuselage, and empennage is located at afterbody two sides, and propelling screws are mounted on fuselage tail
Portion's rearmost end.
Large-scale composite wing, comprising: fixed-wing, four propellers, four propellers pass through mounting bracket and fixed-wing phase
Even, four propellers are divided into two groups, and two groups of central axes relative to fuselage are symmetrical；
Determine the flight vehicle aerodynamic formal parameter of initialization, specific as follows:
According to mission requirements, the initial aerodynamic configuration of aircraft is broadly divided into fuselage and wing two parts, and initial fuselage is long
Preferably 5m, wingspan length are preferably 6m, are one section of circular arc at the top of front fuselage, radius is preferably 5m, the corresponding center of circle of circular arc
Angle number is preferably 20 °, and length of the wing apart from head origin is preferably 3m.
Catia tool is capable of the relative position of the accurate careful aerodynamic configuration for depicting aircraft and each component.
VB software (Visual Basic) is compiled the aerodynamic configuration parameter of the aircraft of extraction, specifically: it determines
Aircraft Handpiece Location and fuselage overall length extract front fuselage arc radius, central angle, wingspan length, wing with respect to head
Position is variable element.
Generate the file that Catia tool can identify, specially text txt format
The file that the Catia tool that Catia tool read step (1) generates can identify, specifically: Catia is read
Txt text document contains a series of basic parameters for Modeling of Vehicle in this document, as Handpiece Location, fuselage length,
Wing length etc. is based on these parameters, draws out aerodynamic configuration.
The file for the aerodynamic configuration that step (2) is obtained is input to Unstlin software and carries out aerodynamic analysis, specifically such as
Under: setting aircraft flight Mach 2 ship 0.1Ma, the cruise angle of attack are 3 °.
The file for the aerodynamic configuration that step (2) is obtained is input to Unstlin software and carries out aerodynamic analysis, flown
Device cruise when lift coefficient, lift resistance ratio, through stability margin and pitching moment.
The advantages of the present invention over the prior art are that:
(1) a kind of method for large-scale composite wing unmanned plane aerodynamic configuration modeling optimization of the invention, aerodynamic configuration are built
Mould is simple, is conducive to the extraction of optimization input parameter.
(2) a kind of method for large-scale composite wing unmanned plane aerodynamic configuration modeling optimization of the invention is joined in optimization
It is accurate that number is chosen, and computational solution precision is high, can be directly as the reference data of engineering design.
(3) a kind of method for large-scale composite wing unmanned plane aerodynamic configuration modeling optimization of the invention, optimization aim are bright
Really, iteration cycle is short, can shorten the engineering development period.
(4) a kind of method for large-scale composite wing unmanned plane aerodynamic configuration modeling optimization of the invention, the gas after optimization
Dynamic shape aeroperformance is good, high-efficient；
Detailed description of the invention
Fig. 1 is unmanned plane modeling optimization general illustration of the present invention；
Fig. 2 is unmanned vehicle schematic diagram after modeling optimization of the present invention；
Fig. 3 is aircraft lift charts for finned heat of the present invention；
Fig. 4 is aircraft resistance charts for finned heat of the present invention；
Specific embodiment
The invention will be described in further detail in the following with reference to the drawings and specific embodiments.
A kind of method of the aircraft parameters optimization based on large-scale composite wing gas of the present invention, first determines the flight of initialization
Device aerodynamic configuration parameter is compiled by aerodynamic configuration parameter of the VB software to the aircraft of extraction, generates Catia tool
The file that can be identified；The file that the Catia tool generated can identify is read using Catia tool, in Catia tool
The aerodynamic configuration for establishing aircraft obtains the file of aerodynamic configuration；By the file of aerodynamic configuration, be input to Unstlin software into
Row aerodynamic analysis obtains the lift coefficient and lift resistance ratio of aircraft；The lift coefficient and lift resistance ratio of aircraft are judged,
If the lift coefficient and lift resistance ratio of aircraft are all satisfied mission requirements, the aerodynamic configuration parameter for retaining the aircraft of extraction is made
For the aircraft parameters after optimization；Otherwise, the flight vehicle aerodynamic formal parameter for adjusting initialization, it is high to have obtained pneumatic efficiency
Aircraft shape improves the flying quality of aircraft.
Aircraft shape of the invention is made of fuselage, wing, empennage, vertical super helix paddle and propelling screws, the invention
The fuselage appearance of main optimization aircraft and wing position.
A kind of method of the aircraft parameters optimization based on large-scale composite wing gas of the present invention, steps are as follows:
(1) the flight vehicle aerodynamic formal parameter for determining initialization, flies extraction by VB software (Visual Basic)
The aerodynamic configuration parameter of row device is compiled, and generates the file that Catia tool can identify；
(2) file that can be identified using the Catia tool that Catia tool read step (1) generates, in Catia tool
The middle aerodynamic configuration for establishing aircraft, obtains the file of aerodynamic configuration；
(3) file for the aerodynamic configuration for obtaining step (2), be input to Unstlin software carry out aerodynamic analysis (how
Analysis), obtain the lift coefficient and lift resistance ratio of aircraft；
(4) lift coefficient of the aircraft obtained to step (3) and lift resistance ratio judge, if the lift system of aircraft
Several and lift resistance ratio is all satisfied mission requirements, then retains step (1) and extract the aerodynamic configuration parameter of aircraft as winged after optimization
Row device parameter；Otherwise, the flight vehicle aerodynamic formal parameter for adjusting initialization, by flight in parameter alternative steps (1) adjusted
Device aerodynamic configuration parameter, as the flight vehicle aerodynamic formal parameter of initialization, return step (1)；
The mode of the flight vehicle aerodynamic formal parameter of specific adjustment initialization is, when static margin is more than threshold value 12%
When, shorten position of the wing apart from head, when the lift resistance ratio when 5 ° of angles of attack is less than 15, increases wingspan length, when 5 ° of angles of attack
Lift coefficient less than 0.4 when, increase front fuselage arc radius, increase wingspan length.
It is as shown in Figure 1 optimization detailed process, the first step determines the flight vehicle aerodynamic formal parameter of initialization, passes through VB
Software (Visual Basic) is compiled generation Catia tool to the aerodynamic configuration parameter of the aircraft of extraction and can identify
File, the file that can identify of Catia tool that second step is generated using Catia tool read step (1), in Catia work
The aerodynamic configuration that aircraft is established in tool obtains the file of aerodynamic configuration, the aerodynamic configuration that third step obtains step (2)
File is input to Unstlin software, carries out Pneumatic Calculation using vortex lattice method, obtain the lift coefficient of aircraft, lift resistance ratio and
Static margin；
4th step judges lift coefficient, lift resistance ratio and the static margin of the aircraft that step (3) obtains, if
Lift coefficient, lift resistance ratio and the static margin of aircraft are all satisfied mission requirements, then retain step (1) and extract aircraft
Aerodynamic configuration parameter is as the aircraft parameters after optimization；Otherwise, the flight vehicle aerodynamic formal parameter of initialization is adjusted, specifically
When adjustment, when static margin is more than threshold value 12%, shorten position of the wing apart from head, the lift resistance ratio when 5 ° of angles of attack
When less than 15, increase wingspan length, when the lift coefficient when 5 ° of angles of attack is less than 0.4, increases front fuselage arc radius, increase
Big wingspan length.
Flight vehicle aerodynamic by flight vehicle aerodynamic formal parameter in parameter alternative steps (1) adjusted, as initialization
Formal parameter, return step (1)；Fig. 2 is the schematic diagram after aircraft optimization, and Fig. 3 is the lift coefficient of aircraft after optimization
Figure, abscissa is the angle of attack, and ordinate is lift coefficient, it can be seen that lift system of the aircraft in 5 ° of angles of attack after optimization
It is vehicle lift-drag schematic diagram after optimization that number, which is greater than 0.4, Fig. 4, and abscissa is the angle of attack, and ordinate is lift resistance ratio, You Tuke with
See, vehicle lift-drag is greater than 15 after optimization.
Aircraft based on large-scale composite wing gas, comprising: large-scale composite wing, fuselage, empennage, propelling screws；Large size is multiple
The middle part that the wing is located at fuselage is closed, empennage is located at afterbody two sides, and propelling screws are mounted on afterbody rearmost end.It is large-scale
Composite wing, comprising: fixed-wing, four propellers, four propellers are connected by mounting bracket with fixed-wing, four propellers
It is divided into two groups, two groups of central axes relative to fuselage are symmetrical；
Determine the flight vehicle aerodynamic formal parameter of initialization, specific as follows:
According to mission requirements, the initial aerodynamic configuration of aircraft is broadly divided into fuselage and wing two parts, and initial fuselage is long
Preferably 5m, wingspan length are preferably 6m, are one section of circular arc at the top of front fuselage, radius is preferably 5m, the corresponding center of circle of circular arc
Angle number is preferably 20 °, and length of the wing apart from head origin is preferably 3m.
Catia tool is capable of the relative position of the accurate careful aerodynamic configuration for depicting aircraft and each component.VB
Software (Visual Basic) is compiled the aerodynamic configuration parameter of the aircraft of extraction, specifically: determine aircraft head
Position and fuselage overall length, it is variable for extracting front fuselage arc radius, central angle, wingspan length, wing with respect to the position of head
Parameter.The file that Catia tool can identify is generated, text txt format is particularly preferred as.
The file that the Catia tool that Catia tool read step (1) generates can identify, specifically: Catia is read
Txt text document contains a series of basic parameters for Modeling of Vehicle in this document, as Handpiece Location, fuselage length,
Wing length etc. is based on these parameters, draws out aerodynamic configuration.
The file for the aerodynamic configuration that step (2) is obtained is input to Unstlin software and carries out aerodynamic analysis, specifically such as
Under: setting aircraft flight Mach 2 ship 0.1Ma, the cruise angle of attack are 3 °.The file for the aerodynamic configuration that step (2) is obtained, it is defeated
Enter to Unstlin software and carry out aerodynamic analysis, lift coefficient when obtaining aircraft cruise, through stability margin and is bowed at lift resistance ratio
Face upward torque.
Aerodynamic configuration modeling of the present invention is simple, is conducive to the extraction of optimization input parameter；In optimization, parameter is chosen quasi-
Really, computational solution precision is high, can be directly as the reference data of engineering design；Optimization aim is clear, and iteration cycle is short, can contract
Casual labourer's journey lead time；Aerodynamic configuration aeroperformance after optimization is good, high-efficient；It has obtained outside the high aircraft of pneumatic efficiency
Shape improves the flying quality of aircraft.
Claims (10)
1. a kind of method of the aircraft parameters optimization based on large-scale composite wing gas, it is characterised in that steps are as follows:
(1) the flight vehicle aerodynamic formal parameter for determining initialization, by VB software to the aerodynamic configuration parameter of the aircraft of extraction
It is compiled, generates the file that Catia tool can identify；
(2) file that can be identified using the Catia tool that Catia tool read step (1) generates, is built in Catia tool
The aerodynamic configuration of vertical aircraft, obtains the file of aerodynamic configuration；
(3) file for the aerodynamic configuration for obtaining step (2) is input to Unstlin software and carries out aerodynamic analysis, obtains aircraft
Lift coefficient and lift resistance ratio；
(4) lift coefficient of the aircraft obtained to step (3) and lift resistance ratio judge, if the lift coefficient and liter of aircraft
Resistance ratio is all satisfied mission requirements, then retains step (1) and extract the aerodynamic configuration parameter of aircraft as the aircraft ginseng after optimization
Number；Otherwise, the flight vehicle aerodynamic formal parameter for adjusting initialization, by flight vehicle aerodynamic in parameter alternative steps (1) adjusted
Formal parameter, as the flight vehicle aerodynamic formal parameter of initialization, return step (1).
2. a kind of method of aircraft parameters optimization based on large-scale composite wing gas according to claim 1, feature exist
In: the aircraft based on large-scale composite wing gas, comprising: large-scale composite wing, fuselage, empennage, propelling screws；Large-scale composite wing position
In the middle part of fuselage, empennage is located at afterbody two sides, and propelling screws are mounted on afterbody rearmost end.
3. a kind of method of aircraft parameters optimization based on large-scale composite wing according to claim 1, it is characterised in that:
Large-scale composite wing, comprising: fixed-wing, four propellers, four propellers are connected by mounting bracket with fixed-wing, four spirals
Paddle is divided into two groups, and two groups of central axes relative to fuselage are symmetrical.
4. a kind of method of aircraft parameters optimization based on large-scale composite wing gas according to claim 1, feature exist
In: determine the flight vehicle aerodynamic formal parameter of initialization, specific as follows:
According to mission requirements, the initial aerodynamic configuration of aircraft is broadly divided into fuselage and wing two parts, the initial a length of 5m of fuselage,
Wingspan length 6m, front fuselage top are one section of circular arc, and radius 5m, the corresponding central angle degree of circular arc is 20 °, wing and machine
The length of the centre distance head origin of body junction is 3m.
5. a kind of method of aircraft parameters optimization based on large-scale composite wing according to claim 3, it is characterised in that:
Catia tool is capable of the relative position of the accurate careful aerodynamic configuration for depicting aircraft and each component.
6. a kind of method of aircraft parameters optimization based on large-scale composite wing according to claim 3, it is characterised in that:
VB software is compiled the aerodynamic configuration parameter of the aircraft of extraction specifically: determines that aircraft Handpiece Location and fuselage are total
Long, extracting front fuselage arc radius, central angle, wingspan length, wing with respect to the position of head is variable element.
7. a kind of method of aircraft parameters optimization based on large-scale composite wing according to claim 3, it is characterised in that:
Generate the file that Catia tool can identify, specially text txt format.
8. a kind of method of aircraft parameters optimization based on large-scale composite wing gas according to claim 3, feature exist
In: the file that the Catia tool that Catia tool read step (1) generates can identify, specifically: Catia reads txt text
Document, contains a series of basic parameters for Modeling of Vehicle in this document, including Handpiece Location, fuselage length, wing are long
Degree；Based on these parameters, aerodynamic configuration is drawn out.
9. a kind of method of aircraft parameters optimization based on large-scale composite wing according to claim 3, it is characterised in that:
The file for the aerodynamic configuration that step (2) is obtained is input to Unstlin software and carries out aerodynamic analysis, specific as follows: setting flight
Device flight Mach number is 0.1Ma, and the cruise angle of attack is 3 °.
10. a kind of method of aircraft parameters optimization based on large-scale composite wing according to claim 3, feature exist
In: the file for the aerodynamic configuration that step (2) is obtained is input to Unstlin software and carries out aerodynamic analysis, obtains aircraft cruise
When lift coefficient, lift resistance ratio, through stability margin and pitching moment.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113641164A (en) * | 2021-07-07 | 2021-11-12 | 中国人民解放军火箭军工程大学 | Simulation test platform for hypersonic aircraft examination and control method thereof |
| CN115408778A (en) * | 2022-10-31 | 2022-11-29 | 北京大学 | Method, device and equipment for determining hydrofoil structure size parameters of cross-medium aircraft |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104992023A (en) * | 2015-07-13 | 2015-10-21 | 南京航空航天大学 | Aircraft parametric design method based on state type function |
| CN105460233A (en) * | 2015-11-12 | 2016-04-06 | 中国人民解放军国防科学技术大学 | Method for designing fixed-wing aircraft capable of vertically taking off and landing |
| CN105539835A (en) * | 2016-01-18 | 2016-05-04 | 成都纵横自动化技术有限公司 | Composite-wing vertical take-off and landing aircraft |
| CN205327411U (en) * | 2016-01-29 | 2016-06-22 | 成都纵横自动化技术有限公司 | Composite wing aircraft |
| US20160244143A1 (en) * | 2014-09-17 | 2016-08-25 | The Boeing Company | Composite wing edge attachment and method |
| CN106043685A (en) * | 2016-01-27 | 2016-10-26 | 北京航空航天大学 | Double-vector-propeller rotor/fixed wing combined type vertical take-off and landing aircraft |
| CN106184737A (en) * | 2016-09-23 | 2016-12-07 | 西北工业大学 | Combined type layout vertically taking off and landing flyer and VTOL flying method |
| CN106672232A (en) * | 2017-03-02 | 2017-05-17 | 北京天宇新超航空科技有限公司 | Efficient vertical takeoff and landing aircraft |
| CN107985626A (en) * | 2017-10-27 | 2018-05-04 | 南京航空航天大学 | A kind of aerodynamic arrangement's design method based on variable configuration re-entry space vehicle |
| US20190291860A1 (en) * | 2016-10-27 | 2019-09-26 | Mono Aerospace Ip Ltd | Vertical take-off and landing aircraft and control method |
-
2018
- 2018-12-13 CN CN201811522276.0A patent/CN109815528A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20160244143A1 (en) * | 2014-09-17 | 2016-08-25 | The Boeing Company | Composite wing edge attachment and method |
| CN104992023A (en) * | 2015-07-13 | 2015-10-21 | 南京航空航天大学 | Aircraft parametric design method based on state type function |
| CN105460233A (en) * | 2015-11-12 | 2016-04-06 | 中国人民解放军国防科学技术大学 | Method for designing fixed-wing aircraft capable of vertically taking off and landing |
| CN105539835A (en) * | 2016-01-18 | 2016-05-04 | 成都纵横自动化技术有限公司 | Composite-wing vertical take-off and landing aircraft |
| CN106043685A (en) * | 2016-01-27 | 2016-10-26 | 北京航空航天大学 | Double-vector-propeller rotor/fixed wing combined type vertical take-off and landing aircraft |
| CN205327411U (en) * | 2016-01-29 | 2016-06-22 | 成都纵横自动化技术有限公司 | Composite wing aircraft |
| CN106184737A (en) * | 2016-09-23 | 2016-12-07 | 西北工业大学 | Combined type layout vertically taking off and landing flyer and VTOL flying method |
| US20190291860A1 (en) * | 2016-10-27 | 2019-09-26 | Mono Aerospace Ip Ltd | Vertical take-off and landing aircraft and control method |
| CN106672232A (en) * | 2017-03-02 | 2017-05-17 | 北京天宇新超航空科技有限公司 | Efficient vertical takeoff and landing aircraft |
| CN107985626A (en) * | 2017-10-27 | 2018-05-04 | 南京航空航天大学 | A kind of aerodynamic arrangement's design method based on variable configuration re-entry space vehicle |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113641164A (en) * | 2021-07-07 | 2021-11-12 | 中国人民解放军火箭军工程大学 | Simulation test platform for hypersonic aircraft examination and control method thereof |
| CN115408778A (en) * | 2022-10-31 | 2022-11-29 | 北京大学 | Method, device and equipment for determining hydrofoil structure size parameters of cross-medium aircraft |
| CN115408778B (en) * | 2022-10-31 | 2023-03-10 | 北京大学 | Method, device and equipment for determining hydrofoil structure size parameters of cross-medium aircraft |
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