CN105253305A - Leading-edge detachable type experiment wing structure based on piezoelectric deicing system - Google Patents
Leading-edge detachable type experiment wing structure based on piezoelectric deicing system Download PDFInfo
- Publication number
- CN105253305A CN105253305A CN201510652738.0A CN201510652738A CN105253305A CN 105253305 A CN105253305 A CN 105253305A CN 201510652738 A CN201510652738 A CN 201510652738A CN 105253305 A CN105253305 A CN 105253305A
- Authority
- CN
- China
- Prior art keywords
- leading edge
- cross plate
- parts
- leading
- wing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a leading-edge detachable type experiment wing structure based on a piezoelectric deicing system. The structure comprises two leading-edge parts, one front-segment crossbeam, two rear-segment parts and one rear-segment crossbeam, wherein each leading-edge part and the rear-segment crossbeam are respectively arranged at the two ends of each rear-segment part, the rear-segment parts and the leading-edge parts are connected through the front-segment crossbeam, the two leading-edge parts are parallel to each other, the two leading-edge parts are symmetrical along a longitudinal center line of the experiment wing structure, and the spacing between the two leading-edge parts can be randomly adjusted. According to the invention, the leading-edge parts can be detachable and adjusted, and wing models with different wing expansion direction dimensions can be combined, such that diversity of research on piezoelectric deicing methods can be realized according to different adjustment wing structures of research objects.
Description
Technical field
The present invention relates to a kind of experimental machine wing structure detachable based on the leading edge of piezoelectricity ice removal system, belong to the technical field of aircraft experimental configuration.
Background technology
When aircraft flies in containing the cloud layer of super-cooling waterdrop, surface such as the lifting surface such as wing, empennage, inlet channel leading edge etc. can be frozen windward, causes serious threat, therefore need to take reasonably anti-icing, deicing measure to flight safety.For the relevant anti-de-icing method of present stage, piezoelectricity de-icing method, as a kind of novel de-icing method, due to the advantage that its energy consumption is low, efficiency is high, has vast potential for future development.
With piezoelectricity de-icing method to the piezoelectricity ice removal system combined, be mainly used in the ice detachment being not suitable for the plane wing surfaces of calorifics de-icing method that some are small-sized.And the leading edge of a wing is as the main icing area of aircraft, in anti-deicing systematic study, there is very high research status and researching value, in piezoelectricity ice removal system, piezoelectric actuator mainly distributes and leading edge of a wing position, therefore the corresponding research for Airfoil leading edge just seems particularly important, for the research of the piezoelectricity deicing effect under the different fixed form of Airfoil leading edge and different size, just need wing structure to need certain changeability and adjustable, the comformability of research can be had simultaneously for different freezing environment.And, the research major part of piezoelectricity ice removal system concentrates on dull and stereotyped research now, research object and research model simple, and little for the research of Practical Wings aerofoil profile, therefore, the piezoelectricity de-icing method under research Airfoil prerequisite and deicing effect seem particularly crucial.
Summary of the invention
In order to solve above-mentioned Problems existing, the invention discloses a kind of experimental machine wing structure detachable based on the leading edge of piezoelectricity ice removal system, the wing structure that a kind of leading edge is detachable is provided, the requirement of the piezoelectricity de-icing method research under different wing dimension, different leading edge of a wing fixed form and icing tunnel environment can be adapted to.
A kind of experimental machine wing structure detachable based on the leading edge of piezoelectricity ice removal system, this experimental machine wing structure surface is equipped with covering, described covering comprises the leading edge of a wing covering being laid on the leading edge of a wing and the trailing edge covering being laid on trailing edge, described leading edge of a wing skin-surface pastes piezoelectric patches, by vibrating to piezoelectric patches energising excitation piezoelectric patches, and then encourage whole leading edge of a wing covering to vibrate, reach deicing object
This experimental machine wing structure comprises two leading edge parts, leading portion crossbeam, two back segment parts and a back segment crossbeam,
Described leading edge parts and back segment crossbeam are separately positioned on the two ends of back segment parts, and back segment parts are connected by leading portion crossbeam with leading edge parts,
Described two leading edge parts are parallel to each other, and described two leading edge parts are symmetrical along the longitudinal centerline of this experimental machine wing structure, and the spacing between described two leading edge parts is adjustable arbitrarily.
Described leading portion crossbeam is an integral structure, it intermediate plate comprising upper cross plate, lower cross plate and connect upper cross plate and lower cross plate, described upper cross plate lower surface and lower cross plate upper surface are parallel to each other, intermediate plate is vertically set on longitudinal center's line position of upper cross plate and lower cross plate, and the lateral cross section of described leading portion crossbeam is in " work " word shape.
The coupling end of described leading edge parts and leading portion crossbeam and the coupling end of back segment parts and leading portion crossbeam are respectively in " convex " word shape.
The coupling end of described leading edge parts and leading portion crossbeam is inserted in the leading portion crossbeam of " work " word shape, the upper and lower surface of the coupling end of leading edge parts and leading portion crossbeam and end face are fitted with upper cross plate, lower cross plate and intermediate plate respectively, and be connected and fixed respectively by attaching parts
The coupling end of described back segment parts and leading portion crossbeam is inserted in the leading portion crossbeam of " work " font, the upper and lower surface of back segment parts and leading portion crossbeam coupling end and end face are fitted with upper cross plate, lower cross plate and intermediate plate respectively, and are connected and fixed respectively by attaching parts.
Described upper cross plate and lower cross plate are provided with several tapped bore towards a lateral edges of leading edge parts, the tapped bore of described upper cross plate and lower cross plate is corresponding up and down successively, the position that described leading edge parts and upper cross plate and lower cross plate are fitted also is provided with tapped bore, and the tapped bore of leading edge parts is consistent with the tapped bore specification of upper cross plate and lower cross plate, be connected with upper cross plate and lower cross plate by leading edge parts by screw thread precession bolt in tapped bore, described leading edge parts can be bolted with the tapped bore corresponding up and down arbitrarily of upper cross plate and lower cross plate.
Principle of work of the present invention is:
Because real aircraft wing dimension is larger, for some Related Experimental Study, the wing of large-size cannot realize the correlation theory research under laboratory condition, therefore the convergent-divergent carrying out wing model is needed, namely Practical Wings is carried out convergent-divergent according to a certain percentage, be scaled the wing model that size is less, this process is called model contracting ratio.The wing model that size is less is representative for the correlated phenomena of research Practical Wings, especially for deicing mode, small size wing model can meet the deicing research process of research Practical Wings structure, and therefore, this invention can meet the piezoelectricity deicing research process of Practical Wings.
Practical Wings structure contains truss, wing cover and other associated support drive mechanisms.But for wing piezoelectric vibration deicing, because real aircraft ice field is mainly distributed in leading edge of a wing region, therefore the piezoelectric vibration research for the leading edge of a wing just seems particularly important, so for this invention, integrally-built design is mainly studied in order to the piezoelectricity deicing of leading edge portion, can say that front edge area is important survey region.The wing structure that this invention proposes is actual is a kind of framed structure, for the unique design of framed structure, not only meets the experimental study under experiment condition, and the structure distribution situation of realistic wing.Because wing cover does not have invention, therefore wing structure is carried out to the invention of certain configuration aspects, the change of structure then can cause the change of covering size, and then meets the deicing research of different size lower wing structure.The structure design of this invention is on the basis meeting Practical Wings structural requirement, carries out the invention of experimental study structure, meets the process of laboratory investigation.
The leading edge of a wing is attached most importance to survey region, wing icing and ice detachment are only relevant to leading edge of a wing part, rear end part does not affect it, therefore just specific requirement is not carried out for rear airfoil end part, as long as ensure certain version, namely the effect of rear end part is to ensure the complete of whole wing structure.Therefore detachable, the adjustable process of leading edge portion is not by the impact of rear end part.Can think that rear end part is a underwork of leading edge portion, in practical study, regulate leading edge portion structure can complete whole process of experimental, do not need to regulate rear end part.Because wing icing region is mainly distributed in leading edge portion, the size of leading edge portion is different, wing is different in the icing amount of leading edge, therefore only need to study leading edge portion, and piezoelectric vibration de-icing element is also be distributed in skins front edges part, therefore the size of rear end part and size do not affect wing icing, do not need specifically to pay close attention to.
For piezoelectric vibration de-icing method, principle is the vibration utilizing the piezoelectric patches be pasted onto on leading edge of a wing covering, encourages the structural vibration of whole leading edge of a wing covering, and then reaches the object of deicing.For skins front edges vibration, the form of vibration and effect can be subject to the impact of covering fixed form and covering size.Covering is fixed both sides and is fixed four limits, the vibrating effect of covering is different, effect for deicing is also different, therefore design leading edge detouchable wing structure is needed, so just can by changing leading edge portion version, change the fixed form of covering, and then study the covering vibrating effect under different fixed form.
The covering of Practical Wings is made up of the little covering of certain size, is similar to Pork-pieces " patch " structure.For large-sized wing, the size of monolithic covering is also larger; For undersized wing, the size of monolithic covering is less.Mention wing cover size above and have impact to covering vibration, and Width is different, the icing amount of the leading edge of a wing is also different, and wing cover size is determined by wing structure, therefore the wing structure in this invention, by changing leading edge structure spacing in the direction of the width, the change in the direction of the width of covering size can be realized, and then meets research purpose.
And for Practical Wings, truss structure and the wing cover of the inside can be regarded as and be made up of multiple similar module, the wing structure of therefore this invention can regard a part of Practical Wings as.Because piezoelectric vibration device is the ad-hoc location of distribution and whole Practical Wings skins front edges, the leading edge of a wing structure deicing mode therefore studying a part can meet the research process of whole wing.For the research model that other width dimensions are different, can design with reference to the wing structure design of this invention, can realize Width changes by two kinds of modes: one is change size on section beam width direction, front and back.Two is the wing structure that can design multiple same section, then carries out Width splices.No matter be which kind of process, the wing structure form that this invention relates to is constant.Thus whole invention meets the different fixed form described in technical requirements and the research purpose on different width dimensions.
The invention has the beneficial effects as follows:
1, the research process for the piezoelectricity de-icing method under experimental machine wing structure condition and deicing compliance test result process is realized;
2, leading edge parts can carry out dismantling and regulating, and realize the variety to the research of piezoelectricity de-icing method;
3, due to the adjustability of experimental machine wing structure leading edge parts, the exhibition of different wing can be formed to the wing model of (width) size, thus according to the different adjustment wing structure of research object, the research contents of piezoelectricity de-icing method can be enriched.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention,
Fig. 2 is the structural representation of leading edge parts of the present invention,
Fig. 3 is the structural representation of leading portion crossbeam of the present invention,
Fig. 4 is the structural representation of back segment parts of the present invention,
Fig. 5 is the structural representation of back segment crossbeam of the present invention,
Reference numerals list: 1-leading edge parts, 2-leading portion crossbeam, 3-back segment parts, 4-back segment crossbeam.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, illustrate the present invention further.Following detailed description of the invention should be understood only be not used in for illustration of the present invention and limit the scope of the invention.
Visible by reference to the accompanying drawings, this a kind of experimental machine wing structure detachable based on the leading edge of piezoelectricity ice removal system, this experimental machine wing structure surface is equipped with covering, described covering comprises the leading edge of a wing covering being laid on the leading edge of a wing and the trailing edge covering being laid on trailing edge, described leading edge of a wing skin-surface pastes piezoelectric patches, by vibrating to piezoelectric patches energising excitation piezoelectric patches, and then encouraging whole leading edge of a wing covering to vibrate, reaching deicing object.
This experimental machine wing structure comprises two leading edge parts, 1, leading portion crossbeam, 2, two back segment parts 3 and a back segment crossbeam 4, described leading edge parts 1 and back segment crossbeam 4 are separately positioned on the two ends of back segment parts 3, back segment parts 3 are connected by leading portion crossbeam 2 with leading edge parts 1, by the connection of each parts, form the experimental machine wing structure with Practical Wings structure scaled down.
Described two leading edge parts 1 are parallel to each other, and described two leading edge parts 1 are symmetrical along the longitudinal centerline of this experimental machine wing structure, and the spacing between described two leading edge parts 1 is adjustable arbitrarily.By changing the spacing between two leading edge parts 1, realizing the change width of experimental machine wing structure leading edge portion, realizing the simulated experiment of the leading edge of a wing under multiple width.
Described leading portion crossbeam 2 comprises upper cross plate, lower cross plate and connects the intermediate plate of upper cross plate and lower cross plate, described upper cross plate and lower cross plate are parallel to each other, intermediate plate is vertically set on longitudinal center's line position of upper cross plate and lower cross plate, and the lateral cross section of described leading portion crossbeam 2 is in " work " word shape.The end of leading edge parts 1 and the end of back segment parts 3 are inserted into the both sides of " work " word shape respectively, and then leading edge parts 1 and back segment parts 3 are connected and fixed with leading portion crossbeam 2 respectively, being connected and fixed of this kind of position relationship.
Described leading edge parts 1 are " convex " word shape with the coupling end of leading portion crossbeam 2 and the coupling end of back segment parts 3 and leading portion crossbeam 2 respectively.Described leading edge parts 1 are inserted in the leading portion crossbeam 2 of " work " word shape with the coupling end of leading portion crossbeam 2, upper and lower surface and the end face of the coupling end of leading edge parts 1 and leading portion crossbeam 2 are fitted with upper cross plate, lower cross plate and intermediate plate respectively, and be connected and fixed respectively by attaching parts, described back segment parts 3 are inserted in the leading portion crossbeam 2 of " work " font with the coupling end of leading portion crossbeam 2, upper and lower surface and the end face of back segment parts 3 and leading portion crossbeam 2 coupling end are fitted with upper cross plate, lower cross plate and intermediate plate respectively, and are connected and fixed respectively by attaching parts.This kind of connection location relation, stable connection, good stability.
Described upper cross plate and lower cross plate are provided with several tapped bore towards a lateral edges of leading edge parts 1, the tapped bore of described upper cross plate and lower cross plate is corresponding up and down successively, the position that described leading edge parts 1 and upper cross plate and lower cross plate are fitted also is provided with tapped bore, and the tapped bore of leading edge parts 1 is consistent with the tapped bore specification of upper cross plate and lower cross plate, be connected with upper cross plate and lower cross plate by leading edge parts 1 by screw thread precession bolt in tapped bore, described leading edge parts 1 can be bolted with the tapped bore corresponding up and down arbitrarily of upper cross plate and lower cross plate.Bolt connects for a kind of conventional simple connection mode that can realize repeating connection and dismounting.
Technological means disclosed in the present invention program is not limited only to the technological means disclosed in above-mentioned technological means, also comprises the technical scheme be made up of above technical characteristic combination in any.
With above-mentioned according to desirable embodiment of the present invention for enlightenment, by above-mentioned description, relevant staff in the scope not departing from this invention technological thought, can carry out various change and amendment completely.The technical scope of this invention is not limited to the content on specification sheets, must determine its technical scope according to right.
Claims (5)
1. one kind based on the detachable experimental machine wing structure of the leading edge of piezoelectricity ice removal system, this experimental machine wing structure surface is equipped with covering, described covering comprises the leading edge of a wing covering being laid on the leading edge of a wing and the trailing edge covering being laid on trailing edge, described leading edge of a wing skin-surface pastes piezoelectric patches, by vibrating to piezoelectric patches energising excitation piezoelectric patches, and then encourage whole leading edge of a wing covering to vibrate, reach deicing object
It is characterized in that this experimental machine wing structure comprises two leading edge parts, leading portion crossbeam, two back segment parts and a back segment crossbeam,
Described leading edge parts and back segment crossbeam are separately positioned on the two ends of back segment parts, and back segment parts are connected by leading portion crossbeam with leading edge parts,
Described two leading edge parts are parallel to each other, and described two leading edge parts are symmetrical along the longitudinal centerline of this experimental machine wing structure, and the spacing between described two leading edge parts is adjustable arbitrarily.
2. a kind of experimental machine wing structure detachable based on the leading edge of piezoelectricity ice removal system according to claim 1, it is characterized in that described leading portion crossbeam is an integral structure, it intermediate plate comprising upper cross plate, lower cross plate and connect upper cross plate and lower cross plate, described upper cross plate lower surface and lower cross plate upper surface are parallel to each other, intermediate plate is vertically set on longitudinal center's line position of upper cross plate and lower cross plate, and the lateral cross section of described leading portion crossbeam is in " work " word shape.
3. a kind of experimental machine wing structure detachable based on the leading edge of piezoelectricity ice removal system according to claim 2, is characterized in that the coupling end of described leading edge parts and leading portion crossbeam and the coupling end of back segment parts and leading portion crossbeam are " convex " word shape respectively.
4. a kind of experimental machine wing structure detachable based on the leading edge of piezoelectricity ice removal system according to claim 3, it is characterized in that the coupling end of described leading edge parts and leading portion crossbeam is inserted in the leading portion crossbeam of " work " word shape, the upper and lower surface of the coupling end of leading edge parts and leading portion crossbeam and end face are fitted with upper cross plate, lower cross plate and intermediate plate respectively, and be connected and fixed respectively by attaching parts
The coupling end of described back segment parts and leading portion crossbeam is inserted in the leading portion crossbeam of " work " font, the upper and lower surface of back segment parts and leading portion crossbeam coupling end and end face are fitted with upper cross plate, lower cross plate and intermediate plate respectively, and are connected and fixed respectively by attaching parts.
5. a kind of experimental machine wing structure detachable based on the leading edge of piezoelectricity ice removal system according to claim 4, it is characterized in that described upper cross plate and lower cross plate are provided with several tapped bore towards a lateral edges of leading edge parts, the tapped bore of described upper cross plate and lower cross plate is corresponding up and down successively, the position that described leading edge parts and upper cross plate and lower cross plate are fitted also is provided with tapped bore, and the tapped bore of leading edge parts is consistent with the tapped bore specification of upper cross plate and lower cross plate, by screw thread precession bolt in tapped bore, leading edge parts are connected with upper cross plate and lower cross plate, described leading edge parts can be bolted with the tapped bore corresponding up and down arbitrarily of upper cross plate and lower cross plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510652738.0A CN105253305B (en) | 2015-10-10 | 2015-10-10 | A kind of detachable experiment wing structure of leading edge based on piezoelectricity deicing system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510652738.0A CN105253305B (en) | 2015-10-10 | 2015-10-10 | A kind of detachable experiment wing structure of leading edge based on piezoelectricity deicing system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105253305A true CN105253305A (en) | 2016-01-20 |
| CN105253305B CN105253305B (en) | 2017-05-31 |
Family
ID=55093340
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510652738.0A Active CN105253305B (en) | 2015-10-10 | 2015-10-10 | A kind of detachable experiment wing structure of leading edge based on piezoelectricity deicing system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105253305B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105923145A (en) * | 2016-03-25 | 2016-09-07 | 哈尔滨飞机工业集团有限责任公司 | Detachable leading edge structure of airplane |
| CN110606208A (en) * | 2019-09-26 | 2019-12-24 | 山东大学 | Giant magnetostrictive material aircraft wing ice preventing and removing device and control system and application thereof |
| CN112623187A (en) * | 2020-12-30 | 2021-04-09 | 吉林大学 | Detachable and replaceable wing-shaped trailing edge device and manufacturing method thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4458865A (en) * | 1980-12-09 | 1984-07-10 | Lockheed Corporation | Nose-torquer electro-impulse deicing systems |
| US4501398A (en) * | 1980-12-09 | 1985-02-26 | Lockheed Corporation | Beam balancer electro-impulse deicing systems |
| CN102570368A (en) * | 2012-01-16 | 2012-07-11 | 南京航空航天大学 | Traveling wave type piezoelectric material vibration anti-icing/deicing device based on in-plane or out-of-plane mode and deicing method |
| CN102941924A (en) * | 2012-11-20 | 2013-02-27 | 南京航空航天大学 | Piezoelectric elastic wave deicing method |
| US20150183530A1 (en) * | 2013-12-11 | 2015-07-02 | Airbus Defence and Space GmbH | Actuator Mounting Method and Method for Producing an Ice Protection Device as well as Mounting Device |
-
2015
- 2015-10-10 CN CN201510652738.0A patent/CN105253305B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4458865A (en) * | 1980-12-09 | 1984-07-10 | Lockheed Corporation | Nose-torquer electro-impulse deicing systems |
| US4501398A (en) * | 1980-12-09 | 1985-02-26 | Lockheed Corporation | Beam balancer electro-impulse deicing systems |
| CN102570368A (en) * | 2012-01-16 | 2012-07-11 | 南京航空航天大学 | Traveling wave type piezoelectric material vibration anti-icing/deicing device based on in-plane or out-of-plane mode and deicing method |
| CN102941924A (en) * | 2012-11-20 | 2013-02-27 | 南京航空航天大学 | Piezoelectric elastic wave deicing method |
| US20150183530A1 (en) * | 2013-12-11 | 2015-07-02 | Airbus Defence and Space GmbH | Actuator Mounting Method and Method for Producing an Ice Protection Device as well as Mounting Device |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105923145A (en) * | 2016-03-25 | 2016-09-07 | 哈尔滨飞机工业集团有限责任公司 | Detachable leading edge structure of airplane |
| CN110606208A (en) * | 2019-09-26 | 2019-12-24 | 山东大学 | Giant magnetostrictive material aircraft wing ice preventing and removing device and control system and application thereof |
| CN110606208B (en) * | 2019-09-26 | 2020-12-18 | 山东大学 | Giant magnetostrictive material aircraft wing ice preventing and removing device and control system and application thereof |
| CN112623187A (en) * | 2020-12-30 | 2021-04-09 | 吉林大学 | Detachable and replaceable wing-shaped trailing edge device and manufacturing method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105253305B (en) | 2017-05-31 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Cao et al. | Aircraft flight characteristics in icing conditions | |
| Potapczuk | Aircraft icing research at NASA Glenn research center | |
| CN105253305A (en) | Leading-edge detachable type experiment wing structure based on piezoelectric deicing system | |
| Zhao et al. | Low speed aerodynamic performance analysis of vortex lift waveriders with a wide-speed range | |
| Hann | UAV icing: Comparison of LEWICE and FENSAP-ICE for ice accretion and performance degradation | |
| Broeren et al. | Independent Effects of Reynolds and Mach Numbers on the Aerodynamics of an Iced Swept Wing | |
| CN205022847U (en) | A high performance fixed wing uavs device for cruising monitoring | |
| Gierens et al. | Aerodynamic contrails: Phenomenology and flow physics | |
| Williams et al. | Modeling, simulation, and flight tests for a T-38 talon with wing fences | |
| Joslin et al. | Synergism of flow and noise control technologies | |
| Harasani et al. | Initial conceptual design and wing aerodynamic analysis of a solar power-based UAV | |
| Wang et al. | Aeroelastic modeling and analysis of the wing/engine system of a large aircraft | |
| Solfelt et al. | CFD analysis of a T-38 wing fence | |
| CN208149590U (en) | A kind of small swing device of replaceable | |
| Like et al. | Improving aircraft aerodynamic performance with bionic wing obtained by ice shape modulation | |
| CN109263856A (en) | High aspect ratio braced wing twin fuselage multipurpose carrier vehicle aerodynamic arrangement | |
| CN115452307A (en) | Method and device for reducing blocking effect of icing wind tunnel on large-size test model | |
| Staelens et al. | Novel pitch control effectors for a blended wing body airplane in takeoff and landing configuration | |
| CN108454822A (en) | A kind of small swing device of replaceable and its change method | |
| Xie et al. | Aeroelastic analysis of flexible large aspect ratio wing. | |
| CN202279230U (en) | Flow guiding grid plate for lift augmentation of airplane | |
| Bennani | Two dimensional modelling of electrothermal ice protection systems | |
| Carter | Legacy aircraft drag reduction | |
| Kreeger et al. | Collaborative Experiments and Computations in Aircraft Icing | |
| Kuwik et al. | CFD investigation of vortex generator additions to the general atomics MQ-9 reaper |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |