CN104354852A - Upper wing adjusting device and high-speed aircraft - Google Patents
Upper wing adjusting device and high-speed aircraft Download PDFInfo
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- CN104354852A CN104354852A CN201410557661.4A CN201410557661A CN104354852A CN 104354852 A CN104354852 A CN 104354852A CN 201410557661 A CN201410557661 A CN 201410557661A CN 104354852 A CN104354852 A CN 104354852A
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Abstract
The invention relates to an upper wing adjusting device and a high-speed aircraft. The upper wing adjusting device comprises at least a lifting poker, a driving element and a controller, wherein the lifting poker is used for connecting the driving element and the upper wing and driven by the motion of the driving element to lift up and down; the driving element is connected with the controller and drives the lifting poker to motion and lift up and down with a certain height under the action of the controller; the input end of the controller is connected with a control device of the aircraft; the output end is connected with the driving element; the controller outputs control signals according to the input signals from the control device of the aircraft, and outputs the control signals to the driving element. When the flight state is changed, the controller reads in flight parameters through the control device and obtains the lifting range of the lifting poker; the upper wing height can be adjusted through the driving element to avoid the safety problem triggered by the situation that when the flight state is changed, the shock waves of the aircraft body are crossed with the upper wing; the position of the upper wing can be controlled to obtain a better aerodynamic performance of the whole aircraft.
Description
Technical field
The present invention relates to high-speed aircraft technology, especially one is put wing adjustable apparatus and high-speed aircraft.
Background technology
High-speed aircraft mainly refers to all kinds of hyprsonic or hypersonic vehicle.Usually the flight being 1.2 ~ 5.0 Mach number M calls supersonic flight; The flight that Mach number M is greater than 5.0 is called hypersonic flight.The shock wave of hypersonic flow and boundary-layer have strong interference, analysis is made to become more complicated, aircraft leading edge is subject to strong compression due to air-flow, there will be the shock 1ayer that temperature reaches several thousand degrees celsius, temperature high like this can make ambient air molecular breakdown even ionize, and brings many new problems to the Design and manufacture of aircraft.
The design of novel high speed aircraft configurations is the hot issue of current aircraft development, especially high lift, the high lift-drag ratio Configuration Design of different dynamic or unpowered glide Ultrasonic wave like speed aircraft or hypersonic vehicle.This kind of aircraft generally adopts punching engine (general consideration adopts scramjet engine under the hypersonic flight condition that flight Mach number is greater than 5), rocket engine as power.High-speed aircraft also comprises unpowered high speed glide vehicle.The aeroperformance that device proposed by the invention can be used for above-mentioned all kinds of aircraft improves.
The radical function of high-speed aircraft is long-range fast transport.Therefore under the condition ensureing large volume and load, obtaining higher aeroperformance is its very crucial index.For this problem, a kind of lift offset-type aircraft configurations scheme was once proposed, be " lift offset-type high-speed aircraft " see denomination of invention, application number is: the patent documentation of 201210558618.0, the program is mainly under the Flight Vehicle Design condition of large volume requirements, utilize body upper wall surface to compress the high pressure produced, by the mode of increase being put the wing, the lift of aircraft is obtained and significantly promote, and make the 1ift-drag ratio acquisition of aircraft increase simultaneously.
But, in practical flight process, attitude (as flying drilling angle) and the inlet flow conditions (as flight Mach number etc.) of aircraft all may change with the change of flight time, and for high speed glide vehicle, this feature is particularly evident.And along with the change of flying drilling angle and flight Mach number, position and the intensity of body compression shock also constantly change.If on put the wing position height immobilize, its aeroperformance will decline on the one hand, on the other hand body shock wave also likely with on put the wing and intersect, injure the safety of putting the wing.
Summary of the invention
The invention provides in one and put wing control apparatus and high-speed aircraft, for overcoming defect of the prior art, when mission requirements change, ensureing the safety of aircraft and good aeroperformance by height change being put the wing.
The invention provides in one and put wing control apparatus, comprising:
At least one lifting bar, for connect drive element and on put the wing, and to be elevated under the action of drive element;
Described drive element, is connected with controller, and under the effect of controller, drive action and the adjustable height of lifting bar;
Described controller, input end is connected with the control setup of aircraft, mouth is connected with described drive element, and described controller exports control signal according to connecing the incoming signal coming from the control setup of described aircraft received from input end, and exports this control signal to drive element.
Improvement further as above-described embodiment:
This device also comprises lifting bar inhibiting device;
This inhibiting device comprises a limiting component, described limiting component is provided with the limiting section moved up and down for the action of described lifting bar being defined as vertical direction.
Embodiment one as above-mentioned lifting bar inhibiting device:
Described limiting component is a riser;
Described limiting section is be arranged on the perforating that the inner quantity of described riser is equal to described lifting bar quantity, and lifting bar described in every root is all arranged in a described perforating, and with described perforating free-running fit.
Preferred version as above-described embodiment one:
Described lifting bar comprises two;
Connected by a cross bar bottom described lifting bar, described cross bar and described drive division mouth are in transmission connection;
Described riser is arranged with two described perforatings in parallel.
Embodiment two as above-mentioned lifting bar inhibiting device:
Described limiting component comprises at least one supporting seat;
Described limiting section comprises at least one guide rail be arranged on described supporting seat and at least one guide groove be arranged on described lifting bar; The length direction of described guide groove is arranged along the axis of described lifting bar;
Described guide rail is identical with the quantity of described guide groove, and the shape of the shape of described guide rail and described guide groove is suitable;
Described guide rail inserts and is arranged in described guide groove.
In embodiment two:
The cross-sectional plane of described guide groove is dovetail form, circle, ellipse, trapezoidal or T-shaped.
On the basis of above-described embodiment:
Described controller is a control chip;
Described drive element is an elevating control motor;
The mouth of described chip is electrically connected with described elevating control motor.
The present invention also provides a kind of high-speed aircraft, aircraft body, and described aircraft body has precursor, and this precursor at least upper wall surface is formed as wedge shape;
On put the wing, being arranged on described aircraft body, for catching the anticyclonic pressure formed after described precursor, thus producing lift to described aircraft body;
Put on described be also provided with between the wing and described aircraft body above-mentioned on put wing control apparatus;
The input end putting the controller of wing control apparatus on described is connected with described flying vehicles control device;
The drive element putting wing control apparatus on described is fixed on described aircraft body.
Wing control apparatus and high-speed aircraft is put on provided by the invention, the change of flight Mach number/angle of attack and the mapping relations of above putting wing upright position are obtained according to numerical value or results of wind tunnel, and these mapping relations are stored in controller, namely within the specific limits, after given above-mentioned flight parameter, controller can export control signal numerical value to drive element, and drive element drives lifting bar to rise or declines, and final drive puts wing lifting to desired location; In practical flight, when flight parameter changes, correlation parameter is by the sensor collection of flying vehicles control device, by input or feed-in controller, after controller obtains input parameter, obtain the position numerical value putting the wing based on aforementioned mapping calculation, export drive element to; Drive element is elevated according to given numerical value, is driven and puts wing rising or decline in desired locations, complete and be once elevated flow process by lifting bar.Main purpose of the present invention is large volume, high lift, high lift-drag ratio demand for high-speed aircraft, when flying condition (flight Mach number, the angle of attack etc.) changes, ensure the safety of aircraft and good aeroperformance by height change being put the wing.The present invention can be applicable to aerodynamic arrangement and the Configuration Design of all kinds of high-speed aircraft, especially effective to the hypersonic aircraft with large volume requirements.
Detailed description of the invention
As shown in Fig. 1, Fig. 3, Fig. 4, the embodiment of the present invention provides in one and puts wing control apparatus, comprises at least one lifting bar 3, drive element 4 and controller 5; Lifting bar 3 for connect drive element 4 and on put the wing 6, and put the wing 6 and be elevated on driving under the action of drive element; Drive element 4 is connected with controller 5, and under the effect of controller 5, drive action and the adjustable height of lifting bar 3; Controller 5 input end is connected with flying vehicles control device, controller 5 mouth is connected with drive element 4, controller 5 exports control signal according to the incoming signal coming from flying vehicles control device received from its input end, and exports this control signal to drive element 4.This control signal for controlling the operational factor of drive element 4, and eventually through lifting bar by put the wing and move to desired location.
Drive element 4 is an elevating control motor, specifically can adopt linear motor or stepper motor, controller 5 can adopt control chip, the mouth of control chip is electrically connected with elevating control motor, the change of flight Mach number/angle of attack and the mapping relations of above putting wing upright position are obtained according to numerical value or results of wind tunnel, and these mapping relations are stored in control chip, namely within the specific limits, after given above-mentioned flight parameter, control chip can find the upright position of putting the wing vertical, according to change and the aforementioned mapping relations of flight parameter, calculate and put wing displacement in vertical direction, this displacement exports to linear motor as control signal the most at last, in practical flight, when flight parameter changes, correlation parameter passes through the sensor collection of flying vehicles control device, by input feed-in control chip, and control chip and then acquisition flight parameter.
Certain drive element 4 also can adopt traditional electrical motor, because of conventional motors output is torque, this just needs the driving device arranged being converted to straight-line motion between electrical motor and lifting bar, specifically can adopt the structure such as screw-driven or wheel and rack transmission, when adopting above-mentioned conventional motors and driving device, just need control chip according to above putting wing displacement in vertical direction, the rotational parameters of electrical motor and the gear ratio calculation of driving device go out the rotational angle of electrical motor, this rotational angle exports to electrical motor using the form of impulse singla as control signal the most at last, control motor rotational angle degree, and finally make to put the wing and carry out rising or declining according to the above-mentioned displacement calculated.
Fig. 3, Fig. 4 sets forth a kind of on put front view and the birds-eye view of wing vertical position adjustment means.Wherein, body is mainly used in holding the associated load of aircraft, fuel and device etc., and lower compressing surface is in order to produce the part lift of aircraft.These two parts design with the demand of practical flight device, may adopt different profiles, but once namely maintain static after having designed.
The main working process of this control apparatus is summarized as follows:
1) obtain the change of flight Mach number/angle of attack and the mapping relations of above putting wing upright position according to numerical value or results of wind tunnel, and above-mentioned mapping relations are stored in control chip.Namely within the specific limits, after given above-mentioned flight parameter, the output signal of control chip is the upright position of putting the wing;
2) in practical flight, when flight parameter changes, correlation parameter by the sensor collection of aircraft, by input feed-in control chip;
3), after control chip obtains input parameter, obtain the position numerical value putting the wing based on aforementioned mapping calculation, export this elevating control motor;
4) elevating control motor is elevated according to given numerical value, is driven and puts wing rising or decline in desired locations, complete and be once elevated flow process by lifting bar.
Below the principle of above putting wing control apparatus is described:
See Fig. 1, after flowing through at a high speed the compression of aircraft body leading edge wedge shape 1, can produce one compression shock, the parameters such as its Angle of Shock Waves and compression strength and free stream Mach number, flying drilling angle and the leading edge angle of wedge are relevant.After flying condition is given, the shock-wave spot produced is as shown in the dotted line 2 in Fig. 1.The design (specifically can see denomination of invention for " lift offset-type high-speed aircraft ", application number is the patent documentation of 201210558618.0) of catching the wing according to high pressure can obtain put the wing position and length as shown in Fig. 13.Such as, and when after mission requirements change, when flight Mach number increases, shock-wave spot is changed to 2' by the position 2 in Fig. 1, if put the invariant position of the wing now, then shock wave with on put the wing generation intersected.In this case, shock wave may produce the safety of above putting the wing in upper intersection of putting the wing and threaten on the one hand, another aspect is put the part upper and lower surface of the wing before shock wave and all can see far field static pressure as, thus do not contribute lift, this also reduces the performance of putting the wing to a certain extent.
If by put the wing Position Design be that vertical dimension is adjustable, still for Fig. 1, when inlet flow conditions changes (such as Mach number increase), by on put the wing upright position regulate certain distance downwards, to the 3' position in Fig. 1, after the leading edge that then can ensure to put the wing is hidden in shock wave, and fully can catch the higher-pressure region after shock wave, thus avoid the problems referred to above.
The embodiment of the present invention is according to flight attitude and flight environment of vehicle parameter, rational change is put the height of the wing, not only can ensure the safety of aircraft, and all can ensure that aircraft has good aeroperformance when the flight Mach number of aircraft, flying drilling angle change.
As the preferred version of above-described embodiment, this device also comprises a lifting bar position limiting structure:
This lifting bar position limiting structure comprises a limiting component, limiting component is provided with the limiting section moved up and down for the action of lifting bar being defined as vertical direction.
Limiting component is for connecting limiting section and aircraft body, and limiting section here can coordinate separately the position-limiting action of lifting bar vertical direction with lifting bar; Such as limiting section is the sleeve that a cross-sectional plane is identical with lifting bar shape of cross section, and lifting bar is arranged in sleeve, and sleeve is fixed on aircraft body by limiting component, and like this, lifting bar just can only carry out along the axis of sleeve when being elevated; Limiting section also can coordinate the position-limiting action jointly completing lifting bar vertical direction with the concrete structure be arranged on lifting bar, such as limiting section is a guide rail, lifting bar is established a shape and the suitable guide groove of guide rail vertically, guide rail is arranged in guide groove, guide rail is fixed on aircraft body by limiting component, and lifting bar can only the direction of axially guide groove move; Limiting section can also be the claw of more than three, all claws enclose space ringwise jointly, lifting bar is arranged in the annular space that claw is enclosed to form jointly, and claw be linear contact lay outside lifting bar or face contacts, claw is all fixed on aircraft body by limiting component, and lifting bar can only move along the length direction of claw.In above-mentioned several scheme, the movement movement of lifting bar be finally defined as in vertical direction all can be reached by the concrete setting arranging limiting section, avoid existing in other directions the displacement error that displacement causes putting the wing, further increase put the wing and regulate accuracy, the safety of aircraft and aeroperformance.
Embodiment one as above-mentioned lifting bar position limiting structure:
See Fig. 3, Fig. 4, limiting component is a riser 7;
Limiting section is be arranged on the perforating that the inner quantity of riser 7 is equal to lifting bar quantity, and every root lifting bar 3 is all arranged in a perforating, and lifting bar 3 and the equal free-running fit of perforating.Be fixed on aircraft body 1 bottom riser 7, drive element 4 and controller 5 are all arranged on the inside of aircraft body 1, on put the wing 6 for axially symmetric structure, and axis of symmetry was positioned on the vertical plane of the central axis of aircraft body, riser 7 is arranged on to be put bottom the wing 6 and to arrange along this vertical plane, perforating is arranged along the vertical direction of riser, like this, can ensure that lifting bar 3 can only move in the vertical direction.
In embodiment one:
The quantity of lifting bar 3 can according to aircraft and on put the concrete shape of the wing and structure is arranged, the lifting bar 3 in the present embodiment is two; Connected by a cross bar 31 bottom lifting bar 3, cross bar 31 is in transmission connection with the mouth of drive element 4; Riser 7 is arranged with two perforatings in parallel.
Being in transmission connection here comprise connected by coupler, key connects or by types of attachment such as bolt assembly removably connect, wear empty be arrangeding in parallel and ensure that two lifting bars 3 can lifting moving in vertical direction smoothly.
In the present embodiment, the shape of lifting bar 3 needs with the shape of perforating suitable, and such as lifting bar 3 is cylindrical, and perforating is circular port; Lifting bar 3 is square, then perforating is square opening; The area of contact of abundant increase lifting bar and perforating, in the course of action of lifting bar 3, stability is higher.
During riser 7 thicker (thickness is greater than the sectional dimension of lifting bar), it is inner that perforating can be set directly at riser 7; During the thinner thickness (thickness is less than or equal to the sectional dimension of lifting bar) of riser 7, separately can establish outer sleeve, utilize the endoporus of sleeve as perforating, riser 7 is fixedly connected with outer sleeve.
Put in Fig. 3 and Fig. 4 wing control apparatus mainly comprise put the wing 6, riser 7, outer sleeve 8, lifting bar 3, elevating control motor and control chip composition.Function and the interrelation of each parts are as follows: putting the wing 6 1) is the major parts producing lift, and these parts are fixedly connected with lifting bar 3; 2) riser 7 is in order to hold outer sleeve 8, and plays a supportive role to outer sleeve 8, riser 7 apical position simultaneously as limiting device, in order to limit lifting bar 3 and above to put the extreme lower position of the wing 6; 3) elevating control motor is in order to control the lifting position of lifting bar 3, and it is connected by transmission device with lifting bar 3, and wherein, transmission device has more matured product, as spiral lifting bar etc., repeats no more herein; 4) control chip is mainly used in exporting lifting bar 3 upright position control data according to flight condition parameter, to determine lifting bar 3 and above to put the upright position of the wing 6.
Embodiment two as above-mentioned lifting bar position limiting structure:
See Fig. 5, Fig. 6, limiting component comprises two supporting seats 9; Two supporting seats 9 are all fixed on aircraft body 1, and limiting section comprises at least one guide rail 91 be arranged on supporting seat 9 and at least one guide groove 32 be arranged on lifting bar 3; Guide rail 91 is identical with the quantity of guide groove 32, and the shape of the shape of guide rail 91 and guide groove 32 is suitable; Guide rail 91 inserts or partial insertion is arranged in guide groove 32.The length direction of guide groove 32 is along the linearly setting of axis of lifting bar 3.
In embodiment two:
The cross-sectional plane of guide groove 32 is dovetail form, circle, ellipse, trapezoidal or T-shaped etc.
When changing below by way of a simple two dimensional configurations check flight Mach number, above put the change of wing position to flight vehicle aerodynamic performance impact, and then the effect of inspection apparatus of the present invention.For simplify calculate, below two-dimentional example only comprise body and on put the wing.
Fig. 7 gives the schematic diagram of inspection example, and the part that wherein quadrangle ABCE surrounds is body, and above putting wing forward terminal is D point, and trailing edge is E' point (identical with the abscissa of E point), and straight line AF is shock line.
The initial parameter of this example is given following (following unit is mm):
Body length AE is 1000, and body corner position (B point coordinate) is (800,135), and trailing edge height CE is 81.8, and body compression angle (∠ BAE) is 10 degree.Initial designs Mach 2 ship 6.By calculating, can obtain Angle of Shock Waves (∠ FAE) is 17.6 degree.Under the design condition of Mach number 6, by obtaining without sticky numerical modelling the aerodynamic parameter changing configuration be: lift coefficient C
l=0.05698, drag coefficient C
d=0.01227,1ift-drag ratio L/D=4.64.
Adopt same on put wing position, when flight Mach number changes into 5, aerodynamic parameter is lift coefficient C
l=0.04469, drag coefficient C
d=0.01333,1ift-drag ratio L/D=3.35.When flight Mach number changes into 7, aerodynamic parameter is lift coefficient C
l=0.05442, drag coefficient C
d=0.01313,1ift-drag ratio L/D=4.14.Meanwhile, when Mach number 7, Angle of Shock Waves (∠ FAE) is 16.4 degree, with on put the wing and produce and intersect.
Based on above putting the adjustable thinking in wing upright position, when flight Mach number 5, by put on wing upright position and rise 15mm, namely vertical dimension is 195mm, then aerodynamic parameter becomes lift coefficient C
l=0.05665, drag coefficient C
d=0.01463,1ift-drag ratio L/D=3.87, the 1ift-drag ratio comparatively front increase 15.6% of position adjustments.Equally, when flight Mach number 7, by put wing upright position decline 12mm, namely vertical dimension is 168mm, then aerodynamic parameter becomes lift coefficient C
l=0.05401, drag coefficient C
d=0.01084,1ift-drag ratio L/D=4.98, the 1ift-drag ratio comparatively front increase 20.3% of position adjustments.And now shock line with on put the wing without intersecting.
Can be proved by above-mentioned example, when mission requirements change, the 1ift-drag ratio of aircraft can be made to obtain by the change of above putting wing upright position and significantly promote, and avoid shock wave and the appearance of above putting wing crossover phenomenon simultaneously.
The embodiment of the present invention also provides a kind of high-speed aircraft, as shown in Figure 2, at least comprise aircraft body 1, on put the wing 6 and on put wing control apparatus 10, aircraft body 1 has precursor, and this precursor at least upper wall surface is formed as wedge shape; On put the wing 6 and be arranged on aircraft body 1, for catching the anticyclonic pressure formed after precursor, thus produce the lift to aircraft body 1; On put wing control apparatus 10 and be arranged on and put between the wing 6 and aircraft body 1, this is put wing control apparatus 10 and put wing control apparatus on described in above-mentioned any embodiment; Wherein, as shown in figures 1 to 6, the input end of controller 5 above putting wing control apparatus is connected with the control setup of aircraft, for obtaining flight parameter; On put wing control apparatus drive element 4 be fixed on aircraft body 1 or in aircraft body 1.
Its basic functional principle is: above put the wing and utilize body to produce higher-pressure region after shock wave to produce lift.When state of flight changes (as flight Mach number, flying drilling angle etc.) sensor reads in flight attitude and environmental parameter signals, pass to auxiliary control circuit, obtain the heave amplitude of lifting bar, and then regulate the level height of putting the wing by controlling motor.When such one side can avoid state of flight to change body shock wave with above put the wing and intersect and the safety problem that causes, the position on the other hand by controlling to put the wing can obtain better complete machine aeroperformance.
Accompanying drawing explanation
Fig. 1 for the embodiment of the present invention provide on put the principle of design figure of wing control apparatus;
The 3 dimensional drawing of the high-speed aircraft that Fig. 2 provides for the embodiment of the present invention;
Fig. 3 for the embodiment of the present invention one provide on put wing control apparatus and the mounting structure schematic diagram with aircraft body thereof;
Fig. 4 is the birds-eye view of Fig. 3;
Fig. 5 for the embodiment of the present invention two provide on put wing control apparatus and the mounting structure schematic diagram with aircraft body thereof;
Fig. 6 is the birds-eye view of Fig. 5;
The inspection example schematic diagram of the high-speed aircraft that Fig. 7 provides for the embodiment of the present invention.
Claims (8)
1. put a wing control apparatus on, it is characterized in that, comprising:
At least one lifting bar, for connect drive element and on put the wing, and to be elevated under the action of drive element;
Described drive element, is connected with controller, and under the effect of controller, drive action and the adjustable height of lifting bar;
Described controller, input end is connected with the control setup of aircraft, mouth is connected with described drive element, and described controller exports control signal according to connecing the incoming signal coming from the control setup of described aircraft received from input end, and exports this control signal to drive element.
2. put wing control apparatus on according to claim 1, it is characterized in that:
This device also comprises lifting bar inhibiting device;
This inhibiting device comprises a limiting component, described limiting component is provided with the limiting section moved up and down for the action of described lifting bar being defined as vertical direction.
3. put wing control apparatus on according to claim 2, it is characterized in that:
Described limiting component is a riser;
Described limiting section is be arranged on the perforating that the inner quantity of described riser is equal to described lifting bar quantity, and lifting bar described in every root is all arranged in a described perforating, and with described perforating free-running fit.
4. put wing control apparatus on according to claim 3, it is characterized in that:
Described lifting bar comprises two;
Connected by a cross bar bottom described lifting bar, described cross bar and described drive division mouth are in transmission connection;
Described riser is arranged with two described perforatings in parallel.
5. put wing control apparatus on according to claim 2, it is characterized in that:
Described limiting component comprises at least one supporting seat;
Described limiting section comprises at least one guide rail be arranged on described supporting seat and at least one guide groove be arranged on described lifting bar; The length direction of described guide groove is arranged along the axis of described lifting bar;
Described guide rail is identical with the quantity of described guide groove, and the shape of the shape of described guide rail and described guide groove is suitable;
Described guide rail inserts and is arranged in described guide groove.
6. put wing control apparatus on according to claim 5, it is characterized in that:
The cross-sectional plane of described guide groove is dovetail form, circle, ellipse, trapezoidal or T-shaped.
7. according to claim 1-6 arbitrary described on put wing control apparatus, it is characterized in that:
Described controller is a control chip;
Described drive element is an elevating control motor;
The mouth of described chip is electrically connected with described elevating control motor.
8. a high-speed aircraft, comprising:
Aircraft body, described aircraft body has precursor, and this precursor at least upper wall surface is formed as wedge shape;
On put the wing, being arranged on described aircraft body, for catching the anticyclonic pressure formed after described precursor, thus producing lift to described aircraft body; It is characterized in that:
Put on described be also provided with between the wing and described aircraft body as arbitrary in claim 1-7 as described on put wing control apparatus;
The input end putting the controller of wing control apparatus on described is connected with described flying vehicles control device;
The drive element putting wing control apparatus on described is fixed on described aircraft body or is fixed in aircraft body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410557661.4A CN104354852B (en) | 2014-10-20 | 2014-10-20 | Upper wing adjusting device and high-speed aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410557661.4A CN104354852B (en) | 2014-10-20 | 2014-10-20 | Upper wing adjusting device and high-speed aircraft |
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| CN104354852A true CN104354852A (en) | 2015-02-18 |
| CN104354852B CN104354852B (en) | 2017-02-22 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106184719A (en) * | 2016-09-08 | 2016-12-07 | 中国人民解放军国防科学技术大学 | A kind of porous flow dynamic control device being applied to hypersonic motor-driven reentry vehicle |
| CN109436298A (en) * | 2018-08-30 | 2019-03-08 | 江西冠通用飞机有限公司 | A kind of tailplane |
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| CN201677938U (en) * | 2010-05-10 | 2010-12-22 | 邱金和 | Device for improving buoyancy |
| CN103029830A (en) * | 2012-12-20 | 2013-04-10 | 中国科学院力学研究所 | Double waverider splicing air suction type hypersonic aircraft forebody and design method thereof |
| CN103350750A (en) * | 2012-12-20 | 2013-10-16 | 中国科学院力学研究所 | Lift compensation type high speed aircraft |
| US20130291753A1 (en) * | 2012-05-03 | 2013-11-07 | Jonathan P. Nikkel | Deployable lifting surface for air vehicle |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5417393A (en) * | 1993-04-27 | 1995-05-23 | Hughes Aircraft Company | Rotationally mounted flexible band wing |
| CN201677938U (en) * | 2010-05-10 | 2010-12-22 | 邱金和 | Device for improving buoyancy |
| US20130291753A1 (en) * | 2012-05-03 | 2013-11-07 | Jonathan P. Nikkel | Deployable lifting surface for air vehicle |
| CN103029830A (en) * | 2012-12-20 | 2013-04-10 | 中国科学院力学研究所 | Double waverider splicing air suction type hypersonic aircraft forebody and design method thereof |
| CN103350750A (en) * | 2012-12-20 | 2013-10-16 | 中国科学院力学研究所 | Lift compensation type high speed aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106184719A (en) * | 2016-09-08 | 2016-12-07 | 中国人民解放军国防科学技术大学 | A kind of porous flow dynamic control device being applied to hypersonic motor-driven reentry vehicle |
| CN109436298A (en) * | 2018-08-30 | 2019-03-08 | 江西冠通用飞机有限公司 | A kind of tailplane |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104354852B (en) | 2017-02-22 |
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