CN205699447U - Telecontrolled aircraft - Google Patents
Telecontrolled aircraft Download PDFInfo
- Publication number
- CN205699447U CN205699447U CN201620292168.9U CN201620292168U CN205699447U CN 205699447 U CN205699447 U CN 205699447U CN 201620292168 U CN201620292168 U CN 201620292168U CN 205699447 U CN205699447 U CN 205699447U
- Authority
- CN
- China
- Prior art keywords
- elevator
- landing
- landing mode
- telecontrolled aircraft
- actuator
- 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.)
- Expired - Fee Related
Links
Landscapes
- Toys (AREA)
Abstract
The application provides a kind of telecontrolled aircraft, and wherein telecontrolled aircraft includes: elevator；Control the actuator of elevator, wherein, in descent, actuating mechanism controls telecontrolled aircraft is changed in the first landing mode and the second landing mode back and forth, and wherein in the second landing mode, the deflection angle of elevator is more than the deflection angle of the elevator of the first landing mode.The telecontrolled aircraft of the application significantly reduces the requirement to landing place, and the impulsive force relatively big damage to telecontrolled aircraft when avoiding telecontrolled aircraft to land.
Description
Technical field
The application relates to aircraft field, more specifically for, relate to a kind of telecontrolled aircraft.
Background technology
Telecontrolled aircraft is a kind of aircraft that can fly with distant control.It is widely used in taking photo by plane, load-carrying, model plane and army
With etc. field.
Telecontrolled aircraft typically requires user and remotely controls flight.And when telecontrolled aircraft is landed, telecontrolled aircraft typically uses downslide
Landing, glide landing needs broad landing place, and to have good spatial domain around place of landing, can not around place
There is the barrier such as towering buildings and trees.
Summary of the invention
One purpose of the application is to provide a kind of telecontrolled aircraft, including: elevator；Control the actuator of elevator,
Wherein, in descent, actuating mechanism controls telecontrolled aircraft is changed in the first landing mode and the second landing mode back and forth,
Wherein in the second landing mode, the deflection angle of elevator is more than the deflection angle of the elevator of the first landing mode.
In certain embodiments, described actuator includes the first actuator and the second actuator.
In certain embodiments, described actuator quantity is 1.
In certain embodiments, described actuator comprises drive mechanism, and described drive mechanism is connected to elevator.
In certain embodiments, described drive mechanism includes rocking arm and connecting rod.
In certain embodiments, the arm of force that performs of the first actuator is more than the execution arm of force of the second actuator.
In certain embodiments, described elevator is flying tail type elevator.
In certain embodiments, the elevator angle degree of the second landing mode is more than 20 °.
In certain embodiments, the elevator angle degree of the first landing mode is between ± 20 °.
In certain embodiments, described elevator is part horizontal tail type elevator.
In certain embodiments, the elevator angle degree of the second landing mode is more than 40 °.
In certain embodiments, the elevator angle degree of the first landing mode is between ± 40 °.
In certain embodiments, described first landing mode is glide landing pattern.
In certain embodiments, described second landing mode is prompt drop pattern.
It is more than the general introduction of the application, may have the situation of simplification, summary and omissions of detail, therefore those skilled in the art
It should be appreciated that this part is only Illustrative, and it is not intended to limit the application scope by any way.This general introduction portion
Point both it is not intended to determine key feature or the essential feature of claimed subject, is also not intended to be used as to determine claimed
The supplementary means of the scope of theme.
Accompanying drawing explanation
Be combined by following description and appending claims and with accompanying drawing, it will be more fully clearly understood that the application
The above and other feature of content.It is appreciated that these accompanying drawings depict only some embodiments of teachings herein, therefore
It is not considered as the restriction to teachings herein scope.By using accompanying drawing, teachings herein will obtain definitely and in detail
Carefully illustrate.
Fig. 1 shows the flying tail type elevator structure schematic diagram of the application one embodiment；
Fig. 2 shows that the flying tail type elevator of the application one embodiment is at the first landing mode and the second landing mode
Position view；
Fig. 3 shows that the elevator of the application one embodiment is at the position view declining state；
Fig. 4 shows the elevator position view in propradation of the application one embodiment；
Fig. 5 shows the elevator position view in prompt drop state of the application one embodiment；
Fig. 6 shows that the elevator of the application one embodiment is at the flat position view flying state；
Fig. 7 shows that the elevator of the application one embodiment is at propradation and the position view of decline state；
Fig. 8 shows the elevator prompt drop view of the application one embodiment.
Detailed description of the invention
In the following detailed description, with reference to constitute part thereof of accompanying drawing.In the accompanying drawings, similar symbol generally represents
Similar ingredient, unless otherwise indicated by context.Illustrative reality described in detailed description, drawings and claims
The mode of executing is not intended to limit.In the case of the spirit or scope without departing from the theme of the application, other can be used to implement
Mode, and other changes can be made.Be appreciated that can in the application general that describe, illustrate in the accompanying drawings
The various aspects of the teachings herein illustrated carry out multiple differently composed configuration, replace, combine, design, and all these
Constitute a part for teachings herein the most clearly.
Existing telecontrolled aircraft generally uses glide landing pattern, and in glide landing pattern, telecontrolled aircraft uses relatively small angle
(e.g., less than 20 degree) uniform descent of bowing, in some practical operations, it will usually the gliding angle using the only several years is low
Head uniform descent, thus cause downslide path longer, and need the landing place of larger area.Additionally, glide landing is wanted
Performance and meteorological condition at that time according to telecontrolled aircraft accurately estimate downslide path, in addition it is also necessary to operator accurately handles distant
Control aircraft glides according to preferable path and flies.Glide landing requires higher for operator.And requirement during glide landing
The barrier such as towering buildings and trees can not be had around broad landing place and landing place.In reinforced concrete forest
City, the landing place of glide landing is very difficult to look for.
To this end, some telecontrolled aircraft uses prompt drop pattern.Prompt drop pattern is to make the elevator of telecontrolled aircraft irreversible in big angle
Degree tilts, and telecontrolled aircraft itself declines along the most vertical track with flat-hand position, until landing.Although prompt drop pattern can
To reduce the requirement to landing place, but, the requirement to telecontrolled aircraft is the highest, the telecontrolled aircraft ground connection of vertical landing
Time impulsive force the biggest, it is desirable to the structure of telecontrolled aircraft fuselage and the impact resistance of airborne equipment are the highest.Use prompt drop mould
Manipulation to telecontrolled aircraft when formula can simplify the estimation to descent path and decline.But just enter prompt drop pattern telecontrolled aircraft
Control command can not be performed again, it is impossible to revise descent path.And during in order to avoid prompt drop ground connection, impulsive force to telecontrolled aircraft and
The destruction of the equipment that telecontrolled aircraft is built-in, telecontrolled aircraft would generally increase the more structure intensity with raising telecontrolled aircraft, and this is again
Cause telecontrolled aircraft deadweight to increase, reduce the performance of telecontrolled aircraft.
At an aspect of the application, the application provides the landing method of the telecontrolled aircraft of an embodiment, including: landing
Cheng Zhong, telecontrolled aircraft is controllably changed in the first landing mode and the second landing mode back and forth, wherein in the second landing mode
The deflection angle of elevator is more than the deflection angle of the elevator of the first landing mode.Embodiments of the invention are by the first fall
Stamping die formula and the second landing mode change one or many back and forth, significantly reduces the requirement to landing place, and keep away
Exempt from the relatively big damage to telecontrolled aircraft of impulsive force during telecontrolled aircraft landing.
In certain embodiments, descent includes two stages, and wherein, the landing mode in a kind of stage is the first landing mould
Formula, the landing mode in another kind of stage is the second landing mode.In further embodiments, descent include three kinds of stages,
Four kinds of stages or more kinds of stage, at least one of which stage is the first landing mode, and at least one stage is the second landing mould
Formula.Controllably change back and forth in the first landing mode and the second landing mode, more preferably to reduce, landing place is wanted
Damage to telecontrolled aircraft when asking and avoid landing.
In certain embodiments, the first landing mode can be glide landing pattern, and the second landing mode can be other fall
Stamping die formula.In certain embodiments, the second landing mode can be prompt drop pattern, and the first landing mode can be other fall
Stamping die formula.In certain embodiments, described first landing mode is glide landing pattern and described second landing mode is prompt drop
Pattern.
As some optional embodiments, including in the descent in two kinds and two or more stages, first in descent
The landing mode in the stage of kind can be prompt drop pattern.The landing mode in the last a kind of stage in descent can be the fall that glides
Stamping die formula.
In certain embodiments, elevator is steerable airfoil portion in telecontrolled aircraft tailplane, and its effect is to aircraft
Carry out pitch control, control aircraft and land with the first landing mode or the second landing mode.Wherein, the second landing mode rises
The deflection angle of fall rudder is more than the deflection angle of the elevator of the first landing mode.In certain embodiments, the second landing mode
It is relatively close to vertical landing, and the first landing mode can be along certain angle glide landing such that it is able to adjusting remote effectively
Speed during aircraft decline and site requirements, so that in descent, reduce landing site requirements and drop impact
Power is little.
In certain embodiments, elevator at the deflection angle of the first landing mode can be between ± 5 °, ± 10 ° between,
Between ± 20 °, ± 30 ° between or ± 40 ° between；Elevator can be to be more than at the deflection angle of the second landing mode
20 °, more than 30 °, more than 40 °, more than 50 °, more than 60 ° or more than 70 °.
Refer to Fig. 1 and Fig. 2, in certain embodiments, elevator 102 is the elevator of flying tail type, Quan Dongping
The elevator of tail type is that horizontal stabilizer is integrated with elevator and can make the aerofoil of unitary rotation around own torque.One
In a little embodiments, the whole tailplane of telecontrolled aircraft is an entirety.In certain embodiments, the one of actuator 140
End includes that drive mechanism 106, drive mechanism 106 are coupled to elevator 102.Actuator 140 is by drive mechanism 106
Elevator 102 is allowed to rotate around rotation axis XX '.Thus control the aerodynamic force suffered by elevator and produce the direction of moment, control
Telecontrolled aircraft processed rises or falls.
As in figure 2 it is shown, in certain embodiments, when elevator 102 is flying tail type elevator, the first landing mould
The elevator angle degree of formula is between ± 20 °, and the elevator angle degree of the second landing mode is more than 20 °.Handle and rise
Fall rudder upward deflects more than 20 ° so that telecontrolled aircraft enters the second landing mode.When elevator upward deflects more than 20 °
(such as, 30 ° or 40 °), telecontrolled aircraft can enter advanced stall, so that telecontrolled aircraft enters the second landing mode,
Telecontrolled aircraft is caused to decline along the most vertical track.Under the second landing mode, telecontrolled aircraft can avoid the obstacle of surrounding
Thing.And when telecontrolled aircraft drops to safe altitude under the second landing mode, telecontrolled aircraft exits from the second landing mode,
Being transformed into the first landing mode, now, telecontrolled aircraft is substantially in the middle of landing place, and the highest, glide process is shorter,
Both will not fly out place, can suitably revise again course line, thus ensure telecontrolled aircraft safe landing.As some embodiments,
The elevator angle degree of the first landing mode is between ± 20 °.It should be noted that under the first landing mode, handle
Elevator upward deflects (0 °～+20 °), and the aerodynamic force suffered by elevator will produce the moment come back, remote control
Aircraft comes back upwards；Handling elevator and deflect down (-20 °～0 °), the aerodynamic force suffered by elevator will produce one
The moment bowed, telecontrolled aircraft is bowed downwards.In certain embodiments, described first landing mode is glide landing pattern,
In certain embodiments, described second landing mode is prompt drop pattern.
In certain embodiments, when the elevator that elevator 102 is flying tail type, decline process can include two
In the stage, wherein the first stage uses prompt drop pattern, makes elevator upward deflect more than 20 °, drop to safety when the first stage
Time highly, being converted to second stage, second stage uses glide landing pattern, elevator is deflected to ± 20 ° between.Need
Illustrating, in the prompt drop pattern of first stage, the deflection angle of elevator can be fixing, and under second stage
In sliding landing mode, the deflection angle of elevator can be variable.In certain embodiments, can be according to the height of safe altitude
Degree, the speed declined and acceleration, wind-force, wind direction, landing place size, adjust the deflection angle of elevator in second stage
Degree, so that impulsive force is little during telecontrolled aircraft landing.
In certain embodiments, it can be more than 40 ° that the second landing mode elevator upward deflects, deep with more favourable entrance
Degree stall.It should be noted that in certain embodiments, it is the biggest more have that the elevator of the second landing mode upward deflects angle
Profit enters advanced stall.But, the elevator of the second landing mode upward deflects angle needs the normal use in telecontrolled aircraft
In the range of, such as, the elevator of the second landing mode upward deflects angle less than 90 °, so as at conversion landing mode
Time be effectively transformed into the first landing mode.In certain embodiments, the second landing mode elevator upward deflects can be 40
° be conducive to entering advanced stall and the first landing mode can being quickly transferred to (including 40 ° and 70 °) between 70 °.
In certain embodiments, during declining, telecontrolled aircraft can be between the first landing mode and the second landing mode
Toggle once, twice, three time, four times or more times, etc..In certain embodiments, can be high according to safety
Height, the speed of decline and the acceleration of degree, wind-force, the number of stages of wind direction selection decline process.As some demonstration example,
When the comparison that safe altitude is arranged is high, it is few that the number of stages of decline process can be arranged.As some demonstration example,
When wind-force is bigger, it is more that the number of stages of decline process can be arranged.In certain embodiments, there is multiple stage
During decline, could be arranged to falling head identical it can also be provided that falling head different each stage.At some
In embodiment, during there is the decline in multiple stage, each stage could be arranged to identical can also set fall time
It is set to fall time different.In certain embodiments, during there is the decline in multiple stage, could be arranged to some rank
The height that section identical, some stage fall time declines is identical.So that the impulsive force declined is less and site requirements is low.
In certain embodiments, safe altitude can rule of thumb be arranged, it is also possible to obtains according to reality test.As some
Embodiment, safe altitude arrange can according to the flying height of telecontrolled aircraft, the speed of decline, acceleration, wind-force and
/ or wind direction be adjusted.
In further embodiments, elevator is part horizontal tail type elevator.In some telecontrolled aircraft, tailplane bag
Including fixed part and movable part, movable part can be rotated about axis, and fixed part is non-rotatable.Movable part constitutes part horizontal tail
Elevator.In descent, telecontrolled aircraft is controllably changed in the first landing mode and the second landing mode back and forth, its
In inclined more than the part horizontal tail elevator of the first landing mode of the deflection angle of part horizontal tail elevator in the second landing mode
Gyration.
In certain embodiments, the elevator of telecontrolled aircraft accounts for the area percentage of tailplane and can enter within a large range
Row selects.It can be 10%-85% that such as part horizontal tail elevator accounts for the area percentage of tailplane.In certain embodiments,
When the area percentage that part horizontal tail elevator accounts for tailplane is 10%-45%, the elevator of the first landing mode is deflected to
Between ± 40 °.The elevator of the second landing mode is deflected to more than 40 °.In certain embodiments, elevator accounts for horizontal tail
The area percentage of the wing is the biggest, and the elevator regulation angle of the first landing mode is the least.In further embodiments, liter is worked as
Fall rudder accounts for the area percentage of tailplane when being 45%-85%, the elevator of the first landing mode is deflected to ± 30 ° between.
The elevator of the second landing mode is deflected to more than 30 °.
Refer to Fig. 3, Fig. 4 and Fig. 5, in certain embodiments, elevator 112 is carried out under two actuating mechanism controls
First landing mode and the conversion of the second landing mode.Wherein, the first actuator can be lifting actuator 121, the
Two actuators can be prompt drop actuator 122；As some embodiments, flying tail elevator 112 has horizontal tail and shakes
Arm 114, horizontal tail rocking arm 114 is connected to one end of connecting rod 116.The other end of connecting rod 116 is connected to the first of rocking arm 118
End 120, lifting actuator 121 is connected to rocking arm 118 at the first junction point, and prompt drop actuator 122 connects second
Point is connected to rocking arm 118, and the execution arm of force D1 of lifting actuator 121 is more than the execution arm of force of prompt drop actuator 122
D2, say, that the distance (D1) of the first junction point distance rocking arm 118 first end 120 is shaken more than the second junction point distance
The distance (D2) of arm 118 first end 120.In certain embodiments, lifting actuator 121 can be as airflight
Time elevator 112 controlling organization, it is also possible to as the controlling organization of elevator 112 during glide landing pattern.As some
Embodiment, lifting actuator 121, according to the instruction during flight received, controls elevator 112 inclined in less angle
Turn.Such as, between ± 20 °, thus regulate state of flight to adapt to the flying condition such as wind-force and wind direction.Real as some
Execute example, when elevator 112 is deflected to 0 ° (refer to the inflection point of elevator shown in phantom in Fig. 3 and Fig. 4),
Telecontrolled aircraft flies state for flat；Elevator 112 is deflected between 0 °～-20 ° (refer to the elevator shown in solid line in Fig. 3
Inflection point) time, telecontrolled aircraft is decline state；Elevator 112 is deflected between 0 °～+20 ° (refer in Fig. 4
The inflection point of the elevator shown in solid line) time, telecontrolled aircraft is propradation.In certain embodiments, perform when prompt drop
Mechanism 122 receives prompt drop instruction, and elevator 112 is under the control of prompt drop actuator 122, and being deflected to (please more than 20 °
With reference to the inflection point of the elevator shown in solid line in Fig. 5) time, telecontrolled aircraft can enter advanced stall, so that remote control
Aircraft enters prompt drop pattern, causes telecontrolled aircraft to decline along the most vertical track.When telecontrolled aircraft drops to safe altitude,
Lifting actuator 121 receives glide landing instruction, and lifting actuator 121 controls elevator 112 and is returned to deflection angle
Between degree is ± 20 °, so that telecontrolled aircraft enters into glide landing pattern, thus reduce rushing when telecontrolled aircraft is landed
Hit power.
Refer to Fig. 6, Fig. 7 and Fig. 8, in certain embodiments, elevator 132 is under an actuator 140 controls
Carry out the first landing mode and the conversion of the second landing mode.As some embodiments, elevator 132 is connected to drive mechanism
One end of 150, the other end of drive mechanism 150 is connected to actuator 140.Actuator 140 receives control command,
According to control command, controlling the motion of drive mechanism 150, elevator 132 deflects under the effect of drive mechanism 150,
According to the difference of elevator 132 deflection angle, control aircraft and enter different landing mode.In certain embodiments, flat
Flying to wait regular flight condition, actuator 140 receives orthodox flight instruction, controls elevator 132 and deflects between ± 20 °；
Wherein, Fig. 6 is that elevator 132 is at the flat deflection angle (elevator angle degree is 0 °) flying state, the dotted line of Fig. 7
The inflection point of the elevator illustrated deflects between ± 20 °；Instruct when user sends prompt drop by remote controller, actuator
140 receive prompt drop instruction, control drive mechanism 150 and allow elevator 132 turn to (please join more than 20 ° around rotation axis
Examine Fig. 8).Telecontrolled aircraft enters advanced stall, so that telecontrolled aircraft enters prompt drop pattern, causes telecontrolled aircraft along several
Vertical track declines.When telecontrolled aircraft drops to safe altitude, user sends glide landing by remote controller and instructs, and holds
Row mechanism 140 receives glide landing instruction, and actuator 140 controls elevator 132 and is returned to deflection angle and is ± 20 °
Between, so that telecontrolled aircraft enters into glide landing pattern, thus reduce impulsive force when telecontrolled aircraft is landed.One
In a little embodiments, glide landing instruction is continually varying controlled quentity controlled variable (such as, convert deflection angle between ± 20 °), speed
Fall instruction is the controlled quentity controlled variable (such as, in an angle more than 20 ° or an angle more than 30 °) of two fixed positions.
In certain embodiments, the operation of two kinds of landing mode of telecontrolled aircraft is the merging by electronic signal or machinery knot
Share of structure carries out mixing.As some embodiments, prompt drop mode instruction and glide landing mode instruction can be merged shape
Becoming a synthetic instruction (or claiming mixing instruction), telecontrolled aircraft performs this instruction automatically.In the case of mixing instructs, prompt drop mould
Formula instruction and glide landing mode instruction become the operational order of a passage, can perform with same actuator 140.
Operation by same two kinds of landing mode of actuating mechanism controls, it is possible to reduce the mechanical part that telecontrolled aircraft is used, alleviates
The weight of aircraft.In certain embodiments, mixing instruction can perform in remote controller, and such as, the lifting of remote controller is handled
Bar is to handle the lifting of telecontrolled aircraft and enter the first landing mode, and remote controller controls telecontrolled aircraft entrance the with a switch
Two landing mode, control the lifting of telecontrolled aircraft with lift control lever during normal flight or enter the first landing mode, needing
Stirring prompt drop switch when entering prompt drop pattern, allow telecontrolled aircraft enter prompt drop pattern, two operational orders are the most mixed in remote controller
Synthesize the operational order of a passage, be sent to receiver by radio wave, only with an execution machine in telecontrolled aircraft
Structure 140 produces control action, drives elevator action.In certain embodiments, mixing can be by frame for movement in remote control
Performing in aircraft, such as, lift control lever is to handle the first landing mode on a remote control, and remote controller is controlled with a switch
System enters the second landing mode, and with the lifting of lift control lever Controlling model aircraft during normal flight, two manipulation signals are the most logical
Crossing radio wave and be sent to receiver, the receiver in telecontrolled aircraft receives the manipulation signal of two passages, in telecontrolled aircraft
The corresponding operational order performing lift control lever with an actuator 121, produces elevating control action, needs to enter
Stir prompt drop switch during prompt drop pattern, telecontrolled aircraft performs prompt drop operational order with another one actuator 122, produce
Raw prompt drop control action, allows the model of an airplane enter prompt drop pattern, and they control elevator under machinery mixing rocking arm 118 effect
Action, perform above-mentioned two landing mode operational order.
In certain embodiments, drive mechanism 150 includes rocking arm and connecting rod.In further embodiments, drive mechanism 150
Including gear and Timing Belt.
The application also provides for the telecontrolled aircraft of an embodiment, including: elevator；The actuator of control elevator, wherein,
In descent, actuating mechanism controls telecontrolled aircraft is changed, wherein in the first landing mode and the second landing mode back and forth
In second landing mode, the deflection angle of elevator is more than the deflection angle of the elevator of the first landing mode.The present embodiment distant
When control aircraft can reduce the requirement to landing place and landing, impulsive force is little.
In certain embodiments, refer to Fig. 3, actuator includes the first actuator and the second actuator, wherein,
First actuator can be lifting actuator 121, and the second actuator can be prompt drop actuator 122.As one
A little embodiments, flying tail elevator 112 has horizontal tail rocking arm 114, and horizontal tail rocking arm 114 is connected to one end of connecting rod 116.
The other end of connecting rod 116 is connected to the first end 120 of rocking arm 118, and lifting actuator 121 is connected at the first junction point
Rocking arm 118, prompt drop actuator 122 is connected to rocking arm 118, the implementation capacity of lifting actuator 121 at the second junction point
Arm D1 is more than the execution arm of force D2 of prompt drop actuator 122, say, that the first junction point distance rocking arm 118 first end
The distance (D1) of 120 is more than the distance (D2) of the second junction point distance rocking arm 118 first end 120.
In certain embodiments, the first actuator performs glide landing mode instruction；In certain embodiments, first perform
Mechanism performs the lifting instruction of glide landing mode instruction and flight.In certain embodiments, the second actuator performs prompt drop
Mode instruction.
In certain embodiments, the first landing mode can be glide landing pattern, and the second landing mode can be other fall
Stamping die formula.In certain embodiments, the second landing mode can be prompt drop pattern, and the first landing mode can be other fall
Stamping die formula.In certain embodiments, described first landing mode is glide landing pattern and described second landing mode is prompt drop
Pattern.
In certain embodiments, when elevator is flying tail type elevator, the elevator angle of the first landing mode
Between degree is ± 20 °, the elevator angle degree of the second landing mode is more than 20 °.
In certain embodiments, when elevator is part horizontal tail type elevator, the elevator angle of the first landing mode
Between degree is ± 30 °, the elevator angle degree of the second landing mode is more than 30 °.
In certain embodiments, when elevator is part horizontal tail type elevator, the elevator of telecontrolled aircraft accounts for tailplane
Area percentage can select within a large range.Such as elevator accounts for the area percentage of tailplane
10%-85%.In certain embodiments, when the area percentage that elevator accounts for tailplane is 10%-45%, the first landing
The elevator of pattern is deflected to ± 40 ° between.The elevator of the second landing mode is deflected to more than 40 °.In some embodiments
In, the area percentage that elevator accounts for tailplane is the biggest, and the elevator regulation angle of the first landing mode is the least.Separately
In some embodiments, when the area percentage that elevator accounts for tailplane is 45%-85%, the elevator of the first landing mode
Be deflected to ± 30 ° between.The elevator of the second landing mode is deflected to more than 30 °.
Although it should be noted that, be referred to some modules or the submodule of telecontrolled aircraft system in above-detailed, but this
Kind divide be merely exemplary rather than enforceable.It practice, according to embodiments herein, above-described two or
The feature of more multimode and function can embody in a module.Otherwise, the feature of an above-described module and merit
Can be able to embody with Further Division for by multiple modules.
The those skilled in the art of those the art can be by research description, disclosure and accompanying drawing and appended power
Profit claim, understands and implements other changes to the embodiment disclosed.In the claims, word " includes " not arranging
Except other element and step, and wording " one ", " one " are not excluded for plural number.In the actual application of the application,
One part may perform the function of multiple technical characteristics cited in claim.Any reference in claim
Should not be construed as the restriction to scope.
Claims (14)
1. a telecontrolled aircraft, it is characterised in that including:
Elevator；
Controlling the actuator of elevator, wherein, in descent, actuating mechanism controls telecontrolled aircraft is in the first fall
Changing back and forth in stamping die formula and the second landing mode, wherein in the second landing mode, the deflection angle of elevator is more than first
The deflection angle of the elevator of landing mode.
2. telecontrolled aircraft as claimed in claim 1, it is characterised in that described actuator include the first actuator and
Second actuator.
3. telecontrolled aircraft as claimed in claim 1, it is characterised in that described actuator quantity is 1.
4. telecontrolled aircraft as claimed in claim 1, it is characterised in that described actuator comprises drive mechanism, described
Drive mechanism is connected to elevator.
5. telecontrolled aircraft as claimed in claim 4, it is characterised in that described drive mechanism includes rocking arm and connecting rod.
6. telecontrolled aircraft as claimed in claim 2, it is characterised in that the execution arm of force of the first actuator is more than second
The execution arm of force of actuator.
7. telecontrolled aircraft as claimed in claim 1, it is characterised in that described elevator is flying tail type elevator.
8. telecontrolled aircraft as claimed in claim 1, it is characterised in that the elevator angle degree of the second landing mode is big
In 20 °.
9. telecontrolled aircraft as claimed in claim 8, it is characterised in that the elevator angle degree of the first landing mode is
Between ± 20 °.
10. telecontrolled aircraft as claimed in claim 1, it is characterised in that described elevator is part horizontal tail type elevator.
11. telecontrolled aircrafts as claimed in claim 10, it is characterised in that the elevator angle degree of the second landing mode is big
In 40 °.
12. telecontrolled aircrafts as claimed in claim 11, it is characterised in that the elevator angle degree of the first landing mode is
Between ± 40 °.
13. telecontrolled aircrafts as claimed in claim 1, it is characterised in that described first landing mode is glide landing pattern.
14. telecontrolled aircrafts as claimed in claim 13, it is characterised in that described second landing mode is prompt drop pattern.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620292168.9U CN205699447U (en) | 2016-04-08 | 2016-04-08 | Telecontrolled aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620292168.9U CN205699447U (en) | 2016-04-08 | 2016-04-08 | Telecontrolled aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205699447U true CN205699447U (en) | 2016-11-23 |
Family
ID=57309564
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620292168.9U Expired - Fee Related CN205699447U (en) | 2016-04-08 | 2016-04-08 | Telecontrolled aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205699447U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106586022A (en) * | 2016-12-07 | 2017-04-26 | 中国直升机设计研究所 | Zero position angle adjustment method of stabilator of helicopter |
| CN107991884A (en) * | 2017-12-28 | 2018-05-04 | 西北工业大学 | Small-sized fixed-wing unmanned plane advanced stall recovery method based on range information |
-
2016
- 2016-04-08 CN CN201620292168.9U patent/CN205699447U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106586022A (en) * | 2016-12-07 | 2017-04-26 | 中国直升机设计研究所 | Zero position angle adjustment method of stabilator of helicopter |
| CN107991884A (en) * | 2017-12-28 | 2018-05-04 | 西北工业大学 | Small-sized fixed-wing unmanned plane advanced stall recovery method based on range information |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10870487B2 (en) | Logistics support aircraft having a minimal drag configuration | |
| US10279904B2 (en) | Fixed structure type vertical take-off and landing aircraft based on dual flying control systems and control method therefor | |
| US7357352B2 (en) | Air vehicle assembly and an associated control system and method | |
| Frank et al. | Hover, transition, and level flight control design for a single-propeller indoor airplane | |
| US20160031554A1 (en) | Control system for an aircraft | |
| DE60200897T2 (en) | Coupled aircraft rotor system | |
| Kubo et al. | Tail-sitter vertical takeoff and landing unmanned aerial vehicle: transitional flight analysis | |
| US8684314B2 (en) | Emergency piloting by means of a series actuator for a manual flight control system in an aircraft | |
| Flores et al. | Transition flight control of the quad-tilting rotor convertible MAV | |
| KR20150038447A (en) | Vertical-takeoff aircraft | |
| RU2389645C1 (en) | Method and device to fly aircraft that optimises ailerons control and increases lift | |
| CN205699447U (en) | Telecontrolled aircraft | |
| CN109436300A (en) | A kind of steerable system of light-duty sport plane | |
| CN103144781A (en) | Method for determining transient process switching corridor of tilt rotor unmanned aircraft | |
| CN106043686A (en) | Vertical take-off and landing fixed wing aircraft | |
| EP2599712A3 (en) | Aerodynamic wing load distribution control | |
| CN109739251A (en) | Unmanned plane Time-sharing control method | |
| CN110498061A (en) | There is the man-machine method for changing unmanned plane based on rudder control system modification | |
| CN106597855B (en) | It is a kind of neutrality speed and forward direction speed stability contorting restrain switching control method | |
| Zhang et al. | Bioinspired drone actuated using wing and aileron motion for extended flight capabilities | |
| WO2011041991A2 (en) | Aircraft using ducted fan for lift | |
| CN205854491U (en) | VTOL Fixed Wing AirVehicle | |
| CN107261521A (en) | The landing method of telecontrolled aircraft and telecontrolled aircraft | |
| CN209396030U (en) | A kind of Aileron control system of light-duty sport plane | |
| KR101194910B1 (en) | Humming bird type of robotic mechanism with hovering capability and method thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20161123 Termination date: 20180408 |