CN205269056U - Model aircraft with strenghthened type fin - Google Patents
Model aircraft with strenghthened type fin Download PDFInfo
- Publication number
- CN205269056U CN205269056U CN201520887975.0U CN201520887975U CN205269056U CN 205269056 U CN205269056 U CN 205269056U CN 201520887975 U CN201520887975 U CN 201520887975U CN 205269056 U CN205269056 U CN 205269056U
- Authority
- CN
- China
- Prior art keywords
- empennage
- model
- wing panel
- ventral
- fin
- 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
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- 210000001015 abdomen Anatomy 0.000 claims description 6
- 238000003780 insertion Methods 0.000 claims description 5
- 230000037431 insertion Effects 0.000 claims description 5
- 230000009286 beneficial effect Effects 0.000 abstract description 3
- 238000005553 drilling Methods 0.000 abstract 1
- 230000002349 favourable effect Effects 0.000 abstract 1
- 230000000694 effects Effects 0.000 description 4
- 238000004904 shortening Methods 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000003245 working effect Effects 0.000 description 1
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- Adjustment And Processing Of Grains (AREA)
Abstract
The utility model discloses a model aircraft with strenghthened type fin, the reciprocating impact tunnel drilling machine comprises a machine body, the fuselage includes fuselage vertical plate, wing panel, quick -witted ventral surface board and left and right ventral curb plate, wing panel inserts the front portion on the fuselage vertical plate, the wing panel below parallel arrangement have machine ventral surface board, through the connection of left and right ventral curb plate between the two, the wing panel rear end is equipped with port tailplane, well fin and right empennage, left and right ventral curb plate rear portion extend to with the port tailplane with right empennage tail end and parallel and level with it adopt the beneficial effects of the utility model are that a left side, right empennage are firm more reliable because of the support that has obtained left and right ventral curb plate, and in addition, because the length of well fin is less than a left side, right empennage, the difficult quilt of fin is damaged in during the aircraft landing, and the well fin behind the shorten has alleviateed whole model aircraft's weight, more favourable flight, and whole model aircraft appearance is pleasing to the eye, and the dough stability is good, and is sturdy and durable.
Description
Technical field
The utility model relates to the model of an airplane, is specifically related to a kind of model of an airplane with reinforced empennage.
Background technology
The model of an airplane also claims model plane, it is be made up of fuselage, wing, empennage and remote operation parts, many as scientific research, amusement, toy articles for use, the dark concern by people and hobby, the novel commodity that a class has certain market scale are become, it is not only interesting strong, and in making and taking a flight test, the especially numerous teenagers of people can also therefrom acquire much science and technology knowledge.
People are frequent due to misoperation in the process of taking a flight test, particularly some models new hand often there will be the situation that aircraft afterbody first lands, as shown in Figure 3 and Figure 4, a left side for tradition model, right machine ventral-lateral plate is general to be only connected and can not extend to and a left side with Wing panel front portion, starboard tailplane tail end, if aircraft afterbody when landing first lands, so left, starboard tailplane can because very easily causing unnecessary damage without any support, the length of the middle empennage of the traditional model of an airplane is generally greater than a left side in addition, the length of starboard tailplane, also very easily cause the breakage of middle empennage when aircraft afterbody first lands thus affect work-ing life of whole aircraft.
Practical novel content
For solving above technical problem, the utility model provides the model of an airplane with reinforced empennage being not easily damaged by collision during a kind of landing.
Technical scheme is as follows:
A kind of model of an airplane with reinforced empennage, comprise fuselage, its key is: described fuselage comprises fuselage stringer board, Wing panel, machine outside of belly plate and left and right machine ventral-lateral plate, on the described fuselage stringer board of described Wing panel front portion insertion, described Wing panel parallel beneath is furnished with described machine outside of belly plate, connects through left and right machine ventral-lateral plate therebetween; Described Wing panel rear end is provided with port tailplane, middle empennage and starboard tailplane, described left and right machine ventral-lateral plate rear portion extend to described port tailplane with described starboard tailplane tail end and concordant with it. Adopt the useful effect of the technical program to be left and right empennage owing to obtaining the support of left and right machine ventral-lateral plate and more solid and reliable, not easily damage because of collision.
As optimization: above-mentioned port tailplane is equal with described starboard tailplane length, and it is greater than the length of described middle empennage, the useful effect of this scheme is adopted to be that the length of middle empennage is less than left and right empennage, in during aircraft landing, empennage is not easily damaged, and the middle empennage after shortening alleviates the weight of the whole model of an airplane.
The middle part of the described fuselage stringer board of above-mentioned Wing panel front portion insertion, adopts the beneficial aspects of this scheme to be that the balance of whole aircraft, stability are better, more stable when taking off or land.
Above-mentioned left and right machine ventral-lateral plate is all perpendicular to described Wing panel, and the two is parallel to each other, and the useful effect adopting this scheme is convenient this model of an airplane of making, and whole aircraft configuration is more attractive in appearance.
Useful effect: adopt the beneficial effects of the utility model to be left and right empennage more solid and reliable because obtaining the support of left and right machine ventral-lateral plate, in addition, owing to the length of middle empennage is less than left and right empennage, in during aircraft landing, empennage is not easily damaged, and the middle empennage after shortening alleviates the weight of the whole model of an airplane, more favorably fly, whole model of an airplane profile good stability attractive in appearance, sturdy and durable.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model;
Fig. 2 is upward view of the present utility model;
Fig. 3 is the structural representation of the tradition model of an airplane;
Fig. 4 is the upward view of the tradition model of an airplane.
Embodiment
Below in conjunction with embodiment and accompanying drawing, the utility model is described in further detail.
As depicted in figs. 1 and 2, a kind of model of an airplane with reinforced empennage, comprise fuselage, described fuselage comprises fuselage stringer board 1, Wing panel 2, machine outside of belly plate 3 and a left side, right machine ventral-lateral plate 4, the middle part of the described fuselage stringer board 1 of described Wing panel 2 front portion insertion, described Wing panel 2 parallel beneath is furnished with described machine outside of belly plate 3, therebetween through a left side, right machine ventral-lateral plate 4 connects, a described left side, right machine ventral-lateral plate 4 is all perpendicular to described Wing panel 2, and the two is parallel to each other, described Wing panel 2 rear end is provided with port tailplane 51, middle empennage 52 and starboard tailplane 53, described port tailplane 51 is equal with described starboard tailplane 53 length, and it is greater than the length of described middle empennage 52, a described left side, right machine ventral-lateral plate 4 rear portion extend to described port tailplane 51 with described starboard tailplane 53 tail end and concordant with it.
Finally it should be noted that; foregoing description is only preferred embodiment of the present utility model; the those of ordinary skill of this area is under enlightenment of the present utility model; under the prerequisite not running counter to the utility model objective and claim; can making multiple similar expression, such conversion all falls within protection domain of the present utility model.
Claims (4)
1. the model of an airplane with reinforced empennage, comprise fuselage, it is characterized in that: described fuselage comprises fuselage stringer board (1), Wing panel (2), machine outside of belly plate (3) and a left side, right machine ventral-lateral plate (4), on the described fuselage stringer board (1) of described Wing panel (2) front portion insertion, described Wing panel (2) parallel beneath is furnished with described machine outside of belly plate (3), therebetween through a left side, right machine ventral-lateral plate (4) connects, described Wing panel (2) rear end is provided with port tailplane (51), middle empennage (52) and starboard tailplane (53), a described left side, right machine ventral-lateral plate (4) rear portion extend to described port tailplane (51) with described starboard tailplane (53) tail end and concordant with it.
2. the model of an airplane with reinforced empennage according to claim 1, it is characterised in that: described port tailplane (51) is equal with described starboard tailplane (53) length, and is greater than the length of described middle empennage (52).
3. the model of an airplane with reinforced empennage according to claim 1 and 2, it is characterised in that: the middle part of the described fuselage stringer board (1) of described Wing panel (2) front portion insertion.
4. the model of an airplane with reinforced empennage according to claim 3, it is characterised in that: described left and right machine ventral-lateral plate (4) is all perpendicular to described Wing panel (2), and the two is parallel to each other.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520887975.0U CN205269056U (en) | 2015-11-09 | 2015-11-09 | Model aircraft with strenghthened type fin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520887975.0U CN205269056U (en) | 2015-11-09 | 2015-11-09 | Model aircraft with strenghthened type fin |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205269056U true CN205269056U (en) | 2016-06-01 |
Family
ID=56053686
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520887975.0U Expired - Fee Related CN205269056U (en) | 2015-11-09 | 2015-11-09 | Model aircraft with strenghthened type fin |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205269056U (en) |
-
2015
- 2015-11-09 CN CN201520887975.0U patent/CN205269056U/en not_active Expired - Fee Related
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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 |
Granted publication date: 20160601 Termination date: 20161109 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |