CN205307792U - Model aircraft with strenghthened type ventral - Google Patents
Model aircraft with strenghthened type ventral Download PDFInfo
- Publication number
- CN205307792U CN205307792U CN201520888001.4U CN201520888001U CN205307792U CN 205307792 U CN205307792 U CN 205307792U CN 201520888001 U CN201520888001 U CN 201520888001U CN 205307792 U CN205307792 U CN 205307792U
- Authority
- CN
- China
- Prior art keywords
- ventral
- machine
- lateral plate
- model
- plate
- 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 utility model discloses a model aircraft with strenghthened type ventral, the reciprocating impact tunnel drilling machine comprises a machine body, the fuselage includes fuselage vertical plate, wing panel, a machine ventral surface board and a left side, right side ventral curb plate, on the anterior insertion machine body vertical plate of wing panel, the organic ventral surface board of wing panel below parallel arrangement, through a left side between the two, right side ventral curb plate is connected, machine ventral surface prelaminar part is equipped with the paddle mounting groove, the quick -witted ventral surface board and the left side in paddle mounting groove the place ahead, right side ventral curb plate junction has at least a department to be equipped with the intensity reinforcement, the intensity reinforcement is " L " type, two linking arms of intensity reinforcement respectively with quick -witted ventral surface board, left or right ventral curb plate fixed connection, adopt the beneficial effects of the utility model are that the intensity reinforcement has improved the intensity of ventral greatly, and the ventral is stronger in the shock -resistant power of the in -process that lands repeatedly, and life is longer, thereby simultaneously because bigger paddle mounting groove can be offered in the enhancement of quick -witted ventral surface board intensity on quick -witted ventral surface board, provides the possibility for the bigger paddle of model aircraft installed power.
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 machine abdomen.
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, it can also help numerous teenagers cultivation to be not only good at dynamic brain but also be good at starting and overcome difficulties the one's best quality daring to keeping forging ahead, and promotes that moral, intelligence, body are all-round developing.
Model of an airplane machine outside of belly plate in landing mission repeatedly to be born great impact power, and particularly machine outside of belly plate is near blade installation place, and the intensity installing groove machine outside of belly plate herein because having offered blade is greatly diminished and is therefore easy to occur damaging.
Practical novel content
For solving above technical problem, the utility model provides the model of an airplane with reinforced machine abdomen 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 machine abdomen, comprise fuselage, its key is: described fuselage comprises fuselage stringer board, Wing panel, machine outside of belly plate, left machine ventral-lateral plate 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, therebetween connect through described left machine ventral-lateral plate and described right machine ventral-lateral plate, described machine outside of belly plate front portion is provided with blade and installs groove, described blade installs the described machine outside of belly plate in groove front and described left machine ventral-lateral plate, described right machine ventral-lateral plate junction has at least a place to be provided with intensity reinforcing member, described intensity reinforcing member is in " L " type, the armstand of described intensity reinforcing member is fixedly connected with described left machine ventral-lateral plate or described right machine ventral-lateral plate, the transverse arm of described intensity reinforcing member is fixedly connected with described machine outside of belly plate. the useful effect adopting the technical program is the intensity that the intensity reinforcing member that machine outside of belly plate and machine ventral-lateral plate junction are arranged substantially increases machine abdomen, machine abdomen impact resistance in the process repeatedly landed is stronger, longer service life, simultaneously owing to the reinforcement of machine abdomen slab strength installs groove it is thus possible to offer bigger blade on machine outside of belly plate, the blade bigger to model of an airplane installation power provides possibility.
As optimization: above-mentioned left machine ventral-lateral plate and described right machine ventral-lateral plate and described machine outside of belly plate junction are equipped with described intensity reinforcing member, and the useful effect adopting this scheme is the intensity further increasing machine outside of belly plate.
Above-mentioned intensity reinforcing member is positioned on the side of described left machine ventral-lateral plate and described right machine ventral-lateral plate, adopts the useful effect of this scheme to be intensity reinforcing member is arranged on machine abdomen inside thus makes whole model of an airplane profile more attractive in appearance.
Above-mentioned left machine ventral-lateral plate and described right machine ventral-lateral plate are 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.
Above-mentioned Wing panel rear end is provided with port tailplane, middle empennage and starboard tailplane, described port tailplane is equal with described starboard tailplane length, and it is greater than the length of described middle empennage, the useful effect adopting this scheme is owing to the length of middle empennage is less than left and right empennage, in during aircraft landing, empennage is no longer very easily damaged by collision because length is longer, middle empennage after shortening in addition alleviates the weight of the whole model of an airplane, the balancing control in favourable flight.
Above-mentioned left machine ventral-lateral plate extend to described right machine ventral-lateral plate rear portion with described port tailplane with described starboard tailplane tail end and concordant with it, adopt the useful effect of this scheme to be left and right empennage because obtaining the support of left and right machine ventral-lateral plate and more solid and reliable, not easily damage because of collision.
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 machine abdomen panel length is less than the length of described middle empennage, and machine outside of belly plate afterbody is concave circular arcs tail, adopts the useful effect of this scheme to be that the weight alleviating fuselage is conducive to the control of the balance in flying and reduces energy consumption.
Useful effect: adopt the beneficial effects of the utility model to be the intensity that the intensity reinforcing member that machine outside of belly plate and machine ventral-lateral plate junction are arranged substantially increases machine abdomen, machine abdomen impact resistance in the process repeatedly landed is stronger, longer service life, simultaneously owing to the reinforcement of machine abdomen slab strength installs groove it is thus possible to offer bigger blade on machine outside of belly plate, the blade bigger to model of an airplane installation power provides possibility, left in addition, starboard tailplane is because obtaining a left side, the support of right machine ventral-lateral plate and more solid and reliable, and the concave circular arcs tail of middle empennage after shortening and machine outside of belly plate afterbody alleviates the weight of the whole model of an airplane, balancing control in favourable flight and reduction energy consumption, whole model of an airplane profile is attractive in appearance, good stability, 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 left view of the present utility model.
Embodiment
Below in conjunction with embodiment and accompanying drawing, the utility model is described in further detail.
As shown in Figure 1-Figure 3, a kind of model of an airplane with reinforced machine abdomen, comprise fuselage, described fuselage comprises fuselage stringer board 1, Wing panel 2, machine outside of belly plate 3 and left machine ventral-lateral plate 41 and right machine ventral-lateral plate 42, 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 connect through described left machine ventral-lateral plate 41 and described right machine ventral-lateral plate 42, described machine outside of belly plate 3 front portion is provided with blade and installs groove 8, described blade installs the described machine outside of belly plate 3 in groove 8 front and described left machine ventral-lateral plate 41, described right machine ventral-lateral plate 42 junction is equipped with intensity reinforcing member 7, described intensity reinforcing member 7 is positioned on the side of described left machine ventral-lateral plate 41 and described right machine ventral-lateral plate 42, described intensity reinforcing member 7 is in " L " type, the armstand of described intensity reinforcing member 7 is fixedly connected with described left machine ventral-lateral plate 41 or described right machine ventral-lateral plate 42, the transverse arm of described intensity reinforcing member 7 is fixedly connected with described machine outside of belly plate 3.
It can also be seen that from figure, described left machine ventral-lateral plate 41 and described right machine ventral-lateral plate 42 are 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, described left machine ventral-lateral plate 41 extend to the rear portion of described right machine ventral-lateral plate 42 with described port tailplane 51 with described starboard tailplane 53 tail end and concordant with it, described machine outside of belly plate 3 length is less than the length of described middle empennage 52, and machine outside of belly plate 3 afterbody is concave circular arcs tail.
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 (8)
1. the model of an airplane with reinforced machine abdomen, comprise fuselage, it is characterized in that: described fuselage comprises fuselage stringer board (1), Wing panel (2), machine outside of belly plate (3), left machine ventral-lateral plate (41) and right machine ventral-lateral plate (42), 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 connect through described left machine ventral-lateral plate (41) and described right machine ventral-lateral plate (42), described machine outside of belly plate (3) front portion is provided with blade and installs groove (8),
Described machine outside of belly plate (3) and described left machine ventral-lateral plate (41), described right machine ventral-lateral plate (42) junction in described blade installation groove (8) front have at least a place to be provided with intensity reinforcing member (7), described intensity reinforcing member (7) is in " L " type, the armstand of described intensity reinforcing member (7) is fixedly connected with described left machine ventral-lateral plate (41) or described right machine ventral-lateral plate (42), and the transverse arm of described intensity reinforcing member (7) is fixedly connected with described machine outside of belly plate (3).
2. the model of an airplane with reinforced machine abdomen according to claim 1, it is characterised in that: described left machine ventral-lateral plate (41) and described right machine ventral-lateral plate (42) are equipped with described intensity reinforcing member (7) with described machine outside of belly plate (3) junction.
3. the model of an airplane with reinforced machine abdomen according to claim 1 and 2, it is characterised in that: described intensity reinforcing member (7) is positioned on the side of described left machine ventral-lateral plate (41) and described right machine ventral-lateral plate (42).
4. the model of an airplane with reinforced machine abdomen according to claim 3, it is characterized in that: described left machine ventral-lateral plate (41) and described right machine ventral-lateral plate (42) are all perpendicular to described Wing panel (2), and the two is parallel to each other.
5. the model of an airplane with reinforced machine abdomen according to claim 1, it is characterized in that: 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 is greater than the length of described middle empennage (52).
6. the model of an airplane with reinforced machine abdomen according to claim 5, it is characterised in that: described left machine ventral-lateral plate (41) extend to described right machine ventral-lateral plate (42) rear portion with described port tailplane (51) with described starboard tailplane (53) tail end and concordant with it.
7. the model of an airplane with reinforced machine abdomen according to claim 4 or 5, it is characterised in that: the middle part of the described fuselage stringer board (1) of described Wing panel (2) front portion insertion.
8. the model of an airplane with reinforced machine abdomen according to claim 5, it is characterized in that: described machine outside of belly plate (3) length is less than the length of described middle empennage (52), and machine outside of belly plate (3) afterbody is concave circular arcs tail.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520888001.4U CN205307792U (en) | 2015-11-09 | 2015-11-09 | Model aircraft with strenghthened type ventral |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520888001.4U CN205307792U (en) | 2015-11-09 | 2015-11-09 | Model aircraft with strenghthened type ventral |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205307792U true CN205307792U (en) | 2016-06-15 |
Family
ID=56188346
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520888001.4U Expired - Fee Related CN205307792U (en) | 2015-11-09 | 2015-11-09 | Model aircraft with strenghthened type ventral |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205307792U (en) |
-
2015
- 2015-11-09 CN CN201520888001.4U patent/CN205307792U/en not_active Expired - Fee Related
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA188198S (en) | Double-seated multi-purpose light aircraft | |
| RU2011141267A (en) | AIRCRAFT WITH OPERATION TYPE "COD TAIL" AND WITH REAR ENGINE | |
| CN205730351U (en) | A kind of wing flap improves the aeromodelling airplane of lift-drag ratio | |
| CN105667790A (en) | General layout of unmanned aerial vehicle capable of taking off with catapult assisted and being recovered by bumping net | |
| CN205652334U (en) | Six rotor unmanned aerial vehicle fuselages | |
| CN205307792U (en) | Model aircraft with strenghthened type ventral | |
| CN205022854U (en) | Deformable compound aircraft | |
| CN204473119U (en) | Lightweight unmanned plane | |
| CN205269052U (en) | Model aircraft with balanced type ventral | |
| CN202666408U (en) | Six-arm model aerial propeller | |
| CN202070156U (en) | Integrated fuselage structure of high simulation degree model airplane | |
| CN208746229U (en) | A kind of Novel model airplane aircraft | |
| CN206502025U (en) | A kind of fixed-wing unmanned plane for adapting to a variety of environment that take off | |
| CN206492210U (en) | A kind of model aircraft of suitable night flying | |
| CN205770131U (en) | A kind of light-duty slide type undercarriage | |
| CN203816222U (en) | Model airplane spiral frame | |
| CN205469791U (en) | A connection structure for helicopter skid landing gear | |
| CN204250346U (en) | A kind of anti-rollover airframe steel framework structure | |
| CN202379089U (en) | Novel unmanned aerial vehicle | |
| CN203666974U (en) | Remote sensing remote metering fixed wing unmanned air vehicle | |
| CN205055432U (en) | Model aeroplane and model ship aircraft with water skis | |
| CN205627085U (en) | Formula V -arrangement fin glider is thrown to hand | |
| CN206171800U (en) | Unmanned helicopter undercarriage | |
| CN202087054U (en) | Toy airplane | |
| CN205269055U (en) | Reliable type model aircraft |
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: 20160615 Termination date: 20161109 |