CN105197225A - Assembled-type unmanned aerial vehicle empennage - Google Patents
Assembled-type unmanned aerial vehicle empennage Download PDFInfo
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- CN105197225A CN105197225A CN201510685440.XA CN201510685440A CN105197225A CN 105197225 A CN105197225 A CN 105197225A CN 201510685440 A CN201510685440 A CN 201510685440A CN 105197225 A CN105197225 A CN 105197225A
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Abstract
The invention relates to an assembled-type unmanned aerial vehicle empennage. The assembled-type unmanned aerial vehicle empennage comprises an empennage framework, a flat empennage stabilizer, a lifting empennage, an empennage rudder, a fuselage, a fuselage tail part, a fixing shaft pin hole and a positioning shaft pin hole. The flat empennage stabilizer is butted with a socket at the fuselage tail part, so that the a fixing pin and a pin hole, a slot and a stabilizing square wall, as well as a lug boss and the socket are coincidently matched respectively; then the fixing shaft pin hole correspondingly coincides with the positioning shaft pin hole; finally, the fixing shaft pin hole and the positioning shaft pin hole are locked by using a fixing shaft pin, and therefore, the flat empennage stabilizer and the fuselage tail part can be connected and fixed into an integral structure. The functions and the effects of the assembled-type unmanned aerial vehicle empennage are the same as those of a traditional unmanned aerial vehicle empennage designed and manufactured integrally. The assembled-type unmanned aerial vehicle empennage has the positive effects that the flat empennage stabilizer and the fuselage are manufactured respectively, so that manufacturing dies are remarkably reduced, the manufacturing cost is greatly saved and the manufacturing difficulty is greatly reduced; the assembled-type unmanned aerial vehicle empennage is convenient for package and transportation of goods and is convenient to assemble, disassemble, repair and maintain.
Description
Technical field
The present invention relates to unmanned plane technical field of aerospace, be specifically related to a kind of novel assembled unmanned airplane empennage.
Background technology
China Patent No. 201420437157.6 discloses a kind of fixed-wing aerial survey unmanned airplane empennage, empennage adopts inverted T shape Wei Shi aerodynamic arrangement, light-duty wooden structures, airflow design, primarily of empennage skeleton, tailplane, vertical tail, elevating rudder, fastening screw pipe composition.Tailplane, vertical tail are connected with fuselage by fastening screw pipe, and bolt is fixed, and elevating rudder is connected with tailplane by hinge, and bolt is fixed.Connect sense assembly to be made up of pull bar, bulb, chuck and rudder pin, be connected with lifting steering wheel.Lifting steering wheel is fixed on fuselage side the latter half.Without wing tip, the design of directionless rudder, avoid elevating rudder seam and cause extension umbrella.
China Patent No. 201320659680.9 discloses a kind of unmanned plane during flying supplementary structure, especially a kind of unmanned plane many spoilers empennage.This structure comprises fuselage, fuselage two middle side part is provided with flank, and fuselage both sides afterbody is provided with side empennage, and tail cone top is provided with empennage, is respectively equipped with multiple stacked spoiler above described both sides empennage.Described unmanned plane many spoilers empennage arranges spoiler above the empennage of fuselage both sides, air-flow through empennage is shunted, homogeneity during maintenance airflow passes empennage and stability, empennage is made to keep stable support to fuselage, avoid fuselage acutely rock or out of control, improve unmanned plane run stability and safety.
China Patent No. 201420581545.1 discloses a kind of modularized combination type unmanned plane, propose the modular combination mode of unmanned plane, by to the decomposition module of unmanned plane constituent elements and the standardization setting of intermodule mounting interface, realize the quick modularization assembling of unmanned plane.Modularized combination type unmanned plane has feature: 1) the multiple standard module of the disassembled one-tenth of unmanned plane, is convenient to vanning transport and safeguards; 2) intermodule adopts standard mounting interface, decreases mounting complexity, provides very large alerting ability for using; 3) monomer, binary and many bodies aircraft can be combined into by quick assembling by modular mode, take into account multiple unmanned plane form, use flexibly, reduce expense.Described Combined unmanned machine body is decomposed into following standard comprising modules: N number of body parts, airfoil member, tail supporting rod and empennage parts; Airfoil member comprises two outer wings and the N number of wing centre section between two outer wings, and empennage parts comprise two vertical fins and the N number of horizontal tail between two vertical fins, and each vertical fin includes vertical fin and lower vertical fin.Be connected by general mounting interface between module with module, monomer, binary even many bodies unmanned plane can be formed by fast speed assembly.
Summary of the invention
The object of this invention is to provide a kind of assembly type unmanned airplane empennage, horizontal tail wing stabilator and fuselage make respectively, obviously reduce to make mould, greatly thrifty cost of manufacture and manufacture difficulty; Both installed, convenient disassembly, be convenient to again maintenance and maintenance.
For achieving the above object, present invention employs such technical scheme: described assembly type unmanned airplane empennage, being made up of empennage skeleton, horizontal tail wing stabilator, lifting empennage, empennage yaw rudder, fuselage, afterbody, anchor shaft pin-and-hole, fix shaft pin-and-hole; It is characterized in that, the top of fuselage is provided with vertical empennage skeleton, and the side of empennage skeleton is provided with empennage yaw rudder; The end of afterbody is provided with the socket vertical with empennage skeleton, and the both sides of socket the inner are respectively equipped with pin-and-hole, and the midway location of pin-and-hole is prefabricated with stable side's wall; The midway location of socket the inner is provided with the fix shaft pin-and-hole of through afterbody; One end of horizontal tail wing stabilator is provided with lifting empennage, and the other end of horizontal tail wing stabilator is provided with the slot with stable side's wall joint match, and the outside, both sides of slot is provided with strengthens convex edge, and the outer end strengthening convex edge is provided with the set pin mated with pin-and-hole; The both sides, middle part of horizontal tail wing stabilator are respectively equipped with the boss with socket joint match, and the end of boss is provided with through anchor shaft pin-and-hole, and anchor shaft pin-and-hole is corresponding with the position of fix shaft pin-and-hole to coincide.
After adopting such structure, horizontal tail wing stabilator is docked with the socket of afterbody, make set pin and pin-and-hole, slot and the side's of stablizing wall, boss and socket joint match respectively; Make anchor shaft pin-and-hole corresponding with fix shaft pin-and-hole identical again; Finally utilize fixing pivot pin (not drawing in figure) that anchor shaft pin-and-hole and fix shaft pin-and-hole are locked, like this, horizontal tail wing stabilator and afterbody can be connected and fixed as integral structure; Its function and efficacy is identical with the unmanned airplane empennage that traditional Integral design manufactures.Good effect of the present invention is: horizontal tail wing stabilator and fuselage make respectively, obviously reduces to make mould, greatly thrifty cost of manufacture and manufacture difficulty; Be convenient to packaging and the transport of commodity.Both installed, convenient disassembly, be convenient to again maintenance and maintenance.
Accompanying drawing explanation
What accompanying drawing was depicted as concrete structure of the present invention disassembles schematic diagram.
Detailed description of the invention
Below in conjunction with accompanying drawing, assembly type unmanned airplane empennage of the present invention is described in detail;
As shown in the figure, described assembly type unmanned airplane empennage, is made up of empennage skeleton 13, horizontal tail wing stabilator 8, lifting empennage 7, empennage yaw rudder 12, fuselage 1, afterbody 15, anchor shaft pin-and-hole 6, fix shaft pin-and-hole 4; It is characterized in that, the top of fuselage 1 is provided with vertical empennage skeleton 13, and the side of empennage skeleton 13 is provided with empennage yaw rudder 12; The end of afterbody 15 is provided with the socket 5 vertical with empennage skeleton 13, and the both sides of socket 5 the inner are respectively equipped with pin-and-hole 2, and the midway location of pin-and-hole 2 is prefabricated with stable side's wall 3; The midway location of socket 5 the inner is provided with the fix shaft pin-and-hole 4 of through afterbody 15; One end of horizontal tail wing stabilator 8 is provided with lifting empennage 7, and the other end of horizontal tail wing stabilator 8 is provided with the slot 10 with stable side's wall 3 joint match, and the outside, both sides of slot 10 is provided with strengthens convex edge 14, and the outer end strengthening convex edge 14 is provided with the set pin 9 mated with pin-and-hole 2; The both sides, middle part of horizontal tail wing stabilator 8 are respectively equipped with the boss 11 with socket 5 joint match, and the end of boss 11 is provided with through anchor shaft pin-and-hole 6, and anchor shaft pin-and-hole 6 is corresponding with the position of fix shaft pin-and-hole 4 to coincide.
Claims (1)
1. an assembly type unmanned airplane empennage, is made up of empennage skeleton (13), horizontal tail wing stabilator (8), lifting empennage (7), empennage yaw rudder (12), fuselage (1), afterbody (15), anchor shaft pin-and-hole (6), fix shaft pin-and-hole (4);
It is characterized in that, the top of fuselage (1) is provided with vertical empennage skeleton (13), and the side of empennage skeleton (13) is provided with empennage yaw rudder (12); The end of afterbody (15) is provided with the socket (5) vertical with empennage skeleton (13), the both sides of socket (5) the inner are respectively equipped with pin-and-hole (2), and the midway location of pin-and-hole (2) is prefabricated with stable side's wall (3); The midway location of socket (5) the inner is provided with the fix shaft pin-and-hole (4) of through afterbody (15);
One end of horizontal tail wing stabilator (8) is provided with lifting empennage (7), the other end of horizontal tail wing stabilator (8) is provided with the slot (10) with stable side's wall (3) joint match, the outside, both sides of slot (10) is provided with strengthens convex edge (14), and the outer end strengthening convex edge (14) is provided with the set pin (9) mated with pin-and-hole (2); The both sides, middle part of horizontal tail wing stabilator (8) are respectively equipped with the boss (11) with socket (5) joint match, the end of boss (11) is provided with through anchor shaft pin-and-hole (6), and anchor shaft pin-and-hole (6) is corresponding with the position of fix shaft pin-and-hole (4) to coincide.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510685440.XA CN105197225A (en) | 2015-10-16 | 2015-10-16 | Assembled-type unmanned aerial vehicle empennage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510685440.XA CN105197225A (en) | 2015-10-16 | 2015-10-16 | Assembled-type unmanned aerial vehicle empennage |
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| Publication Number | Publication Date |
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| CN105197225A true CN105197225A (en) | 2015-12-30 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510685440.XA Pending CN105197225A (en) | 2015-10-16 | 2015-10-16 | Assembled-type unmanned aerial vehicle empennage |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113148106A (en) * | 2021-05-17 | 2021-07-23 | 北京航空航天大学 | Modularized replaceable tail wing |
| CN114408155A (en) * | 2021-12-30 | 2022-04-29 | 中国特种飞行器研究所 | Horizontal tail fuselage butt-joint structure of small-sized general aircraft |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6186854B1 (en) * | 1999-09-13 | 2001-02-13 | Thunder Tiger Corporation | Assembling structure for tail wing of a model airplane |
| CN203666972U (en) * | 2013-11-20 | 2014-06-25 | 天津三爻航空航天科技发展有限公司 | Quick assembling and disassembling structure for tail part of fixed wing aircraft |
| CN104608917A (en) * | 2015-01-28 | 2015-05-13 | 梧州晟裕科技有限公司 | Tail wing structure of fixed wing unmanned aerial vehicle |
| CN205076028U (en) * | 2015-10-16 | 2016-03-09 | 河南翱翔航空科技有限公司 | Assembled unmanned aerial vehicle fin |
-
2015
- 2015-10-16 CN CN201510685440.XA patent/CN105197225A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6186854B1 (en) * | 1999-09-13 | 2001-02-13 | Thunder Tiger Corporation | Assembling structure for tail wing of a model airplane |
| CN203666972U (en) * | 2013-11-20 | 2014-06-25 | 天津三爻航空航天科技发展有限公司 | Quick assembling and disassembling structure for tail part of fixed wing aircraft |
| CN104608917A (en) * | 2015-01-28 | 2015-05-13 | 梧州晟裕科技有限公司 | Tail wing structure of fixed wing unmanned aerial vehicle |
| CN205076028U (en) * | 2015-10-16 | 2016-03-09 | 河南翱翔航空科技有限公司 | Assembled unmanned aerial vehicle fin |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113148106A (en) * | 2021-05-17 | 2021-07-23 | 北京航空航天大学 | Modularized replaceable tail wing |
| CN114408155A (en) * | 2021-12-30 | 2022-04-29 | 中国特种飞行器研究所 | Horizontal tail fuselage butt-joint structure of small-sized general aircraft |
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Application publication date: 20151230 |