CN205168891U - Can receive and release many rotor crafts of combined type of wing - Google Patents
Can receive and release many rotor crafts of combined type of wing Download PDFInfo
- Publication number
- CN205168891U CN205168891U CN201520907996.4U CN201520907996U CN205168891U CN 205168891 U CN205168891 U CN 205168891U CN 201520907996 U CN201520907996 U CN 201520907996U CN 205168891 U CN205168891 U CN 205168891U
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- CN
- China
- Prior art keywords
- wing
- organism
- rocking arm
- landing gear
- retractable
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Abstract
Can receive and release many rotor crafts of combined type of wing, time of endurance is short, the limited problem of loading capacity owing to structural reason leads to mainly to solve prior art. It mainly includes: the motor, screw, rocking arm, organism, lithium cell group, scalable wing, retractable landing gear and flight control system. Above -mentioned each partial assembling scheme: the screw is installed on the motor, and the motor passes through the installed part and fixes the one end at the rocking arm, and the centre at the organism is fixed to the other end of rocking arm. Flight control system installs middle position directly over the organism, the middle position under the organism is installed by lithium cell group, the both sides position is leaned on in installing of retractable landing gear symmetry below the organism, scalable wing passes through the installed part to be fixed on the retractable landing gear. The aircraft is in the back of taking off, and the undercarriage can be packed up, and the wing extends to the outside simultaneously, has improved the lift of these many rotor crafts greatly to effectual time of endurance and the loading capacity of having improved.
Description
Technical field
The utility model relates to a kind of multi-rotor aerocraft, especially a kind of can folding and unfolding the combined type multi-rotor aerocraft of retractable wing, belong to field of aerospace technology.
Background technology
Multi-rotor aerocraft has vertical takeoff and landing, hovering, the ability of flying all around, can realize accuracy, not need special airport, can be applicable to multiple-task, as dark woods fire prevention, traffic monitoring, farmland protection, aerial survey etc. of taking photo by plane.In recent years, after motor technology, battery technology, particularly commercial MEMS sensor appearance, many rotors market has been ignited, particularly in the field of taking photo by plane.
Improving the cruise duration of rotor craft, load carrying ability, is the emphasis in current rotor craft R&D process.General multi-rotor aerocraft only relies on screw propeller to provide lift and adjusts self attitude (comprising perpendicular movement, luffing, rolling movement, yawing rotation), cannot obtain more lift to extend cruise duration, to improve load carrying ability.
Summary of the invention
The utility model, for the purpose of solving the problem, mainly solves prior art and causes the problem that cruise duration is short, load carrying ability is limited due to structural reason.
For achieving the above object, the technical solution adopted in the utility model is: can the combined type multi-rotor aerocraft of folding and unfolding wing, aircaft configuration adopts the composite material based on carbon fiber, rotor craft and Fixed Wing AirVehicle are combined, thus obtains more lift to extend cruise duration, to improve load carrying ability.Concrete structure: it mainly comprises: electrical motor, screw propeller, rocking arm, body, lithium cell group, retractable wing, retractable landing gear and flight control system.Each part mentioned above assembling scheme: described screw propeller is arranged on electrical motor, electrical motor is fixed on one end of rocking arm by fabricated section, and the other end of rocking arm is fixed on the centre of body.Described flight control system is arranged on middle position directly over body; Described lithium cell group is arranged on the middle position immediately below body; Being arranged on below body by two side positions of described retractable landing gear symmetry; Described retractable wing is fixed on retractable landing gear by fabricated section.
Principle of work: during aircraft takeoff, by lithium cell group for electrical motor provides propulsion source, after flight control system control electrical motor carrying screws reaches certain rotating speed, aircraft leaves ground; Aircraft after take off, pack up by retractable landing gear, and retractable wing stretches laterally simultaneously; During aircraft landing, retractable wing is regained, and retractable landing gear puts down, until safe landing.
The beneficial effects of the utility model and feature:
(1) multi-rotor aerocraft after take off, and alighting gear can be packed up, and wing stretches laterally simultaneously, substantially increases the lift of this multi-rotor aerocraft, thus effectively raises cruise duration and load carrying ability;
(2) take lithium cell as the new cleaning fuel of the energy, operating cost is low, and in addition, noise is little, little on the life impact of ground staff;
(3) body and rocker structure are carbon fiber composite structure, and structure efficiency is high, profile streamline, smooth surface, and the life-span is long, easy care;
Accompanying drawing explanation
Fig. 1 is front view of the present utility model.
Fig. 2 is the left view of Fig. 1.
View when Fig. 3 is the utility model landing.
Shown in figure: 1, electrical motor; 2, screw propeller; 3, rocking arm; 4, body; 5, lithium cell group; 6, retractable wing; 7, retractable landing gear; 8, flight control system.
Detailed description of the invention
Embodiment
As shown in Figure 1, Figure 2 and Figure 3, can the combined type multi-rotor aerocraft of folding and unfolding wing, aircaft configuration adopts the composite material based on carbon fiber, rotor craft and Fixed Wing AirVehicle is combined, thus obtains more lift to extend cruise duration, to improve load carrying ability.Concrete structure: it mainly comprises: electrical motor 1, screw propeller 2, rocking arm 3, body 4, lithium cell group 5, retractable wing 6, retractable landing gear 7 and flight control system 8.Each part mentioned above assembling scheme: described screw propeller 2 is arranged on electrical motor 1, and electrical motor 1 is fixed on one end of rocking arm 3 by fabricated section, the other end of rocking arm 3 is fixed on the centre of body 4.Described flight control system 8 is arranged on middle position directly over body 4; Described lithium cell group 5 is arranged on the middle position immediately below body 4; Being arranged on below body 4 by two side positions of described retractable landing gear 7 symmetry; Described retractable wing 6 is fixed on retractable landing gear 7 by fabricated section.
During aircraft takeoff, control steering wheel by flight control system 8 and upwards pack up alighting gear 7, after alighting gear 7 is retracted into level attitude, retractable wing 6 is also along with alighting gear 7 arrives level attitude, flight control system 8 controls the state that the outside expansion wing of retractable wing 6 reaches regulation afterwards, thus plays the effect increasing lift; During aircraft landing, first control after retractable wing 6 regains wing by flight control system 8, then control the landing state that steering wheel drop 7 arrives regulation, until aircraft security landing is landed.
Claims (1)
1. can the combined type multi-rotor aerocraft of folding and unfolding wing, it is characterized in that: it mainly comprises: electrical motor, screw propeller, rocking arm, body, lithium cell group, retractable wing, retractable landing gear and flight control system, described screw propeller is arranged on electrical motor, electrical motor is fixed on one end of rocking arm by fabricated section, and the other end of rocking arm is fixed on the centre of body; Described flight control system is arranged on middle position directly over body; Described lithium cell group is arranged on the middle position immediately below body; Being arranged on below body by two side positions of described retractable landing gear symmetry; Described retractable wing is fixed on retractable landing gear by fabricated section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520907996.4U CN205168891U (en) | 2015-11-13 | 2015-11-13 | Can receive and release many rotor crafts of combined type of wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520907996.4U CN205168891U (en) | 2015-11-13 | 2015-11-13 | Can receive and release many rotor crafts of combined type of wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205168891U true CN205168891U (en) | 2016-04-20 |
Family
ID=55732908
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520907996.4U Expired - Fee Related CN205168891U (en) | 2015-11-13 | 2015-11-13 | Can receive and release many rotor crafts of combined type of wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205168891U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105314105A (en) * | 2015-11-13 | 2016-02-10 | 辽宁通用航空研究院 | Hybrid multi-rotor aircraft with retractable wings |
-
2015
- 2015-11-13 CN CN201520907996.4U patent/CN205168891U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105314105A (en) * | 2015-11-13 | 2016-02-10 | 辽宁通用航空研究院 | Hybrid multi-rotor aircraft with retractable wings |
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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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160420 Termination date: 20171113 |