IL303140A - Asymmetric multirotor - Google Patents
Asymmetric multirotorInfo
- Publication number
- IL303140A IL303140A IL303140A IL30314023A IL303140A IL 303140 A IL303140 A IL 303140A IL 303140 A IL303140 A IL 303140A IL 30314023 A IL30314023 A IL 30314023A IL 303140 A IL303140 A IL 303140A
- Authority
- IL
- Israel
- Prior art keywords
- wing
- creation position
- multirotor aircraft
- wings
- low
- Prior art date
Links
- 230000005484 gravity Effects 0.000 claims 2
- 230000002452 interceptive effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Landscapes
- Artificial Filaments (AREA)
Description
ASYMMETRIC MULTIROTOR Description TECHNICAL FIELD The present invention refers to an asymmetric multirotor with collapsible and foldable wings. In order to enable stability for a multirotor with wings with VTOL (vertical take-off and landing) ability, it is possible to fold the wing in the unstable stages, which are take-off, landing and hovering, but having folding wings involves several problems. The first is to maintain the stability of the aircraft while the wings are folded. The second is where to store the collapsed wing without interfering the thrusters. The third is opening and deploying them while maintaining the aircraft stability while unfold the wings until fully deployed. This invention provides a solution to those problems by innovative design and new processes. Prior knowledge VTOL (vertical take-off and landing) aircrafts are equipped with wings that allow them to be effective, fly farther and for more time when they fly forward, than an aircraft without wing. The wing which contributes greatly during the flight forward, causes unbearable instability in take-off, landing and hovering in harsh weather or windy conditions which endangers the aircraft its passengers and people on the ground. There are several ways to deal with the problem and one of them is to fold the wings while hovering, take-off and landing and when starting forward flight, the wings deployed, and lift is generated. Folding and opening the wings without the risking the aircraft or affecting the stability of the aircraft requires innovative and original planning. List of drawings The intention of the drawings attached to the request is not to limit the scope if the invention and its application. The drawings are intended only to illustrate the invention and they constitute only one possibility for its implementation. FIG. 1A depicts an aircraft with a rigid loose wing in a locked and deployed mode. FIG. 1B depicts the aircraft with the rigid loose wing in released state when folding starts.
Claims (6)
1. A multirotor aircraft that comprises a body, at least three motors and at least one wing that is connected to the body; wherein said at least one wing is deigned to be folded and unfolded during flight of the multirotor aircraft and designed to change during the flight a low-drag creation position to a lift creation position, and vice versa.
2. The multirotor aircraft according to claim 1, wherein when said at least one wing is in said low-drag creation position the at least one wing is in a loose connection state with the body and when said at least one wing is in said lift creation position the at least one wing is in a fixed connection state with the body.
3. The multirotor aircraft according to claim 1, wherein when said at least one wing is in said low-drag creation position the at least one wing is in a non-spread state and when said at least one wing is in said lift creation position the at least one wing is in a spread state.
4. A multirotor aircraft that comprises a body, at least three motors and at least one wing that is connected to the body; wherein said wing is designed to be folded and unfolded during flight of the multirotor aircraft and designed to change during the flight a low-drag creation position to a lift creation position, and vice versa; wherein at least one motor out of said at least three motors has a greater motor power than at least another one motor out of said at least three motors; wherein a distance from the at least one motor to a center of gravity of the multirotor aircraft is shorter than a distance from the at least another one motor to said center of gravity; and wherein the wing is positioned in a geometric area between the at least three motors.
5. The multirotor aircraft according to claim 4, wherein when said wings is in said low-drag creation position the wing is in a loose connection state with the body and when said wing is in said lift creation position the wings is in a fixed connection state with the body. 30
6. The multirotor aircraft according to claim 4, wherein when said wings is in said low-drag creation position the wing is in a non-spread state and when said wing is in said lift creation position the wings is in a spread state.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| IL303140A IL303140A (en) | 2023-05-23 | 2023-05-23 | Asymmetric multirotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| IL303140A IL303140A (en) | 2023-05-23 | 2023-05-23 | Asymmetric multirotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| IL303140A true IL303140A (en) | 2023-07-01 |
Family
ID=87163106
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| IL303140A IL303140A (en) | 2023-05-23 | 2023-05-23 | Asymmetric multirotor |
Country Status (1)
| Country | Link |
|---|---|
| IL (1) | IL303140A (en) |
-
2023
- 2023-05-23 IL IL303140A patent/IL303140A/en unknown
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