JP6537000B1 - Stabilization mechanism of an aircraft having two or more rotors - Google Patents
Stabilization mechanism of an aircraft having two or more rotors Download PDFInfo
- Publication number
- JP6537000B1 JP6537000B1 JP2018014123A JP2018014123A JP6537000B1 JP 6537000 B1 JP6537000 B1 JP 6537000B1 JP 2018014123 A JP2018014123 A JP 2018014123A JP 2018014123 A JP2018014123 A JP 2018014123A JP 6537000 B1 JP6537000 B1 JP 6537000B1
- Authority
- JP
- Japan
- Prior art keywords
- fuselage
- arm
- rotary
- fuselage body
- aircraft
- 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.)
- Active
Links
- 230000006641 stabilisation Effects 0.000 title 1
- 238000011105 stabilization Methods 0.000 title 1
- 230000035939 shock Effects 0.000 claims abstract description 15
- 239000006096 absorbing agent Substances 0.000 claims description 11
- 230000005484 gravity Effects 0.000 claims description 2
- 230000003139 buffering effect Effects 0.000 abstract 2
- 230000000694 effects Effects 0.000 description 2
Images
Landscapes
- Vibration Prevention Devices (AREA)
- Fluid-Damping Devices (AREA)
Abstract
【課題】２個以上の回転翼で飛行する航空機の減速時や着陸時に機体に生じる負荷を緩衝し安全性能を向上する。【解決手段】２個以上の回転翼を有する航空機において回転翼を機体に接続するアーム部を可動式として上下方向へ可動するアーム部と機体の間に緩衝装置を設け回転翼ならびに着陸脚にかかる機体の荷重を緩衝するとともに回転翼に負荷がかかった場合に機体胴体に対する回転翼の回転面に上反角が生じる構造とし飛行中の機体を安定させる。【選択図】図２An object of the present invention is to improve a safety performance by buffering a load generated on an aircraft at the time of deceleration or landing of an aircraft flying with two or more rotary wings. In an aircraft having two or more rotary wings, a shock absorbing device is provided between the wing and an air moving arm which connects an rotary wing to an airframe so as to move the arm to move the rotary wing and the landing leg It stabilizes the in-flight fuselage by buffering the load of the fuselage and creating a diversion on the rotary surface of the rotary blade with respect to the fuselage when the load is applied to the rotary blade. [Selected figure] Figure 2
Description
２個以上の回転翼を有する航空機の構造に関するものである。The present invention relates to the structure of an aircraft having two or more rotors.
複数の回転翼をもつ一般にドローン、マルチコプターと呼ばれる航空機が開発されており機体胴体部と回転翼部を接続するアーム部は可能式の物もあるが飛行中は固定式である。An aircraft generally called a drone or multicopter having a plurality of rotors has been developed. The arm connecting the fuselage fuselage and the rotor is available while it is stationary during flight.
飛行機の機体胴体部に取り付けられた揚力を発生させる翼に上反角を設けることで機体の安定性を向上できることが知られている。It is known that the stability of the fuselage can be improved by providing a diversion on a wing attached to the fuselage body of the aircraft to generate lift.
２個以上の回転翼で機体を制御する航空機の回転翼と機体の間の構造にかかる負荷を低減するとともに機体の安定性を向上する。It controls the fuselage with two or more rotors, reduces the load on the structure between the rotor and the fuselage of the aircraft, and improves the stability of the fuselage.
２個以上の回転翼を有する航空機において、回転翼を機体胴体部に接続するアーム部の連結部を中心としてアーム部を上下方向に可動式とし機体胴体部とアーム部の間に緩衝装置を設けるIn an aircraft having two or more rotary wings, an arm is vertically movable centering on a connecting portion of the arm connecting the rotary wing to the fuselage body, and a shock absorber is provided between the fuselage body and the arm
回転翼と機体胴体部を接続するアーム部が上方に可動した際に機体胴体部に対し回転翼の回転面に上反角が生じる構造とする。When the arm connecting the rotor and the fuselage body is moved upward, an upward angle is produced on the rotational surface of the rotor relative to the fuselage body.
降下中の機体が降下速度の減速を行った場合、機体胴体部とアーム部の間に生じる負荷を緩衝できる。If the descent aircraft is slowing down, the load generated between the fuselage body and the arm can be buffered.
機体が前進あるいは後進状態から回転翼の揚力で減速を行った場合に機体胴体部とアーム部の間にかかる負荷を緩衝できる。The load applied between the fuselage body portion and the arm portion can be buffered when the body is decelerated by the lift of the rotary wing from the forward or reverse state.
緩衝装置が縮んだ状態になった際に機体胴体部と回転翼の回転面の間に上半角をあたえるとともに回転翼の回転面に対し機体胴体部の重心を低くし機体の安定性を向上できる。When the shock absorber is contracted, the upper half-angle can be provided between the fuselage body and the rotary surface of the rotary wing, and the center of gravity of the fuselage body can be lowered relative to the rotary surface of the rotary wing to improve the stability of the fuselage. .
着陸時に機体の着陸脚ならびに着陸脚を取り付ける部位にかかる機体胴体部の荷重を緩衝できる。It can buffer the load of the fuselage fuselage that is applied to the landing leg of the airframe and the site to which the landing leg is attached at the time of landing.
機体胴体部に回転翼をアーム部を介して連結しアーム部と機体胴体部を接続する回転軸を中心にアームが上下方向に可動するようにする。The rotary wing is connected to the fuselage body via an arm, and the arm is movable in the vertical direction around a rotation axis connecting the arm and the fuselage body.
アーム部と機体胴体部の間に緩衝装置をとりつけ負荷が加わった場合、緩衝装置で負荷を緩衝できるようにする。Install a shock absorber between the arm and the fuselage body so that if a load is applied, the shock absorber can cushion the load.
アーム部が上方に可動した際に機体胴体部と回転翼の回転面の間に上反角が生じるようにする。An upward angle is produced between the fuselage body and the rotational surface of the rotary wing when the arm moves upward.
図１で示すように機体胴体部１に回転軸５を介してアーム部４を取り付けアーム部４には回転翼２と回転翼２を駆動する装置が設けられる。As shown in FIG. 1, the arm 4 is attached to the fuselage body 1 via the
機体が降下状態から回転翼の揚力を大きくして降下速度を減速した場合、機体胴体部１の荷重がアーム部４の回転軸５にかかり回転軸５を中心にアーム部４には上方へ回転する力が生じる。When the lift of the rotor is increased from the descent state to decrease the descent speed, the load of the fuselage body 1 is applied to the
アーム部４にかかる力は図２で示すようにアーム部４と機体胴体部１の間に設けた緩衝装置３へと伝わり緩衝装置３で負荷を緩衝する。The force applied to the arm 4 is transmitted to a
緩衝装置３が作動しアーム部４が回転軸５を中心に回転することで機体胴体部１と回転翼２の回転面の間に上反角が生じ機体を安定させる。The
機体が着陸した際に機体胴体部１の荷重が機体胴体部１と回転軸５で接続されるアーム部４にかかった場合も同様に緩衝装置３が働き着陸脚６にかかる荷重を緩衝する。Similarly, when the load of the fuselage body 1 is applied to the arm 4 connected with the fuselage body 1 and the
図３で示すように機体胴体部１上部側に緩衝装置３を取り付けることも可能であり実施例１と同様の効果を得ることができる。As shown in FIG. 3, it is also possible to attach the shock absorber 3 to the upper side of the fuselage body 1 and it is possible to obtain the same effect as the first embodiment.
回転翼２の羽根の角度を変更することで揚力の発生方向を変更し連続して背面飛行を行う機体では、緩衝装置３を回転翼２にかかる負荷が正方向、逆方向いづれの場合でも緩衝することができる構造とすることで背面飛行中であっても実施例１、実施例２と同様の効果を得ることができる。In the airframe where the direction of lift generation is changed by changing the angle of the blades of the
複数の回転翼で飛行する航空機の安全性能を向上することができる。It is possible to improve the safety performance of an aircraft flying with a plurality of rotors.
１ 機体胴体部
２ 回転翼
３ 緩衝装置
４ アーム部
５ 回転軸
６ 着陸脚1
Claims (2)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2018014123A JP6537000B1 (en) | 2018-01-15 | 2018-01-15 | Stabilization mechanism of an aircraft having two or more rotors |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2018014123A JP6537000B1 (en) | 2018-01-15 | 2018-01-15 | Stabilization mechanism of an aircraft having two or more rotors |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JP6537000B1 true JP6537000B1 (en) | 2019-07-03 |
| JP2019123486A JP2019123486A (en) | 2019-07-25 |
Family
ID=67144673
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2018014123A Active JP6537000B1 (en) | 2018-01-15 | 2018-01-15 | Stabilization mechanism of an aircraft having two or more rotors |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP6537000B1 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2024056195A1 (en) | 2022-09-16 | 2024-03-21 | Kji Dronelab Bv | Propulsion system for multicopters and related aircrafts |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB393445A (en) * | 1931-10-28 | 1933-06-08 | Dornier Metallbauten Gmbh | Improvements in or relating to aircraft landing gear |
| GB513664A (en) * | 1937-04-05 | 1939-10-18 | Getefo | Spring suspension for aircraft |
| JPH03148396A (en) * | 1989-11-01 | 1991-06-25 | Hiroaki Yasuda | Hang glider glidable by human power |
| FR2959208B1 (en) * | 2010-04-22 | 2012-05-25 | Eurl Jmdtheque | GYROPENDULAR ENGINE WITH COMPENSATORY PROPULSION AND COLLIMATION OF MULTIMODAL MULTI-MEDIUM FLUID FLOWING GRADIENT WITH VERTICAL LANDING AND LANDING |
| CN104755371B (en) * | 2014-06-26 | 2016-08-31 | 深圳市大疆创新科技有限公司 | A kind of aircraft and holding wire protection assembly thereof |
| WO2015196436A1 (en) * | 2014-06-26 | 2015-12-30 | 深圳市大疆创新科技有限公司 | Deforming aircraft |
| JP6465205B2 (en) * | 2015-04-03 | 2019-02-06 | 株式会社Ｓｏｋｅｎ | Flying object |
| JP5997342B1 (en) * | 2015-09-29 | 2016-09-28 | 京商株式会社 | Multicopter toy |
| CN205186541U (en) * | 2015-11-24 | 2016-04-27 | 零度智控（北京）智能科技有限公司 | Unmanned aerial vehicle organism support |
| US11420766B2 (en) * | 2016-05-17 | 2022-08-23 | Espheric, Llc | Multi sensor support structure |
-
2018
- 2018-01-15 JP JP2018014123A patent/JP6537000B1/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| JP2019123486A (en) | 2019-07-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP4603222B2 (en) | Airplane and flight method | |
| US10011349B2 (en) | Tiltrotor aircraft having rotatable wing extensions | |
| US20200180756A1 (en) | Propeller-Hub Assembly With Folding Blades For VTOL Aircraft | |
| US8998127B2 (en) | Pre-landing, rotor-spin-up apparatus and method | |
| US3426982A (en) | Vertiplane vtol aircraft | |
| US20120168568A1 (en) | Rotor unloading apparatus and method | |
| EP2733068A2 (en) | A fixed winged aircraft with foldable auto-rotation rotor | |
| EP2818410B1 (en) | Rotorcraft anti-torque control system | |
| JP2009051381A (en) | Cycloidal blade | |
| CN105501439A (en) | Rotor wing decelerating and locking device for rotor wing and fixed wing combined type vertical take-off and landing air vehicle | |
| US20140326825A1 (en) | System and a method for controlling pitching stabilizer means of an aircraft | |
| JP2021521056A (en) | Personal vertical takeoff and landing flight equipment | |
| JP6537000B1 (en) | Stabilization mechanism of an aircraft having two or more rotors | |
| JP2018531835A (en) | Flying object | |
| CN104875899B (en) | A kind of stoppable rotor aircraft drive system and the method for changing its rotor system working condition | |
| RU2700323C2 (en) | Aeromechanical method of controlling configuration and flight mode of converted aircraft (convertoplane) | |
| CN107985583A (en) | Tilting rotor wing unmanned aerial vehicle | |
| WO2022029435A1 (en) | Flying vehicle rotor arrangement | |
| WO2017049806A1 (en) | Quadrotor jet aircraft with simultaneously dynamically varying pitches | |
| CN107651184A (en) | One kind is without displacement helicopter | |
| CN106275415A (en) | The aircraft that a kind of fixed-wing and many rotors can automatically switch | |
| CN216611596U (en) | Unmanned aerial vehicle | |
| JPH07132893A (en) | Rotary-wing aircraft | |
| CN105923156B (en) | Helicopter V-type rotor driver | |
| JP2016514647A (en) | Device for controlling the speed of an airplane during the transition from the space flight phase to the air flight phase and its transition method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| A621 | Written request for application examination |
Free format text: JAPANESE INTERMEDIATE CODE: A621 Effective date: 20180226 |
|
| A977 | Report on retrieval |
Free format text: JAPANESE INTERMEDIATE CODE: A971007 Effective date: 20181105 |
|
| A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20181113 |
|
| A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20181203 |
|
| TRDD | Decision of grant or rejection written | ||
| A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 Effective date: 20190514 |
|
| A61 | First payment of annual fees (during grant procedure) |
Free format text: JAPANESE INTERMEDIATE CODE: A61 Effective date: 20190524 |
|
| R150 | Certificate of patent or registration of utility model |
Ref document number: 6537000 Country of ref document: JP Free format text: JAPANESE INTERMEDIATE CODE: R150 |