JPWO2021030630A5 - - Google Patents

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Publication number
JPWO2021030630A5
JPWO2021030630A5 JP2022509056A JP2022509056A JPWO2021030630A5 JP WO2021030630 A5 JPWO2021030630 A5 JP WO2021030630A5 JP 2022509056 A JP2022509056 A JP 2022509056A JP 2022509056 A JP2022509056 A JP 2022509056A JP WO2021030630 A5 JPWO2021030630 A5 JP WO2021030630A5
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Japan
Prior art keywords
rotational speed
rotor blades
aircraft
blade pitch
speed threshold
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Pending
Application number
JP2022509056A
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Japanese (ja)
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JP2022544540A (en
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Priority claimed from PCT/US2020/046240 external-priority patent/WO2021030630A2/en
Publication of JP2022544540A publication Critical patent/JP2022544540A/en
Publication of JPWO2021030630A5 publication Critical patent/JPWO2021030630A5/ja
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Claims (18)

前方推力を提供するように構成されたプロップローターと、
ローターアセンブリと、を備え、
前記ローターアセンブリは、
揚力を提供するように構成された複数のローターブレードと、
少なくとも１つの取り付け部材とを含む、上部ローターハブアセンブリと、を備え、
前記各取り付け部材は、
中央セクションと、
複数の前記ローターブレードのうちの２つを前記中央セクションの対向する端部に結合するブレードピッチ調整リンケージであって、前記ローターブレードの回転速度が第１の回転速度閾値よりも遅い間は前記２つのローターブレードを第１のブレードピッチに維持し、前記ローターブレードの回転速度が第１の回転速度閾値よりも大きい第２の回転速度閾値よりも速い間は前記２つのローターブレードを第２のブレードピッチに維持するように構成された、ブレードピッチ調整リンケージと、を備え、
前記ブレードピッチ調整リンケージは、前記ローターブレードの１つを前記中央セクションに結合するガススプリングをそれぞれ含み、前記ガススプリングは、前記ローターブレードの回転速度の増加に関連する遠心力の増加を受けたとき、前記ブレードピッチの増加を引き起こすように構成された、航空機。 a prop rotor configured to provide forward thrust;
a rotor assembly;
The rotor assembly is
a plurality of rotor blades configured to provide lift;
an upper rotor hub assembly including at least one mounting member;
Each of the mounting members
a central section;
A blade pitch adjustment linkage coupling two of the plurality of rotor blades to opposite ends of the central section, wherein the two rotor blades rotate while the rotational speed of the rotor blades is less than a first rotational speed threshold. maintaining one rotor blade at a first blade pitch, and maintaining the two rotor blades at a second blade pitch while the rotational speed of the rotor blades is greater than a second rotational speed threshold greater than the first rotational speed threshold; a blade pitch adjustment linkage configured to maintain pitch;
The blade pitch adjustment linkages each include a gas spring coupling one of the rotor blades to the central section, the gas springs being subjected to an increase in centrifugal force associated with an increase in rotational speed of the rotor blades. , an aircraft configured to cause an increase in said blade pitch. 前記ガススプリングは、前記第１の回転速度閾値よりも低い回転速度の範囲にわたって伸長された位置に留まるように構成されている、請求項１に記載の航空機。 2. The aircraft of claim 1, wherein the gas spring is configured to remain in an extended position over a range of rotational speeds below the first rotational speed threshold. 前記ガススプリングは、前記ローターブレードの回転速度が前記第１の回転速度閾値から前記第２の回転速度閾値まで増加したときに、前記伸長された位置から完全に崩壊される位置まで崩壊するようにさらに構成されている、請求項２に記載の航空機。 The gas spring collapses from the extended position to a fully collapsed position when the rotational speed of the rotor blades increases from the first rotational speed threshold to the second rotational speed threshold. 3. The aircraft of claim 2, further comprising: 前記第１の回転速度閾値は、４５０ＲＰＭ以下であり、前記第２の回転速度閾値は、少なくとも５５０ＲＰＭである、請求項１に記載の航空機。 2. The aircraft of claim 1, wherein the first rotational speed threshold is no greater than 450 RPM and the second rotational speed threshold is at least 550 RPM. 前記第２のブレードピッチは正のブレードピッチであり、前記第１のブレードピッチはフラットブレードピッチまたは前記第２のブレードピッチより低い正のブレードピッチである、請求項１に記載の航空機。 2. The aircraft of claim 1, wherein the second blade pitch is a positive blade pitch and the first blade pitch is a flat blade pitch or a positive blade pitch less than the second blade pitch. モーターを介して前記ローターブレードを回転させるように構成された制御回路をさらに含む、請求項１に記載の航空機。 2. The aircraft of claim 1, further comprising a control circuit configured to rotate said rotor blades via a motor. 前記制御回路は、前記航空機が垂直飛行モードまたはホバリング飛行モードで動作している間、前記第２の回転速度閾値よりも速い回転速度で前記ローターブレードを回転させるように構成されている、請求項６に記載の航空機。 4. The control circuit is configured to rotate the rotor blades at a rotational speed greater than the second rotational speed threshold while the aircraft is operating in a vertical flight mode or a hovering flight mode. 6. Aircraft according to 6. 前記制御回路は、前記航空機が前進飛行モードで動作している間、前記第１の回転速度閾値よりも遅い回転速度で前記ローターブレードを回転させるように構成されている、請求項６に記載の航空機。 7. The control circuit of claim 6, wherein the control circuit is configured to rotate the rotor blades at a rotational speed less than the first rotational speed threshold while the aircraft is operating in a forward flight mode. aircraft. 前記制御回路は、前記第１の回転速度閾値と前記第２の回転速度閾値との間の回転速度の中間範囲内で、前記ローターブレードの持続的な回転を防止するように構成されている、請求項６に記載の航空機。 the control circuit is configured to prevent sustained rotation of the rotor blades within an intermediate range of rotational speeds between the first rotational speed threshold and the second rotational speed threshold; 7. An aircraft according to claim 6. 前記モーターは、前記モーターが動力を供給しているときには前記モーターを前記ローターアセンブリに回転可能に結合し、前記モーターが動力を供給していないときには前記ローターアセンブリが自由に回転することを可能にするクラッチ機構またはワンウェイベアリングによって前記ローターアセンブリに結合される、請求項６に記載の航空機。 The motor rotatably couples the motor to the rotor assembly when the motor is powered and allows the rotor assembly to rotate freely when the motor is not powered. 7. The aircraft of claim 6, coupled to said rotor assembly by a clutch mechanism or a one-way bearing. 前記制御回路は、前記モーターが前記第２の回転速度閾値よりも速い回転速度で前記ローターブレードを回転させる垂直飛行モードまたはホバリング飛行モードから、
少なくとも、一つまたは複数の前記プロップローターを作動させて前方推力を提供し、
前記ローターブレードの回転速度が、前記第１の回転速度閾値と前記第２の回転速度閾値との間の中間範囲にある間に、前記ローターブレードの回転速度が前記第１の回転速度閾値よりも低下し、前記ブレードピッチ調整リンケージが前記２つのローターブレードを前記第２のブレードピッチから前記第１のブレードピッチに移動させるように、前記モーターに前記ローターブレードの回転を停止させることによって、
前進飛行モードに移行するように構成されている、請求項６に記載の航空機。 from a vertical flight mode or a hovering flight mode in which the motor rotates the rotor blades at a rotational speed greater than the second rotational speed threshold;
actuating at least one or more of said proprotors to provide forward thrust;
the rotational speed of the rotor blades is greater than the first rotational speed threshold while the rotational speed of the rotor blades is in an intermediate range between the first rotational speed threshold and the second rotational speed threshold; by causing the motor to stop rotating the rotor blades so that the blade pitch adjustment linkage moves the two rotor blades from the second blade pitch to the first blade pitch;
7. The aircraft of claim 6, configured to transition to a forward flight mode. 前記制御回路は、前記ローターアセンブリを垂直位置から、前記前進飛行モードにおける前記ローターブレードの自由回転を容易にする後方の傾斜位置に傾けるようにさらに構成されている、請求項１１に記載の航空機。 12. The aircraft of claim 11, wherein the control circuit is further configured to tilt the rotor assembly from a vertical position to a tilted aft position that facilitates free rotation of the rotor blades in the forward flight mode. 前記制御回路は、前記ローターブレードが前記第１の回転速度閾値よりも遅い回転速度で自由回転する前記前進飛行モードから、
少なくとも、一つまたは複数の前記プロップローターを停止して前方推力の供給を停止し、
前記ローターブレードの回転速度が、前記第１の回転速度閾値と前記第２の回転速度閾値との間の中間範囲にある間に、前記ブレードピッチ調整リンケージが前記２つのローターブレードを前記第１のブレードピッチから前記第２のブレードピッチに移動させ、前記ローターブレードの回転速度を前記第２の回転速度閾値よりも上げるように、前記モーターを作動させることによって、
垂直飛行モードまたはホバリング飛行モードに移行するように構成されている、請求項６に記載の航空機。 from the forward flight mode in which the rotor blades are free-rotating at a rotational speed less than the first rotational speed threshold;
stopping at least one or more of said prop rotors from supplying forward thrust;
The blade pitch adjustment linkage moves the two rotor blades to the first position while the rotational speed of the rotor blades is in the intermediate range between the first rotational speed threshold and the second rotational speed threshold. by actuating the motor to move from the blade pitch to the second blade pitch and increase the rotational speed of the rotor blades above the second rotational speed threshold;
7. The aircraft of claim 6, configured to transition to a vertical flight mode or a hovering flight mode. 前記制御回路は、前記垂直飛行モードまたはホバリング飛行モードに移行するときに、前記ローターアセンブリを後方の傾斜位置から垂直位置に傾けるようにさらに構成されている、請求項１３に記載の航空機。 14. The aircraft of claim 13, wherein the control circuit is further configured to tilt the rotor assembly from a rearward tilted position to a vertical position when transitioning to the vertical or hovering flight mode. 前記ブレードピッチ調整リンケージは、前記取り付け部材に結合され、前記ローターブレードのブレードピッチを同期させるように構成された少なくとも１つの同期リンケージを含む、請求項１に記載の航空機。 2. The aircraft of claim 1, wherein the blade pitch adjustment linkage includes at least one synchronizing linkage coupled to the mounting member and configured to synchronize blade pitch of the rotor blades. 前記ローターアセンブリは、前記前記中央セクションの対向する端部から延びる内側シリンダーをさらに含み、前記２つのローターブレードはそれぞれ、前記内側シリンダーの１つをスライド式に受け入れる外側シリンダーに結合される、請求項１５に記載の航空機。 4. The rotor assembly further comprising an inner cylinder extending from opposite ends of the central section, the two rotor blades each being coupled to an outer cylinder slidingly receiving one of the inner cylinders. 15. Aircraft according to 15. 前記外側シリンダーは、ピン受け入れ開口部を含み、前記内側シリンダーは、トラックを画定する開口部を含み、前記ブレードピッチ調整リンケージは、前記内側シリンダーの開口部を通って延在するピンを含み、前記外側シリンダーが前記内側シリンダーに対して相対的にスライドするとき、前記ピンが前記トラックを通ってスライドし、それによって前記内側シリンダーに対する前記外側シリンダーの相対的な回転を引き起こす、請求項１６に記載の航空機。 the outer cylinder includes a pin receiving opening, the inner cylinder includes an opening defining a track, the blade pitch adjustment linkage includes a pin extending through the opening of the inner cylinder, and the 17. The pin of claim 16, wherein when the outer cylinder slides relative to the inner cylinder, the pin slides through the track, thereby causing relative rotation of the outer cylinder with respect to the inner cylinder. aircraft. 前記航空機は、少なくとも４つのローターブレードおよび少なくとも２つの取り付け部材を含み、各々の取り付け部材は、複数のローターブレードのうちの２つの反対側に配置されたローターブレードに結合され、各々の取り付け部材は、少なくとも１つの他の取り付け部材が独立してティータリングすることができるように成形される、請求項１に記載の航空機。 The aircraft includes at least four rotor blades and at least two mounting members, each mounting member coupled to two oppositely disposed rotor blades of the plurality of rotor blades, each mounting member comprising: , wherein the at least one other mounting member is shaped such that it can be teetered independently.
JP2022509056A 2019-08-14 2020-08-13 aircraft Pending JP2022544540A (en)

Applications Claiming Priority (7)

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US201962886578P 2019-08-14 2019-08-14
US62/886,578 2019-08-14
US201962896257P 2019-09-05 2019-09-05
US62/896,257 2019-09-05
US202063018848P 2020-05-01 2020-05-01
US63/018,848 2020-05-01
PCT/US2020/046240 WO2021030630A2 (en) 2019-08-14 2020-08-13 Aerial vehicle

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