CN105129072A - Aircraft tail - Google Patents
Aircraft tail Download PDFInfo
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- CN105129072A CN105129072A CN201510637731.1A CN201510637731A CN105129072A CN 105129072 A CN105129072 A CN 105129072A CN 201510637731 A CN201510637731 A CN 201510637731A CN 105129072 A CN105129072 A CN 105129072A
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- aircraft
- tail
- vertical tail
- complete dynamic
- servomechanism
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- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
The invention discloses an aircraft tail. According to the technical scheme, for a vertically taking-off and landing fixed-wing aircraft of Application No. 2015203521439, the aircraft tail aims at reducing resistance during rotary flight, accurately adjusting a aircraft landing point and adjusting the aircraft stability during rotary takeoff and landing. The aircraft tail consists of a full-automatic vertical tail, a full-automatic vertical tail strengthening beam or full-automatic vertical tail strengthening sheet, a full-automatic vertical tail rotation shaft, a full-automatic vertical tail server, an auxiliary horizontal tail, an auxiliary horizontal tail rotation shaft and an auxiliary horizontal tail server, wherein the full-automatic vertical tail can have a function of performing forward and reverse 180-degree rotation around the straight line parallel to the vertical axis of the aircraft under the control of the full-automatic vertical tail server, and the auxiliary horizontal tail can have a function of performing forward and reverse 90-degree rotation around the straight line parallel to the longitudinal axis of the aircraft under the control of the auxiliary horizontal tail server.
Description
(1) technical field
the present invention relates to a kind of aircraft tail, particularly a kind of fixed-wing vertical take-off and landing aircraft (VTOL aircraft) regulates the aircraft tail of landing balance.
(2) background technology
at present, patent 2015203521439, in the aircraft of vertical takeoff and landing (VTOL) fixed wing aircraft, when the spiraling action of landing of taking off vertically, vertical tail can produce excessive flight resistance, can to housing construction intensity, rotative speed, engine power all can produce important impact.
(3) summary of the invention
in view of the shortcoming of vertical take-off and landing aircraft (VTOL aircraft) is in the past with not enough, the object of this invention is to provide resistance when a kind of aircraft tail effectively can reduce spiraling, and can the drop point of fine adjustment aircraft landing, the technical scheme of stability when regulating aircraft to rotate landing.
the technical solution adopted for the present invention to solve the technical problems is: a kind of aircraft tail, it is characterized in that: by entirely moving vertical tail, complete dynamic vertical tail strength beam or complete dynamic vertical tail reinforced sheet, complete dynamic vertical tail S. A., complete dynamic vertical tail servomechanism, subsidiary level empennage, subsidiary level tail rotor shaft, subsidiary level empennage servomechanism forms, complete dynamic vertical tail is fixed on complete dynamic vertical tail S. A. with complete dynamic vertical tail strength beam or complete dynamic vertical tail reinforced sheet in the lump, complete dynamic vertical tail S. A. is arranged on complete dynamic vertical tail servomechanism, and can do under the control of complete dynamic vertical tail servomechanism and just be parallel to aircraft Z vertical shaft (steering shaft) straight line, negative 180 degree of rotations, namely complete dynamic vertical tail can do along being just parallel to aircraft Z vertical shaft (steering shaft) straight line under the control of complete dynamic vertical tail servomechanism, negative 180 degree of functions of rotating, subsidiary level empennage is fixed on subsidiary level tail rotor shaft, subsidiary level tail rotor shaft is arranged on subsidiary level empennage servomechanism, and can do along being just parallel to the aircraft X longitudinal axis (wobble shaft) straight line under the control of subsidiary level empennage servomechanism, negative 90 degree of rotations, namely subsidiary level empennage can do along being just parallel to the aircraft X longitudinal axis (wobble shaft) straight line under the control of subsidiary level empennage servomechanism, negative 90 degree of functions of rotating, subsidiary level empennage, subsidiary level tail rotor shaft, subsidiary level empennage servomechanism is arranged on airplane tail group or aircraft stem.
in addition an aircraft tail, comprises the steps: at omniplane descent
step 1, patent 2015203521439, the aircraft of vertical takeoff and landing (VTOL) fixed wing aircraft aloft rotates, complete dynamic vertical tail servomechanism control complete dynamic vertical tail and aircraft rotational circle tangent, subsidiary level empennage servomechanism regulates the angle of subsidiary level empennage, the dynamic adjustments center of gravity of airplane, reaches the object that the center of gravity of airplane overlaps with aircraft rotation center, i.e. aircraft sustained turn.
step 2, patent 2015203521439, the aircraft of vertical takeoff and landing (VTOL) fixed wing aircraft is stable aloft to be rotated, aircraft prow will point near or away from target time, regulate the deflection angle of originally tangent with aircraft rotational circle vertical tail, apply positive force or negative force to aircraft prow direction.
step 3, aircraft prow rotate through point near or away from target time, regulate the deflection angle of vertical tail, return to vertical tail and the tangent state of aircraft rotational circle.
step 4, repeats step 2, step 3 when the next circular movement of aircraft, until aircraft near or away from intended target.
step 5, patent 2015203521439, the aircraft stable rotation in overhead, desired location aloft of vertical takeoff and landing (VTOL) fixed wing aircraft, reduces pitch or the reduction aircraft rotative speed of the complete dynamic aileron in left and right, slowly drops to desired location.
the invention has the beneficial effects as follows, the invention provides patent 2015203521439, vertical takeoff and landing (VTOL) fixed wing aircraft reduces flight resistance in vertical takeoff and landing process, stabilized flight, the technical scheme of precision approach, and the stable landing for aircraft has great importance.
(4) accompanying drawing explanation
fig. 1 is the schematic perspective view of a kind of aircraft tail of the present invention.。
in figure, 1. move vertical tail entirely, and 2. dynamic vertical tail strength beam or entirely dynamic vertical tail reinforced sheet entirely, 3. move vertical tail servomechanism, 4. subsidiary level empennage entirely.
(5) detailed description of the invention
for Fig. 1, complete dynamic vertical tail is fixed on complete dynamic vertical tail S. A. with complete dynamic vertical tail strength beam or complete dynamic vertical tail reinforced sheet in the lump, complete dynamic vertical tail S. A. is arranged on complete dynamic vertical tail servomechanism, subsidiary level empennage is fixed on subsidiary level tail rotor shaft, subsidiary level tail rotor shaft is arranged on subsidiary level empennage servomechanism, complete dynamic vertical tail S. A. is arranged on complete dynamic vertical tail servomechanism and subsidiary level empennage servomechanism controls in real time by aircraft computer, stabilized flight and precision approach.
Claims (7)
1. an aircraft tail, it is characterized in that: by entirely moving vertical tail, complete dynamic vertical tail strength beam or complete dynamic vertical tail reinforced sheet, complete dynamic vertical tail S. A., complete dynamic vertical tail servomechanism, subsidiary level empennage, subsidiary level tail rotor shaft, subsidiary level empennage servomechanism forms, complete dynamic vertical tail is fixed on complete dynamic vertical tail S. A. with complete dynamic vertical tail strength beam or complete dynamic vertical tail reinforced sheet in the lump, complete dynamic vertical tail S. A. is arranged on complete dynamic vertical tail servomechanism, and can do under the control of complete dynamic vertical tail servomechanism and just be parallel to aircraft Z vertical shaft (steering shaft) straight line, negative 180 degree of rotations, namely complete dynamic vertical tail can do along being just parallel to aircraft Z vertical shaft (steering shaft) straight line under the control of complete dynamic vertical tail servomechanism, negative 180 degree of functions of rotating.
2. a kind of aircraft tail according to claim 1, it is characterized in that: subsidiary level empennage is fixed on subsidiary level tail rotor shaft, subsidiary level tail rotor shaft is arranged on subsidiary level empennage servomechanism, and can do along being just parallel to the aircraft X longitudinal axis (wobble shaft) straight line under the control of subsidiary level empennage servomechanism, negative 90 degree of rotations, namely subsidiary level empennage can do along being just parallel to the aircraft X longitudinal axis (wobble shaft) straight line under the control of subsidiary level empennage servomechanism, negative 90 degree of functions of rotating, subsidiary level empennage, subsidiary level tail rotor shaft, subsidiary level empennage servomechanism is arranged on airplane tail group or aircraft stem.
3. a kind of aircraft tail according to claim 1, is characterized in that
comprise the steps: at omniplane descentstep 1, patent 2015203521439, the aircraft of vertical takeoff and landing (VTOL) fixed wing aircraft aloft rotates, complete dynamic vertical tail servomechanism control complete dynamic vertical tail and aircraft rotational circle tangent, subsidiary level empennage servomechanism regulates the angle of subsidiary level empennage, the dynamic adjustments center of gravity of airplane, reaches the object that the center of gravity of airplane overlaps with aircraft rotation center, i.e. aircraft sustained turn.
4. step 2, patent 2015203521439, the aircraft of vertical takeoff and landing (VTOL) fixed wing aircraft is stable aloft to be rotated, aircraft prow will point near or away from target time, regulate the deflection angle of originally tangent with aircraft rotational circle vertical tail, apply positive force or negative force to aircraft prow direction.
5. step 3, aircraft prow rotate through point near or away from target time, regulate the deflection angle of vertical tail, return to vertical tail and the tangent state of aircraft rotational circle.
6. step 4, repeats step 2, step 3 when the next circular movement of aircraft, until aircraft near or away from intended target.
7. step 5, patent 2015203521439, the aircraft stable rotation in overhead, desired location aloft of vertical takeoff and landing (VTOL) fixed wing aircraft, reduces pitch or the reduction aircraft rotative speed of the complete dynamic aileron in left and right, slowly drops to desired location.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510637731.1A CN105129072A (en) | 2015-10-07 | 2015-10-07 | Aircraft tail |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510637731.1A CN105129072A (en) | 2015-10-07 | 2015-10-07 | Aircraft tail |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105129072A true CN105129072A (en) | 2015-12-09 |
Family
ID=54714762
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510637731.1A Pending CN105129072A (en) | 2015-10-07 | 2015-10-07 | Aircraft tail |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105129072A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106902521A (en) * | 2016-10-30 | 2017-06-30 | 天津师范大学 | A kind of modular form launches aerodone |
| CN106902519A (en) * | 2016-10-30 | 2017-06-30 | 天津师范大学 | A kind of ejection type soaring plane model |
| CN106902520A (en) * | 2016-10-30 | 2017-06-30 | 天津师范大学 | It is a kind of that the ejection type soaring aeroplane model for spiraling is regulated and controled by empennage |
| CN106914021A (en) * | 2016-10-30 | 2017-07-04 | 天津师范大学 | A kind of ejection type soaring aeroplane model |
| CN107796670A (en) * | 2017-09-18 | 2018-03-13 | 中国科学院东北地理与农业生态研究所 | A kind of passive atmospheric sampling apparatus and its application method by all-wing aircraft control direction |
-
2015
- 2015-10-07 CN CN201510637731.1A patent/CN105129072A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106902521A (en) * | 2016-10-30 | 2017-06-30 | 天津师范大学 | A kind of modular form launches aerodone |
| CN106902519A (en) * | 2016-10-30 | 2017-06-30 | 天津师范大学 | A kind of ejection type soaring plane model |
| CN106902520A (en) * | 2016-10-30 | 2017-06-30 | 天津师范大学 | It is a kind of that the ejection type soaring aeroplane model for spiraling is regulated and controled by empennage |
| CN106914021A (en) * | 2016-10-30 | 2017-07-04 | 天津师范大学 | A kind of ejection type soaring aeroplane model |
| CN106902519B (en) * | 2016-10-30 | 2023-03-28 | 天津师范大学 | Ejection type gliding aircraft model |
| CN107796670A (en) * | 2017-09-18 | 2018-03-13 | 中国科学院东北地理与农业生态研究所 | A kind of passive atmospheric sampling apparatus and its application method by all-wing aircraft control direction |
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