CN113212738A - Method capable of adaptively adjusting focal point position in flight and aircraft - Google Patents
Method capable of adaptively adjusting focal point position in flight and aircraft Download PDFInfo
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- CN113212738A CN113212738A CN202110548392.5A CN202110548392A CN113212738A CN 113212738 A CN113212738 A CN 113212738A CN 202110548392 A CN202110548392 A CN 202110548392A CN 113212738 A CN113212738 A CN 113212738A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/30—Balancing hinged surfaces, e.g. dynamically
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Abstract
The invention discloses a method for self-adaptively adjusting the position of a focal point in flight and an aircraft, wherein the aircraft comprises an aircraft body, a first main wing and a second main wing, wherein the first main wing and the second main wing are positioned on two sides of the aircraft body. The flight control of the aircraft judges the position relation of the center of gravity and the focus through the deflection of the control surface of the tail wing, and then adjusts the position of the main wing through the translation mechanism or the rotating mechanism so as to adjust the focus position of the aircraft, so that the flight center of gravity and the focus are in reasonable and safe positions, the deflection of the control surface of the tail wing is reduced, the aircraft is in a safe flight state, and the flight efficiency is high.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a method for adaptively adjusting the position of a focal point in flight and an aircraft.
Background
The positional relationship of the aircraft focal point (aerodynamic center) to the center of gravity is a determining factor in the longitudinal (pitch) static stability of the aircraft. If the focal point of the aircraft is positioned behind the gravity center, the aerodynamic force increment generates a low head moment to the gravity center, so that the attack angle of the aircraft is reduced, and the aircraft can still return to the original balance position even if not controlled; if the focus is located in front of the center of gravity, the aerodynamic force increment generates a pitching moment to the center of gravity, so that the aircraft continues to raise the head, the deviation continues to be enlarged, and if a pilot or flight control is not controlled in time, the loss of the flight stability is caused until a flight accident occurs. The focus of the existing composite wing aircraft (a fixed wing for lifting and landing) and the fixed wing aircraft is fixed and is very sensitive to the gravity center, so that the requirement on the gravity center of the aircraft for loading goods is strict, the requirement on the installation position is high, and otherwise, flight accidents are easy to happen.
An effective solution to the problems in the related art has not been proposed yet.
Disclosure of Invention
Aiming at the problems in the related art, the invention provides a method for adaptively adjusting the position of a focal point in flight and an aircraft, so as to overcome the technical problems in the prior related art.
Therefore, the invention adopts the following specific technical scheme:
the aircraft capable of adaptively adjusting the focal position in flight comprises an aircraft body, a first main wing and a second main wing, wherein the first main wing and the second main wing are positioned on two sides of the aircraft body.
Preferably, the translation mechanism comprises a support located in the machine body, a transversely arranged screw rod is arranged in the support, a sliding block matched with the screw rod is sleeved on the screw rod, one side of the screw rod is connected with an output end of a servo motor located on the support, and the sliding block is correspondingly connected with the first main wing and the second main wing.
Preferably, the rotating mechanism comprises a first connecting piece and a second connecting piece which are symmetrically arranged in the machine body, a second servo motor is arranged between the first connecting piece and the second connecting piece, a worm is arranged at the output end of the second servo motor, worm gears correspondingly connected with the first connecting piece and the second connecting piece are symmetrically arranged on two sides of the worm, and the first connecting piece and the second connecting piece are correspondingly connected with the first main wing and the second main wing.
Preferably, the load is disposed inside or at the bottom of the body.
Preferably, the tail is a V-shaped tail, a horizontal tail or a canard front wing structure.
The method for self-adaptively adjusting the focal position of the aircraft in flight is characterized in that the flight control of the aircraft judges the position relation of the focal point and the focal point through the deflection of an empennage control surface, and then adjusts the position of a main wing through a translation mechanism or a rotating mechanism so as to adjust the focal position of the aircraft, so that the flight focal point and the focal point are in reasonable and safe positions, the deflection of the empennage control surface is reduced, and the aircraft flies in a safe and balanced state.
Preferably, the method specifically comprises the following steps: in the normal horizontal flight process of the aircraft, the relation between the gravity center of the aircraft and the focus of the aircraft is confirmed through the deflection angle of the control surface of the empennage; when the flight controller gives an instruction for making the control surface of the empennage deviate downwards, the gravity center of the aircraft deviates backwards; when the flight controller gives an instruction to make the control surface of the empennage deviate upwards, the gravity center of the aircraft deviates forwards; when the gravity center is too far forward or far backward, the aircraft can generate extra pitching moment, the flight control can adjust the position of the main wing through the translation or rotating mechanism so as to adjust the position of the focus, and the aircraft is in a state with high balancing efficiency.
The invention has the beneficial effects that: during the normal flat flight process of the aircraft, the flight control of the aircraft judges the position relation of the center of gravity and the focus through the deflection of the control surface of the tail wing, and then the position of the main wing is adjusted through the translation mechanism or the rotating mechanism so as to adjust the focus position of the aircraft, so that the flight center of gravity and the focus are in a reasonable and safe position, the deflection of the control surface of the tail wing is reduced, the aircraft flies in a safe and balanced state, and the flight efficiency is high.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a schematic illustration of an aircraft with adaptive in-flight adjustment of the focal point position in accordance with an embodiment of the present invention;
FIG. 2 is a schematic diagram of a translation mechanism in an aircraft with adaptive in-flight adjustment of a focal point position, according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of a rotary mechanism in an aircraft that is capable of adaptive in-flight adjustment of the focal point position in accordance with an embodiment of the present invention;
FIG. 4 is a schematic diagram of translating the front and rear main wings to change the focal position of the aircraft according to a third embodiment of the present invention;
FIG. 5 is a schematic diagram of a second embodiment of the present invention for changing the focal position of an aircraft by rotating the main wing angle.
In the figure:
1. a body; 2. a first main wing; 3. a second main wing; 4. a load; 5. a tail wing; 6. an empennage control surface; 7. a support; 8. a screw rod; 9. a slider; 10. a first servo motor; 11. a first connecting piece; 12. a second connecting piece; 13. a servo motor II; 14. a worm; 15. a worm gear.
Detailed Description
For further explanation of the various embodiments, the drawings which form a part of the disclosure and which are incorporated in and constitute a part of this specification, illustrate embodiments and, together with the description, serve to explain the principles of operation of the embodiments, and to enable others of ordinary skill in the art to understand the various embodiments and advantages of the invention, and, by reference to these figures, reference is made to the accompanying drawings, which are not to scale and wherein like reference numerals generally refer to like elements.
According to an embodiment of the invention, an aircraft is provided that can adaptively adjust the focus position in flight.
The first embodiment;
as shown in fig. 1 to 5, an aircraft capable of adaptively adjusting a focal point position in flight according to an embodiment of the present invention includes an aircraft body 1, and a first main wing 2 and a second main wing 3 located on two sides of the aircraft body 1, and is characterized in that a load 4 is disposed on the aircraft body 1, the top end of the aircraft body 1 is provided with symmetrically disposed empennages 5, each empennage 5 is provided with an empennage control surface 6 matched with the empennage control surface, and translation mechanisms respectively connected to the first main wing 2 and the second main wing 3 are symmetrically disposed in the aircraft body 1.
Preferably, the load 4 is disposed inside or at the bottom of the body 1.
Preferably, the tail 5 is a V-shaped tail, a horizontal tail or a canard front wing structure.
Example two;
as shown in fig. 1-5, the translation mechanism includes a bracket 7 located in the machine body 1, a lead screw 8 transversely arranged is arranged in the bracket 7, a sliding block 9 matched with the lead screw 8 is sleeved on the lead screw 8, one side of the lead screw 8 is connected with an output end of a servo motor one 10 located on the bracket 7, and the sliding block 9 is correspondingly connected with the main wing one 2 and the main wing two 3. In the normal horizontal flight process of the aircraft, the relation between the gravity center of the aircraft and the focus of the aircraft is confirmed through the deflection angle of the tail wing control surface 6; when the flight controller gives an instruction to make the tail wing control surface 6 deflect downwards, the gravity center of the aircraft is deviated; on the contrary, when the gravity center is too far forward, the aircraft has a low head moment, the flight control can generate a pitching moment by controlling the deflection of the control surface 6 of the tail wing, so that the aircraft is in a balanced state, when the deflection of the control surface 6 of the tail wing is too much, the anti-jamming capability of the aircraft is reduced, and an accident is easy to happen.
Example three;
as shown in fig. 1-5, the machine body 1 is symmetrically provided with a rotating mechanism respectively corresponding to the first main wing 2 and the second main wing 3, the rotating mechanism includes a first connecting piece 11 and a second connecting piece 12 symmetrically arranged in the machine body 1, a second servo motor 13 is arranged between the first connecting piece 11 and the second connecting piece 12, an output end of the second servo motor 13 is provided with a worm 14, two sides of the worm 14 are symmetrically provided with worm gears 15 corresponding to the first connecting piece 11 and the second connecting piece 12, and the first connecting piece 11 and the second connecting piece 12 are correspondingly connected with the first main wing 2 and the second main wing 3. When the flight controller (flight control) judges that the center of gravity is located behind the aircraft focus, the aircraft can automatically rotate or translate the main wing through the rotating mechanism and the translation mechanism to adjust the aircraft focus position (for aircrafts with different layouts, the aircraft focus position can be adjusted through rotating or translating canard wings uniformly) to be located behind the aircraft center of gravity, the aircraft is enabled to go out to be in a stable flight state, and the aircraft focus position is changed by translating the main wing forwards and backwards.
In conclusion, by means of the technical scheme, in the normal horizontal flight process of the aircraft, the relation between the gravity center of the aircraft and the focal point of the aircraft is confirmed through the deflection angle of the tail control surface 6; when the flight controller gives an instruction to make the tail wing control surface 6 deflect downwards, the gravity center of the aircraft is deviated; on the contrary, when the gravity center is too far forward, the aircraft has a low head moment, the flight control can generate a pitching moment by controlling the deflection of the control surface 6 of the tail wing, so that the aircraft is in a balanced state, when the deflection of the control surface 6 of the tail wing is too much, the anti-jamming capability of the aircraft is reduced, and an accident is easy to happen.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (8)
1. The utility model provides an aircraft that can self-adaptation control focus position in flight, includes organism (1) and is located the main wing (2) and the main wing two (3) of organism (1) both sides, its characterized in that, be equipped with load (4) on organism (1), the top of organism (1) is equipped with fin (5) that the symmetry set up, all be equipped with on fin (5) rather than assorted fin rudder face (6), the symmetry be equipped with respectively in organism (1) with main wing (2) with the corresponding translation mechanism or the rotary mechanism who connects of main wing two (3).
2. The aircraft capable of adaptively adjusting the focal position in flight according to claim 1, wherein the translation mechanism comprises a bracket (7) located in the aircraft body (1), a transversely arranged screw rod (8) is arranged in the bracket (7), a sliding block (9) matched with the screw rod (8) is sleeved on the screw rod (8), one side of the screw rod (8) is connected with an output end of a first servo motor (10) located on the bracket (7), and the sliding block (9) is correspondingly connected with the first main wing (2) and the second main wing (3).
3. The aircraft capable of adaptively adjusting the focal position in flight according to claim 1, wherein the rotating mechanism comprises a first connecting piece (11) and a second connecting piece (12) which are symmetrically arranged in the aircraft body (1), a second servo motor (13) is arranged between the first connecting piece (11) and the second connecting piece (12), and an output end of the second servo motor (13) is provided with a worm (14).
4. The aircraft capable of adaptively adjusting the focal position in flight according to claim 3, wherein worm gears (15) connected with the first connecting piece (11) and the second connecting piece (12) are symmetrically arranged on two sides of the worm (14), and the first connecting piece (11) and the second connecting piece (12) are correspondingly connected with the first main wing (2) and the second main wing (3).
5. The aircraft capable of adaptive adjustment of the focal position in flight according to claim 1, characterized in that the load (4) is arranged inside or at the bottom of the airframe (1).
6. An aircraft with adaptive focus adjustment in flight according to claim 1, characterised in that the tail (5) is a V-tail, a horizontal tail or a canard configuration.
7. A method for self-adaptive adjustment of the focal position of an aircraft in flight according to any one of claims 1 to 6, wherein the flight control of the aircraft determines the position relationship between the center of gravity and the focal point through the deflection of the control surface of the tail wing, and then adjusts the position of the main wing through a translation mechanism or a rotation mechanism so as to adjust the focal position of the aircraft, so that the center of gravity and the focal point are in a reasonable and safe position, and the deflection of the control surface of the tail wing is reduced, so that the aircraft flies in a safe and balanced state.
8. The method for the adaptive in-flight adjustment of the focal point position of the aircraft according to claim 7, specifically comprising: in the normal horizontal flight process of the aircraft, the relation between the gravity center of the aircraft and the focus of the aircraft is confirmed through the deflection angle of the control surface of the empennage; when the flight controller gives an instruction for making the control surface of the empennage deviate downwards, the gravity center of the aircraft deviates backwards; when the flight controller gives an instruction to make the control surface of the empennage deviate upwards, the gravity center of the aircraft deviates forwards; when the gravity center is too far forward or far backward, the aircraft can generate extra pitching moment, the flight control can adjust the position of the main wing through the translation or rotating mechanism so as to adjust the position of the focus, and the aircraft is in a state with high balancing efficiency.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110548392.5A CN113212738A (en) | 2021-05-19 | 2021-05-19 | Method capable of adaptively adjusting focal point position in flight and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110548392.5A CN113212738A (en) | 2021-05-19 | 2021-05-19 | Method capable of adaptively adjusting focal point position in flight and aircraft |
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| CN113212738A true CN113212738A (en) | 2021-08-06 |
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| CN202110548392.5A Pending CN113212738A (en) | 2021-05-19 | 2021-05-19 | Method capable of adaptively adjusting focal point position in flight and aircraft |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114001861A (en) * | 2021-10-25 | 2022-02-01 | 中航通飞华南飞机工业有限公司 | Method for determining front and rear limits of water flying gravity center of water surface aircraft |
| CN115126968A (en) * | 2022-05-31 | 2022-09-30 | 国网河北省电力有限公司沧州供电分公司 | Electric power marketing data acquisition device |
| CN115355769A (en) * | 2022-08-23 | 2022-11-18 | 中国空气动力研究与发展中心高速空气动力研究所 | Variable static stability tactical missile aerodynamic configuration and application thereof |
-
2021
- 2021-05-19 CN CN202110548392.5A patent/CN113212738A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114001861A (en) * | 2021-10-25 | 2022-02-01 | 中航通飞华南飞机工业有限公司 | Method for determining front and rear limits of water flying gravity center of water surface aircraft |
| CN114001861B (en) * | 2021-10-25 | 2024-05-24 | 中航通飞华南飞机工业有限公司 | Method for determining front and rear limits of water flight center of gravity of water surface aircraft |
| CN115126968A (en) * | 2022-05-31 | 2022-09-30 | 国网河北省电力有限公司沧州供电分公司 | Electric power marketing data acquisition device |
| CN115355769A (en) * | 2022-08-23 | 2022-11-18 | 中国空气动力研究与发展中心高速空气动力研究所 | Variable static stability tactical missile aerodynamic configuration and application thereof |
| CN115355769B (en) * | 2022-08-23 | 2023-12-29 | 中国空气动力研究与发展中心高速空气动力研究所 | Variable static stability tactical missile pneumatic layout and application thereof |
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