CN110539880A - High-overload symmetric maneuvering control method for multi-control-surface flying-wing unmanned aerial vehicle - Google Patents
High-overload symmetric maneuvering control method for multi-control-surface flying-wing unmanned aerial vehicle Download PDFInfo
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- CN110539880A CN110539880A CN201910878108.3A CN201910878108A CN110539880A CN 110539880 A CN110539880 A CN 110539880A CN 201910878108 A CN201910878108 A CN 201910878108A CN 110539880 A CN110539880 A CN 110539880A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/02—Initiating means
- B64C13/16—Initiating means actuated automatically, e.g. responsive to gust detectors
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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
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Abstract
The invention relates to a high-overload symmetric maneuvering control method for a multi-control-surface flying-wing unmanned aerial vehicle, which is characterized by comprising the following steps: the method comprises the following steps: step 1: acquiring a control surface which is firstly subjected to airflow separation and a control surface which has the largest influence on the pitching moment; step 2: the control surface rudder (4) at the outermost side delays the airflow separation of the wingtips; and step 3: the control surface rudder (3) is deflected downwards to make up the lift loss of the outermost control surface rudder (4). The invention does not increase the iterative workload of the pneumatic layout design scheme, the structural weight and the burden of the flight control computer, does not increase the design and manufacturing cost, and is simple and efficient.
Description
Technical Field
The invention relates to an operation method of a multi-control-surface flying-wing unmanned aerial vehicle, in particular to an operation method of a flying-wing unmanned aerial vehicle.
background
In order to consider both the investigation and the cruise task and the high maneuverability, the high-overload maneuvering flying wing unmanned aerial vehicle generally adopts a wing type with smaller curvature and a small aspect ratio pneumatic layout. However, when the angle of attack is slightly larger, the trailing edge of the wing profile with the camber is easy to stall, the wing tip with the small aspect ratio is also easy to stall, and after the two are overlapped, the longitudinal moment characteristic is prone to early deviating from linearity and rising, so that the maximum available angle of attack is limited in a small range, and the high-overload maneuvering capacity and the maneuvering altitude speed range are limited.
the control surface is a movable component of the unmanned aerial vehicle, and the main function of the control surface is to generate pneumatic force and moment increment and change the linear acceleration and the angular acceleration of the unmanned aerial vehicle so as to realize maneuvering. The disclosed data, namely 'research on multi-control surface control distribution technology of tailless flying wing aircraft' and 'research on multi-control surface distribution method of flying wing layout unmanned aerial vehicle' considering nonlinear influence, carry out complex matrix reconstruction and algorithm research on multi-control surface combination distribution, can solve different methods under the condition of obtaining optimization of multiple targets in different flight stages, and can obtain the optimal solution of control surface distribution theoretically if the algorithms are bound in a flight control computer for real-time solution. At present, no control method for improving the high-overload symmetric maneuvering capability of the multi-control-surface flying-wing unmanned aerial vehicle is disclosed in China.
disclosure of Invention
The invention provides a simple and efficient high-overload symmetrical maneuvering control method for a multi-control-surface flying-wing unmanned aerial vehicle, which aims to overcome the defects of the prior art, and achieves the purpose of optimizing the large-attack-angle aerodynamic characteristics of full power and moment by utilizing the action that the control surfaces are positioned at the trailing edge of the airfoil and change the flow field of the whole airfoil after deflection; based on the method, the control surface function is distributed in advance, the control method of the control surface of the wing tip is optimized according to the position difference and the aerodynamic contribution difference of the control surface, and the simple control method is bound to the flight control computer in advance, so that the longitudinal moment characteristic in the case of a large attack angle is improved, the maximum available attack angle is improved, the calculation period of the flight control computer is reduced, the maneuvering capability is improved, and the maneuvering envelope is expanded.
The technical scheme is that the high overload symmetrical maneuvering control method of the multi-control-surface flying-wing unmanned aerial vehicle comprises the following steps: step 1: acquiring a control surface which is firstly subjected to airflow separation and a control surface which has the largest influence on the pitching moment; step 2: the control surface rudder 4 at the outermost side delays the airflow separation of the wing tips; and step 3: the control surface rudder 3 is deflected downwards to make up for the loss of lift of the outermost control surface rudder 4.
Preferably, in step 1, by analyzing the characteristics of the air flow separation, the control surface where the air flow separation occurs first and the control surface having the largest influence on the pitching moment are obtained.
Preferably, in step 1, the flying wing drone is in a swept-back wing layout, the air flow separation starts from the wing tip first, so that the outermost control surface rudder 4 is the control surface where the air flow separation occurs first, and meanwhile, the arm of force of the outermost control surface rudder 4 relative to the center of gravity of the airplane is the largest, so that the influence of the arm of force on the pitching moment is the largest.
Preferably, in step 2, the outermost control surface rudder 4 is deflected upwards at an angle.
preferably, the upward deflection angle delta 4 of the control surface rudder 4 at the outermost side ranges from 5 degrees to 10 degrees.
Preferably the control surface rudder 3 in step 3 is adjacent the outermost control surface rudder 4.
Preferably, in step 3, the angle of the downward deflection of the control surface rudder 3 is optimized according to the following formula,
δ3≤Ｓ４×δ４/Ｓ3
δ3≤Ｓ４×δ４×L４/（Ｓ3×L3）。
Preferably, S3 in the formula represents the area of the control surface rudder 3; s4 represents the area of the outermost control surface rudder 4; l3 represents the distance of the center of the rudder 3 from the center of gravity; l4 represents the distance of the center of the plane of the outermost control surface rudder 4 from the center of gravity.
The invention has the following beneficial effects:
the method achieves the purposes of delaying torque rising, improving available attack angle, improving lift force and improving overload maneuvering capacity by only differentially presetting the control surfaces at the wing tips and optimizing the control method on the premise of not changing aerodynamic layout and structural design scheme.
Drawings
The invention is further described below with reference to the accompanying drawings and implementation steps.
FIG. 1 is a typical multi-control surface flying wing drone aerodynamic layout;
fig. 2 is a method of multi-control surface flying wing drone control surface deflection.
Detailed Description
A high-overload symmetric maneuvering control method for a multi-control-surface flying-wing unmanned aerial vehicle comprises the following steps:
1. control surface with the first air flow separation and control surface with the largest influence on pitching moment
The aerodynamic layout of a typical multi-control-surface flying-wing unmanned aerial vehicle is shown in fig. 1, and the control surface which is firstly subjected to airflow separation and the control surface which has the largest influence on the pitching moment are obtained by analyzing the airflow separation characteristics. The flying wing unmanned aerial vehicle is in a sweepback wing layout, airflow separation starts from a wing tip firstly, so the control surface rudder 4 at the outermost side is the control surface which is firstly subjected to airflow separation, and meanwhile, the force arm of the control surface rudder 4 at the outermost side relative to the gravity center of the aircraft is the largest, so the influence of the force arm on pitching moment is the largest.
2. Up-biased outermost control surface rudder 4 delaying wing tip flow separation
The outermost control surfaces 4 are inclined upwardly by an angle delta 4, typically 5 to 10 degrees. By the control surface 4 which is at the outermost side, the local angle of attack of the wing tip is reduced, thereby delaying the separation of the airflow of the wing tip and delaying the moment from rising.
3. The control surface rudder 3 at the lower inner side makes up the lift loss of the control surface rudder 4 at the outermost side
After the control surface 4 at the outermost side deflects upwards, a negative increment is generated for the whole mechanical force, the lift coefficient under the same attack angle is reduced, the overload capacity is improved disadvantageously, and therefore the lift coefficient needs to be increased under the condition that the moment raising characteristic is not changed. The control surface rudder 3 is closer to the wing, and the contribution to the longitudinal moment is smaller than that of the rudder 4, so that the control surface rudder 3 is properly deflected downwards, the determination of the deflection angle of the control surface rudder 3 is optimized by adopting a formula (1), and the deflection of the control surface rudder 3 can increase the lift coefficient without changing the tendency of delaying the rising of the moment characteristic, so that the high overload capacity is improved, as shown in fig. 2.
δ3≤Ｓ４×δ４/Ｓ3
δ3≤Ｓ４×δ４×L４/（Ｓ3×L3）
In the above formula:
S3 represents the area of rudder 3;
S4 represents the area of rudder 4;
L3 represents the distance of the center of the rudder 3 from the center of gravity;
L4 represents the distance of the center of the rudder 4 from the center of gravity.
Examples
Taking a certain flying wing unmanned aerial vehicle as an example, the moment raising attack angle is increased from 6 degrees to 7 degrees through the control surface 4 at the outermost side deviating from 10 degrees upwards and the control surface rudder 3 deviating from-10 degrees downwards, and the maximum normal overload is improved by 10 percent, so that the high overload maneuvering capacity is improved.
Claims (8)
1. the high-overload symmetric maneuvering control method for the multi-control-surface flying-wing unmanned aerial vehicle is characterized by comprising the following steps: the method comprises the following steps: step 1: acquiring a control surface which is firstly subjected to airflow separation and a control surface which has the largest influence on the pitching moment; step 2: the control surface rudder (4) at the outermost side delays the airflow separation of the wingtips; and step 3: the control surface rudder (3) is deflected downwards to make up the lift loss of the outermost control surface rudder (4).
2. The method for high-overload symmetric maneuvering of multi-control-surface flying-wing drones according to claim 1, characterized by: in the step 1, by analyzing the characteristics of the air flow separation, the control surface which is firstly subjected to the air flow separation and the control surface which has the largest influence on the pitching moment are obtained.
3. The method for high-overload symmetric maneuvering of multi-control-surface flying-wing drones according to claim 2, characterized in that: in the step 1, the flying wing unmanned aerial vehicle is in a sweepback wing layout, airflow separation starts from a wing tip firstly, so that the control surface rudder (4) at the outermost side is the control surface with the airflow separation firstly, and meanwhile, the force arm of the control surface rudder (4) at the outermost side relative to the gravity center of the aircraft is the largest, so that the influence of the control surface rudder on the pitching moment is the largest.
4. The method for high-overload symmetric maneuvering of multi-control-surface flying-wing drones according to claim 1, characterized by:
In step 2, the outermost control surface rudder (4) is deflected upwards by an angle δ 4.
5. The method for high-overload symmetric maneuvering of multi-control-surface flying-wing drones according to claim 4, characterized by comprising the following steps: the range of the upward deflection angle delta 4 of the control surface rudder (4) at the outermost side is 5-10 degrees.
6. the method for high-overload symmetric maneuvering of multi-control-surface flying-wing drones according to claim 2, characterized in that: the control surface rudder (3) in step 3 is adjacent to the outermost control surface rudder (4).
7. The method for high-overload symmetric maneuvering of multi-control-surface flying-wing drones according to claim 1, characterized by: in step 3, the downward deflection angle of the control surface rudder (3) is optimized according to the following formula,
δ3≤Ｓ４×δ４/Ｓ3
δ3≤Ｓ４×δ４×L４/（Ｓ3×L3）。
8. The method for high-overload symmetric maneuvering of multi-control-surface flying-wing drones according to claim 7, characterized by comprising the following steps: s3 in formula (1) represents the area of the control surface rudder (3); s4 represents the area of the outermost control surface rudder (4); l3 represents the distance between the center of the control surface rudder (3) and the center of gravity; l4 represents the distance of the center of the outermost rudder (4) plane from the center of gravity.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112173065A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Be applied to wing of wing aircraft that verts |
| CN113184166A (en) * | 2021-03-31 | 2021-07-30 | 成都飞机工业（集团）有限责任公司 | Stability augmentation control method for flying wing layout unmanned aerial vehicle |
| CN113371171A (en) * | 2021-06-18 | 2021-09-10 | 武汉理工大学 | Deformable rudder blade with self-adaptive deflection front edge and deflection method |
| CN114872883A (en) * | 2022-07-08 | 2022-08-09 | 航空航天工业沈阳六0一科技装备制造有限公司 | Method for changing tail rotor of flying wing type layout airplane |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112173065A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Be applied to wing of wing aircraft that verts |
| CN113184166A (en) * | 2021-03-31 | 2021-07-30 | 成都飞机工业（集团）有限责任公司 | Stability augmentation control method for flying wing layout unmanned aerial vehicle |
| CN113371171A (en) * | 2021-06-18 | 2021-09-10 | 武汉理工大学 | Deformable rudder blade with self-adaptive deflection front edge and deflection method |
| CN113371171B (en) * | 2021-06-18 | 2022-11-15 | 武汉理工大学 | Deformable rudder blade capable of adaptively deflecting front edge and deflection method |
| CN114872883A (en) * | 2022-07-08 | 2022-08-09 | 航空航天工业沈阳六0一科技装备制造有限公司 | Method for changing tail rotor of flying wing type layout airplane |
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Application publication date: 20191206 |