CN-122020857-A - Method and device for determining severe hinge moment of aileron of unmanned aerial vehicle

CN122020857ACN 122020857 ACN122020857 ACN 122020857ACN-122020857-A

Abstract

The invention relates to the technical field of aircraft scheme design, and discloses a method and a device for determining the moment of a serious hinge of an aileron of an unmanned aerial vehicle, wherein the method firstly selects calculation state points in a flight envelope and calculates the attack angle of the unmanned aerial vehicle under each selected calculation state point, and then estimating the aileron rudder output quantity under each calculation state point, carrying out elastic correction on the calculation result, calculating the aileron hinge moment according to the corresponding attack angle and the estimated aileron rudder output quantity under each calculation state point, comparing the obtained aileron hinge moment under all calculation state points, and finally determining the serious value of the aileron hinge moment. The method can quickly and reliably determine the serious hinge moment of the aileron in the design stage of the unmanned aerial vehicle, provides basis for steering engine model selection and the like, avoids the increase of cost, weight and the like caused by over conservation of the hinge moment, and simultaneously can also avoid the design upset in the later stage caused by insufficient hinge moment.

Inventors

YIN JUN
ZHAO CHUANGXIN
GUO QIANG
YAO JIEKE
LIU YUAN
WANG CHENYING
LIU HUI
WANG QINGHU

Assignees

成都飞机工业（集团）有限责任公司

Dates

Publication Date: 20260512
Application Date: 20260210

Claims (13)

1.A method for determining the moment of a severe hinge of an aileron of an unmanned aerial vehicle, the method comprising the steps of: According to possible working condition point positions of the unmanned aerial vehicle aileron severe hinge, selecting the following key point positions as calculation state points in a flight envelope, wherein the key point positions comprise point positions on a maximum table speed line, intersection points of a maximum Mach number and a maximum height, point positions on an equal table speed line and point positions on a minimum table speed line; Based on the selected calculation state points, determining the attack angles corresponding to the plane fly roll maneuver and roll change maneuver of the unmanned plane under each calculation state point; Calculating the rudder output of the aileron of the unmanned aerial vehicle at each calculated state point and correcting the rudder output; according to the attack angle of the unmanned aerial vehicle and the rudder output quantity of the aileron, the aileron hinge moment of the unmanned aerial vehicle under each calculated state point is obtained; And comparing the values of all the calculated hinge moments, and selecting the hinge moment value with the largest absolute value as the serious value of the aileron hinge moment.
2. The method for determining the severe hinge moment of an aileron of an unmanned aerial vehicle according to claim 1, wherein two end points of a maximum table speed line and at least one middle point on the line are selected as calculation status points.
3. The method for determining the severe hinge moment of the aileron of the unmanned aerial vehicle according to claim 1, wherein 1-2 points are arbitrarily selected on a constant-speed table line as calculation state points.
4. The method for determining the severe hinge moment of the aileron of the unmanned aerial vehicle according to claim 1, wherein 1 point position is arbitrarily selected as a calculation state point on a minimum table speed line.
5. The method for determining the serious hinge moment of the aileron of the unmanned aerial vehicle according to claim 1, wherein the attack angle corresponding to the plane fly roll maneuver of the unmanned aerial vehicle is calculated as follows: Obtaining the lift coefficient of the unmanned aerial vehicle under the calculation state point according to the following calculation expression Q×S×CL =mg(1); Wherein Q is flight velocity pressure, S is the whole aircraft reference area, CL is the lift coefficient, m is the unmanned aerial vehicle strength design weight, g is gravity acceleration; And obtaining the attack angle of the unmanned aerial vehicle under the current calculation state point based on the CL-alpha lift coefficient curve.
6. The method for determining the severe hinge moment of an aileron of an unmanned aerial vehicle according to claim 1, wherein the calculation mode of changing the roll of the unmanned aerial vehicle to the corresponding attack angle of the maneuver is as follows: Obtaining the lift coefficient of the unmanned aerial vehicle under the calculation state point according to the following calculation expression Q×S×CL =0.8×Nz×mg(2); Wherein Q is the flying speed pressure of the unmanned aerial vehicle, S is the reference area of the whole machine, CL is the lift coefficient, m is the strength design weight of the unmanned aerial vehicle, g is the gravitational acceleration, and Nz is the normal overload of the whole machine; And obtaining the attack angle of the unmanned aerial vehicle under the current calculation state point based on the CL-alpha lift coefficient curve.
7. The method for determining the serious hinge moment of the aileron of the unmanned aerial vehicle according to claim 1, wherein the calculation mode of the rudder output of the aileron of the unmanned aerial vehicle at each calculation state point is as follows: 0.5×ρ×v 2 ×S×Cl δ ×δ×b = 0.25×ρ×v×S×Cl p ×p×b 2 + 0.5×ρ×v 2 ×S×Cl β ×β×b Formula (3); Wherein ρ is air density, v is flying speed (true speed), S is total aircraft reference area, b is total aircraft extension, cl δ is aileron efficiency, cl p is rolling damping derivative, cl β is rolling moment coefficient-sideslip angle derivative, p is maximum rolling angle rate required by rolling maneuvering process, beta is maximum sideslip angle of rolling maneuvering process, and delta is aileron rudder output quantity of unmanned aircraft.
8. The method for determining the severe hinge moment of the aileron of the unmanned aerial vehicle according to claim 7, wherein the correction mode of the rudder output of the aileron of the unmanned aerial vehicle is as follows: δ 1 =δxk formula (4); delta 1 is the rudder output of the corrected unmanned aerial vehicle aileron, and K is the correction coefficient.
9. The method for determining the severe hinge moment of an aileron of an unmanned aerial vehicle according to claim 1, wherein the calculation mode of the hinge moment of the aileron of the unmanned aerial vehicle is as follows: M J =0.5×ρ×v 2 ×S a ×C a X Cmj (delta, alpha) formula (5); Wherein M J is the control surface hinge moment, S a and C a are the reference area and the reference chord length of the aileron respectively, v is the flying speed (true speed), cmj is the aileron hinge moment coefficient, ρ is the air density, and α is the attack angle of the unmanned plane.
10. The method for determining the severe hinge moment of an unmanned aerial vehicle aileron according to claim 1, wherein if the corrected aileron rudder output amount of the unmanned aerial vehicle exceeds a pneumatically allowed maximum aileron deflection, the pneumatically allowed maximum aileron deflection is taken as the unmanned aerial vehicle aileron rudder output amount.
11. An unmanned aerial vehicle aileron serious hinge moment determining apparatus for implementing the unmanned aerial vehicle aileron serious hinge moment determining method according to any of the preceding claims 1 to 10, comprising: The state point selection module is used for selecting a key point in the flight envelope as a calculation state point according to possible working condition point positions of the serious hinge moment of the aileron of the unmanned aerial vehicle, wherein the calculation state point comprises a point position on a maximum table speed line, an intersection point of a maximum Mach number and a maximum height, a point position on an equal table speed line and a point position on a minimum table speed line; the attack angle determining module is used for determining attack angles corresponding to plane flight roll maneuver and roll change maneuver of the unmanned plane under each calculation state point based on the selected calculation state point; The aileron rudder output calculating and correcting module is used for calculating the aileron rudder output of the unmanned aerial vehicle at each calculated state point according to rolling and changing out maneuver and correcting the aileron rudder output; The aileron hinge moment calculation module is used for obtaining the aileron hinge moment of the unmanned aerial vehicle at each calculation state point according to the attack angle of the unmanned aerial vehicle and the corrected aileron rudder output quantity; And the aileron serious hinge moment determining module is used for carrying out numerical comparison on all calculated hinge moments and selecting a hinge moment value with the largest absolute value as the aileron hinge moment serious value.
12. A storage medium having stored thereon a computer program which, when executed by a processor, implements a method of determining a severe hinge moment of an aileron of a unmanned aerial vehicle as claimed in any of the preceding claims 1 to 10.
13. A computer device comprising a memory, a processor and a computer program stored on the memory and executable in the processor, the processor implementing a method of determining a severe hinge moment of an aileron of a drone according to any of the preceding claims 1-10 when the computer program is executed.

Description

Method and device for determining severe hinge moment of aileron of unmanned aerial vehicle Technical Field The invention relates to the technical field of aircraft scheme design, in particular to a method and a device for determining the moment of a serious hinge of an aileron of an unmanned aerial vehicle. Background In the scheme design stage of the unmanned aerial vehicle, the serious hinge moment of the control surface is one of important parameters to be determined, and a steering engine model selection scheme, a structural arrangement scheme and the like of the unmanned aerial vehicle are directly determined. To obtain accurate severe hinge moment, it is generally necessary to perform flight attitude solutions under various flight conditions within a full envelope, and perform a hinge moment wind tunnel test or CFD calculation within the full envelope, so as to determine the hinge moment within the full envelope, and then perform the most-value screening to obtain a severe value. But this work typically takes several months, which makes it difficult to meet the design requirements of the project phase. Therefore, how to quickly and reliably determine the severe hinge moment of the control surface in the scheme design stage is one of the difficulties in the field. Ailerons are one of the main control surfaces of unmanned aerial vehicles and face the difficulties. The invention patent with publication number CN117669055A discloses a method for determining the maximum hinge moment of an aileron of a transport aircraft, which can quickly calculate the maximum hinge moment of an elevator under the condition of not calculating the full-envelope full-configuration hinge moment, and has higher accuracy of calculation results. But the method is only suitable for transportation airplanes, and meanwhile, the parameters such as aileron deflection (1/3 of maximum deflection), attack angle and the like are selected only as experience values of large transportation airplanes, and the method is lack of accuracy and general. For example, the invention patent with publication number CN119577954a discloses a method for determining the maximum hinge moment of the flap in the design stage of the aircraft scheme, which can quickly obtain the available maximum hinge moment of the flap and support the design of the flap actuator without carrying out wind tunnel test and large amount of calculation of the hinge moment of the full-envelope full-configuration wing in the design stage of the aircraft scheme. However, when the prior art calculates, the maneuvering speed is directly taken as the flight speed corresponding to the maximum hinge moment of the elevator, the steering surface deflection directly takes the positive and negative steering deflection extreme values, and the taking method is only taken according to the development experience of the transport aircraft and has no universal applicability. Disclosure of Invention In order to solve the defects and shortcomings in the prior art, the invention provides a method and a device for determining the serious hinge moment of an aileron of an unmanned aerial vehicle, which can quickly and reliably determine the serious hinge moment of the aileron in the scheme design stage of the unmanned aerial vehicle, provide basis for steering engine type selection and the like, avoid the increase of cost, weight and the like caused by over conservation of the hinge moment, and simultaneously avoid the later design overturned caused by insufficient hinge moment. In order to achieve the above object, the present invention has the following technical scheme: The invention discloses a method for determining the serious hinge moment of an aileron of an unmanned aerial vehicle, which comprises the following steps of firstly determining a plurality of calculation state points in a flight envelope of the unmanned aerial vehicle according to selection rules of corresponding calculation state points, then calculating a plane fly roll maneuver of the unmanned aerial vehicle under each calculation state point and a roll change maneuver corresponding attack angle, then estimating and obtaining the aileron rudder output quantity of the unmanned aerial vehicle under each calculation state point according to the requirement of the unmanned aerial vehicle roll change maneuver, correcting a calculation result, then obtaining the aileron hinge moment of the unmanned aerial vehicle under each calculation state point according to the attack angle of the unmanned aerial vehicle and the corrected aileron rudder output quantity, and finally comparing all calculated hinge moments, and selecting a hinge moment value with the largest absolute value as the aileron hinge moment serious value of the unmanned aerial vehicle. In the invention, the selection rule of the calculation state points means that the selection of the calculation state points takes the key working condition which possibly appears to cover the