CN116050101A - Method for improving landing precision of aircraft under influence of ground effect - Google Patents

Method for improving landing precision of aircraft under influence of ground effect Download PDF

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CN116050101A
CN116050101A CN202211686938.4A CN202211686938A CN116050101A CN 116050101 A CN116050101 A CN 116050101A CN 202211686938 A CN202211686938 A CN 202211686938A CN 116050101 A CN116050101 A CN 116050101A
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aircraft
landing
track
pitch angle
angle
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倪金付
黄琪
杨广
蒋盼盼
饶祺
岳定春
朱芸
徐王强
靳宇翔
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Jiangxi Hongdu Aviation Industry Group Co Ltd
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Abstract

The invention discloses a method for improving landing precision of an aircraft under the influence of ground effect, which comprises the following steps: s1, constructing a downslope landing flight dynamics model and a simulation database model; s2, establishing a longitudinal dynamics equation of the aircraft; s3, creating a sliding track in an ideal state; s4, simulating a sliding track in an ideal state, and calculating aerodynamic force data with ground effect; calculating the time variable quantity of parameters such as the aircraft speed, the track angle, the pitch angle speed and the like under the influence of the ground effect; s5, constructing a horizontal tail deflection control equation, and controlling automatic deflection of the horizontal tail according to the horizontal tail deflection control equation to adjust the attitude of the aircraft, so that the track of the aircraft is adjusted, and the aircraft falls in an ideal landing area. The method effectively reduces the influence of ground effect on the landing area, improves the landing precision, and in addition, the deviation is automatically adjusted by the pitch angle and the pitch angle speed feedback horizontal tail without pilot operation, thereby greatly reducing the landing burden of the pilot.

Description

Method for improving landing precision of aircraft under influence of ground effect
Technical Field
The invention belongs to the field of aviation, and particularly relates to a method for improving landing accuracy of an aircraft under the influence of ground effect.
Background
The aircraft is inevitably influenced by the ground effect in the stage of landing approaching the ground, the ground effect changes the flow field around the aircraft, the aerodynamic characteristics of the aircraft are changed when approaching the ground, the motion track and the like of the aircraft at the last moment of landing are influenced, the deviation from an expected landing area is caused, and at the moment, if the pilot is improperly operated, the deviation distance is easily caused to be overlarge, so that landing safety accidents are caused; the invention provides a method for improving landing precision under the influence of an airplane ground effect, which mainly realizes the improvement of landing precision through automatic compensation deflection of an airplane horizontal tail; from the published literature on manipulation control strategies for coping with ground effects, a method for improving landing accuracy by autonomous manipulation of pilots is mentioned, but the time of the aircraft affected by the ground effects during landing is very short, even the pilots have not yet reacted, the aircraft has landed at a place deviated from an ideal landing area, and the landing deviation range is easy to cause and difficult to control due to the difference of the manipulation habits of different pilots, so that the method for reducing the influence of the ground effects on the landing accuracy by autonomous manipulation of pilots has poor operability; in addition, the disclosed literature also provides a full-automatic guiding method for reducing the influence of ground effect on landing precision, but the method has high degree of automation, high requirements on factors such as cooperative coordination of a ground system and an airborne system, data interaction and the like, and high implementation difficulty.
Disclosure of Invention
The invention provides a method for improving landing precision of an aircraft under the influence of ground effect, which can improve track holding capacity of the aircraft in the process of landing approaching the ground, enable the aircraft to fall in an ideal landing area and improve landing precision.
The technical scheme of the invention is as follows:
a method for improving landing precision of an aircraft under the influence of ground effect comprises the following steps:
s1, constructing a landing flight dynamics model according to the stress characteristics and the motion characteristics of an airplane in the landing process, and constructing a simulation database model according to the overall parameters, aerodynamic data, engine data and the like of the airplane;
s2, establishing a longitudinal dynamics equation of the aircraft according to the downslope landing flight dynamics model;
s3, creating a sliding track in an ideal state according to the longitudinal dynamics equation and the simulation database model;
s4, simulating a sliding track in an ideal state, and calculating aerodynamic force data with a ground effect in real time according to the change of the attack angle of the aircraft and the height from the ground; calculating the time variable quantity of parameters such as aircraft speed, track angle, pitch angle speed and the like under the influence of the ground effect according to aerodynamic data with the ground effect and a longitudinal dynamics equation;
s5, constructing a horizontal tail deflection control equation according to the pitch angle and the pitch angle speed, and controlling automatic deflection of the horizontal tail according to the horizontal tail deflection control equation to adjust the attitude of the aircraft, so that the track of the aircraft is adjusted, and the aircraft falls in an ideal landing area.
Further, the aircraft longitudinal dynamics equation is:
Figure BDA0004018574810000021
/>
Figure BDA0004018574810000022
Figure BDA0004018574810000023
wherein V is the flying speed; alpha is the included angle between the flying speed direction and the axis of the machine body; l is the lift force of the air flow acting on the aircraft; d is the resistance of the airflow to the aircraft; p is the thrust of the aircraft engine;
Figure BDA0004018574810000031
is the included angle between the thrust line of the engine and the axis of the engine body; m is the mass of the aircraft; θ is the track angle of the aircraft; g is gravity acceleration; i z The moment of inertia of the aircraft around the pitching axis; m is M z Is the pitching moment of the aircraft; omega z Is the pitch rate of the aircraft; y is p Is the vertical distance from the center of gravity of the aircraft to the thrust line.
Further, creating the lower track in the ideal state in step S3 includes the steps of:
s31, giving initial parameter conditions: the aircraft slides down according to a preset track angle, and parameters such as the weight of the aircraft, the speed of the aircraft, the track angle, the attack angle, the pitch angle speed and the like are kept unchanged;
s32, calculating a longitudinal dynamics equation of the aircraft according to the given initial parameter conditions and the flight time, and solving a sliding track in an ideal state.
Further, the horizontal tail skewness control equation is:
Figure BDA0004018574810000032
delta in e Is the horizontal tail skewness of the aircraft; delta 0 The trimming tail deviation degree is the trimming tail deviation degree under the ideal track state of the airplane;
Figure BDA0004018574810000033
is the pitch angle of the aircraft; />
Figure BDA0004018574810000034
The pitch angle is the pitch angle of the aircraft under the ideal track state; c (C) 1 Is an adjustable parameter item related to pitch angle speed; c (C) 2 Is an adjustable parameter item related to the variation of the pitch angle;
wherein, C1 and C2 are simulation preset values, C1 and C2 can be adjusted according to simulation results, and corresponding optimal values under different working conditions can be obtained through simulation.
The method effectively reduces the influence of ground effect on the landing area, improves the landing precision, and in addition, the deviation is automatically adjusted by the pitch angle and the pitch angle speed feedback horizontal tail without pilot operation, thereby greatly reducing the landing burden of the pilot.
Drawings
FIG. 1 is a schematic diagram of the contrast of lift coefficients for an active and an inactive;
FIG. 2 is a graph showing the pitch moment coefficients versus the active and inactive modes;
FIG. 3 is a graph comparing an ideal downslope landing trajectory with an actual landing trajectory;
FIG. 4 is a graph comparing an ideal glide landing site with an actual landing site;
FIG. 5 is a graph comparing angle of attack in an ideal downslope landing with an actual landing;
FIG. 6 is a graph comparing pitch angle rate in an ideal downslope landing and an actual landing;
FIG. 7 is a graph comparing the landing track of the glide before and after adjustment;
FIG. 8 illustrates a comparison of glide landings before and after adjustment;
FIG. 9 is a graph comparing angle of attack for glide landing before and after adjustment;
FIG. 10 is a graph comparing pitch angle rate of landing with pitch angle of landing;
FIG. 11 is a schematic flow chart of an embodiment of the present invention;
Detailed Description
The present invention will be further described by way of the following examples, however, the scope of the present invention is not limited to the following examples.
Examples: a method for improving landing precision of an aircraft under the influence of ground effect comprises the following steps:
s1, establishing a database model required by landing flight simulation according to overall parameters, aerodynamic data, engine data and the like of an aircraft, and establishing a set of landing dynamics model according to the stress characteristics and the motion characteristics of the aircraft in the landing process.
S2, establishing a longitudinal dynamics equation of the aircraft according to the downslope landing flight dynamics model;
the longitudinal dynamics equation of the aircraft is shown as formulas (1) - (3).
Figure BDA0004018574810000041
Figure BDA0004018574810000051
Figure BDA0004018574810000052
Wherein V is the flying speed; alpha is the included angle between the flying speed direction and the axis of the machine body; l is the lift force of the air flow acting on the aircraft; d is the resistance of the airflow to the aircraft; p is the thrust of the aircraft engine;
Figure BDA0004018574810000053
is the included angle between the thrust line of the engine and the axis of the engine body; m is the mass of the aircraft; θ is the track angle of the aircraft; g is gravity acceleration; i z The moment of inertia of the aircraft around the pitching axis; m is M z Is the pitching moment of the aircraft; omega z Is the pitch rate of the aircraft; y is p Is the vertical distance from the center of gravity of the aircraft to the thrust line.
S3, creating a sliding track in an ideal state according to the longitudinal dynamics equation and the simulation database model;
creating a down track in an ideal state includes the steps of:
s31, giving initial parameter conditions: the aircraft slides down according to a preset track angle, and parameters such as the weight of the aircraft, the speed of the aircraft, the track angle, the attack angle, the pitch angle speed and the like are kept unchanged;
s32, calculating a longitudinal dynamics equation of the aircraft according to the given initial parameter conditions and the flight time, and obtaining the sliding track in an ideal state.
In the process of sliding down and landing, if the weight change of the aircraft is ignored, the aircraft slides down according to a preset track angle and keeps the attack angle basically unchanged, and if the aircraft is not disturbed, the aircraft is in an ideal sliding down state, and parameters such as the flight speed V, the track angle theta, the pitch angle speed omega z and the like in the formulas (1) - (3) are unchanged, so that the ideal sliding down track can be obtained according to the flight speed V and the flight time.
S4, simulating a sliding track in an ideal state, and calculating aerodynamic force data with a ground effect in real time according to the change of the attack angle of the aircraft and the height from the ground; calculating the time variable quantity of parameters such as aircraft speed, track angle, pitch angle speed and the like under the influence of the ground effect according to aerodynamic data with the ground effect and a longitudinal dynamics equation; in actual flight, when the aircraft approaches the ground, the aerodynamic force suffered by the aircraft is affected by the ground effect, a comparison curve of the change of lift coefficient and pitching moment coefficient of the aircraft without the ground effect and the ground effect along with the change of attack angle is given in fig. 1 and 2, and it can be found that when the aircraft approaches the ground from the air, the lift coefficient of the aircraft is increased, and a low moment is brought to the aircraft, and the aerodynamic model with the ground effect is closely related to the height of the aircraft from the ground, so that in the ground effect influence area, the longitudinal aerodynamic model is a two-dimensional database about the attack angle and the height, local aerodynamic data are calculated in real time according to the change of the local attack angle and the height from the ground in simulation, and further, the change quantity of parameters such as the flight speed, the track angle, the pitch angle speed and the like along with time in solution formula (1) to (3) is obtained through numerical integration.
Fig. 3 and 4 show the comparison of an ideal landing trajectory with an actual landing trajectory, and assuming that there is no effect of the ground effect, the aircraft will land on the ideal landing site, and the range of several meters in front of and behind the ideal landing site can be set as an ideal landing area in consideration of the difference of manual manipulation of pilots, and in the actual landing process, the effect of the ground effect will cause the landing site to deviate from the ideal landing area.
S5, constructing a horizontal tail deflection control equation according to the pitch angle and the pitch angle speed, and controlling automatic deflection of the horizontal tail according to the horizontal tail deflection control equation to adjust the attitude of the aircraft, so that the track of the aircraft is adjusted, and the aircraft falls in an ideal landing area.
The invention provides an automatic deflection of a horizontal tail to adjust the attitude of the aircraft, thereby adjusting the track of the aircraft, achieving the aim of enabling the aircraft to fall in an ideal landing area, the deflection strategy of the horizontal tail deflection is to increase the horizontal tail negative deflection through pitch angle and pitch angle speed signal feedback, so that the horizontal tail generates head lifting moment,
equation (4) gives the horizontal tail skewness control equation:
Figure BDA0004018574810000071
delta in e Is the horizontal tail skewness of the aircraft; delta 0 The trimming tail deviation degree is the trimming tail deviation degree under the ideal track state of the airplane;
Figure BDA0004018574810000072
is the pitch angle of the aircraft; />
Figure BDA0004018574810000073
The pitch angle is the pitch angle of the aircraft under the ideal track state; c (C) 1 Is an adjustable parameter item related to pitch angle speed; c (C) 2 Is an adjustable parameter item related to the pitch angle variation.
At the initial of simulation, C can be preset 1 And C 2 Value, then carrying out flight simulation evaluation in the down-landing stage, and carrying out C according to simulation results 1 And C 2 And the value is adjusted, so that the aircraft finally falls in an ideal landing area, and the optimal value corresponding to different landing weights can be obtained through simulation aiming at different working conditions such as different landing weights. 7-10 show the landing simulation results after the horizontal tail deviation adjustment strategy is introduced, and it can be seen that the adjusted landing points are close to ideal landing points and fall in ideal landing areas, and the flight track is also close to the ideal downslope landing track state. Fig. 11 shows a schematic flow chart of the implementation of the scheme of the present invention.
While the fundamental and principal features of the invention and advantages of the invention have been shown and described, it will be apparent to those skilled in the art that the invention is not limited to the details of the foregoing exemplary embodiments, but may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are, therefore, to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present disclosure describes embodiments, not every embodiment is provided with a separate embodiment, and that this description is provided for clarity only, and that the disclosure is not limited to the embodiments described in detail below, and that the embodiments described in the examples may be combined as appropriate to form other embodiments that will be apparent to those skilled in the art.

Claims (4)

1. A method for improving landing precision of an aircraft under the influence of ground effect is characterized by comprising the following steps: the method comprises the following steps:
s1, constructing a landing flight dynamics model according to the stress characteristics and the motion characteristics of an airplane in the landing process, and constructing a simulation database model according to the overall parameters, aerodynamic data, engine data and the like of the airplane;
s2, establishing a longitudinal dynamics equation of the aircraft according to the downslope landing flight dynamics model;
s3, creating a sliding track in an ideal state according to the longitudinal dynamics equation and the simulation database model;
s4, simulating a sliding track in an ideal state, and calculating aerodynamic force data with a ground effect in real time according to the change of the attack angle of the aircraft and the height from the ground; calculating the time variable quantity of parameters such as aircraft speed, track angle, pitch angle speed and the like under the influence of the ground effect according to aerodynamic data with the ground effect and a longitudinal dynamics equation;
s5, constructing a horizontal tail deflection control equation according to the pitch angle and the pitch angle speed, and controlling automatic deflection of the horizontal tail according to the horizontal tail deflection control equation to adjust the attitude of the aircraft, so that the track of the aircraft is adjusted, and the aircraft falls in an ideal landing area.
2. A method of improving landing accuracy of an aircraft under the influence of ground effects according to claim 1, wherein the aircraft longitudinal dynamics equation is:
Figure FDA0004018574800000011
Figure FDA0004018574800000012
Figure FDA0004018574800000013
wherein V is the flying speed; alpha is the included angle between the flying speed direction and the axis of the machine body; l is the lift force of the air flow acting on the aircraft; d is the resistance of the airflow to the aircraft; p is the thrust of the aircraft engine;
Figure FDA0004018574800000021
is the included angle between the thrust line of the engine and the axis of the engine body; m is the mass of the aircraft; θ is the track angle of the aircraft; g is gravity acceleration; i z The moment of inertia of the aircraft around the pitching axis; m is M z Is the pitching moment of the aircraft; omega z Is the pitch rate of the aircraft; y is p Is the vertical distance from the center of gravity of the aircraft to the thrust line.
3. A method of improving landing accuracy of an aircraft under the influence of ground effects according to claim 1, wherein creating a glide track in an ideal state in step S3 comprises the steps of:
s31, giving initial parameter conditions: the aircraft slides down according to a preset track angle, and parameters such as the weight of the aircraft, the speed of the aircraft, the track angle, the attack angle, the pitch angle speed and the like are kept unchanged;
s32, calculating a longitudinal dynamics equation of the aircraft according to the given initial parameter conditions and the flight time, and solving a sliding track in an ideal state.
4. The method for improving landing accuracy of an aircraft under the influence of ground effect according to claim 1, wherein the horizontal tail bias control equation is:
Figure FDA0004018574800000022
delta in e Is the horizontal tail skewness of the aircraft; delta 0 The trimming tail deviation degree is the trimming tail deviation degree under the ideal track state of the airplane;
Figure FDA0004018574800000023
is the pitch angle of the aircraft; />
Figure FDA0004018574800000024
The pitch angle is the pitch angle of the aircraft under the ideal track state; c (C) 1 Is an adjustable parameter item related to pitch angle speed; c2 is an adjustable parameter term related to the amount of pitch angle variation;
wherein, C1 and C2 are simulation preset values, C1 and C2 can be adjusted according to simulation results, and corresponding optimal values under different working conditions can be obtained through simulation.
CN202211686938.4A 2022-12-26 2022-12-26 Method for improving landing precision of aircraft under influence of ground effect Pending CN116050101A (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117452974A (en) * 2023-12-22 2024-01-26 中国航空工业集团公司西安飞机设计研究所 Method and device for optimizing short-distance landing of conveyor airport

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117452974A (en) * 2023-12-22 2024-01-26 中国航空工业集团公司西安飞机设计研究所 Method and device for optimizing short-distance landing of conveyor airport
CN117452974B (en) * 2023-12-22 2024-04-09 中国航空工业集团公司西安飞机设计研究所 Method and device for optimizing short-distance landing of conveyor airport

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