CN115657458A - Aircraft climbing track control method based on energy matching - Google Patents

Aircraft climbing track control method based on energy matching Download PDF

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CN115657458A
CN115657458A CN202211405829.0A CN202211405829A CN115657458A CN 115657458 A CN115657458 A CN 115657458A CN 202211405829 A CN202211405829 A CN 202211405829A CN 115657458 A CN115657458 A CN 115657458A
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drone
loop
climbing
transfer function
flight
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凡文帅
于云峰
凡永华
许红羊
李田丰
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Northwestern Polytechnical University
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Abstract

The invention discloses an aircraft climbing track control method based on energy matching, which comprises the following steps: s1: establishing a transfer function of a longitudinal channel of the drone; s2: designing a stability augmentation loop of a control system, and establishing a transfer function of the stability augmentation loop; s3: will gain K ω 、K α And K ny Input into the drone control system, the drone being based on the gain K ω 、K α And K ny Climbing flight is carried out; s4: calculating the difference delta Ma between the Mach number Ma of the actual flight state of the target drone and the Mach number of the reference trajectory, taking the difference delta Ma and the Mach number Ma as an interpolation table of the dynamic amplitude limiting value of the target drone, adjusting the deviation amplitude limiting values of different height positions according to the interpolation table, calculating the reasonable climbing rate of the target drone in the climbing flight segment, and controlling the plane to climb according to the climbing rate. The invention designs a reasonable climbing track of the target drone in the climbing flight process, calculates the reasonable climbing rate of the climbing flight section of the target drone and prevents the occurrence of stallAnd (4) generating.

Description

Aircraft climbing track control method based on energy matching
Technical Field
The invention relates to the field of aircraft fuselages, in particular to an aircraft climbing track control method based on energy matching.
Background
During flight, the forces acting on the drone are mainly gravity, thrust and aerodynamic. If the inclined angle of the climbing trajectory of the target drone is too large in the climbing process and the climbing rate is high, the component of the thrust in the longitudinal direction is large, most of the thrust is used for overcoming the gravity to do work, and the utilization efficiency of the thrust is reduced; if the trajectory tilt angle of the climb segment is too low, the drone will climb very slowly. The target drone takes a long time to climb to a preset height, which causes excessive energy consumption of the target drone, so the design of the climbing track in the takeoff and climbing phase of the target drone is crucial to the whole flight process.
Therefore, the invention provides an aircraft climbing track control method based on energy matching for the first time, and a reasonable climbing track of a target drone in the climbing flight process is designed. If the speed of the target drone is lower in the climbing stage, the trajectory inclination angle of the climbing flight of the target drone is smaller in the speed lifting stage, the thrust of the target drone is mainly used for lifting the speed, the longitudinal component of the thrust is smaller, the aerodynamic lift is smaller, and the target drone climbs more gently. After passing through the speed lifting section, the target drone has a higher speed and enters the height lifting section. The flight speed of the target drone at the height lifting section is high, the generated lift force is high, the gravity is overcome by the aerodynamic lift force of the target drone, the resistance is overcome by the thrust, and the trajectory inclination angle of the target drone at the height lifting section is high, so that the target drone can climb to a preset height more steeply.
Disclosure of Invention
In order to overcome the defects in the prior art, the invention provides an aircraft climbing track control method based on energy matching.
In order to achieve the purpose of the invention, the technical scheme adopted by the invention is as follows:
the method for controlling the climbing track of the aircraft based on energy matching comprises the following steps:
s1: establishing dynamic models of the drone aircraft at different heights and Mach numbers in a climbing section, and performing small disturbance linearization and Laplace transformation on the dynamic models to obtain a transfer function of a longitudinal channel of the drone aircraft;
s2: designing a stability augmentation loop of a control system, establishing a transfer function of the stability augmentation loop, and calculating a gain K of an angular rate feedback loop ω Control gain K of pseudo attack angle feedback loop α And control gain K of different heights and different Mach numbers ny ；
S3: will gain K ω 、K α And K ny Input into the drone aircraft control system, the drone aircraft being based on the gain K ω 、K α And K ny Climbing flight is carried out;
s4: calculating the difference delta Ma between the Mach number Ma of the actual flight state of the target drone and the Mach number of the reference trajectory, taking the difference delta Ma and the Mach number Ma as an interpolation table of the dynamic amplitude limiting value of the target drone, adjusting the deviation amplitude limiting values of different height positions according to the interpolation table, calculating the reasonable climbing rate of the target drone in the climbing flight segment, and controlling the plane to climb according to the climbing rate.
Further, step S1 includes:
s11: establishing a dynamic equation of a longitudinal channel of the drone:
Figure BDA0003937087610000021
wherein: theta is the trajectory inclination, m is the mass of the drone, V is the speed of the drone, P is the thrust of the drone, alpha is the angle of attack, X is the axial force, Y is the normal force, J z Is the pitch moment of inertia, omega z For pitch angle rate, M z In order to be the pitching moment,
Figure BDA0003937087610000031
is a pitch angle, t is a flight time, g is a gravitational acceleration, y is a normal flight distance, and x is an axial flight distance;
in the kinetic equation:
Figure BDA0003937087610000032
wherein, C y Lifting system for a droneNumber, q is the current dynamic pressure of the drone, q =1/2 ρ V 2 S is the reference area of the drone, ma is the Mach number, δ z is a pitch rudder deflection angle;
s12: carrying out small-disturbance linearization on the kinetic equation to obtain a differential equation set:
Figure BDA0003937087610000033
in system of differential equations
Figure BDA0003937087610000034
a 4 ＝(P+Y α )/(mV)，
Figure BDA0003937087610000035
Wherein, a 1 、a 2 、a 3 、a 4 、a 5 Are all kinetic coefficients, Y α Is the normal force in the direction of the angle of attack,
Figure BDA0003937087610000036
the normal force in the deflection angle direction of the pitching rudder;
s13: the transfer function of the longitudinal channel of the drone is obtained by carrying out Laplace transformation on a differential equation set and neglecting the small amount of the dynamic coefficient of the reaction projectile body and the control surface washing:
Figure BDA0003937087610000041
wherein n is y Normal overload;
further, step S2 includes:
s21: designing a stability augmentation loop of an automatic pilot of the target drone, wherein the stability augmentation loop comprises an angular rate loop and a pseudo attack angle loop;
s22: according to the control parameter and the transfer function of the stability augmentation loop, an open-loop transfer function omega of the angular rate loop is established z Open(s) and closed loop transfer function ω z _close(s)：
Figure BDA0003937087610000042
Figure BDA0003937087610000043
Wherein the content of the first and second substances,
Figure BDA0003937087610000044
is the gain of the angular rate feedback loop;
s23: establishing a pseudo attack angle loop open loop transfer function alpha _ open(s) and a pseudo attack angle loop closed loop transfer function alpha _ close(s):
Figure BDA0003937087610000045
Figure BDA0003937087610000046
wherein, K α Control gain for pseudo attack angle feedback loop
S24: establishing a characteristic polynomial equation det(s) corresponding to the ideal pole:
Figure BDA0003937087610000051
where ξ and ω n Damping ratio and frequency corresponding to the ideal pole respectively;
s25: using characteristic polynomial equation det(s) and open-loop transfer function omega z Open(s), closed loop transfer function omega z The _ close(s), the pseudo attack angle loop open loop transfer function α _ open(s), and the pseudo attack angle loop closed loop transfer function α _ close(s) result in:
Figure BDA0003937087610000052
s26: gain of angular rate feedback loop and control gain K of pseudo attack angle feedback loop of control system of automatic pilot α Comprises the following steps:
Figure BDA0003937087610000053
s27: setting control gains K of different heights and different Mach numbers of the target drone according to the amplitude margin, the phase angle margin and the rise time T of the control system ny ：
Figure BDA0003937087610000054
Further, step S4 includes:
s41: calculating a difference value delta Ma between the Mach number Ma of the actual flight state of the drone and the Mach number of the reference trajectory, and taking the difference value delta Ma and the Mach number Ma as an interpolation table of the dynamic amplitude limit value of the drone, wherein the Mach number Ma is a horizontal axis variable of the interpolation table, and the difference value delta Ma is a longitudinal variable of the interpolation table;
s42: collecting the Mach number Ma of the target drone in the climbing stage, and when the Mach number Ma is in the interval [ Ma Standard of reference -Ma Wave motion ，Ma Standard of merit +Ma Wave motion ]If yes, judging the size of the difference value delta Ma:
if Delta Ma is more than or equal to Delta Ma Threshold value Outputting an interpolation table through an interpolation module, and selecting a smaller deviation amplitude limit value in the interpolation table, thereby ensuring the stable flight of the aircraft;
if Δ Ma < Δ Ma Threshold value Outputting an interpolation table through an interpolation module, and selecting a larger deviation amplitude limit value in the interpolation table, so that the aircraft is ensured to have enough energy tracking reference trajectory;
s43: and calculating the reasonable climbing rate of the climbing flight section of the target plane according to the obtained deviation amplitude limit value, and controlling the plane to climb according to the climbing rate.
Further, the method also comprises the following steps:
s5: selecting a plurality of characteristic points on the flight trajectory of the target drone, collecting different heights and different Mach numbers on the different characteristic points, checking the performance margin of the autopilot according to the different heights and the different Mach numbers, and comparing the amplitude margin, the phase angle margin, the cut-off frequency and the rise time on all the characteristic points with corresponding expected indexes respectively to make the amplitude margin, the phase angle margin, the cut-off frequency and the rise time on all the characteristic points accord with the expected indexes.
The invention has the beneficial effects that: the invention provides an aircraft climbing track control method based on energy matching, which is used for designing a reasonable climbing track of a target drone in the climbing flight process, wherein if the speed of the target drone in the climbing stage is lower, the trajectory inclination angle of the target drone in the climbing flight in the speed lifting stage is smaller, the thrust of the target drone is mainly used for lifting the speed, the longitudinal component of the thrust is smaller, the aerodynamic lift is smaller, and the target drone climbs more gently. After passing through the speed lifting section, the target drone has a higher speed and enters the height lifting section. The flight speed of the target drone at the height lifting section is high, the generated lift force is high, the gravity is overcome by the aerodynamic lift force of the target drone, the resistance is overcome by the thrust, and the trajectory inclination angle of the target drone at the height lifting section is high, so that the target drone can climb to a preset height more steeply.
According to the actual flight Mach number Ma in the climbing flight process, the Mach number of the reference trajectory and the error delta Ma of the actual flight Mach number, a two-dimensional interpolation table of dynamic amplitude limiting values is designed to obtain amplitude limiting values changing in real time, different height position deviation amplitude limiting values are selected according to different flight states of the target drone so as to match the real-time energy of the target drone, the reasonable climbing rate of the climbing flight section of the target drone is calculated, and stalling is prevented.
Drawings
FIG. 1 is a diagram of a height control loop.
Fig. 2 is a block diagram of a dynamic clipping value structure.
Fig. 3 is a mach number plot.
Fig. 4 is a height profile.
Figure 5 is a ballistic dip curve.
Detailed Description
The following description of the embodiments of the present invention is provided to facilitate the understanding of the present invention by those skilled in the art, but it should be understood that the present invention is not limited to the scope of the embodiments, and it will be apparent to those skilled in the art that various changes may be made without departing from the spirit and scope of the invention as defined and defined in the appended claims, and all matters produced by the invention using the inventive concept are protected.
The aircraft climbing track control method based on energy matching comprises the following steps:
s1: establishing dynamic models of the target drone at different heights and Mach numbers in a climbing section, and performing small disturbance linearization and Laplace transformation on the dynamic models to obtain a transfer function of a longitudinal channel of the target drone; the step S1 comprises the following steps:
s11: establishing a dynamic equation of a longitudinal channel of the drone:
Figure BDA0003937087610000081
wherein: theta is the trajectory inclination, m is the mass of the drone, V is the speed of the drone, P is the thrust of the drone, alpha is the angle of attack, X is the axial force, Y is the normal force, J z Is the pitch moment of inertia, omega z For pitch angle rate, M z In order to be the pitching moment,
Figure BDA0003937087610000085
is a pitch angle, t is a flight time, g is a gravitational acceleration, y is a normal flight distance, and x is an axial flight distance;
in the kinetic equation:
Figure BDA0003937087610000082
wherein, C y Q is the lift coefficient of the drone, q is the current dynamic pressure of the drone, q =1/2 ρ V 2 S is the reference area of the target, γ V In order to obtain the speed-rolling angle,
Figure BDA0003937087610000083
ballistic declination, ma Mach number, delta z Is the pitch rudder deflection angle;
s12: carrying out small-disturbance linearization on the kinetic equation to obtain a differential equation set:
Figure BDA0003937087610000084
system of differential equations
Figure BDA0003937087610000091
a 4 ＝(P+Y α )/(mV)，
Figure BDA0003937087610000092
Wherein, a 1 、a 2 、a 3 、a 4 、a 5 Are all kinetic coefficients, Y α Is the normal force in the direction of the angle of attack,
Figure BDA0003937087610000093
the normal force in the deflection angle direction of the pitching rudder;
s13: the transfer function of the longitudinal channel of the drone is obtained by carrying out Laplace transformation on a differential equation set and neglecting the small amount of the dynamic coefficient of the reaction projectile body and the control surface washing:
Figure BDA0003937087610000094
wherein n is y Normal overload;
s2: designing a stability augmentation loop of a control system, as shown in fig. 1, establishing a transfer function of the stability augmentation loop through a height control loop structure diagram, and calculating a gain K of an angular rate feedback loop ω Control gain K of pseudo attack angle feedback loop α And control gain K of different heights and different Mach numbers ny ；
The step S2 comprises the following steps:
s21: designing a stability augmentation loop of an automatic pilot of the target drone, wherein the stability augmentation loop comprises an angular rate loop and a pseudo attack angle loop;
s22: according to the control parameter and the transfer function of the stability augmentation loop, an open-loop transfer function omega of the angular rate loop is established z Open(s) and closed loop transfer function ω z _close(s)：
Figure BDA0003937087610000101
Figure BDA0003937087610000102
Wherein the content of the first and second substances,
Figure BDA0003937087610000103
in order to be the gain of the angular rate feedback loop,
s23: establishing a pseudo attack angle loop open loop transfer function alpha _ open(s) and a pseudo attack angle loop closed loop transfer function alpha _ close(s):
Figure BDA0003937087610000104
Figure BDA0003937087610000105
wherein, K α A control gain of a pseudo attack angle feedback loop;
s24: establishing a characteristic polynomial equation det(s) corresponding to the ideal pole:
Figure BDA0003937087610000106
where ξ and ω n Damping ratio and frequency corresponding to the ideal pole respectively;
s25: using a characteristic polynomial equation det(s),Open loop transfer function omega z Open(s), closed loop transfer function omega z The _ close(s), the pseudo attack angle loop open loop transfer function α _ open(s), and the pseudo attack angle loop closed loop transfer function α _ close(s) result in:
Figure BDA0003937087610000107
s26: gain of angular rate feedback loop and control gain K of pseudo attack angle feedback loop of control system of automatic pilot α Comprises the following steps:
Figure BDA0003937087610000111
s27: setting control gains K of different heights and different Mach numbers of the target drone according to the amplitude margin, the phase angle margin and the rise time T of the control system ny ：
Figure BDA0003937087610000112
Where V is the velocity.
S3: will gain K ω 、K α And K ny Input into the drone aircraft control system, the drone aircraft being based on the gain K ω 、K α And K ny Climbing flight is carried out;
s4: calculating a difference value delta Ma between the Mach number Ma of the actual flight state of the target drone and the Mach number of the reference trajectory, taking the difference value delta Ma and the Mach number Ma as an interpolation table of dynamic amplitude limiting values of the target drone, adjusting deviation amplitude limiting values of different height positions according to the interpolation table, calculating a reasonable climbing rate of a climbing flight segment of the target drone as shown in fig. 2, and controlling the aircraft to climb according to the climbing rate. Step S4 comprises the following steps:
s41: calculating a difference value delta Ma between the Mach number Ma of the actual flight state of the drone and the Mach number of the reference trajectory, and taking the difference value delta Ma and the Mach number Ma as an interpolation table of the dynamic amplitude limit value of the drone, wherein the Mach number Ma is a horizontal axis variable of the interpolation table, and the difference value delta Ma is a longitudinal variable of the interpolation table;
s42: collecting the Mach number Ma of the target drone in the climbing stage, and when the Mach number Ma is in the interval [ Ma Standard of merit -Ma Wave motion ，Ma Standard of merit +Ma Wave motion ]And if so, judging the magnitude of the difference value delta Ma:
if Delta Ma is more than or equal to Delta Ma Threshold value Outputting an interpolation table through an interpolation module, and selecting a smaller deviation amplitude limit value in the interpolation table, thereby ensuring the stable flight of the aircraft;
if Δ Ma < Δ Ma Threshold value Outputting an interpolation table through an interpolation module, and selecting a larger deviation amplitude limit value in the interpolation table, so that the aircraft is ensured to have enough energy tracking reference trajectory;
s43: and calculating the reasonable climbing rate of the climbing flight section of the target plane according to the obtained deviation amplitude limit value, and controlling the plane to climb according to the climbing rate.
Through the interpolation table of the dynamic amplitude limiting value, the longitudinal variable of the interpolation table is the difference delta Ma between the Mach number Ma of the reference trajectory and the Mach number of the actual flight state, and the horizontal axis variable of the interpolation table is the Mach number Ma of the actual flight of the drone. When the flight Mach number of the drone in the climbing section reaches a value, if the value of delta Ma is large, a small amplitude limit value is obtained through an interpolation table, and if the value of delta Ma is small, the actual flight Mach number of the drone is close to the reference trajectory Mach number, a large amplitude limit value is obtained through the interpolation table.
Further comprising:
s5: selecting a plurality of characteristic points on the flight trajectory of the target drone, collecting different heights and different Mach numbers on the different characteristic points, checking the performance margin of the autopilot according to the different heights and the different Mach numbers, and comparing the amplitude margin, the phase angle margin, the cut-off frequency and the rise time on all the characteristic points with corresponding expected indexes respectively to make the amplitude margin, the phase angle margin, the cut-off frequency and the rise time on all the characteristic points accord with the expected indexes.
The effectiveness of the effect of the invention is verified through simulation verification, and the method comprises the following steps:
and selecting a module of the dynamic amplitude limiting value to be added into the six-degree-of-freedom model, and verifying the effectiveness and feasibility of the method. According to the fact that the drag of a target drone in a certain model is increased and the thrust is reduced in the pulling-bias simulation climbing process, the Mach number rises slowly in the climbing process, in order to prevent the target drone from stalling, a dynamic amplitude limit is added after the altitude position deviation, the actual flight Mach number and the reference trajectory Mach number are compared with each other, the dynamic amplitude limit value is output, and the obtained simulation result is shown in the figures 3-5.

Claims (5)

1. An aircraft climbing track control method based on energy matching is characterized by comprising the following steps:
s1: establishing dynamic models of the drone aircraft at different heights and Mach numbers in a climbing section, and performing small disturbance linearization and Laplace transformation on the dynamic models to obtain a transfer function of a longitudinal channel of the drone aircraft;
s2: designing a stability augmentation loop of a control system, establishing a transfer function of the stability augmentation loop, and calculating a gain K of an angular rate feedback loop ω Control gain K of pseudo attack angle feedback loop α And control gain K of different heights and different Mach numbers ny ；
S3: will gain K ω 、K α And K ny Input into the drone aircraft control system, the drone aircraft being based on the gain K ω 、K α And K ny Climbing flight is carried out;
s4: calculating the difference delta Ma between the Mach number Ma of the actual flight state of the target drone and the Mach number of the reference trajectory, taking the difference delta Ma and the Mach number Ma as an interpolation table of the dynamic amplitude limiting value of the target drone, adjusting the deviation amplitude limiting values of different height positions according to the interpolation table, calculating the reasonable climbing rate of the target drone in the climbing flight segment, and controlling the plane to climb according to the climbing rate.
2. The energy matching-based aircraft climb trajectory control method of claim 1, wherein the step S1 comprises:
s11: establishing a dynamic equation of a longitudinal channel of the drone:
Figure FDA0003937087600000011
wherein: theta is the trajectory inclination, m is the mass of the drone, V is the speed of the drone, P is the thrust of the drone, alpha is the angle of attack, X is the axial force, Y is the normal force, J z To the moment of inertia in pitch, ω z For pitch angle rate, M z In order to be the pitching moment,
Figure FDA0003937087600000021
is a pitch angle, t is a flight time, g is a gravitational acceleration, y is a normal flight distance, and x is an axial flight distance;
in the kinetic equation:
Figure FDA0003937087600000022
wherein, C y Q is the lift coefficient of the drone, q is the current dynamic pressure of the drone, q =1/2 ρ V 2 S is the reference area of the drone, ma is the Mach number, delta z Is the pitch rudder deflection angle;
s12: carrying out small-disturbance linearization on the kinetic equation to obtain a differential equation set:
Figure FDA0003937087600000023
in system of differential equations
Figure FDA0003937087600000024
a 4 ＝(P+Y α )/(mV)，
Figure FDA0003937087600000025
Wherein, a 1 、a 2 、a 3 、a 4 、a 5 Are all kinetic coefficients, Y α Is the normal force in the direction of the angle of attack,
Figure FDA0003937087600000026
the normal force in the deflection angle direction of the pitching rudder;
s13: the transfer function of the longitudinal channel of the drone is obtained by carrying out Laplace transformation on a differential equation set and neglecting the small amount of the dynamic coefficient of the reaction projectile body and the control surface washing:
Figure FDA0003937087600000031
wherein n is y Is normally overloaded.
3. The energy matching-based aircraft climb trajectory control method of claim 1, wherein the step S2 comprises:
s21: designing a stability augmentation loop of an automatic pilot of the target drone, wherein the stability augmentation loop comprises an angular rate loop and a pseudo attack angle loop;
s22: according to the control parameter and the transfer function of the stability augmentation loop, an open-loop transfer function omega of the angular rate loop is established z Open(s) and closed loop transfer function ω z _close(s)：
Figure FDA0003937087600000032
Figure FDA0003937087600000033
Wherein the content of the first and second substances,
Figure FDA0003937087600000034
in order to be the gain of the angular rate feedback loop,
s23: establishing a pseudo attack angle loop open loop transfer function alpha _ open(s) and a pseudo attack angle loop closed loop transfer function alpha _ close(s):
Figure FDA0003937087600000035
Figure FDA0003937087600000036
wherein, K α Control gain of the pseudo attack angle feedback loop;
s24: establishing a characteristic polynomial equation det(s) corresponding to the ideal pole:
Figure FDA0003937087600000041
where ξ and ω n Damping ratio and frequency corresponding to the ideal pole respectively;
s25: using characteristic polynomial equation det(s) and open-loop transfer function omega z Open(s), closed loop transfer function omega z The _ close(s), the pseudo attack angle loop open loop transfer function α _ open(s), and the pseudo attack angle loop closed loop transfer function α _ close(s) result in:
Figure FDA0003937087600000042
s26: gain of angular rate feedback loop and control gain K of pseudo attack angle feedback loop of control system of automatic pilot α Comprises the following steps:
Figure FDA0003937087600000043
s27: setting control gains K of different heights and different Mach numbers of the target drone according to the amplitude margin, the phase angle margin and the rise time T of the control system ny ：
Figure FDA0003937087600000044
4. The energy matching-based aircraft climb trajectory control method of claim 1, wherein the step S4 comprises:
s41: calculating a difference value delta Ma between the Mach number Ma of the actual flight state of the drone and the Mach number of the reference trajectory, and taking the difference value delta Ma and the Mach number Ma as an interpolation table of the dynamic amplitude limit value of the drone, wherein the Mach number Ma is a horizontal axis variable of the interpolation table, and the difference value delta Ma is a longitudinal variable of the interpolation table;
s42: collecting the Mach number Ma of the target drone in the climbing stage, and when the Mach number Ma is in the interval [ Ma Standard of merit -Ma Wave motion ，Ma Standard of merit +Ma Wave motion ]And if so, judging the magnitude of the difference value delta Ma:
if Delta Ma is more than or equal to Delta Ma Threshold value Outputting an interpolation table through an interpolation module, and selecting a smaller deviation amplitude limit value in the interpolation table, thereby ensuring the stable flight of the aircraft;
if Δ Ma < Δ Ma Threshold value Outputting an interpolation table through an interpolation module, and selecting a larger deviation amplitude limit value in the interpolation table, so that the aircraft is ensured to have enough energy tracking reference trajectory;
s43: and calculating the reasonable climbing rate of the climbing flight section of the target plane according to the obtained deviation amplitude limit value, and controlling the plane to climb according to the climbing rate.
5. The energy matching-based aircraft climb trajectory control method of claim 1, further comprising:
s5: selecting a plurality of characteristic points on the flight trajectory of the target drone, collecting different heights and different Mach numbers on the different characteristic points, checking the performance margin of the autopilot according to the different heights and the different Mach numbers, and comparing the amplitude margin, the phase angle margin, the cut-off frequency and the rise time on all the characteristic points with corresponding expected indexes respectively to make the amplitude margin, the phase angle margin, the cut-off frequency and the rise time on all the characteristic points accord with the expected indexes.
CN202211405829.0A 2022-11-10 2022-11-10 Aircraft climbing track control method based on energy matching Pending CN115657458A (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117075481A (en) * 2023-10-13 2023-11-17 中国空气动力研究与发展中心高速空气动力研究所 Mach number composite control method for wind tunnel transonic ladder variable attack angle test

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117075481A (en) * 2023-10-13 2023-11-17 中国空气动力研究与发展中心高速空气动力研究所 Mach number composite control method for wind tunnel transonic ladder variable attack angle test
CN117075481B (en) * 2023-10-13 2023-12-19 中国空气动力研究与发展中心高速空气动力研究所 Mach number composite control method for wind tunnel transonic ladder variable attack angle test

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