CN108845583A - Improve the jaw channel control method of BTT control aircraft yaw angle rejection ability - Google Patents
Improve the jaw channel control method of BTT control aircraft yaw angle rejection ability Download PDFInfo
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- CN108845583A CN108845583A CN201810618685.4A CN201810618685A CN108845583A CN 108845583 A CN108845583 A CN 108845583A CN 201810618685 A CN201810618685 A CN 201810618685A CN 108845583 A CN108845583 A CN 108845583A
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- yaw angle
- control
- jaw channel
- btt
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot
- G05D1/08—Control of attitude, i.e. control of roll, pitch, or yaw
- G05D1/0808—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft
Abstract
The invention discloses a kind of jaw channel control structures of raising BTT control aircraft yaw angle rejection ability, belong to technical field of flight control.Method provided by the present invention includes：Step 1: inertial navigation solving unit calculates dynamic pressure, Mach number is sent to jaw channel control loop by the attitude angular velocity of sensing element processing unit measurement guided missile, overload；Step 2: yaw overload obtains pseudo- yaw angle by yaw angle reconstruction of function；Step 3: calculating the control parameter of jaw channel according to dynamic pressure, mach indicator；It is instructed Step 3: calculating corresponding rudder according to attitude angular velocity, pseudo- yaw angle and corresponding control parameter；Step 4: giving rudder instruction to steering engine, guided missile control surface deflection is driven, realizes the inhibition to yaw angle.Jaw channel control structure provided by the invention effectively improves the rejection ability to yaw angle, so as to improve the flight Control platform of BTT control aircraft.
Description
Technical field
The present invention relates to aircraft flight control field, it is related to improving the inclined of BTT control aircraft yaw angle rejection ability
Boat channel control method, in particular to control aircraft yaw angle suppressing method using BTT.
Background technique
BTT control provides positive lift by mainpiston, and aircraft guidance instruction is polar form, i.e. synchronization
It provides and overloads motor-driven direction and size, it is dynamic to carry out supercharger on desired direction in space, it needs to control guided missile and quickly rolls
Turn.When the motor-driven and quick rolling of big overload is motor-driven, kinematics coupling, inertia coupling, the pneumatic coupling of guided missile can enhance, and generate
Biggish coupling yaw angle since aerial mission or aircraft feature have inhibition yaw angle demand, for example is started using air suction type
The aircraft of machine inhibits more harsh to yaw angle, and yaw angle can significantly improve the risk of engine misses when increasing,
Nothing is related to improving jaw channel yaw angle rejection ability in current country BTT control flying vehicles control method field
Jaw channel control method.
Summary of the invention
Problems solved by the invention is to provide a kind of jaw channel control method suitable for BTT control aircraft, makes to fly
Row device is completed effectively to inhibit yaw angle while overload is motor-driven and rolling is motor-driven.
A kind of jaw channel control method improving BTT control aircraft yaw angle rejection ability provided by the invention,
Step includes：
Step 1: attitude angular velocity, overload and the inertial navigation solving unit meter of sensing element processing unit measurement guided missile
Calculate dynamic pressure, Mach number is sent to jaw channel control loop；
Step 2: yaw overload obtains pseudo- yaw angle by yaw angle reconstruction of function；
Step 3: the control structure gone out according to given in attitude angular velocity, pseudo- yaw angle and figure calculates corresponding rudder
Instruction；
Step 4: giving rudder instruction to steering engine, guided missile control surface deflection is driven, realizes the inhibition to yaw angle.
Further, yaw angle reconstruction of function input variable is yaw overload, dynamic pressure, Mach number in step 2.
Further, step 3 centered rudder instructs DzCalculation method：Dz=Kωy×ωy+Kbeta×beta.It is ω in formulayPosture
Angular speed, beta are pseudo- yaw angle, the K that reconstruct comes outwyAnd KbetaFor control system parameter.
The rudder calculated instruction Dz is further driven into aircraft rudder deflecting facet, realizes the inhibition to yaw angle.
Advantages of the present invention includes：Provided yaw angle reconstruction of function and jaw channel control structure meter through the invention
Jaw channel control instruction is calculated, solves the aircraft using air admission type engine when the motor-driven and quick rolling of big overload is motor-driven
The problem of coupling and yaw angle caused to increase.
Detailed description of the invention
Fig. 1 is the side path control structure figure that BTT provided by the embodiment of the present invention controls that aircraft yaw angle inhibits.
Specific embodiment
Hereinafter, the present invention is further elaborated in conjunction with the accompanying drawings and embodiments.
In conjunction with reference Fig. 1, sensing element processing unit measures the attitude angular velocity of guided missile, overload, and inertial navigation resolves single
Member calculates dynamic pressure, Mach number is sent to jaw channel control loop, and yaw overload obtains pseudo- side by yaw angle reconstruction of function
Sliding angle is instructed according to attitude angular velocity, pseudo- yaw angle and corresponding control parameter according to corresponding rudder is calculated；Rudder is instructed
Steering engine is given, guided missile control surface deflection is driven, realizes the inhibition to yaw angle.
In one embodiment of the invention, control parameter K is determined previously according to state of flightwy、Kbeta。
In the embodiment, specific workflow is described as follows：
1. sensing element processing unit measures the overload of guided missile, inertial navigation solving unit calculates dynamic pressure, Mach number, leads to
It crosses and pseudo- yaw angle beta is reconstructed with minor function, reconstruction of function is taken as：
Beta=(a1+b1×Ma)×Nz/Q
Ma indicates that Mach number, Q indicate dynamic pressure, N in above formulazIndicate overload, a1、b1For coefficient, a can use1=377682, b1=
85600。
2. measuring the angular velocity omega of guided missile according to sensing element processing unity, reconstruct come pseudo- yaw angle beta and
Calculated control parameter calculates rudder and instructs Dz, calculation method is：
Dz=Kωy×ωy+Kbeta×beta
3. the rudder calculated is instructed Dz, steering engine is given, controls control surface deflection.
The present invention effectively improves the rejection ability to yaw angle by the jaw channel control method based on reconstruct yaw angle,
So as to improve the flight Control platform of BTT control aircraft.
Although the invention has been described by way of example and in terms of the preferred embodiments, but it is not for limiting the present invention, any this field
Technical staff without departing from the spirit and scope of the present invention, may be by the methods and technical content of the disclosure above to this hair
Bright technical solution makes possible variation and modification, therefore, anything that does not depart from the technical scheme of the invention, and according to the present invention
Technical spirit any simple modifications, equivalents, and modifications to the above embodiments, belong to technical solution of the present invention
Protection scope.
Claims (3)
1. it is a kind of improve BTT control aircraft yaw angle rejection ability jaw channel control method, which is characterized in that including with
Lower step：
Step 1: attitude angular velocity, overload and the inertial navigation solving unit of sensing element processing unit measurement guided missile calculate
Dynamic pressure, Mach number are sent to jaw channel control loop；
Step 2: yaw overload obtains pseudo- yaw angle by yaw angle reconstruction of function；
Step 3: calculating corresponding rudder according to attitude angular velocity, pseudo- yaw angle and instructing；
Step 4: giving rudder instruction to steering engine, guided missile control surface deflection is driven, realizes the inhibition to yaw angle.
2. according to a kind of jaw channel control method for improving BTT control aircraft yaw angle rejection ability described in claim 1,
It is characterized in that, yaw angle reconstruction of function input variable is yaw overload N in the step 2z, dynamic pressure Q, Mach number Ma, i.e., it is pseudo-
Yaw angle beta=fun (Nz, Q, Ma).
3. a kind of jaw channel controlling party for improving BTT control aircraft yaw angle rejection ability according to claim 1
Method, which is characterized in that the step 3 centered rudder instructs DzCalculation method：Dz=Kωy×ωy+Kbeta×beta；ω in formulayFor
Attitude angular velocity, beta are pseudo- yaw angle, the K that reconstruct comes outwyAnd KbetaFor control system parameter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810618685.4A CN108845583B (en) | 2018-06-15 | 2018-06-15 | Yaw channel control method for improving sideslip angle inhibition capability of BTT control aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810618685.4A CN108845583B (en) | 2018-06-15 | 2018-06-15 | Yaw channel control method for improving sideslip angle inhibition capability of BTT control aircraft |
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| Publication Number | Publication Date |
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| CN108845583A true CN108845583A (en) | 2018-11-20 |
| CN108845583B CN108845583B (en) | 2021-08-06 |
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| CN201810618685.4A Active CN108845583B (en) | 2018-06-15 | 2018-06-15 | Yaw channel control method for improving sideslip angle inhibition capability of BTT control aircraft |
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Cited By (5)
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| CN111578793A (en) * | 2020-05-07 | 2020-08-25 | 北京星途探索科技有限公司 | Sideslip angle control method for rocket fairing separation in windy condition |
| CN111949043A (en) * | 2020-08-07 | 2020-11-17 | 上海航天控制技术研究所 | Start-control moment online extraction method based on attitude angular velocity discrimination |
| CN112433532A (en) * | 2019-08-26 | 2021-03-02 | 北京理工大学 | Decoupling self-driving instrument considering second-order steering engine dynamics and decoupling control method thereof |
| CN114237295A (en) * | 2021-12-20 | 2022-03-25 | 北京航空航天大学 | Unconventional flight control technology for high-agility air-to-air missile at large angle of attack |
| CN115390590A (en) * | 2022-10-27 | 2022-11-25 | 中南大学 | Large maneuvering control method and related equipment for axisymmetric aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114237295A (en) * | 2021-12-20 | 2022-03-25 | 北京航空航天大学 | Unconventional flight control technology for high-agility air-to-air missile at large angle of attack |
| CN115390590A (en) * | 2022-10-27 | 2022-11-25 | 中南大学 | Large maneuvering control method and related equipment for axisymmetric aircraft |
| CN115390590B (en) * | 2022-10-27 | 2023-02-28 | 中南大学 | Large maneuvering control method and related equipment for axisymmetric aircraft |
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| CN108845583B (en) | 2021-08-06 |
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