CN108845583B - Yaw channel control method for improving sideslip angle inhibition capability of BTT control aircraft - Google Patents
Yaw channel control method for improving sideslip angle inhibition capability of BTT control aircraft Download PDFInfo
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- CN108845583B CN108845583B CN201810618685.4A CN201810618685A CN108845583B CN 108845583 B CN108845583 B CN 108845583B CN 201810618685 A CN201810618685 A CN 201810618685A CN 108845583 B CN108845583 B CN 108845583B
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- 238000000034 method Methods 0.000 title claims abstract description 14
- 230000005764 inhibitory process Effects 0.000 title abstract description 10
- 230000001629 suppression Effects 0.000 claims description 6
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 abstract description 4
- 230000008878 coupling Effects 0.000 description 4
- 238000010168 coupling process Methods 0.000 description 4
- 238000005859 coupling reaction Methods 0.000 description 4
- 238000005096 rolling process Methods 0.000 description 2
- 238000004364 calculation method Methods 0.000 description 1
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- 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
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Abstract
The invention discloses a yaw channel control structure for improving the sideslip angle inhibition capability of a BTT control aircraft, and belongs to the technical field of flight control. The method provided by the invention comprises the following steps: firstly, measuring the attitude angular velocity and overload of a missile by a sensitive element processing unit, and calculating dynamic pressure and Mach number by a strapdown inertial navigation resolving unit and sending the dynamic pressure and the Mach number to a yaw channel control loop; step two, obtaining a pseudo sideslip angle through a sideslip angle reconstruction function in yaw overload; step three, calculating control parameters of a yaw channel according to the dynamic pressure and the Mach number; step three, calculating a corresponding rudder instruction according to the attitude angular velocity, the pseudo sideslip angle and the corresponding control parameter; and step four, sending a rudder instruction to the steering engine to drive the missile rudder surface to deflect, and realizing the inhibition of the sideslip angle. The yaw channel control structure provided by the invention effectively improves the inhibition capability on the sideslip angle, thereby improving the flight control quality of the BTT control aircraft.
Description
Technical Field
The invention relates to the field of flight control of aircrafts, in particular to a yaw channel control method for improving the sideslip angle inhibition capability of a BTT control aircraft, and particularly relates to a method for inhibiting the sideslip angle of the BTT control aircraft.
Background
The BTT control provides positive lift force through a main lifting surface, the aircraft guidance instruction is in a polar coordinate form, namely the direction and the size of the overload maneuver are given at the same time, and the missile is required to be controlled to roll quickly for the overload maneuver in the required spatial direction. The kinematic coupling, the inertial coupling and the pneumatic coupling of the missile can be enhanced during large overload maneuver and fast rolling maneuver, a larger coupling sideslip angle is generated, the requirement of suppressing the sideslip angle is met due to flight mission or characteristics of the aircraft, for example, the aircraft adopting an air suction type engine has severe suppression on the sideslip angle, the risk of engine flameout can be obviously improved when the sideslip angle is increased,
at present, in the field of domestic BTT control aircraft control methods, a yaw channel control method for improving the sideslip angle inhibition capability of a yaw channel is absent.
Disclosure of Invention
The invention aims to provide a yaw channel control method suitable for a BTT control aircraft, so that the aircraft can complete overload maneuver and roll maneuver and can effectively inhibit a sideslip angle.
The invention provides a yaw channel control method for improving the sideslip angle inhibition capability of a BTT control aircraft, which comprises the following steps:
firstly, a sensitive element processing unit measures the attitude angular velocity and overload of a missile, and a strapdown inertial navigation resolving unit calculates dynamic pressure and Mach number and sends the dynamic pressure and the Mach number to a yaw channel control loop;
step two, obtaining a pseudo sideslip angle through a sideslip angle reconstruction function in yaw overload;
step three, calculating a corresponding rudder instruction according to the attitude angular velocity, the pseudo sideslip angle and a control structure given in the figure;
and step four, sending a rudder instruction to the steering engine to drive the missile rudder surface to deflect, and realizing the inhibition of the sideslip angle.
Further, in the second step, the input variables of the sideslip angle reconstruction function are yaw overload, dynamic pressure and Mach number.
Further, step three middle rudder instruction DzThe calculating method of (2): dz＝Kωy×ωy+KbetaX beta. In the formula is omegayThe attitude angular velocity and beta are reconstructed pseudo sideslip angle and KwyAnd KbetaTo control system parameters.
And further driving the control surface of the aircraft to deflect by the calculated rudder instruction Dz to realize the suppression of sideslip angle.
The advantages of the invention include: the yaw channel control instruction is calculated through the sideslip angle reconstruction function and the yaw channel control structure, and the problem that the sideslip angle is increased due to the fact that an aircraft adopting the air inlet type engine is coupled when the aircraft is subjected to large overload maneuver and fast rolling maneuver is solved.
Drawings
FIG. 1 is a block diagram of a lateral passage control for controlling aircraft sideslip angle suppression by BTT according to an embodiment of the present invention.
Detailed Description
The invention is further illustrated below with reference to the figures and examples.
With reference to fig. 1, the sensing element processing unit measures the attitude angular velocity and overload of the missile, the strapdown inertial navigation resolving unit calculates dynamic pressure and mach number and sends the dynamic pressure and mach number to the yaw channel control loop, yaw overload obtains a pseudo sideslip angle through a sideslip angle reconstruction function, and a corresponding rudder instruction is calculated according to the attitude angular velocity, the pseudo sideslip angle and corresponding control parameters; and a rudder instruction is sent to a steering engine to drive the missile rudder surface to deflect, so that the suppression of the sideslip angle is realized.
In one embodiment of the invention, the control parameter K is determined beforehand as a function of the flight statewy、Kbeta。
In this embodiment, the specific workflow is described as follows:
1. the sensitive element processing unit measures the overload of the missile, the strapdown inertial navigation resolving unit calculates dynamic pressure and Mach number, the pseudo sideslip angle beta is reconstructed through the following functions, and the reconstruction function is taken as follows:
beta＝(a1+b1×Ma)×Nz/Q
in the above formula, Ma represents Mach number, Q represents dynamic pressure, and NzIndicates an overload, a1、b1As a coefficient, may take a1＝377682，b1＝85600。
2. Measuring the angular velocity omega of the missile according to the processing unit of the sensitive elementyThe reconstructed pseudo sideslip angle beta and the calculated control parameter calculate a rudder instruction DzThe calculation method comprises the following steps:
Dz＝Kωy×ωy+Kbeta×beta
3. and sending the calculated rudder instruction Dz to a steering engine to control the deflection of the control surface.
According to the invention, the yaw channel control method based on the reconstructed sideslip angle effectively improves the inhibition capability of the sideslip angle, so that the flight control quality of the BTT control aircraft is improved.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (1)
1. A yaw channel control method for improving the sideslip angle suppression capability of a BTT control aircraft is characterized by comprising the following steps of:
firstly, a sensitive element processing unit measures the attitude angular velocity and overload of a missile, and a strapdown inertial navigation resolving unit calculates dynamic pressure and Mach number and sends the dynamic pressure and the Mach number to a yaw channel control loop;
step two, obtaining a pseudo sideslip angle through a sideslip angle reconstruction function in yaw overload;
step three, calculating a corresponding rudder instruction according to the attitude angular velocity and the pseudo sideslip angle;
step four, a rudder instruction is sent to a steering engine to drive the missile rudder surface to deflect, and the suppression of sideslip angle is realized, wherein in the step two, the input variable of the sideslip angle reconstruction function is yaw overloadN zDynamic pressure Q, mach number Ma, i.e. pseudo slip angle beta = fun: (N zQ, Ma) the rudder instruction D in the third stepzThe calculating method of (2):
(ii) a In the formulaω y Is the attitude angular velocity, beta is the reconstructed pseudo sideslip angle,K wyAndK betato control system parameters.
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| 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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| CN112433532B (en) * | 2019-08-26 | 2022-06-21 | 北京理工大学 | Decoupling self-driving instrument considering second-order steering engine dynamics and decoupling control method thereof |
| CN111578793B (en) * | 2020-05-07 | 2022-08-23 | 北京星途探索科技有限公司 | Sideslip angle control method for rocket fairing separation in windy condition |
| CN111949043B (en) * | 2020-08-07 | 2024-02-23 | 上海航天控制技术研究所 | On-line extraction method for start control time based on attitude angular speed discrimination |
| 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 |
| 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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| CN103558857A (en) * | 2013-11-14 | 2014-02-05 | 东南大学 | Distributed composite anti-interference attitude control method of BTT flying machine |
| CN103587680A (en) * | 2013-10-16 | 2014-02-19 | 中国运载火箭技术研究院 | Sideslip turning control method for aircraft |
| CN103587681A (en) * | 2013-10-16 | 2014-02-19 | 中国运载火箭技术研究院 | Hypersonic speed aircraft control method capable of suppressing constant deviation influence of sideslip angle signal |
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Patent Citations (4)
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| WO2010119442A1 (en) * | 2009-04-16 | 2010-10-21 | Israel Aerospace Industries Ltd. | Air vehicle and method for operating an air vehicle |
| CN103587680A (en) * | 2013-10-16 | 2014-02-19 | 中国运载火箭技术研究院 | Sideslip turning control method for aircraft |
| CN103587681A (en) * | 2013-10-16 | 2014-02-19 | 中国运载火箭技术研究院 | Hypersonic speed aircraft control method capable of suppressing constant deviation influence of sideslip angle signal |
| CN103558857A (en) * | 2013-11-14 | 2014-02-05 | 东南大学 | Distributed composite anti-interference attitude control method of BTT flying machine |
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