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Магнитогидродинамические эффекты в задачах ориентации вращающихся космических аппаратов - PowerPoint PPT Presentation


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Магнитогидродинамические эффекты в задачах ориентации вращающихся космических аппаратов. Борис Рабинович Институт Космических Исследований РАН Январь 2003. Аннотация.

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slide1

Магнитогидродинамическиеэффектыв задачах ориентации вращающихся космических аппаратов

Борис Рабинович

Институт Космических Исследований РАН

Январь 2003

slide2
Аннотация
  • Излагаются основные результаты теоретических и экспериментальных исследований, связанных с использованием магнитогидродинамических (МГД) эффектов в задачах стабилизациии ориентации вращающихся КА с деформируемыми элементами .
  • Рассматривается новый принцип использования этих эффектов, основанный на идее «жидкого гироскопа» (вращающаяся тороидальная полость, частично заполненная электропроводной замагниченной жидкостью).
slide3
Предлагается использовать такого рода МГД-элементы для создания не требующих затрат рабочего тела, бесшарнирных систем ориентации и стабилизации вращающихся КА.
  • МГД элементы новой конфигурации позволяют, в отличие отих первоначальной версии, реализовать постоянные и медленно меняющиеся управляющие моменты.
  • При этом открываются широкие возможности включения в состав измерений не только интегрирующих акселерометров, но и солнечных датчиков
slide4
Автор благодарен ктн Алексею Гришину за большую работу по математическому моделированию и построению корневых годографов и кф-мн Виктории Прохоренко за подготовку электронной версии этого доклада
slide9


Stability and instability domains for the rotating SC of the AP type:- - stability; + - instability (one unstable root); + + instability (two unstable roots)

I

slide11

s

Mathematical simulation of the nutation of the gyro-stable AP- type SC (0 = const = 0.0523 s-1 and c = 0.06 s-1): (a) s is a vector locus corresponding to the mass m displacement by the strains of the flexible element; (b)  is a vector locus corresponding to the angular components of the SC

slide12

s

Mathematical simulation of the nuta tion of the gyro-unstable SC of the AP type (0 = const = 0.0523 s-1 and c = 0.03 s-1): (a) s is a vector locus corresponding to the mass m displacement by the strains of the flexible element; (b)  is a vector locus corresponding to the angular components of the SC

the mhd element of the torus shape completely filled with an electroconductive magnetized liquid
The MHD-element of the torus shape completely filled with an electroconductive magnetized liquid
mathematical model of a rotating sc with mhd control
Mathematical model of a rotating SC with MHD control

The root of the characteristic equations responsible for the stability

slide17

s

Stabilization of the gyro-stable SC of the AP- type with MHD elements and accelerometers. The mathematical simulation for 0 = const = 0.0523 s-1, c = 0.06 s-1 (a0 = 2, a1 = 3): (a) s is a vector locus corresponding to the mass m displacement by the strains of the flexible element; (b)  is a vector locus corresponding to the angular components of the SC

slide18

s

Stabilization of the gyro-unstable SC of the AP- type with MHD elements and accelerometers. The mathematical simulation for 0 = const = 0.0523 s-1, c = 0.03 s-1 (a0 = 2, a1 = 3): (a) s is a vector locus corresponding to the mass m displacement by the strains of the flexible element; (b)  is a vector locus corresponding to the angular components of the SC

experimental results
Experimental results

Amplitude and phase responses of I/V control loop

  • Theory
  • Experiment, A(f)
  • Experiment, (f)

, 

The hydrodynamical moment acting on the torus during the slow braking of its rotation

  • Theory
  • Experiment without magnetic field
  • Experiment with magnetic field
slide21
MHD-element for the attitude control and stabilization of a rotating spacecraftSome new ideas [7, 8, 9, 10]
reminiscences concerning some problems of rocket carriers dynamics and stability
Reminiscences concerning some problems of Rocket Carriers dynamics and stability

The launches of N-1 heavy Rocket Carrier (RC) in the years 1969 – 1972 discovered the disturbing moment in the roll plane, caused by the twist of the Liquid Propellant Engines (LPE) jets combination around the longitudinal axis of the RC.

the heavy rc n 1
The heavy RC N-1

The view from the tail on the 30 LPE of the N-1 RC

the equilibrium forms of 8 interacting lpe jets
The equilibrium forms of 8 interacting LPE jets
  • a – The form with the regular symmetry
  • b – The form with two planes of symmetry
  • c - The form with screw symmetry
mechanical models of the lpe jets forms presented in the previous slide
Mechanical models of the LPE jets forms presented in the previous slide
  • a – The form with the regular symmetry
  • b – The form with two planes of symmetry
  • c - The form with the screw symmetry
general comment to the slide 22
General comment to the slide 22
  • Analyzing the situation described above we see the arising in particular cases of the roll moment caused by a gas dynamical eccentricity of LPE jets. The moment is acting on a non rotating object (RC).
  • We are looking forward to use the analogous phenomena for generating the pitch and yaw moments for the attitude control of the rotating SC. These moments must be in the contrary to the previous case under strict control. The point is that we can use for this purpose a hydro dynamical eccentricity with MHD control.

Let us consider this problem more closely.

mhd effects in the nature
MHD effects in the Nature

Force lines of the Jovian magnetic field in the vicinity of the Io orbit

The forces acting on the elements of a rotating plasma torus

Eccentric Jovian plasma torus including the Io moon’s orbit

table 1 parameters of jupiter
1

Radius R0 [km]

71 950

2

Period of self rotation T [hr]

9. 9

3

Gravitational acceleration on the planets equator g0 [g]

2. 64

4

Strength of magnetic field on the planets equator μ0H0 [Gauss]

4. 28

5

Eccentricity of dipole ε0 [R0]

0. 14

6

Inclination of dipole to the planets

axis γ [deg]

9. 6

Table 1. Parameters of Jupiter
table 2 parameters of jovian torus
1

Radius r [R0]

Mean

Min

Max

6.19

5.64

6.73

2

Mean eccentricity ε [r]

0. 223

3

Thickness h [r]

Mean

Min

Max

0.176

0.167

0. 191

4

Mean strength of magnetic field μ0H [Gauss]

0. 00242

5

Strength of magnetic field [μ0H]

Mean

Min

Max

1

0.385

1.72

Table 2. Parameters of Jovian torus
new mhd element realizing the attitude control of a spinning sc
New MHD-element realizing the attitude control of a spinning SC

Ferromagnetic magnet guide

Electro conductive liquid

Winding

rotating sc with a new mhd element
Rotating SC with a new MHD-element

Mathematical model

Steady-state regime

slide34
Summary
  • The fact of vital importance is that the system being under consideration has no hinges and does not need any special fuel expenses
  • To confirm the new conception and to make the next step for its practical application we must fulfill a good deal of theoretical and experimental investigation.
references
References
  • Dokuchaev, L.V., Rabinovich, B.I. Analisis of Perturbed Motion near the Stability Boundary of a Rotating Spacecraft of the INTERBALL Auroral Probe Type, Cosmic Research, Vol. 37. No. 6, 1999, pp. 554 – 562.
  • Dokuchaev, L.V, Nazirov, R.R., Rabinovich, B.I., Ulyashin, A.I., On the Concordance of the Mathematical Model of Nutation of the Interball-2 Sattelite with a Flight Experiment. Cosmic Research, Vol. 38, No 5, 2000, pp. 454 – 462.
  • Rabinovich, B.I., Lebedev, V.G., Mytarev, A.I. Vortex Processes and Solid Body Dynamics. The Dynamic Problems of Spacecraft and Magnetic Levitation Systems. Kluwer Academic Publishers, Dordrecht, 1994, 296 p.
  • Churilov, G.A., Klishev, O.P., Mytarev, A.I., Rabinovich, B.I. Experimental Research of Toroidal Magnetohydrodynamic Element. Physical and Mathematical Models of Slow Breking Process, Scientific and technical journal «Polyot» («Flight»), No 9, 2001, pp. 21 – 27 (In Russian).
  • Dokuchaev, L.V., Rabinovich, B.I., Grishin, A.V. About the Stabilization of the Spacecraft with Deformable Elements Using the Magnetohydrodynamic Effects, Scientific and technical Journal «Polyot» («Flight»), No 7, 2000, pp. 21 – 27 (In Russian).
slide36
6. B.I. Rabinovich. Structural Control of a Rotating Spacecraft with Elastic Spike Antennas Using the Magnetohydrodynamic Control System. 3rd International Workshop on Structural Control. Paris July 2000, pp. 453-461.
  • Rabinovich, B.I., Prokhorenko., V.I. Concerning the rolling disturbance caused by the joint work of a Rocket Carriers LPR Engines, PreprintSpace Research Institute Russian Academy of Sciences, Пр.-2023, 2000, 18.

8. Rabinovich, B.I. A Plasma Ring Rotating in a Gravitational.– Magnetic Field: The Stability Problem, Doklady Physics, Vol 44, No 7, 1999, pp. 482 – 485.

9. Rabinovich, B.I., Prokhorenko, V.I. A Spacecraft with a Liquid Stabilized by Rotation, Plasma Torus and Alfven`s Problem, Scientific and technical journal «Polyot» («Flight»), No 5, 1999, pp. 9 – 16 (In Russian).

10. B.I. Rabinovich. Some New Ideas of the Attitude Control Based on the Magnetohydrodynamic Phenomena. The Application to the Rotating Spacecraft. Astro2000, 11 CASI Conference on Astronautics, Ottawa, Canada, November 2000, p. 240a.

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