Short rendezvous missions for advanced Russian human spacecraft

Murtazin, Rafail; Budylov, Sergey G.

doi:10.1016/j.actaastro.2010.05.012

Cited by 17 publications

(6 citation statements)

References 2 publications

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“…Interestingly, they observed particle acceleration over the axis of the load coil of 300-1000 ms -2 . Murzatin et al 116 have also used microdroplets and NPs as probes for the investigation of spatial effects in the ICP by studying the atomisation process end-on and side-on. They observed significant spatial shifts in the position of atomisation, depending on operating conditions, particle size and the presence of concomitant elements, which have consequences for, e.g.…”

Section: Fundamentalsmentioning

confidence: 99%

Atomic spectrometry update: review of advances in atomic spectrometry and related techniques

Evans

Pisonero

Smith

et al. 2018

J. Anal. At. Spectrom.

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SUMMARY OF CONTENTS This review covers developments in 'Atomic Spectrometry'. It covers atomic emission, absorption, fluorescence and mass spectrometry, but excludes material on speciation and coupled techniques which is included in a separate review. It should be read in conjunctionwith the other related reviews in the series. [1][2][3][4][5][6] Sample introductionThis section covers developments in sample introduction for all instrumental methods. LiquidsLiquid sample introduction relates to methods wherein the sample is introduced into the instrument in the form of a liquid, such as through nebulization or into a thermal vaporizer; whereas in vapour generation the sample is initially in the form of a liquid but is converted to a vapour prior to introduction into the instrument. Sample pre-treatment.A general review of on-line preconcentration for ICP-MS has been published by Das et al. 7 , covering solid phase methods and including 63 references. Several reviews of sample pretreatment methods used for atomic spectrometry are worth noting because they focus on specific areas: Kocurova et al. 8and Jain and Verma 9 have reviewed advances in DLLME (53 references) and SDME (407 references) respectively; Zhao et al. the same authors studied the stability of the labelled complexes at different pH and temperature, and when subject to separation using LC. They reported a significant decrease in stability when LC separation was used, and some degradation at 37 °C compared to 2 °C.Li et al. An immunoassay-linked method using gold nano-particles has been developed by Jarujamrus et al. 33 . In this approach the monoclonal antibody-chloramphenicol was attached to a solid support. Antigen-chloramphenicol was labelled with gold nano-particles (10 nm) at pH 9.5, attached to a bovine serum albumin protein and mixed with unlabelled antigenchloramphenicol, which was then added to the antibody-chloramphenicol. for U and Th respectively in water samples.

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Section: Fundamentalsmentioning

confidence: 99%

Atomic spectrometry update: review of advances in atomic spectrometry and related techniques

Evans

Pisonero

Smith

et al. 2018

J. Anal. At. Spectrom.

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show abstract

“…For a high-thrust AS, such as the "Soyuz", the long range guidance is performed as an orbit transfer at an aim point with a near zero phase angle at a specified final time t f [8][9]12]. Currently, for twoday rendezvous missions [12], the first two burns at 3 th -4 th revolutions formed a phasing orbit that must be eliminated the phase displacement. The next two phasing burns are performed at 28 th -30 th revolutions with transfer to the aim point.…”

Section: High-thrust Rendezvous Missions For Space Stationsmentioning

confidence: 99%

“…The target objective of the phasing segment is to reduce the phase angle between an active spacecraft (AS) and a SS, based on a difference of their orbital periods. Such issues for high-thrust rendezvous missions was detailed studied [8][9][10][11][12]. In the case of continuous medium-or low-thrust spacecraft the phasing strategy is closely related with available thrust-to-weigth ratio.…”

Section: Introductionmentioning

confidence: 99%

Optimal Rendezvous Trajectories as a Function of Thrust-to-Weight Ratio

Ulybyshev

2010

AIAA/AAS Astrodynamics Specialist Conference

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An optimal rendezvous trajectory analysis of long-range guidance (or phasing and transfer to a target orbit) related with design of low-thrust propulsion system is considered. Typical rendezvous missions to low Earth orbit space stations for an active spacecraft with different thrust-to-weight ratios (or thrust acceleration) are studied. The method of pseudoimpulse sets is used for the computations. This approach combines large-scale linear programming algorithms with the well-known discretization of the trajectories on small segments and uses discrete pseudo-impulse sets which are considered independently for each segment. Such method is very suitable for spacecraft trajectory optimization with arbitrary thrust from high to low. Existence of low-thrust optimal solutions is briefly discussed. An analysis of thrust-to-weight ratio factor for phasing orbit is presented. As for the high thrust case, for low-thrust trajectories there also are optimal phase solutions, i.e. there is a range of initial phase angles for which required characteristic velocity is almost equal to optimal orbit transfer between initial and target orbit. Possible rendezvous trajectory types in a wide ranges of thrust acceleration values from high to low (including a continuous multirevolution burn) and phase angles are described. Nomenclature a, a = thrust acceleration vector and its magnitude A = matrix of inequality constraints A e = matrix of equality constraints e, e r , e n , e b = thrust direction unit vector and its components in local vertical/local horizontal coordinate system -radial, along-track, cross-track i = segment number j = pseudo-impulse number J = performance index k = quantity of pseudo-impulses at each segment m = number of boundary conditions n = quantity of segments q = weight coefficient vector ρ = vector of relative coordinates N R = specified number of revolutions for rendezvous mission P = boundary condition vector 2 r ω . = mean radius of circular reference orbit t = time Δt AN = relative time from ascending node V = vector of relative velocity T = orbit period X = vector of decision variables Δt i = duration of i-th segment ΔV i (j) = characteristic velocity of j-th pseudo-impulse at i-th segment ΔV x = characteristic velocity μ = gravitational parameter for the Earth ϑ = pitch angle , Fig. 4 ϕ = phase angle, Fig. 1 ψ = yaw angle, Fig. 4Ф, Ф ρρ , Ф ρV , Ф Vρ , Ф VV = transition matrix and its sub-matrices ω = mean angular velocity of orbit motion

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“…In the last century, the early space programs carried out by the United States and Russia have accumulated rich RPO technological experiences, hence, some famous projects have naturally become the main research objects of scholars. Fehse [1] presented the background information, related concepts, and control strategies of early RPO tasks, such as the Gemini [2], Apollo [3], and Space Shuttle of the US, as well as the Soyuz/Progress [4] of the former Soviet Union, or Russia. Goodman [5] surveyed the overall development and flight history of the Space Shuttle from 1983 to 2005 and gave a detailed introduction to the procedural limitations and technical challenges encountered in the early space shuttle RPO missions.…”

Section: Introductionmentioning

confidence: 99%

Convex Optimization for Rendezvous and Proximity Operation via Birkhoff Pseudospectral Method

Zhang

Zhao

Li³

et al. 2022

Aerospace

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Rapid and accurate rendezvous and proximity operations for spacecraft are crucial to the success of most space missions. In this paper, a sequential convex programming method, combined with the first-order and second-order Birkhoff pseudospectral methods, is proposed for the autonomous rendezvous and proximity operations of spacecraft. The original nonlinear and nonconvex close-range rendezvous problem with thrust constraints and no-fly zone constraints is converted into its convex version by using the sequential convexification techniques; then, the Birkhoff pseudospectral method is used to transcribe the dynamic constraints into a series of linear algebraic equality constraints, in other words, a convex second-order conic programming problem with a relatively small condition number. Thus, the resulting problem can be accurately and efficiently solved by a convex solver. The simulation results indicate that the proposed methods, especially the second-order Birkhoff pseudospectral method, have obvious advantages over other methods in computational efficiency and sensitivity.

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Short rendezvous missions for advanced Russian human spacecraft

Cited by 17 publications

References 2 publications

Atomic spectrometry update: review of advances in atomic spectrometry and related techniques

Atomic spectrometry update: review of advances in atomic spectrometry and related techniques

Optimal Rendezvous Trajectories as a Function of Thrust-to-Weight Ratio

Convex Optimization for Rendezvous and Proximity Operation via Birkhoff Pseudospectral Method

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