American Journal of Aerospace Engineering
Volume 2, Issue 5, October 2015, Pages: 36-42

Organization of Uniform Dispersal for Group of Small Satellites After Their Separation and Acceptable Spread at Stages of Their Further Approaches

Alexander Degtyarev, Irina Vorobiova, Anatoliy Sheptun

Yuzhnoye SDO, Dnepropetrovsk, Ukraine

Email address:

(I. Vorobiova)

To cite this article:

Alexander Degtyarev, Irina Vorobiova, Anatoliy Sheptun. Organization of Uniform Dispersal for Group of Small Satellites After Their Separation and Acceptable Spread at Stages of Their Further Approaches. American Journal of Aerospace Engineering. Vol. 2, No. 5, 2015, pp. 36-42. doi: 10.11648/j.ajae.20150205.11


Abstract: Mutual-relative motion of satellites constellation after their placing into initial orbit is characterized the satellites reiterated approaches to minimal distances. Determined separation conditions for each satellite pair in constellation, which realization leads to minimal satellites approaches. It was sustained, that distances between satellites can reach extreme minimal values due to minor angular deviations of orbit planes and always occurring flight altitudes long-period oscillations. Received analytical relations for estimation of angular deviations and distances between satellites orbit planes at the phases of periodical approaches. It was approved that in some vicinity of orbit numbers can occur following almost simultaneously: small differences of angular distances from the equator for any satellite pair in constellation; minimal angular deviations of satellites orbit planes (in general they have different precession after separation of different directions and with various velocities). Analytical relationships were numerically confirmed with using software for satellites movement prediction at the phases of their approaches to the minimum distances. The area of satellites separation parameters was built, with its implementation in a small vicinity of flight orbits the satellites approach to distances less than 100 m. The minimum distance in the specified area according to the single calculations is ~10 m.

Keywords: Group Launches, Minimal Distances, Satellites Spatial Separation, Angular Spatial Separation of Orbit Planes, Estimation of Maximal Satellites Approaches, Maximal Satellites Approaches


1. Introduction

1.1.Basic Assumptions

The tendency of reducing weights and dimension of near space satellites, considerable rocket capabilities and new technologies allow ensuring injection of fair quantities of satellites by one launch. Issues concerning organization of uniform dispersal for constellation of small satellites after their separation and acceptable spread at stages of their further approaches are topical in the rocket building industry. Physical movement foundations in the terrestrial gravitational field determine satellites periodical approaches. Such issues occur two times per orbit in case satellites separation along the normal to orbital velocity and more rarely (up to several thousands of orbits) in case separation along flight direction (fig. 1 shows satellites approaches during their autonomous flight with differences between their separation velocities 0.75 m/s).

In case of small number of satellites in constellation their separation velocities are differ from each other by 1-2 m/s. The mutual relative motion analysis of satellites constellation and their dispersal during first flight orbits after separation is sufficient. Such analysis method is acceptable for practice. However, relative separation velocities are reducing with growth the number of satellites in constellation (10-20 and more). As a result difficulties of ensuring organization of uniform dispersal for small satellites constellation occur during their first flight orbits after separation. The necessity of satellite approaches estimation during long time intervals occurs at the same time.

The conditions of uniform dispersal for satellite constellation (the number of objects is 12, fig. 2) during their first flight orbits were determined and analytical relations for analysis satellites approaches during long time intervals were preliminary obtained. They were presented in articles [2,5] and in the reports [3,4] at 64th (Beijing) and 65th (Toronto) International Astronautical Congresses. Numerical evaluations of satellites approaches for their single separation along the flight direction were also presented. There were noticed satellite approaches on the distances near 100 m. The results of such calculations forces to carrying out of more detailed researches about mentioned issues.

a)

b)

Fig. 1. The typical picture of changing of distances between satellites: а) separation along normal to orbital velocity vector b) separation along flight direction.

The conditions which correspond to satellites approaching on minimal distances for a long time intervals have not researched before.

1.2. Problem Statement

The research task is definition of conditions which implementation leads to reducing distances between satellites at the phases of their maximal approaches and obtaining data of numerical evaluation of these distances. Current researches continue ballistic analysis of mutual-related motion for satellites constellation (12 objects) after their separation from side surface of dispenser normal to longitudinal axis of launch vehicle (fig. 2), which was started in [2-5]. It was presumed that longitudinal axis of dispenser specified along radius-vector. It should be noted that dispencer longitudinal axis OX1 was set along nadir direction.

Fig. 2. The scheme of satellites location on dispenser's surface.

The conditions of satellites constellation separation after putting them into initial orbit which ensure uniform dispersal with step of ~2.6 km along orbit for each flight orbit (fig. 3, table 1) were determinedin [2].

Table 1. Directions and satellites separation velocities (m/s).

Stabilizationplanes Platformindex Satellites separation velocities
I II III IV
A V V V V
B 0.677·V 0.833·V 0.677·V 0.833·V
C 0.333·V 0.677·V 0.333·V 0.677·V

The estimation of satellite pairs approaching in constellation were carried out on the base of calculation results of satellites movement after their separation, in case of putting them into sun-synchronous orbits with altitude ~650 km and inclination 98° by one launch.

Fig. 3. Satellites separation scheme and their location in flight ()a) after separationb) by the end of first flight orbit.

Application Satellite Tool Kit was used for required calculations.

2. Analytical Relations

It is examined mutual-relative motion of small satellites constellation with equal ballistic coefficients after putting them into frequently used orbits with low aerodynamic drag (h>600 km) by one launch. General characteristic of each satellite flight orbit after separation is small differences of semi axis dimensions and inclination (in most cases to 1 km and 10-4 rad correspondently). As a result parameters of satellites orbit planes precession motion differ insignificantly. Satellites approaches on minimal distances during long time intervals are also possible.

Location of two of satellites orbits after their separation and at the expiration some number of flight orbits showed at fig. 4, 5.

The distances between satellites decrease and reach their minimal values in some vicinity of flight orbits  after reaching of the maximum distances between any pair (i, j) of satellites in constellation ( thousands of km, where ri,j– are orbital radiuses):

,

( – orbital periods of two (i, j) satellites,  – flight velocity at the initial orbit, – the difference of separation velocities projections of satellites pair along flight direction).

General number l of satellite pair combinations determines as  in case of number of flight objects equal to n=13 (constellation of 12 satellites and the dispenser).

The distances between satellites in constellation at phases of minimal distances in the vicinity of orbit number are determined by angular spacing of orbital planes ( – orbital plane rotation angle per one flight orbit), by changing of average altitudes owing to atmospheric resistance, flight altitudes periodic changes, etc.

Fig. 4. Location of two satellites orbits after their separation.

Fig. 5. Location of two satellites orbits at the expiration some number of flight orbits .

Relations for estimation of orbital planes angular spacing , linear shifts along lateral directionand changings of orbital average altitudes  for two of satellites in constellation in the vicinity of orbit number  are presented below:

(1)

(index «0» refers to initial orbit parameters)

Using expressions for , ,  from [1-5] and spherical geometry formulas the first relation in (1) was transformed into:

(2)

( – the difference of separation velocities projections of any satellites pair (i, j) in constellation along the normal to flight direction ;  –point on the orbit, which corresponds to angular distance from the equator at the moment of satellites constellation separation (fig. 4)).

First summand in (2) characterizes influence of different average flight altitudes of two satellites onto orbital precession parameters and as a result onto angular dispersal of orbital planes in the vicinity of flight orbit number . Second summand in (2) characterizes influence of different initial orbit inclinations after satellites separation. Also next statements follow from (2):

Angular dispersal of any satellite pair (i, j) in constellation are caused by the difference of separation velocities projections  in the vicinity of flight orbit number . Such dispersal are equal to each other and in accepted calculation conditions are:

9.5 ang. min

The usage of satellites separation angularly to initial orbit plane () leads to changing (increase or decrease) angular dispersal of two satellites orbits. Assimilation to zero the expression in brackets in (2) leads to satellites orbit planes correspondence accurate within  in cafe of realization next condition:

(3)

Relation obtained below follows from (3) for sun-synchronous orbits (i0= 98°) and satellites separation at the equator :

(4)

Relation (3) affects more onto increasing of two satellites (i, j) approach frequency to minimal distances in the vicinity of flight orbit number . In case of condition (3) fulfillment the angle between satellites orbit planes does not exceed of angular minutes splits in both directions during valuable orbits number related to 'approaching event' time. This implies that frequency of events of satellites approaching to minimal distances increases.

For example, for sun-synchronous orbits (i~ 98°) with 600-700 km altitude in case of condition (3) fulfillment the angular distance between satellites orbit planes does not exceed of 0.2 - 0.3 angular minutes during 200 flight orbits.

There were determined separation conditions (separation velocities and inclinations) for any satellite pair (i, j) in constellation, which realization leads to minimal satellites approaches. In particular it was approved that in some vicinity of orbit numbers can occur almost simultaneously following:

Small differences of angular distances from the Equator for any satellite pair (i, j) in constellation;

Minimal angular deviations of satellites orbit planes (in general they have different precession after separation of divers directions with various velocities).

Satellites approaches occur during further flight after their first approaching event. The number of such events  for each satellite pair determines as integer part of relation , where  – the number of flight orbits during active satellite exploitation time. This relation for accepted conditions of satellite separation approximately is of the form . The range of  value changing (during 5 year exploitation period, which corresponds to 27000 orbits) for every possible satellite pairs in constellation is from 1 to 19 approaching events. General approaches number for all 78 satellite pairs during mentioned time interval is 551.

Angular orbit planes dispersal of two (i, j) satellites at the moment their kij approach to minimal distances can be written as  besides condition of angular orbit dispersal minimization [3] will be constant.

It should be noted that orbit inclinations would not change with dispenser longitudinal axis angular placing normal to orbit plane and maintaining of conditions showed at fig. 2 and table 1. As a result conditions (3) for minimal angular deviation are not implemented in some vicinity of flight orbit . With increase of satellites approaching events number the expression of inaccuracy angular orbit planes dispersal , which can be represented as a linear subjection from number kij of approaching events, decreases. As a result the accuracy of formula (4) for kij of approaching event decreases.

3. Numerical Estimation of Minimal Distances

The calculations were carried out for sun-synchronous orbits with ~650 km altitude for constellation composed of 12 satellites2-5, which were uniform set on the circle of dispenser in points I, II, III, IV at tiers А, В, С. Satellites separation was accepted at the equator () normal to dispenser longitudinal axis (the angular orientation of it is presented at fig. 2). Velocities and separation directions implement satellite uniform dispersal during first flight orbits and their numerical values were accepted according to data from fig. 2.

The calculations of flight trajectory for approach evaluation of satellite pair (i, j) in constellation in some vicinity of number  were carried out considering change of initial movement conditions due to satellites separation from dispenser. The differences of relative separation velocities  and of inclinations  of satellite pair (i, j) in constellation, which were accepted for calculations according to initial data (table 1, V=1 m/s), are showed in table 2. Also there were showed data of full orbit numbers () to the moment of first satellite pair (i, j) approach and count ki,j of approach events.

Fig. 6. Distances between satellites at the moment of their first approach in some vicinity of orbit number  (nominal separation conditions).

The calculations for three values pericentre argument ω0=0°; 69°; 100° were carried out for pericentre argument initial value influence of initial orbit with excentricity equal е0=0.00115 (ω0=69° and е0=0.00115 with h0~650 km altitude satisfy stable near-Earth orbits, which parameters ω0 and е0 remain constant in ascending nodes for long time intervals).

The numbers of distances ρi,j between satellite pair (i, j) in some vicinity of number  on the assumption of nominal separation conditions are showed at fig. 6.

Next conclusion can be drawn from fig. 6, that low border of minimal distance between satellites with nominal separation conditions is at 0,5 km level in difference range of relative separation velocities 0,15-1,35 m/s. Nominal values of satellites minimal distances increase with time.

Table 2.Combination of satellite pair (i, j) separation parameters differences.

 (m/s) 0.15 0.3 0.45 0.6 0.75 0.9 1.05 1.2 1.35 1.5 1.65 1.8

 (rad)

10-5 4∙10-5 1.6∙10-5 2∙10-5 8∙10-5 1.2∙10-4 1.7∙10-4 8∙10-5 1.2∙10-4 1.8∙10-4 4∙10-5 9∙10-5 1.4∙10-4 1.6∙10-4 0 5∙10-5 10-4 2∙10-4 10-5 4∙10-5 6∙10-5 2.4∙10-4 2∙10-5 3∙10-5 8∙10-5 2∙10-5 7∙10-5 8∙10-5 6∙10-5 9∙10-5 10-4 1.1∙10-4 1.2∙10-4

~16500 ~8250 ~5500 ~4100 ~3300 ~2750 ~2350 ~2050 ~1820 ~1650 ~1500 ~1380
kij 1 3 4 6 8 9 11 13 14 16 18 19

Relation (3) equal "1" (minor difference from condition (4)) for two satellite pair А2-С3 and А1-С4 (fig. 7) among 78 satellite pair combinations, which were created after satellites separation from dispenser.

Orbit planes of satellite А23, А14 in some vicinity of orbit number  have minor angular separation (to 20-30 ang. sec). The values of differences of relative separation velocities projections along flight direction  and along the normal to ОХ1 axis of dispenser  for these satellite pairs are  0.75 m/s. Distance between mentioned satellites pairs is about ~0.5 km by the moment of their maximal approach in some vicinity of orbit number  (fig. 6).

Fig. 7. Conditions of satellite pairs separation ()а) pairА2-С3.b) pairА1-С4.

Values of inaccuracies for satellite separation parameters  and  were determined due to carried out calculation results. These inaccuracies correspond to maximal satellites approaches to distances 9 and 12 m (fig. 8 points ""). Thus 1/3 of objects from all satellite number in constellation (fig. 2, 7) can approach to distances about ~10 m.

Area D() of inaccuracies is also showed at fig. 8. Its bounds correspond to satellites approach to 100 m (it was conditionally accepted that distance 100 m between satellites is acceptable boundary point of their autonomous flight including existing separation inaccuracies, physical nature of movement, calculation model imperfective and other factors).

Behavior of altitude inclinations , geodetic latitudes  and longitudes  at the phase of satellite approach to minimal distances are showed at fig. 9 a-c (the moment of satellite pair maximal approach is marked with «»)

Fig. 8. Area of satellite approach critical values.

* Origin of coordinates corresponds to calculating parameters of satellite separation  = 0,75 m/s and  = 10-4 rad.

a)

b)

c)

Fig. 9. Range of orbital parameters change of satellites pair А23a) by altitude b) by latitude c) by longitude .

4. The Alternative Separation Scheme for Big Constellation of Satellites

The implementation of satellites separation scheme by fig. 2 is based on the usage of mechanical, electrical, pneumatic and other separation appliances. It is obvious, that such appliances have significant scattering of satellites separation operation (about 10% from nominal) because of absence of power adjusting hardware. As a result there will be marked change of satellites separation conditions and deviation of further distances between them at the beginning of their autonomous flight and in further. In this case providing of satellites non-closing in constellation (or part of them) above mentioned bound of minimal distances between satellites in some vicinity of number  sometimes can lead some difficulties.

Scheme at fig. 10 can be used as alternative one (satellites are separated serially normal to dispenser longitudinal axis in case of rocket moving with minor longitudinal acceleration along flight direction ).

The advantage of this scheme is possibility of every further satellite separation by the control system instructions after achieving determined increase of flight velocity. Required characteristics of satellites constellation mutual-relative motion at the first phase after separation (including realization of tracing their flight trajectories on the safety distance () from gas flows, which are formed by racing of thruster) and at further phases of their approaches are provided by following:

Longitudinal rocket acceleration;

Durations of satellites separation time intervals;

Satellites separation velocities normal to longitudinal rocket axis .

Imposition of velocity increment  restriction for two (i, j) satellites, which are separated serially, provides their non-closing in some vicinity of orbit number  to distances that are lower than determined distance bounds. For satellites safety flight in the gas flows zone this restriction can be determined by relation (5) (fig. 10):

(5)

Fig. 10. Alternative separation scheme for big constellation of satellites.


References

  1. Эльясберг, П. Е. Введение в теорию полетаискусственныхспутников Земли // Павел Ефимович Эльясберг // – М.: Наука, 1965. – 540с.
  2. Degtyarev A. Research of trajectories of spacecraft cluster injection into different orbits in one «Cyclone-4» vehicle launch//Degtyarev A., Degtyarenko P., Sirenko V., Sheptun A.//Space research in Ukraine 2010-2012.–Kyiv.
  3. Degtyarev A. Feasibility study of spacecraft cluster lunches with lunch vehicle into various basic orbits // Degtyarev A., Sheptun A., Mashtak I. // IAC-13-D2.P.16, 64th International Astronautical Congress, China, 2013.
  4. Vorobiova I. Launch vehicle energy performance during single injection of the satellites into individual orbits // Vorobiova I., Sheptun A. // IAC-14-D2.2.9, 65th International Astronautical Congress, Canada, 2014.
  5. ВоробьеваИ.А. Проектно-баллистические исследования по групповым запускам спутников в одном пуске ракеты носителя на разнесенные базовые // Воробьева И. А., Шептун А.Д. // Научный журнал ХУПС, № 3, 2014.

Article Tools
  Abstract
  PDF(2748K)
Follow on us
ADDRESS
Science Publishing Group
548 FASHION AVENUE
NEW YORK, NY 10018
U.S.A.
Tel: (001)347-688-8931