Chapter 3 General Performance Capabilities Table of Contents List of Figures

Home , Azimuth, Orbital inclination, Orbit insertion, Synchronous orbit, Transfer orbit

Chapter 3 General Performance Capabilities

Table of Contents

3 General Performance Capabilities...... 3-1 3.1 Introduction...... 3-1 3.2 Launch Azimuths and Orbit Inclinations from Plesetsk ...... 3-1 3.3 Low Earth Orbits...... 3-2 3.3.1 Payload Performance for Circular Orbits ...... 3-2 3.3.2 Performance for Elliptical Orbits ...... 3-3 3.3.3 Sun-Synchronous Orbits...... 3-3 3.4 Mission Profile Description ...... 3-8 3.5 Baikonur Performance...... 3-13 3.6 Spacecraft Injection and Separation ...... 3-14 3.6.1 Injection Accuracy...... 3-14 3.6.2 Spacecraft Separation ...... 3-14 3.6.2.1 Spin Stabilised Separation...... 3-14 3.6.2.2 Three-Axis Stabilised Separation...... 3-15 3.6.2.3 Typical Multiple Satellite Deployment Scenarios ...... 3-16

List of Figures

Figure 3-1 Rockot/Breeze-KM payload performance for circular orbits...... 3-4 Figure 3-2 Rockot/Breeze-KM payload performance for elliptical orbits at 63.2° inclination...... 3-5 Figure 3-3 Rockot/Breeze-KM payload performance for elliptical orbits at 72.0° inclination...... 3-6 Figure 3-4 Rockot/Breeze-KM payload performance for elliptical orbits at 82.5° inclination...... 3-7 Figure 3-5 Cycling orientation of Breeze-KM relative to the sun during coast flight maintained for one hour (a), and for half an hour (b)...... 3-9 Figure 3-6 Typical Rockot/Breeze-KM ascent (650 km circular, 86.583° inclination). (a) Trajectory. (b) Acceleration timeline...... 3-10 Figure 3-7 Typical Rockot/Breeze-KM ascent (1000 km circular, 99.52° inclination). (a) Trajectory. (b) Acceleration timeline...... 3-11 Figure 3-8 Typical Rockot/Breeze-KM ascent (320 km perigee, 820 km apogee at 96.8° inclination and SSO 820 km, at 98.7° inclination). (a) Trajectory. (b) Acceleration timeline...... 3-12 Figure 3-9 Sun-synchronous orbit injection scheme...... 3-13 Figure 3-10 Example of sequential deployment of three spacecraft...... 3-16 Figure 3-11 Example of simultaneous deployment of six spacecraft...... 3-17

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List of Tables

Table 3-1 Allowable launch azimuths that can be served from Plesetsk...... 3-1 Table 3-2 Orbital injection accuracy...... 3-15

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3 General 3.2 Launch Azimuths and Orbit Inclinations from Plesetsk Performance The Plesetsk Cosmodrome is located Capabilities about 200 km south of the port city of Archangel in Northern Russia at geo- This chapter describes the performance of graphical coordinates 62.8°N and 40.3°E. the Rockot/Breeze-KM launch vehicle into The location of populated areas drives the circular and elliptical low earth orbits from allowable launch azimuths and drop zones its launch site in the Plesetsk Cos- available from this launch site. Launch modrome, Northern Russia, as well as its azimuths and resulting orbital inclinations potential launch base in Baikonur. Back- achievable from Plesetsk are listed in ground information and the assumptions Table 3-1. made for the performance curves are pre- Launch Azimuth Corresponding Orbital Inclination sented. 76.2° 63.2° 41.6° 72.0° 3.1 Introduction 13.7° 82.5° The launch vehicle payload performance 15.2° to 4.8° 82.0° to 86.4° is driven by many variables and includes 4.8° 86.4° amongst others the specific launch vehicle 341.5° SSO and other retrograde orbits characteristics, launch pad location, al- Table 3-1 Allowable launch azimuths that lowable launch azimuths, drop zones, and can be served from Plesetsk. the availability of ground measuring stations for telemetry information reception. Rockot/Breeze-KM, equipped with its The Rockot launch site in the Cos- modern inertial based control system is modrome Plesetsk, historically the most able to perform dog-leg manoeuvres dur- active launch site in the world with over ing the second stage operation so that 1700 launches, is well situated for polar inclinations beyond these allowable and high inclination launches due to its launch azimuths can be reached. The northerly latitude. Rockot/Breeze-KM dog-leg manoeuvres may result in a de- launched from Plesetsk Cosmodrome and crease of payload mass. equipped with its modern restartable upper stage Breeze-KM can serve a wide In coordination with the Customer and range of both circular and elliptical orbits their demands the Breeze-KM upper stage in the range from 200 km up to over 2000 enables high flexibility in the selection of km and a range of inclinations from 50° to the ascent profile provided by its attitude- SSO by direct injection or via orbital plane and orbit correction system, precise change. guidance, navigation and control electron- ics including a three-axis gyro system and long life batteries. This enables a Cus- tomer adapted ascent profile and payload

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deployment scheme under consideration parking orbit with the first burn of the of radiovisibility by Russian ground track- main engine and one or several ad- ing stations, earth shadow phases, sepa- justment burns to form the target orbit. ration time and other constraints. Note: If the required altitude of the orbit To achieve inclinations other than those does not exceed 400 km, both injection indicated in Table 3-1, Breeze-KM also schemes can be used, and if the orbit alti- provides the possibility to change inclina- tude is higher than 400 km, the second tion up to ±17° by a main engine ignition injection scheme is generally used. in the vicinity of the equatorial node of the All payload performances are calculated transfer orbit. In such cases the possible for the standard Rockot/Breeze-KM decrease of the payload mass has to be configuration including the payload fairing determined for each specific mission pro- as described in chapter 2. The requisite file. The minimum possible orbital inclina- payload adapter fitting/ dispenser masses tion for the launches from Plesetsk cos- plus the separation system must be sub- modrome without dog-leg manoeuvres tracted from these figures. and/or main engine ignition in the vicinity of the nodes is 62.8°. Usually, the payload fairing is not jettisoned until the free molecular heat-flow The propellant consumed by Breeze-KM has dropped below 1135 W/m2. during possible payload collision and con- tamination avoidance manoeuvres is mi- The performance values are confirmed by nor and will not affect the payload per- the data of former Rockot/Breeze-KM formance. On the other hand, fuel con- commercial launches as well as the over sumption for possible Breeze-KM deorbi- 150 SS-19 missile flights. tation must be subtracted from the performance capacity. It should be noted that the performances given in this user guide are generally 3.3 Low Earth Orbits based on conservative assumptions. Fur- thermore, due to mass saving measures The payload performance of the such as incremental improvements to the Rockot/Breeze-KM vehicle has been cal- upper stage, an increase in payload per- culated for both circular and elliptical or- formance can be expected. In specific bits from the Plesetsk launch site. To at- cases, where such additional performance tain the maximum payload capacity for a is necessary, the Customer is invited to dedicated mission, two injection schemes contact EUROCKOT directly for a dedi- are generally used: cated mission analysis.

• The target orbit is achieved via a sin- 3.3.1 Payload Performance for Circular gle burn of the Breeze-KM upper Orbits stage main engine. Figure 3-1 illustrates the performance ca- • The Breeze-KM upper stage with a pabilities associated with the correspond- payload is injected into an elliptic ing circular orbits that can be served from

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the launch site in Plesetsk using the al- 3.3.3 Sun-Synchronous Orbits lowable launch azimuths indicated in sec- Sun-synchronous orbits (SSO) can be tion 3.2. It should be noted that direct in- served from the Plesetsk launch site via jection into inclinations that lie between use of the 341.5° launch azimuth corridor. i = 82.0° and 86.4° are possible but Different ascent trajectory options are subject to a dedicated internal Russian available depending on the requirements approval process for the overflight permis- of the dedicated mission. sion. Inclinations not shown in the performance graphs can also be served by The launch vehicle is initially launched Rockot/Breeze-KM, but only via a dog-leg with an azimuth of 341.5° from Plesetsk. manoeuvre during the 2nd stage burn or a Yaw manoeuvres during the second stage plane change manoeuvre performed by burn allow the second stage drop zone to the upper stage. In these cases, perform- be precisely positioned outside of any for- ances should be calculated on a case by eign country's territorial waters. case basis by EUROCKOT, a linear inter- polation between the curves is not possi- The upper composite comprised of ble. Some loss of performance can be Breeze-KM and the payload is injected expected due to the necessity to perform into a 96.7° or 99.5° inclined parking orbit. dog-leg or plane change manoeuvres. Finally, the target orbit inclination is reached via a plane change manoeuvre 3.3.2 Performance for Elliptical Orbits carried out by a Breeze-KM main engine ignition near the equator crossing. The Rockot/Breeze-KM performance ca- The payload performance for SSO is de- pabilities for elliptical orbits with inclina- picted in Figure 3-1. It corresponds to the tions of 63.2°, 72.0° and 82.5° are pre- payload capacity into the required orbit sented in Figure 3-2 to Figure 3-4. Any with the SSO typical combination of target argument of perigee can be achieved ac- altitude and inclination. cording to the Customer's requirements.

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2200

2000

1800 i = 63.2° i = 72.0° i = 82.5° 1600 i = 86.4°

1400

1200 Payload mass, kg Payload mass, SSO Parking orbit i = 96.7° 1000 Parking orbit i = 99.5°

800

600

400 0 500 1000 1500 2000

Circular orbit altitude, km

Figure 3-1 Rockot/Breeze-KM payload performance for circular orbits.

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2000 Perigee altitude, km 200 500 700 1000 1500 1500 2000

1000 Payload mass, kg Payload mass,

500

0 100 1000 10000 100000

Apogee altitude, km

Figure 3-2 Rockot/Breeze-KM payload performance for elliptical orbits at 63.2° inclination.

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2000

Perigee altitude, km 200 500

1500 700 1000 1500 2000

1000 Payload mass, kg Payload mass,

500

0 100 1000 10000 100000

Apogee altitude, km

Figure 3-3 Rockot/Breeze-KM payload performance for elliptical orbits at 72.0° inclination.

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2000

Perigee altitude, km 200 500 700 1000 1500 1500 2000

1000 Payload mass, kg Payload mass,

500

0 100 1000 10000 100000

Apogee altitude, km

Figure 3-4 Rockot/Breeze-KM payload performance for elliptical orbits at 82.5° inclination.

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the Customer’s specific requirements be- 3.4 Mission Profile Description tween the main engine burns. For instance, This section describes typical circular low- for thermal sensitive payloads, a step-wise earth mission profiles and presents exam- rotation about any axis can be performed. ples of trajectories. In the absence of any specific requirements, Breeze-KM performs manoeuvres The selected flight trajectories take into to meet its own thermal requirements. For account the dedicated impact sites permit- 1 hour the +XUS axis is oriented towards ted for Rockot elements. the sun. If coasting continues for more than

one hour, the –XUS axis is oriented towards The launch sequence begins with Stage 1 the sun for the next half an hour. During ignition. The first stage propels the vehicle +XUS orientation, the angle between the to approximately 60 km height and impacts +XUS axis and the direction of sun light some 990 to 1100 km down range. The should be α ≤ 100°. During –XUS orienta- ignition of the Stage 2 vernier engines oc- tion, the angle between the –XUS axis and curs shortly before Stage 1 burn-out. the sun direction should be α ≤ 50° (Figure After shut down of stage 1 engine, stage 1 3-5). is separated using its solid retro rockets. For a chosen orientation, an accuracy of Once the free molecular heat-flow has 10° about each of the three axes of stabili- fallen below 1135 W/m2, usually, the pay- sation can be provided during the coast load fairing is jettisoned. phase. The second stage's propelled flight phase Typical trajectories for Rockot missions is completed by the successive shut down with different numbers of upper stage igni- of the main engine and vernier thrusters. tions are shown in Figure 3-6 to Figure 3-8. The following stage separation is assisted These figures show the main events of the by use of the second stage's retro rockets. mission: main engine burns and cut-offs, The Breeze-KM upper stage manoeuvres the Spacecraft separation and trajectory begin immediately after stage 2 separation characteristics, such as: and are performed by the upper stage • flight time t counted from launch, s main engine, which can be ignited several times, if required. An initial burn is per- • relative velocity v, m/s formed in the boost mode directly following stage 2 separation. Further ignitions of the • relative flight path angle θ, deg main engine are performed in accordance • dynamic pressure q, kg/m2 with the specific flight programme. • altitude h, km During the coast phase between the main engine burns Breeze-KM generally follows Figure 3-9 shows a typical injection a sun-oriented flight programme to meet scheme for sun-synchronous orbits.

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-50°≤α≤ -100 ≤ α ≤ 100 -X ++X XUS - XUS α ≤ 50° α ≤ 100° α α U Breeze-KM PayloadPayload B Directionction from from Directionction from from GCoG to Su ton sun GCoG to Sunto sun Upper Stage Breeze-KMBreeze-KM Centreter ofof Gravitygravity Payload Centrenter ofof Gravitygravity G) (CoG) OG) (CoG)

per StagBreeze-Ke M er Breeze-KStage M longitudinalgitudinal axi axiss longitudinalgitudinal axisaxis

(a) (b)

Figure 3-5 Cycling orientation of Breeze-KM relative to the sun during coast flight maintained for one hour (a), and for half an hour (b).

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Spacecraft End of deployment Breeze-KM t = 5861 s second burn Orbit parameters t = 4850 s h = 650.0 km v = 7622 m/s p ha = 650.0 km Stage 2 θ = 0.02° Fairing separation i = 86.583° separation, t = 173 s Final orbit Breeze-KM parameters q = 0 Pa first burn v = 3599 m/s hp = 499.2 km t = 305 s θ = 16° ha = 506.1 km v = 5634 m/s h = 125.6 km i = 88.999 θ = 7.3° h = 235.7 km Breeze-KM second burn Breeze-KM Stage 1 withdrawal separation t = 4360 s v = 7367 m/s t = 6915 s t = 122 s θ = -0.03° q = 586.44 Pa h = 665.6 km Orbit parameters v = 3163 m/s End of Breeze-KM hp = 140.7 km θ = 23.3° first burn ha = 660.8 km h = 68.3 km t = 882 s i = 86.582° v = 7832 m/s θ = -1.5° h = 250.7 km Maximum Transfer orbit dynamic pressure parameters

t = 50 s hp = 160 km q = 61.29 kPa ha = 635.3 km v = 567 m/s i = 86.577° Launch θ = 47.9° h = 10.7 km t = 0 s L = 1076 km L = 1391 km L = 3662 km

time

(a)

Stage 1 and 2 Operation Breeze Operation Transfer Orbit Stage 1 Stage 2 Separation Separation Breeze Spacecraft Breeze Fairing Deployment Venting/ Jettisoning Breeze Second Withdrawal Depressurisation First Burn Burn of Breeze Tank

Launch 0 122 173 305 882±43 4360 4399±3 5861 6915 t (s Retro Rocket Retro Rocket time, s of Stage 1 of Stage 2

(b)

Figure 3-6 Typical Rockot/Breeze-KM ascent (650 km circular, 86.583° inclination). (a) Trajectory. (b) Acceleration timeline.

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Spacecraft End of deployment Breeze-KM t = 5768 s second burn t = 4505 s Orbit parameters v = 7455 m/s hp = 1000.0 km θ = -0.006° ha = 1000.0 km i = 99.52° Final orbit parameters Breeze-KM withdrawal hp = 1001.1 km ha = 1009.5 km t = 6368 s Stage 2 i = 99.516 Fairing separation separation, Orbit parameters t = 164 s Breeze-KM hp = 776.5 km q = 0 Pa first burn ha = 1001.1 km v = 3480 m/s t = 305 s i = 99.594° θ = 18.2° v = 5543 m/s h = 119.9 km θ = 9.7° h = 257.2 km Breeze-KM second burn Stage 1 separation t = 4456 s v = 7226 m/s t = 122 s θ = 0.07° q = 479.55 Pa h = 1005.9 v = 3153 m/s End of Breeze-KM θ = 24.2° first burn h = 69.7 km t = 922 s v = 7984 m/s θ = -2.4° h = 291.3 km Transfer orbit Maximum parameters dynamic pressure h = 160 km t = 50 s p ha = 976.3 km q = 60.63 kPa i = 99.46° v = 566 m/s θ = 48.8° Launch h = 10.7 km t = 0 s L = 1082 km L = 1329 km L = 3857 km

time

(a)

Stage 1 and 2 Operation Breeze Operation Transfer Final Orbit Orbit Stage 1 Stage 2 Separation Separation Breeze Spacecraft Fairing Deployment Breeze Venting/ Jettisoning Breeze Second Depressurisation First Burn Burn Withdrawal of Breeze Tank

Launch 0 122 164 305 922±45 4456 4505±3 5768 6368 t ( Retro Rocket Retro Rocket time, s of Stage 1 of Stage 2

(b)

Figure 3-7 Typical Rockot/Breeze-KM ascent (1000 km circular, 99.52° inclination). (a) Trajectory. (b) Acceleration timeline.

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End of Breeze-KM third burn Spacecraft t = 5213 s deployment v = 7537 m/s θ = -0.006° t = 5481 s Final orbit Orbit parameters parameters hp = 820.0 km h = 820.0 km hp = 820.1 km a h = 828.9 km i = 98.7° Spacecraft a i = 98.696° deployment Fairing separation t = 2826 s Stage 2 t = 171 s separation, Breeze-KM Orbit q = 0 Pa Breeze-KM Breeze-KM second burn parameters v = 3638 m/s first burn third burn t = 2636 s hp = 320.0 km θ = 14.3° t = 5156 s t = 305 s v = 7785 m/s ha = 820.0 km h = 120.2 km v = 7393 m/s v = 5892 m/s θ = 1.41° i = 96.80° θ = 0.86° θ = -3.8° h = 326.9 km h = 200.4 km h = 820.9 km Stage 1 separation t = 122 s End of Breeze-KM Breeze-KM q = 653.12 Pa second burn withdrawal v = 3212 m/s End of Breeze-KM t = 2687 s t = 6061 s θ = 22.6° first burn v = 7917 m/s h = 67.7 km t = 800 s θ = -0.0004° Orbit parameters v = 7920 m/s h = 208.8 km hp = 673.7 km θ = -0.08° ha = 821.1 km h = 208.8 km Transfer orbit i = 98.703° parameters Maximum Transfer orbit hp = 320.6 km dynamic pressure parameters ha = 826.9 km t = 50 s hp = 160 km i = 96.80° q = 62.65 kPa ha = 470.0 km v = 574 m/s Launch i = 96.864° θ = 47.1° t = 0 s h = 10.7 km L = 1082 km L = 1325 km L = 3201 km

time

(a)

Stage 1 and 2 Operation Breeze Operation Transfer Final Orbit Final Orbit Orbit Stage 1 Stage 2 Separation Separation Breeze Spacecraft Breeze Spacecraft Fairing Deployment Third Deployment Breeze Venting / Jettisoning Breeze Second Depressurisation First Burn Burn Burn Withdrawal of Breeze Tank

Launch 0 122 171 305 799±36 2636 2688±32826 5156 5213±3 5481 6061 t (se Retro Rocket Retro Rocket of Stage 1 of Stage 2 time, s

(b)

Figure 3-8 Typical Rockot/Breeze-KM ascent (320 km perigee, 820 km apogee at 96.8° inclination and SSO 820 km, at 98.7° inclination). (a) Trajectory. (b) Acceleration timeline.

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Required orbit

Stage 2 separation End of ascent phase Fairing separation

Coast phase Stage 1 separation

Descending node. Breeze-KM engine ignition

Ascending node. Breeze-KMBREEZE engine ignition

Transfer orbit Equatorial plane

Figure 3-9 Sun-synchronous orbit injection scheme.

missions. Baikonur is particularly suited for 3.5 Baikonur Performance serving inclinations in the 50° range, which Although Rockot launches have occurred cannot be efficiently reached from Plesetsk in the past from Baikonur cosmodrome, it due to its northerly latitude. The achievable is currently no longer operational for mass performances from Baikonur for in- Rockot launches. An activation of the site clinations from about 50° to about 65° are for Rockot requires extensive upgrades subject to detailed analyses. However, and modifications to existing facilities. A they can be assumed to be slightly above decision for site activation will be made on the mass performance for launches from a case-by-case basis, should the need Plesetsk. For more detailed information arise. The information contained in this regarding Baikonur launch performance, section is for customers interested in the EUROCKOT should be contacted, directly. potential use of this launch site for their

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3.6 Spacecraft Injection and Spacecraft can either be spun-up along the Separation Breeze-KM longitudinal axis or released from the upper stage in a three-axis stabi- Rockot, equipped with the Breeze-KM up- lised mode. per stage allows a large variety of options with regard to spacecraft orbital injection 3.6.2.1 Spin Stabilised Separation and separation. The following sections provide information about the orbital injec- Spin stabilisation is performed around the tion conditions and the separation possibili- upper stage longitudinal axis with rates of ties for payloads. up to 10°/min. Higher spin rates may be considered upon Customer's request. 3.6.1 Injection Accuracy Spin parameters are to be agreed Table 3-2 provides 3-sigma orbital injection individually for each specific payload taking errors depending on the average altitude of into account: the target orbit ensured by accuracy prop- • Payload mass distribution (MoI), centre erties of the Rockot/Breeze-KM launch of mass (CoM) position and spacecraft vehicle control system. dynamic properties In particular cases the injection accuracies • Customer requirements for the spin given in Table 3-2 can be improved after regime such as: the specific trajectory analysis. − attitude orientation and its accuracy during upper stage spin manoeuvre 3.6.2 Spacecraft Separation − orientation accuracy of the payload af- The spacecraft separation from Breeze-KM ter its separation can take place in a number of different − other payload requirements for the ways and is driven primarily by the Breeze-KM upper stage • Necessity to continue flight control of • characteristics of the separation sys- the upper stage after payload separa- tem, e.g. stiffness of spring pushers, tion • type of release mechanism, Controlled deorbiting of the upper stage • the direction of the separation impulse after separation can be provided, if re- of the payload, quired. On the completion of the mission, Breeze-KM vents all its tanks to put the payload mass, moments of inertia, • stage in a safe mode. • the Breeze-KM burn-out mass

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Orbital parameters error type 3-Sigma error

Average orbital altitude ±1.5%

Inclination ±0.06° Eccentricity (for circular orbits) ≤0.0025

Right ascension of ascending node ±0.05° Argument of perigee (for elliptical orbits) depends on eccentricity

Table 3-2 Orbital injection accuracy.

3.6.2.2 Three-Axis Stabilised Separation The schemes are selected by EUROCKOT and agreed with the Customer. In general, any required payload attitude can be provided. Following orbit insertion, As a possible way to reduce potential dis- the Breeze-KM avionics subsystem can turbances acting on the spacecraft during execute a series of pre-programmed com- separation, the following measures shall be mands to provide the desired initial pay- applied: load attitude prior to its separation. • Selection of pusher with optimal char- This capability can also be used to reorient acteristics including their energy Breeze-KM for the deployment of multiple payloads with independent attitude re- • Adjustment of pusher position for com- quirements. pensation of lateral offset of the CoM

The 3-sigma attitude error about each Besides, electrical connectors can be se- spacecraft geometrical axis will not exceed lected taking into account their separation 1.5° - 3° depending on the spacecraft prop- forces characteristics. erties. Analysis shows that even for light space- The maximum angular velocities of the craft having a mass of not more than 500 combined Breeze-KM / spacecraft prior to kg and moments of inertia of up to 50 2 the payload deployment are: kg·m the total angular velocities ωy and ωz will not exceed 2.5°/s and the longitudinal

ωx = ± 1°/s component of ωx will not exceed 1.5°/s af- ωy = ± 0.5°/s ter separation, if the above methods are ωz = ± 0.5°/s combined. For spacecraft of larger size and higher inertia the disturbance values The spacecraft separation scheme system are smaller. design including the number of pushers, their allocation and energy is developed in Please note that these values shall be accordance with the requirements for en- considered as conservative ones. The ac- suring the spacecraft normal operations. tual parameters can be smaller depending on the properties of the specific spacecraft.

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To fulfil the Customer's requirements for Depicted in the figures below are two typi- the spacecraft separation, EUROCKOT cal payload deployment schemes. Figure selects the best suited of above methods 3-10 shows the sequential separation of to provide an optimal solution. three spacecraft with Δv added to each spacecraft to aid in-orbit plane phasing. 3.6.2.3 Typical Multiple Satellite Deployment Figure 3-11 shows a sequence in which six Scenarios spacecraft are released simultaneously.

Breeze-KM is able to perform a wide vari- The separation scenario of the spacecraft ety of complex pre-programmed manoeu- is laid out in accordance with number, ar- vres using a combination of its main, rangement and energy of the pushers and vernier and attitude control engines, that their requirements for normal operation of allow to implement injection of several pay- the satellite. The separation scenario is loads into specified target orbits. selected in cooperation with the Customer.

SC separation velocity 3 m/s SC separation velocity 3 m/s 26.5 26.5

t = 40 s t = 40 s Turn to Turn to t = 60 s payload t = 60 s t = 45 s t = 10 s payload Release SC2 separation Release SC1 and Realign Breeze-KM Impulse separation and stabilise direction stabilise Breeze-KM with velocity vector Δv = 5 m/s direction Breeze-KM

SC separation velocity 3 m/s

26.5

Target orbit t = 40 s plane Turn to t = 100 s t = 45 s t = 10 s payload t = 60 s Reorient Breeze-KM Realign Breeze-KM Impulse separation Release SC3 and Breeze-KM for deorbit with velocity vector Δv = 5 m/s direction stabilise Breeze-KM deorbiting manoeuvre

Figure 3-10 Example of sequential deployment of three spacecraft.

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TargetTarget Orbit orbit Planeplane

Upper composite Rotation around Rotation along the upper aligned with velocity the pitch axis stage longitudinal axis vector followed by simultaneous release of satellites into the target orbit plane

Figure 3-11 Example of simultaneous deployment of six spacecraft.

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