Μlambda Rocket Concept for Small Satellites

μLambda Rocket Concept for Small Satellites

Yuichi Noguchi, Kazuhiro Yagi, Takumi Kanzawa, Takashi Arime and Seiji Matsuda IHI AEROSPACE Co., Ltd. | [email protected] | Tomioka-shi, Gunma, Japan

Hideki Kanayama CSP Japan, Inc. | [email protected] | Tokyo, Japan

Yoichi Harada Monohakobi Technology Institute | [email protected] | Tokyo, Japan

Takayoshi Fuji Japan Space Systems | [email protected] | Tokyo, Japan

26th Annual AIAA/USU Conference on Small Satellites | 13-16 August 2012 | Logan, Utah USA | SSC12-V-8 P.0 Contents

¾ 1.Background ¾ 1.1 Small Launches Trends ¾ 1.2 IA Rocket Systems ¾ 1.3 Other Countries Activities for Small Launcher ¾ 2.Objectives ¾ 3.Air Launch System ¾ 3.1 Air Launch Objectives ¾ 3.2 Air Launch Method ¾ 4.μLambda ¾ 4.1 μLambda Overview ¾ 4.2 μLambda Typical Flight Sequence ¾ 4.3 μLambda Launch Capabilities ¾ 5.Small Launcher Avionics ¾ 6.Air Launch System Trade ¾ 7.Summary

P.1 1.1 Small Launches Trends

9The number of small satellites will be expected to increase by taking advantage of their lower development cost and risk. 9Necessary to provide low-cost and flexible launch opportunity for low-cost small satellites, not larger launch systems.

(Source: Eurospace, Sep. 30th 2011) P.2 1.2 IA Rocket Systems

9IHI AEROSPACE Co., Ltd. (IA) has been a leading company in solid rocket development within Japan.

¾Sounding rocket flight : Over 1400 ¾μG Experiment rocket flight : 7 ¾Satellite LVS flight : 27

10(m) 30 (m) Still in use

0 0 MT-135 S-210 K-9M K-10 S-310 S-520 SS-520 L-4S M-4S M-3C M-3H M-3S M-3SII M-V Total Length 3.3m 5.2m 11.1m 9.8m 7.1m 8.0m 9.65m Total 16.5m 23.6m 20.2m 23.8m 23.8m 27.8m 30.7m Diameter 0.135m 0.21m 0.42m 0.42m 0.31m 0.52m 0.52m Length Weight 0.07t 0.26t 1.5t 1.78t 0.7t 2.1t 2.6t Diameter 0.735m 1.41m 1.41m 1.41m 1.41m 1.41m 2.5m Altitude 60km 110km 330km 240km 190km 430/350km 1000/800km Total 9.4t 43.6t 41.6t 48.7t 48.7t 61t 139t Payload 2kg 20kg 55kg 132kg 70kg 70/150kg 30/60kg Weight Flight Year 1964 1969 1962 1965 1975 1980 1998 Payload to 26kg 180kg 195kg 300kg 300kg 770kg 1800kg Launches 1200+ 44 88 1441 39 2426 2 LEO Flight year 1970 1971 1974 1977 1980 1985 1997 Image Source Rate (s/l) 1/5 3/4 3/4 3/3 4/4 7/8 6/7 Sub-Orbital LVS (Sounding Rocket) Satellite LVS

P.3 1.3 Other Countries Activities for Small Launcher

9Derivatives of sounding rockets and air launch systems are getting more attention for low-cost and flexible launchers.

SPARK / SuperStrypi ALDEBARAN Virgin Galactic

GO Nanosatellite launch challenge

DARPA HLS, ALASA ALISC / ALAC (Polyot) Stratolaunch

Derivatives of sounding rockets Air launch systems P.4 2.Objectives

9 To provide low-cost and flexible launch opportunity ¾ Low-cost: small launch systems not depending on larger launches ¾ Flexible: air launch systems

9 ”μLambda”: capable of lifting up a 100kg payload into LEO 250km ¾ Smaller and lighter avionics ¾ New air launch systems by employing existing aircrafts

P.5 3.1 Air Launch System Objectives

9Air launch systems are most effective for low-cost launches. They can provide low-cost and flexible launches to respond small satellites demand for the following reasons. ¾Increase of rocket performance ¾No need for large launchpad ¾No constraints to launch window ¾Optimum launch for a satellite orbit 9Given this background, authors have been conducting R&D on air launch systems. The air launch systems provide high reliability, flexibility and responsiveness to meet the future needs of small satellite users.

P.6 3.2 Air Launch Method

9There are three major types of air launch method.

Separation Velocity Subsonic Supersonic

Air Drop Subsonic Horizontal Supersonic Zoom Flight

Air Launch Method

Example

Source: Boeing Source: OSC Source: Air Launch Launch Capability 60 [kg] 80 [kg] 110 [kg] (in case of 6 ton rockets) (LEO250km) (LEO250km) (LEO250km) P.7 3.2 Air Launch Method

9Each of air launch method can increase performance (launch capability).

Launch Method LEO250[km] * In case of 6 ton rockets 120 Supersonic zoom flight

100 Subsonic horizontal with wing w/o wing

60 資料の英語化必要打上能力[kg] 高度15km マッハ1.5 (F-15) Launch capability [kg] 40 Alt. 15km M1.5 (F-15) 高度12km マッハ0.8 (Boeing747)Alt. 12km M0.8 (Boeing 747) Air drop 20 高度10km マッハ0.6 (C-X)Alt. 10km M0.6 (C-X) 陸上発射Ground launch Ground launch 0 0 20406080100 Flight-path飛行経路角 angleγ γ[de[deg]g] P.8 3.2 Air Launch Method

9Performance increase factors are shown.

Air drop Subsonic horizontal Supersonic zoom flight Air launch method

Performance increase factors Altitude 10 [km] 12 [km] 15 [km] Lower dynamic pressure due to lower atmosphere density Drag Lower velocity loss by drag, lighter structure

By altitude Larger thrust due to lower pressure thrust loss and larger 1st stage nozzle Thrust expansion ratio Initial velocity Mach 0.6 Mach 0.8 Mach 1.5 Less than 0 [deg] 0 [deg] About 40 [deg] Rocket initial velocity Rocket initial velocity is Rocket initial velocity is Flight-path angle increase is about zero equal to aircraft initial equal to aircraft initial velocity velocity By velocity Maneuver loss caused Optimum flight-path by pitch-up angle

By Launch spot flexibility Fewer constraints for flight safety, optimum azimuth others P.9 3.2 Air Launch Method

9Air launch systems can decrease much amount of velocity loss. 35

(In case of subsonic horizontal air launch, it’s about 60% as Uchinoura ground launch.) 30

Æ Contribute performance increase Ｂ１ＢＯ 25

4000 大東島回避の重力損失Gravity loss DoglegためのIIP制約空気抵抗損失Drag loss 20 3500 制御損失Control loss 大気圧による推力損失Thrust loss 3000 15

Ｂ２ＢＯ 2500

北緯 [degN] 10

2000 5 セラム島付近の遠方の飛行安全をConstraints for IIP通過点制約 North Longtitude [degN] 考慮した飛行経路flight safety

速度損失 [m/s] 1500 Velocity loss [m/s] 0 1000

-5 -－○ 陸上発射（内之浦）Ground launch 500 -－△ 海上発射（紀伊半島沖）Sea launch -－□ 空中発射（紀伊半島沖）Air launch -10 0 120 125 130 135 140 145 Air 空中発射launch Sea 海上発射 launch 陸上発射Ground launch (Uchinoura) 東経 [degE] (USC) East Latitude [degE] Velocity loss (in case of SSO500km) Trajectories for SSO500km P.10 4.1 μLambda Overview

9μLambda is a three-staged solid rocket designed to meet the needs of small satellite users. 9The motor mass ratio of all the stages is 0.93.

After B2 Sep. Fixed Tail Fins After Fairing Sep.

After B1 Sep. μLambda for Supersonic Zoom Flight (the same as ground launch) Item Value Total Length 13.4 [m] Diameter φ850 [mm] Gross Weight 7,350 [kg] (excluding payload or wing) Canard Control 1st Stage 4,080 [kg] Wing Propellant Mass 2nd Stage 1,800 [kg] 3rd Stage 460 [kg]

μLambda for Subsonic Horizontal P.11 4.2 μLambda Typical Flight Sequence

9μLambda typical flight sequence is shown below. Nose Faring Sep. B3 Bo.

B3 Ig. Satellite Sep. Yo-Yo de-spin B2 Ig. B2 Bo. B1 Bo. B2 Sep. 3rd Stage Control B1 Sep. 2nd Stage Control by RCS by TVC 3rd Stage Control by TVC 1st Stage Aerodynamic Spin Stabilization 2nd Stage Control by Fixed Tail Fins by RCS (during coasting) B1 Ig.

Ground launch OR Spin Stabilization instead of TVC (lower cost but less performance in orbit precision)

Evacuation

Separation Take-off Air launch (subsonic horizontal) Attached under the Wing of MD-80 P.12 4.3 μLambda Launch Capabilities

9Each launch capability of each air launch method is shown below. 9Air launch methods increase launch capability.

LEO250km 140

120

100

40 Launch Capability [kg] 20

0 Ground launch Subsonic horizontal Supersonic zoom flight

EA-6 F-15 P.13 5.Small Launcher Avionics

9Low-cost smaller and lighter avionics are needed for small launchers. 9Current avionics are too heavy to increase launch capability. 9Each device can be smaller and lighter by reduction of functions and so on.

Flight Termination, included in the others Flight Termination Power Supply, GN & C, 8 GN & C, 43 6 Data Data Power Acquisition Acquisition RT & Control and and and Command, Supply, 132 19 Telemetry, Telemetry, 11 45 Power Control and Supply, 8

Current Mass [kg] Target Mass [kg] Total: 220 [kg] Total: 52 [kg] Æ To less than 40 [kg] P.14 5.Small Launcher Avionics

9The following activities make avionics smaller and lighter. ¾Get relays smaller and lighter ¾Serial communication

[Now] [Downsizing] [Future concept] - mechanical relay - semiconductor relay - self-diagnosis function - high-density mounting - efficient operation

44mm

8.0 8.0 8.0 17.517.517.517.5 26mm 26mm 13.4 3.4 13.5 質量 3.3g 26mm 26mm

Mechanical relay Semiconductor relay IC with self-diagnosis function (MOSFET) (ex.: for automobile airbags)

P.15 6.Air Launch System Trade

9Trade result indicates priority of air launch system in 10 years.

Rocket μLambda

Air Launch Method Attached under the wing Piggyback

Launch Configuration US Patent 4208949

Launch Capability ~100 [kg] (LEO250km) ◎ ◎ ○ △~× ○~△ Less conversion Less conversion Need conversion on Need large Need conversion on Easier to maintain Easier to maintain attachments conversion on the the aircraft back Easier to get aircrafts Easier to get aircrafts Easier to maintain aircraft More difficult to Priority Easier to get aircrafts Easier to maintain maintain More difficult to get Easier to get aircrafts aircrafts

P.16 7.Summary

9 μLambda concept was shown as a low-cost and flexible rocket system. ¾ The results of the activities for smaller and lighter avionics showed that it’s possible to achieve 52 kg avionics. ¾ The merits of air launch systems were shown. About 50% increase of launch capability was also shown. ¾ The air launch system candidates by employing existing aircrafts were shown. ¾ To realize μLambda and the air launch system, international cooperation of manufactures and operators of aircrafts, engines and so on are indispensable. 9 μLambda concept study will be progressed. ¾ The goal mass of avionics will be 40 kg. ¾ Rocket system trade on control system and performance will be conducted.

P.17