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Launching Small Satellites on the H-IIA Rocket

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Launching Small Satellites on the H-IIA Rocket SSC03-II-4 Launching Small Satellites on the H-IIA Rocket Shoichiro Asada Mitsubishi Heavy Industries, Ltd. 1- Oye-cho Minato-ku Nagoya Aichi Prefecture 455-8515 Japan 81-52-611-8040 [email protected] Naohiko Abe Mitsubishi Heavy Industries, Ltd. 1200 Higashi-Tanaka Komaki Aichi Prefecture 485-8561 Japan 81-568-79-1229 [email protected] Koichi Andoh AeroAstro Japan Co. Ltd. 3-10-5 Nishiwaseda Shinjuku, Tokyo 169-0051 Japan 81-3-5285-1275 [email protected] Dr. Rick Fleeter AeroAstro, Inc. 20145 Ashbrook Place Ashburn, VA 20147 USA 1-703-723-9800 x102 [email protected] Abstract. Over the last 40 years, the lowest cost transportation to space for small payloads has been achieved by utilizing excess capacity on large launches. Because the mass and volume used by small payloads on large vehicles are otherwise unused, often the pricing only needs to cover manifesting, integration and qualification of the so- called piggyback payload. Unfortunately this lack of economic incentive has suppressed supply – large rocket developers and operators may have little or no incentive to invest in small payload accommodations. In taking on the management of Japan's newest and largest rocket, the H-IIA, from the National Space Development Agency of Japan (NASDA), Mitsubishi Heavy Industries has decided to aggressively pursue opportunities for comanifesting nano, micro and mini-satellites, leveraging proven capabilities developed by NASDA for small satellite launches on Japan's largest launch vehicle. This new capability, to be demonstrated on the next H-IIA launch this year, has the potential to more than double the secondary space available to small payloads worldwide, and will reduce queueing time for launching small satellites. Introduction developed with little technical difficulty, if a customer so chooses. These factors induce many newcomers to The current state of the space industry is poor. There is enter the small satellite world, with a variety of new, little demand for telecom satellites, limited usage of the innovative ideas for small satellite applications. International Space Station, and minimal advanced vehicle development projects underway. In this Mitsubishi Heavy Industries (MHI) is aiding the small situation, small satellites have the potential to help satellite community by preparing to offer piggyback rejuvenate the space market. In general, small satellites launch accommodations and services to small satellite do not require significant budgets and they can be developers. MHI plans to provide launches to Sun- Asada, Shoichiro 1 17th Annual AIAA/USU Conference on Small Satellites Synchronous Orbits (SSO) and other Low-Earth Orbits their desired orbits on time. Four of the eleven (LEO), as well as Geosynchronous Transfer Orbit payloads were “small satellites”. Table 1 shows the (GTO). Accommodations range from approximately 50 flight results of the H-IIA launch vehicle to date. The kg to over 300 kg. AeroAstro and AeroAstro Japan are data demonstrates not only the reliability but also the cooperating with MHI to supply sales, marketing, and accurate performance of the H-IIA launch vehicle. engineering support to their secondary payload program. Basic Concept of Piggyback Launch on the H-IIA This paper outlines the launch services offered aboard The accommodations and services offered by the H-IIA the H-IIA for small, piggyback payloads. In particular, launch vehicle to a small, piggyback satellite depends the accommodations for a sample 50 kg satellite are heavily on that of the primary payload. Nevertheless, outlined in detail. H-IIA aims to provide the small satellite developer with the same level of service as the primary payload, H-IIA Launch Vehicle Flight Results without disrupting the mission of the primary payload. A variety of services can be requested, and H-IIA will After two successful test flights and two operational make every effort to address these requests. Detailed flights, the H-IIA launch vehicle lifted off on its third discussions regarding specific accommodations and operational mission on March 28, 2003. The H-IIA services are held on a case-by-case basis prior to launches have brought a total of eleven payloads to negotiating the launch service contract. Table 1. Flight Results of the H-IIA Launch Vehicle. TF1 TF2 F3 F4 F5 Launcher (H2A202) (H2A2024) (H2A2024) (H2A202) (H2A2024) August 29, February 4, September 10, December 14, March 28, 2001 2002 2002 2002 2003 Launch date ADEOS-II MDS-1 DRTS FedSat Government Satellite LRE DASH USERS WEOS Mission (Dual) µ-LabSat Payload 4S 4/4D-LC 4/4D-LC 5S 4/4D-LC Fairing GTO (MDS-1) GTO (DRTS) Orbit GTO SSO SSO LEO (DASH) LEO (USERS) Achieved Achieved Achieved Achieved ∆ ∆ ∆ ∆ (Target) (Target) (Target) (Target) Apogee Semi- 7,190 36,191 35,696 36,203 Altitude 5 -39 -3 Major (7,190 0 (36,186) (35,735) (36,206) (km) Axis (km) ±20) 0.001 Perigee 251 500 449.5 (0.001 Altitude 0 0 -0.5 Eccentricity 0 N/A (251) (500) (450.0) -0.001 (km) +0.003) Orbital 96.68 28.50 28.5 28.5 Inclination 0.01 0.0 0.0 Inclination (98.67± 0.01 (28.49) (28.5) (28.5) (deg) 0.25) Argument 179.2 179 179 of Perigee 0.1 0 0 (179.1) (179) (179) (deg) (Courtesy of NASDA) Asada, Shoichiro 2 17th Annual AIAA/USU Conference on Small Satellites Case of 50 kg Satellite Table 2. Quasi-Static Acceleration. Longitudinal Lateral In order to demonstrate the capabilities of the H-IIA for Acceleration Acceleration launch of small satellites using piggyback launch accommodations, an example has been selected, -58.84 m/s2 ±49.04 m/s2 Compression studied, and detailed in the sections below. This (-6.0 g) (±5.0 g) example is for a 50 kg satellite with main dimensions of 49.04 m/s2 ±49.04 m/s2 500mm x 500mm x 450mm and a top protrusion with Tension dimensions of Ø225mm x 50mm. (5.0 g) (±5.0 g) Services Available for Small Satellite Sine Wave Vibration The following services are provided by H-IIA to the Table 3 shows the maximum (three-sigma) sine wave small satellite: vibration limit levels in both the longitudinal and lateral directions. These levels are prescribed at the satellite ÿ Separation of Satellite: interface (satellite separation plane). The vibration is applied at the base of the adapter with a 4 In order to be separated, three split springs are to be octave/minute sweep rate in the up and down direction installed at the separation portion of the satellite. so that vibration levels at the spacecraft interface are The maximum stress limit at the edge of the split equal to the above levels. spring is 500N. Table 3. Sine Wave Vibration Levels. ÿ Command Signal to Initialize Satellite Equipment: A command to initialize equipment onboard the Direction Frequency (Hz) Acceleration satellite can be made by the separation detector. 2 Longitudinal 5-100 24.52 m/s Though the provision of the metal adapter on the Direction (2.5 g) rocket side is included as part of the launch services, the separation detector must be provided by the Lateral 5-100 19.62 m/s2 satellite developer. Direction ÿ Umbilical Random Vibration Umbilical (electrical) support is provided for use by the small satellite. The level of umbilical support Table 4 shows the random vibration levels in both the available is dependent on the requirements of the longitudinal and lateral directions. Random vibration is primary payload. primarily caused by acoustic noise. The satellite must be able to endure this vibration environment for 60 seconds. ÿ External Battery Charging If the small satellite developer prepares a cable from Table 4. Random Vibration Levels. the satellite to the exterior door of the rocket, the satellite battery can be charged from outside its Frequency Width (Hz) Acceleration (G2/Hz) fairing. 20-200 +3 dB/octave Launch Environment 200-2,000 0.032 Mechanical Environment Actual 7.8 Grms Quasi-Static Acceleration Acoustics Table 2 shows the maximum (three-sigma) quasi-static Table 5 shows the acoustic environment levels (two- acceleration in both the longitudinal and lateral sigma). Random vibrations are generated by the noise directions. The maximum quasi-static acceleration – a of the first stage main engine and Solid Rocket Booster, combination of static acceleration and low-frequency and the pressure vibration caused by buffeting and dynamic acceleration – is experienced at main engine boundary layer noise during the phase of the transonic (of the first stage) cutoff. The satellite structure must flight and the high dynamic pressure. The satellite must be designed to withstand this maximum aceeleration. be able to endure this environment for 80 seconds. Asada, Shoichiro 3 17th Annual AIAA/USU Conference on Small Satellites Table 5. Acoustic Pressure Inside Fairing The aerodynamic heat acceleration after separation of (No Acoustic Blanket) the fairing from the launch vehicle is less than 1,135 W/m2. Center H2A202 H2A212 Acoustic Frequency Acoustic Level Level [Reference] The temperature at the connection between the PAF and (Hz) (dB) (dB) the satellite varies between –10C and 50C. 31.5 125.0 128.0 63 126.5 129.5 Internal Pressure Environment 125 132.0 135.0 The air inside the payload fairing is vented during the 250 136.0 139.0 ascent phase through one-way vent ports. The pressure 500 134.0 137.0 decay rate typically varies while the launch vehicle is in 1,000 136.0 139.0 transonic flight, with a maximum rate of 4.51KPa/s. 2,000 130.0 133.0 4,000 121.0 124.0 Interface Conditions 8,000 116.0 119.0 Mechanical Interface Overall 141.5 144.5 The satellite must fit within a main envelope of 500mm Shock x 500mm x 450mm plus a top protrusion of Ø225mm x 50mm.
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