Falcon 9 Launch Vehicle Payload User's Guide - SpaceX

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5.2.3.6. Fairing Internal Pressure Environment Falcon 9 User’s Guide Payload fairing internal pressure decay rates are limited to 0.4 psi/sec (2.76 kPa/sec), except for a transonic spike to 0.9 psi/sec (6.2 kPa/sec). 5.2.3.7. Payload Temperature Exposure During Flight The Falcon 9 payload fairing is a composite structure consisting of a 1‐inch (2.5‐cm) thick aluminum honeycomb core surrounded by carbon fiber face sheet plies. The emissivity of the payload fairing is approximately 0.9. Based upon this emissivity, the payload fairing inner wall temperature is bounded as shown in Figure 5‐7. The curve is truncated at 250 seconds, although the approximate time of payload fairing jettison for a geosynchronous transfer orbit mission from Cape Canaveral is earlier, at 200 seconds. Payload fairing jettison timing is determined by customer requirements. Figure 5‐7 ‐ Maximum Payload Fairing Temperature Seen By Payload 5.3. Payload Interfaces Falcon 9 will provide the pyrotechnic impulses necessary to initiate separation events. The launch vehicle will also provide a signal to the payload at separation to initiate payload power‐ up. Alternate configurations for separation signals (break‐wires, separation switches monitored directly by the payload, or other configurations) can be accommodated as options. The standard payload fairing provides up to 3 access doors, 24” (61 cm) in height, for prelaunch access. These doors are not designed for emergency access into the payload fairing once the launch vehicle is on the pad. Under nominal operating conditions, all processing that requires access to the payload must be complete prior to fairing installation. In the event of a spacecraft SCM 2008‐010 Rev. 1 Copyright ‐‐ SpaceX 2009 40
Falcon 9 User’s Guide propellant system failure that requires contingency propellant offload, the standard concept of operations for Falcon 9 is to return the launch vehicle to the hangar. 5.3.1. Falcon 9 Payload Attach Fittings Falcon 9 launch vehicles do not baseline a specific separation system. Customers have the option to provide the payload adapter and separation system to interface directly with a payload adapter attachment location provided as a standard service by SpaceX. Alternatively, SpaceX can supply the payload adapter and separation system as a non‐standard service. The Falcon 9 Payload Interface Ring is used in the 5.2 m (17 ft) fairing configuration. This simple interface is provided for customers with medium‐ and intermediate‐class payloads that prefer to provide their own launch vehicle adapter/separation system. A diagram of the Falcon 9 payload interface, which consists of a 1575 mm diameter bolt pattern, follows in Figure 5‐8. SpaceX has experience integrating numerous commercially‐available and internally‐developed payload separation systems. A Marmon clamp system was flown on the first Falcon 1 demonstration flight 1 and a LightBand system from Planetary Systems Corporation was employed on the second Falcon 1 demonstration flight. Additionally, SpaceX is currently developing a low‐shock tension band separation system for the Falcon 9, which uses a non‐ pyrotechnic release mechanism. SCM 2008‐010 Rev. 1 Copyright ‐‐ SpaceX 2009 41
Page 1 and 2: Falcon 9 Launch Vehicle Payload Use
Page 3 and 4: Falcon 9 User’s Guide 5. General
Page 5 and 6: Falcon 9 User’s Guide Our design
Page 7 and 8: Falcon 9 User’s Guide rocket‐ g
Page 9 and 10: Falcon 9 User’s Guide crewed laun
Page 11 and 12: 2.2. Vehicle Axes/Attitude Definiti
Page 13 and 14: Figure 3‐3 ‐ Space Launch Compl
Page 15 and 16: Falcon 9 User’s Guide 3.3. Space
Page 17 and 18: Falcon 9 User’s Guide 3.5. Test F
Page 19 and 20: 4.1.1. Low Earth Orbit Payload Mass
Page 21 and 22: 4.1.3. Sun Synchronous Payload Mass
Page 23 and 24: 4.1.5. Geosynchronous Transfer Orbi
Page 25 and 26: 4.1.7. Geosynchronous Transfer Orbi
Page 27 and 28: Falcon 9 User’s Guide 4.2. Sample
Page 29 and 30: Falcon 9 User’s Guide 4.3. Mass P
Page 31 and 32: 5.1.3. Payload Separation Falcon 9
Page 33 and 34: AXIAL (G) -2, 3.5 -2, -1.5 -0.5, 6
Page 35 and 36: Figure 5‐4 ‐ Falcon 9 acoustic
Page 37 and 38: Function Table 5‐2 ‐ Falcon 9 L
Page 39: Freq (MHz) E Field Limit (dBμV/m)
Page 43 and 44: 5.3.2. Test Fittings and Fitcheck P
Page 45 and 46: Figure 5‐9 ‐ Spacecraft to Laun
Page 47 and 48: Falcon 9 User’s Guide encapsulati
Page 49 and 50: Launch Vehicle Ops Ground Ops Paylo
Page 51 and 52: Falcon 9 User’s Guide • Process
Page 53 and 54: Falcon 9 User’s Guide replaced wi
Page 55 and 56: 6.2. Spacecraft Transport to Launch
Page 57 and 58: Choice of 2 more consoles in these
Page 59 and 60: 6.3.1. Mission Integration Plan Tab
Page 61 and 62: 7. Safety 7.1. Safety Requirements
Page 63 and 64: Payload Information Payload Name/Ti
Page 65 and 66: Do you have a Spacecraft Separation
Page 67 and 68: 6. Please describe the RF systems t
Page 69 and 70: Falcon 9 User’s Guide 9.2. List o

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