1、SMPTE EG*8 93 m 8357403 0001308 4T3 SMPTE ENGINEERING GUIDELINE Specif cat ions for Mot ion-Pictu re Camera Equipment Used in Space Environment EG 8-1993 Revision of EG 8-1984 1 Scope This guideline specifies the technical and operational requirements for the use of documentary and theatri- cal moti
2、on-picture cameras aboard a space shuttle. Page 1 of 7 pages Customer Service Center for customer liaison and interface with the STS program. The “document tree“ approach to the documentation structure has been implemented to facilitate easy access. (See figure 1 .) 3 Basic technical requirements 2
3、Objective 3.1 Electrical characteristics and speclflcations The objective of this guideline is to specify the con- ceptual design and associated technical specifica- tions for an onboard camera system that will enable NASA to offer motion-picture producers access to the space shuttle. These specific
4、ations cover the hard- ware that would be required for using the space shuttle as a universal camera platform and an earth orbit location for depicting mans presence in space. (Detailed specifications are listed in annex A.3.) 2.1 Concept 1 Figure 1 provides a generic description of payload integrat
5、ion above the shuttle to familiarize users with a typical scenario of the integration process. New design, redesign, and/or new utilization of pay- load hardware must take into account requirements of the integration process in the early stages of the project for cost effectiveness and efficiency. T
6、he extent and complexity of each integration step will depend largely upon the specific payload and its planned utilization. Requalification of previously flown equipment for reflights is a relatively easy process. Introduction of new equipment and new utilization may involve the full integration pr
7、ocess. Sufficient and adequate planning is highly advisable in the initial stages of the project to meet the overall objectives for the payload and make a specific flight of the shuttle, if desirable. 2.2 Basic references NASA has established a methodological approach for the shuttle documentation s
8、ystem and is providing a I 3.1.1 Power DC or ac power may be made available through the shuttle orbiter (see reference 7 of annex A.3). DC power - voltage: 28 V 2 4 V upon location power: TBD watts depending AC power - voltage: 115 V * 5 V rms power: TBD watts frequency: 400 Hz e 7 Hz 3.1.2 Fusing c
9、riteria The payload element is required to provide circuit protection in the form of fuses, resistors, or other current limiting devices on its side of the inter- face in order to protect payload elementlorbiter wiring. 3.1.3 Electromagnetic compatibility (EMC) The payload shall comply with the radi
10、ated and conducted electromagnetic interference require- ments of ICD 2-19001 , paragraphs 10.7.3, 10.7.3.1, and 10.7.3.2 (see reference 2 of annex A.3). As a design goal, cargo wiring on the pay- load side of the interface shall meet the require- ments of Table 10.7.1 -2 (see reference 2 of annex A
11、.3) or utilize equivalent shielding. Copyright O 1993 by the SOCIETY OF MOTION PICTURE AND TELEVISION ENGINEERS 595 W. Hartsdale Ave., White Plains, NY 10607 (914) 761-1100 Approved November 17,1993 SMPTE EG*8 73 m 8357403 OOOL307 33T m EG 8-1993 Y -8 F 2 c c s Page 2 of 7 pages SMPTE EG*8 93 835740
12、1 0001310 051 3.2 Basic mechanical characteristics and specif ications 3.2.1 Approved lubricants shall be as shown below: b (a) Crew cabin - JSC-approved (Johnson Space Center) lubricants (see annex A.4); (b) Payload bay - lubricants meeting MIL L-8937 or L-4601 O (see annex A.4). 3.2.2 Finish shall
13、 be anodized or painted as per Mil-spec MIL C-83286, unless titanium is used as the structural material. 3.2.3 Controls and adjustments shall be acti- vated with minimal force and shall achieve pos- itive positioning (see annex A.l). 3.2.4 Mounting points shall be provided for locking attachment on
14、three sides of camera ho us i ng . 3.2.5 All material used shall meet JSC Spec. SE-R-OO6B. 3.3 Camera/ location b EG 8-1993 Single locker Double locker Height: 9.5 in 20.5 in 16.8 in Width: 16.8 in 19.7 in Depth: 19.7 in These dimensions allow for %in clearance all the way around for the isolation/s
15、uspension foam. 3.5.2 Magazines or film canisters should be quick-release type. 3.5.3 Self-threading film path is preferred. 3.5.4 Weight not to exceed 150 Ibs (68 kg) with full film load. 3.6 Categories of locatlons and requirements The categories range from a completely self- contained system that
16、 requires activation only at certain times to an elaborate multi-camera operation including directed camera movement from both on- board and remote locations outside the shuttle while in space. 3.6.1 Cabin environment conditions (a) Temperature: Nominal 65OF-75“F (1 8%-24“C); 3.3.1 Cabin location (b
17、) Relative humidity: Nominal 50%; 3.3.2 External location (c) Gravity: O g; 3.3.2.1 Payload bay gas can 3.3.2.2 Payload bay pallet and brackets 3.3.2.3 EVA location 3.4 Camera operating systems 3.4.1 Manual control 3.4.2 Remote control 3.5 Basic physical characteristics of cameras 3.5.1 External dim
18、ensions to permit camera to be placed in storage locker: (d) Acceleration/vibration/shock: Up to 9 gs 25 Hz minimum; (e) Lighting: 1 O footcandles average; (9 Power: 28Vdc; (9) Mechanical: Mounting points for equipment storage areas below deck; (h) Weight: 150 Ibs maximum (68 kg); (i) Finish and com
19、ponents: No outgassing. 3.6.1.1 Photographic equipment to be used in this environment is subject to certification by Page 3 of 7 pages SMPTE EG*8 93 = 8357403 000333L T98 EG 8-1993 NASA. (A listing of previously certified cameras used for instruments or documentary purposes can be obtained from the
20、NASA Customer Service Center.) 3.6.2 Payload bay gas can The Get-Away Special (Gas Can) and self-contained power supply with remote control would not require special NASA certification. This camera would be in a fixed position with the field of view predetermined by the mounting. 3.6.2.1 Gas can env
21、ironment operating condi- tions (a) Temperature: Depending upon the use of insula- tion and heaters, nominal 5O0F-80“F (1 O“G27“C); (b) Relative humidity: Use of dry nitrogen could maintain humidity at less than 10%. Moisture problem on glass surfaces; (c) Gravity: O g; (d) Acceleration/vibration/sh
22、ock: Up to 9 gs ? 25 Hz minimum; (e) Lighting: Ambient - bright sunlight to space black; (9 Power: Battery or orbiter power; (9) Mechanical: Mounting points in canister (suspen- sior in solamide foam is advisable); (h) Weight: 200 Ibs maximum (91 kg); (i) Size: 20“ I.D. x 28“ height, cylinder (MDA c
23、onfig- uration). 3.6.2.2 Photographic equipment Camera equipment is at the discretion of the user. The equipment must withstand launch and re-entry shock and vibration. 3.6.3 Payload bay (environmental and operational conditions) 3.6.3.1 Structure using existing mounting points 3.6.3.2 Pallet mounti
24、ng fixed - remote operation 3.6.3.3 Pallet-mounted remote pan and tilt 3.6.3.4 Payload bay environment operating conditions I (a) Temperature: -273F to 21 2F; (b) Relative humidity: 0% to 100%: (c) Gravity: O g; (d) Acceleration/vibration/shock: Up to 9 gs ? 25 Hz minimum; (e) Lighting: Ambient brig
25、ht sunlight to space black; (9 Power: 28VDC; (9) Mechanical: Mounting points compatibility; (h) Weight: TBD ibs maximum; (i) Size: TDB cube; (i) Finish and components: No outgassing. The cameras and lenses to be exposed to the space environment shall require protective enclosures, heat- ing and cool
26、ing provisions, and special shock and vibration mountings. If the cameras utilize shuttle power, they will be certified by NASA for compliance with RFVEMI and other electrical specifications. The same requirement will also apply to all remote-control equipment. 3.6.4 Remote manipulator systems (RMS
27、arm) The mast that is used for moving and placing payloads may be used for photographic purposes. However, this mast has limited travel capability and cannot handle any heavy weight until the shuttle is in orbit. 3.6.5 Free flyer This type of operation requires the .photographic system to be capable
28、 of being ejected or placed in space and remotely controlled. The remote control may come from either the shuttle or a ground-based control center. It is also possible to utilize the free flyer as a type of satellite system with complex movements for pan, tilt, and scan. The system may be combined w
29、ith a television observation system to permit opera- tors to choose their fields of view. Alterations in the orbit of the photographic platform are also possible. ( Page 4 of 7 pages SMPTE EG*8 93 W 8357401 0001312 92L, 3.6.6 Extravehicular activity (EVA)/extravehicular I mobility unit (EMU) A descr
30、iption of EVNEMU and their requirements are shown in annexes A.l and A.2, and refer to Sec. 9.0 of Vol. XIV, Revision H, JSC 07700, Space Shuttle System Payload Accommodations. Any user who plans on employing the EVNEMU for photographic purposes must be aware of the con- straints and extensive plann
31、ing required to utilize this option. The categories that have been described are a method for providing the potential user with a choice of shuttle capabilities. As the user decides on the needs for the photographic coverage, the lead time, cost, and coordination are progressively more com- plex and
32、 expensive. The user shall determine from these categories what equipment is required and plan accordingly. EG 0-1993 6.2 Storage, handling, and transportatlon All equipment shall be in an approved container which is capable of withstanding environmental require- ments as per annex A.3. The equipmen
33、t in its con- tainer shall be identified to indicate its type, ownership, mission number, special handling instruc- tions, weight, and volume. Expiration dates for any components, supplies, parts, critical sensors, and material shall be provided. 6.3 Personnel certiflcation All personnel involved wi
34、th the equipment who will be interfacing with NASA personnel shall be identified by name and social security number. People requiring access to NASA installations, facilities, and areas shall be certified at least ten days in advance of their first visit. 4 Illumination sources 6.4 Camera documentat
35、ion equipment Illumination, including incandescent, arc, xenon or other gas-filled tube, fluorescent, and reflective, shall meet safety and environmental specifications for photog rap hic eq u i pment . Requests for inClUSi0n on shuttle flights shall be Sub- mitted 24 months Prior to desired date on
36、 NASA Form 1 OO. Reports of operations and projected time-lines shall be submitted 60 days after approval. I 5 Motion-picture film stock 5.1 Types of film 5.2 Optical filter requirements 5.3 Film storage in space 5.3.1 Unexposed stock 6.5 Change requests Final change requests shall be submitted 180
37、days prior to mission launch date. No changes will be accepted after that date. A penalty will be imposed on any contractor who cancels his request less than 18 months before a scheduled launch. 5.3.2 Exposed stock 7 General responsibility 5.4 Film storage prior to and after mission 6 Basic operatio
38、nal requirements 6.1 Equipment certification All equipment shall be available for initial certification tests at least 120 days prior to date of scheduled mission. If the equipment has not been certified previously for shuttle use, it shall be initially certified 18 months prior to the mission on wh
39、ich it is planned to be used. 1 The organization supplying the equipment and recording material is responsible for its proper perfor- mance. NASA personnel will assist the supplier with the installation, checkout, storage, and removal but should a failure occur, the supplier accepts total responsibi
40、lity. Operation of the equipment by shuttle personnel shall be performed in as professional a manner as possible; however, should there be operational variations from the requested time-lines, the supplier shall accept those variations due to oper- ational problems. Page 5 of 7 pages SMPTE EG* 73 =
41、8357403 OOOL3L3 8bO EG 8-1993 8 Safety guidelines the applicable requirements outlined in the above references. References 8 and 9 of annex A.3 establish the safety requirements and guidelines applicable to all STS payloads and their GSE. It is the responsibility of each payload organization to assu
42、re the safety of its payload and to implement all The Safety Panel review meetings (Phase O, I, II, and Ill) are being arranged and scheduled with NASAin order to assist the payload organization in identifying poten- tial safety hazards and provide cost-effective methods for their elimination. Atypi
43、cal time plan for scheduling the Safety review meetings is shown in figure 1. Annex A (informative) Additional data A.l Extravehicular activity (EVA) A.1.3 EVA guidelines and constraints A.l.l Shuttle orbiter EVA definition and provisions The term EVA, as applied to the space shuttie, inciudes all a
44、ctivities for which crew members don their space suits and life-support systems and then exit the orbiter cabin into a vacuum space environment to perform operatioris internal to or external to the cargo bay volume All EVA equipment and payload interfaces for EVA must be designed to be compatible wi
45、th shuttle and EVA operations such as those mentioned below. A.1.2 EVA capabilltles Given adequate restraints, working volume, and compatible man-machine interfaces, the EVA crew members can dupli- cate almost any task designed for manned operation on the ground. The following typical EVA tasks demo
46、nstrate the range of EVA opportunities available to the payload designer: (a) Inspection, photography, and possible manual override of vehicle and payload systems, mechanisms, and com- ponents; (b) Installation, removal, or transfer of film cassettes, material samples, protective covers, instrumenta
47、tion, and launch or entry tie-downs; The following general EVA guidelines and constraints shall apply to payload EVA design. EVA operations will be developed using tha capabilities, requirements, definitions, and specifications set forth in JSC 10615, Shuttle EVA Description and Design Criteria. A.1
48、.4 Airlock specifications The size of the airlock, tunnel adapter, and associated hatches limits the external dimensions of packages that can be transferred to or from payloads to 22 x 22 x 50 in (559 x 559 x 1270 mrn) for unsuited operations and to 18 x 18 x 50 in (457 x 457 x 1270 mm) for pressure
49、-suit operations. Package sizes exceeding these dimensions shall be evalu- ated on an individual basis. A.2 Extravehicular mobility unit (EMU) The extravehicular mobility unit consists of a self-contained (no umbilicals) life-support system and an anthropomorphic pressure garment with thermal and mircometeoroid protec- tion. A.3 Reference documents Integration related 1 07700, Vol. XIV, latest revision) Space Shuttle System Payload Accommodations (JSC 2 Shuttle OrbiterlCargo Standard Interfaces (Attachment 1 of Jsc 07700, IcD 2-19001) (c) Operation of equipment, including too
