Mcoomml

Oat 26 November 1< 62 - ,T L0U Sf Min0URI _12. 3-5-1 DESCRIPTION - The Model 133L Spacecraft shall be of semi-conical configuration, incorporating a blunt forebody designed to mate the booster adapter and support the retrograde rocket package (see Figure 1, Page 9 ) The convex contour of the forebody shall provide maximum practical wave drag and uniform heating consistent with other requirements. The afterbody shall consist of a truncated conical section s amounted (in 1attitude) by a short...

Rkponta

vimd -i ffrinnir IT ITltW moocl Mercury Spacecraft 3-11* COMMUNICATIONS SYSTEM - The communications system provided aboard the Mercury Spacecraft shall be compatible with the world-wide ground station complex. Wherever practicable, existing systems of telemetry, tracking, and voice communications shall be used. The following systems of communication (Drawing No. 45-05700) shall be provided aboard the spacecraft Telemetry equipment - spacecraft to ground 3-14.1 TWO-WAY HF UHP ORBITAL VOICE...

Reaction Contr

SHUT NEE SHUT-OFF (Hp> NEEDLE VALVE (HP) 3.11.1 DESCRIPTION - The re-entry phase of the mission shall be initiated by firing a retrograde rocket system consisting of three Thiokol Model TE-316 solid propellant rockets and associated components as specified in Appendix I-C, Item 2. The target value for magnitude of the retrograde impulse shall be to provide a velocity decrement of approximately 465 feet per second for the spacecraft weight as specified in Paragraph 3*1.1.3. Each rocket shall...

A

POWER SYSTEM - The A.C. power system shall consist of two main and one standby static inverters and filters for conversion of 24-volt D.C. power to 115-volt, single-phase, 400-cycle A.C. power. Ambient air in the vicinity of the inverters shall be drawn through a screened duct installation (Drawing No. 1+5-83144) to the cabin fan intake. The cabin fan shall force the air through the cabin heat exchanger to assist in dissipating heat resulting from inverter operation. 3.13.3.1 MAIN...

Threeaxis Hand Controller

Mercury Spacecraft 3-9 SPACECRAFT ENVIRONMENTAL CONTROL 3-9-1 ENVIRONMENTAL CONTROL SYSTEM - Control of suit and cabin environment shall be accomplished by means of an environmental control system (Drawing No. 1+5-83700). The environmental control system shall provide the following a. Environmental control, pressure 3uit (internal circuit) b. Environmental control, cabin and equipment 3 9-1-1 DESCRIPTION - The environmental control system shall consist of a gaseous oxygen supply that shall...

Info

3.8.9.4.1 WARNING LIGHTS - (Continued) CO2 PRESS (Suit CO2 Content Above 8 mm Hg.) OUT OF ORB MODE (High Thruster Firing) O2 EMERGENCY (Emergency Oxygen Rate Valve Open) O2 QUAN (Depletion of Secondary 02 to 65OO psig) EXCESS H2O (Low Heat-Exchanger Exhaust Temperature) STANDBY AC AUTO (Standby Inverter in Operation) FUEL QUANTITY (Depletion of Automatic Fuel to 10 Pounds or Manual Fuel to 15 Pounds) RETRO WARN (30 Seconds to Retrograde Firing) RETRO RESET (Satellite Clock Reset From Command...

PAT Hovwter T LOUSt Miuourii

vi 0-__ flUBM 1 mffWW i (iOOCL Mercury Spacecraft vi 0-__ flUBM 1 mffWW i (iOOCL Mercury Spacecraft 3.8.9.7 FUSE SWITCHES - Fuse switches shall be provided for manual reset of interrupted circuits, but actuation by the astronaut shall be based upon his knowledge of the spacecraft systems and their functions. No special visual system for indication of an interrupted circuit shall be provided. Fuse switches shall be located on the main instrument panel and on a switch panel (Drawing No....

Hf Dipole Antenna Continued

The spools shall be held in the stowed position by squib-disconnected retaining straps. At spacecraft separation plus 10 seconds, antenna extension shall be initiated. Upon unwinding from the spools, the metal tape shall return to its original tubular form. The m UTlly Select the DIPOLE ANT position on the HF ANTENNA SEIECT switch (see Paragraph 3-14.6). At retrograde package separation, the antenna coax cable shall be severed by a squib-actuated cutter. The...

Leach

CONTRACTOR-FURNISHED EQUIPMENT - CONTBACTOR INSTAT-TTT) ELECTRICAL SYSTEM - (Continued) 4.64 7 fc.65 3 4.66 l T.I mit Switch Limit Switch Limit Switch Limit Switch Push Button Relay - Time Delay 2 Seconds Relay - Time Delay 5 Seconds qate 26 November 1962 nevisco ___________ qate 26 November 1962 nevisco ___________ CONTRACTOR-FURNISHED EQUIPMENT - CONTRACTOR INSTALLED ELECTRICAL SYSTEM - (Continued) 4.80 3 Light Assembly (Green) 4.81 2 Light Assembly ( mber) 45-79720-49 33340-49-327...

Oisa

Valve, Throttle, 1-6 Lb. (1 4) Manual T C Assy., Roll, Lower (l to 6 Lb.) Manual T C Assy., Roll, Upper (l to 6Lb.) Manual T C Assy., Pitch and Yaw 1 Lb., Auto (Mod. by 45-62110) T C Assy., Roll Lower, (1 and 6 Lb.) Auto (Mod. by 1+5-62110) T C Assy., Roll Upper, (1 and 6 Lb.) Auto (Mod. by 45-62110) * To be shipped to launch site for installation Communications System Consisting of 1 Transmitter-Receiver, HF Voice (Mod. By 45-85017) 1 Power Divider, C-Band (Mod. By 45-65038) 1 Isolator, Blcone...

Ore November

CONTRACTOR-FURNISHED EQUIPMENT - CONTRACTOR INSTALLED ENVIRONMENTAL CONTROL SYSTEM - (Continued) 5-83700-835 45-83700-845 45-837OO-847 * * To be shipped to launch site for installation CONTRACTOR-FURNISHED EQUIPMENT - CONTRACTOR INSTALLED INSTRUMENTATION SYSTEM No. Mfg. No. System, Instrumentation, Consisting of Instrumentation Package A, Including Resistance Element, A.C. Power Supply * To be shipped to launch site for installation Assembly, Instrumentation, Filter, Noise Amplifier Power...

AMcdonnkll

' st. louis, Minoum h4 visko-- _moo.l Mercury Spacecraft 3'9-9 INSTRUMENTATION AMD DISPLAYS - Continued Astronaut's Recording Method Warnings Indication See Figure 8 3.8.9-1 SATELLITE CLOCK - A satellite clock Drawing No. 45-81710 shall be provided. This clock, a spring-driven chronometer, shall indicate time of day, elapsed tine from launch, retrograde initiation time, and time remaining until retrograde initiation. A time zero reference shall be established in the clock at liftoff. The...

Ie A

3.14.6.2 BICONE ANTENNA - The bicone antenna shall operate during pre-launch, launch, orbit, and re-entry phases of the mission. This antenna shall be incorporated in, and Jettisoned with, the communications antenna assembly see Paragraph 3.5.6 . Through a multiplexing system, the HF and UHF orbital voice communications, the command receiver and the telemetry transmitter shall utilize the bicone antenna. 3.14.6.2.1 MULTIPLEXER - A multiplexer shall be provided to permit simultaneous or...

Revised qA

___ fy OTTVBtttyprm MOOCL Mercury Spacecraft 3.14.1.2 ASTRONAUT'S HEADSET MICROPHONE ASSEMBLIES - Two headset microphone assemblies shall be available for astronaut use. One assembly shall be contained in the astronaut's helmet, and shall be connected to the communications system through the applicable suit connector. Transmitter keying shall be accomplished by and or automatic circuits in the spacecraft. This assembly shall be used from pre-launch through landing. The second headset microphone...