R

2.9.4.4.16 ASC HI REG Caution Light. (See O, figure 2. 9-1 ) The ASC HI REG caution light goes on if the helium pressure downstream of the regulator , in the ascent helium lines exceeds 219. 5 psia. A CWEA comparator detects a malfunction signal and causes the ASC HI REG caution light to go on. The light goes off when nominal pressure is restored. The remedial action, in the event of a malfunction, is to set the ASCENT He REG 1 and REG 2 switches to CLOSE. This closes ascent regulator solenoid...

AGS

Selects inputs for FDAI and X-pointer indicator. Shaft and trunnion angles from the RR are displayed by pitch and yaw error needles of FDAI LOS azimuth and elevation rates arc displayed on X-pointer indicator (illuminating LOS AZ and LOS ELE V). Vehicle attitude errors (PGNS or AGS as selected with ATTITUDE MON switch), arc displayed by FDAI error needles. Forward and lateral velocities from the LR (PGNS or AGS as selected with MODE SEL switch) are displayed on the X-pointer indicator...

Alm

Station rence Measurements X axis d ign r f r nc* point kwt at +200.000. X axis d ign r f r nc* point kwt at +200.000. Figure 1-4. Station rence Measurements 1.2.2.1.1 Control and Display Panels. (See figure 1-7.) The crew compartment has 12 control and display panels two main display panels (1 and 2) that are canted forward 10 , two center panels (3 and 4) that slope down and aft 45 towards the horizontal, two bottom side panels (5 and 6), two lower side panels (8 and 12), one...

Info

84 watts, momentarily during battery switching 10 watts, steady-state 84 watts, momentarily during battery switching 20 watts, steady-state 2. 5. 6 OPERATIONAL LIMITATIONS AND RESTRICTIONS. The operational limitations and restrictions for the EPS are as follows When EPS batteries are in use, the primary glycol cooling loop (ECS) must be operating. If this restriction is not observed, EPS components will be damaged. The only deviation to this is at low power levels (200 watts or less) then...

Mike Filter Bypass Mike Filter Bypass Mike Signal Return

EMU Electrical Connectors The EVCS consists of a pair of extravehicular communicators (EVC-1 and EVC-2), which are an integral part of the PLSS. The EVC-1 consists of two AM transmitters, two AM receivers, one FM receiver, signal-conditioning circuits, a telemetry system, a warning system, and other components required for system operation. The EVC-2 is similar to the EVC-1, except that it has an FM transmitter instead of an FM receiver. Each EVC is controlled with a...

Roll And Yaw Pivotal Points

ACA - Angular Displacements The other set of contacts sends a proportional secondary voltage to the LGC or the ATCA. The output gradient voltages are 0. 28 volt degree of displacement (1 to 11 ). Positive rotation commands generate in-phase voltage negative commands, 180 out-of-phase voltage. During attitude control (ATTITUDE CONTROL . ROLL, PITCH, or YAW switch set to MODE CONT) when the minimum pulse mode is selected via the DSKY and the PGNS is in control, the LGC common...

Operational Limitations And Restrictions

The operational limitations and restrictions for the EDS are as follows The landing gear legs must be deployed before the descent engine is fired. In the stowed position, the legs are in the path of the descent engine plume descent engine firing would damage them. The ASCENT He PRESS switch should not be actuated longer than 24 hours before termination of ascent engine operation. The ascent pressurization valves are designed to operate for only 24 hours after exposure to propellant vapors....

Typical For All Cards

Typical Analog Multiplexer Driver Card - Simplified Logic Diagram During a 39-microsecond sampling period, the capacitor is charged to the PAM analog input voltage from the high-speed gates. At the end of 39 microseconds, the sampling gate is disabled and the capacitor voltage appears at the output of the sample-and-hold output buffer. Sample-and-hold commands from the programmer, coincident with the buffer output, initiate successive approximation cycles. The timing generator is...

Lmalm Apollo Operations Handbook Controls And Displays

Connects CDU neu Ihix lo neg xlunnr bus for t.M ground No loss of function relay contacts In inrallcl with cb IVr from CUH bus to low- and high-voltage coils in kca No. 1 ft > thru III vol.tatsk i i.mv voi.taok sw Pwr lo des bals Iv hv off ft dea< lface relay rc.set for abort sLige ltc< Kindant cb on I.MP panul .supplies pwr (rom I.Ml bus IVr from CDU l*ia to pwr supplies of both dea KCA' 9 (or cuv Vuni C i'vvovae cu rient ind ft O C protection Redundant cb on I.MI jxinel .supplies pwr...

Uao

Prpint vlvs ils of sys B TCA BSC) prim auto ont of lad 2 hardover, act. ft *X-oot av U cot ) Pwr to prpint viva prim colla of sy B quad 3 TCA (B3A ft B3D) Loa a of prim auto ft man cont of aya B quad 3 TCA'a (hardover, AGS direct, It *X-tranal cont avail thru sec colls) Pwr to prpint viva prim colls of sys B quad 4 TCA (B4F ft B4U) Loss of prim auto ft man cont of sys B quad 4 TCA's (hardover. AGS direct. It +X-transl cont avail thru sec coils) Pwr to prpint crossfeed vlvs thru CRSFD aw Cannot...

To Cabin Pressure Switch

Cabin Repressurization and Emergency Oxygen Valve - Functional Schematic maintain cabin pressure at 3. 5 psia for at least 2 minutes, allowing the astronauts to return to a closed-suit environment. The valve is controlled by a three-position handle on the oxygen control module. When the AUTO position is selected, valve operation is controlled by the solenoid, which is actuated by the cabin pressure switch. If cabin pressure drops below normal, the cabin pressure switch energizes...

Antenna

The RR modulates its transmitted 9832. 8-mc signal with range tones. The transponder demodulates the RR-transmitted signal and modulates its 9792-mc (plus Doppler) signal with the range tones phase-coherent with the range tones present on the received RR-transmitted signal. The transponder signal is received by a four-port feedhorn. The feedhorn, arranged in a simultaneous lobing configuration, is located at the focus of a Cassegrainian antenna. (See figure 2.2-3.) If the...

M

ACA Manipulations 2.1.1. 3. 2 Thrust Translation Controller Assemblies. (See figure 2.1-10.) The TTCA's control LM translation in any axis they are functionally integrated translation and thrust controllers. The astronauts use these assemblies to command vehicle translations by firing RCS thrusters and to throttle the descent engine between 10 and 92. 5 thrust magnitude. The controllers are three-axis, T-handle, left-hand controllers, mounted with their longitudinal axis...

Severance

Explosive Devices Subsystem - Overall Block Diagram EDS relays are actuated by 28 volts dc received through the Commander's and LM Pilot's buses of the Electrical Power Subsystem (EPS). Contacts of these relays route ED battery current to associated explosive devices in the Main Propulsion Subsystem (MPS) and the Reaction Control Subsystem (RCS) and to explosive devices that enable landing gear deployment, interstage structural connection separation, electrical circuit...

Rsd

Alternative two-jet policies when a P rotational jet fails. **If one U or V rotational jet fails, the other jet completes rotation. Alternative two-jet policies when a P rotational jet fails. **If one U or V rotational jet fails, the other jet completes rotation. Solenoid Driver Preamplifiers and Jet Solenoid Drivers. Thirty-two solenoid driver preamplifiers accept pulsed inputs from the 16 PRM outputs when the AGS is used or from the 16 PGNS outputs when the primary guidance mode is used....

Gyro Touque Signals

Inertial Subsection - Functional Diagram 2.1.4.1.1 Navigation Base. (See figure 2.1-23.) The navigation base is a lightweight mount that supports, in critical alignment, the IMU, ASA, and AOT. It consists of a center ring with four legs that extend from either side. The IMU is mounted to the ends of one side of the four legs. The AOT and the ASA are mounted to the opposite ends of the legs. The navigation base is bolted to thf LM structure above the astronauts' head, with three...

Nvf

And explosive blade charge generates a shock wave that drives the cutting blades through the interstage umbilical. The blades sever the umbilical, cutting all electrical wires, the descent water tank supply hardline, and the waste management hardline between the ascent and descent stages. Loss of the ascent water tank supply is prevented by check valves in the ascent stage plumbing. Reaction time for cutter assembly operation is approximately 5 milliseconds, after 3. 5 amperes (minimum) of...

Radar Subsystem

Filter assures that AGC response is mostly determined by the received signal level. The AGC loop maintains the 6.8-mc receiver output signal constant despite the va 'ion of the signal input from the RR. Carrier Lock Loop Subassembly. The acquisition logic and sweep generator circuit produces a sawtooth output, which sweeps the VCO linearly with time. By use of a difference amplifier, the lock-up and threshold detector compares the respective signal power of a 6.8-mc wide-band (100 kc) signal...

Vac

Helium flows into the top of the fuel and oxidizer tanks. Diffusers at the top of the tanks uniformly distribute the helium throughout the ullage space. The outflow from each propellant tank divides into two paths. In the primary path, each propellant flows through a trim orifice to the propellant filter in the engine assembly, and then to the isolation and bipropellant valve assemblies (propellant shutoff valves). The trim orifice provides an engine interface pressure of 170 psia for proper...

P

2.9.4.5 Data Storage Electronics Assembly. (See figure 2. 9-16.) The DSEA is a single-speed, four-track, magnetic-tape recorder that stores voice and time-correlation data (TCD) (mission elapsed time). A maximum of 10 hours of recording time is provided (2. 5 hours on each track) by driving the tape in one direction over the record head and, on completion of a pass, switching to the next track and reversing tape direction. The tape is supplied in a magazine, consisting of a supply reel and...

Pgns Pgns Pgns Pgns Pgns Pgns

PART PRESS C02 indicator (7M1) PGNS MODE CONTROL switch (11S24) IMU OPR circuit breaker (4CB124) IMU STBY circuit breaker (4CB161) LDG RDR circuit breaker (4CB105) LGC DSKY circuit breaker (4CB122) RNDZ RDR RDR circuit breaker (4CB29) SIG STR DISP circuit breaker (4CB154) PITCH control (14B2) PITCH indicator (14M3) PLSS FILL valve (7H4) POWER TEMP MON selector switch (4S15) PRE AMPS caution light (6DS30) PRESS indicator (10M3) PRESS indicator power failure indicator (16DS90) PRESS indicator...

Thrust Chamber Assembly Cluster

Reaction Control Subsystem - Component Location propellants are blocked by normally closed fuel and oxidizer valve assemblies until a thruster-on command is issued. As the selected TCA receives a thruster -on command, its fuel and oxidizer valve assemblies open to route the propellants through the TCA injector into the combustion I chambers, where they impinge and ignite. Switches on panel 2 (LGC THRUSTER PAIR CMOS) generate signals for the LGC, telemetry, and caution and warning...

Vent Overboard

Water Management Section - Simplified Functional Flow Diagram The primary coolant loop is char . - with coolant at GSE fill points and is then sealed. The glycol pumps force the coolant through the loop. The glycol accumulator maintains a constant head of pressure (5.25 to 9 psia, depending on coolant level) at the inlets of the primary loop glycol pumps. Coolant temperature at the inlets is approximately +40 F. A switch in a low-level sensor trips when only 10 5 of coolant volume...

Des Hover

Enables LGC to position I.R antenna as function of mission phase. Drives antenna to first position used before hover point. Drives antenna to its second position for final landing phase. Because antenna cannot be driven to its first position by LGC and it is necessary to check out completely two-position capability and provide override of position drive signal if I.R antenna interface fails, DES and HOVER positions are used.

S

TTCA - Angular Displacements Figure 2.1-42. TTCA - Angular Displacements provide a discrete to the LGC when the astronaut operates the TTCA 0. 25 inch out of its detent (neutral) position. The discrete commands the LGC to issue translation change commands in accordance with the TTCA motion. When the AGS is controlling the vehicle, the limit switches issue on and off translation commands directly to the RCS jet logic and driver circuitry. The nonlinear potentiometer provides an...

Primary Waterglycol

Cessna 177 Problems

SENSE LINES TO ' H20 PRESSURE c REGULATORS Figure 2. 6-6. Atmosphere Revitalization Section - Simplified Functional Flow Diagram Figure 2. 6-6. Atmosphere Revitalization Section - Simplified Functional Flow Diagram the lights go on and switchover to fan No. 2 is required. The ECS caution light goes off when No. 2 fan is selected and the SUIT FAN warning light goes on. The SUIT FAN component caution light goes off when fan No. 2 comes up to speed and builds up normal differential pressure. The...

Internal Vent Outlet

Ascent Propulsion Section - Relief Valve Assembly and four solenoid-operated pilot valve and actuator assemblies. Each bipropellant valve assembly and each isolation valve assembly consists of one fuel shutoff valve and one oxidizer shutoff valve. These are ball valves that are operated by a common shaft, which is connected to its respective pilot valve and actuator assembly. Shaft seals and vented cavities prevent the propellants from coming into contact with each other....

Dge

FDAI 1 switch (9S23) FDAI 2 switch (9S24) Flight director attitude indicator (FDAI) (9M1) Flight director attitude indicator (FDAI) (9MG) FLIGHT DISPLAYS CDR FDAI circuit breaker (4CB97) COAS circuit breaker (4CB188) GASTA circuit breaker (4CB88) MISSION TIMER circuit breaker (4CB159) ORDEAL circuit breaker (4CB227) RNG RNG RT ALT ALT RT circuit breaker (4CB123) THRUST circuit breaker (4CB1G8) CDR X-PNTR circuit breaker (4CB133) FLIGHT DISPLAYS FLIGHT DISPLAYS FLIGHT DISPLAYS FLIGHT DISPLAYS...

Main Overboard Vent

Burst Diaphram Assembly - Functional Schematic Filters at the inlets to the oxygen control module and the PLSS disconnect remove particulate matter from the oxygen. Filtering capability is 18 microns nominal and 40 microns absolute. 2.6.4.2.5 Oxygen Control Module. (See figure 2. 6-2.) The oxygen control module is mounted on the suit circuit package located to the right rear of the LM Pilot's station. It consists of a cast housing that contains filters, a PLSS oxygen shutoff...

Lighting

Interior Lights - Color, Brightness, and Lighting Method (cont) Table 2.10-2. Interior Lights - Color, Brightness, and Lighting Method (cont) Continuous from less than 0.5 foot-lambert Background translucent gray white Legend black with white letters Computer status condition indicator (DSKY and DEDA) Computer caution condition indicator (DSKY) Self-luminous devices (toggle switch tips) Landing-point designator and, docking window reticles Outer window pale green Inner window pale...

Water From Separators

Water Tank Selector Valve - Functional Schematic Figure 2. 6-23. Water Pressure Regulator - Functional Schematic Figure 2. 6-23. Water Pressure Regulator - Functional Schematic The accumulators have a low-level sensor with a switch that trips when only 10+5 of the coolant volume remains. The switch is mounted on top of the accumulator. A tube extending from the top of the accumulator, houses a rod attached to the piston. The switch provides a telemetry signal. The primary...

Tens

Provides slewing function for EVENT TIMER indicator. Slews tens-column digit of SEC columns at rate of two digits per second as long as switch is held in this position. Slews units-column digit of SEC columns at rate of two digits per second as long as switch is held in this position. FLT DISP EVENT TIMER SE FDAI (panel 16)

To Gda To

Descent Engine Control Assembly - Simplified Block Diagram only manual commands are displayed on the THRUST indicator. Manual throttle commands consist of a-c voltages, proportional to the active TTCA X-axis displacement, which are applied to the DECA. The active TTCA always provides at least a 10 command. These commands drive a nonlinear circuit that provides the desired thrust level. With nonlinear thrust levels, more resolution is obtained at the lower levels. (See figure 2....

Xuu

The VHF receiver (figure 2.7-12) is an amplitude-modulation, fixed-tuned, single-conversion superheterodyne receiver that uses carrier-controlled squelch. There are two VHF receivers in the CS. The receivers can receive voice signals at 296. 8 and 259. 7 mc (channels A and B, respectively) and during EVA-programmed missions, biomed and suit data from the EVA via channel B. The frequency of a crystal-controlled-oscillator output is multiplied, and mixed with the received VHF signal in the mixer....

Lowait

Coordinates velocities Vxa, Vya, and Vza. With the velocity frequency trackers locked on, the VDG discretes gate the lateral (Vya) and forward (Vza) velocities, in d-c voltage form, to the X-pointer indicators the altitude rate (Vxa), as a PRF with altitude rate sign sense, to the ALT RATE indicator. The altitude rate sign sense conveys positive or negative Doppler velocity. The VDG discretes also gate the Vxa, Vya, and Vza, as PRF, to the signal data circuits of the signal data range converter...

Diy Barberpole Indicator

Electrical Power Subsystem - Power Interface Diagram (Sheet 3 of 3) A-C power is provided to LM subsystems by either of two identical, redundant inverters it is controlled by the EPS INV 1 and ENV 2 circuit breakers (panel 11 and 16, respectively), the INVERTER switch, and the AC BUS A BUS TIE or AC BUS B BUS TIE circuit breakers on panel 11. The EPS INV 1 or INV 2 circuit breaker supplies 28 volts dc from the LM Pilot's or Commander's 28-volt d-c bus to the chosen normally...

Battery A

Heat Switch Cryogenic

TO LANDING > GEAR EXPLOSIVE DEVICES Figure 2. 8-6. Landing Gear Deployment - Simplified Schematic Diagram 2.8.3.4 Descent Propellant Tank Prepressurization. (See figure 2. 8-8.) An ambient helium isolation valve is used in conjunction with two compatibility valves (each downstream of its respective quad check valve in the descent stage) when prepressurizing the descent propellant tanks. The valves are normally closed. Setting the MASTER ARM switch to ON arms the ED buses momentarily holding...

Oxidizer Flow Throttle Control Valve Valve Actuator

Descent Engine and Head End Assembly The mechanical linkage that connects the pintle of the flow control valves and the injector sleeve is pivoted about a fulcrum attached to the injector body. Throttling is controlled by the throttle valve actuator, which positions the linkage in response to electrical input signals. At maximum thrust, the actuator positions the linkage to fully open the flow control valves and injector apertures. As commanded thrust is reduced, the actuator...

Transfor

The cycle counter is a five-bit counter that controls shift instructions and certain long orders. The counter is loaded from the six least significant bits of the M-register. Operation Code Register. The operation code register is a five-bit static register that is loaded under software-control, from the five most significant bits of the data bus. The register holds the five-bit order code during its execution. Adder. The arithmetic section is designed around an 18-bit,...

Power Limiter Amplifier

S-Band Transmitter - Block Diagram Figure 2. 7-6. S-Band Transmitter - Block Diagram The S-band receivers (figure 2. 7-7) receive voice uplink data and coded PRN signals from MSFN. One receiver serves as backup for the normally used unit. The S-band receivers receive a 2101. 8-mc carrier which is phase-modulated by the 30- and 70-kc subcarriers and the PRN ranging code. The output of the 19-mc VCO is routed through a chain of multiplier stages, where it is multiplied to 2054-3...

Abort Stage

Pwr to cabin pnl, fwd ft ovhd flood Its thru FLOOD sw Pwr to cabin fwd ft ovhd It thru docking hatch sw Pwr to tracking It thru EXTERIOR LTG sw ft tracking It electronics assy Pwr to caut ft warn anun, eng START ft STOP, docking thru EXTERIOR LTG sw, comp caut, ind pwr (all, fa DSKY status Its Pwr to AEA pwr supply for internal use ft DEDA pwr (ENG ARM sw - DES) Pwr to des eng actuator isol vlvs thru DECA relays (ENG ARM sw - ASC) Pwr to AELD to enable asc eng Ignition Pwr to relay drivers for...

Timing Referenc

TIME COUNTER INCREMENTING DECREMENTING PULSES TIMING PULSES (TO ALL FUNCTIONAL AREAS) flight data that are displayed to assist the astronaut during various phases of the mission are as follows total LM attitude, attitude errors, altitude and altitude rate, forward and lateral velocities, and percentage of descent engine thrust commanded by the LGC. Total attitude is generated from the IMU gimbal angles. With the ATTITUDE MON switch (panel 1) set to PGNS, the IMU gimbal angles are routed to the...

Lw

Aerospace Gyroscope Bearings

TOROUE MOTOR DUPLEX BALL-BEARING SLIPRING ( -CONTACT) GYRO ERROR RESOLVER (IX) DUPLEX BALL-BEARING SLIPRING (40-CONTACT) MUITISPEED RESOLVER (IX AND 14X) JORQUE MOTOR DUPLEX BALL-BEARING SUPRING ( -CONTACT) TOROUE MOTOR DUPLEX BALL-BEARING SLIPRING ( -CONTACT) JORQUE MOTOR DUPLEX BALL-BEARING SUPRING ( -CONTACT) GYRO ERROR RESOLVER (IX) DUPLEX BALL-BEARING SLIPRING (40-CONTACT) MUITISPEED RESOLVER (IX AND 14X) TOROUE MOTOR DUPLEX BALL-BEARING SUPRING (40-CONTACT) DUPLEX (ALL-BEARING SUPRING...

Lunar Module Circuit Breakers Panel Diagram

Figur 2. 1 18 Dfflcent Kleine C'iinlrol Schematic (She t l ul 2) GUIDANCE, NAVIGATION, AND CONTROL SUBSYSTEM Djal- r*J_ffbn'r> ' Clu * 1 *Prl' ' 71 Page J. 1-J7 LMA890 3 LM A PO I j I.O OPERATIONS HANDBOOK SUBSYSTEMS DATA Figure 2. 1-18. Desrent Engine Control Schematic (Sheet 2 of 2) Figure 2. 1-18. Desrent Engine Control Schematic (Sheet 2 of 2) GUIDANCE, NAVIGATION, AND CONTROL SUBSYSTEM Mission LM Basic Date 1 February 1970 Change Date I.MA7UU-3-I.M AKJl.l.O OPERATIONS HANDBOOK SUDSYSTEMS...

Purpose Burst Disk In Aerspace Apollo

Each pressure regulator unit consists of a direct-sensing main stage and a pilot stage. The valve in the main stage is controlled by the valve in the pilot stap which senses small changes in the regulator outlet pressure Pr and converts these changes to pre- ionally larr changes in control pressure Pc . The main stage valve poppet is positioned for va flow dem ,ds by changes in the control pressure acting on the main stage piston. A reduction i w demand causes a rise in the regulator outlet...

Highexplosive Charge

Helium Isolation Valves and Compatibility Valves. These valves are similar and operate in the same manner they are used singly or in pairs, depending on the function RCS, ascent, or descent propellant tank pressurization . Each RCS explosive valve is actuated by a single cartridge. Redundant valves are used. Each ascent helium isolation valve and the descent helium and compatibility valves are actuated by two cartridges. One of the two ascent fuel compatibility valves and two ascent oxidizer...

Lmaulm Apollo Operations Handbook Subsystems Data

Ci'iurul I lcctrotiica Sectluii - Suiiilnury gt 1 MikIks ul Auitudf Contrul Tuljle 2.1-1. Ci'iurul I lcctrotiica Sectluii - Suiiilnury gt 1 MikIks ul Auitudf Contrul GUID CONT sw - PGNS ATTITUDt CONTROL ROLL, PITCH, and YAW sw -MODK CONT normally Automatic steering and translation are performed by LGC commands to jet drivers. linear translation of LM by on-and-off firing of ihrusters when TTCA is moved out of delenl Pitch and roll gimbal commands from LGC applied to Dt'.CA All...

Deadface

Enables interruption of power from descent batteries to ascent stage. Applies power from descent batteries to ascent stage. Retains status of last initiated switch position. Energizes deadface relays, isolating descent batteries on ascent stage side of staging guillotine. EPS ASC ECA CONT panel 11 and or panel 1G Switch is level locked to center position. Momentary actuation of switch sets latching relays in descent ECA's. Descent batteries are normally connected to ascent stage. DES BATS gray...

LM

When the SIDE PANELS switches are set to OFF, the Commander's and LM Pilot's side panel integral lighting is interrupted. Setting the FLOOD toggle switch panel 3 to ALL routes 28 volts dc to the Commander's and LM Pilot's overhead and forward floodlights and to their side panel floodlights. The OVHD FWD FLOOD dimming controls panels 3 and 5 adjust the intensity of the LM Pilot's and Commander's respective overhead and forward floodlights. There is no intensity control for the side panels....

Probe

The upper end of the primary strut attaches to the descent stage outrigger fitting the lower end has a ball joint support for the footpad. Crushable aluminum honeycomb inside the primary strut is used as the shock-absorbing medium. The primary strut absorbs compression loads only. The footpad assures minimal penetration of the lunar surface. It has a diameter of 37 inches and can pivot at the end of the primary strut. A lunar-surface sensing probe is attached to each footpad except the forward...

ERA

Environmental limits Vibration Acceleration Shock Temperature Operating Nonoperating D-C amplifiers Inputs Bipolar mode Output AC-to-dc converters Input frequency Output Analog signal isolating buffer Input Output An efficient thermal path exists between heat-producing sources within subassemblies and an external heat sink. lt l f to 13 0 F -65 to 160 F 0 to 200 millivolts dc and 0 to 5 volts dc -100 millivolts to -2. 5 volts dc and 100 millivolts to 2. 5 volts dc 0 to 5 volts dc four single...

Tca

Cant angle data are used by AEA to account for canted thrust direction. The X, Y, Z thrust chamber assemblies assumed to thrust along X-, Y , Z-body-axes, respectively. Before in-orbit maneuvers, the astronauts choose which TCA s will be used. The AGS must be informed, via the DEDA, of the decision to fire the ascent engine, so that steering transients will not occur at the start of the burn. Before AGS-controlled orientation to the desired thrust attitude, the following DEDA selection...