| Objectives |
| Develop the engineering technology for spacecraft environment control, power conversion, attitude control, and communications to deliver scientific equipment in support of subsequent lunar and planetary missions. Produce scientific, engineering, and environmental data associated with deep space trajectories. |
Collect gamma-ray data both in flight and at the vicinity of the moon; obtain lunar surface photographs; transmit, after landing, lunar seismic and temperature data; experiment with trajectory error correction and terminal attitude maneuver; continue the development of basic spacecraft technology; perfect sterilization techniques. |
Obtain television pictures of the lunar surface for the benefit of the scientific program and the U.S. manned lunar program. Pictures to be at least an order of magnitude better in resolution than any available from earth-based photography. |
| Spacecraft description |
| Hexagonal magnesium frame base, 1.5-m diameter. Two trapezoidal solar panels, diametrically opposed, hinged to base; full span 5.2 m. Magnesium vertical supports connected together with A.1 angles and tubes supporting superstructure containing scientific experiments and omni-antenna. Pointable high-gain antenna hinge-mounted to base. Attitude control jets mounted to base of frame. Overall height, 3.6 m. |
Hexagonal magnesium frame base, 1.5-m diameter. Two trapezoidal solar panels, diametrically opposed, hinged to base; full span 5.2 m. Magnesium vertical supports connected together with magnesium angles and tubes. Block I superstructure replaced by lander capsule and equipment for gamma-ray and vidicon; omni-antenna atop capsule. Pointable high-gain antenna. Radar altimeter antenna. Midcourse propulsion in center of space frame. Retro- rocket in capsule assembly. Attitude jets on base of frame. Overall height, 3.6 m. |
Hexagonal aluminum frame base, 1.5-m diameter. Two rectangular solar panels, diametrically opposed, hinged to base, full span 4.6 m. Television cameras mounted directly above base structure, with body-fixed optical axis. Pointable high-gain antenna hinge-mounted to base. Omni- directional low-gain antenna mounted at apex of superstructure. Midcourse propulsion located in center of hexagonal structure. Attitude control jets mounted to base of frame. Overall height 3.6 m |
| Weight, kg (lb) |
| Structures/mechanisms |
60.8 |
| Electrical (RF, TM, data) |
27.0 |
| Power |
105.0 |
| Attitude control (inert) |
11.0 |
| Controller-timer |
4.4 |
| Cabling |
33.4 |
| Friction experiment |
9.5 |
| Science (bus) |
51.2 |
| Expendables |
4.4 |
| Allowable launch weight |
306.7
(674.7) |
|
| Structures/mechanisms |
36.5 |
| Electrical (RF, TM, data) |
34.6 |
| Power |
42.5 |
| Central computer |
5.3 |
| Attitude control (inert) |
17.3 |
| Cabling |
19.5 |
| Propulsion (inert) |
10.9 |
| Lunar capsule system |
148.3 |
| Science (bus) |
13.7 |
| Expendables |
7.6 |
| Average allowable launch weight |
336.2
(739.6) |
|
| Structures/mechanisms |
43.0 |
| Electrical (RF, TM, data) |
26.2 |
| Power |
57.8 |
| Central computer |
4.4 |
| Attitude control (inert) |
25.9 |
| Cabling |
15.6 |
| Propulsion (inert) |
10.4 |
| Television system |
173.0 |
| Expendables |
12.4 |
| Allowable launch weight |
368.7
(811.1) |
|
| Control |
- 10 N2 jets
- 3 gyros
- 2 primary sun sensors
- 4 secondary sun sensors
- 1 earth sensor
|
- 10 N2 jets
- 3 gyros
- 2 primary sun sensors
- 4 secondary sun sensors
- 1 earth sensor
|
- 12 N2 jets
- 3 gyros
- 2 primary sun sensors
- 4 secondary sun sensors
- 1 earth sensor
|
| Electrical power |
- 4340 Si solar cells/panel (2)
- Panels: 26.7 x 74.4 x 184.4 cm
- Total area: 1.8 m2
- 78.5 to 97 max. w/panel
- Ag-Zn battery, 9000 Wh
- Ag-Zn battery, 10 Wh
- Note: no recharge capability for batteries
|
- 4340 Si solar cells/panel (2)
- Panels: 26.7 X 74.4 X 184.4 cm
- Total area: 1.8 m 2
- 78.5 to 97 max. w/panel
- Ag-Zn battery, 1000 Wh
- Note: battery rechargeable
|
- 4896 Si solar cells/panel (2)
- Panels: 73.9 X 153.7 cm
- Total area: 2.3 m2
- 100 w/panel
- Ag-Zn battery, 1000 Wh (2) S/C
- Ag-Zn battery, 1200 Wh (2) TV
|
| Telecommunication |
- 3-W L-band transponder
- 250-mW transmitter
- Quasiomnidirectional low-gain antenna, parabolic high-gain antenna
- Engineering data: 2 subcarriers, analog commutated, 1 sample per sec
- Science data: 4 binary, 2 analog and 1 special subcarrier
|
- 3-W L-band transponder
- 50-mW L-band capsule transmitter
- Quasiomnidirectional low-gain antenna
- 9 data subcarriers, analog commutated, sample rates of 0.1, 1.0 and 25 samples/s 2.5 and 25 bps. Video data at 2 kHz
|
- 3-W L-band transponder
- 60W L-band TV transmitter
- Quasiomnidirectional low-gain antenna, parabolic high-gain antenna
- Engineering data: 1 binary and 7 analog, commutated at 25., 1.0, 0.1 and 0.01 sample/s
- TV data: 1 analog, commutated at 1 sample/s
|
| Propulsion |
| None |
- Monopropellant hydrazine
- 222-N thrust
- ΔV = 0.03 m/s to 43.9 m/s
- Isp = 230 s
- Total impulse = 14,000 N-s
- 4 jet-vane vector control
|
- Monopropellant hydrazine
- 224-N thrust
- ΔV = 0.03 m/s to 60 m/s
- Isp = 230 s
- Total impulse = 23,500 N-s
- 4 jet-vane vector control
|
| Command |
RTC-3 at 1 bps
SC-10 |
RTC-7 at 1 bps
SC-6 |
RTC-8 at 1 bps
SC-6 |