Pioneer Venus: Mission Characterization - Dr. Andrew Ketsdever Lesson 2 AME 5595
←
→
Page content transcription
If your browser does not render page correctly, please read the page content below
Pioneer Venus: Mission
Characterization
Dr. Andrew Ketsdever
Lesson 2
AME 5595
Background
• Pioneer Venus evolved from
recommendations from the Space Science
Board of the National Academy of
Sciences
– “Need” for relatively low-cost orbiters and
landers to explore the planet Venus
– Earth’s closest neighbor, yet relatively little
was known (especially about the lower
atmosphere)
– What was known raised many scientific
questions
Background
– What was known
• Planet is covered with clouds
• Atmosphere primarily CO2 (Traces of sulphuric acid)
• Surface pressure is 95 Earth atmospheres
• Surface temperature is 493 ºC
– Questions
• “Why do two planets with about the same mass, probably
formed out of similar materials and situated at comparable
distances from the sun, have atmospheres that evolved so
differently?”
• “Why is the surface of Venus baked by a searing heat, while
Earth is not?”
– Answers to these questions should enhance knowledge
of Earth’s atmosphere and weather
• Venus represents a relatively simple weather “machine” absent
of the influence of oceans
Subject: Venus
• Diameter: 12,100 km (⊕ 12,745km)
• Mass: 0.81 M ⊕
• Density: 5.26 g/cm3 (⊕ 5.5 g/cm3)
• Mean Orbital Radius: 108.2 Million km
• Orbital Period: 224.7 days
• Rotation: Once per 243.1 days
• Clouds rotate in about 4 days (at the top)
• Rotation is retrograde
– Opposite to direction that planet travels around sun
– One day is 117 Earth days
– Only 6º tilt of axis with respect to its orbital plane
• Minimum energy launch opportunities come every
584 days
Subject: Venus • Surface Pressure – 95 ⊕ Atm – 9,616 kPa • Surface Temperature – 750 K – 480 ºC • Albedo – 1.82 ⊕ • Nearly 1.98 ⊕ solar intensity • Similar atmospheric absorption of solar energy
Mission Objectives
• Subject: Characterization of the atmosphere,
ionosphere, and surface of Venus
• Objectives
– Determine the composition of the clouds
– Determine the composition and structure of the
atmosphere from the surface to high altitude
– Determine the composition and structure of the
ionosphere
– Determine the characteristics of the surface on a
planetary scale
– Investigate the interactions of the magnetic field and
the solar wind
– Investigate the planet’s gravitational field harmonics
Mission Concept
• Two spacecraft
– Orbiter
• Spacecraft subsystems
• 12 scientific instruments (payloads)
– Multi-probe
• Spacecraft bus
• 3 small probes
• 1 large probes
DRIVER: Determine the composition and structure of the
atmosphere from the surface to high altitude
Mission Details
• Pioneer Venus 1 (Orbiter)
– Launched 20 May 1978
– Atlas SLV-3D/Centaur
– Planet Arrival 4 Dec 1978
• Pioneer Venus 2 (Multi-
Probe)
– Launched 8 Aug 1978
– Atlas SLV-3D/Centaur
– Planet Arrival 9 Dec 1978
(Probes)
PV1: Orbit Details
• Type II Interplanetary Trajectory
– Travels more than 180º around the sun
– Used to reduce the spacecraft’s velocity upon arrival
at Venus
– Less propellant required (180kg propellant used –
545 kg total spacecraft mass)
– Travel of 480 million km, in 7 months
• Venus Orbit
– 28 sec burn of solid propellant motor
– Elliptical (300 km periapsis / 66,000 km apoapsis)
– 24 hr period
– 75º inclination
– Later: Periapsis commanded to 150 km
PV1: Interplanetary Orbit
PV1: Venus Orbit
PV1: Venus Orbit
PV1: Orbit Details
PV2: Orbit Details
• Type I Interplanetary Trajectory
– Travels less than 180º around the sun
– Launched a few days after PV1 crossed back
inside Earth’s orbit
– 4 month trip time
– Arrival speed at Venus 19,500 km/hr (5.4
km/s)
– 24 days to Venus: Large probe released
– 20 days to Venus: Small probes released
– Bus re-entry in Venus atmospherePV2: Interplanetary Orbit
PV2: Orbit Details
PV2: Orbit Details
The Spacecraft
• Built by Hughes “Aircraft” Company
• Project was managed by NASA Ames RC
– Expertise
• High velocity (hypersonic) flight dynamics
• Re-entry
• Planetary atmosphere sensing (Earth demonstrations)
• We will look at some of the design specifics
– Orbiter (PV1)
• Accomplish retro-fire at Venus to achieve specified orbit
• Accommodate 47.6 kg of scientific payloads
• Support dual frequency (S and X bands) for occultation exp
– Multiprobe (PV2)
• Mechanically and electrically support probes (1 large / 3 small)
• Target and release probes at Venus
• Accommodate 57.6 kg of scientific payloadsThe Orbiter (PV1)
• Requirements
– Return data for 243 days in Venus orbit
– Spin stabilization
• Disk shape
• Mass concentrated at perimeter (Iz/Ip = 1.2)
– Solar thermal environment of up to 2 ⊕
– Instrument pointing requirements ~0.2º accuracy
– Atlas / Centaur upper stage
• Limited mass (587.4 kg completion / 523 kg inception)
• 15g max vibration load
• Fundamental frequency >4Hz
• Shroud constrained dimensions
• Clamping arrangement (LV interface)The Orbiter (PV1)
• Spacecraft element
– Spacecraft bus (subsystems)
• Six basic assemblies
– Despun antenna assembly
– Bearing and power transfer assembly (slip ring) and support
structure
– Equipment shelf
– Solar panel
– Orbit insertion motor
– Thrust tube
– 12 scientific instruments
• Mounted on periphery of equipment shelf to provide adequate
viewing angles
• Many instruments required diamond and sapphire windows
• Isolated from spacecraft contaminants
– For example, magnetometer is mounted at the end of a 15.7 ft.
boom to isolate it from the spacecraftOrbiter (PV1)
Orbiter
Orbiter
• Spin-stabilized
platform
• Flat Cylinder
– 2.5 m diameter
– 1.2 m high
• Despun antenna
– 1.09 m diameter
– High gain, parabolic
– S and X band
operationPayloads
• 12 scientific instruments
– Cloud Photopolarimeter (OCPP)
• Measure vertical distribution of cloud and haze particles
• 5 kg, 5.4W
• 3.7 cm aperture telescope with filter wheel
– Surface Radar Mapper (ORAD)
• Produce first maps of large areas of Venus not observable from
Earth
• 9.7 kg, 18W
• 150 m resolution
– Infrared Radiometer (OIR)
• Measure infrared radiation emitted by the atmosphere at various
altitudes
• 5.9 kg, 5.2W
• Determine where maximum deposition from solar energy is locatedPayloads
– Airglow Ultraviolet Spectrometer (OUVS)
• Measure UV light scattered or emitted by clouds
• 3.1 kg, 1.7W
• Airglow is the absorption of UV light by gases in the upper
atmosphere
– Neutral Mass Spectrometer (ONMS)
• Measure neutral atom and molecular densities
• 3.8 kg, 12W
• Vertical and horizontal distribution of neutral gases
– Solar Wind Plasma Analyzer (OPA)
• Measure properties of the solar wind at Venus (density, velocity, flow
direction, temperature)
• 3.9 kg, 5W
• Electrostatic energy analyzer
– Magnetometer
• Investigate weak magnetic field of Venus
• 2 kg, 2.2W
• Weak magnetic field may play an important role in solar wind
interactionsPayloads
– Electric Field Detector (OEFD)
• Measure electric fields of plasma waves and radio
emissions from 50-50,000Hz
• 0.8 kg, 0.7W
• Answer questions about how the solar wind is deflected
around Venus
– Electron Temperature Probe (OETP)
• Measure thermal characteristics of ionosphere
• 2.2 kg, 4.8W
• Electron temperature, density and spacecraft potential
– Ion Mass Spectrometer (OIMS)
• Measure distribution of charged particles in the atmosphere
• 3 kg, 1.5W
• Positive charge distribution and concentrations
– Charged-Particle Retarding Potential Analyzer (ORPA)
• Measures the energy of ions in the ionosphere
• 2.8 kg, 2.4W
• Velocity, temperature and concentration of most abundant ion species
– Gamma Ray Burst Detector (OGBD)
• Measure gamma ray bursts from outside the solar system
• 2.8 kg, 1.3W
• Gamma ray energies from 0.2 to 2 MeV
– Radio Science Experiments
• Occultation of X and S bands (atmosphere)
• Doppler shifts (spacecraft accelerations)Spacecraft Configuration
Attitude Determination and Control • Shape and weight distribution conform to basic mechanical requirements for a spin stabilized vehicle – Roll-to-Pitch Ratio greater than one • Attitude determination – Dual slit sun sensor (x3) – Star sensor • Propulsion provided control – Spin rate – Attitude control – Orbit insertion
Attitude Control Thrusters
Propulsion
• Attitude control
– 7 total thrusters
• Liquid monopropellant hydrazine (N2H4)
• 23.78 kg of propellant required (spin, despin, orientation)
• Catalytic decomposition
• 4.45 N of thrust (each)
• Blow-down mode
• System
– Tanks and Pressurant (He)
– Resevoir (60 sec of propellant – 5 sec of spin up thrust
required)
– Filters
– Feedlines
– Heaters (to prevent freezing)
– Valves
– Thrust chamber
– NozzlePropulsion
Propulsion
• Orbit insertion
– 1 thruster
• Solid propellant
• 18000 N of thrust provided
• ∆V ~ 1.05 km/sec
– System
• Tank
• Insulation
• Safe and arm unit (igniter)
• NozzlePower
• Requirements
– 305.1W (EOL) at Venus
– 28V bus (30V max)
• 432 W-hr stored batter energy
– Two, 24 cell 7.5 A-hr NiCd batteries
• Launch
• Eclipse
• Periapsis (high temperature)
• Solar Arrays provided power in sunlit portion of orbit (7.4 m2)
– More efficient cell identified then baselined in CDR
• Mass savings of over 10 kg
• $12K/kg cost for weight savings
• Better resistance to high temperature degradation
• Better resistance to radiation degradation
• High reliability with either cell
• Assembly time is the same
• New cells are more easily replaced
– Interconnects had to be shielded from ambient plasma environmentPower
Thermal
• Up to 1.98 Earth solar intensity
• Passive and Active thermal control
techniques utilized
– Insulation Blankets
– Thermal finishes (white paints)
– Power Subsystem heat dissipation to
equipment shelf
– Heaters (propellant)
– Louvers and RadiatorsThermal
Comm and Data Handling • Spacecraft to Earth S-Band Transmitter (2.295 GHz) – Receivers on ground: Deep Space Network – US, Australia, Spain, Guam, Chile Ground Stations • Antenna dish on board – Parabolic, 109 cm diameter – Two additional omni-directional antennas on board (redundancy) – X-band used only for occultation experiments • Twelve telemetry data rates between 8 and 2048 bits/sec available – 1024 bits/sec used during interplanetary travel • Data storage of 524Kb – 1024 minor frames of telemetry – Mostly for occultation (behind Venus) – 26 min occultation implies 1Mb at 672 bits/sec
Operations
• Commands for orbit insertion
sent to spacecraft from the
ground hours before maneuver
– No communication with the
orbiter during or immediately
after the 30 sec burn
– Occultation event
• Each subsequent
occultation event
– Stored commands to
operate instruments
– Store data in memory
– Send telemetry
• Power budgets addressed
by operational and scientific
need
– Periapsis vs. apoapsisThe Multiprobe (PV2)
• Requirements
– Same basic structure as PV1 (for bus)
– Bus spin stabilization
• Disk shape
• House 1 large and 3 small probes near cg plane
– Probes to inner atmosphere and surface
• Not required to survive impact with surface
– Solar thermal environment of up to 2 ⊕
– Bus pointing accuracy for probes and instruments
– Atlas / Centaur upper stage
• Limited mass (905.4 kg completion / 848.2 kg inception)
• 15g max vibration load
• Fundamental frequency >4Hz
• Shroud constrained dimensions
• Clamping arrangement (LV interface)The Multiprobe (PV2)
• Spacecraft element
– Spacecraft bus
• Similar in design to Orbiter
• 2 scientific instruments
• Five basic assemblies
– Large probe support
– Small probe support
– Equipment shelf
– Solar Panel
– Thrust tube
– Large probe
• Released from bus
• Seven scientific instruments
– Three small probes
• Released from bus after large probe
• Three scientific instrumentsMultiprobe (PV2)
Large Probe (Payload)
• The Pioneer Venus large probe was equipped with 7 science
experiments, contained within a sealed spherical pressure vessel.
• After deceleration from initial atmospheric entry at about 11.5 km/s
near the equator on the Venus night side, a parachute was deployed
at 47 km altitude.
• The large probe was about 1.5 m in diameter and the pressure vessel
itself was 73.2 cm in diameter. Pressure vessel was Titanium filled
with 102 kPa of Nitrogen.
• Weight: 315 kg
• The science experiments were:
– a neutral mass spectrometer to measure the atmospheric composition
– a gas chromatograph to measure the atmospheric composition
– a solar flux radiometer to measure solar flux penetration in the
atmosphere
– an infrared radiometer to measure distribution of infrared radiation
– a cloud particle size spectrometer to measure particle size and shape
– a nephelometer to search for cloud particles
– temperature, pressure, and acceleration sensorsLarge Probe
1 – Radio Transparent
Window 4.1
2 – Aft Cover
3 – Antenna
4 – Pressure Vessel
5.2
4.1 – Parachute Tower
5 – Cloud Particle 5.1
Spectrometer
5.1 – Neutral Mass
Spectrometer
5.2 – Solar Flux Radiometer
6 – Deceleration ModuleLarge Probe
Small Probes
• The three small probes were identical
– 0.8 m in diameter, 90 kg
– Spherical pressure vessels filled with
102 kPa of Xenon
– Unlike the large probe, they had no parachutes
– Aeroshells did not separate from the probe
– Instruments
• Nephelometer and temperature, pressure and acceleration sensors, as well as a
net flux radiometer experiment to map the distribution of sources and sinks of
radiative energy in the atmosphere
– The radio signals from all four probes were also used to characterize the
winds, turbulence, and propagation in the atmosphere.
– The small probes were each targeted at different parts of the planet and
were named accordingly.
• The North probe entered the atmosphere at about 60 degrees north latitude on
the day side.
• The night probe entered on the night side.
• The day probe entered well into the day side, and was the only one of the four
probes which continued to send radio signals back after impact, for over an hour.Small Probe 1 – Antenna Housing 2 – Temperature and Pressure Sensors 3 – Deceleration Module (carbon phenolic heat shield) 4 – Hermetically Sealed Container 5 – Nephelometer 6 – Net Flux Radiometer
Probes
Attitude Determination and Control • For the spacecraft bus, the ADCS is similar to the Orbiter • Bus spacecraft had to position itself for Large Probe Release • Reposition itself for release of Small Probes (all three simultaneous) • Final reposition for Bus re-entry • Bus center of mass shifts significantly during these maneuvers
Propulsion
• Attitude control
– Same as for Orbiter with one less thruster
– 6 total thrusters
• Liquid monopropellant hydrazine (N2H4)
• 15.34 kg of propellant required (∆V, spin, despin,
orientation)
• Catalytic decomposition
• 4.45 N of thrust (each)
• Blow-down mode
• No orbit insertion motor requiredComm and Data Handling • Data Handling for Multiprobe was identical to the Orbiter except it had no data storage • Data systems for probes was handled by the individual probes after separation • Two omni-directional and one medium-gain horn antenna were used • During separation and entry into the atmosphere, the DSN communicated with 6 separate spacecraft (Orbiter, Bus, Large Probe, 3 Small Probes) – All spacecraft communicated directly to Earth
Scientific Results
REFERENCES • Fimmel, R., Colin, L., Burgess, E., Pioneer Venus, NASA SP-461, 1983. • Brodsky, R., Pioneer Venus: Case Study in Spacecraft Design, AIAA, 1980. • “Pioneer Venus”, Press Kit, Release 78-68, NASA, 1978. • Venus and Mars: Atmospheres, Ionospheres and Solar Wind Interactions. (edited by J.G. Luhmann, M. Tatrallyay and R.O. Pepin) 225- 236, American Geophysical Union, 1992.
You can also read
