TOPEX/POSEIDON (22076)

COSPAR: 1992-052A | Alt Name: Topex-Poseidon

Image
TOPEX/POSEIDON Satellite Image
Additional Sources
Launch Details

Launch Date

August 10, 1992

Launch Site

FRGUI

Launch Pad

ELA2

Launch Vehicle

Ariane 42P

Orbital Elements

NORAD ID

22076

International Designator

1992-052A

Epoch

Sat, 04 Jul 2026 04:52:54 GMT

Apogee

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Perigee

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Inclination

66.04°

Right Ascension

96.81°

Eccentricity

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Argument of Perigee

269.29°

Period

112.40 min

Mean Motion

12.81 rev/day

Latitude

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Longitude

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Altitude

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Velocity

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Polar Plot
3D Visualization
Basic Satellite Info

Name

TOPEX/POSEIDON

Alternative Name

Topex-Poseidon

Type

Payload

Status

Non-operational

Owner

JPL/CNES

Country

United States

Constellation

N/A

Related Satellites

Major Events

N/A

Latest TLEs
1 22076U 92052A   26185.20341275 -.00000026  00000-0  15073-3 0  9999
2 22076  66.0411  96.8144 0008221 269.2852 255.1375 12.81094383585663

Source: Celestrak

Summary
TOPEX/POSEIDON was an Earth observation satellite launched on August 10, 1992, from ELA2 launch pad at FRGUI using the Ariane 42P launch vehicle. The spacecraft measured 6.6 meters in length and had a diameter of 2.8 meters with a span of 11.5 meters, carrying equipment including NRA, TMR, LRA, DORIS, SSALT, and GPSDR. It operated for over three years beyond its planned lifespan, achieving an operational period of thirteen years. The satellite was jointly owned by JPL/CNES and had a dry mass of 2185 kilograms with a launch mass of 2402 kilograms. Its power source consisted of deployable solar arrays and batteries. The shape of the satellite was described as Box + Box + Pan, with a radar cross-section (RCS) of 7.79 square meters. It was manufactured by FAIR for Earth observation purposes.
Physical Characteristics

Length

6.6

Diameter

2.8

Span

11.5

Dry Mass

2185

Launch Mass

2402

Shape

Box + Box + Pan

Radar Cross Section

7.79

Visual Magnitude

Unknown

Color

Unknown

Material Composition

Unknown

Technical Details

Payload

Topex-Poseidon

Purpose

Earth observation

Mission

Earth observation

Manufacturer

FAIR

Life Expectancy

3 years (planned); 13 years (achieved)

Bus

MMS

Configuration

MMS

Motor

?

Equipment

NRA, TMR, LRA, DORIS, SSALT, GPSDR

Power System

Deployable solar array, batteries

ADCS

Unknown

Transmitter Frequency

Unknown

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