1. Mission Objectives

Mars 2MV-3 No.1 was the first mission of the second generation of Soviet Mars probes (2MV), specifically designed as a lander. Its objectives were:

Engineering:

• Validate the 2MV spacecraft platform (orbital module and lander).
• Test the ignition of the escape stage (Blok-L) from a terrestrial parking orbit for trans-Mars injection (TMI).
• Execute the first deep-space trajectory correction maneuver (TCM).
• Test the atmospheric entry, descent, and landing (EDL) system on Mars.

Scientific:

• Achieve the first soft landing on the Martian surface.
• Transmit data on surface conditions (pressure, temperature).
• Measure radiation and magnetic fields during interplanetary cruise and on the surface.

2. Probe Specifications (Platform 2MV-3)

The spacecraft was a two-component design consisting of an orbital module (cruise stage) and a landing module (ALS - Automatic Landing Station).

• Total Mass: Approx. 890 kg
• Orbital Module (Cruise Stage): Acted as the carrier vehicle. It provided power (solar panels), attitude control (sun/star sensors, gas thrusters), communications, and the trajectory correction engine (KDU).
• Landing Module (ALS): A spherical capsule of ~1 meter in diameter. It contained the scientific instruments, communication system, and batteries. It was designed to separate from the orbital module before arrival and perform a direct atmospheric entry. The landing design likely combined a heat shield, a parachute, and a retrorocket or an impact-damping system.

3. Scientific Instrumentation (Planned for Lander)

The instrument package was focused on survival and basic surface analysis:

• Atmospheric Sensors: To measure pressure and temperature during descent and on the surface.
• Magnetometer: To search for a local magnetic field.
• Radiation Counter (Cosmic Ray Detector): To measure the radiation environment.
• Surface Instruments: Possibly a basic TV camera or a spectrometer (exact payload details for this failed mission are scarce).

4. Launch Vehicle and Escape Stage

The four-stage Molniya 8K78 launcher was used. This vehicle was necessary to send such a large mass beyond Earth orbit.

• Stages 1 & 2: Core configuration (Blok-A) and four boosters (Blok B, V, G, D) of the R-7.
• Stage 3 (Blok-I): An upper stage designed to operate in vacuum and insert the payload into the parking orbit.
• Stage 4 (Blok-L): The critical escape stage. Designed to ignite in LEO and provide the final impulse for trans-Mars injection.

5. Launch Failure Analysis

1. Initial Sequence: The launch on November 4, 1962, proceeded nominally. Stages 1, 2, and 3 (Blok-I) functioned correctly, placing the Mars 2MV-3 No.1 probe and the Blok-L escape stage into the planned low Earth parking orbit (LEO).
2. Failure Event: The Blok-L stage, which was supposed to ignite for trans-Mars injection, failed to start its engine.
3. Root Cause: Post-flight analysis (based on telemetry from the sister mission failure, Sputnik 22) indicated that strong resonant longitudinal vibrations (Pogo oscillations) during the operation of the third stage (Blok-I) caused critical damage to the systems of the fourth stage (Blok-L).
4. Failure Result: The damage prevented the ignition of the Blok-L engine. This could have been due to a failure in the turbopump control system, the pyrotechnic ignition system, or the guidance avionics.
5. Orbital Decay: Unable to escape Earth's gravity, the spacecraft (now designated "Sputnik 24" by NORAD) was stranded in LEO. It disintegrated in Earth's atmosphere approximately two and a half months later, on January 19, 1963.

6. Technical Conclusion

The Mars 2MV-3 No.1 mission was a launch failure, specifically a failure of the escape stage. The mission failed to leave Earth orbit. The failure, along with that of the Sputnik 22 (Mars 2MV-4) flyby attempt just 11 days earlier, revealed a fundamental design flaw in the Molniya launcher (third-stage Pogo vibrations). This led to a redesign of the vehicle, but the 1962 launch window was entirely lost.