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The InSight mission to Mars launched with a C 3 of 8.19 km 2 /s 2. [5] The Parker Solar Probe (via Venus) plans a maximum C 3 of 154 km 2 /s 2. [6] Typical ballistic C 3 (km 2 /s 2) to get from Earth to various planets: Mars 8-16, [7] Jupiter 80, Saturn or Uranus 147. [8] To Pluto (with its orbital inclination) needs about 160–164 km 2 /s 2. [9]
Deep Space 2 project manager Sarah Gavit with the engineering hardware of the probe. Deep Space 2, also known as "Mars Microprobe," [2] was the second spacecraft developed under the NASA New Millennium Program to flight-test advanced technologies concepts for space missions. The purpose of the program was to do high-risk technology ...
In ballistics, the ballistic coefficient (BC, C b) of a body is a measure of its ability to overcome air resistance in flight. [1] It is inversely proportional to the negative acceleration: a high number indicates a low negative acceleration—the drag on the body is small in proportion to its mass.
First derivative of mean motion; the ballistic coefficient [13]-.00002182 10: 45–52: Second derivative of mean motion (decimal point assumed) [13] 00000-0 11: 54–61: B*, the drag term, or radiation pressure coefficient (decimal point assumed) [13]-11606-4 12: 63: Ephemeris type (always zero; only used in undistributed TLE data) [14] 0 13: ...
The region about a target body where ballistic capture occurs is called a weak stability boundary. [2] The term weak stability boundary transfer is also used, or for short, WSB transfer. In 2014, ballistic capture transfer was proposed as an alternate low energy transfer for future Mars missions . [ 6 ]
This figure is mainly (~7.8 km/s) for horizontal acceleration needed to reach orbital speed, but allows for atmospheric drag (approximately 300 m/s with the ballistic coefficient of a 20 m long dense fueled vehicle), gravity losses (depending on burn time and details of the trajectory and launch vehicle), and gaining altitude.
The peak heat flux experienced by the Viking 1 aeroshell which landed on Mars was 21 W/cm 2. For Viking 1, the TPS acted as a charred thermal insulator and never experienced significant ablation. Viking 1 was the first Mars lander and based upon a very conservative design. The Viking aeroshell had a base diameter of 3.54 meters (the largest ...
Harry Allen and Alfred Eggers, based on their studies of ICBM trajectories, were able to derive an analytical expression for the velocity as a function of altitude. [2] They made several assumptions: The spacecraft's entry was purely ballistic (=). The effect of gravity is small compared to drag, and can be ignored.