Spacecraft components

gas-tight protective suit for astronauts who are in the vacuum of space

thumb|300px|Radar and other avionics in the nose of a Cessna Citation I|Cessna Citation I/SP thumb|right|Republic F-105 Thunderchief|F-105 Thunderchief with avionics laid out

type of spacecraft propulsion that takes advantage of solar radiation

continuously computed dead reckoning

thumb|right|Jewish refugees look out through a porthole of a ship while docked in the port of Haifa, 1950–1959

method used to accelerate spacecraft

device containing volatile liquid in a sealed chamber to transfer heat by conduction and phase transition

component to shield a substance from absorbing excessive heat

system to provide safe egress for crew if a rocket launch fails

part of the International Space Station; sequence of connected trusses

thumb|right|280 px|An airlock on board Space Shuttle Atlantis

Canadarm or Canadarm1 (officially Shuttle Remote Manipulator System or SRMS, also SSRMS) is a series of robotic arms that were used on the Space Shuttle orbiters to deploy, maneuver, and capture payloads. After the Space Shuttle Columbia disaster, the Canadarm was always paired with the Orbiter Boom Sensor System (OBSS), which was used to inspect the exterior of the shuttle for damage to the thermal protection system.

spacecraft propulsion system which uses electricity

joining of two or more spacecraft

right|thumb|Descent of a Martian lander halted by retrorockets (computer-generated impression) thumb|Soyuz (spacecraft)|Soyuz space capsule retro-rockets cushion the landing impact A retrorocket (short for retrograde rocket) is a rocket engine providing thrust opposing the motion of a vehicle, thereby causing it to decelerate. They have mostly been used in spacecraft, with more limited use in short-runway aircraft landing. New uses are emerging since 2010 for retro-thrust rockets in reusable launch systems.

rocket engine for maneuvering

inspection boom used as an extension of Canadarm and Canadarm2

spacecraft docking mechanism

spacecraft docking adapter

mechanism used to connect all non-Russian pressurized modules of the International Space Station

proposed spacecraft propulsion method that takes advantage of solar wind

spacecraft compartment containing a variety of support systems used for spacecraft operations; equivalent to the spacecraft bus assembly on uncrewed spacecraft

type of hypervelocity impact shield used on spacecraft

spacecraft mechanism

A magnetorquer or magnetic torquer (also known as a torque rod) is a satellite system for attitude control, detumbling, and stabilization built from electromagnetic coils. The magnetorquer creates a magnetic dipole that interfaces with an ambient magnetic field, usually Earth's, so that the counter-forces produced provide useful torque.

spacecraft module designed to reenter an atmosphere intact

solar cell panel on a spacecraft operating in the inner Solar System

thumb|upright=1.5|Ballute-equipped Mark 82 bombs, Mk-82AIRs, being dropped by an American [[F-111 attack aircraft]] A ballute (a portmanteau of balloon and parachute) is a parachute-like braking device optimized for use at high altitudes and supersonic velocities.

spacecraft section intended for use only in space

docking system used by Soviet and Russian spacecraft

device used to reduce the spin of satellites, typically soon after launch

long conducting wires which can act as electrical motors or generators

thumb|right|Logo HAL/S (High-order Assembly Language/Shuttle) is a real-time aerospace programming language compiler and cross-compiler for avionics applications used by NASA and associated agencies (JPL, etc.). It has been used in many U.S. space projects since 1973 and its most significant use was in the Space Shuttle program (approximately 85% of the Shuttle software was coded in HAL/S). It was designed by Intermetrics in 1972 for NASA and delivered in 1973. HAL/S is written in XPL, a dialect of PL/I. Although HAL/S is designed primarily for programming on-board computers, it is general eno

type of prototype spacecraft plasma propulsion system

thumb|250 px|Apollo and Orion Avcoat AVCOAT 5026-39 is a NASA code for several versions of a specific ablative heat shield material originally created by Avco for the Apollo program. It is composed of silica fibers in an epoxy novolac resin. The original AVCOAT was used for the Apollo Command Module heat shield. A reformulated version was used for the initial Orion heat shield and later for a redesigned Orion heat shield.

type of rocket propulsion system