Betekenis van:
inertial navigation

inertial navigation
Zelfstandig naamwoord
    • a method of controlling the flight of a missile by devices that respond to inertial forces

    Synoniemen

    Hyperoniemen


    Voorbeeldzinnen

    1. Inertial navigation systems
    2. Note:Flight control and navigation systems in 7A103.d. include gyrostabilizers, automatic pilots and inertial navigation systems.
    3. Inertial navigation systems or gyro-astro compasses, containing accelerometers or gyros, specified in 7A001 or 7A002;
    4. "Source code" for the "use" of any inertial navigation equipment, including inertial equipment not controlled by 7A003 or 7A004, or Attitude and Heading Reference Systems (AHRS).
    5. "Source code" for the "use" of any inertial navigation equipment, including inertial equipment not specified in 7A003 or 7A004, or Attitude and Heading Reference Systems (’AHRS’).
    6. Inertial Navigation Systems (INS) (gimballed or strapdown) and inertial equipment designed for "aircraft", land vehicle, vessels (surface or underwater) or "spacecraft" for navigation, attitude, guidance or control and having any of the following and specially designed components therefor:
    7. Designed for use in inertial navigation or guidance systems and specified to function at linear acceleration levels exceeding 100 g;
    8. Designed for use in inertial navigation systems or in guidance systems of all types and usable in ’missiles’;
    9. An inertial measurement device (e.g., an attitude and heading reference system, inertial reference unit, or inertial navigation system); b. One or more external sensors used to update the position and/or velocity, either periodically or continuously throughout the flight (e.g., satellite navigation receiver, radar altimeter, and/or Doppler radar); and
    10. Inertial navigation systems (INS) (gimballed or strapdown) and inertial equipment designed for "aircraft", land vehicle, vessels (surface or underwater) or "spacecraft" for attitude, guidance or control, having any of the following characteristics, and specially designed components thereof:
    11. navigation error (free inertial) subsequent to normal alignment of 0,8 nautical mile per hour (nm/hr) "Circular Error Probable" (CEP) or less (better); or
    12. Navigation error (free inertial) subsequent to normal alignment of 0,8 nautical mile per hour (nm/hr) ’Circular Error Probable’ (’CEP’) or less (better); or
    13. Hybrid Inertial Navigation Systems embedded with Global Navigation Satellite Systems(s) (GNSS) or with "Data-Based Referenced Navigation" ("DBRN") System(s) for navigation, attitude, guidance or control, subsequent to normal alignment and having an INS navigation position accuracy, after loss of GNSS or "DBRN" for a period of up to four minutes, of less (better) than 10 metres "Circular Error Probable" (CEP);
    14. Hybrid Inertial Navigation Systems embedded with Global Navigation Satellite Systems(s) (GNSS) or with "Data-Based Referenced Navigation" ("DBRN") System(s) for attitude, guidance or control, subsequent to normal alignment, having an INS navigation position accuracy, after loss of GNSS or "DBRN" for a period of up to four minutes, of less (better) than 10 metres 'Circular Error Probable' (CEP).
    15. Integrated flight instrument systems, which include gyrostabilisers or automatic pilots, designed or modified for use in space launch vehicles specified in 9A004, unmanned aerial vehicles specified in 9A012 or sounding rockets specified in 9A104; c. 'Integrated navigation systems', designed or modified for space launch vehicles specified in 9A004, unmanned aerial vehicles specified in 9A012 or sounding rockets specified in 9A104 and capable of providing a navigational accuracy of 200 m Circle of Equal Probability (CEP) or less. Technical Note: An 'integrated navigation system' typically incorporates the following components: 1. An inertial measurement device (e.g., an attitude and heading reference system, inertial reference unit, or inertial navigation system); 2.