Betekenis van:
inertial guidance

Voorbeeldzinnen

1. Designed for use in inertial navigation or guidance systems and specified to function at linear acceleration levels exceeding 100 g;
2. Designed for use in inertial navigation systems or in guidance systems of all types and usable in ’missiles’;
3. designed for use in inertial navigation systems or in guidance systems of all types and usable in "missiles";
4. 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:
5. 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:
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. 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 therefor:
8. Linear accelerometers designed for use in inertial navigation or guidance systems and having any of the following characteristics, and specially designed components therefor:
9. Accelerometers with a threshold of 0,05 g or less, or a linearity error within 0,25 % of full scale output, or both, which are designed for use in inertial navigation systems or in guidance systems of all types;
10. linear accelerometers, designed for use in inertial navigation systems or in guidance systems of all types, usable in "missiles", having all the following characteristics, and specially designed components therefor:
11. Linear accelerometers, other than those specified in 7A001, designed for use in inertial navigation systems or in guidance systems of all types, usable in ’missiles’, having all the following characteristics, and specially designed components therefor:
12. Linear accelerometers, designed for use in inertial navigation systems or in guidance systems of all types, usable in 'missiles', having all the following characteristics, and specially designed components therefor;
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. 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’);