曝光台 注意防骗
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workload is excessrve or mission effectiveness is inadequate or both.
592 PERFORMANCE, STABILITY, DYNAMtCS, AND CONTROL
co
a
(/
Fraquency, racVs
Frequency response: yaw rate
Fig. 630 Frequency response of the general aviation airplane: yaw rate to aileron
inpuL
Category A fiight phases can be terminated safely, and category B and C fiight
phases can be completed. The fiight phases are divided as follows.
Category A. Nonterminal flight phases that require rapid maneuvering, preci-
sion tracking, or precise fiight-path control. Included in the categor}r are air-to-air
combat, ground attack, weapon delivery/launch, aerial recov'er)r, reconnaissance,
in-flight refueling (receiver), terrain following, antisubmarine search, and close-
formation flying.
Category B. Nonterminal flight phases that are normally accomplished using
gradual maneuvers and without precision tracking, althoug~'accurate flight-path
control may be required. Included in the category are climb, cruise, loiter, in- flight
refueling (tanker), descent, emergency descent, emergency deceleration, and aerial
delivery.
Termina/ f/ight phases.
Category C. Terminal flight phases are normally accomplished using grad-
ual maneuvers and usually re6quire accurate flight-path control. Included in this
category are takeoff, catapult takeoff, approach, wa'veofftgo-around, and landing.
AfRPLANE RESPONSE AND CLOSED-LOOP CONTROL 593
The aircraft are classified as follows.
Class /. Small, light airplanes, such as light utility, primary trainer, and light
observation craft.
Class ///- Large, heavy, low-to-medium maneuverabilit)t airplanes, such as
heavy transport/cargo/tanker, heavy bomber, and trainer for class III.
C/ass /V High-maneuverability airplanes, such as 1ighter/interceptor, attack,
tactical reconnaissance, observation, and trainer for class I'V.
6.4.1 Longitudinal Flying Clua/ities
Phugoid mode.4,5
Levell = c > 0.04
Levelll: < > 0
Levellll = T2 > 55 s
In the level III, the aircraft is assumed to have an unstable (divergent) phugoid
mode, and T2 denotes the time required for the amplitude to double the init:ial
value.
The requirements on the natural frequencies of the short- )d mode4.5 for
category A, B, and C flight phases according to MIL- F~878gtCp6esrihooduld lie within
the linuts as given in Table 6.3.
Table 6.2 Damping ratios for short-period mode
-7----. _-__-_-___--
Cat A and C Cat A and C Cat B Cat B
<sp.min Csp,max Csp,min <rp.max
-_--_ ---~--~-_-_---__-~
Levell 0.35 1.30 0.30 2.0
Levelll 0.25 2.0 0.20 2.0
Levellll 0.15 -- 0.15 N
_-_ -==: --r------~--
C/ass//. Medium-weight,low-to-mediummaneuverabilityairplanes,suchas
heavy utility/search and rescue, light or medium transport/cargo/tanker, reconnais-
sance, tactical bomber, heavy attack, and trainer for class II-
Short-period mode. The damping ratios ofthe short-period mode4.S for var-
ious levels of flying qualities for category A, B, and C fiight phases are given in
Table 6.2.
594 ' PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL
Table 63 Linuts oncO:Z,,p/(nlo:)
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