Analysis of dynamic jettison hinge forces for Centaur nose fairing
Performance tests on dynamic jettison hinge loads of Centaur nose fairing
Tang, H. M.↗
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Performance of an auxiliary inlet ejector nozzle with fixed doors and single-hinge trailing-edge flap
Auxiliary inlet ejector nozzle with fixed doors and single-hinge trailing-edge flaps
Johns, A. L.↗
Performance of an auxiliary inlet ejector nozzle with fixed inlet doors and triple-hinge trailing-edge flap
Performance of auxiliary inlet ejector nozzle with fixed inlet doors and triple-hinge trailing edge flap over subsonic and transonic free stream range for supersonic aircraft
Johns, A. L.↗
Double hinged flap Patent
Double hinged flap for boundary layer control over trailing edges of wings
Turner, T. R.↗
Fin loads and control-surface hinge moments measured in full-scale wind-tunnel tests on the X-24A flight vehicle
Fin loads and control surface hinge moments measured in full scale wind tunnel tests on X-24A flight vehicle
De Angelis, V. M.↗
Vertical-Tail Loads and Control-surface Hinge-Moment Measurements on the M2-F2 Lifting Body During Initial Subsonic Flight Tests
Vertical tail loads and control surface hinge moment measurements on M2-F2 lifting body at subsonic speeds
Jenkins, J. M.↗
Performance of an auxiliary inlet ejector nozzle with floating inlet doors and floating single-hinge trailing-edge flaps
Performance of auxiliary inlet ejector nozzle with floating inlet doors and floating single hinge trailing edge flaps
Johns, A. L.↗
Vertical-fin loads and rudder hinge-moment measurements on a 1/8 scale model of the M2-F3 lifting body vehicle at Mach numbers from 0.50 to 1.30
Transonic wind tunnel tests of vertical fin loads and rudder hinge moments on M2-F3 lifting body scale model at Mach 0.50 to 1.30
Tang, M. H.↗
Comparison of hinge moments for a simple delta wing and a delta-wing orbiter concept at Mach 6
Comparisons of hinge moments for simple delta wing and delta wing orbiter concept at Mach 6
Ashby, G. C., Jr.↗
Dynamic analysis of a system of hinge-connected rigid bodies with nonrigid appendages
Equations of motion are derived for use in simulating a spacecraft or other complex electromechanical system amenable to idealization as a set of hinge-connected rigid bodies of tree topology, with rigid axisymmetric rotors and nonrigid appendages attached to each rigid body in the set. In conjunction with a previously published report on finite-element appendage vibration equations, this report provides a complete minimum-dimension formulation suitable for generic programming for digital computer numerical integration.
Likins, P. W.↗
Investigation of space shuttle orbiter subsonic stability and control characteristics and determination of control surface hinge moments in the Rockwell International low speed wind tunnel (OA37)
Experimental aerodynamic investigations were conducted on a string-mounted 0.030 scale representation of the 140A/B space shuttle orbiter in the 7.75- by 11-foot low speed wind tunnel. The primary test objectives were to establish basic longitudinal and lateral directional stability and control characteristics for the basic configuration plus control surface hinge moments. Aerodynamic force and moment data were measured in the body axis system by an internally mounted, six-component strain gage balance. Additional configurations investigated were sealed rudder hingeline gaps, sealed elevon gaps and compartmentized speedbrakes.
Hughes, T.↗
Dynamic analysis of a system of hinge-connected rigid bodies with nonrigid appendages
Equations of motion are derived for use in simulating a spacecraft or other complex electromechanical system amenable to idealization as a set of hinge-connected rigid bodies of tree topology, with rigid axisymmetric rotors and nonrigid appendages attached to each rigid body in the set. In conjunction with a previously published companion paper on finite-element appendage vibration equations, this paper provides a complete minimum-dimension formulation suitable for generic programming for digital computer numerical integration.
Likins, P. W.↗
Results of an investigation elevon hinge moments and dual panel elevon effectiveness using an .0405-scale model (16-0) of the configuration 140C space shuttle orbiter in the Rockwell International NAAL low speed wind tunnel (OA119B)
Experimental aerodynamic investigations were conducted on a sting mounted .0405-scale representation of the 140C outer mold line space shuttle orbiter in a 7.75 x 11.00 foot low speed wind tunnel during the time period from August 22, 1974 to September 6, 1974. The primary test objectives were to define dual panel elevon/aileron effectiveness and to investigate elevon hinge-moments for the 140C orbiter configuration with wing/elevon upper hingeline sealing flapper doors. The elevon parametric variations, consisting of the basic elevons with 6 inch gaps and flapper doors, elevons with no flapper doors and completely open upper hingeline gap, and an entirely sealed solid elevon, were tested with elevon deflections from +20 to -35 deg at various aileron deflections. Aerodynamic force and moment data were measured in the body axis system by a 2.5 inch task type internal strain gage balance.
Mennell, R. C.↗
An investigation in the MSFC TWT to determine spoiler effects on wing loads and elevon hinge moments utilizing 0.004-scale models (77-0 and 74-OTS) of the shuttle vehicle 5 configuration (IA125)
Information is presented for wind tunnel tests (IA125) of a 0.004-scale orbiter, external tank, and solid rocket motor integrated vehicle model (77-0 and 74-OTS) in the MSFC Trisonic Wind Tunnel. These tests were conducted in support of MCR's 1344 and 1346. Data from these tests provide spoiler effects on wing bending/torsion and elevon hinge moments, elevon effectiveness data and the influence of solid plumes from Mach numbers of 0.6 through 2.74 at angles of attack and sideslip from -10 through 10 degrees.
Allen, E. C.↗
Effect of hinge-moment parameters on elevator stick forces in rapid maneuvers
The importance of the stick force per unit normal acceleration as a criterion of longitudinal stability and the critical dependence of this gradient on elevator hinge moment parameters are investigated with special reference to transient effects for maneuvers of short duration. The analysis shows that different combinations of elevator parameters, which give the same stick force per unit acceleration in turns, give widely different force variations during the entries into and recoveries from steady turns and during maneuvers of short duration such as abrupt pull-ups. The stick force per unit acceleration is greater for abrupt than for gradual control movements.
Jones, R. T.↗
Combined hinge and latch
In door mechanism, hinge and latch are combined in single four-part assembly. Latch eliminates need for protruding hook, and can be modified to lock door in ninety degree position.
Appleberry, W. T.↗
Hinge-connected rigid bodies
Package of subroutines solve minimum dimension sets of discrete coordinate equations of motion for arbitrary number of hinge-connected rigid bodies assembled in tree topology.
Fleischer, C. E.↗
Analysis and flight evaluation of a small, fixed-wing aircraft equipped with hinged plate spoilers
The results of a four phase effort to evaluate the application of hinged plate spoilers/dive brakes to a small general aviation aircraft are presented. The test vehicle was a single engine light aircraft modified with an experimental set of upper surface spoilers and lower surface dive brakes similar to the type used on sailplanes. The lift, drag, stick free stability, trim, and dynamic response characteristics of four different spoiler/dive brake configurations were determined. Tests also were conducted, under a wide range of flight conditions and with pilots of various experience levels, to determine the most favorable methods of spoiler control and to evaluate how spoilers might best be used during the approach and landing task. The effects of approach path angle, approach airspeed, and pilot technique using throttle/spoiler integrated control were investigated for day, night, VFR, and IFR approaches and landings. The test results indicated that spoilers offered significant improvements in the vehicle's performance and flying qualities for all elements of the approach and landing task, provided a suitable method of control was available.
Olcott, J. W.↗