db „laros”

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Specifications of „Laros —100”

Characteristics of aircraft

  1. The aircraft „Laros 100” is represented as two-seater semicantilever high-plan, tandem crew position, three-desk chassis and tail crutch. Nose crutch airplane exists too.
  2. Geometrical adjectives
    • span clearance, m 7,15
    • length, m 6.45
    • height on parking, m 1,85
    1. Fuselage
      • Length, m 5.75
      • Width, m 0.75
      • Length of cabin, m 2
      • Height, m 1.2
      • Square of master cross-section, m2 0.9
    2. Foil
      • Type NACA23014
      • Wingspan, m 7.15
      • Chord, m 1.5
      • Sqare, m2 10.7
      • Elongation 5.2
      • Taper ratio 1
      • Wing setting, degree 0
      • Angle V, degree 0
      • Sweep angle, degree 0
    3. Horizontal tail
      • Wingspread of horizontal tail, m 2.7
      • Area of horizontal tail, m2 2.1
      • Elongation of horizontal tail 3.47
      • Taper ratio of horizontal tail 1.67
      • Arm, m 3.29
      • First moment 0.44
    4. Diving-plane
      • Area of diving-plane, m2 1.21
      • Squint angle of diving-plane, degree +25...-30
    5. Rudder unit
      • Height of rudder unit, m 1.47
      • Mean chord of rudder unit 0.76
      • Arm, m 3.45
      • Area of rudder unit, m2 1.15
      • First moment 0.053
    6. Rudder
      • Area of rudder, m2 1.06
      • Angle of deflection, degree +30...-30
    7. Aileron
      • Wingspread of ailerons, m 2х2.325
      • Chord, m 0.375
      • Area of ailerons, m2 2х0.875
      • Relative wing plane, that served by ailerons 0.575
    8. Undercarriage
      • Base, m 4.63
      • Main wheel track, m 1.8
      • Sweptback angle, degree 0
  3. Mass-centering adjectives
    • gross take-off weight, kg 700
    • empty weight, kg 420
    • fuel weight, kg 72
    • center of gravity operation range, % AMC (aerodynamic mean chord) 21…36
    • overload operational range, g +7 ... -4
  4. Airplane performance characteristics
    • dash speed (H=0), km/h 260
    • rate of climb (G=600 kg), m/s 7
    • touchdown speed, km/h 85
    • unstick distance, m 100

Design description

  1. Fuselage of aircraft has mixed construction. The tail-part of fuselage made like the quadrangular truss that has riveted from rectangular pipes, alloy 6063-Т6. The middle-part of construction includes cabin accommodation figured as frame construction.
  2. The junctions of stabilizer, fin and tail crutch of weel trail take place at the back part of fuselage’s tail truss.  Fuselage includes fairing, cover lower and left and right side panels. Panels made from aluminium composite material.
  3. The cabin doors take place by the right board of fuselage, open opposite the flight direction. Construction of the door is the contour made from rectangular pipes 6063-Т6 having the horizontal crossbar. Above this crossbar takes place the glass, lower the crossbar is the three-layered aluminium composite panel.   Emergency release of the doors is provided.
  4. Cabin’s transparency secures the view to the pilots, consists of these details:
    • windshield glazing combined with overhead;
    • left panel’s transparency;
    • backlights;
    • door’s transparency.
    All the transparencies made from the polycarbonate with non-scratch covering. Thickness of transparency is 2 mm. It is pasted-in by the acrylic glue and duct tape of high-adhesive acrylic glue layer.
    1. Mainplane — consists of two consoles, braced and two-spar.
    2. Wing main frame has mixed construction. Strength part made from aluminium alloys profile, shape-generating is from three-layered composite panels.
    3. Wing main frame contains kit of ribs and longerons made from aluminium alloy „ДКАТ”
    4. Wing covering produced from three-layered aluminium composite panels.
    5. At the root of the wing, between  the longerons, fuel call provided.
  5. There are two kinds of fins — horizontal tail and vertical rudder unit. Horizontal tail includes stabilizer, two blades of diving-plane, rudder unit has tail fin and rudder.
    1. Mixed construction stabilizer has alumuinium framework and aluminium skin.
    2. Diving-plane has two blades. Each blade has two elevator hinge fitting’s junctions. At the root of each blade, which stands proud the diving plane up to the plane of symmetry of the aircraft, engine control crank has fixed. Horn and mass balancing have fixed at the extremity. Trimming device with electric drive placed at the left blade of the diving plane.
    3. Tail fin has fixed on the proper junctions of stabilizer.
    4. Rudder has the same construction as the blade of the diving plane. It has two elevator hinge fitting’s junctions. At the top — on the tail fin, below — on the bracket of fuselage tail section.
  6. Undercarriage is irremovable, it includes tree gear legs. Tailweel is free directed, possible to fix it at the neutral position.
    1. Main landing gears are sprung. Each landing gear is the separate sprung inserted into the former's low crossbeam and join-fixed near to the plane of symmetry of the aircraft. At the extremity of each sprung weel shaft and disc brake's rigging up bracket have fixed. Main landing weels, size 5x5", have brakes and hydraulic fluid power.
    2. Tail crutch has sprung that fixed on two junctions at the tail-end of the fuselage.  Swiveling block of weel allows to have a free orient at the aircraft ground run up to 360 degrees.
  7. This aircraft has dual control including manual actuation and foot pedal control. Manual actuation reserved for fore-aft actuator. Foot pedal control is made for directional control and differential braking acquisition by the main weels of undercarriage. Rudder control by the ties is hard.
  8. Power package includes the engine, tractor airscrew, cowl panel and bodies of control placed in the flight-deck.
    1. Engine Lykoming AE 10360, or the same by its characteristics.
    2. Controllable propeller Whirlwind 200 C.
    3. Fuel flow system includes wing tanks and feeder tank.
  9. Instrumentation system of the aircraft is variable by the usage conditions. The main point is the possibility of system's usage from the both pilot's stations.
    1. Pilot seats have 22 degrees of backrest angle. It is more comfortable for load perception and convenience at the straight flight. Seats have fivepoint tethered system with backpack parachute placing opportunity.
    2. Additional instrumentation system:
      • handle of tailwheel stopper;
      • Control valve of cabin ventilation ramp by open air;
      • luggage rack and reservoirs for small parts.