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Robin HR.100
|
|
Robin HR.100/250TR Tiara aircraft D-EKRF, at Lelystad Airport (EHLE), 22 May 1993
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Role
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Four-seat light monoplane
Type of aircraft
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National origin
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France
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Manufacturer
|
Avions Pierre Robin
|
Designer
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Chris Heintz
|
First flight
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1969
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Produced
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1969-1976
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Number built
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178
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Developed from
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Robin DR.200
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The
Robin HR100
is a French four-seat light monoplane, designed by
Chris Heintz
[1]
and built by
Avions Pierre Robin
as metal-winged version of the
Robin DR253 Regent
.
Development
[
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]
The prototype of the Robin HR100 was the prototype DR253 Regent which was rebuilt with metal wings and powered by a 180 hp (134 kW) Lycoming O-360 engine. It first flew on 3 April 1969 as the
Robin HR100/180
. The HR100 is a low-wing cantilever monoplane with a conventional cantilever tail unit and a fixed tricycle landing gear. A number of different variants were produced in the 1970s. From 1972 a high-powered improved version was produced as the
HR100/285
with a 285 hp (213 kW)
Continental Tiara 6-285B
engine and retractable landing gear and airframe modifications.
The
French Air Force
ordered a number of
HR.100/250
aircraft in the mid 1970s and these were used for communications and other duties.
A two-seat trainer version was developed as the
HR200
, and a modified version with a lighter airframe and new fin and rudder was developed as the
R1180 Aiglon
in 1977.
Variants
[
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]
- HR.100 Royal
- 1969 Prototype with a 180hp (134kW)
Lycoming O-360
engine, one built.
- HR.100/180
- 1976 Prototype with a 180hp (134kW) Lycoming O-360 engine, one built.
- HR.100/200B Royal
- Initial production version with a 200hp (149kW) Lycoming IO-360 engine.
- HR.100/210 Safari
- Production version with a 210hp (157kW) engine, 113 built of both 200B Royal and 210 Safari variants.
- HR.100/235TR
- Experimental HR.100 with an enlarged tail and retractable landing gear and a 235hp
Lycoming O-540
-B engine, one built.
- HR.100/250TR
- HR.100/235 with a 250hp (186kW) Lycoming IO-540-C4B5 engine, 24 built.
- HR.100/285TR Tiara
- HR.100/235 with a 285hp (213kW)
Continental Tiara 6-285
engine, 37 built
- HR.100/320 4+2
- Experimental version with two extra children's seats, one built
Operators
[
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]
Military operators
[
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]
-
France
Specifications (HR.100/285)
[
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]
Data from
Jane's All the World's Aircraft 1976?77
[2]
General characteristics
- Crew:
1
- Capacity:
3?4 passengers
- Length:
7.59 m (24 ft 11 in)
- Wingspan:
9.08 m (29 ft 9 in)
- Height:
2.71 m (8 ft 11 in)
- Wing area:
15.20 m
2
(163.6 sq ft)
- Aspect ratio
:
5.36:1
- Airfoil
:
NACA 64A515 (modified)
- Empty weight:
840 kg (1,852 lb)
- Max takeoff weight:
1,400 kg (3,086 lb)
- Fuel capacity:
440 L (97 imp gal; 120 US gal)
- Powerplant:
1 ×
Teledyne Continental Tiara 6-285
flat-six
, 213 kW (285 hp)
- Propellers:
3-bladed Hoffmann wooden
constant-speed propeller
, 2.00 m (6 ft 7 in) diameter
Performance
- Maximum speed:
325 km/h (202 mph, 175 kn) at sea level
- Cruise speed:
293 km/h (182 mph, 158 kn) (65% power)
- Stall speed:
110 km/h (68 mph, 59 kn) (flaps down)
- Never exceed speed
:
360 km/h (220 mph, 190 kn)
- Range:
2,344 km (1,456 mi, 1,266 nmi) (econ. cruise)
- Service ceiling:
5,700 m (18,700 ft)
- Rate of climb:
6.0 m/s (1,180 ft/min)
- Takeoff run to 15 m (50 ft):
600 m (1,970 ft)
- Landing run from 15 m (50 ft):
660 m (2,170 ft)
See also
[
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]
Related development
References
[
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]
- The Illustrated Encyclopedia of Aircraft (Part Work 1982-1985), 1985, Orbis Publishing, Page 2799
- R.W.Simpson,
Airlife's General Aviation
, Airlife Publishing, England, 1991,
ISBN
1-85310-194-X
- Taylor, John W. R.
, ed. (1976).
Jane's All the World's Aircraft 1976?77
. London: Jane's Yearbooks.
ISBN
0-354-00538-3
.