Lockspeiser LDA-01
| Land Development Aircraft | |
|---|---|
| |
| Role | Experimental utility transport |
| Manufacturer | Lockspeiser |
| Designer | David Lockspeiser |
| First flight | 24 August 1971 |
| Status | Destroyed, cancelled from register. |
| Number built | 1 |
The Lockspeiser LDA-01 ("Land Development Aircraft") was a British seven-tenths scale research and development tandem wing aircraft,[1] which was designed and built by test pilot and engineer David Lockspeiser to prove a concept for a low-cost utility transport.
Design and development
The LDA-01 was a single-seat tandem-wing monoplane, fabric covered with metal construction. The foreplane had a common design to the separately-made port and starboard wings of the main plane, giving it half the area. The intention was to reduce the number of spare parts needed by re-using the same wing component interchangeably in each location.[2] The main wings were mounted at the rear-end of the box structure fuselage and the fore wing was attached underneath the front. The fuselage was fitted with a four wheeled landing gear [citation needed] and was designed to be fitted with a detachable payload container to allow easy conversion between roles. It was powered by a rear-mounted pusher engine. The LDA-01 G-AVOR first flew on 24 August 1971 at Wisley in Surrey, under the power of an 85 hp (63 kW) Continental C85 piston engine, but was later refitted with a more powerful Lycoming O-320 engine.
The aircraft (which by this time had been re-registered G-UTIL), and had been renamed the Boxer 500, was being modified to planned production configuration by Brooklands Aerospace at Old Sarum Airfield when it was destroyed in a fire on 16 January 1987.[3][4][5]
Specifications (LDA-01)
Data from ,[6] British Civil Aircraft since 1919,[7] Jane's All The World's Aircraft 1976-77.[8]
General characteristics
- Crew: 1
- Length: 22 ft 6 in (6.86 m)
- Wingspan: 13 ft 0 in (3.96 m) foreplane
- Rearplane span: * 13 ft (4.0 m)
- Height: 10 ft 3 in (3.12 m)
- Wing area: 108.8 sq ft (10.11 m2)
- Aspect ratio: Rear wing:7; Forward wing:4.5
- Airfoil: NACA 23012
- Empty weight: 1,237 lb (561 kg)
- Gross weight: 1,616 lb (733 kg)
- Max takeoff weight: 1,700 lb (771 kg)
- Fuel capacity: 138 L (36 US gal; 30 imp gal) in two fuel tanks fore and aft of the cargo bay
- Powerplant: 1 × Lycoming O-320-D1A 4-cyl. air-cooled horizontally-opposed piston engine, 160 hp (120 kW)
- Propellers: Hoffmann HO-V72
- Propellers: 5 ft 9 in (1.76 m) diameter constant-speed metal pusher propeller
Performance
- Cruise speed: 92 kn (110 mph, 170 km/h)
- Stall speed: 42 kn (48 mph, 78 km/h)
- Range: 140 nmi (160 mi, 260 km)
References
- ^ "Flight International report" (pdf), Flight International: 673, 24 April 1975
- ^ LOCKSPEISER, David (9 September 1971). "AERIAL LAND ROVER". Flight International: 404–405. Retrieved 23 April 2017.
- ^ "GINFO Search Results, G-AVOR". CAA. Retrieved 7 January 2008.
- ^ "GINFO Search Results, G-UTIL". CAA. Retrieved 7 January 2008.
- ^ Walters, Brian (August 1991). "LDA - Phoenix or dead duck?". Air International. 41 (2): 71–72. ISSN 0306-5634.
- ^ Taylor, John W.R., ed. (1975). Jane's all the world's aircraft, 1975-76 (66th annual ed.). New York: Franklin Watts Inc. ISBN 978-0531032503.
- ^ Jackson, A.J. (1974). British civil aircraft 1919-1972 Vol.3 (2nd ed. ed.). London: Putnam. p. 259. ISBN 0-370-10014-X.
{{cite book}}:|edition=has extra text (help) - ^ Taylor, John W. R., ed. (1976). Jane's all the World's Aircraft 1976-77. London: Jane's Yearbooks. p. 190. ISBN 0 3540 0538 3.
External links
