Dassault Mirage III V. Balzac

The aircraft was rebuilt, and resumed flight testing on 2 February 1965.

On 8 September 1965, the aircraft suffered another fatal crash, once again while in a low altitude hover. The aircraft was being evaluated by United States Air Force Major P E Neale, as part of a Franco-American information exchange on VTOL programmes.

Major Neale made an unsuccessful ejection outside the ejection seat's escape envelope.

The findings of the accident investigation were never made public. It was speculated that hydraulic control difficulties coupled with excessive use of the lift engines resulted in fuel starvation and the flame-out of all nine engines.

Once again, the damage was not irreparable, but this time the aircraft was not rebuilt, as flight development of the Mirage IIIV prototype was already underway.

Specifications (Balzac V)

General characteristics

* Crew: 1
* Length: 13.1 m (42 ft 11.75 in)
* Wingspan: 7.3 m (23 ft 11.25 in)
* Height: 4.6 (m 15 ft)
* Wing area: 27.2 m² (292.78 ft²)
* Empty weight: 6,124 kg (13,500 lb)
* Loaded weight: 7,000 kg (15,432 lb)
* Powerplant:
o 1× Bristol-Siddeley Orpheus BOr 3 Cruise turbojet, 21.57 kN (4,850 lbf)
o 8× Rolls-Royce RB108-1A lift turbojet, 9.6 kN (2,160 lbf) each

Performance

* Maximum speed: 1,104 km/h (686 mph) at sea level
* Wing loading: 257.3 kg/m² (52.7 lb/ft²)
* Thrust/weight (jet): 1.12:1 in vertical flight
* Endurance: 15 minutes

Bibliography

* Breffort, Dominique and Andre Jouineau. "The Mirage III, 5, 50 and derivatives from 1955 to 2000." Planes and Pilots 6. Paris: Histoire et Collections, 2004. ISBN 2-913903-92-4.
* Green, William. Macdonald Aircraft Handbook. London. Macdonald & Co. (Publishers) Ltd., 1964.
* Pérez, San Emeterio Carlos. Mirage: Espejismo de la técnica y de la política (in Spanish). Madrid: Armas 30. Editorial San Martin, 1978. ISBN 8-47140-158-4.

Le Mirage III V sur Wikipedia.en

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The Dassault Mirage IIIV (three vee) fighter aircraft is a vertical take-off and landing (VTOL) fighter. Unlike its predecessor, the Dassault Mirage III, the IIIV model featured eight small vertical lift jets straddling the main engine.

The design was in response to a mid-1960s NATO specification for a VTOL strike fighter.

Design and development

Four designs were submitted, the Mirage IIIV design, the Fokker-Republic D.24 Alliance, the BAC 584 and the Hawker P.1154, to NATO in January 1962 in competition for the AC/169 specification for a supersonic V/STOL strike fighter to meet NATO Basic Military Requirement 3.

In May that year the resulting judgement that the P.1154 was the technically superior, but when considering as well the financing and work-sharing opportunities the Mirage IIIV was judged its equal in merit.

NATO was not in the position to fund the full development of either winner leaving it up to the individual member countries

Since the Rolls-Royce RB162 lift engines specified for the Mirage IIIV were not expected to be available before 1963, Dassault modified the first Mirage III prototype as the Balzac V to serve as an interim VTOL testbed.

Fitted with eight Rolls-Royce RB.108 lift engines and an unreheated Bristol Orpheus BOr 3 as the main engine.

The Balzac began tethered hovering on 12 October 1962 and achieved the first free hover only six days later.

The first accelerating transition from vertical take-off to horizontal flight took place on its 17th sortie on March 18, 1963.
The aircraft had two fatal accidents, one in January 1964 and one in September 1965. After the last accident the aircraft was not repaired.

In the meantime, the Balzac had led to the actual Mirage IIIV, which was twice as big. Two prototypes were built.
The first Mirage IIIV performed its first hovering trial in February 1965.
The IIIV had the general layout of earlier Mirage fighters, but it was longer and had a bigger wing, and, like the Balzac, nine engines: a single SNECMA-modified Pratt & Whitney JTF10 turbofan, designated TF104, with thrust of 61.8 kN (13,900 lbf), and eight Rolls-Royce RB162-1 engines, each with thrust of 15.7 kN (3,525 lbf), mounted vertically in pairs around the centreline.

The TF104 was originally evaluated on a special-built trials machine, the Mirage IIIT, which was much like a Mirage IIIC except for the change in engine fit.

The TF104 engine was quickly replaced by an upgraded TF106 engine, with thrust of 74.5 kN (16,750 lbf), before the first prototype made its initial transition to forward flight in March 1966. It later attained Mach 1.32 in test flights.

The second prototype featured a TF306 turbofan for forward thrust of 82.4 kN (18,500 lbf), and first flew in June 1966. In September of that year, it attained Mach 2.04 in level flight, but was lost in an accident on 28 November 1966. The Mirage IIIV was never able to take off vertically and successfully go supersonic in the same flight.

The loss of the second prototype effectively killed the program, and in fact killed any prospect of an operational Mach 2 vertical take-off fighter for decades.
The British Hawker P.1154 had been cancelled in 1965 by the government just as the prototypes were being built, though its subsonic brother, the Hawker-Siddeley Kestrel VTOL attack aircraft was flying in tri-partite trials with the UK, US and West Germany.

The French preferred the Mirage IIIV, and the international cooperation needed to make the P.1154 a reality never materialized.

Snecma / P&W TF 306

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