Soong P-4
| P-4 | |
|---|---|
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| |
Role
|
Intermediate trainer aircraft |
National origin
|
Monsilva |
Manufacturer
|
Soong Aerospace Company |
First flight
|
29 July 1985 |
Introduction
|
1988 |
Primary users
|
 Monsilvan Air Force Baltanese Air Force
|
Produced
|
208+ |
Unit cost
|
¥108.5 million (2020)
|
The Soong P-4 is a Monsilvan subsonic intermediate jet trainer aircraft developed and manufactured by Soong Aerospace Company. Its main operator is the Monsilvan Air Force. In addition to its primary training missions, the P-4 is also used in aerobatic teams as well as liaison duties with most fighter units. The first XP-4 prototype flew on 29 July 1985, while the first production aircraft was delivered during September 1988.
Contents
Development
In November 1981, Soong was selected as the main contractor to design and manufacture a suitable trainer aircraft, which was initially designated as the MP-X program. The MP-X program had been launched to procure a replacement for the Monsilvan Air Force's aging training aircraft. Furthermore, there was also a desire for the prospective trainer aircraft to take over some of the syllabus that was being handled by contemporary fighter aircraft. The design team worked in close conjunction with the Monsilvan Defense Agency.
The design produced by Soong had to satisfy aspects of the MAF's training regime that was previously performed by multiple aircraft. As such, the type had to demonstrate a range of transonic aerodynamic effects, as well as achieving a high level of manoeuvrability, a relatively-low operating cost, and high reliability levels. Easy handling was also required so that trainees could convert from piston-engined aircraft. The economics for operating the type was to be comparable to the leading international competitors at that time.
Out of these effots emerged the P-4, a clean-sheet indigenously-developed trainer aircraft.
Design
The Soong P-4 is a Monsilvan subsonic intermediate jet trainer aircraft. It is a twin-engined aircraft, being powered by a pair of turbofan units. These engines, which were capable of generating up to 15.7 kN (3,520 lbf) of thrust, were indigenously-developed in conjunction with the P-4. While no combat-orientated model of the aircraft has been developed to date, the standard P-4 features three hard points, enabling the installation of various air-to-air missiles, bombs and a gun pod.
The P-4 has a sturdy, damage-tolerant airframe that is largely composed of conventional aluminium alloys, although some composite materials are also present in some areas. Its structure has sufficient strength to enable high-g manoeuvres, being rated to perform instantaneous dives of 7.33g when flown in a clean configuration. It is furnished with a thick-section transonic aerofoil, which was developed by Soong and the Industrial Technology Research Institute of Monsilva (ITRIM) to provide outstanding high-angle-of-attack handling and favorable spin characteristics. An unusual aerodynamic feature present on the P-4 is the compact leading-edge root extensions (LERX) just forward of its wings along the forward fuselage, these generate additional vortex lift and enhance the aircraft's high-g departure tendencies, such as the supression of wing-drop and pitch-up during aerodynamic stalls. The use of LERX avoided any need for vortex generators.
The avionics of the P-4 are digital in nature; this approach was chosen in order to reduce both the size and weight of the avionics while also increasing thier reliablility. The majority of onboard systems are of a convential nature; however the use of a licensed onboard oxygen generation system (OBOGS) is an unusual choice for a trainer aircraft and had required considerable effort to adapt it for use aboard the P-4.
Specifications
General characteristics
- Crew: 2
- Length: 13.00 m (42 ft 8 in)
- Wingspan: 9.94 m (32 ft 7 in)
- Height: 4.60 m (15 ft 1 in)
- Wing area: 21.00 m2 (226.0 sq ft)
- Aspect ratio: 4.7:1
- Empty weight: 3,700 kg (8,157 lb)
- Max takeoff weight: 7,500 kg (16,535 lb)
- Fuel capacity: 2,241 L (493 imp gal; 592 US gal) internal fuel
Performance
- Maximum speed: 1,038 km/h (645 mph, 560 kn) at sea level
- Stall speed: 167 km/h (104 mph, 90 kn)
- Range: 1,668 km (1,036 mi, 901 nmi) with two 450 L (99 imp gal; 120 US gal)
- Service ceiling: 15,240 m (50,000 ft)
- Rate of climb: 51 m/s (10,000 ft/min)
Armament
- Hardpoints: 5 (4 underwing and 1 under fuselage) for drop tanks, practice bombs and target towing equipment
