Boeing Chinook (UK variants) vs PZL SW-4 Puszczyk

Royal Air Force^[source]

Polish Armed Forces^[source]

72 (all RAF models)^[source]

40^[source]

22 November 1980 (with RAF)^[source]

2002^[source]

23 March 1980 (HC1)^[source]

29 October 1996^[source]

Boeing CH-47 Chinook^[source]

HC1, HC1B, HC2, HC3, HC4, HC5, HC6, HC6A, HC7^[source]

55 soldiers and up to 10 tonnes of freight or equipment^[source]

4 passengers^[source]

2× M134 Miniguns and 1× M60 machine gun^[source]

2 x M134 Miniguns, 1 x M60 Machine Gun^[source]Chinook / RAF specification (variant not stated) · Guns

5,655.2 sq ft (525.39 m 2 )^[source]

64 m 2 (690 sq ft)^[source]

- root: Boeing VR-7; tip: Boeing VR-8^[source]

Glass cockpit with a BAE Systems Digital Advanced Flight Control System (DAFCS), includes automatic modes such as auto-hover and auto-descend to ease pilot workload.^[source]

Electro-Optical Sensor Turret (EOST) with two infrared cameras and a low-light TV function .^[source]

EOST turret including two infrared cameras and a low-light TV function^[source]Chinook / RAF specification (variant not stated) · Electro optics

Missile Warning Receiver, Infrared Warning Receiver, Radar Warning Receiver, Counter-measure dispensing system (flares).^[source]

United States^[source]Boeing Chinook (UK variants) · origin explicitly stated in the linked current national-inventory row; no inference from operator or shipyard

Two Honeywell 55-L-714A Free-Turbine engines^[source]Chinook / RAF specification (variant not stated) · Powerplant

4,168shp each^[source]Chinook / RAF specification (variant not stated) · ThrustSource text · numeric interpretation needs review

15,000ft^[source]Chinook / RAF specification (variant not stated) · Maximum altitude

Poland^[source]

1996–present^[source]

25 kg/m 2 (5.1 lb/sq ft)^[source]

0.21 kW/kg (0.13 hp/lb)^[source]

Polish light single-engine multipurpose helicopter^[source]

The original design for the SW-4 called for it to be powered by a 300 kW (400 shp ) PZL Rzeszow GTD350 turboshaft engine, as featured upon the prototype mockup.^[source]PZL SW-4 Puszczyk · Development / Origins; only the objects and conditions stated in this passage

According to PZL-Swidnik, the early SW-4 could reach the rated top speed of about 240 km/h (130 kn ) and a max range with auxiliary fuel tank about 900 km (485 nmi ).^[source]PZL SW-4 Puszczyk · Development / Origins; only the objects and conditions stated in this passage

PZL-Świdnik's parent company, AgustaWestland chose to use the SW-4 as the basis for an optionally manned rotorcraft, the PZL-Świdnik SW-4 Solo. In 2011, development of an optionally-manned demonstrator began. The SW-4 Solo was first was shown at the MSPO 2012 in Poland as "SW-4 Solo" RUAS/OPH platform (Rotorcraft Unmanned Air System/Optionally Piloted Helicopter). In 2013, AgustaWestland was given a Royal Navy contract for the SW-4 Solo's development as part of the UK's RWUAS (Rotary Wing Unmanned Air System) Capability Concept Demonstrator (CCD) programme. Development of the SW-4 Solo is also being supported by the Italian Ministry of Defence 's Directorate for Air Armaments under the Italian National Military Research Plan. By September 2015, the SW-4 Solo had performed a total of 26 demonstration flights, which included simulated shipboard integration tests. In November 2015, AgustaWestland stated that the SW-4 Solo was "ready for sale".^[source]PZL SW-4 Puszczyk · Development / Further development; only the objects and conditions stated in this passage

The SW-4 is powered by a single 335 kW (450 shp ) (283 kW/380 shp max continuous rated) Rolls-Royce Model 250C20R/2 turboshaft engine, which drives the rotorcraft's three-blade main rotor and two-blade tail rotor. An alternative engine is provided in the form of the 460 kW (615 shp) Pratt & Whitney Canada PW200 /9 turboshaft engine. The main rotor is fully articulated and the rotor blades on both the main and tail rotors are composed of composite materials. The SW-4 uses hydraulic flight controls, the rotorcraft has been promoted as possessing excellent flight controls, and can be flown in both day and night visual flight rules conditions.^[source]PZL SW-4 Puszczyk · Design; only the objects and conditions stated in this passage

The SW-4 is capable of transporting up to five people, including a pilot, in crashworthy seats; passengers are provided with a high level of external visibility and comfort, an optional vibration absorption system is also offered. The main cabin can be rapidly reconfigured between passenger and cargo-carrying configurations and is accessed via two sliding doors on either side of the cabin, a dedicated baggage compartment is also present beneath the main cabin. PZL- Świdnik stated that multi-role operations had been a high priority during the SW-4's development; and that the rotorcraft is well-suited to passenger transport, primary and advanced training, patrol and surveillance missions.^[source]PZL SW-4 Puszczyk · Design; only the objects and conditions stated in this passage

Various optional equipment can be installed, such as removable co-pilot flight controls, wire strike protection system , a forward looking infrared (FLIR) sensor system, instrument flight rules (IFR) training fittings, radio altimeter, emergency medical system, moving map, external loudspeakers and/or search light, flotation gear, and an external cargo sling. Much of the external equipment is designed to be held on external extension arms; overall, the SW-4 can mount/carry a useful payload of up to nearly 600 kilograms. Both basic and advanced trainer variants of the SW-4 have been developed to conform with NATO standards and military pilot training regulations, it is promoted as possessing a high level of inherent flight stability and safety; the advanced model is compatible with night vision goggles (NVG) and is equipped with an emergency simulation unit.^[source]PZL SW-4 Puszczyk · Design; only the objects and conditions stated in this passage

Capacity: 4 passengers^[source]PZL SW-4 Puszczyk · Specifications (SW-4); only the objects and conditions stated in this passage

Length: 10.57 m (34 ft 8 in)^[source]PZL SW-4 Puszczyk · Specifications (SW-4); only the objects and conditions stated in this passage

Height: 3.05 m (10 ft 0 in)^[source]PZL SW-4 Puszczyk · Specifications (SW-4); only the objects and conditions stated in this passage

Empty weight: 1,050 kg (2,315 lb)^[source]PZL SW-4 Puszczyk · Specifications (SW-4); only the objects and conditions stated in this passage

Gross weight: 1,600 kg (3,527 lb)^[source]PZL SW-4 Puszczyk · Specifications (SW-4); only the objects and conditions stated in this passage

Max takeoff weight: 1,800 kg (3,968 lb)^[source]PZL SW-4 Puszczyk · Specifications (SW-4); only the objects and conditions stated in this passage

Powerplant: 1 × Rolls-Royce 250-C20R/2 turboshaft engine, 336 kW (451 hp)^[source]PZL SW-4 Puszczyk · Specifications (SW-4); only the objects and conditions stated in this passage

Main rotor diameter: 9 m (29 ft 6 in)^[source]PZL SW-4 Puszczyk · Specifications (SW-4); only the objects and conditions stated in this passage

Main rotor area: 64 m 2 (690 sq ft)^[source]PZL SW-4 Puszczyk · Specifications (SW-4); only the objects and conditions stated in this passage

Maximum speed: 260 km/h (160 mph, 140 kn)^[source]PZL SW-4 Puszczyk · Specifications (SW-4); only the objects and conditions stated in this passage

Range: 790 km (490 mi, 430 nmi)^[source]PZL SW-4 Puszczyk · Specifications (SW-4); only the objects and conditions stated in this passage

Service ceiling: 5,200 m (17,100 ft)^[source]PZL SW-4 Puszczyk · Specifications (SW-4); only the objects and conditions stated in this passage

Rate of climb: 10.3 m/s (2,030 ft/min)^[source]PZL SW-4 Puszczyk · Specifications (SW-4); only the objects and conditions stated in this passage