| AMENDED CLAIMS received by the International Bureau on 23 December 2014 (23.12.2014) Claims 1. Propulsion system for an air vehicle (1 ) that comprises at least one differential velocity fan (4), housed in and concentrically arranged in a fan housing (30), which differentiated velocity fan comprises a rotor hub (12), by which said rotor hub fan blades are attached and stretches mainly radially out from the rotor hub, and that at least one power unit (2)ear and at least one power transmission device (3) for transferring power from the power unit to the differentiated velocity fan and that said propulsion system is c h a r a c t e r i z e d i n that said propulsion system comprices a velocity fan or velocity fans that are arranged with their rotational axis perpendicular to the longituditional axis of the air vehicle and that the velocity fan has a length, b, and a diameter D, and that b <=D and that said propulsion_system comprises least one forward air duct (41) and at least one rearward air duct (42) for air are arranged to lead air from air intakes (5, 16) rearwards in the air vehicle in the forward air duct and the rearward air duct causing the static pressure to increase and the speed of the air decreases by widening of the forward air duct and thereafter the air led axially into the differential velocity fan that rotates and pushes the air out radially from the fan into the rearward air duct and the speed of the air successively increases in the rearward air duct by the successively decreasing of its cross section and the static pressure decreases, further a portion of the air is forced out through an opening (13) on the upper side of the air vehicle and gives an energized airflow (14) on the upper side of the air vehicle while the bulk part of the air passes through jet nozzles (6), that each is regulated by a nozzle flap/spoiler (1 1) and upper nozzle flap (10) and then said nozzles generates drag by the passage of air from the differential velocity fans passes through them. 2. Propulsion system for an air vehicle according to claim 1 c h a r a c t e r i z e d i n that it forward air duct is situated between the rearward ducts to make the air pass from the forward air duct axially into the differential velocity fan and further out radially from the forward air duct, the forward air duct is so shaped that the air in the forward air duct describes a spirally shaped motion with decreasing radius in the vertical plane and the air that is pressed out through the rearward air ducts describes a spirally shaped motion with increasing radius in the vertical plane. 22 3. Propulsion system for an air vehicle ch a ra cterize d in that the fan blades (27) are attached to the rotor hub (12) with an angle (29) relative to the normal (28) to the rotor hub (12) making them lean backwards, from the differential velocity fan's (4) rotation direction, and that the part of the fan blades (27) innermost closest to the rotor hub have a substantially straight profile and that they by their outer edge, furthest away from the rotor hub have a substantially curved profile (25) that makes them arched forward. 23 4. Propulsion system for an air vehicle according to claim 1 ch a ra cterize d i n that the differential velocity fan (4) has a separating wall/disc betweenleft and right side of the fan rotor (38) that separates the right and left side of it so that air cannot flow across the differentiated velocity fan (4). 5. Propulsion system for an air vehicle according to claim 1 ch a ra cterize d i n that the differential velocity fan's width (48) is less or equal to the differentiated differential velocity fan's diameter (47). 6. Propulsion system for an air vehicle according to claim 1 ch a ra cterize d i n that the fan blades have an aerodynamic design with a subsonic airprofile, said profile providing a robust and aerodynamically uncritical construction. |
Title:
PROPULSION SYSTEM FOR AN AERIAL VEHICLE
Document Type and Number:
WIPO Patent Application WO/2014/209198
Kind Code:
A4
Abstract:
The invention relates to a propulsion system concept that is a propulsion system that is integrated in the hull of an aerial vehicle (1), which propulsion concept comprises at least one differential velocity fan (4), which is arranged on a shaft driven by one or more power units (2). The propulsion concept is intended to provide short takeoff and landing distances, high flight speed (high subsonic to transsonic) and to be able to provide low IR signature, low radar signature, a small cross section and low air resistance. The propulsion concept is called HPVO (High Performance Optimized Versatile propulsion). The invention is useful both for air vehicles of the type for conventional takeoff and landing, "CTOL" (Conventional Take Off and Landing), "Chair" and for vertical takeoff and landing, "V (t) OL" (Vertical (Take) Off and Landing ') and the flying wing (blended-body). The concept is applicable to both large and small aircraft, manned as well as unmanned aerial vehicles.
Inventors:
PRISELL ERIK (SE)
Application Number:
PCT/SE2014/000090
Publication Date:
February 26, 2015
Filing Date:
June 25, 2014
Export Citation:
Assignee:
FÖRSVARETS MATERIELVERK (SE)
International Classes:
B64C15/02; B64C21/04; B64C21/06; B64C21/08; B64C39/02; B64U10/13; B64U50/00; B64U50/34
Attorney, Agent or Firm:
FÖRSVARETS MATERIELVERK (Stockholm, SE)
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Claims: