1. An aircraft comprising:
two parallel fuselages (2G, 2D) spaced symmetrically apart with respect to a longitudinal mid-plane (L-L);
a front lower wing (9) that is symmetric with respect to said longitudinal mid-plane (L-L) and supports the front lower parts of said fuselages (2G, 2D);
a rear upper wing (10) that is symmetric with respect to said longitudinal mid-plane (L-L) and is supported by the rear upper parts of said fuselages (2G, 2D); and
a propulsion system (11, 12, 13),
wherein:
at least the symmetric external parts (9G, 9D) of said front lower wing (9) have a sweep forward (\u03a6a);
the lift generated by said rear upper wing (10) is greater than the lift generated by said front lower wing (9);
said rear upper wing (10) is in direct contact with the rear upper parts of said fuselages (2G, 2D); and
said propulsion system (11, 12, 13) comprises at least one turboprop engine having at least one propeller and is carried by the internal part (10I) of said rear upper wing (10), the axis (l-l) of said propulsion system lying on said longitudinal mid-plane (L-L).
2. The aircraft as claimed in claim 1,
wherein the lift generated by said rear upper wing (10) represents at least approximately 60% of the overall lift generated by said aircraft, so that the lift generated by said front lower wing (9) represents at least approximately 40% of said overall lift.
3. The aircraft as claimed in claim 1,
and which comprises four sets of landing gear (5G, 5D, 7G, 7D) distributed at the front and rear of the two fuselages (2G, 2D) respectively.
4. The aircraft as claimed in claim 1,
wherein said propulsion system (11, 12, 13) comprises at least one turboprop with at least one pusher propeller (12) positioned behind said rear upper wing (10).
5. The aircraft as claimed in claim 1,
wherein said propulsion system (11, 12, 13) comprises at least one turboprop having at least one tractor propeller (13) positioned in front of said rear upper wing (10).
6. The aircraft as claimed in claim 4,
wherein said turboprop with at least one pusher propeller (12) and said turboprop with at least one tractor propeller (13) are enclosed in a common cell (11) borne by said rear upper wing (10).
7. The aircraft as claimed in claim 1,
wherein said rear upper wing (10) has a sweep forward (\u03a6r).
8. The aircraft as claimed in claim 7,
wherein said tractor propeller (13) is positioned in front of said rear upper wing (10) so as not to risk damaging it if any debris from said tractor propeller (13) or from the turboprop that drives it is thrown out.
9. The aircraft as claimed in claim 5,
wherein, facing said tractor propeller (13), each of said fuselages (2G, 2D) has a partially pressurized chamber (17G, 17D).
10. The aircraft as claimed in claim 9, in which each fuselage (2G, 2D) comprises a passenger cabin (4G, 4D) and a rear landing gear bay (8G, 8D) for said rear landing gear (7G, 7D),
wherein each partially pressurized chamber (17G, 17D) is located between the corresponding passenger cabin (4G, 4D) and the corresponding rear landing gear bay (8G, 8D).
11. The aircraft as claimed in claim 10, in which each passenger cabin (4G, 4D) is air-conditioned by a stream of air-conditioning air and has a discharge valve (22) capable of discharging said stream of air-conditioning air to outside said aircraft,
wherein said discharge valve (22) from said cabin can be made to close and to open and wherein the following are provided:
a communication (20) allowing a controlled flow of air between said passenger cabin (4G, 4D) and said chamber (17G, 17D), it being possible to instigate the opening and closure of said communication (20), and
an additional operable discharge valve (23) positioned in said chamber (17G, 17D) and capable of placing this chamber in communication with the outside of the aircraft.
12. The aircraft as claimed in claim 11,
wherein a safety device (21) guarding against overpressure is provided between said chamber (17G, 17D) and said rear landing gear bay (8G, 8D).
13. The aircraft as claimed in claim 1,
wherein the internal part (9I) of said front lower wing (9) has the shape of a circumflex accent that is symmetric with respect to said longitudinal mid-plane (L-L) and has the same sweep forward (\u03a6a) as said external parts (9G, 9D) of said front lower wing (9).
14. The aircraft as claimed in claim 13,
wherein the trailing edge of said internal part (9I) comprises a central cut-out (16).
15. The aircraft as claimed in claim 1,
wherein the internal part (9I) of said front lower wing (9) has the shape of a circumflex accent that is symmetric with respect to said longitudinal mid-plane (L-L) and has a sweep back that is the opposite of the sweep forward of said external parts (9G, 9D) of said front lower wing (9).
The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.
1. A motor vehicle, having a motor vehicle carcass body, and with a luggage area having a bottom and with two facing side panels, with a plurality of spaced apart elongated functional tracks disposed in each of the side panels, the functional tracks being arranged at least one of horizontally and vertically in the side panels, the functional tracks further being mounted flush to inside surfaces of the side panels, and being connected by support sections with parts of the motor vehicle carcass body, wherein the functional tracks are formed by profile units, that are connected by support sections (11) to carcass body parts (10).
2. The motor vehicle according to claim 1, further comprising fastening elements operably configured to be insertably received in and affixed to the functional tracks.
3. The motor vehicle according to claim 1, wherein the functional tracks (5 to 7) are arranged in corresponding pairs disposed opposite one another in the side panels (4).
4. The motor vehicle according to claim 1, wherein segmenting parts (8), which are at least one of vertically positionable and horizontally positionable, are provided, which are equipped with fastening elements matched to the fastening functions of the functional tracks (5 to 7).
5. The motor vehicle according to claim 1, wherein covering parts (8), which are at least one of vertically positionable and horizontally positionable, are provided, which are equipped with fastening elements matched to the fastening functions of the profile rails (5 to 7).