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any apparatus attached to the aircraft structure oscillates between - 5*10-2 and + 5*10-2
g (z-axis) and between - 10-2 and + 10-2 g (x- and y-axis).
A small object free floating in the cabin may benefit from a higher quality of
weightlessness (microgravity less than 10-4 g) for a period of five to ten seconds, i.e.
until it touches the walls of the aircraft. This is called the free-float technique
necessitating at least one person from the safety crew as additional assistance.
A300 Zero-G Parabolic Flight Technique Chapter 2
Edition 5.2 2.3
The piloting techniques may be, up to a technically realizable degree, adapted to the
needs of the experimenters.
The different techniques are:
a) Standard technique where the crew is trying to obtain a level of microgravity
as close to zero as possible (in average and in amplitude) and as long as
possible.
b) The procedure to minimize negative microgravity values, called soft
procedure.
c) The procedure to keep a residual gravity (of low or high value).
d) The free-float procedure where the piloting is done with respect to keeping
an object free-floating in the middle of the cabin (visible for the pilots on a
video screen).
The application of procedures which are not standard ones may result in parabolas of
minor quality, i. e. of reduced duration. As these techniques might necessitate a special
training or material (especially the last two ones, c and d) and therefore generate
additional cost for the user, the interested experimenters are highly recommended to
contact Novespace early before a campaign to express their needs.
Edition 5.2 3.1
Experimentation Chapter 3
Area Description
In this chapter we present the resources of the aircraft. These resources (room
availability, electric power, venting...) are to be shared by different experiments.
Although it seems obvious, we would like to emphasize the fact that unless the entire
aircraft is commissioned by one single company, all experimenters are obliged to share
the aircraft resources. Hence, the aircraft will not be entirely at one's disposal. In a
standard campaign, 10 to 15 different experiments share global resources.
3.1 Cabin dimensions (See Figures 2, 3, and 4)
The testing cavity is 20 meters in length, 5 meters in width, and 2.3 meters in height
(see figures 2, 3, and 4). The second front door, through which equipment is loaded, is
1.93 m high by 1.07 m wide. An experiment being larger than the door may be loaded
by being taken apart.
The total volume of the cabin is 300 m3.
Experimentation Area Description Chapter 3
Edition 5.2 3.2
Fig. 3 - Bi-Section of Aircraft Cabin
Fig.2 - Upper View of the Cabin
video gaz and liquid electrical supply
camera exhaust pannel
Experimentation Area Description Chapter 3
Edition 5.2 3.3
Fig. 4 - Cross Section of Aircraft Cabin - Position of attachment rails
Experimentation Area Description Chapter 3
Edition 5.2 3.4
3.2 Environment
Cabin pressure is maintained at approximately 800 mb during parabolic maneuvers. A
further loss of cabin pressure must be considered in the design of the test equipment.
Normally, cabin temperature varies from 18 to 25 degrees Celsius in flight. The
temperature in the cabin is not controlled while the airplane is on the ground.
Lights are installed in the aircraft test section. These are sufficient to support
photography of most open test equipment.
The interior walls of the cargo compartment are covered with foam padding for the
protection of personnel and equipment.
3.3 Electrical Power and Interfaces
The following electrical power is available in the test section of the aircraft :
1. 220 volt AC, 50 Hz, single phase 2 kVA per electric panel x 10
(20 kVA total)
2. 28 volt DC 20 amps per electrical panel x 5
(100 amps total)
3. 115-200 volt AC, 400 Hz, three phase on early request
The aircraft electrical test power is distributed to ten power distribution panels along the
lower side walls of the test section. All power and ground leads from test equipment to
the panels should be 6 meters long. The 50 Hz AC power leads require the standard
French grounded plug. The 28V DC requires a Souriau 840-23-832 connector:
terminal 1 = +28 V, terminal 2 = ground. All exposed power leads and electrical
contacts should be covered to protect personnel and equipment.
Experimentation Area Description Chapter 3
Edition 5.2 3.5
In specific cases and if available, power exceeding 2kVA can be furnished. A Souriau
840-45-810 connector and a Souriau 840-40-004 rear connector are necessary in these
cases.
On ground an external power supply is provided allowing to light up the aircraft inside
　
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