JPH0867300A - Split type inter-orbit transport aircraft - Google Patents

Abstract

(57) [Summary] (Correction) [Purpose] Divided orbits that can secure a sensor field of view and a docking surface by providing a sensor and a docking surface in the traveling direction of the inter-orbit transport aircraft. Provide transport aircraft. [Structure] A sensor 2 and a docking mechanism unit 4 fixedly arranged at a front portion of a payload support structure 1, and
It comprises a propulsion device fixedly arranged at the rear of the payload support structure.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a split type inter-orbit transport aircraft for transporting payload between various orbits in space.

[0002]

2. Description of the Related Art A conventional inter-orbit transport aircraft is shown in FIG.
It has a configuration as shown in. In FIG. 4, 11
Is an inter-orbit transport aircraft, 12 is an arrow indicating the transportation direction, 13 is a payload support structure, 14 is a payload, 15 is an optical sensor, and 16 is a thruster.

That is, the conventional inter-orbit transport aircraft 11 has a payload support structure 13 arranged at the front thereof.

[0004]

As described above, since the conventional inter-orbit transport aircraft 11 has the payload support structure 13 arranged at the front thereof, that is, the inter-orbit transport aircraft 1
There is a payload 14 in the traveling direction of 1, and the optical sensor 15
Had a problem that it could not secure the field of view and could not secure the docking surface in the traveling direction.

The present invention is intended to solve the above problems. That is, the present invention is to provide a split type inter-orbital transportation device that can provide a sensor and a docking surface in the traveling direction of the inter-orbital transportation device, and can secure a sensor field of view and a docking surface. It is intended.

[0006]

To achieve the above object, the present invention comprises a sensor and a docking mechanism fixedly arranged at the front of the payload support structure, and at the rear of the payload support structure. It is assumed that the propulsion device is fixedly arranged.

[0007]

According to the present invention, since the sensor and the docking mechanism portion fixedly arranged at the front portion of the payload supporting structure are provided, and the propulsion device fixedly arranged at the rear portion of the payload supporting structure is provided. The front of the sensor and the docking mechanism, that is, the front in the traveling direction, has no obstacle, and a sufficient field of view is secured.

[0008]

1 is a side view showing an embodiment of the present invention, FIG. 2 is a front view, and FIG. 3 is a rear view. In FIG. 1, 1 is a payload support structure, 2 is an optical sensor, 3 is an antenna, 4 is a docking mechanism part, 5 is a propulsion device, 6 is a thruster, 7 is a payload, and 8 is an arrow indicating a transportation direction.

That is, the payload support structure 1 is provided with an optical sensor 2 and a docking mechanism portion 4 which are fixedly arranged at the front portion thereof, and a propulsion device 5 which is fixedly arranged at the rear portion of the payload support structure 1. There is.

In the inter-orbit transport aircraft constructed as shown in FIG. 1, the optical sensor 2, the docking mechanism portion 4 and the like and the propulsion device 5 are divided into a front portion and a rear portion with the payload support structure 1 in the middle. In addition, since the optical sensor 2, the antenna 3, and the docking mechanism unit 4 are arranged in the front portion, there is no obstacle in front of the traveling direction, and a sufficient field of view is secured.

It should be noted that the payload support structure 1 may be designed and changed to an optimum size according to the size and shape of the payload 7.

[0012]

As described above, according to the present invention,
The payload or the payload support structure is large because it has a sensor and a docking mechanism part fixedly arranged at the front part of the payload support structure and a propulsion device fixedly arranged at the rear part of the payload support structure. However, there is no obstacle in front of the sensor and the docking mechanism portion, and the field of view of the sensor and the docking surface of the docking mechanism portion can be secured.

[Brief description of drawings]

FIG. 1 is a side view showing an embodiment of the present invention.

FIG. 2 is a front view of FIG.

FIG. 3 is a rear view of FIG. 1;

FIG. 4 is a side view showing an example of a conventional technique.

[Explanation of symbols]

 1 Payload Support Structure 2 Optical Sensor 4 Docking Mechanism 5 Propulsion Device

Claims (1)

[Claims] 1. A payload supporting structure is provided with a sensor and a docking mechanism part fixedly arranged at a front part thereof, and a propulsion device fixedly arranged at a rear part of the payload supporting structure. , Split type inter-orbit transport aircraft.