JPH055699U - Landing gear for celestial bodies - Google Patents

Abstract

(57) [Summary] [Purpose] Make a soft landing on the celestial body with a simple structure. [Structure] A propulsion unit 12 for reverse injection is attached to the luggage 11. On the landing side 13 of this propulsion unit 12, a plurality of landing legs 1
4 is provided so that it can be deployed. A spring 15 is stretched between the landing leg 14 and the inside of the propulsion unit 12 to cushion the landing on the celestial body surface A.

Description

[Detailed description of the device]

[0001]

[Industrial application]

 The present invention relates to a device for softly landing luggage on a celestial body.

[0002]

[Prior Art]

 In recent years, experiments and research outside the atmosphere of the earth have become frequent, and it is expected that the active region in space will expand to celestial bodies such as the Moon and Mars. To be done.

In order to send a person or a load (payload) to such an celestial body, as shown in FIG. 4, the landing leg 2 provided on the spacecraft body 1 is extended and the injection nozzle 3 of the propulsion machine is reversely injected. It is common to perform soft landing while controlling the attitude. The landing leg 2 is formed so as to be capable of expanding and contracting in the longitudinal direction, and a spring 4 or the like is provided inside the landing leg 2 so as to absorb the impact at the time of landing.

[0004]

[Problems to be solved by the device]

 By the way, the conventional landing leg 2 has a relatively robust structure. This is because, in addition to cushioning during landing, it also has the function of maintaining the posture during launch (takeoff) by the injection nozzle 5 of the main propulsion unit.

However, in the case of softly landing only the luggage that does not return on the celestial body, such a large landing leg is not necessary, and it suffices to mainly perform the cushioning at the time of landing.

Therefore, in view of the above circumstances, the present invention was devised to newly provide a landing device for an celestial body that has a simple structure and does not cause excess equipment.

[0007]

[Means for Solving the Problems] The present invention is directed to a propulsion unit for injection attached to a luggage, a plurality of landing legs rotatably provided on the landing side of the propulsion unit, and the landing legs and propulsion. It is equipped with a spring that is stretched between the machine and the leg to urge the leg and the excavator to make a predetermined angle.

[0008]

[Action]

 With the above configuration, the luggage descends according to the appropriate reverse injection of the propulsion machine, and the landing legs are attached to the surface of the celestial body to land. At this time, the spring cushions the landing leg from expanding outward due to the impact of landing, and also holds the landing posture.

[0009]

【Example】

 Hereinafter, embodiments of the present invention will be described with reference to the accompanying drawings.

FIG. 1 and FIG. 2 show an embodiment of a luggage landing apparatus for a celestial body according to the present invention. This device is composed of an injection propulsion unit 12 attached to a luggage 11, a plurality of landing legs 14 rotatably provided on a landing side 13 of the propulsion unit 12, a landing leg 14 and an inside of the propulsion unit 12. It is mainly configured by a spring 15 stretched between them.

Two propulsion units 12 are provided so as to sandwich the luggage 11 from both sides, and a control device (not shown) for controlling the operation of the propulsion units 12 is provided, and the propulsion units 12 are directed to the landing side 13. An injection nozzle 19 is provided. That is, when landing, the jet force and jet time are appropriately changed to counteract the attractive force (gravitational force) of the celestial body and adjust to achieve a predetermined descent speed and descent posture.

The landing legs 14 are rods with a relatively small diameter, and in the present embodiment, a total of eight radial legs are provided. Each base end side is attached to the outer end portion of the propulsion unit 12 via a hinge 16, and a landing portion 17 slidable on the celestial body surface A is formed on the tip end side.

The spring 15 keeps the landing leg 14 at a predetermined angle θ in a normal position (during the descent), for example, in an inclined state in which the landing leg 14 is separated from the inner bottom surface of the propulsion unit 12 by about 120 degrees. In addition, it is configured to generate a biasing force that can appropriately absorb the impact at the time of landing.

In the present embodiment, each spring 15 has a pyrotechnic 18 attached thereto, and after the landing, the control device of the propulsion unit 12 appropriately ignites the spring 15 to disconnect it. There is. That is, the restriction on the outward deployment of the landing leg 14 is removed and the landing leg 14 is opened 180 degrees or more so that the luggage 11 can be completely grounded.

Next, the operation of this embodiment will be described.

When landing the luggage 11 from the mother ship or the like onto the celestial body surface A such as the moon, the propulsion machine 12 is jetted to maintain an appropriate posture and to descend at a predetermined speed in balance with gravity.

At the moment when the ground contact portion 17 of the landing leg 14 reaches the celestial body surface A, an upward force in the figure acts on the landing leg 14 and acts in a direction to expand the landing leg 14 outward. When the spring 15 resists this force, the impact force is substantially absorbed. The degree of this absorption is determined by the balance between the celestial body attraction force, the spring force of the spring 15 and the "hardness" of the hinge 16. In other words, the spring 15 and the hinge 16 should be formed so that a suitable cushion is obtained.

When the dynamic impact force is stopped by the unfolding operation of the landing leg 14, the dynamic impact force is held in the posture shown in FIG. The balance at this time is determined by the static load (weight on the celestial body) of the luggage 11 and the propulsion device, and the tensile force (spring force and member rigidity) of the spring 15 in the extended state.

Next, the springs 15 are cut, for example, every other one by the ignition of the pyrotechnic 18 to weaken the holding force of the landing legs 14, so that the luggage 11 is brought closer to the celestial body surface A, and Completely ground by cutting.

In this way, the propulsion unit 12 for injection is attached to the luggage 11, the deployable landing leg 14 is provided, and the spring 15 is stretched between the landing leg 14 and the propulsion unit 12. With such a configuration, the luggage 11 can be softly landed on the celestial body surface A. In other words, the conventional solid landing legs are no longer needed, which contributes to downsizing of landing equipment and reduction of manufacturing costs.

Further, in this embodiment, since the spring 15 is appropriately cut off so that the luggage 11 is grounded, the luggage 11 can be immediately stabilized after landing, and at the time of using the luggage 11. Since it is not necessary to lower the landing leg 14 from the state where it is supported, the subsequent handling becomes extremely easy. This cutting may be performed by igniting the pyrotechnic product by the impact at the time of landing.

Although depending on the scale of the luggage 11 and the length of the landing leg 14, the spring 15 is not cut even after landing and is left in the state of FIG. Alternatively, the propulsion unit 12 may be detached from the luggage 11 and then transported.

[0023]

[Effect of the device]

 In short, according to the present invention, the following excellent effects are exhibited.

Since the propulsion unit attached to the luggage, the landing leg provided so as to be deployable, and the spring stretched between the landing leg and the thruster are provided, the luggage can be lifted to the ceiling with a simple structure. Can be soft landed on the body.

[Brief description of drawings]

FIG. 1 is a side view showing an embodiment of a luggage landing apparatus for a celestial body according to the present invention.

FIG. 2 is a plan view of FIG.

FIG. 3 is a side view for explaining the operation of FIG.

FIG. 4 is a side view showing a conventional luggage landing apparatus for celestial bodies.

[Explanation of symbols]

 11 Luggage 12 Propulsion machine 13 Landing side of propulsion machine 14 Landing leg 15 Spring θ Predetermined angle

Claims (1)

[Claims for utility model registration] [Claim 1] A propulsion unit for injection mounted on luggage, a plurality of landing legs provided on the landing side of the propulsion unit so as to be deployable, the landing leg and the propulsion A luggage landing device for a celestial body, comprising: a spring that is stretched between the machine and a spring to urge the leg and the excavator so that the angle is a predetermined angle.