JPH0419298A - Support structure for telescope for space navigating object - Google Patents

Abstract

PURPOSE:To reduce the weight of a lower support part, resulting in reduction of the weight of the whole of a telescope, by providing the modulus of elasticity high necessary to absorption of a thermal strain generated on an orbit and forming an upper support part providing strength and rigidity durable to vibration and impact environment during launching. CONSTITUTION:A stay 5 has the modulus of elasticity capable of absorbing a strain produced due to a difference in the coefficient of thermal expansion between a space navigation object 2 and a telescope 1. A pipe 6 hung down from the space navigating body 2 is formed in a hollow cylindrical shape with which the stay 5 is surrounded, and is secured to the space navigating object 2. A piezoelectric element 7 is mounted on the end surface of a pipe 6, and is formed in a hollow cylindrical shape expandable in the axial direction of the pipe 6. During launching of the space navigating object 2, the piezoelectric element 7 at the tip of the pipe 6 is expanded in an axial direction and presses a telescope 1 with a pressure for securing. On an orbit, the piezoelectric element 7 is contracted in an axial direction to release the telescope 1 from a constraining force thereon, and a strain generated due to a difference in the coefficient of thermal expansion between the space navigating object 2 and the telescope 1 is absorbed by the stay 5. This constitution reduces the weight of a lower support part 4.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a support structure for supporting a telescope mounted on a spacecraft.

[Conventional technology]

Conventionally, in the support structure of this type of telescope, as shown in FIG.
The structure was designed to absorb the strain caused by the difference in thermal expansion coefficient between the spacecraft and the spacecraft.

[Problem to be solved by the invention]

In the conventional telescope support structure described above, the upper support part does not contribute to the strength and rigidity necessary to withstand the mechanical environment during launch, in order to maintain an elastic modulus that can absorb thermal strain in orbit. Although most of the strength and rigidity required during launch is provided by the lower support, the weight of the lower support increases, making it difficult to reduce the weight of the entire telescope.

[Means to solve the problem]

The support structure for a telescope for a spacecraft of the present invention is provided between the spacecraft and the telescope in the upper support part, has high strength and rigidity in the axial direction, and has high strength and rigidity in the direction perpendicular to the axial direction. A support having an elastic modulus that absorbs strain due to a difference in coefficient of thermal expansion between the spacecraft and the telescope, a hollow pipe suspended from the spacecraft so as to surround the support, and the pipe. a piezoelectric element provided on an end face on the telescope side of the pipe, the piezoelectric element being expandable in the axial direction of the pipe, expanding during launch to apply a restraining force to the telescope, and contracting during orbit to release the restraining force; and a lower support portion for fixing a lower portion of the spacecraft to the spacecraft.

〔Example〕

Next, the present invention will be explained with reference to the drawings.

Figures 1 and 2 are a front view and a perspective view including a cross section of essential parts of an embodiment of the present invention, and Figures 3 (a) and (b) show the state of this embodiment at launch and on orbit. FIG.

The support 5 installed between the telescope 1 and the spacecraft 2 has high strength and rigidity in the axial direction, and supports the spacecraft 2 and the telescope 1 that occur on the orbit in the lateral direction perpendicular to the axial direction. It has an elastic modulus that can absorb the strain caused by the difference in the coefficient of thermal expansion.

The vibro, which is suspended from the spacecraft 2, has a hollow cylindrical shape that surrounds the support column 5 with sufficient clearance, and is fixed to the spacecraft 2 with screws. The piezoelectric element 7 is attached to the end face of the vibro on the telescope 1 side, and has a hollow cylindrical shape that can be expanded and contracted in the axial direction of the vibro. The lower support part 4 is integral with the telescope 1 and is fixed to the spacecraft 2 with screws.

In this embodiment, when the spacecraft 2 is launched, the piezoelectric element 7 at the tip of the vibro is extended in the axial direction, and the telescope 1 is firmly pressed and fixed, as shown in FIG. 3(a). In addition, while in orbit, as shown in FIG. 3(b), the piezoelectric element 7 is compressed in the axial direction to release the restraining force on the telescope 1.
The strut 5 absorbs strain caused by the difference in thermal expansion coefficient between the spacecraft 2 and the telescope 1.

In this way, according to this embodiment, the upper support part 3 has elasticity to absorb thermal strain on orbit and exerts a high restraining force during launch, so the lower support part 4 can be made lighter. .

〔Effect of the invention〕

As explained above, the present invention provides a support structure for a telescope for spacecraft that has an elastic modulus necessary to absorb thermal strain generated in orbit, and has enough strength to withstand the vibration and shock environment during launch. - By configuring the upper support part that can take on rigidity, the weight of the lower support part can be reduced, and the weight of the entire telescope can therefore be reduced.

[Brief explanation of drawings]

Figures 1 and 2 are a front view and a perspective view including a cross section of essential parts of an embodiment of the present invention, and Figures 3 (a) and (b) show the state of this embodiment at launch and on orbit. FIG. 4 is a front view including a cross section of the main parts shown, and FIG. 4 is a perspective view showing an example of a support structure of a conventional spacecraft telescope. 1... Telescope, 2... Space antibody, 3.8... Upper support part, 4゜9... Lower support part, 5... Pillar, 6... Pipe, 7... Piezoelectricity element.

Claims (1)

[Claims] The upper support part is provided between the spacecraft and the telescope, and has high strength and rigidity in the axial direction, and in the direction perpendicular to the axis, there is a difference in the coefficient of thermal expansion between the spacecraft and the telescope that occurs on the orbit. a strut having an elastic modulus that absorbs the strain caused by the
A hollow pipe is installed vertically from the spacecraft so as to surround this support, and a hollow pipe is provided on the end surface of the pipe on the telescope side, and is extendable and retractable in the axial direction of the pipe, so that it can be expanded and retracted at the time of launch. A piezoelectric element that applies a restraining force to the telescope and releases the restraining force by contracting in orbit, and a lower support part that fixes a lower part of the telescope to the spacecraft. Telescope support structure.