JPH01172099A - Spreading latch mechanism - Google Patents

Abstract

PURPOSE:To hold only the outermost panel in the position 90 deg. spread and increase the generated electric power on a transfer locus in a spread latch mechanism such as a solar cell paddle to be used in the space. CONSTITUTION:When restraint or No.1 panel 1 situated outermost is released in the No.1 stage spread position, only No.1 panel 1 is spread with a hinge pin 7 as the center by a spring 22 incorporated in No.1 and No.2 hinge crevice metal pieces 4, 5. When the No.1 panel 1 attains the 90 deg. spread position, a latchup pin 10 of a latchup arm 9 is pressed to a latchup guide 8 by a leaf spring 21, and the spreading of the No.1 panel 1 is stopped by contacting of a contact adjusting screw 29 of pulley outer stopper 24 with a beam outer stopper 27. In the No.1 stage spread position thereafter, all panels 1-3 are liberated from restraint and spread.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a deployment mechanism for a deployable solar battery paddle that can be deployed, for example, in outer space.

[Conventional technology]

Figures 7 to 10 are diagrams showing the conventional unfolding mechanism, and show the member m (
It has a hinge structure in which the clevis fitting (41(5)) to which the clevis fitting (41(5)) is attached can be rotated freely through the hinge pin (7) and the bearing (Ill). A latch-up arm a equipped with a pin α2 is attached via a shaft +141, and a latch-up guide α5) is provided on the clevis fitting (5).

Furthermore, latch-up pin az is latch-up guide 0.
A spring σG is provided to pull the latch-up pin a'at in the direction of the hinge pin (7) in order to slide on the latch-up pin a'at and finally fit into the groove provided in the clevis fitting (5).

Next, the operation will be explained. In Figs. 7 and 8, member f
l) (2) shows the retracted state before deployment, but as the deployment of one member progresses, the latch-up pin (L2) is moved to the periphery of the thin semi-disc-shaped latch-up guide ttS by the action of the spring tte. Slide the adjacent parts (1) (2)
When the latch-up pin t is flush with the latch-up guide u9 (see Figures 9 and 10),
12 is a clevis fitting (5) that is supported by the tensile force of spring αe.
falls into a groove set in the At that time, use the clevis fitting (
The width of the groove provided in 5) becomes narrower as it goes deeper, as shown in Figure 8.

Latch-up is often completed with the latch-up pin Q2 biting into the groove. Since the groove is higher on the right edge than on the left edge, the latch-up pin Q2 will not pass through the groove during latch-up (latch-up can be performed reliably).

When the latch-up is completed, a locking force is obtained by the frictional force between the latch-up pin r1z and the groove, the tensile force of the spring wire, and the deployment surplus force, and the member +1) (2) is maintained at the predetermined deployed position. Ru.

[Problem that the invention seeks to solve]

In the conventional deployment latch mechanism as described above, two members (1
However, in recent years, as shown in Figure 6, in order to increase the power generated when the satellite (A) is flying in a transition orbit, external Only the solar battery panel (1) at the end is held in a 90 degree expanded state, and all panels (1) are expanded after entering the geostationary orbit.
1(21(31ση) has become necessary to deploy, but with the conventional deployment latch mechanism, it is difficult to hold the 90 degree deployed state once and then expand it another 90 degrees due to the structure of the two mechanisms. There was a problem.

This invention was made in order to solve the above-mentioned problems, and includes a deployment latch mechanism that can hold only the outer end panel at a 90 degree deployment position and then bring the other panels to the deployment state. The purpose is to obtain.

[Means for solving problems]

The deployment latch mechanism according to the present invention forms a pair with a first hinge clevis fitting fixed to a first panel serving as an outer end, and the first hinge clevis fitting.

a second hinge clevis fitting fixed to a second panel adjacent to the first panel; a third panel adjacent to the second hinge clevis fitting and adjacent to the second panel; a third hinge clevis fitting; a hinge pin rotatably connecting the first hinge clevis fitting and the second hinge clevis fitting; a third hinge clevis fitting that is coaxially attached to the hinge pin and applies a deployment force to the first and second panels; A pulley outer stopper is attached coaxially to the hinge pin and integrally provided on the peripheral edge.

A pulley for synchronizing deployment having a pulley inner stopper and a contact adjustment screw, a latch-up guide provided on the second hinge clevis fitting and having a step at the 90-degree deployed position on its periphery and a groove at all deployed positions; 1st above
It is rotatably attached to the hinge clevis fitting by a pin built in parallel to the hinge pin, and the other end slides on the latch-up guide and when the first panel is unfolded 90 degrees, the above-mentioned It fell into the step at the 90 degree deployment position on the latch-up guide.

a latch-up arm having a latch-up pin that engages with a groove at the 180-degree deployed position on the latch-up guide when deployed 180 degrees; provided between the latch-up arm and the first hinge clevis fitting; A leaf spring that acts to press the latch-up pin onto the latch-up guide, which is fixed to the first hinge clevis fitting and hits the contact adjustment screw attached to the pulley outer stopper at the 90-degree expanded position. A beam outer stopper that stops the first panel from unfolding beyond 90 degrees is fixed to the third hinge clevis fitting at 90 degrees.
and a beam inner stopper that absorbs the impact force transmitted to the pulley when the beam outer stopper stops the first panel from unfolding.

[Effect]

The deployment latch mechanism in this invention is provided integrally with the second hinge clevis fitting fixed to the second panel,
The above-mentioned latch-up guide, which has a step at the 90 degree unfolded position and a groove at all unfolded positions, accompanies the first stage unfolding of only the first panel at the outer end.

Rotate while guiding the latch-up pin of the latch-up arm, which is rotatably incorporated into the first hinge clevis metal fitting that pairs with the second hinge clevis metal fitting.
The beam outer stopper provided on the first clevis fitting is in contact with the pulley outer stopper provided on the pulley coaxial with the hinge pin. Stop the deployment by hitting the lll adjustment screw, and at the same time, at the 90 degree deployment position of the first panel at the outer end, the latch wrap bin falls into the step of the latch up guide at the 90 degree deployment position. As a result, the first panel at the outer end is stopped and held at the 90 degree unfolded position. When the other panels begin to unfold in the second stage of deployment, the third hinge clevis fitting and the second hinge clevis fitting adjacent thereto are separated (
This causes the pulley inner stopper provided on the pulley to come into contact with the beam inner stopper provided on the third hinge clevis fitting, allowing the pulley to rotate in synchronization with the expansion of other panels. first end
The panel starts unfolding again in the same way as the other panels, and when the full deployment is completed, the latch-up pin catches the groove in the latch-up guide at the fully deployed position, and the latch is performed.

〔Example〕

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

In Figure 1 (Ill) and (b), (1) is the first panel at the outer end.

(2) is a second panel adjacent to the first panel (1),
(3) is the third panel adjacent to the second panel (2),
(41 (51 is the first and second panel fl)
(2) first and second hinge clevis fittings connecting the panels, and (6) a third hinge clevis fitting connecting the third panel (3) to a further inner panel (not shown);
(7) indicates the first and second hinge clevis fittings (4).
) The hinge pin (8), which is the center of rotation of (5), is fixed to the second hinge clevis fitting (5) and has a step at the 90-degree deployed position A.

The latch-up guide (9) has a groove in all deployed positions, and the hinge pin (7) is attached to the first hinge clevis fitting (4).
Parallel to ) is the latch-up arm rotatably fixed by the bin QO, α0) is the attachment pin, (21
+ is the latch-up arm (9) latch-up guide (
8) (plate spring, 02 is the first hinge clevis fitting (4) and second hinge clevis fitting (5) A helical spring (c23) which provides a deployment force through a pulley (the deployment synchronization mechanism is not shown) which performs deployment synchronization, (the side is
(C) is a pulley outer stopper that stops the expansion of panel 11 at the 90-degree expanded position, and (c) is the pulley inner stopper that transmits the impact when the 90-degree expansion is stopped to the third panel.

(5) is the pulley outer stopper (2) when unfolded at 90 degrees.
4).

A beam outer stopper is provided on the first hinge clevis fitting (4) to stop the first panel (1) at the outer end on the adjustment screw (2) for adjusting the 90 degree expansion stop position. This is a beam inner stopper provided on the third hinge clevis fitting (6) to receive the impact of the pulley inner stopper (c).

Next, the operation will be explained.

FIGS. 1(a) and 1(b) show the state before deployment. (See Figure 6, upper right diagram) In the first stage of development, the first
When the restraint of panel (1) is released (the mechanism involved in holding and releasing the panel is not shown), the first and second
Only the hinge pin (the first panel fl at the outer end with the force as the center of rotation) starts to expand due to the energy of the spring (c) incorporated in the hinge clevis fittings (4) and (5).

When the deployment progresses and the 90 degree deployment position is reached (Figure 2), the latch-up pin a of the latch-up arm (9) is moved toward the latch-up guide (8) by the leaf spring c! The first panel (1
) is stopped at the 90-degree deployed position when the hit adjustment screw (c) provided on the pulley outer stopper t2 comes into contact with the beam outer stopper, and at the same time the latch-up guide (8) is rotated at 90 degrees. The latch-up pin θ [is the leaf spring C! By falling due to the action of η, reverse rotation in the storage direction is also restrained. The impact of this hit is applied to the pulley (through 2j), the pulley inner stopper C9, the beam inner stopper (goods), the third hinge clevis fitting (6), and the third
The information is transmitted to panel (3).

This interrupts deployment of the outer end first panel and holds it in the position of FIG. 2. (Figure 6(b)) Next, in the second stage of deployment, when all other panels including the first, second, and third panels (11(2), (3)) are released, By the energy of a spring (not shown) incorporated in each hinge, the first, second, and third panels f
l) (2) All other panels (including 31e) begin to unfold, and the second panel (2) and the third panel (3) adjacent thereto move away from each other, and the pulley ) is released from the rotation restraint by the beam inner stopper (281) (FIG. 3).Then, the first, second and third beams are released.
The third hinge clevis fitting (41 (51) (61) and all other hinge clevis fittings (not shown) are regenerated by the energy of a spring (not shown) incorporated in the third hinge clevis fitting (41 (51) (61)).

Start deployment.

At the same time, the latch pin 0 of the latch-up arm (9) begins to slide while being pressed against the latch-up guide (8) by the action of the leaf spring c+++.

(Figures 4 and 6 (C)) Then, the adjacent panels (for example, the first panel (1) and the second spring /l/ (21) are in the fully expanded position (flush state)
When the latch-up pin 0Q reaches the fully deployed position, the latch-up pin 0Q engages with the groove A on the latch-up guide (8), and the deployment is completed. (Figs. 5 and 6(d)) [Effects of the Invention] This invention provides a beam outer stopper, an adjacent beam outer stopper, and a first hinge clevis fitting illustrated in the first panel at the outer end of the through hole as described above. The third hinge clevis fitting is equipped with a beam inner stopper, the deployment synchronization pulley (C) is equipped with a pulley outer stopper (C), a pulley inner stopper (C), and a contact adjustment screw (C).

Compared to conventional hinges, with a simple modification, only the first panel at the outer end can be stopped and held at the 90-degree deployed position, which has the effect of increasing the power generated during the transition orbit of the satellite. .

[Brief explanation of the drawing]

Figures 1 to 6 are diagrams showing one embodiment of the present invention.
Figure (8) is a front view in the Kakuen state, the side view in Figure 1 (1)), and Figure 2 is a front view in the middle of the second stage of development. Figure 3 is a front view after the start of the second stage deployment, Figure 4 is a front view of the second stage deployment.
Figure 5 is a front view in the middle of staged deployment, Figure 5 is a front view of the fully deployed state, and Figure 6 is an overall view of the satellite body and deployable solar array paddle in each state to supplement Figures 1 to 5. be. Figures 1 to 10 are diagrams showing the conventional deployment latch mechanism.
8 is a front view of the stored state, and FIG. 9 is a front sectional view of the unfolded state. FIG. 10 is a plan view of the state after development. In the figure (1) (21 (3) is the panel, (4)
(5) (6) is a hinge clevis fitting, (71 is a hinge pin, (8) is a latch-up guide, (9) is a latch-up arm, (10) is a latch-up pin, (2B is a leaf spring, @ is a pin) The same symbols in the figures indicate the same or equivalent parts.

Claims (1)

[Claims] In the deployment latch mechanism of a deployable solar array paddle having a plurality of panels that can be deployed in outer space, a first hinge clevis fitting fixed to a first panel serving as an outer end;
a second hinge clevis fitting paired with the first hinge clevis fitting and fixed to a second panel adjacent to the first panel; a third hinge clevis fitting fixed to the third panel adjacent to the panel; a hinge pin rotatably connecting the first hinge clevis fitting and the second hinge clevis fitting; a hinge pin coaxially attached to the hinge pin; A coiled spring that provides a force for deploying the first and second panels, a pulley outer stopper and a pulley inner stopper that are coaxially attached to the hinge pin and are integrally provided on the peripheral edge, and a hit provided on the pulley outstopper. A pulley for synchronizing deployment having an adjustment screw, a latch-up guide fixed to the second hinge clevis fitting and having a step at the 90-degree deployed position and a groove for engagement at the 180-degree deployed position, one end. is rotatably attached to the first hinge clevis fitting by a pin incorporated in parallel with the hinge pin, and the first panel slides on the latch-up guide at the other end, and the first panel is attached at 9.
A latch-up pin that falls onto the step at the 90-degree deployed position on the latch-up guide when deployed at 0 degrees, and engages with a fitting groove at the 180-degree deployed position on the latch-up guide when deployed 180 degrees. a leaf spring provided between the latch-up arm and the first hinge clevis fitting and acting to press the latch-up pin onto the latch-up guide;
A beam outer stopper that is fixed to the first hinge clevis fitting and stops the first panel from expanding beyond 90 degrees by hitting the adjustment screw at the 90-degree expanded position, and fixed to the third hinge clevis fitting. and a beam inner stopper that absorbs the impact force transmitted to the pulley when the beam outer stopper stops the first panel from unfolding when the first panel is unfolded at 90 degrees.