CN207732095U - A kind of space deployable reflector antenna bi-directional locking arrangement - Google Patents

Abstract

The utility model is related to a kind of space deployable reflector antenna bi-directional locking arrangement, the utility model includes end member, middle member, intermediate connector, compressed spring, pin.There are two the end members, is symmetrically distributed in the outside of locking mechanism, and bolt or screw can be used to be connected with fixing end, and equipped with the sleeve being connected with middle member；There are two middle members, is connected with end member by sleeve.The two-way pin of spring is provided in middle member, after being rotated in place, pin can be popped up and be locked, and the middle member other end is connected with intermediate connector by bolt or screw with ring flange.The utility model design is simple, easy to operate, and the locking of energy efficient stable effectively improves the fundamental frequency and surface accuracy of unfolding mechanism, ensures the smooth realization of satellite deployable structure function.

Description

A Two-way Locking Mechanism for Spatially Deployable Reflector Antenna

technical field

The utility model belongs to the field of aerospace technology, in particular to a two-way locking mechanism for a reflector antenna that can be deployed in space.

Background technique

With the development of the economy, the requirements for satellite capabilities are getting higher and higher, and the aperture of satellite antennas is also getting larger and larger. However, due to the limitation of the space size of the rocket's fairing, satellite deployable antennas are required. As shown in FIGS. 1 and 2 , the satellite deployable reflector antenna consists of an antenna 1 , a support arm 2 , a locking mechanism 3 and a base 4 . The expandable antenna is in a folded state when launching. After reaching the predetermined position in the space, the support arm will rotate around the fixed axis and unfold to the working state. At this time, a locking mechanism is required to fix the position of the support arm and provide structural support rigidity.

At present, this type of spring locking mechanism uses a traditional one-way pulling pin locking mechanism, and the pulling pin is pressed inside the locking mechanism by the antenna arm when the antenna is unfolded. When the antenna is unfolded in place, the support arm is blocked by the stopper, and the pull pin is ejected from the mechanism opening under the thrust of the spring, and inserted into the outside of the antenna support arm, so that the reverse movement of the antenna can be prevented. The article "Determination of the Deployment Impact Speed and Moment of the Satellite Antenna Reflector" pointed out that under the action of the spring force, pulling out the pin will increase the rotation speed of the antenna support arm, thereby increasing the impact force of the support arm and the stopper. Moreover, in the extreme high and low temperature conditions of the space orbit, the reflector antenna will have a certain deformation due to the change of temperature, and the deformation will act on the pin through the support arm, which will generate a force along the axial direction of the pin on the pin, and this force will cause the pin Move back sideways. This will reduce the stiffness of the antenna, while causing a large error in the antenna pointing.

In view of the shortcomings of the one-way pin-pull locking mechanism, the utility model proposes a two-way pin-inserted locking mechanism, which is located inside the rotating shaft of the antenna support arm. The pins lock the rotating shaft in a direction opposite to that of 180° at the same time. Because the mechanism adopts two pins, it has high locking rigidity, which can improve the pointing accuracy of the reflector under the high and low temperature of the track. At the same time, since the size of the spring and the pin is small, the impact force on the reflector and the support arm is very small when locked.

Contents of the invention

The purpose of the utility model is to provide a two-way locking mechanism for a spatially deployable reflector antenna.

The utility model includes two end components, two middle components, a connecting piece, four locking pins and two springs; the two middle components have the same structure, including a middle flange, a main shaft and a pin hole. One end of the main shaft is provided with a middle flange, and the other end is provided with a step, and a pin hole is opened on the step; the middle parts of the two end members are connected with the bottom support arm of the reflector;

The two end members have the same structure, and both include end flanges, sleeves, pin insertion holes and guide grooves. Inside the sleeve, the orbital position where the two locking pins rotate is provided with an annular pin guide groove. Two pin insertion holes are symmetrically arranged on the guide groove with the center of the guide groove as the center, and the pins in the pin holes of the end components are clamped.

The middle part of the connector is a hollow cylindrical central shaft, and the two ends of the central shaft are provided with connecting flanges; the middle flanges on the two middle members are respectively connected with the connecting flanges at the two ends of the connector; The steps on the middle member are respectively inserted into the sleeves of the two end members, and are connected to the end members through the guide groove; the end flanges on the two end members are fixedly connected to the base respectively; the middle member is connected to the base The part rotates around the axis of the sleeve of the end member as the center of rotation;

The locking pins are boss-shaped, four locking pins are set in the pin holes of the two middle components in pairs, two springs are respectively set in the middle of the pin holes of the two middle components, and the countersunk parts of the two locking pins The top surface is respectively fixedly connected with the two ends of the spring in the pin hole. The locking parts of the two locking pins can pass through the pin holes.

The two end members and the two middle members are symmetrically distributed on both sides of the connector.

Two outriggers are arranged in the middle of the two end members, and the two outriggers are arranged in parallel in the middle of the main shaft. Bolt connection holes are opened on the outriggers, and are connected with the bottom support arm of the reflector by bolts or screws.

Bolt connection holes are provided on the middle flange, and are connected to the connecting flange by bolts or screws.

Bolt connection holes are opened on the end flange, and the base is fixed by bolts or screws.

The spring is a high-strength compression spring.

The utility model solves the problem of small locking rigidity when the satellite antenna is unfolded in place. Compared with the existing satellite antenna unfolding and locking mechanism, the utility model realizes the two-way locking of the satellite antenna, and at the same time realizes the elimination of the locking gap, which can greatly improve the locking stiffness and improve the stability of the antenna. Pointing accuracy, less impact on the antenna when locked.

Description of drawings

Fig. 1 is a schematic structural diagram of a deployable satellite antenna in a locked state;

Fig. 2 is a schematic diagram of the structure of the expandable satellite antenna in an undeployed state;

Fig. 3 is a schematic diagram of the overall structure of the utility model;

Fig. 4 is a structural exploded view of the end member in Fig. 3;

Fig. 5 is the structural representation of middle member among Fig. 3;

Fig. 6 is an assembly drawing of the overall structure of the utility model;

Fig. 7 is a schematic structural view of the locking pin.

Detailed ways

Preferred embodiments of the present utility model will be described in detail below with reference to the accompanying drawings.

As shown in Figures 3 to 6, a space expandable reflector antenna two-way locking mechanism is arranged on the bottom of the reflector antenna, and the support arm at the bottom of the reflector is connected with the locking mechanism; the locking mechanism includes two end members 41, two Middle member 42, a link 43, four locking pins and two springs. The two middle members 42 are identical; the two end members 41 are identical; they are distributed symmetrically along the connecting piece 43 . The connecting piece 43 is arranged in the middle, and the middle part is a hollow cylindrical central shaft, and the two ends of the central shaft are provided with connecting flanges; Flange connection; the steps where the pin holes 5 on the two middle members are respectively inserted into the sleeves 14 of the two end members, and the end flanges 6-2 on the end members are fixedly connected with the base; the locking mechanism is fixed While on the base, it rotates with the central axis of the sleeve of the end member as the rotation center; the locking pin is arranged in the pin hole of the middle member.

The two middle components 41 both include a middle flange 6 - 1 , two outriggers 7 , a main shaft 13 and a pin hole 5 . One end of the main shaft 13 is provided with a middle flange 6-1, the other end is provided with a step, and a pin hole 5 is opened on the step; two outriggers 7 are arranged in parallel in the middle of the main shaft 13, and a bolt connection hole is opened on the outrigger 7 8. It is used to connect with the support arm at the bottom of the reflector through bolts or screws; the middle flange 6-1 has a bolt connection hole, which is used to connect with the intermediate connecting piece through bolts or screws. The diameter of the step where the pin hole 5 is located is the same as the inner diameter of the sleeve of the middle member, which is used to realize the cooperative installation of the middle member and the end member. After the installation of the mechanism is completed, due to the limitation of axial displacement, the middle member can only The member rotates around the axis. A fixed compression spring is placed in the middle of the pin hole, two pins are placed at both ends of the spring, and the top surfaces of the countersunk parts 11 of the two pins are respectively fixedly connected with the two ends of the spring. The locking portions 12 of the two locking pins can pass through the pin holes. During the deployment of the antenna (not fully deployed), the locking pin is always buried in the pin hole, and the compression spring is in a fully compressed state.

The two end members include end flanges 6 - 2 , sleeves 14 , pin insertion holes 9 and guide grooves 10 . Bolt connection holes are provided on the end flange 6-2 for fixing with the base 4 by bolts or screws. The inner diameter of the sleeve 14 is the same as the diameter of the step where the pin hole in the end member is located, and is used to realize the cooperative installation of the end member and the middle member. In the inside of the sleeve, an annular pin guide groove 10 is arranged at the orbital position where the locking pin rotates, which restricts the movement of the pin during use so that the pin can only rotate in a designated track. Two pin sockets 9 are set at the corresponding positions on the sleeve, and the two pin sockets are set on the guide groove 10, and are arranged symmetrically with the center of the guide groove 10 as the center; it is used to realize the pin hole of the end member after the antenna is fully deployed. The card position of the pin.

As shown in Figure 7, the locking pin is in the shape of a boss, the diameter of the countersunk part 11 is the same as the diameter of the pin hole in the two middle members, and the locking part 12 is the same as the pin insertion hole in the end member, so that the pin, the two middle members and the middle Coordinated installation of components.

The working process is as follows: during the launch phase, the satellite antenna is bound to the corresponding position of the rocket, the locking mechanism is in an unlocked state, the compression spring in the pin hole is in a fully compressed state, and the pin is completely buried in the pin hole.

When the satellite reaches the designated orbit, the antenna binding is released. Driven by the motor, the two middle components of the locking mechanism start to rotate, and the reflector antenna is driven to unfold through the support arm. During the unfolding process, the two compression springs in the pin holes of the two middle components are in a fully compressed state, and the locking parts of the two locking pins in each pin hole are in the sleeve guide grooves and rotate with the two middle components.

When the antenna is unfolded to the position where the pin holes on the two middle members are fully aligned with the pin insertion holes on the sleeve of the end member, under the push of the compressed springs in the two pin holes, the two locking pins in each pin hole pop out, and the two locking pins are locked. The pin locking part is inserted into the pin socket, restricting the rotational freedom of the reflector antenna, and completing the locking. At this time, the thrust force of the high-strength compression spring in the inner space of the sleeve has the effect of eliminating the gap between the pin locking part and the pin insertion hole.

Finally, it should also be noted that what is listed above is only a specific embodiment of the present invention. All deformations that a person of ordinary skill in the art can derive or associate directly from the content disclosed in the utility model shall be considered as the protection scope of the utility model.

Claims (6)

1. A space expandable reflector antenna two-way locking mechanism, comprising two end members, two middle members, a connector, four locking pins and two springs; it is characterized in that: the two middle members The structure is the same, including a middle flange, a main shaft and a pin hole; one end of the main shaft is provided with a middle flange, and the other end is provided with a step, and a pin hole is opened on the step; the middle part of the two end members and the bottom support arm of the reflector connect; The two end members have the same structure, and both include end flanges, sleeves, pin sockets and guide grooves; inside the sleeve, an annular pin guide groove is set at the orbital position where the two locking pins rotate; Two pin sockets are symmetrically arranged on the guide groove with the center of the guide groove as the center, and the pins in the pin holes of the end members are clamped; The middle part of the connector is a hollow cylindrical central shaft, and the two ends of the central shaft are provided with connecting flanges; the middle flanges on the two middle members are respectively connected with the connecting flanges at the two ends of the connector; The steps on the middle member are respectively inserted into the sleeves of the two end members, and are connected to the end members through the guide groove; the end flanges on the two end members are fixedly connected to the base respectively; the middle member is connected to the base The part rotates around the axis of the sleeve of the end member as the center of rotation; The locking pins are boss-shaped, four locking pins are set in the pin holes of the two middle components in pairs, two springs are respectively set in the middle of the pin holes of the two middle components, and the countersunk parts of the two locking pins The top surface is respectively fixedly connected with the two ends of the spring in the pin hole; the locking parts of the two locking pins can pass through the pin hole. 2. A two-way locking mechanism for a spatially deployable reflector antenna according to claim 1, wherein the two end members and the two middle members are symmetrically distributed on both sides of the connector. 3. A two-way locking mechanism for space-deployable reflector antennas as claimed in claim 1, characterized in that: two outriggers are arranged in the middle of the two end members, and the two outriggers are arranged parallel to the main shaft In the middle part, there is a bolt connection hole on the outrigger, which is connected with the bottom support arm of the reflector by bolts or screws. 4. A two-way locking mechanism for space-deployable reflector antennas as claimed in claim 1, characterized in that: said middle flange is provided with a bolt connection hole, which is connected to the connection flange by bolts or screws. 5. A two-way locking mechanism for spatially deployable reflector antennas as claimed in claim 1, characterized in that: said end flanges are provided with bolt connection holes, which are fixed to the base by bolts or screws. 6. A space-deployable reflector antenna two-way locking mechanism as claimed in claim 1, characterized in that: said spring is a high-strength compression spring.