Search

CN-122009537-A - Thermal lock structure for space satellite

CN122009537ACN 122009537 ACN122009537 ACN 122009537ACN-122009537-A

Abstract

The invention discloses a thermal lock structure for an aerospace satellite, which comprises a first structural member, a second structural member, a thermal lock assembly, a winding assembly and a restraint belt. When the thermal knife fuses the restraint strap, the knife holder is retracted under the action of the spring, the stop pin synchronously releases the locking of the limiting piece on the winding roller, the winding roller rapidly rotates under the driving of the pre-tightening torsion spring, and the fused restraint strap is fully rewound into the closed cavity in the shell through the guide wire. The design ensures that the residue of the restraint strap generated in the separation process is actively contained and restrained, thereby fundamentally eliminating the risk that the residue freely flies into space garbage or interferes with the satellite body and the unfolding mechanism. The whole recovery process does not need extra energy, is driven by only relying on elastic potential energy pre-stored by a mechanism, has the advantages of high reliability, low impact and no secondary pollution, and obviously improves the safety and cleanliness of the on-orbit unlocking and releasing task of the spacecraft.

Inventors

  • ZHU SHIRONG
  • WANG ZHIJIE
  • ZE XIUMEI
  • ZHU CHENYING

Assignees

  • 贺得(上海)实业有限公司

Dates

Publication Date
20260512
Application Date
20260330

Claims (10)

  1. 1. A thermal lock structure for an aerospace satellite, comprising: the first structural member (0100) comprises a first butt joint surface (0101), and a positioning convex surface (0102) is arranged on the first butt joint surface (0101); the second structural member (0200) comprises a second butt joint surface (0201), and a positioning concave surface (0202) is arranged on the second butt joint surface (0201); The thermal lock assembly (0300) is arranged on the second structural member (0200), and comprises a hot knife (0301), a knife holder (0302) and a knife holder spring (0307), wherein the hot knife (0301) is arranged on the knife holder (0302), a stop pin (0308) is arranged on one surface, facing away from the hot knife (0301), of the knife holder (0302), and the knife holder spring (0307) is arranged between the second structural member (0200) and the knife holder (0302); The winding component (0400), the winding component (0400) is arranged on one surface of the second structural component (0200) opposite to the thermal lock component (0300), and comprises a shell (0401), a winding roller (0408) and a torsion spring (0412), wherein the shell (0401) is connected to the second structural component (0200), the winding roller (0408) and the torsion spring (0412) are arranged inside the shell (0401), two ends of the torsion spring (0412) are respectively connected to the winding roller (0408) and the shell (0401), a guide wire (0409) is connected to the winding roller (0408), the tail end of the guide wire (0409) protrudes out of the shell (0401), and a limiting part is fixed on the side surface of the winding roller (0408); a restraining belt (0500), wherein the restraining belt (0500) is connected to the guide wire (0409) and the inner edge is abutted against the hot knife (0301), and the restraining belt (0500) is used for pre-tightening the first structural member (0100) and the second structural member (0200); The stop pin (0308) extends into the shell (0401) and abuts the stop.
  2. 2. The thermal unlocking structure for space satellites according to claim 1, characterized in that the limiting element is a cam (0413), the lower end of the stop pin (0308) being circular arc-shaped and cooperating with the cam (0413).
  3. 3. The thermal unlocking structure for space satellites according to claim 1, wherein a torsion spring tensioning mechanism (0418) is arranged on the side face of the shell (0401), the torsion spring tensioning mechanism (0418) comprises a ratchet wheel (0419) and a driving wheel (0420) which are coaxially arranged, the ratchet wheel (0419) is arranged towards the inside of the shell (0401), the driving wheel (0420) is arranged towards the outside of the shell (0401), one end of the torsion spring (0412) is fixed to the ratchet wheel (0419), a stop pawl (0422) is arranged on the shell (0401) and is matched with the ratchet wheel (0419), and a driving groove (0421) is arranged on the driving wheel (0420) back to the ratchet wheel (0419).
  4. 4. The thermal unlocking structure for the space satellite according to claim 1, wherein the tool apron (0302) comprises a first seat plate (0304) and a second seat plate (0305) which are connected with each other, the thermal knife (0301) is installed on the first seat plate (0304), an adjusting gap (0306) is formed between the first seat plate (0304) and the second seat plate (0305), a guide post (0204) is arranged on one surface of the second structural member (0200) facing the tool apron (0302), the spring is sleeved on the outer edge of the guide post (0204), a bolt hole is formed in the middle of the guide post (0204), an adjusting bolt (0205) is arranged in the bolt hole, and a nut of the adjusting bolt (0205) is clamped in the adjusting gap (0306).
  5. 5. The thermal unlocking structure for space satellites according to claim 1, wherein a wire passing groove (0407) is formed in one side, away from the second structural member (0200), of the shell (0401), one end of a guide wire (0409) penetrates through the wire passing groove (0407) and is connected to the constraint belt (0500), protective covers (0423) are arranged on two sides of the wire passing groove (0407), and a closed space is formed inside the shell (0401) when the protective covers (0423) are closed.
  6. 6. The thermal unlocking structure for aerospace satellites according to claim 1, wherein the second structural member (0200) is symmetrically provided with guide shields (0206) on both sides, and the guide shields (0206) comprise guide grooves (0207) through which the restraining bands (0500) can pass.
  7. 7. The thermal unlocking structure for aerospace satellites according to claim 1, wherein the tool apron (0302) comprises a tool groove (0303), at least two parallel hot tools (0301) are installed in the tool groove (0303), and one end of the hot tools (0301) abutting against the restraining belt (0500) is provided with a chamfer.
  8. 8. The thermal unlocking structure for the space satellite according to claim 1, wherein one side of the second structural member (0200) close to the winding assembly (0400) is symmetrically provided with a mounting plate (0203), the mounting plate (0203) is rotationally connected to the second structural member (0200), the outer edge of the shell (0401) is provided with a mounting inclined surface (0402) matched with the mounting plate (0203), and the mounting inclined surface (0402) and the mounting plate (0203) are provided with coaxial bolt holes.
  9. 9. The thermal unlocking structure for aerospace satellites according to claim 1, wherein the housing (0401) further comprises: a detachable cover plate (0404) is arranged at the detachment opening (0403); the dismounting channel (0405) is used for the winding roller (0408) to pass through; The axial channel (0406), the axial channel (0406) is used for installing the wind-up roll (0408), one side of the axial channel (0406) facing away from the cam (0413) is provided with a first elastic piece (0416) and a second elastic piece (0417), the first elastic piece (0416) is axially arranged for pushing the wind-up roll (0408) to move towards the cam (0413), and the second elastic piece (0417) is circumferentially arranged for limiting the axial movement of the first elastic piece (0416); Convex edges (0410) are arranged at two ends of the winding roller (0408), the convex edges (0410) of the back-facing cams (0413) are matched with the second elastic piece (0417), the convex edges (0410) of the front-facing cams (0413) are provided with splines (0411), and a key groove (0414) is arranged on one surface of the front-facing cams (0413) of the winding roller (0408) and is matched with the splines (0411).
  10. 10. The thermal unlocking structure for space satellites according to claim 9, characterized in that the first elastic element (0416) and the second elastic element (0417) are in particular metallic bent sheets with elasticity.

Description

Thermal lock structure for space satellite Technical Field The invention relates to the technical field of spacecraft unlocking, in particular to a thermal unlocking structure for a space satellite. Background In the technical field of spacecrafts, in order to ensure the mechanical safety of satellites and loads thereof in a transmitting section, a plurality of parts are required to be in a locking state during transmitting, and unlocking and unfolding are performed after the satellites and loads are in orbit. The reliability of this unlock release function is directly related to the success or failure of the on-track task. Traditionally, initiating explosive device unlocking devices are adopted, separation is achieved by generating instantaneous explosive force, but the inherent limitations of large impact, high pollution risk and the like exist. In order to adapt to the precise spacecraft platform with increasingly higher requirements on clean and low-impact environments, a non-initiating thermal cutting unlocking device is generated. The device mainly comprises a high-strength restraint belt bearing pretightening force and a matched hot knife. After the unlocking instruction is received in the orbit, the hot knife is electrified to generate heat, and the constraint belt contacted with the hot knife is instantaneously fused, so that the mechanical constraint on the connected parts is relieved, and the mechanisms such as satellite orbit separation, solar wings and antennas are unfolded. The technology has become an important development direction of the unlocking mechanism of the modern spacecraft due to the advantages of small impact, no pollution and the like. However, the current widely-used hot cutting unlocking technology has a common defect that the technology only completes the fusing and unlocking function, and the design of effective on-track disposal of the residual section of the restraint strap in a free state after fusing is lacking. The residues are directly thrown into an orbit space to become potential space fragments, or remain nearby the spacecraft body to freely float, so that the residues are very easy to wind and hook in the subsequent posture adjustment of the satellite or the unfolding process of the mechanism, and serious potential safety hazards and interference risks are formed for the normal operation of the spacecraft. The unresolved problem of space debris restricts the further application of the hot cutting unlocking technology in high-reliability and high-cleanliness space missions. Disclosure of Invention Accordingly, in order to solve the above-mentioned problems, an object of the present invention is to provide a thermal lock structure for an aerospace satellite, comprising: the first structural member comprises a first butt joint surface, and a positioning convex surface is arranged on the first butt joint surface; the second structural member comprises a second butt joint surface, and a positioning concave surface is arranged on the second butt joint surface; the thermal locking assembly is arranged on the second structural member and comprises a hot knife, a knife holder and a knife holder spring, the hot knife is arranged on the knife holder, a stop pin is arranged on one surface of the knife holder, which is opposite to the hot knife, and the knife holder spring is arranged between the second structural member and the knife holder; the winding assembly is arranged on one surface of the second structural member, which is opposite to the thermal locking assembly, and comprises a shell, a winding roller and a torsion spring, wherein the shell is connected with the second structural member, the winding roller and the torsion spring are arranged inside the shell, two ends of the torsion spring are respectively connected with the winding roller and the shell, a guide wire is connected on the winding roller, the tail end of the guide wire protrudes out of the shell, and a limiting part is fixed on the side surface of the winding roller; and the restraint strap is connected to the guide wire, the inner edge of the restraint strap abuts against the hot knife, and the restraint strap is used for pre-tightening the first structural member and the second structural member. The stop pin extends into the shell and abuts against the limiting piece. Preferably, the limiting part is a cam, and the lower end of the stop pin is arc-shaped and is matched with the cam. Preferably, the side of the shell is provided with a torsion spring tensioning mechanism, the torsion spring tensioning mechanism comprises a ratchet wheel and a driving wheel which are coaxially arranged, the ratchet wheel is arranged towards the inside of the shell, the driving wheel is arranged towards the outside of the shell, one end of the torsion spring is fixed on the ratchet wheel, the shell is provided with a stop pawl which is matched with the ratchet wheel, and the driving wheel is provided with a driving groove