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CN-121990188-A - Separation method for light and small reentry and return cabin

CN121990188ACN 121990188 ACN121990188 ACN 121990188ACN-121990188-A

Abstract

The invention relates to a separation method for a light and small reentry and return cabin, which belongs to the technical field of reentry and return of spacecrafts, wherein a main detector firstly sends out a control instruction, and power supply and communication between the main detector and the return cabin are stopped; and the main detector stops gesture control, then sends out an unlocking command, returns to unlock the cabin, and drives the return cabin to separate. The amplitude of the motion of the return cabin around the non-spin axis is reduced through the attitude damping system on the return cabin, so that the attitude of the return cabin meets the reentry requirement. The invention adopts the electrical separation mode of the initiating explosive device cutter, namely the electrical separation mode of the cable between the cutter cabins of the initiating explosive device cutter can effectively avoid the abnormal conditions of uncertain service life, reduced separation reliability, vacuum cold welding and the like of the long-term on-orbit separation electrical connector of the return cabin, and realize reliable separation of electrical connection between the cutter cabins.

Inventors

  • WANG QIANG
  • LEI YINGJUN
  • ZHANG HE
  • ZENG FUMING
  • CHEN CHUNLIANG
  • LI HAIFEI
  • Fu zijing
  • ZHU WANG
  • LIU PI
  • MA BIN

Assignees

  • 北京空间飞行器总体设计部

Dates

Publication Date
20260508
Application Date
20260206

Claims (9)

  1. 1. The separation method for the light and small reentry and return cabin is characterized by comprising the following steps of: (1) The main detector sends out a control instruction, and power supply and communication between the main detector and the return cabin are stopped; (2) The main detector sends a cable cutting instruction at a set moment, and the cable between the cabin is cut off once; (3) And stopping gesture control by the main detector, then sending an unlocking instruction, unlocking the return cabin, and driving the return cabin to separate by the main detector.
  2. 2. The method according to claim 1, wherein in the step (2), the cable is cut by using a fire cutter.
  3. 3. A separation method for a lightweight miniaturized reentry pod as defined in claim 1, wherein in step (2) the main probe is mechanically coupled to the pod after the cable is cut.
  4. 4. The method according to claim 1, wherein in the step (2), after the cable is cut, the remaining cable is stored in the return compartment by the cable storage device and heat-sealed.
  5. 5. The method according to claim 1, wherein in the step (3), the posture control is stopped within one second before the unlocking and the separation.
  6. 6. The method of claim 1, wherein in the step (3), a spiral guide rail is provided on the main detector, and the return pod is driven to move along the spiral guide rail and be separated by screwing by a spring after the return pod is unlocked from the main detector.
  7. 7. The method of claim 1, wherein in step (3), the returning cabin is separated, and the returning cabin is moved around the non-spin axis by the on-cabin attitude damping system to reduce the amplitude of the returning cabin, so that the returning cabin attitude meets the reentry requirement.
  8. 8. The method of claim 7, wherein the attitude damping system is operated for no more than 20 minutes, and the return pod flies freely to the reentry point after the attitude damping system stops operating.
  9. 9. The method of claim 1, wherein in step (3), a separation point is set, and the main detector issues an unlock command after reaching the separation point.

Description

Separation method for light and small reentry and return cabin Technical Field The invention belongs to the technical field of reentry and return of spacecrafts, and particularly relates to a separation method for a light and small reentry and return cabin. Background Extraterrestrial celestial body sampling returns are an important form of detection for deep space exploration. The return cabin returns to the earth after the sampling of the extraterrestrial celestial body is completed along with the main detector, is separated from the main detector nearby the earth, and then independently flies for a period of time and then enters the earth atmosphere to safely land, so that the sample return is realized. For light and small reentry cabins, a posture control system is generally not provided under the condition of mass constraint, after the reentry cabins are separated from a main detector, the reentry cabins enter a free flight state, the posture of the reentry cabins is determined by disturbance introduced at the moment of separation, in order to ensure that the posture of the reentry cabins meets the reentry requirement, the posture disturbance of the reentry cabins caused by the separation process is restrained by the reentry cabins in a spinning motion mode by the aid of a spinning dead axle principle after separation, the posture of the reentry cabins cannot diverge after separation, and the reentry requirement of the posture can be met when the reentry cabins freely fly. The separation process typically includes electrical separation, mechanical separation, and spin-up of the return pod. As deep space probes fly to more far space, sample return tasks face the situation of longer in-orbit flight times and more severely constrained resources. The separation process reliability and safety of the connection separation device between the cabin are greatly influenced by environmental factors, the separation mode is required to be simple and reliable, the disturbance means for restraining the separation process of the light and small reentry cabin is less due to the constraint of quality resources, and the difficulty and the requirement for ensuring the reentry posture of the reentry cabin after free flight are high. The traditional spacecraft separation scheme has the following defects: 1) The traditional electrical connector is adopted between the cabin to realize electrical connection, after long-term on-orbit flying, the state of the electrical connector is uncertain due to environmental influence, the situation such as vacuum cold welding and the like can be generated, the uncertainty is large, the ground verification is difficult, and the reliable separation of the electrical connection cannot be ensured; 2) The back-and-forth cabin and the main detector are separated from the main detector, the back-and-forth cabin is rotated again after separation, the mode cannot determine the state of the return cabin during the rotation, and the state of the return cabin after the rotation is uncertain; 3) The method for ensuring the posture of the returning cabin by utilizing spin stabilization after separation has large mass, and the light and small returning cabin cannot support the scheme. And the returning cabin has small quality, so that the method has low attitude stability and precision, and the returning cabin reentry attitude uncertainty is large. Disclosure of Invention The invention aims to overcome the defects in the prior art and provide a separation method for a light and small reentry return cabin, which can realize reliable separation of electrical and mechanical structural connection between the return cabin and a main detector under the condition of resource limitation of the return cabin. The above object of the present invention is mainly achieved by the following technical solutions: a separation method for a lightweight compact reentry pod comprising the steps of: (1) The main detector sends out a control instruction, and power supply and communication between the main detector and the return cabin are stopped; (2) The main detector sends a cable cutting instruction at a set moment, and the cable between the cabin is cut off once; (3) And stopping gesture control by the main detector, then sending an unlocking instruction, unlocking the return cabin, and driving the return cabin to separate by the main detector. In the step (2), a fire cutter is adopted to cut the cable. In the step (2), after the cable is cut, the main detector is mechanically connected with the return cabin. In the step (2), after the cable is cut, the residual cable is stored in the return compartment by the cable storage device and heat-sealed. In the step (3), the posture control is stopped within one second before the unlocking separation. In the step (3), a spiral guide rail is arranged on the main detector, and after the return cabin is unlocked from the main detector, the return cabin is driven by a spring to move