Reusable spaceship parachute distance-reducing soft landing device

Abstract

The invention discloses a reusable spaceship parachute distance shrinkage soft landing device, and belongs to the technical field of spacecraft recovery landing. Comprising a distance reducing device, the distance reducing device is arranged below a parachute bay and in the side wall of a reentry capsule, the distance reducing device comprises a firer push rod arranged in the middle, the upper end and the lower end of the firer push rod are each provided with an upper assembly and a lower assembly, the upper assembly and the lower assembly are each provided with four pulleys, and a parachute cord sequentially penetrates through the pulleys. The length of a parachute cord in the device is increased through extension of the firer push rod, the distance between the reentry capsule and the parachute is shortened, and distance shrinkage is achieved. The firer push rod is adopted as a driving device, the energy density is high, the weight and complexity of the mechanism are reduced, and the carrying efficiency of the reentry spacecraft is improved. In addition, the distance reducing device is small in occupied space, and the working length of the distance reducing device is increased. The system complexity can be reduced, and astronauts can leave the cabin in time. And meanwhile, the method has the characteristics of high accuracy, less possible interference and high reliability.

Description

Technical Field

[0001] The invention relates to the technical field of spacecraft recovery and landing, and in particular to a reusable spacecraft parachute retraction soft landing device. Background Art

[0002] At present, the technical approaches of reusable spacecraft recovery and landing systems at home and abroad mainly include five forms: parachute deceleration, controllable parafoil fixed-point non-destructive landing, inflatable attachment deceleration landing, power deceleration + soft landing bracket buffer, landing gear + drag parachute. Manned spacecraft recovery and landing technology has distinct characteristics and higher requirements. At present, the return spacecraft generally adopts parachute deceleration + reverse rocket as a soft landing method, but this solution has some problems, such as the reverse rocket needs to open a hole in the bottom of the return cabin, which may have structural strength problems; the heat-resistant bottom must be discarded before the reverse rocket works, which increases the complexity of the system; and the reverse rocket causes dust, which affects the astronauts' timely exit from the cabin.

[0003] The meaning of the parachute retraction soft landing technology is to quickly shorten the rope between the parachute and the payload when the payload descends very close to the ground to shorten the distance between the two, thereby reducing the descent speed of the payload and achieving a soft landing. This technology is currently a relatively new soft landing technology. If it is applied to the soft landing of the spacecraft return capsule, it is expected to achieve good results.

[0004] At present, the existing reduced-pitch soft landing devices are mainly used in the field of airborne landing, and have not yet been used in the field of spacecraft return. In addition, the existing devices are large in size and weight, which is not conducive to the reliability and reusability of the devices, and does not meet the requirements of spacecraft to save space and weight as much as possible. In addition, the return capsule often has a hanging conversion process, and the reduced-pitch device is set on the external parachute rope, which is not conducive to the release and opening of the parachute. Summary of the invention

[0005] The purpose of the present invention is to provide a reusable spacecraft parachute retraction soft landing device, which solves the problem that the existing devices have not been applied to the field of spacecraft return, and the existing devices are large in size and weight, which is not conducive to the reliability and reusability of the device, and does not meet the requirements of spacecraft to save space and weight as much as possible.

[0006] To achieve the above-mentioned purpose, the present invention provides a reusable spacecraft parachute retraction soft landing device, including a retraction device, which is arranged below the parachute cabin and inside the side wall of the return cabin, and the retraction device includes a middle part provided with a pyrotechnic push rod, and upper and lower ends of the pyrotechnic push rod are both installed with an upper component and a lower component, and the upper component and the lower component are respectively installed with four pulleys, and the parachute rope passes through each of the pulleys in turn.

[0007] Preferably, the upper component and the lower component are respectively connected to the fixed structure in the side wall of the return capsule. After the parachute rope passes through the pulley, the connection point between the upper end and the parachute is fixed on the parachute capsule, and the connection point between the lower end and the spacecraft is fixed on the spacecraft.

[0008] Preferably, a gunpowder column is installed inside the pyrotechnic push rod to provide power. When the return capsule approaches the ground, the pyrotechnic push rod is extended to increase the length of the parachute rope between the upper and lower components, shorten the distance between the parachute and the return capsule, and further reduce the speed of the return capsule.

[0009] A reusable spacecraft parachute retraction soft landing device achieves soft landing through the following steps: S1. Analyze and study the parachute retraction process in advance, and establish a relationship model between different return capsule masses and the optimal retraction starting height; S2. According to the mass of the return capsule measured in real time, the optimal starting height of the current return capsule is calculated by the above relationship model, and the height is measured in real time by using an altimeter; S3. When the altimeter detects that the return capsule has reached the optimal altitude, the retraction device is activated to begin retraction to achieve a soft landing of the spacecraft.

[0010] Preferably, in step S3, the shortening device uses a pyrotechnic push rod as an actuating device, which has high energy density and good shortening effect.

[0011] Preferably, in step S3, the shortening device arranges the pulleys in a ring shape, which helps to save space and improve the carrying efficiency of the return capsule.

[0012] Therefore, the present invention adopts a reusable spacecraft parachute retracted soft landing device with the above structure, which has the following beneficial effects: (1) The present invention designs a retracting device for landing a spacecraft return capsule, which uses a pyrotechnic push rod as a driving device, has high energy density, reduces the weight and complexity of the mechanism, and helps to improve the carrying efficiency of the re-entry spacecraft.

[0013] (2) The present invention arranges the main part of the distance reduction device inside the side wall of the spacecraft return capsule, which saves space and increases the working length of the distance reduction device; the distance reduction device is arranged inside the side wall and will not damage the load-bearing structure of the return capsule.

[0014] (3) After the reverse thrust rocket is eliminated in the present invention, the heat-resistant base does not need to be discarded, which helps to reduce the complexity of the system; the retracted pitch device will not cause dust when the return capsule lands, which helps astronauts to leave the cabin in time.

[0015] (4) The present invention uses the total weight of the reentry spacecraft and the altitude obtained by the altimeter to calculate the start time of the retraction, which has high accuracy, less possible interference, and high reliability.

[0016] The technical solution of the present invention is further described in detail below through the accompanying drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic structural diagram of a retracting device of a reusable spacecraft parachute retracting soft landing device according to the present invention; Figure 2 It is a schematic structural diagram of a reusable spacecraft parachute retraction soft landing device in a deployed state; Figure 3 It is a schematic diagram of the arrangement of a retracting device of a reusable spacecraft parachute retracting soft landing device according to the present invention; Figure 4 It is a schematic diagram of the arrangement of a retracting device of a reusable spacecraft parachute retracting soft landing device in a manned spacecraft parachute cabin of the present invention; Figure 5 This is a schematic diagram of the working process of a retracting device of a reusable spacecraft parachute retracting soft landing device of the present invention; Reference numerals 1. Pyrotechnic push rod, 2. Upper assembly, 3. Lower assembly, 4. Parachute rope, 5. Pulley. DETAILED DESCRIPTION

[0018] The technical solution of the present invention is further described below through the accompanying drawings and embodiments.

[0019] Unless otherwise defined, the technical terms or scientific terms used in the present invention should be understood by people with ordinary skills in the field to which the present invention belongs. The words "first", "second" and similar words used in the present invention do not indicate any order, quantity or importance, but are only used to distinguish different components. "Include" or "comprise" and similar words mean that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, without excluding other elements or objects. "Connect" or "connected" and similar words are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. "Up", "down", "left", "right" and the like are only used to indicate relative positional relationships. When the absolute position of the described object changes, the relative positional relationship may also change accordingly.

[0020] Example like Figure 1-4As shown, the present invention provides a reusable spacecraft parachute retraction soft landing device, including a retraction device, which is arranged below the parachute cabin and inside the side wall of the return cabin, and the retraction device includes a middle part provided with a pyrotechnic push rod, and the upper and lower ends of the pyrotechnic push rod are both installed with an upper component and a lower component, and the upper component and the lower component are respectively installed with four pulleys, and the parachute rope passes through each pulley in turn.

[0021] The upper and lower components are respectively connected to the fixed structure inside the side wall of the return capsule. After the parachute rope passes through the pulley, its upper end is fixed to the parachute cabin at the connection point with the parachute, and the lower end is fixed to the spacecraft at the connection point with the spacecraft.

[0022] There is a gunpowder column inside the pyrotechnic push rod to provide power.

[0023] like Figure 5 As shown, a reusable spacecraft parachute retraction soft landing device achieves soft landing through the following steps: S1. Study the parachute retraction process in advance, conduct simulations and tests for different load weights and different charge masses, obtain the retraction starting height corresponding to the load reaching the minimum speed and landing under the corresponding conditions, and finally establish a relationship model between different return capsule masses and the optimal retraction starting height; S2. Install a radio altimeter on the return capsule to continuously measure the height of the return capsule from the ground when it is close to landing; calculate the optimal starting height of the retraction corresponding to the current mass of the return capsule through the relationship model established in S1 based on the estimated mass of the return capsule, and use the altimeter to measure the height in real time; S3. The altimeter measures the current altitude of the return capsule in real time and compares it with the optimal retraction starting altitude obtained by the relationship model. When the altimeter detects that the return capsule has reached the optimal altitude, the retraction is started, the pyrotechnic push rod is extended, the length of the parachute rope between the upper and lower components is increased, the distance between the parachute and the return capsule is shortened, and the falling speed is further reduced to achieve a retraction soft landing of the spacecraft.

[0024] The use of a piston-pulley device as a retracting device can effectively improve the retracting effect of the retracting device and save space. The use of a pyrotechnic push rod as an actuating device has high energy density and good retracting effect. The circular arrangement of the pulleys helps save space and improve the carrying efficiency of the return capsule.

[0025] Workflow: The parachute retraction process was studied in advance, and simulations and tests were performed for different load weights to obtain the retraction starting height corresponding to the load reaching the minimum speed and landing under the corresponding conditions. Finally, a relationship model between different return capsule masses and the optimal retraction starting height was established. Before the re-entry spacecraft takes off, the parachute and the distance reduction device are installed in the parachute cabin according to the distance reduction device layout plan, so as to realize the installation of the distance reduction device and the rational use of the return capsule space.

[0026] Before re-entry, the total mass of the spacecraft is estimated based on factors such as changes in load conditions and fuel consumption during the flight. Based on the relationship model between different return capsule masses and optimal starting altitudes, the optimal retraction starting altitude corresponding to the return capsule mass is obtained.

[0027] During re-entry, the parachute is opened at an appropriate altitude to decelerate the return capsule until it reaches a uniform descent state.

[0028] Starting at an altitude of about 100 meters, an altimeter is used to continuously measure the current altitude of the return capsule and compare it with the optimal retraction starting altitude obtained by the relationship model. When the optimal retraction starting altitude is reached, an actuation command is sent to the pyrotechnic push rod to ignite the gunpowder, extend the pyrotechnic push rod, increase the length of the parachute rope inside the device, shorten the distance between the return capsule and the parachute, and achieve retraction deceleration.

[0029] According to the data obtained from the model of the relationship between different return capsule masses and the optimal starting height, the return capsule will land just when its falling speed reaches the minimum value, achieving a soft landing.

[0030] Therefore, the present invention adopts the above-mentioned reusable spacecraft parachute retraction soft landing device, designs a retraction device for the landing of the spacecraft return capsule, adopts a pyrotechnic push rod as a driving device, has high energy density, reduces the weight and complexity of the mechanism, and helps to improve the carrying efficiency of the re-entry spacecraft. The main part of the retraction device is arranged in the side wall of the spacecraft return capsule, which saves space and increases the working length of the retraction device; the retraction device is arranged in the side wall and will not damage the load-bearing structure of the return capsule. After the reverse thrust rocket is cancelled, the heat-proof outsole can be retained, which helps to reduce the complexity of the system; the retraction device will not cause dust when the return capsule lands, which helps astronauts to leave the cabin in time. The retraction start time is calculated using the total weight of the loaded spacecraft and the height obtained by the altimeter, which has high accuracy, less possible interference, and high reliability.

[0031] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that they can still modify or replace the technical solution of the present invention with equivalents, and these modifications or equivalent replacements cannot cause the modified technical solution to deviate from the spirit and scope of the technical solution of the present invention.

Claims

1. A reusable spacecraft parachute retracted soft landing device, characterized in that: It includes a retracting device, which is arranged below the parachute cabin and inside the side wall of the return cabin. The retracting device includes a middle part with a pyrotechnic push rod, and upper and lower ends of the pyrotechnic push rod are both installed with an upper component and a lower component. The upper component and the lower component are respectively installed with four pulleys, and the parachute rope passes through each of the pulleys in turn.

2. A reusable spacecraft parachute retracted soft landing device according to claim 1, characterized in that: The upper component and the lower component are respectively connected to the fixed structure in the side wall of the return capsule. After the parachute rope passes through the pulley, the connection point between the upper end and the parachute is fixed on the parachute cabin, and the connection point between the lower end and the spacecraft is fixed on the spacecraft.

3. The reusable spacecraft parachute retraction soft landing device according to claim 1, characterized in that: The pyrotechnic push rod is internally provided with a gunpowder column for providing power. The length of the parachute rope in the device is increased through the extension of the pyrotechnic push rod and the mechanical advantage of the pulley block, thereby shortening the distance between the return capsule and the parachute and achieving distance reduction.

4. A reusable spacecraft parachute retraction soft landing device according to any one of claims 1 to 3, characterized in that: A soft landing is achieved by following these steps: S1. Analyze and study the parachute retraction process in advance, and establish a relationship model between different return capsule masses and the optimal retraction starting height; S2. According to the mass of the return capsule measured in real time, the optimal starting height of the current return capsule is calculated by the above relationship model, and the height is measured in real time by using an altimeter; S3. When the altimeter detects that the return capsule has reached the optimal altitude, the retraction device is activated to begin retraction, shortening the distance between the return capsule and the parachute, further reducing the speed of the return capsule and achieving a soft landing of the spacecraft.

5. The reusable spacecraft parachute retraction soft landing device according to claim 4, characterized in that: In step S3, the shortening device uses an pyrotechnic push rod as an actuating device, which has high energy density and good shortening effect.

6. The reusable spacecraft parachute retraction soft landing device according to claim 4, characterized in that: In step S3, the shortening device arranges the pulleys in a ring shape, which helps to save space and improve the carrying efficiency of the return capsule.

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