CN115072003A - Hollow annular foldable Mars rotor aircraft - Google Patents
Hollow annular foldable Mars rotor aircraft Download PDFInfo
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- CN115072003A CN115072003A CN202210719792.2A CN202210719792A CN115072003A CN 115072003 A CN115072003 A CN 115072003A CN 202210719792 A CN202210719792 A CN 202210719792A CN 115072003 A CN115072003 A CN 115072003A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
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Abstract
The invention discloses a hollow annular foldable Mars rotor craft, the foldable Mars rotor craft is installed on a rocket launching tube rack, the rocket launching tube rack is installed at the central position above a Mars lander, a return rocket is installed in the rocket launching tube rack, and the foldable Mars rotor craft comprises: the Mars rotor craft body, the rotor folding and unfolding mechanism and the landing leg folding and unfolding mechanism are arranged on the side edge of the rocket launching barrel frame, and clamping and locking of the Mars rotor craft body are achieved. The invention can effectively realize the high folding-unfolding ratio storage of the Mars rotor craft body, can realize the independence of the Mars rotor craft and the return rocket working space, and improves the reliability of the sampling return task.
Description
Technical Field
The invention relates to the technical field of Mars rotor crafts, in particular to a hollow annular foldable Mars rotor craft.
Background
The detection of the mars is beneficial to deepening the understanding of the evolution law of the planets of the solar system for human beings. The collection of the Mars surface samples and the return of the samples to the earth have important significance for developing the Mars geological structure and life chemistry research of human beings. The existing Mars rover technology has the defects of limited patrol range, low moving speed and the like, and the rotary wing aircraft can realize large-range flight detection by utilizing Mars low-altitude atmosphere, so that the detection capability of a Mars detection system is expanded. The united states tried a mars helicopter on the mars surface in 2021, which had very limited ability to carry payload. And the mars sampling return requires the mars rotor aircraft to have higher loading capacity to carry the sample and send it into the returner, so a multi-shaft rotor configuration is required. Deep space exploration requires that mars rotor craft possess less size envelope, for solving the contradiction between the area load ability of small-scale rotor craft and the size envelope of large-scale rotor craft, needs to design a mechanism and accomodates the aircraft on mars lander to can be before flight with aircraft unblock, expansion. The spark and the earth have larger communication time delay, and a folding and unfolding mechanism is required to realize automatic unfolding. In addition, in order to match the smooth progress of the sampling return task, the mars aircraft needs to have a special structure to avoid interfering with the launch of the return rocket.
Disclosure of Invention
The invention aims to provide a mars rotor aircraft which can be folded on a lander and unlocked and unfolded so as to realize the patrol detection of the mars aircraft and return collected samples to the earth by matching with a return rocket.
The technical scheme adopted by the invention for solving the technical problems is as follows:
a hollow ring-shaped deployable mars rotor aircraft mounted on a rocket launch canister mount, the rocket launch canister mount being mounted in a central location above a mars launcher, and a return rocket being mounted inside the rocket launch canister mount, comprising: the Mars rotor craft body, the rotor folding and unfolding mechanism and the landing leg folding and unfolding mechanism are arranged on the side edge of the rocket launching barrel frame, and clamping and locking of the Mars rotor craft body are achieved.
Further, mars rotor craft body includes rotor blade, the folding hinge of paddle, rotor arm, the cyclic annular fuselage of cavity, upper rotor propulsion motor and lower rotor propulsion motor, the cyclic annular fuselage top equipartition of cavity has the rotor arm, install lower rotor propulsion motor on the rotor arm, upper rotor propulsion motor is installed at lower rotor propulsion motor top, upper rotor propulsion motor with the rotor of lower rotor propulsion motor all has rotor blade through the folding hinged joint of paddle.
Further, mars rotor craft body still includes landing leg folding hinge and landing leg, the equipartition of cavity cyclic annular fuselage bottom has the landing leg, the landing leg pass through landing leg folding hinge with cavity cyclic annular fuselage links to each other.
Furthermore, every rotor arm position department all corresponds and is provided with rotor folding and unfolding mechanism for press from both sides tightly and lock the rotor arm, and be used for pressing from both sides tightly and lock the rotor paddle.
Furthermore, the rotor wing folding and unfolding mechanism comprises a right main clamping frame, a left main clamping frame, a rotor wing unlocking explosive bolt, a rotor wing unlocking hinge, a rotor wing folding and unfolding support, a rotor wing unlocking spring and a blade folding and unfolding module; the rotor wing folding and unfolding support is connected to the side wall surface of the rocket launching barrel frame and is respectively connected with the right main clamping frame and the left main clamping frame through the rotor wing unlocking hinge; the middle parts of the right main clamping frame and the left main clamping frame are connected through the rotor wing unlocking explosion bolt; the lower parts of the right main clamping frame and the left main clamping frame are connected through a rotor wing unlocking spring under pretension; the upper parts of the right main clamping frame and the left main clamping frame are connected with two layers of blade folding and unfolding modules for clamping and locking rotor blades; the middle parts of the right main clamping frame and the left main clamping frame are respectively connected with semicircular structures which are symmetrically arranged and used for clamping and locking the rotor arm.
Furthermore, each layer of blade folding and unfolding module is provided with two symmetrical blades, one blade is connected with the right main clamping frame, and the other blade is connected with the left main clamping frame.
Further, the blade folding and unfolding module comprises a blade unlocking explosion bolt, a blade lower clamping plate, a blade upper clamping plate, an elastic clamping block, a blade unlocking hinge and a blade unlocking spring; the right main clamping frame or the left main clamping frame connects the lower blade clamping plate and the upper blade clamping plate through a blade unlocking hinge, two ends of the lower blade clamping plate and the upper blade clamping plate are respectively connected through the blade unlocking explosive bolt and a pre-tensioned blade unlocking spring, elastic clamping blocks are respectively installed on the lower surface of the upper blade clamping plate, the upper surface of the lower blade clamping plate and the inner surface of the lower blade clamping plate, far away from the blade unlocking explosive bolt, and the rotor blade is clamped and locked between the three elastic clamping blocks.
Further, the landing leg folding and unfolding mechanism comprises a landing leg folding and unfolding support, a landing leg left clamping block, a landing leg unlocking spring, a landing leg right clamping block and a landing leg unlocking explosion bolt; the landing leg folding and unfolding support is installed on the side wall surface of a rocket launching barrel frame, two slideways are arranged on the surface of the landing leg folding and unfolding support, the left landing leg clamping block and the right landing leg clamping block are respectively arranged in the two slideways, the left landing leg clamping block and the right landing leg clamping block are connected through a landing leg unlocking explosion bolt, a pre-stressed landing leg unlocking spring is connected to the middle of the landing leg left clamping block and the landing leg right clamping block, and the landing legs are clamped by the left landing leg clamping block and the right landing leg clamping block in a clamping and locking state through respective semi-circular arc surfaces.
Has the advantages that:
1. the invention can effectively realize the high folding-unfolding ratio storage of the Mars rotor craft body.
2. The invention can realize the independence of the Mars rotor craft body and the return rocket working space, and improve the reliability of the sampling return task.
3. The folding locking device can realize effective folding locking of the Mars rotor craft body, the blades are clamped by the blade clamping plates, the rotor arms and the landing legs are clamped by the arc surfaces, and the connection rigidity of the Mars rotor craft body and the lander in the launching process is improved.
4. The invention can realize the effective and autonomous unlocking and unfolding of the Mars rotor craft body, the folding and unfolding mechanism realizes the locking by virtue of the explosive bolt and realizes the unlocking and unfolding by virtue of the unlocking spring, the process can be actively controlled by an electric signal, and the convenience of ground remote control is improved.
Drawings
Figure 1 is a general layout of the present invention on a mars lander.
Fig. 2 is a schematic perspective view of the present invention.
FIG. 3 is a perspective view of the Mars aircraft body in the deployed state of the present invention;
figure 4 is a front view of the rotor wing deployment mechanism of the present invention;
figure 5 is a top view of the rotor wing deployment mechanism of the present invention;
FIG. 6 is an enlarged view at A in FIG. 4;
fig. 7 is a perspective view of the landing leg folding and unfolding mechanism of the present invention.
Wherein, in the figure: 1. the aircraft comprises a Mars rotor craft, 1-1 rotor blade, 1-2 blade folding hinges, 1-3 rotor arms, 1-4 hollow annular fuselages, 1-5 upper rotor propulsion motors, 1-6 lower rotor propulsion motors, 1-7 landing leg folding hinges, 1-8 landing legs, 2 return rockets, 3 rotor folding and unfolding mechanisms, 3-1 right main clamping frames, 3-2 left main clamping frames, 3-3 rotor unlocking explosive bolts, 3-4 rotor unlocking hinges, 3-5 rotor folding and unfolding supports, 3-6 rotor unlocking springs, 3-7 blade unlocking explosive bolts, 3-8 blade lower clamping plates, 3-9 blade upper clamping plates, 3-10 elastic clamping blocks, 3-11 blade unlocking hinges, 3-12 of a blade unlocking spring, 4 of a landing leg folding and unfolding mechanism, 4-1 of a landing leg folding and unfolding support, 4-2 of a landing leg left clamping block, 4-3 of a landing leg unlocking spring, 4-4 of a landing leg right clamping block, 4-5 of a landing leg unlocking explosion bolt, 5 of a rocket launching barrel frame and 6 of a mars lander.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1, the present invention discloses a hollow ring-shaped deployable mars rotor craft 1, the deployable mars rotor craft 1 being mounted on a rocket launcher 5, the rocket launcher 5 being mounted in a central position above a mars lander 6, and a return rocket 2 being mounted inside the rocket launcher 5, comprising: the mars rotor craft body 1, rotor roll over and open mechanism 3 and landing leg roll over and open mechanism 4 and install at rocket launching cradle 5 side, realize the clamp of mars rotor craft body 1 tightly with the locking.
In this embodiment, the folded mars rotor craft body 1 is installed above the return rocket 2, and the hollow annular fuselage structure ensures that the return rocket 2 will not interfere with the craft and the folding and unfolding mechanism during takeoff. Thus, the reliability of the work of the return rocket 2 is ensured.
Referring to fig. 2 and 3, the mars rotor craft body 1 includes rotor blades 1-1, blade folding hinges 1-2, rotor arms 1-3, hollow annular airframe 1-4, upper rotor propulsion motor 1-5 and lower rotor propulsion motor 1-6, rotor arms 1-3 are evenly distributed at the top of hollow annular airframe 1-4, lower rotor propulsion motor 1-6 is installed on rotor arms 1-3, upper rotor propulsion motor 1-5 is installed at the top of lower rotor propulsion motor 1-6, upper rotor propulsion motor 1-5 and the rotor of lower rotor propulsion motor 1-6 are connected with rotor blades 1-1 through blade folding hinges 1-2. The mars rotor craft body 1 further comprises landing leg folding hinges 1-7 and landing legs 1-8, the landing legs 1-8 are evenly distributed at the bottoms of the hollow annular fuselages 1-4, and the landing legs 1-8 are connected with the hollow annular fuselages 1-4 through the landing leg folding hinges 1-7. The upper rotor wing propulsion motor 1-5 and the lower rotor wing propulsion motor 1-6 are coaxially arranged in series, the rotor wing blades 1-1, the blade folding hinges 1-2, the upper rotor wing propulsion motor 1-5 and the lower rotor wing propulsion motor 1-6 form a rotor wing system, and the four groups of coaxial rotor wing systems are connected to the hollow annular airframe 1-4 through the rotor wing arms 1-3.
Referring to fig. 2-6, a rotor folding and unfolding mechanism 3 is correspondingly arranged at each position of the rotor arms 1-3, and is used for clamping and locking the rotor arms 1-3 and clamping and locking the rotor blades 1-1. The rotor wing folding and unfolding mechanism 3 comprises a right main clamping frame 3-1, a left main clamping frame 3-2, a rotor wing unlocking explosive bolt 3-3, a rotor wing unlocking hinge 3-4, a rotor wing folding and unfolding support 3-5, a rotor wing unlocking spring 3-6 and a blade folding and unfolding module; the rotor wing folding and unfolding support 3-5 is connected to the side wall surface of the rocket launching barrel frame 5 and is respectively connected with the right main clamping frame 3-1 and the left main clamping frame 3-2 through the rotor wing unlocking hinge 3-4; the middle parts of the right main clamping frame 3-1 and the left main clamping frame 3-2 are connected through the rotor wing unlocking explosion bolt 3-3; the lower parts of the right main clamping frame 3-1 and the left main clamping frame 3-2 are connected through a rotor wing unlocking spring 3-6 under pretension; the upper parts of the right main clamping frame 3-1 and the left main clamping frame 3-2 are connected with two layers of blade folding and unfolding modules for clamping and locking the rotor blade 1-1; the middle parts of the right main clamping frame 3-1 and the left main clamping frame 3-2 are respectively connected with symmetrically arranged semicircular structures for clamping and locking the rotor arm 1-3.
In this embodiment, each layer of blade folding and unfolding module is provided with two symmetrical blades, one of which is connected with the right main clamping frame 3-1, and the other of which is connected with the left main clamping frame 3-2. The blade folding module comprises 3-7 parts of blade unlocking explosive bolts, 3-8 parts of blade lower clamping plates, 3-9 parts of blade upper clamping plates, 3-10 parts of elastic clamping blocks, 3-11 parts of blade unlocking hinges and 3-12 parts of blade unlocking springs; the right main clamping frame 3-1 or the left main clamping frame 3-2 connects a lower blade clamping plate 3-8 with an upper blade clamping plate 3-9 through a blade unlocking hinge 3-11, two ends of the lower blade clamping plate 3-8 and the upper blade clamping plate 3-9 are respectively connected with a pre-tensioned blade unlocking spring 3-12 through a blade unlocking explosive bolt 3-7, elastic clamping blocks 3-10 are respectively arranged on the lower surface of the upper blade clamping plate 3-9, the upper surface of the lower blade clamping plate 3-8 and the inner surface of the lower blade clamping plate 3-8 far away from the blade unlocking explosive bolt 3-7, and the rotor blade 1-1 is clamped and locked between the three elastic clamping blocks 3-10.
Referring to fig. 2, 3 and 7, the landing leg folding and unfolding mechanism 4 comprises a landing leg folding and unfolding support 4-1, a landing leg left clamping block 4-2, a landing leg unlocking spring 4-3, a landing leg right clamping block 4-4 and a landing leg unlocking explosive bolt 4-5; the landing leg folding and unfolding support 4-1 is installed on the side wall surface of a rocket launching barrel frame 5, two slideways are arranged on the surface of the landing leg folding and unfolding support 4-1, the landing leg left clamping block and the landing leg right clamping block 4-4 are respectively arranged in the two slideways, the landing leg left clamping block 4-2 and the landing leg right clamping block 4-4 are connected through a landing leg unlocking explosive bolt 4-5, a pre-stressed landing leg unlocking spring 4-3 is connected in the middle, and the landing leg left clamping block 4-2 and the landing leg right clamping block 4-4 in a clamping and locking state clamp the landing legs 1-8 through respective semi-circular arc surfaces.
The invention can effectively realize the high folding-unfolding ratio storage of the Mars rotor craft body 1. The invention can realize the independence of the working space of the Mars rotor craft body 1 and the return rocket 2, and improve the reliability of the sampling return task. The folding locking device can realize effective folding locking of the Mars rotor craft body 1, utilizes the plurality of blade clamping plates to clamp the blades, and simultaneously uses the arc surfaces to clamp the rotor arms 1-3 and the landing legs 1-8, thereby improving the connection rigidity of the Mars rotor craft body 1 and a lander in the launching process. The invention can realize the effective and autonomous unlocking and unfolding of the Mars rotor aircraft body 1, the folding and unfolding mechanism realizes the locking by unlocking the explosive bolts 3-3 by the rotor and realizes the unlocking and unfolding by utilizing the unlocking spring, the process can be actively controlled by an electric signal, and the convenience of ground remote control is improved.
The working principle of the invention is as follows:
folding of mars rotor craft body: the two blades are combined to form a group of rotors, the rotors are driven by an upper propulsion motor and a lower propulsion motor and rotate around opposite directions to offset the generated pneumatic torque reversal, and four groups of coaxial double rotors are combined to form a rotor system of the Mars aircraft. The rotor blade 1-1 can be folded around the blade folding hinge 1-2 to be parallel to the rotor arm 1-3, the blade clamp faces the center of the fuselage, and the landing leg 1-8 can be folded downwards around the land leg folding hinge 1-7 to be in a vertical state. The folding hinge 1-2 is elastically deformed after being folded from an unfolded state, and can be restored to a high-rigidity state after locking constraint is eliminated, so that the rigidity of the whole mechanism is ensured.
The rotor is rolled over locking and unblock of exhibition mechanism to mars rotor aircraft body: when the rotor of the Mars rotor aircraft body is in a folded state and the blades are in a locked state, the rotor blades 1-1 are clamped between the blade lower clamping plates 3-8 and the blade upper clamping plates 3-9, and the clamping mechanism can be ensured to be adaptive to the irregular curved surface shape of the blades through the elastic clamping blocks 3-10; when the rotor wing unlocking explosive bolt 3-3 is disconnected under the unlocking instruction of the rotor wing blade 1-1, the blade unlocking spring under the pretension can contract and drive the blade lower clamping plate 3-8 and the blade upper clamping plate 3-9 to rotate anticlockwise and clockwise around the blade unlocking hinge 3-11 respectively, so that an included angle is formed between the blade lower clamping plate and the blade upper clamping plate, and the rotor wing blade 1-1 is unlocked; when the rotor of the Mars rotor aircraft body is in a folded state and the blades are in an unlocked state, the right main clamping frame 3-1 and the left main clamping frame 3-2 are connected together through a rotor unlocking explosive bolt 3-3 in a rotor locking state, and a semicircular structure between the two clamps the rotor arm 1-3 tightly; when the rotor wing explosion bolt 3-3 is disconnected under an unlocking instruction, the right main clamping frame 3-1 and the left main clamping frame 3-2 respectively rotate clockwise and anticlockwise around the rotor wing unlocking hinge 3-4 under the action of the rotor wing unlocking spring 3-6, so that the rotor wing main clamping frame is opened by an angle, the rotor wing blades are completely released, and the rotor wing blades 1-1 are unfolded to two sides of the rotor wing arms 1-3 around the blade folding hinge 1-2.
The landing leg folding and unfolding mechanism locks and unlocks the Mars rotor aircraft body: when the landing leg of the Mars rotor craft body is in a folded and locked state, the landing leg unlocks an explosive bolt 4-5 to connect the left clamping block 4-2 of the landing leg and the right clamping block 4-4 of the landing leg together; when the landing leg unlocking explosion bolt 4-5 is disconnected under an unlocking instruction, the prepressing landing leg unlocking spring 4-3 can be extended to enable the landing leg left clamping block 4-2 and the landing leg right clamping block 4-4 to generate relative displacement along the two slideways of the landing leg folding and unfolding support 4-1, the landing leg 1-8 is released, and the landing leg folding and unfolding bolt is unfolded to the outer side of the airplane body around the landing leg folding hinge 1-7.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, and not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (8)
1. A hollow annular stowable mars rotor aircraft mounted on a rocket launch canister frame mounted in a central location above a mars launcher and a return rocket mounted inside the rocket launch canister frame, comprising: the Mars rotor craft body, the rotor folding and unfolding mechanism and the landing leg folding and unfolding mechanism are arranged on the side edge of the rocket launching barrel frame, and clamping and locking of the Mars rotor craft body are achieved.
2. A hollow annular stowable mars rotor aircraft according to claim 1, wherein the mars rotor aircraft body comprises rotor blades, blade folding hinges, a rotor arm, a hollow annular fuselage, an upper rotor propulsion motor, and a lower rotor propulsion motor, the rotor arm is uniformly distributed on the top of the hollow annular fuselage, the lower rotor propulsion motor is mounted on the rotor arm, the upper rotor propulsion motor is mounted on the top of the lower rotor propulsion motor, and the rotors of the upper rotor propulsion motor and the lower rotor propulsion motor are connected with the rotor blades through the blade folding hinges.
3. A hollow annular stowable mars rotor aircraft according to claim 2, wherein said mars rotor aircraft body further comprises landing leg fold hinges and landing legs, and wherein landing legs are evenly distributed on the bottom of the hollow annular fuselage and are connected to the hollow annular fuselage by the landing leg fold hinges.
4. A hollow annular stowable mars rotor aircraft according to claim 2, wherein a rotor fold-out mechanism is provided at each rotor arm location for clamping and locking the rotor arm and for clamping and locking the rotor blade.
5. The stowable mars rotor aircraft of claim 4, wherein the rotor stowing and stowing mechanism comprises a right main cradle, a left main cradle, a rotor unlatching explosion bolt, a rotor unlatching hinge, a rotor stowing mount, a rotor unlatching spring, and a blade stowing and stowing module; the rotor wing folding and unfolding support is connected to the side wall surface of the rocket launching barrel frame and is respectively connected with the right main clamping frame and the left main clamping frame through the rotor wing unlocking hinge; the middle parts of the right main clamping frame and the left main clamping frame are connected through the rotor wing unlocking explosion bolt; the lower parts of the right main clamping frame and the left main clamping frame are connected through a rotor wing unlocking spring under pretension; the upper parts of the right main clamping frame and the left main clamping frame are connected with two layers of blade folding and unfolding modules for clamping and locking rotor blades; the middle parts of the right main clamping frame and the left main clamping frame are respectively connected with semicircular structures which are symmetrically arranged and used for clamping and locking the rotor arm.
6. A collapsible Mars rotorcraft in the shape of a hollow toroid as claimed in claim 5, wherein there are two symmetrical blade folding and unfolding modules per layer, one connected to the right main cradle and the other connected to the left main cradle.
7. The hollow annular deployable mars rotor aircraft of claim 6, wherein said blade-folding module comprises a blade-unlocking explosion bolt, a blade lower clamp, a blade upper clamp, a resilient clamp, a blade-unlocking hinge, and a blade-unlocking spring; the right main clamping frame or the left main clamping frame connects the lower blade clamping plate and the upper blade clamping plate through a blade unlocking hinge, two ends of the lower blade clamping plate and the upper blade clamping plate are respectively connected through the blade unlocking explosive bolt and a pre-tensioned blade unlocking spring, elastic clamping blocks are respectively installed on the lower surface of the upper blade clamping plate, the upper surface of the lower blade clamping plate and the inner surface of the lower blade clamping plate, far away from the blade unlocking explosive bolt, and the rotor blade is clamped and locked between the three elastic clamping blocks.
8. The hollow annular stowable mars-rotor aircraft of claim 3, wherein landing leg stowing mechanism comprises landing leg stowing mount, landing leg left clamp, landing leg unlatching spring, landing leg right clamp, and landing leg unlatching explosion bolt; the landing leg folding and unfolding support is installed on the side wall surface of a rocket launching barrel frame, two slideways are arranged on the surface of the landing leg folding and unfolding support, the left landing leg clamping block and the right landing leg clamping block are respectively arranged in the two slideways, the left landing leg clamping block and the right landing leg clamping block are connected through a landing leg unlocking explosion bolt, a pre-stressed landing leg unlocking spring is connected to the middle of the landing leg left clamping block and the landing leg right clamping block, and the landing legs are clamped by the left landing leg clamping block and the right landing leg clamping block in a clamping and locking state through respective semi-circular arc surfaces.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210719792.2A CN115072003B (en) | 2022-06-23 | 2022-06-23 | Hollow annular retractable spark rotor aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210719792.2A CN115072003B (en) | 2022-06-23 | 2022-06-23 | Hollow annular retractable spark rotor aircraft |
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| CN115072003B CN115072003B (en) | 2024-08-23 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115027698A (en) * | 2022-06-23 | 2022-09-09 | 哈尔滨工业大学 | Eight rotor type mars aircraft of collapsible four-axis |
| CN115367146A (en) * | 2022-09-30 | 2022-11-22 | 哈尔滨工业大学 | Three-axis six-rotor type mars aircraft and fixing and locking device thereof |
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| CN104627390A (en) * | 2014-12-18 | 2015-05-20 | 北京空间机电研究所 | Mars exploration landing buffer device |
| US20180072413A1 (en) * | 2016-04-05 | 2018-03-15 | Swift Engineering, Inc. | Rotating wing assemblies for tailsitter aircraft |
| CN106184704A (en) * | 2016-08-08 | 2016-12-07 | 北京航空航天大学 | One is applicable to rocket-propelled quadrotor |
| CN106516169A (en) * | 2016-11-03 | 2017-03-22 | 中国人民解放军国防科学技术大学 | Planet surface landing system |
| US20210031913A1 (en) * | 2019-05-24 | 2021-02-04 | Randy MARTEL | Rocket propelled drone |
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| US20210107645A1 (en) * | 2019-10-09 | 2021-04-15 | California Institute Of Technology | Passive and active stability systems for ballistically launched multirotors |
| CN216169918U (en) * | 2021-11-10 | 2022-04-05 | 西南科技大学 | Solid rocket model multi-rotor fixed-point landing structure |
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| CN115027698A (en) * | 2022-06-23 | 2022-09-09 | 哈尔滨工业大学 | Eight rotor type mars aircraft of collapsible four-axis |
| CN115027698B (en) * | 2022-06-23 | 2024-08-23 | 哈尔滨工业大学 | Foldable four-axis eight-rotor type Mars aircraft |
| CN115367146A (en) * | 2022-09-30 | 2022-11-22 | 哈尔滨工业大学 | Three-axis six-rotor type mars aircraft and fixing and locking device thereof |
| CN115367146B (en) * | 2022-09-30 | 2024-08-09 | 哈尔滨工业大学 | Triaxial six-rotor type Mars aircraft and fixed locking device thereof |
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