'Chinese reusable experimental spacecraft' CSSHQ / Shenlong (Divine Dragon) / Aotian-1

[sferrin]

And regarding the 'can-do attitude' you claim has died in the west please make sure you qualify that you are speaking for yourself.

Yeah? Where's Fasthawk? RATTLRS? HyFly? X-51 developments? LRASM-B? AARGM? ATKs MSST? What happened to follow on HTV-2 flights? US Army AHW? There are isolated exceptions to the rule (SpaceX and Blue Origin for example) but in the DoD? Please. The only X-51 flight that was marginally successful (the last one) they ALMOST DIDN'T DO BECAUSE THEY THOUGHT, "WHAT IF WE FAIL?". That's straight from the horse's mouth. And what did they do with that glimmer of success? Quit immediately. "Whoa, that was scary. Better not do that again, we might not get as lucky."

 

[VH]

I worked third shift on Apollo at what was then North American. I was right out of high school and attending Harbor JC to later transfer to UCSD. The dedication of our work team was phenomenal. The sheer determination to beat the Russians to the moon was beyond belief. While things may have slipped a bit since that time that same heart still beats among other Americans today.

Yeah I said it: Americans. Like you I also want more and would like to see those projects you mentioned come to fruition. But I am not bitter due to our lack of progress in certain areas. There are too many examples of America raising up and raising hell. And the damn damn is about to be rained down on those who doubt our ability to lead the way.

Please stay tuned!

 

[antigravite]

I worked third shift on Apollo at what was then North American. I was right out of high school and attending Harbor JC to later transfer to UCSD. The dedication of our work team was phenomenal. The sheer determination to beat the Russians to the moon was beyond belief. While things may have slipped a bit since that time that same heart still beats among other Americans today.

Yeah I said it: Americans. Like you I also want more and would like to see those projects you mentioned come to fruition. But I am not bitter due to our lack of progress in certain areas. There are too many examples of America raising up and raising hell. And the damn damn is about to be rained down on those who doubt our ability to lead the way.

Please stay tuned!

Okay guys. If you want to discuss US technological supremacy and 3rd shift Apollo, there is the bar.

The context has changed. Tools changed. The global situation has changed and we all have to understand this. You cant think of today's situation framed in the past. We should get back to China's hypersonic aerospace / reentry topic.

I'm not like you. In those matters I stick to the facts and I am agnostic to understand what the hell is going out here. Wether you like it or not, China is making huge progress in various areas of hypersonics.

Back to the point. Thank you.

A.

 

[antigravite]

Thermal protection device of attitude control system for hypersonic-speed and large-attack-angle reentry vehicle
Patent No.CN106394938 (A)
Inventor(s): SHAN HUAWEI; LU DI; LIU LIHONG; WANG HUI; HU CHENGLAN; LIN XUEFENG; TU ZHENGGUANG; QIN JIANFEI; SHU MENGJIONG +
Applicant(s): THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD +
Application number: CN20161863521 20160929
Priority number(s): CN20161863521 20160929
Abstract: The invention discloses a thermal protection device of an attitude control system for a hypersonic-speed and large-attack-angle reentry vehicle. The thermal protection device is used for thermal protection of an attitude control power unit, and comprises a rear bottom cover plate, a rear bottom cover plate heat-proof layer, an attitude control heat-proof force-bearing plate, an attitude control heat-proof layer, an attitude control engine jet pipe heat-proof sleeve and a pluggable plug heat-proof sleeve, wherein the rear bottom cover plate is mounted on a cabin and serves as a force-bearing piece, the attitude control power unit is arranged on the rear bottom cover plate, and the rear bottom cover plate is covered with the rear bottom cover plate heat-proof layer; attitude control power unit is wrapped and sleeved with the attitude control heat-proof force-bearing plate, and the attitude control heat-proof force-bearing plate is covered with the attitude control heat-proof layer; the attitude control power unit comprises an attitude control engine, an attitude control engine jet pipe is arranged at an outlet of the attitude control engine, and an end opening of the attitude control engine jet pipe is wrapped and sleeved with the attitude control engine jet pipe heat-proof sleeve; and a pluggable plug is wrapped and sleeved with the pluggable plug heat-proof sleeve. By adoption of the thermal protection device of the attitude control system for the hypersonic-speed and large-attack-angle reentry vehicle, thermal protection of the attitude control system for the hypersonic-speed and large-attack-angle reentry vehicle can be effectively achieved, and the design reliability of the attitude control system can be improved.

Thermal protection device for hypersonic gliding aircraft
Patent No. CN106547965 (A)
Inventor(s): SHAN HUAWEI; WANG HUI; HU CHENGLAN; LU DI; LIU LIHONG; LIN XUEFENG; TU ZHENGGUANG; QIN JIANFEI; SHU MENGJIONG +
Applicant(s): THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD +
Application number: CN20161929527 20161031
Priority number(s): CN20161929527 20161031
Abstract(A) The invention discloses a thermal protection device for a hypersonic gliding aircraft. The thermal protection device comprises a thermal protection layer, a heat-insulation layer and a carrying layer, wherein the carrying layer is covered with the heat-insulation layer; the heat-insulation layer is covered with the thermal protection layer; the thermal protection layer and the carrying layer are separated from each other without physical connection or contact in order to ensure free deformation of the thermal protection layer and the carrying layer in a pneumatic heating environment; a plurality of pieces of thermal protection layers are spliced with one another to form the whole thermal protection layer; the plurality of pieces of thermal protection layers are spliced with one another at the corners of cabin segments, angle parts of the cabin segments, and joints between horizontal fins and a cabin body; a plurality of thermal protection strips are locally arranged between the thermal protection layer at the joints of the cabin segments and the carrying layer; the plurality of thermal protection strips are arranged at intervals; the thermal protection strips can slide freely relative to the thermal protection layer in order to adapt to stress deformation; and the thermal protection strips and the thermal protection layer are made of the same material. In the thermal protection device, the plurality of pieces of thermal protection layers are provided, and the thermal protection layer and the carrying layer are designed separately, so that the problems of thermal matching and thermal stress can be solved effectively, and the reliability of the thermal protection device is enhanced.


Device for determining performance of control surface transmission mechanism in thermal-mechanical environments
PatentNo.CN106352925 (A)
Inventor(s): LIU YEBAO; RONG HUA; CHEN LIANG; YUAN YUAN; SHI MIQING; ZHAO JIANBO; SHA AN'AN; DU PENGFEI; ZHENG SIXING; HUANG SHIYONG; ZHANG JING; CAI QIAOYAN; HAI ERHAN; ZHAO DAHAI; SHAO QIUHU +
Applicant(s): CHINA ACADEMY LAUNCH VEHICLE TECHNOLOGY +
Application number: CN20161839685 20160921
Priority number(s): CN20161839685 20160921
Abstract
The invention discloses a device for determining performance of a control surface transmission mechanism in thermal-mechanical environments and relates to the field of thermal protection of hypersonic flight vehicles in aerospace. The device comprises an oscillating guide bar-torsion shaft type air rudder mechanism, a heating device, a bearing reaction simulation device, a torque sensor, a transition supporting seat, a torque applying device, a connecting platform, a heat insulation device and a steering engine supporting seat support. The device has the advantages that the device is capable of carrying out not only mechanism function test in a mechanical environment at a normal temperature but also motion reliability test and determination of thermal sealing and thermal transfer characteristics of the mechanism in a thermal environment, so that utilization rate of the device is improved; simultaneous thermal-mechanical loading during motion of the oscillating guide bar-torsion shaft type air rudder mechanism can be achieved; six-component force and rotation inertia of a control surface are simulated sufficiently, so that testing result reliability is improved, and the device is widely applicable to testing of different models of air rudder systems.

A.

 

[Airplane]

And regarding the 'can-do attitude' you claim has died in the west please make sure you qualify that you are speaking for yourself.

Yeah? Where's Fasthawk? RATTLRS? HyFly? X-51 developments? LRASM-B? AARGM? ATKs MSST? What happened to follow on HTV-2 flights? US Army AHW? There are isolated exceptions to the rule (SpaceX and Blue Origin for example) but in the DoD? Please. The only X-51 flight that was marginally successful (the last one) they ALMOST DIDN'T DO BECAUSE THEY THOUGHT, "WHAT IF WE FAIL?". That's straight from the horse's mouth. And what did they do with that glimmer of success? Quit immediately. "Whoa, that was scary. Better not do that again, we might not get as lucky."

The advent of stealth, followed about 10 years later by the fall of the Soviet Union killed the need for speed. Many big ticket items were scrapped immediately after the demise of the USSR including the Virginia, the B-2, the Midgetman and others... That was the 90s. Then came 2001 and we know where defense spending went for the next 16 years. There has been no need for hypersonic weapons, and only now are we seeing things starting to get warm again with potential foes.

There were other more important weapons systems to modernize the military that were canceled to even be concerned about hypersonic weapons that were not needed.

 

[sferrin]

There were other more important weapons systems to modernize the military that were canceled to even be concerned about hypersonic weapons that were not needed.

Really? So why all the failed programs then if they weren't needed?

 

[Airplane]

There were other more important weapons systems to modernize the military that were canceled to even be concerned about hypersonic weapons that were not needed.

Really? So why all the failed programs then if they weren't needed?

I work in engineering on unspecified "vehicles", and I've been both a mechanical and electrical engineer. If you do not keep the talent pool "warm" with projects for the sake of maintaining first hand knowledge, then a given capability is truly 100% lost forever until it is reinvented. What you may call a failed project is actually a 'win' for maintaining experience and know-how. These failed projects are giving many engineers first hand experience and also making gains in knowledge over what was done in the past. Be thankful the US is keeping the talent warm until such time these weapons may be needed. We learn as much from 'fails' as we learn with the 'wins'.


Oops! In the above post I meant "seawolf" instead of "virgina"

 

[sferrin]

There were other more important weapons systems to modernize the military that were canceled to even be concerned about hypersonic weapons that were not needed.

Really? So why all the failed programs then if they weren't needed?

I work in engineering on unspecified "vehicles", and I've been both a mechanical and electrical engineer. If you do not keep the talent pool "warm" with projects for the sake of maintaining first hand knowledge, then a given capability is truly 100% lost forever until it is reinvented. What you may call a failed project is actually a 'win' for maintaining experience and know-how. These failed projects are giving many engineers first hand experience and also making gains in knowledge over what was done in the past. Be thankful the US is keeping the talent warm until such time these weapons may be needed. We learn as much from 'fails' as we learn with the 'wins'.

The purpose was not to keep the pool "warm". If they were interested in charity programs for that purpose they'd have been worried about not losing what we already had. (Nuclear weapon expertise, large solid motors, and ramjets for example.) With these other programs, quitting at the first sign of difficulty only teaches how to produce failures. They never get the chance to find out what actually works. They just know what they did didn't work. Doesn't sound incredibly effective to me.

 

[antigravite]

Hi, here's another might-be related interesting patent. Enjoy.

A.

Thermal protection device for hypersonic gliding aircraft
Patent Number: CN106547965 (A)
Inventor(s): SHAN HUAWEI; WANG HUI; HU CHENGLAN; LU DI; LIU LIHONG; LIN XUEFENG; TU ZHENGGUANG; QIN JIANFEI; SHU MENGJIONG +
Applicant(s): THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD +
Application number: CN20161929527 20161031
Priority number(s): CN20161929527 20161031
Abstract: The invention discloses a thermal protection device for a hypersonic gliding aircraft. The thermal protection device comprises a thermal protection layer, a heat-insulation layer and a carrying layer, wherein the carrying layer is covered with the heat-insulation layer; the heat-insulation layer is covered with the thermal protection layer; the thermal protection layer and the carrying layer are separated from each other without physical connection or contact in order to ensure free deformation of the thermal protection layer and the carrying layer in a pneumatic heating environment; a plurality of pieces of thermal protection layers are spliced with one another to form the whole thermal protection layer; the plurality of pieces of thermal protection layers are spliced with one another at the corners of cabin segments, angle parts of the cabin segments, and joints between horizontal fins and a cabin body; a plurality of thermal protection strips are locally arranged between the thermal protection layer at the joints of the cabin segments and the carrying layer; the plurality of thermal protection strips are arranged at intervals; the thermal protection strips can slide freely relative to the thermal protection layer in order to adapt to stress deformation; and the thermal protection strips and the thermal protection layer are made of the same material. In the thermal protection device, the plurality of pieces of thermal protection layers are provided, and the thermal protection layer and the carrying layer are designed separately, so that the problems of thermal matching and thermal stress can be solved effectively, and the reliability of the thermal protection device is enhanced.

 

[antigravite]

Below is a database-ready csv list of known patents (64 as of today's posting) filed by and issued to the "THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACADEMY". Some of them are useful and bear special relevance in the context of hypersonics, reentry, and VTHL & HTHL RLVs. (Table head followed by structured data.)

Title,"Publication number","Publication date","Inventor(s)","Applicant(s)","International classification","Cooperative Patent Classification","Application number","Date of application","Priority number(s)","Patents cited in the search report","Literature cited in the search report","Patents cited during examination","Literature cited during examination","Other patent citations","Other literature citations","Patents used in opposition","Literature used in opposition","Patents cited by the applicant","Literature cited by the applicant","International search citation","International search NPL citation","Supplementary international search citation","Supplementary international search NPL citation"


Thermal protection device of attitude control system for hypersonic-speed and large-attack-angle reentry vehicle,"CN106394938 (A)","2017-02-15","SHAN HUAWEI LU DI LIU LIHONG WANG HUI HU CHENGLAN LIN XUEFENG TU ZHENGGUANG QIN JIANFEI SHU MENGJIONG","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","B64G1/58","","CN20161863521","20160929","CN20161863521 20160929","","","","","","","","","","","","","",""

Missile-rotating satellite searching method for hypersonic velocity missile,"CN106568355 (A)","2017-04-19","MAO JING ZENG QINGWEI SUN LIHUA MAO JINDI LI SHUMIN DENG CHAN SHU MENGJIONG CUI YUEJUN GUI YONGFENG GUO JIANGTAO LIN XUEFENG TU ZHENGGUANG YANG XIN ZHOU ZHENG LI GUANGLEI MENG BIN LIU LIHONG CHEN KEWEN","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","F42B15/01","","CN20161939916","20161101","CN20161939916 20161101","","","","","","","","","","","","","",""
Aircraft rudder system three-dimensional load performance testing device and test method thereof,"CN106564616 (A)","2017-04-19","GUO HUIRONG ZHANG ZHENGYI DENG ZHIJUN CHU CHENGBIAO HU SHANGANG DUAN XIANGJUN FAN KAICHUN","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","B64F5/60","","CN20161947869","20161026","CN20161947869 20161026","","","","","","","","","","","","","",""

Mounting structure for aircraft built-in type engine and shifting assembly method for mounting structure,"CN106564605 (A)","2017-04-19","ZHANG ZHENGYI LIU QING HU SHANGANG WANG HUI FAN KAICHUN","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","B64D27/26 B64F5/10","","CN20161951439","20161026","CN20161951439 20161026","","","","","","","","","","","","","",""

Azimuth measurement method based on distance measurement principle,"CN106569222 (A)","2017-04-19","XU WEIGUO MA XINPU QIN CHUN SONG CHANGZHE CHEN XINGFU HAN MINGJING ZHANG HONG","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","G01S17/42","","CN20161935503","20161101","CN20161935503 20161101","","","","","","","","","","","","","",""

Integral proportional guidance nonlinear correction method,"CN106556287 (A)","2017-04-05","YAN QINTAO YUE XINGZUO WU LEI JIANG JINLONG YANG DENGFENG CHEN XINGFU CUI YUEJUN XIA FEI TIAN QUNFANG ZHU WEI ZHU ZHENGHUI","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","F41G3/00","","CN20161944823","20161102","CN20161944823 20161102","","","","","","","","","","","","","",""

Thermal protection device for hypersonic gliding aircraft,"CN106547965 (A)","2017-03-29","SHAN HUAWEI WANG HUI HU CHENGLAN LU DI LIU LIHONG LIN XUEFENG TU ZHENGGUANG QIN JIANFEI SHU MENGJIONG","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","G06F17/50","","CN20161929527","20161031","CN20161929527 20161031","","","","","","","","","","","","","",""

Low-altitude hood casting device for high-speed unmanned aerial vehicle,"CN106516077 (A)","2017-03-22","ZHANG ZHENGYI WANG WENLONG XU GUOWEI QIN YOUHUA BAO YONGDING ZHAI HAITAO","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","B64C1/14","","CN20161897912","20161014","CN20161897912 20161014","","","","","","","","","","","","","",""

Single-soldier rapid rocket battle field testing method and system based on network communication,"CN106524838 (A)","2017-03-22","LIU QIHANG LI XIAODAN GAN LIN HUA QING YU GUISHENG XIAO YIN WANG DENG","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","F42B35/02","","CN20161901770","20161014","CN20161901770 20161014","","","","","","","","","","","","","",""

Demodulation method for incoherent spread spectrum communication system,"CN106506037 (A)","2017-03-15","LI RAN PENG KEXUE WANG DONG FU TAO LI ZHI ZHANG JING WANG JIE","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","H04B1/707 H04B1/708 H04L27/233","","CN20161939433","20161025","CN20161939433 20161025","","","","","","","","","","","","","",""

Locking device for large-tonnage carrier,"CN106494642 (A)","2017-03-15","ZHU SHUFENG LI MINGBING LI XIUZHEN ZHANG KUN LI FANG","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","B64G1/16","","CN20161905952","20161018","CN20161905952 20161018","","","","","","","","","","","","","",""

Four-core flight control computer based on dual-SoC architecture SiP modules,"CN106527261 (A)","2017-03-22","CHEN MINGXIN ZHENG YU LI BING HUANG XIAOMING CHEN JIALIN DING BO SONG CHANGZHE WU XIANG HAN MINGJING WANG HUAN","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","G05B19/042","","CN20161947821","20161026","CN20161947821 20161026","","","","","","","","","","","","","",""

Separation, connection and locking device for launching vehicle and launching pad,"CN106468522 (A)","2017-03-01","ZHU SHUFENG LI MINGBING LI XIUZHEN ZHANG ALING","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","F41F1/00 B60R11/00","","CN20161834292","20160913","CN20161834292 20160913","","","","","","","","","","","","","",""

Vehicle heat preservation layer and manufacturing method thereof,"CN106428644 (A)","2017-02-22","WANG YANGJIAN XU GUOWEI FENG KAI GUO HUIRONG CHEN WEI","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","B64G1/58","","CN20161887243","20160928","CN20161887243 20160928","","","","","","","","","","","","","",""

Shear-stress-resisting flange butt joint device,"CN106438602 (A)","2017-02-22","ZHANG XIAOBO LI XIUZHEN LI MINGBING FAN ZHIYONG ZHOU XINHONG XU CHENGLONG","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","F16B1/02","","CN20161887315","20160928","CN20161887315 20160928","","","","","","","","","","","","","",""

Compound attitude control method of grid rudder and lateral jet,"CN106444807 (A)","2017-02-22","GUO YIJIANG YAO SHAOJUN LI YAN JIANG JINLONG WANG ZHIJUN TIAN QUNFANG BAO XIAOQIANG ZHU WEI YANG DENGFENG CHEN XINGFU SU MAO","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","G05D1/08","","CN20161864293","20160929","CN20161864293 20160929","","","","","","","","","","","","","",""

Gas detecting device,"CN106442354 (A)","2017-02-22","WANG YULEI WANG HUIHUA XU WEICAI HU HAILI YAN LISONG YANG XIAOWEI LAN SHUO LI MENGQING","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","G01N21/31 G01N21/03","","CN20161863505","20160929","CN20161863505 20160929","","","","","","","","","","","","","",""

High-temperature-resisting flexible quartz fiber sealing ring,"CN106439019 (A)","2017-02-22","WANG HUI ZHANG ZHENGYI HU SHANGANG FAN KAICHUN","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","F16J15/10","","CN20161850923","20160926","CN20161850923 20160926","","","","","","","","","","","","","",""

Satellite and rocket separation system,"CN106428645 (A)","2017-02-22","LIANG JIQIU XIANG BIN HU CHANGWEI PENG WEI HU SHI HUANG LEI XIAO RENQIN WEN XIAONI HAN TONG WU JIHUA","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","B64G1/64","","CN20161754292","20160829","CN20161754292 20160829","","","","","","","","","","","","","",""

Self-locked folding grid rudder integrating positioning and bearing,"CN106197172 (A)","2016-12-07","WU JINGFENG WANG BOZHE FAN KAICHUN LIANG JIQIU CHU CHENGBIAO BAO YONGDING XIN AO","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","F42B15/00","","CN20161817188","20160908","CN20161817188 20160908","","","","","","","","","","","","","",""

Aircraft head heat container with repeatable disassembly and assembly,"CN106394937 (A)","2017-02-15","GAO HAO LI MINGBING LI XIUZHEN ZHU SHUFENG","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","B64G1/52","","CN20161834566","20160920","CN20161834566 20160920","","","","","","","","","","","","","",""

High-Mach number long-endurance aircraft surface sensor mounting device,"CN106379547 (A)","2017-02-08","WANG HUI WANG WENLONG FAN KAICHUN SHAN HUAWEI LU DI DAI ZHAOPENG ZHU XUAN XIAO HANSHAN","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","B64D47/00","","CN20161863465","20160929","CN20161863465 20160929","","","","","","","","","","","","","",""

Sectional semitrailer,"CN106379431 (A)","2017-02-08","ZHANG XIAOBO LI XIUZHEN LI MINGBING CHEN PING ZHOU XINHONG ZHU SHUFENG","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","B62D53/06 B60B35/00 B60B35/12 B60G17/00 B60S9/04 B60S9/10 B62D53/08","","CN20161887103","20160928","CN20161887103 20160928","","","","","","","","","","","","","",""

Aircraft nonlinear attitude control system stability analysis method,"CN106383523 (A)","2017-02-08","BAO XIAOQIANG ZHU WEI CHEN XINGFU CHEN HONGYAN YANG DENGFENG TIAN QUNFANG JIANG JINLONG GUO YIJIANG LI YAN CUI YUEJUN YE CHANG","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","G05D1/08","","CN20161874908","20160930","CN20161874908 20160930","","","","","","","","","","","","","",""

Transition navigation method applicable to airborne launching of missile,"CN106379559 (A)","2017-02-08","LIU JIANXIONG XIA FEI XU FANGJIA WANG ZHIJUN YAO SHAOJUN JIANG JINLONG SONG CHANGZHE LI HAN HUANG XINXIN CHEN XINGFU XU GUOWEI","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","B64G1/24 F42B15/01","","CN20161864500","20160929","CN20161864500 20160929","","","","","","","","","","","","","",""

Isolation type electric push rod control method and device with in-place feedback function,"CN106354040 (A)","2017-01-25","ZHENG ZHIWEI CAI CHUNMEI SUN BINGGANG CHEN YAO HE DONG CHEN ZHE HE QINNAN LEI YONGJIE ZHANG YANPING","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","G05B19/04","","CN20161905882","20161018","CN20161905882 20161018","","","","","","","","","","","","","",""

Folding fin automatic and synchronous unlocking driving device,"CN106352746 (A)","2017-01-25","XU CHENGLONG CHEN PING DING WEI YANG HUI LI XIUZHEN ZHANG XIAOBO","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","F42B10/02","","CN20161906020","20161018","CN20161906020 20161018","","","","","","","","","","","","","",""

Heat protection and diversion integrated device of attitude control nozzle in high-Mach environment,"CN106347637 (A)","2017-01-25","LU DI WANG HUI SHAN HUAWEI DAI ZHAOPENG WANG WENLONG FAN KAICHUN","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","B64C15/02 B64D33/04","","CN20161864195","20160929","CN20161864195 20160929","","","","","","","","","","","","","",""

Starting monitoring device and method for torque extraction generator,"CN106357179 (A)","2017-01-25","LI GANG CHEN ZHE WANG WENJUN HUANG JUYING","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","H02P9/08 H02P101/45","","CN20161817218","20160908","CN20161817218 20160908","","","","","","","","","","","","","",""

Space-based Internet-of-Things system structure and networking method thereof,"CN106357321 (A)","2017-01-25","YAN HAIPING XIANG BIN LIANG JIQIU WANG XINGYOU CHI XIANBIN SUN SHUPENG WU XIAOMENG DUAN XIAO YAN YEHUI","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","H04B7/185 H04L29/08 H04W4/00","","CN20161817127","20160908","CN20161817127 20160908","","","","","","","","","","","","","",""

Fiber laser asymmetric compensation spectral synthesizing device,"CN106338836 (A)","2017-01-18","LIU HOUKANG DING SHULIN ZHAO PENGFEI LYU LIANG WU CHUNFENG JIANG YONGLIANG LI QIANG","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","G02B27/10","","CN20161933072","20161025","CN20161933072 20161025","","","","","","","","","","","","","",""

Angle deviation calibration method between two interferometer emergence plane wave light beams,"CN106338261 (A)","2017-01-18","YAN LISONG WANG HUIHUA LI QIANG CHEN XIAOCHEN SHI YAOTAO JIANG YONGLIANG XU WEICAI WANG YULEI HU HAILI","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","G01B11/26","","CN20161820673","20160913","CN20161820673 20160913","","","","","","","","","","","","","",""

Object tracking control system,"CN106338808 (A)","2017-01-18","XU YANGANG TUO WENBO LEI YANG SONG LEI WU YILING ZHANG GUIQING","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","G02B7/182 G05D1/12","","CN20161902481","20161017","CN20161902481 20161017","","","","","","","","","","","","","",""

End cap heat resistance connecting device,"CN106314758 (A)","2017-01-11","DAI ZHAOPENG WANG HUI WANG WENLONG FAN KAICHUN ZHU XUAN LIU QING OU CHAO","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","B64C1/40","","CN20161863502","20160929","CN20161863502 20160929","","","","","","","","","","","","","",""

Universal controller of spaceflight carrier rocket,"CN106325292 (A)","2017-01-11","DAN CHUNHUA DING BO SONG CHANGZHE TAO JIN DU PENG XIE YANG ZHANG HONGQIAN CHEN MINGXIN WU XIANG ZHENG YU","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","G05D1/08 G05D1/10","","CN20161899957","20161017","CN20161899957 20161017","","","","","","","","","","","","","",""

Method and system for determining airborne load of missile distribution,"CN106326664 (A)","2017-01-11","SUN MEIFENG ZHANG YIGUANG JIA XIANGTING RAN HONG CHAO KAIXIU CHEN KEWEN","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","G06F19/00","","CN20161769626","20160830","CN20161769626 20160830","","","","","","","","","","","","","",""

Underwater unmanned platform aircraft autonomous test launch and control system,"CN106292644 (A)","2017-01-04","LONG YAOSONG XI MAOJUN WANG ZHONGLING WANG ZHUO YAO SHAOJUN JIANG JINLONG SONG CHANGZHE DING BO LI BING ZHANG KUI LU HONGHAI","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","G05B23/02","","CN20161866277","20160929","CN20161866277 20160929","","","","","","","","","","","","","",""

Rapid analysis and optimization method for vibration response characteristic of carrier rocket cabin,"CN106295074 (A)","2017-01-04","CAO PENG FU MIGUO LIANG JIQIU LIU XIAOLEI SHU MENGJIONG ZHAO TAO FENG NANPENG ZHAO QUAN ZHOU LYU CHEN ZHIGUO","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","G06F17/50","","CN20161764335","20160830","CN20161764335 20160830","","","","","","","","","","","","","",""

Flight test data recording device and method for recording and reading test data,"CN106296872 (A)","2017-01-04","FU TAO QI SHIBING WANG XIAOLIN WANG YUFEI WANG DENG WANG DONG","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","G07C5/08 G06F3/06","","CN20161638321","20160805","CN20161638321 20160805","","","","","","","","","","","","","",""

Object type and position state recognition method,"CN106289335 (A)","2017-01-04","LI GANG CHEN YAO HE QINNAN ZHENG WEI","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","G01D5/249","","CN20161569649","20160719","CN20161569649 20160719","","","","","","","","","","","","","",""

Border area coolant flow adjusting device for injector,"CN106246412 (A)","2016-12-21","HUANG FENG WANG TAOFENG LIANG JIQIU WANG XIAOYU ZHANG FANG LIU ZHANGLONG ZHOU LEI LIU YANG CHEN ZE CHEN WEI YANG YI YU QUAN CHEN WENJIE","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","F02K9/64","","CN20161866526","20160929","CN20161866526 20160929","US4739613 (A) US6324832 (B1) CN105736181 (A) CN105888883 (A)","","","","","","","","","","","","",""

Horizontal wing inner wall temperature sensor installation device and method,"CN106248234 (A)","2016-12-21","LU DI WANG HUI DAI ZHAOPENG SHAN HUAWEI WANG WENLONG FAN KAICHUN","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","G01K1/14","","CN20161863504","20160929","CN20161863504 20160929","","","","","","","","","","","","","",""

Launching stand with lifting deflector,"CN106247855 (A)","2016-12-21","XU CHENGLONG YANG HUI LI MINGBING LI FANG","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","F41F3/04 F16C35/00","","CN20161834232","20160913","CN20161834232 20160913","","","","","","","","","","","","","",""

Large-aperture plane mirror splicing detection alignment method,"CN106248352 (A)","2016-12-21","YAN LISONG LI QIANG WANG HUIHUA CHEN XIAOCHEN SHI YAOTAO JIANG YONGLIANG XU WEICAI WANG YULEI YANG ZIWEI","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","G01M11/02","","CN20161820991","20160913","CN20161820991 20160913","","","","","","","","","","","","","",""

Method for controlling rolling time domain of flight orbit of spacecraft,"CN106114910 (A)","2016-11-16","CHI XIANBIN LIANG JIQIU HU ZHANGWEI SUN SHUPENG YAN YEHUI YE CHANG ZHANG JIANPENG DUAN XIAO WU XIAOMENG WANG KUN","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","B64G1/24","","CN20161442832","20160615","CN20161442832 20160615","","","","","","","","","","","","","",""

Inertial navigation standard prism misalignment angle self adaptive measuring method based on linear array type CCD (charge coupled device),"CN106153075 (A)","2016-11-23","LI CHUNQUAN ZHOU HAI WANG YONG ZHANG LI","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","G01C25/00","","CN20161673251","20160811","CN20161673251 20160811","","","","","","","","","","","","","",""

Supplement type two-cylinder synchronous hydraulic control method and system thereof,"CN106122140 (A)","2016-11-16","WANG WENJUN LI XIUZHEN LEI JIANHONG CHEN YIHONG CHEN PING","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","F15B11/22 F15B21/02","","CN20161820672","20160913","CN20161820672 20160913","","","","","","","","","","","","","",""

Combined throat liner spraying pipe of solid rocket engine and manufacturing method,"CN106050477 (A)","2016-10-26","XU YURONG ZHONG ZHIWEN ZHOU SHENGPAN XU JIERONG YU QUAN CHEN WENJIE SI XUELONG","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","F02K9/97","","CN20161623732","20160728","CN20161623732 20160728","","","","","","","","","","","","","",""

High-speed vehicle insulating layer and installation method thereof,"CN106005485 (A)","2016-10-12","XU GUOWEI FAN KAICHUN LIU QING HU SHANGANG","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","B64G1/58","","CN20161492898","20160628","CN20161492898 20160628","","","","","","","","","","","","","",""

Integrated airborne optical pod test system,"CN106017862 (A)","2016-10-12","YU XIANG YANG KAIXIN ZHONG HUA WU FENGYANG CHEN LIFENG ZHOU SHIPING","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","G01M11/00","","CN20161303282","20160510","CN20161303282 20160510","","","","","","","","","","","","","",""

Flexible connection device for high-temperature resistant radome,"CN105914463 (A)","2016-08-31","XU GUOWEI WANG YANGJIAN CHEN WEI SANG XIJUN QIN YOUHUA","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","H01Q1/42 H01Q1/12 H01Q1/28","","CN20161488553","20160628","CN20161488553 20160628","","","","","","","","","","","","","",""

Sun-pointing control system for satellite and control method of sun-pointing control system,"CN105905317 (A)","2016-08-31","YAN YEHUI LIANG JIQIU HU CHANGWEI SUN SHUPENG CHI XIANBIN GUO YIJIANG WU XIAOMENG DUAN XIAO ZHANG JIANPENG WANG KUN","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","B64G1/24","","CN20161414531","20160607","CN20161414531 20160607","","","","","","","","","","","","","",""

Calibration method of inertial unit optical aiming prism installation error,"CN105910624 (A)","2016-08-31","SHEN XIAOLONG LIU MING WANG ANDI HU HUAFENG YANG DAOAN","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","G01C25/00 G01C1/06","","CN20161302867","20160504","CN20161302867 20160504","","","","","","","","","","","","","",""

Serial inertial navigation system having self-calibrating, self-aligning and self-diagnosing functions,"CN105865486 (A)","2016-08-17","LIU YUANYUAN YU QIANG HU QIBO LIU JUNQING REN YONGFANG GAO BO YANG XIN ZHENG YONGQIANG LYU JIANGTAO LIU MING LUO WEI HU HUAFENG DAI SHILONG","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","G01C25/00","","CN20161181486","20160328","CN20161181486 20160328","","","","","","","","","","","","","",""

General advanced upper stage of solid launch vehicle,"CN105841556 (B) CN105841556 (A)","2016-08-10","LIANG JIQIU HU CHANGWEI SUN SHUPENG XIE YANG XIAO RENQIN GAN LIN WU XIAOMENG YAN YEHUI CHI XIANBIN WANG KUN DUAN XIAO DING BO WANG YUFEI SONG CHANGZHE WANG BOZHE YAN HAIPING","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","F42B15/00 F42B15/01 G05D1/08","","CN20161102622","20160225","CN20161102622 20160225","US4798141 (A) US7687025 (B2) CN102530267 (A) US2012227374 (A1) CN102717900 (A) CN104675562 (A) CN105099504 (A) CN105370440 (A)","","","","","","","","","","","","",""

Near space satellite launching platform and method,"CN105819002 (A)","2016-08-03","CAO HONGWEI FAN KAICHUN DUAN XIANGJUN RAO TIANLIANG FANG WANGLIN HAO LINGYUN ZHANG MEINING","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","B64G1/00","","CN20161226663","20160408","CN20161226663 20160408","","","","","","","","","","","","","",""

Image correction method and system of navigation height errors,"CN105825517 (A)","2016-08-03","WANG CHUNLIAN JIN MIN CHEN SHUTAO XIE XIAOMIN SHEN ZHI","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","G06T7/00 G01C25/00 G06K9/46 G06K9/62","","CN20161195049","20160331","CN20161195049 20160331","","","","","","","","","","","","","",""

Single-power-source single-point-locking three-stage synchronous unfolding device,"CN105644811 (A)","2016-06-08","LI YUNFENG FAN KAICHUN MA WEI WU YONG CHENG CHANG ZHANG ZHOUZHOU CHEN QINGWEI","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","B64G1/64","","CN20161185733","20160329","CN20161185733 20160329","JPH02160494 (A) US5040748 (A) JPH0763245 (A) CN102102701 (A) CN103625656 (A)","","","","","","","","","","","","",""

Multifunctional platform device used for parking, overturning and transferring of aircraft cabin,"CN105644806 (A)","2016-06-08","DAI ZHAOPENG WANG BOZHE BAO YONGDING XIN AO FAN KAICHUN YANG PAN","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","B64F5/00","","CN2016104582","20160106","CN2016104582 20160106","US2008011932 (A1) EP2221151 (A2) US2012228839 (A1) CN203365162U (U) CN104097789 (A)","","","","","","","","","","","","",""

Heterogeneous optical scene matching target template based performance assessment system and method,"CN105740913 (A)","2016-07-06","ZHONG HUA CUI JUN WANG PINXI LI JIAO CHEN SHUTAO JIN MIN GUO CHENYU YANG KAIXIN CHEN JIE WU FENGYANG","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","G06K9/62","","CN20161101879","20160225","CN20161101879 20160225","","","","","","","","","","","","","",""

Missile warhead,"CN105509576 (A)","2016-04-20","CAO HONGWEI RAO TIANLIANG FANG WANGLIN","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","F42B15/00 F42B15/01","","CN20151821161","20151119","CN20151821161 20151119","DE202004010194U (U1) GB2430994 (A) JP4462735B (B2) US8084724 (B1) EP1714105 (B1)","","","","","","","","","","","","",""

Method for measuring installation errors of star sensor and strapdown inertial measurement unit of aircraft,"CN105424060 (A)","2016-03-23","WANG YAJUN ZHOU HAI LI CHUNQUAN WANG YONG LU ZHUANGZHI","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","G01C25/00","","CN20151794566","20151118","CN20151794566 20151118","","","","","","","","","","","","","",""

Optical fiber inertia measurement combined device,"CN105424039 (A)","2016-03-23","GAO BO HU ZHENLIN LU JUNQING LIU YUANYUAN LYU JIANGTAO YUAN HUIZHENG YANG YUANXIA WANG ANDI DAI SHILONG","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","G01C21/16 G01C25/00","","CN2016105780","20160106","CN2016105780 20160106","","","","","","","","","","","","","",""

Multi-degree-of-freedom stage-separation test device and test method,"CN105416617 (B) CN105416617 (A)","2016-03-23","LIANG JIQIU CHEN BO LIU XIAOLEI XIANG BIN HU CHANGWEI HUANG LEI WANG BOZHE PENG WEI WU JIHUA HU SHI CHEN XU","THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD","B64G7/00","","CN20151777730","20151114","CN20151777730 20151114","JPH0664598 (A) RU2385445 (C1) CN102050230 (A)","","","","","","","","","","","","",""

 

[antigravite]

... I miss Aotian project related news.

Hmmm...

A.

 

[antigravite]

High-temperature heat-proof cover structure
Patent CN110723275 (A)
Issued: 2020-01-24
Inventor(s): WANG HUI; HU SHANGANG; CHEN XINGFENG; YANG PAN; MA ZHI
Applicant(s): GENERAL DESIGNING INST HUBEI SPACE TECH ACADEMY
Application number: CN20191119619 20191024
Priority number(s): CN20191119619 20191024
Abstract: The invention discloses a high-temperature heat-proof cover structure, and belongs to the technical field of aircraft thermal protection. The structure comprises a bearing layer, a heat-proof layer, aheat-proof cover and a heat-proof screw assembly, wherein the heat-proof layer is positioned on the outer surface of the bearing layer, and an opening is formed in the heat-proof layer; the heat-proof cover is positioned in the opening of the heat-proof layer and used for blocking the opening of the heat-proof layer, and an installation hole connected with the heat-proof layer is formed in the heat-proof cover; the heat-proof screw assembly penetrates through the installation hole of the heat-proof cover and is fixedly connected with the heat-proof layer. According to the invention, the heat-proof screw assembly for fixing the heat-proof cover is connected between the heat-proof cover and the heat-proof layer without being connected with the bearing layer, so when tangential displacementis generated between the heat-proof layer and the bearing layer due to thermal matching, the heat-proof cover moves synchronously with the heat-proof layer without causing thermal matching problem, sothe difficult problem of thermal matching generated when the conventional heat-proof cover and the bearing layer are connected integrally is effectively avoided, and the structural damage generated when the heat-proof cover is connected with a bearing structure is prevented.

- - - - - - - - - - -

Method for designing quasi-gliding trajectory based on landing angular velocity constraint
Patent CN110717245 (A)
Issued: 2020-01-21
Inventor(s): LUO QINQIN; CHEN SHIFU; ZHAO TAO; PAN FEI
Applicant(s): GENERAL DESIGNING INST HUBEI SPACE TECH ACADEMY
Application number: CN201910827980 20190903
Priority number(s): CN201910827980 20190903
Abstract: The invention discloses a method for designing a quasi-gliding trajectory based on landing angular velocity constraint, which comprises the following steps of: constructing a simulation model to forma quasi-gliding trajectory with a climbing stage, a maneuvering guidance stage and an aiming stage; initializing design parameters of the aircraft model; after the aircraft model simulates flight on the quasi-gliding trajectory according to the initialized design parameters and preset control conditions, the actual landing speed, obtaining the actual firing range and the trajectory of the quasi-gliding trajectory of the aircraft model; judging whether the actual falling speed, the actual firing range and the form of the trajectory formed in the maneuvering guidance stage meet preset conditionsor not, and if so, determining that the corresponding design parameters meet expectation; if not, correspondingly updating the design parameters, and enabling the aircraft model to simulate flight again on the simulated gliding trajectory according to the updated design parameters until all the design parameters meet the expectation; and outputting the design parameters updated last time to finish the design of the simulated gliding trajectory.

A.

 

[antigravite]

Hi there. Important news today which might be related to the Aotian project.

As it seems, PRC launched today (Friday September 4th, 2020) from its Jiuquan Satellite Launch Center (site 901), sometime around 05:20 UTC (nighttime), its first space-rated, secretive, experimental reusable space vehicle. While often described as a spaceplane on various forums — in which case it might be considered as China's response to the US X37B — this remains to be seen.

Its launch carrier rocket was a Long March CZ-2F, also known as 'Shenjian' (translated as 'Divine Arrow') since it was renamed by CPC General Secretary and President Jiang Zemin in 1993. So, to the very best of my understanding, the secret experimental reusable space vehicle shall not be (mis)identified nor confused with nor designated as 'Shenjian'.

This spacecraft is sometimes identified as project "500 000". Dont be fooled. This figure is not a codename and by no means anything official. In today's Chinese popular culture, 500k projets refer to the (financial) award one would get, by exposing any foreign espionnage operation / attempt / plot against any secret military systems. By extent, the "500 000" designator naturally came to identify any secret military project.

To this day, i.e. a few hours after launch, no evidence supports that this vehicle is a military project, even if its dual use would be more than likely.

The official press release is tightlipped:

China launches reusable experimental spacecraft - Xinhua | English.news.cn

Of course, this post will be updated when we get new info.

A.

 

[sferrin]

They copy everything else, why not the X-37? They've probably downloaded the entire data package.

 

[Flyaway]

They copy everything else, why not the X-37? They've probably downloaded the entire data package.

See the articles I’ve posted links to in the Chinese Space Program thread.

 

[antigravite]

Hi.
Does anybody have a higher res of this image?
That might be quite of interest...

A.

 

[antigravite]

Hi.
This other image with a chinese spaceplane, might be some older study presentation.
I have no info on the image source.
So, as alway, if you come across anything related to that, feel free to comment and contextualize.

A.

 

[dark sidius]

Hi.
Does anybody have a higher res of this image?
That might be quite of interest...

A.

X-37 b copy cat

 

[cattalonX]

AT-1B？？

 

[cattalonX]

 

[antigravite]

X-37 b copy cat

Maybe. Maybe not.

A.

 

[antigravite]

Hi there.

Yesterday, Philippe Coué, one of the best Chinese space program watchers – he's been tracking the manned space program since the early 1980s — published what he claims to be the very first illustration (3D rendering) of PRC's reusable satellite originating from CSSHQ— the so-called "X37B copycat". His linkedn post is worth reading and automatically translates as follows: "CSSHQ - According to a conference given in May in Hong Kong, the Chinese spaceplane that is currently in orbit would be thermally protected during atmospheric re-entry by 1285 tiles made of Ulfica, a material stronger than the PicaX used by SpaceX's Dragon capsules. During the second flight, 286 CSSHQ tiles were slightly damaged. The illustration shows, for the first time, what the Chinese CSSHQ spaceplane really looks like."

Enjoy.

A.

 

[antigravite]

Hi.

Not quite sure this has ever been posted here but definitely worth it. An orbital picture of the X37B (or its chinese counterpart as rumors currently spread) taken by Maxar.

The source image seems to come from this linkedin post on the occasion of the "Space forum in National assembly" held in South Korea in november 2024:

Kyungsub Kim on LinkedIn: Space forum in National assembly

Space forum in National assembly

www.linkedin.com

To be more specific, the slide was shot during Col. John "JP" Patrick's lecture on "US Space Forces Korea"

Enjoy.

A.

 

[dark sidius]

It look different than the X-37 B no same wing shape not the same nose shape ....

 

[antigravite]

It look different than the X-37 B no same wing shape not the same nose shape ....

Thx. Here's the close-up. Your comment explains why a rumor associates this picture with the chinese equivalent of X37B. What matters is the context where this image appeared (so I passed it on, to make sure everyone had the source).

A.

 

[dark sidius]

Thx. Here's the close-up. Your comment explains why a rumor associates this picture with the chinese equivalent of X37B. What matters is the context where this image appeared (so I passed it on, to make sure everyone had the source).

A.

It look more elongated than the X-37 B

 

[archipeppe]

In the image we see notable differences from such "object" and the X-37B (as we know it):

1. The fusalage is different, this one is more squared and little longer. No rear side enlargements (like the X-37B).
2. Nose shape is different.
3. Wing shape is different. The wing design is more "chubby".
4. The service module is different. This apperars to be a truncated cone rather than the cylinder one for the X-37B.
5. This one has two solar wings while the X-37B has only one folded into the cargo bay.

The question is: why the USSF has used such image to represent a X-37B asset?
It was unintentional?
Who knows....