45results about How to "Improve engineering realizability" patented technology

A high-orbit optical remote sensor vacuum hot test external heat flow simulation method comprises the steps of firstly determining solar radiation heat flow according to on-orbit solar absorptance of an optical remote sensor (3), secondarily arranging the optical remote sensor (3) in a vacuum environment simulation chamber (1), then determining a 'sun outage' time period by judging whether the solar radiation heat flow Q1 (t) absorbed by an optical system within a orbit period is 0 or not, determining the time period of the Q1 (t) unequal to 0 as the 'sun outage' time period, adopting a solar simulator (2) and electric heater combined simulation scheme to perform outer heat flow simulation, determining that the time period of the Q1 (t) equal to 0 is a 'non-sun outage' time period, and adopting an independent electric heater simulation scheme to perform outer heat flow simulation. The problem that an existing non-contact space optical remote sensor outer heat flow simulation method does not have a solar spectral energy spectrum characteristic and directionality is solved, energy distribution of solar spectrum of the remote sensor on orbit can be accurately simulated, simulation accuracy is high, and project realization is promoted.

The invention provides an underwater array scanning laser imaging device, said device comprising: a carrier (1), an electrical module (19) and an imaging module (18); said carrier (1) is the shell of the whole device, The electrical module (19) includes an illumination laser (15), a combined inertial navigation (16) and a control processing unit (17); each component of the electrical module (19) is fixed on both sides of the mounting plate (22), and is installed The plate (22) is fixed to the carrier (1); the imaging module (18) includes a pitch servo mechanism (5), a roll servo mechanism (6) and an optical imaging module (14), and the optical imaging module (14) comprises imaging lens (7), optical filter (8), gate imaging sensor (9) and illumination lens (10); The laser light that described illumination laser (15) emits is transmitted to Lighting lenses (10). The device of the invention has the characteristics of miniaturization and the ability to realize area array scanning under water.

The invention discloses a driven energy absorbing pulling / pressing both-way buffer capable of being repeatedly used, and belongs to the technical field of spaceflight equipment. The device is mainly composed of four parts including an outer barrel assembly, a middle barrel assembly, an inner barrel assembly and a pull barrel assembly, wherein the middle barrel assembly is coaxially arranged in theouter barrel assembly, the inner barrel assembly is coaxially arranged in the middle barrel assembly, and the pull barrel assembly is coaxially arranged on the periphery of the connecting position ofthe outer barrel assembly and the middle barrel assembly. According to the device, through an innovatively-designed aluminum honeycomb resetting mechanism, a mechanical spring resetting device and aratchet one-way locking device are combined with the pulling / pressing both-way buffer based on aluminum honeycomb crushing energy absorbing materials, and the advantages that a traditional driven energy absorbing both-way buffer is simple in structure, small in mass and high in reliability are sufficiently inherited; and the traditional pulling / pressing both-way buffer can be repeatedly used and can be used for repeatedly-used soft landing devices needed for multi-target deep space exploration tasks in future.

The invention discloses a satellite-borne terahertz ice cloud nadir detector system, which comprises an antenna and scanning subsystem, a multi-frequency-band terahertz receiving channel, a calibration subsystem, a data collecting and processing platform, a control power distribution system and control and signal processing equipment, wherein the antenna and scanning subsystem, the multi-frequency-band terahertz receiving channel, the calibration subsystem, the data collecting and processing platform and the control power distribution system are installed on a detection head part; the controland signal processing equipment is installed on a satellite platform; and the detection head part carries out conical scanning, and observation for a target, observation for a thermal calibration source body and observation for cold air are successively finished in a scanning process so as to realize the scanning imaging of ice cloud and the in-orbit two-point calibration of a detector. A receiving front end design scheme of an offset paraboloid reflector and a quasi-optics feed network is adopted, and conical scanning is carried out through a rotary antenna feeder system to realize the nadirobservation of ice water particles in cloud.